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  • Inorganic Chemistry  (5,276)
  • Aircraft Stability and Control
  • Limnology
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  • 1
    Publication Date: 2019-07-20
    Description: These slides describe a method and technology of modeling flexible aircraft for active control of structural dynamics. Objective: Generate models useful for the design and evaluation of control laws for active structural control and flutter suppression that are able to accurately predict body freedom flutter.
    Keywords: Aircraft Stability and Control
    Type: AFRC-E-DAA-TN66921 , Aerospace Control and Guidance Systems Committee (ACGSC) Meeting; Mar 27, 2019 - Mar 29, 2019; Santa Fe, NM; United States
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  • 2
    Publication Date: 2019-07-20
    Description: A multi-objective optimal control technique is modified to accommodate changing cost function weights and is used to control a flexible wing aircraft model. Variation of the weights is used to adjust the relative importance of each objective according to either a prescribed function of time or of the state. Several techniques for obtaining a practical approximation to the optimal control solution are presented, and stability of a specific weight structure with the optimal controller is demonstrated. Functionality of the multi-objective control design with weight variation is demonstrated in simulation of a flexible wing transport aircraft and is shown to improve performance over the fixed weight version both at a constant flight condition and across changing flight conditions.
    Keywords: Aircraft Stability and Control
    Type: ARC-E-DAA-TN64647 , AIAA SciTech Forum 2019; Jan 07, 2019 - Jan 11, 2019; San Diego, CA; United States
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  • 3
    Publication Date: 2019-07-20
    Description: A new 6-DoF aeroservoelastic (ASE) Common Research Model (CRM) provided by The Boeing Company with aspect ratio 13.5 and 17 control surfaces per wing is utilized to demonstrate combined tracking and optimal multi-objective control. The multi-objective controller is derived on the closed loop tracking controller, and utilizes state and gust estimates provided by an extended state observer. Various methods of model reduction useful for control and estimation are presented. A computationally efficient MATLAB/Simulink simulation is presented which includes actuator dynamics, rate and deflection saturation limits, and gust disturbance inputs. The platform is used to demonstrate excellent 6-DoF tracking control performance coupled with the multi-objective controller, which is shown to effectively reduce structural mode movement, wing root bending moment, and drag. State and gust estimation is also shown to perform well, even when derived and/or implemented with significantly fewer states than the original full-sized model.
    Keywords: Aircraft Stability and Control
    Type: ARC-E-DAA-TN271828 , AIAA Science and Technology Forum and Exposition; Jan 07, 2019 - Jan 11, 2019; San Diego, CA; United States
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  • 4
    Publication Date: 2019-07-20
    Description: Slides for an invited presentation (as part of a series) at Santa Clara University, invited by prof. Mohammad Ayoubi. The slides are an overview and summary of past and current research projects in the field of envelope protection, upset prevention and stall recovery guidance, with the aim to avoid loss of control accidents and improve safety in air transportation. The overall aim of this presentation series is to inspire students and to show them possible opportunities that they can pursue for their later careers paths.
    Keywords: Aircraft Stability and Control
    Type: ARC-E-DAA-TN52363 , Santa Clara University Invited Lecture Series; Santa Clara, CA; United States
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  • 5
    Publication Date: 2019-09-13
    Description: An extension of model reference adaptive control is presented that accommodates use of a time-varying reference model. Specifically, the reference model is taken to be a time-varying convex combination of two linear, time-invariant models. The design is intended to act as a way to smoothly transition between two different reference models without resorting to a scheduled switch. It also provides the ability to use an interpolated reference model when the plant is operating between design points. The time variation of the combination must satisfy some requirements to ensure stability but is otherwise user choice. Subject to these requirements, bounded tracking error behavior is demonstrated via Lyapunov stability analysis for the single-input, single-output, output feedback case. Tracking error convergence is asymptotic when time variation ceases. The proposed design is demonstrated in simulation of a numerical model.
    Keywords: Aircraft Stability and Control
    Type: ARC-E-DAA-TN66631 , American Control Conference; Jul 10, 2019 - Jul 12, 2019; Philadelphia, PA; United States
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  • 6
    Publication Date: 2019-10-30
    Description: No abstract available
    Keywords: Aircraft Stability and Control
    Type: AFRC-E-DAA-TN74004
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  • 7
    Publication Date: 2019-07-13
    Description: This paper verifies a motion cueing strategy for improved pilot stall recovery training in commercial transport simulators. Eight airline transport pilots flew a high-altitude stall recovery task in the NASA B747 level-D-certified full flight simulator under three different motion configurations: no motion, baseline motion, and enhanced motion. For each motion condition, pilots performed the task with both baseline aircraft dynamics and aircraft dynamics enhanced with lateral-directional characteristics of the airplane at angle of attack approaching stall. Motion configuration significantly affected: 1) pilot opinions on the helpfulness of motion in performing the task, 2) the maximum roll angle in the stall maneuver, 3) the minimum load factor in the recovery, 4) the number of secondary stick shakers in the stall recovery, and 5) the maximum airspeed in the recovery. The two different aircraft dynamics significantly affected: 1) pilot opinions on the noticeability of the banking roll off near the stall and 2) the maximum roll angle in the stall maneuver. These results indicate that the relatively minor enhancements to the motion logic of heritage commercial transport simulators presented here can significantly improve pilot performance in simulated stall recoveries, and potentially improve stall recovery training.
    Keywords: Aircraft Stability and Control
    Type: ARC-E-DAA-TN65276 , AIAA SciTech Forum 2019; Jan 07, 2019 - Jan 11, 2019; San Diego, CA; United States
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  • 8
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    In:  CASI
    Publication Date: 2019-07-13
    Description: An overview of the flight control work in the Intelligent Systems Division at NASA Ames is presented. The highlight focuses on efforts surrounding performance-adaptive aeroelastic wing shaping for aircraft with flexible wings. Topics covered include aeroservoelastic modeling capabilities, online drag-optimizing control designs, gust and maneuver load alleviation techniques, and related wind tunnel demonstrations.
    Keywords: Aircraft Stability and Control
    Type: ARC-E-DAA-TN67091 , Aerospace Control and Guidance Systems Committee Meeting; Mar 27, 2019 - Mar 29, 2019; Santa Fe, NM; United States
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  • 9
    Publication Date: 2019-07-13
    Description: No abstract available
    Keywords: Aircraft Stability and Control
    Type: JSC-E-DAA-TN69878-2 , AIAA AVIATION Forum and Exposition; Jun 17, 2019 - Jun 21, 2019; Dallas, TX; United States
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  • 10
    Publication Date: 2019-07-13
    Description: No abstract available
    Keywords: Aircraft Stability and Control
    Type: JSC-E-DAA-TN69878-1 , AIAA AVIATION Forum and Exposition; Jun 17, 2019 - Jun 21, 2019; Dallas, TX; United States
    Format: text
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  • 11
    Publication Date: 2021-05-19
    Description: Aquaculture activity is restricted mainly to rainbow trout in cold waters and carps in warm waters in inland waters of Iran as well as Fars Province. Probably for this reason saline waters of south and southeast Fars have not been used for aquaculture. These rivers are ecosystems with a diverse biota, it is predictable that can be found some there endemic aquatic organisms with a potential for aquaculture. Finding a suitable organism can help increase wise use of this natural resource, and local production and recruitment. However, it is highly needed to investigate various environmental elements prior to any use to obtain an estimation of the environmental consequences, parallel to finding usage potentials. In This study, we investigated Dehram saline river in south of Fars Province. Hydrological and physiographical properties, chemical composition of the river, and aquatic populations were sampled and measured monthly in 3 stations in one year. Salinity, electrical conductivity, and total dissolved solids increased from station 1 to 3, reaching from 6.6 g/L, 14.3 g/L, and 12800 µs/cm to 13.5 g/L, 17.7 g/L, and 16500 µs/cm, respectively. Dissolved oxygen and oxygen saturation were higher in station 3, and in autumn and winter. Nitrite showed lowest values in winter (0.006 mg/L) and highest values in spring (0.013 mg/L). Nitrate showed the lowest concentration in station 3 (0.43 mg/L), but no differences were seen among seasons. Ammonium showed no differences among stations or seasons. Phosphate levels in station 1 and 3 were 0.13 mg/L‌to 0.17 mg/L, with the highest level (0.29 mg/L) seen in the spring. Five species of fishes were identified in the river, which all were widely favored by local people. Some of these have been categorized as edible in previous studies, others as ornamental. On the other hand, intensive growth of an algal species throughout the river demonstrates a potential for algal cultivation. Significant role of algae in production of food for both man and livestock is now well recognized in aquaculture industry.
    Description: Iranian Fisheries Science Research Institute
    Description: Published
    Keywords: Ecology ; Dehram River ; Limnology ; Saline water ; Physico-chemical parameters ; Aquaculture
    Repository Name: AquaDocs
    Type: Report , Refereed
    Format: 62pp.
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  • 12
    Publication Date: 2021-05-19
    Description: Limnological factors of brackish water pounds of the rainbow trout, Onchorhynchus mykiss were studied at Bafgh region in Yazd province. Physicochemical factors, phytoplankton, zooplankton and benthic populations of pools, supply and drainage channels from different farms were studied in aquaculture cycle in 2002 and 2003. Means were compared using Tukey HSD and t tests. Meanings of factors in 2002 and 2003 were respectively: and 9.3 0.2ppt; dissolved oxygen 7.9 0.2mg/l water temperature 13.8 0.3°c and 14.9 0.6°c; salinity 12.3 0.2ppt and 7.2 0.1mg/l; pH between 7.8 to 9.2 and 8.1 to 9.5; depth of hyalinity 0.85 0.1m and 1.1 0.1m; ammonium 0.1-0.5mg/l; and nitrate 1.8-21mg/l. Main phytoplankton were diatoms specially Chaetoceros, and Cyanophyta. Rotifera were the dominant zooplankton. Benthic fauna mainly included immature Chironomids. Final mean lengths were between 24.7cm to 31.5cm, mean weights between 11179.9gr to 434.6gr. FCR between 1.16 to 1.6; DGR between 1.04gr/day to 3.03gr/day; production 0.03kg/m2 to 0.84 kg/m2. Supply channels had the optimum limnological condition for trout aquaculture. Limnological factors were often not significantly different between pools and drainage channels. Saeeid and Rangin-Kaman farms were the most successful farms.
    Description: Iranian Fisheries Science Research Institute
    Description: Published
    Keywords: Limnology ; Brackish water ; Onchorhynchus mykiss ; Rainbow trout ; Phytoplankton ; Zooplankton ; Chaetoceros ; Survey ; Pond culture
    Repository Name: AquaDocs
    Type: Report , Refereed
    Format: 175pp.
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  • 13
    Publication Date: 2021-05-19
    Description: Gahar-roud is in 18 kilometer far from Doroud city from East of lorestan province . This river orginated from internal part of Oshteran-kouh mountain altitude and Gahar-Lake . Survey on Gahar roud Limnology began from the end of 2001 year and during the 18 month achived, at first on the length of 20 kilometer five station of sampling was selected and biological, physical and chemical character of this river was surveyed this river in all path of it feeding with large and small spring, little rivers and water of icehouse. The amount water of this river is different and maximum water is about 21 m/s in April month. Specifity of this river is be enough the temperature of water for fish. Minimum in the Jan is about 3 centigrad deegree and maximum is July and Aug about 24 centigrade deegree phis between 6.5-8.2 and is few basic . solauble oxigen is enough and is between 8.5-13 mg/lit.during the year.This river is very bright and haven t the source of polution and during the path of river and be enaugh the dosage of mineral in water are the important physical and chemical character of this river. Gahar-roud is not biological hardness quality. About 31 genus and species from 5 family of phytoplangton and 42 genus from 26 family from the order of insects, molusca, worms and crustacea and 9 species from 12 family from the side aquatic. Plants was collected and recognized. Based on ecological potential of this region, because Gahar- roud river is poor for food material and classified in oligotroph river and hasn t high biological value. And also have a few population and in fact haven t any population and based on the safer system belong to the quatiy elass of oligotroph and amount of water, regular circulation of water with microclima condition rate of natural resource land around river, having program for culture of cold water fish is important but it is better that use from culture of fish, be regulated key word limnology, Gahar-roud, river plangton, bentoz, fish.
    Description: Iranian Fisheries Science Research Institute
    Description: Published
    Keywords: Limnology ; Fish ; Bentos ; Plankton
    Repository Name: AquaDocs
    Type: Report , Refereed
    Format: 84pp.
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  • 14
    Publication Date: 2021-05-19
    Description: Dorudzan reservoir is the main provider of drinking water for the capital Shiraz, as well as the most significant storage of water in the Kor river course. In addition of eroded material, a load of agricultural outputs from upstream are moved to the lake every year. Main physiographic, physical and chemical, and biological components of the lake were monthly sampled and analysed from Novembr 2010 to October 2011. Mean annual measures were water temperature 16.7 ˚C (SD=5.8), pH 8.2 (SD=0.3), dissolved oxygen 7.6 mg/l (SD=1.7), ammonium 0.05 mg/l (SD=0.08), nitrite 0.004 mg/l (SD=0.003), nitrate 0.44 mg/l (SD=0.44), phosphate 0.20 mg/l (SD=0.23), silicate 7.00 mg/l (SD=2.49), BOD 2.29 mg/l (SD=1.00), COD 24.49 mg/l (SD=15.47), electrical conductivity 720 µs/cm (SD=219), total dissolved solids 457.67 mg/l (SD=138.72), calcium hardness 61.30 mg/l (SD=13.45), and magnesium hardness 20.23 mg/l (SD=9.18). Living parts of the ecosystem including species of fish, orders and families of benthic invertebrates, zooplanktons, and phytoplanktons were investigated. Benthic macroinvertebrates included various nematodes, oligochates, gastropods, bivalves, and insect larvae (dipteral and coleptera), most abundant of which were dipteran larvae, mollusks, and nematodes. Dominant zooplankton was Bosmina, with Daphnia and Cyclops in next ranks. Among rotifer, Trichocera was more abundant than Lecanae. Bosmina showed the most abundance in summer and Daphnia in spring. Trichocera had its most abundance in summer as well, while Lecanae was more abundant in Automn and winter. A total of 41 algal genera from 8 divisions were found. Dominant phytoplankton division was Chlorophyta, with genus Pediastrum. Dominant microalga was Dynobrion (Chrysophyta) in Spring, Cylindrospermum and (both Cyanophyta) in Summer, Microsystis in Automn, and Ceratium (Dynophyta) in Winter. Ceratium were found in all seasons in most of the sampling sites, and showed highest abundance compared to other genera of its division. Dominant genus of diatoms was Fragilaria. Fish populations include Alburnus mossulensis, Capoeta aculeate, Capoeta damascina, Carasobarbus luteus, Carassius gibelio, Cyprinus carpio, and Hypophthalmichthys molitrix. Main different parts of the lake showed quite different composition of fish species. An epidemic occurance of the crustacean ectoparasite Lernea cyprinacea among most fishes was another important finding. These findings will serve as a base for future studies as a set point of drought situations.
    Description: Iranian Fisheries Science Research Institute
    Description: Published
    Keywords: Limnology ; Reservoir ; Plankton ; Fish ; Alburnus mossulensis ; Capoeta aculeate ; Capoeta damascina ; Carasobarbus luteus ; Carassius gibelio ; Cyprinus carpio ; Hypophthalmichthys molitrix
    Repository Name: AquaDocs
    Type: Report , Refereed
    Format: 72pp.
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  • 15
    Publication Date: 2021-05-19
    Description: Abbarik River is an important river in Kerman. Study of limnology of Abbarik River for aquatics & culture was started from Mehr 1381 to Day 1382. Base of this study was physical- chemical and Biological factors. In this research 3 stations was appointed. PH- oxygen- salinity- Ca- Mg- Na- K- Cl and was majored and bentetic- fish was recognized. This study was achievement in 4 season and twice in month. Bentosis recognize was Ephemeroptera- Diptera- Anisoptera- Cleoptera Trichoptera Fishes recognize was Capoeta damascina- Nemachilus sargadensis- Cyprinion watsoni.
    Description: Iranian Fisheries Science Research Institute
    Description: Published
    Keywords: Physical ; Chemical ; Biological ; Limnology ; Bentosis fish ; Aquatic ; Culture ; PH ; Salinity ; Oxygen ; Ephemeroptera ; Diptera ; Anisoptera ; Cleoptera Trichoptera ; Capoeta damascina ; Nemachilus sargadensis ; Cyprinion watsoni
    Repository Name: AquaDocs
    Type: Report , Refereed
    Format: 44pp.
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  • 16
    Publication Date: 2021-05-19
    Description: The shiroud river is one of the important riveres in point of view of fisheries matter which located in western part of Mazndran provience. The project of Limnological study have done in this river during June/ 2002 - Jun / 2003 for more and better underestanding situations, of biological and nonbiological parameters like as phytoplankton, zooplonkton, benthoses, Ichthyology, physico - chemical and pesticides of water. - Physico- chemical paramaters by ASTM methods and spectrophotometer and pestisides by US-EPA- method and GC- ECD determined. The procedures of detemination of zooplanklon and phytoplankton by manuals of Newell, 1970 and Sorina, 1974 idantify and determined respectinely. In Ichthyology, by manual procedure Berg, 1949 identifind. The sampeling have been in four stations during four seasons and result as follow: - The maximum and minimum amount of pH were in station 5 (spring) and Station no. 4 (summer) 8.19 and 7.75 respectively. - The maximum and minimum temperature of water were in station no. 8 (summer) and stations no. 2 (winter) 27.7 c and 7.7c respectively. The fluctuatcions of nutroients datas of this study and other studies done during last 5 years showed, there were not big diffrence between them but also these datas were very close to each other. - The maximum residues of pesticides for heptachlor Epoxide (Winter ) and Lindane (spring) betweenresidues of sixteen pesticdes were 79.4 and 3.7 ppb respectively. - The maximum and minimum amount of phytoplankton biomass belong to chrysophyta during four seasons were 2572 through 1081 mg/m3. - The percentage of zooplankton belong to Rotatoria , Protozoa , Copepoda , Cladocera and Zoobenthos were in 41 , 31 , 12 , 4 and 12 percent recpectively. - The maximum aboundant percentage of bentheic animals belong to Diptera with 42 percent and were dominate whole sampeling stations . - The abundence of fishes in this river belong to two species of C. capoeta gracilis and Al. bipunctatus were catched in four seasons at eight stations . The percentages of C. capoeta gracilis species were catched in four seasons at eight stations during winter, summer , spring and fall with 96 ,81 , 73 and 67 percent respectively. The percentages of Al. bipunctatus species were catched in four seasons at eight stations during winter, summer , spring and fall with 47 , 44 , 43 and 40 percent respectively.
    Description: Iranian Fisheries Science Research Institute
    Description: Published
    Keywords: Pesticdes residues ; Phytoplankton ; Zooplankton ; Riverine fishes ; Nutrients ; Limnology ; ASTM ; Rotatoria ; Protozoa ; Copepoda ; Cladocera ; Zoobenthos
    Repository Name: AquaDocs
    Type: Report , Refereed
    Format: 127pp.
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  • 17
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    Woods Hole Oceanographic Institution
    Publication Date: 2022-05-26
    Description: This is a report describing activities associated with the Matamek program in 1977. Research was conducted on biological, chemical and physical factors related to salmonid production in Matamek River and Matamek Lake. Canadian universities, the Quebec government and Woods Hole Oceanographic Institution cooperated in the program.
    Description: Supported by Woods Hole Oceanographic Institution and the Department of Tourism, Fish and Game of the Province of Quebec.
    Keywords: Ecology ; Limnology
    Repository Name: Woods Hole Open Access Server
    Type: Technical Report
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  • 18
    Publication Date: 2019-07-20
    Description: The ability to meet a controlled time of arrival during a continuous descent operation will enable environmentally friendly and fuel efficient descent operations while simultaneously maintaining airport throughput. Previous work showed that guidance strategies based on a frequent recalculation of the optimal trajectory during the descent result in excellent environmental impact mitigation figures while meeting operational constraints in the presence of modelling errors. However, the time lag of recalculating the trajectory using traditional optimisation algorithms could lead to performance degradation and stability issues. This paper proposes an alternative strategy, which allows for fast updates of the optimal trajectory based on parametric sensitivities. Promising results show that the performance of this method is comparable to that of instantaneously recalculating the optimal descent trajectory at each time sample.
    Keywords: Aircraft Stability and Control
    Type: NF1676L-30424 , AIAA/IEEE Digital Avionics Systems Conference (DASC); Sep 23, 2018 - Sep 27, 2018; London, England; United Kingdom
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  • 19
    Publication Date: 2019-07-20
    Description: A deconvolution method is presented for estimating input data from measured output data and a model of the dynamic process involved. The method uses an optimal Wiener filter for separating the measured data into signal and noise components, and a high-accuracy Fourier transform for inverting the model dynamics in the frequency domain. The method is an extension of optimal Fourier smoothing, and uses a technique to enhance the contrast between the signal and noise spectra in designing the Wiener filter. The deconvolution method was applied to simulation and flight test data for the purposes of removing unwanted distortions introduced by signal-conditioning filters and sensor dynamics, and for reconstructing turbulence inputs from measured sensor data. Results indicated hat the method performs well given good signal-to-noise levels and accurate models of the dynamic process.
    Keywords: Aircraft Stability and Control
    Type: NF1676L-28783 , AIAA Aviation and Aeronautics Forum and Exposition; Jun 25, 2018 - Jun 29, 2018; Atlanta, GA; United States
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  • 20
    Publication Date: 2019-07-20
    Description: A method for estimating aeroelastic stability and control derivatives for flexible aircraft is developed and demonstrated using flight test data for the X-56A subscale demonstrator. The method uses the equation-error approach with frequency-domain data, and can be applied post-flight or in real time during flight. The non-dimensional aeroelastic forces and moments and the explanatory variables (including generalized displacement, rate, and acceleration states for the vibration modes) are estimated using a finite element model and onboard sensor measurements in both a least squares and Kalman filtering framework. The data are then transformed into the frequency domain for parameter estimation using equation error. This method can result in a more efficient analysis than with other iterative methods, and can leverage existing statistical tools for model structure determination, data collinearity detection, combining multiple maneuvers or prior information, and others to improve model quality.
    Keywords: Aircraft Stability and Control
    Type: NF1676L-28533 , AIAA Aviation and Aeronautics Forum (Aviation 2018); Jun 25, 2018 - Jun 29, 2018; Atlanta, GA; United States
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  • 21
    Publication Date: 2019-07-20
    Description: Active flutter suppression has been demonstrated in simulation by many researchers, generally using methods based on linear aerodynamics and often with simplistic geometries. In this paper, active flutter suppression is demonstrated in a simulation using a Navier-Stokes aerodynamics code, FUN3D (Fully Unstructured Navier-Stokes Three-Dimensional), and a realistic transport aircraft configuration. This is accomplished using simple observer-feedback controllers derived from linear aeroelastic models, including reduced order models built via FUN3D data. The development of these reduced order models is described here. It is shown that controllers derived from reduced order models of the nonlinear aerodynamics outperform controllers based on linear aerodynamics.
    Keywords: Aircraft Stability and Control
    Type: NF1676L-28523 , AIAA Aviation and Aeronautics Forum (Aviation 2018); Jun 25, 2018 - Jun 29, 2018; Atlanta, GA; United States
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  • 22
    Publication Date: 2019-07-13
    Description: In recent studies, it has been observed that loss of control in flight is the most frequent primary cause of accidents. A significant share of accidents in this category can be remedied by upset prevention if possible, and by upset recovery if necessary, in this order of priorities. One of the most important upsets to be recovered from is stall. Recent accidents have shown that a correct stall recovery maneuver remains a big challenge in civil aviation, partly due to a lack of pilot training. A possible strategy to support the flight crew in this demanding context is calculating a recovery guidance signal, and showing this signal in an intuitive way on one of the cockpit displays, for example by means of the flight director. Different methods for calculating the recovery signal, one based on fast model predictive control and another using an energy based approach, have been evaluated in four relevant operational scenarios by experienced commercial as well as test pilots in the Vertical Motion Simulator at NASA Ames Research Center. Evaluation results show that this approach could be able to assist the pilots in executing a correct stall recovery maneuver.
    Keywords: Aircraft Stability and Control
    Type: ARC-E-DAA-TN50867 , SciTech Forum; Jan 08, 2018 - Jan 12, 2018; Kissimmee, FL; United States
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  • 23
    Publication Date: 2019-07-13
    Description: This paper describes a recent development of an integrated fully coupled aeroservoelastic flight dynamic model of the NASA Generic Transport Model (GTM). The integrated model couples nonlinear flight dynamics to a nonlinear aeroelastic model of the GTM. The nonlinearity includes the coupling of the rigid-body aircraft states in the partial derivatives of the aeroelastic angle of attack. Aeroservoelastic modeling of the control surfaces which are modeled by the Variable Camber Continuous Trailing Edge Flap is also conducted. The R.T. Jones' method is implemented to approximate unsteady aerodynamics. Simulations of the GTM are conducted with simulated continuous and discrete gust loads..
    Keywords: Aircraft Stability and Control
    Type: ARC-E-DAA-TN50754 , AIAA SciTech Forum; Jan 08, 2018 - Jan 12, 2018; Kissimmee, FL; United States
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  • 24
    Publication Date: 2019-07-13
    Description: Stall characteristics of a wing whose design was based on Prandtls minimum induced drag analysis is presented. Flow field is resolved using RANS CFD (Computational Fluid Dynamics) solver OVERFLOW-2. Both in freestream and in ground effect are analyzed. In addition, effect of low-Mach preconditioner on the stall characteristic is presented. Results show that simulations that lack preconditioner predicts higher stall angle as well as much more benign behavior near the stall angle. Stall analysis in freestream show that flow begins to separate at the inboard region. The flow at the tip remains attached until approximately 19.0 degrees angle of attack.
    Keywords: Aircraft Stability and Control
    Type: AFRC-E-DAA-TN48257 , AIAA Applied Aerodynamics Conference; Jun 25, 2018 - Jun 29, 2018; Atlanta, GA; United States|AIAA Aviation and Aeronautics Forum (Aviation 2018); Jun 25, 2018 - Jun 29, 2018; Atlanta, GA; United States
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  • 25
    Publication Date: 2019-07-13
    Description: These slides are the companion to the paper on the ACT experiment flown using a G-III autopilot and ADS-B datalink.
    Keywords: Aircraft Stability and Control
    Type: AFRC-E-DAA-TN58037 , AIAA Aviation Forum; Jun 25, 2018 - Jun 29, 2018; Atlanta, GA; United States
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  • 26
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    In:  CASI
    Publication Date: 2019-07-13
    Description: This presentation discusses the NASA Armstrong PTERA-SAW flight simulation. The uses of this simulation are to study the aerodynamic effects of moving outer wing panels in flight, develop a flight control system, flight safety analysis, mission planning, flight envelope expansion, and post-flight data analysis.
    Keywords: Aircraft Stability and Control
    Type: AFRC-E-DAA-TN57916 , AIAA Aviation 2018; Jun 25, 2018 - Jun 29, 2018; Atlanta, GA; United States
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  • 27
    Publication Date: 2019-08-28
    Description: An extremum-seeking control system for formation flight that uses blended performance parameters in a conglomerate performance function that better approximates drag reduction than performance functions formed from individual measurements. Generally, a variety of different measurements are taken and fed to a control system, the measurements are weighted, and are then subjected to a peak-seeking control algorithm. As measurements are continually taken, the aircraft will be guided to a relative position which optimizes the drag reduction of the formation. Two embodiments are discussed. Two approaches are shown for determining relative weightings: "a priori" by which they are qualitatively determined (by minimizing the error between the conglomerate function and the drag reduction function), and by periodically updating the weightings as the formation evolves.
    Keywords: Aircraft Stability and Control
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  • 28
    Publication Date: 2019-10-19
    Description: Project Link! is a NASA-led effort to study the feasibility of multi-aircraft aerial docking systems. In these systems, a group of vehicles physically link to each other during flight to form a larger ensemble vehicle with increased aerodynamic performance and mission utility. This paper presents a dynamic model and control architecture for a system of fixed-wing vehicles with this capability. The dynamic model consists of the 6 degree-of-freedom fixedwing aircraft equations of motion, a spring-damper-magnet system to represent the linkage force between constituent vehicles, and the NASA-Burnham-Hallock wingtip vortex model to represent the close-proximity aerodynamic interactions between constituents before the linking occurs. The control architecture consists of a guidance algorithm to autonomously drive the constituents towards their linking partners and an inner-loop angular rate controller. A simulation was constructed from the model, and the flight dynamic modes of the linked system were compared to the individual vehicles. The main contributions of this work are twofold. First is the introduction of close-proximity aerodynamic effects to create a realistic simulation framework for this problem. Second is the application of a sophisticated leaderfollower guidance algorithm to achieve in-air wingtip docking. Simulation results for both before and after linking are presented.
    Keywords: Aircraft Stability and Control
    Type: NF1676L-28646 , Journal of Guidance, Control, and Dynamics (ISSN 0731-5090) (e-ISSN 1533-3884); 41; 11; 2327-2337
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  • 29
    Publication Date: 2019-07-12
    Description: A summary of output measurement equations for onboard sensors used in flight testing of flexible aircraft is presented. These equations include the effects of structural flexibility and are considerably more complex than the standard equations for rigid-body aircraft. The output equations discussed include accelerations from linear accelerometers, strains, angular rates, angular accelerations, Euler angles, true airspeed, and air flow angles. The output equations are derived in full form and then simplified in some cases. Linearized output equations, suitable for state-space or transfer function models, are also developed. Example flight test data from the X-56A subscale aeroelastic demonstrator is discussed, for reference.
    Keywords: Aircraft Stability and Control
    Type: NASA/TM-2018-220102 , L-20956 , NF1676L-31027
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  • 30
    Publication Date: 2019-07-13
    Description: From April to May 2017, the National Aeronautics and Space Administration Armstrong Flight Research Center completed a series of flights with a trail C-20A airplane surfing in the wake of a Gulfstream III airplane using a commercially available datalink as the primary communication between the two aircraft. The purpose of this test was to characterize the aerodynamic benefits received by the trail airplane flying in the upwash portion of the wake generated from the lead airplane. Lateral and vertical relative position to the wake were automatically controlled through an experimental programmable autopilot on the C-20A airplane. Long-track, the separation distance between the two aircraft, was maintained by test pilots managing throttle position using customized cockpit displays. These displays provided the pilots with throttle cues for maintaining long-track position and situational awareness of the wake vortex relative to the position of the trail airplane. Flight testing demonstrated the ability of the pilots to use these displays to maintain a safe long-track distance, but found there to be trades between tracking performance and the frequency of throttle motion. The wake awareness display provided the pilots with adequate situational awareness of the wake vortex during the flight experiment. This paper presents a summary of the design, development, and flight evaluation of the pilot displays and long-track control.
    Keywords: Aircraft Stability and Control
    Type: AFRC-E-DAA-TN54320 , AIAA Aviation and Aeronautics Forum and Exposition; Jun 25, 2018 - Jun 29, 2018; Atlanta, GA; United States
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  • 31
    facet.materialart.
    Unknown
    Universidade Estadual de Maringá. Departamento de Biologia. Programa de Pós-Graduação em Ecologia de Ambientes Aquáticos Continentais.
    Publication Date: 2022-05-13
    Description: The environmental variables are important in the functioning and dynamics of freshwater ecosystems, since changes in physical and chemical conditions of these environments contribute to alterations in the ecological functioning. This research was conducted in four neotropical flood plains: Amazônica, Araguaia, Pantanal e Paraná. The samples of zooplankton were performed in the subsurface region of limnetic lakes each floodplain, in the years 2011 and 2012 (dry and wet). At the same time the environmental variables were measured and obtained water samples for later laboratory analysis. Our goal was to investigate the effect of environmental variables in the abundance of copepods, and the following hypothesis was tested: HI) the abundance of copepods has a great set with environmental variables, and extremes range of environmental variation, the lower the abundance of these organisms, unimodal effect. Local factors (physical and chemical environmental conditions) determined the abundance of copepods, as well as the environmental gradient showed a close relationship in the spatial and temporal distribution of the species, being possible to observe higher abundance at specific levels of environmental variables (toward the great). Studies that focus on tolerance limits of the species and their relationships with environmental conditions has risen in recent years, as the anthropogenic changes in climate and natural environments has caused significant changes in community structure, facilitating the invasion by non-native species and loss species diversity and the consequent change in ecosystem functioning. However, the hypothesis (HI) was partially supported, as the abundance follows a pattern of rise towards the great, but it was not possible to clearly unimodal effect on abundance for many species.
    Description: As variáveis ambientais têm papel relevante no funcionamento e dinâmica de ambientes aquáticos continentais, uma vez que, mudanças nas condições físicas e químicas desses ambientes contribuem para alterações no padrão de funcionamento ecológico. Esta investigação foi realizada em quatro planícies de inundação neotropicais: Amazônica, Araguaia, Pantanal e Paraná. As coletas de organismos zooplanctônicos foram realizadas na subsuperfície da região limnética das lagoas de cada planície de inundação, nos anos de 2011 e 2012 (seca e cheia). Ao mesmo tempo foram medidas as variáveis ambientais e obtidas amostras de água para posterior análise em laboratório. O nosso objetivo foi investigar o efeito das variáveis ambientais na abundância dos copépodes, e foi testada a seguinte hipótese: HI) a abundância de copépodes possui um ótimo estabelecido com as variáveis ambientais, e em extremos de amplitude de variação ambiental, menor será a abundância desses organismos, efeito uninodal. Os fatores locais (condições físicas e químicas do ambiente) determinaram a abundância de copépodes, bem como a variação ambiental apresentou uma estreita relação na distribuição espacial e temporal das espécies, sendo possível observar maiores valores de abundância em níveis específicos das variáveis ambientais (direção ao ótimo). Estudos que focam nos limites de tolerância das espécies e suas relações com as condições ambientais tem ressurgido nos últimos anos, pois as alterações antropogênicas no clima e nos ambientes naturais tem causado expressivas mudanças na estrutura da comunidade, facilitação à invasão por espécies não nativas e perda da diversidade de espécies e a consequente alteração no funcionamento ecossistêmico. Contudo, a hipótese (HI) foi parcialmente corroborada, pois a abundância segue um padrão de ascensão em direção ao ótimo, porém não foi possível estabelecer claramente para muitas espécies um efeito unimodal na distribuição da abundância.
    Description: Masters
    Keywords: Copepoda ; Ciências Ambientais ; Ecology ; Community ; Abundance ; Spatial distribution ; Niche ; Brazil ; Temporal distribution ; Abundância ; Limnologia ; Distribuição espacial ; Nicho ; Copépodes (Crustacea: Copepoda) ; Planícies de inundação ; Comunidades, Ecologia de ; Brasil ; Distribuição temporal ; Limnology
    Repository Name: AquaDocs
    Type: Thesis/Dissertation
    Format: 37pp.
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  • 32
    Publication Date: 2022-05-26
    Description: © The Author(s), 2017. This article is distributed under the terms of the Creative Commons Attribution License. The definitive version was published in Geophysical Research Letters 44 (2017): 209–218, doi:10.1002/2016GL071378.
    Description: Global lake volume estimates are scarce, highly variable, and poorly documented. We developed a rigorous method for estimating global lake depth and volume based on the Hurst coefficient of Earth's surface, which provides a mechanistic connection between lake area and volume. Volume-area scaling based on the Hurst coefficient is accurate and consistent when applied to lake data sets spanning diverse regions. We applied these relationships to a global lake area census to estimate global lake volume and depth. The volume of Earth's lakes is 199,000 km3 (95% confidence interval 196,000–202,000 km3). This volume is in the range of historical estimates (166,000–280,000 km3), but the overall mean depth of 41.8 m (95% CI 41.2–42.4 m) is significantly lower than previous estimates (62–151 m). These results highlight and constrain the relative scarcity of lake waters in the hydrosphere and have implications for the role of lakes in global biogeochemical cycles.
    Description: Knut and Alice Wallenberg Foundation; National Science Foundation Graduate Research Fellowship Program Grant Number: 2388357; National Science Foundation Grant Number: OCE-1315201
    Keywords: Limnology ; Topograhy ; Scaling ; Volume ; Mean depth
    Repository Name: Woods Hole Open Access Server
    Type: Article
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  • 33
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    Unknown
    American Association for the Advancement of Science (AAAS)
    In: Science
    Publication Date: 2017-02-10
    Description: Author: Jake Yeston
    Keywords: Inorganic Chemistry
    Print ISSN: 0036-8075
    Electronic ISSN: 1095-9203
    Topics: Biology , Chemistry and Pharmacology , Geosciences , Computer Science , Medicine , Natural Sciences in General , Physics
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  • 34
    facet.materialart.
    Unknown
    American Association for the Advancement of Science (AAAS)
    In: Science
    Publication Date: 2017-01-27
    Description: Author: Jake Yeston
    Keywords: Inorganic Chemistry
    Print ISSN: 0036-8075
    Electronic ISSN: 1095-9203
    Topics: Biology , Chemistry and Pharmacology , Geosciences , Computer Science , Medicine , Natural Sciences in General , Physics
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  • 35
    facet.materialart.
    Unknown
    American Association for the Advancement of Science (AAAS)
    In: Science
    Publication Date: 2017-01-27
    Description: Polynitrogens have the potential for ultrahigh-performing explosives or propellants because singly or doubly bonded polynitrogens can decompose to triply bonded dinitrogen (N2) with an extraordinarily large energy release. The large energy content and relatively low activation energy toward decomposition makes the synthesis of a stable polynitrogen allotrope an extraordinary challenge. Many elements exist in different forms (allotropes)—for example, carbon can exist as graphite, diamond, buckyballs, or graphene. However, no stable neutral allotropes are known for nitrogen, and only two stable homonuclear polynitrogen ions had been isolated until now—namely, the N3− anion (1) and the N5+ cation (2). On page 374 of this issue, Zhang et al. (3) report the synthesis and characterization of the first stable salt of the cyclo-N5− anion, only the third stable homonuclear polynitrogen ion ever isolated. Author: Karl O. Christe
    Keywords: Inorganic Chemistry
    Print ISSN: 0036-8075
    Electronic ISSN: 1095-9203
    Topics: Biology , Chemistry and Pharmacology , Geosciences , Computer Science , Medicine , Natural Sciences in General , Physics
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  • 36
    Publication Date: 2019-06-11
    Description: Three different types of maneuvers were designed to separately quantify the pitch rate and angle-of-attack rate contributions to the nondimensional aerodynamic pitching moment coefficient. These maneuvers combined pilot inputs and automatic multisine excitations, and they were demonstrated with the subscale T-2 and Bat-4 airplanes using the NASA Airborne Subscale Transport Aircraft Research flight-test facility. Stability and control derivatives (in particular, Cmq and Cm) were accurately estimated from the flight-test data. These maneuvers can be performed with many types of aircraft, and the results can be used to improve physical insight into the flight dynamics, facilitate more accurate comparisons with wind-tunnel experiments or numerical investigations, and increase simulation prediction fidelity.
    Keywords: Aircraft Stability and Control
    Type: NF1676L-26357 , Journal of Aircraft (ISSN 0021-8669) (e-ISSN 1533-3868); 54; 6; 2367-2377
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  • 37
    Publication Date: 2019-07-12
    Description: A test in the Langley 12-Foot Low-Speed Tunnel was conducted as a risk mitigation effort to quickly obtain some low-speed stability and control data on a "double-bubble" or D8 transport configuration. The test also tested some configuration design trades. A 5-percent scale model was tested with stabilizer, elevator, rudder and aileron control deflections. This report summarizes the test results.
    Keywords: Aircraft Stability and Control
    Type: NASA/TM-2017-219797 , L-20897 , NF1676L-29029
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  • 38
    Publication Date: 2019-07-20
    Description: Kalman filter based spacecraft attitude estimation has been used in many space missions and has been widely discussed in literature. While some models in spacecraft attitude estimation include spacecraft dynamics, most do not. To our best knowledge, there is no analysis to determine which model is a better choice. In this paper, we discuss the reasons why spacecraft dynamics should be considered in the Kalman filter based spacecraft attitude estimation problem. We also propose a reduced quaternion spacecraft dynamics model which admits additive noise. Geometry of the reduced quaternion model and the additive noise are discussed. This formulation makes computation easier than the one with full quaternion. Simulations are conducted to justify our claims.
    Keywords: Aircraft Stability and Control
    Type: NF1676L-24892 , Advances in Aircraft and Spacecraft Science (ISSN 2287-528X) (e-ISSN 2287-5271); 4; 3; 335-351
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  • 39
    Publication Date: 2019-07-20
    Description: In this project, work has been done in the field of conceptual design of experimental tiltrotors. The main tools that have been used are NDARC (NASA Design and Analysis of Rotorcraft) and SIMPLI-FLYD. NDARC is a conceptual design tool for rotorcraft, and it is used to find trim points under various flight conditions. SIMPLI-FLYD is an integrated collection of software tools that enables a flight dynamics and control assessment of the rotorcraft vehicle design generated from NDARC. Two different tiltrotors have been investigated. Initially, work was done with the Bell XV- 15 tiltrotor. NDARCs ability to correctly model the tiltwing transition between airplane mode and hover mode was looked into. In addition, data from old flight tests were compared to the NDARC output, to see how accurately performance could be predicted. After the XV-15 analysis, an NDRARC model of a novel tiltwing concept from Elytron Aircraft was written and analyzed together with SIMPLI-FLYD. Elytron 2S is an experimental tiltwing aircraft, consisting of a joined-wing design with a small central wing for the proprotor. An alternative approach to hover control is used, where the typical rotor hub and swash plate are substituted for linear actuators controlling pitch, yaw and roll. The objective with the analysis of Elytron is to obtain a more complete understanding of the maneuverability and possible performance of this alternative aircraft configuration.
    Keywords: Aircraft Stability and Control
    Type: ARC-E-DAA-TN39203 , NASA/CR-2017-219456
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  • 40
    Publication Date: 2019-07-13
    Description: This paper presents a new adaptive control approach that involves a performance optimization objective. The control synthesis involves the design of a performance optimizing adaptive controller from a subset of control inputs. The resulting effect of the performance optimizing adaptive controller is to modify the initial reference model into a time-varying reference model which satisfies the performance optimization requirement obtained from an optimal control problem. The time-varying reference model modification is accomplished by the real-time solutions of the time-varying Riccati and Sylvester equations coupled with the least-squares parameter estimation of the sensitivities of the performance metric. The effectiveness of the proposed method is demonstrated by an application of maneuver load alleviation control for a flexible aircraft.
    Keywords: Aircraft Stability and Control
    Type: ARC-E-DAA-TN42886 , Eighteenth Yale Workshop on Adaptive and Learning Systems; Jun 21, 2017 - Jun 23, 2017; New Haven, CT; United States
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  • 41
    Publication Date: 2019-07-13
    Description: The paper presents an on-board estimation, navigation and control architecture for multi-rotor drones flying in urban environment. It consists of adaptive algorithms to estimate vehicle's aerodynamic drag coefficients with respect to still air and the urban wind components along the flight trajectory, with guaranteed fast and reliable convergence to the true values; navigation algorithms to generate feasible trajectories between given way-points that take into account the estimated wind; and of control algorithms to track the generated trajectories as long as the vehicle retains sufficient number of functioning rotors capable of compensating for the estimated wind. All components of this on-board system are computationally effective and are intended for a real time implementation. The algorithms were tested in simulations.
    Keywords: Aircraft Stability and Control
    Type: ARC-E-DAA-TN38102 , AIAA SciTech Forum; Jan 09, 2017 - Jan 13, 2017; Grapevine, TX; United States
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  • 42
    Publication Date: 2019-07-13
    Description: While many widely accepted methods and techniques exist for validation and verification of traditional controllers, at this time no solutions have been accepted for Fuzzy Logic Controllers (FLCs). Due to the highly nonlinear nature of such systems, and the fact that developing a valid FLC does not require a mathematical model of the system, it is quite difficult to use conventional techniques to prove controller stability. Since safety-critical systems must be tested and verified to work as expected for all possible circumstances, the fact that FLC controllers cannot be tested to achieve such requirements poses limitations on the applications for such technology. Therefore, alternative methods for verification and validation of FLCs needs to be explored. In this study, a novel approach using formal verification methods to ensure the stability of a FLC is proposed. Main research challenges include specification of requirements for a complex system, conversion of a traditional FLC to a piecewise polynomial representation, and using a formal verification tool in a nonlinear solution space. Using the proposed architecture, the Fuzzy Logic Controller was found to always generate negative feedback, but inconclusive for Lyapunov stability.
    Keywords: Aircraft Stability and Control
    Type: ARC-E-DAA-TN38074 , SciTech 2017; Jan 09, 2017 - Jan 13, 2017; Grapevine, TX; United States
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  • 43
    Publication Date: 2019-07-13
    Description: Unlike basic Model Reference Adaptive Control (MRAC)l, Optimal Control Modification (OCM) has been shown to be a promising MRAC modification with robustness and analytical properties not present in other adaptive control methods. This paper presents an analysis of the OCM method, and how the asymptotic property of OCM is useful for analyzing and tuning the controller. We begin with a Lyapunov stability proof of an OCM controller having two adaptive gain terms, then the less conservative and easily analyzed OCM asymptotic property is presented. Two numerical examples are used to show how this property can accurately predict steady state stability and quantitative robustness in the presence of time delay, and relative to linear plant perturbations, and nominal Loop Transfer Recovery (LTR) tuning. The asymptotic property of the OCM controller is then used as an aid in tuning the controller applied to a large scale aeroservoelastic longitudinal aircraft model for flutter suppression. Control with OCM adaptive augmentation is shown to improve performance over that of the nominal non-adaptive controller when significant disparities exist between the controller/observer model and the true plant model.
    Keywords: Aircraft Stability and Control
    Type: ARC-E-DAA-TN50278 , AIAA SciTech Forum; Jan 08, 2018 - Jan 12, 2018; Kissimmee, FL; United States
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  • 44
    Publication Date: 2019-07-13
    Description: This presentation is given at a NASA DLR (German Aerospace Center) meeting at NASA ARC on March 14, 2017. The presentation provides an overview of the Advanced Control and Evolvable Systems (ACES) group at NASA ARC and the research areas in UAS autonomy, stall recovery guidance, and flexible aircraft flight control.
    Keywords: Aircraft Stability and Control
    Type: ARC-E-DAA-TN39958 , NASA/DLR Collaboration Meeting; Mar 14, 2017; Moffett Field, CA; United States
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  • 45
    Publication Date: 2019-07-13
    Description: This paper discusses the implementation and simulated performance of the FNPEG (Fully Numerical Predictor-corrector Entry Guidance) algorithm into GNC FSW (Guidance, Navigation, and Control Flight Software) for use in an autonomous re-entry vehicle. A few modifications to FNPEG are discussed that result in computational savings -- a change to the state propagator, and a modification to cross-range lateral logic. Finally, some Monte Carlo results are presented using a representative vehicle in both a high-fidelity 6-DOF (degree-of-freedom) sim as well as in a 3-DOF sim for independent validation.
    Keywords: Aircraft Stability and Control
    Type: JSC-CN-38080 , AIAA SciTech Forum 2017; Jan 09, 2017 - Jan 13, 2017; Grapevine, TX; United States
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  • 46
    Publication Date: 2019-07-13
    Description: Link! is a multi-center NASA e ort to study the feasibility of multi-aircraft aerial docking systems. In these systems, a group of vehicles physically link to each other during flight to form a larger ensemble vehicle with increased aerodynamic performance and mission utility. This paper presents a potential field guidance algorithm for a group of multi-rotor vehicles to link to each other during flight. The linking is done in pairs. Each vehicle first selects a mate. Then the potential field is constructed with three rules: move towards the mate, avoid collisions with non-mates, and stay close to the rest of the group. Once a pair links, they are then considered to be a single vehicle. After each pair is linked, the process repeats until there is only one vehicle left. The paper contains simulation results for a system of 16 vehicles.
    Keywords: Aircraft Stability and Control
    Type: NF1676L-27073 , AIAA Aviation and Aeronautics Forum and Exposition (AIAA Aviation 2017); Jun 05, 2017 - Jun 09, 2017; Denver, CO; United States
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  • 47
    Publication Date: 2019-07-13
    Description: The NASA Unmanned Aircraft System (UAS) Traffic Management (UTM) project is conducting research to enable civilian low-altitude airspace and UAS operations. A goal of this project is to develop probabilistic methods to quantify risk during failures and off nominal flight conditions. An important part of this effort is the reliable prediction of feasible trajectories during off-nominal events such as control failure, atmospheric upsets, or navigation anomalies that can cause large deviations from the intended flight path or extreme vehicle upsets beyond the normal flight envelope. Few examples of high-fidelity modeling and prediction of off-nominal behavior for small UAS (sUAS) vehicles exist, and modeling requirements for accurately predicting flight dynamics for out-of-envelope or failure conditions are essentially undefined. In addition, the broad range of sUAS aircraft configurations already being fielded presents a significant modeling challenge, as these vehicles are often very different from one another and are likely to possess dramatically different flight dynamics and resultant trajectories and may require different modeling approaches to capture off-nominal behavior. NASA has undertaken an extensive research effort to define sUAS flight dynamics modeling requirements and develop preliminary high fidelity six degree-of-freedom (6-DOF) simulations capable of more closely predicting off-nominal flight dynamics and trajectories. This research has included a literature review of existing sUAS modeling and simulation work as well as development of experimental testing methods to measure and model key components of propulsion, airframe and control characteristics. The ultimate objective of these efforts is to develop tools to support UTM risk analyses and for the real-time prediction of off-nominal trajectories for use in the UTM Risk Assessment Framework (URAF). This paper focuses on modeling and simulation efforts for a generic quad-rotor configuration typical of many commercial vehicles in use today. An overview of relevant off-nominal multi-rotor behaviors will be presented to define modeling goals and to identify the prediction capability lacking in simplified models of multi-rotor performance. A description of recent NASA wind tunnel testing of multi-rotor propulsion and airframe components will be presented illustrating important experimental and data acquisition methods, and a description of preliminary propulsion and airframe models will be presented. Lastly, examples of predicted off-nominal flight dynamics and trajectories from the simulation will be presented.
    Keywords: Aircraft Stability and Control
    Type: NF1676L-25779 , 2017 AIAA Aviation and Aeronautics Forum; Jun 05, 2017 - Jun 09, 2017; Denver, CO; United States
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  • 48
    Publication Date: 2019-07-13
    Description: Aircraft dynamics characteristics can only be identified from flight data when the aircraft dynamics are excited sufficiently. A preliminary study was conducted into what types and levels of manual piloted control excitation would be required for accurate Real-Time Parameter IDentification (RTPID) results by commercial airline pilots. This includes assessing the practicality for the pilot to provide this excitation when cued, and to further understand if pilot inputs during various phases of flight provide sufficient excitation naturally. An operationally representative task was evaluated by 5 commercial airline pilots using the NASA Ice Contamination Effects Flight Training Device (ICEFTD). Results showed that it is practical to use manual pilot inputs only as a means of achieving good RTPID in all phases of flight and in flight turbulence conditions. All pilots were effective in satisfying excitation requirements when cued. Much of the time, cueing was not even necessary, as just performing the required task provided enough excitation for accurate RTPID estimation. Pilot opinion surveys reported that the additional control inputs required when prompted by the excitation cueing were easy to make, quickly mastered, and required minimal training.
    Keywords: Aircraft Stability and Control
    Type: NASA/CR-2017-219600
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  • 49
    Publication Date: 2019-07-13
    Description: No abstract available
    Keywords: Aircraft Stability and Control
    Type: M17-5798 , NESC GNC Technical Discipline Team Face-to-Face Meeting; Jan 23, 2017 - Jan 27, 2017; Mountain View, CA; United States
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  • 50
    Publication Date: 2019-07-13
    Description: Three different types of maneuvers were designed to separately quantify pitch rate and angle of attack rate contributions to the nondimensional aerodynamic pitching moment coefficient. These maneuvers combined pilot inputs and automatic multisine excitations, and were own with the subscale T-2 and Bat-4 airplanes using the NASA AirSTAR flight test facility. Stability and control derivatives, in particular C(sub mq) and C(sub m alpha(.)) were accurately estimated from the flight test data. These maneuvers can be performed with many types of aircraft, and the results can be used to increase simulation prediction fidelity and facilitate more accurate comparisons with wind tunnel experiments or numerical investigations.
    Keywords: Aircraft Stability and Control
    Type: NF1676L-24686 , 2017 AIAA SciTech; Jan 09, 2017 - Jan 13, 2017; Dallas, TX; United States
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  • 51
    Publication Date: 2019-07-13
    Description: While many widely accepted methods and techniques exist for validation and verification of traditional controllers, at this time no solutions have been accepted for Fuzzy Logic Controllers (FLCs). Due to the highly nonlinear nature of such systems, and the fact that developing a valid FLC does not require a mathematical model of the system, it is quite difficult to use conventional techniques to prove controller stability. Since safety-critical systems must be tested and verified to work as expected for all possible circumstances, the fact that FLC controllers cannot be tested to achieve such requirements poses limitations on the applications for such technology. Therefore, alternative methods for verification and validation of FLCs needs to be explored. In this study, a novel approach using formal verification methods to ensure the stability of a FLC is proposed. Main research challenges include specification of requirements for a complex system, conversion of a traditional FLC to a piecewise polynomial representation, and using a formal verification tool in a nonlinear solution space. Using the proposed architecture, the Fuzzy Logic Controller was found to always generate negative feedback, but inconclusive for Lyapunov stability.
    Keywords: Aircraft Stability and Control
    Type: ARC-E-DAA-TN32797 , SciTech 2017; Jan 09, 2017 - Jan 13, 2017; Grapevine, TX; United States
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  • 52
    facet.materialart.
    Unknown
    In:  CASI
    Publication Date: 2019-08-26
    Description: An aircraft control structure for drag management includes a nozzle structure configured to exhaust a swirling fluid stream. A plurality of swirl vanes are positioned within the nozzle structure, and an actuation subsystem is configured to cause the plurality of swirl vanes to move from a deployed state to a non-deployed state. In the non-deployed state, the plurality of swirl vanes are substantially flush with the inner surface of the nozzle structure. In the deployed state, the plurality of swirl vanes produce the swirling fluid stream.
    Keywords: Aircraft Stability and Control
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  • 53
    Publication Date: 2019-07-13
    Description: As aircraft wings become much more flexible due to the use of light-weight composites material, adverse aerodynamics at off-design performance can result from changes in wing shapes due to aeroelastic deflections. Increased drag, hence increased fuel burn, is a potential consequence. Without means for aeroelastic compensation, the benefit of weight reduction from the use of light-weight material could be offset by less optimal aerodynamic performance at off-design flight conditions. Performance Adaptive Aeroelastic Wing (PAAW) technology can potentially address these technical challenges for future flexible wing transports. PAAW technology leverages multi-disciplinary solutions to maximize the aerodynamic performance payoff of future adaptive wing design, while addressing simultaneously operational constraints that can prevent the optimal aerodynamic performance from being realized. These operational constraints include reduced flutter margins, increased airframe responses to gust and maneuver loads, pilot handling qualities, and ride qualities. All of these constraints while seeking the optimal aerodynamic performance present themselves as a multi-objective flight control problem. The paper presents a multi-objective flight control approach based on a drag-cognizant optimal control method. A concept of virtual control, which was previously introduced, is implemented to address the pair-wise flap motion constraints imposed by the elastomer material. This method is shown to be able to satisfy the constraints. Real-time drag minimization control is considered to be an important consideration for PAAW technology. Drag minimization control has many technical challenges such as sensing and control. An initial outline of a real-time drag minimization control has already been developed and will be further investigated in the future. A simulation study of a multi-objective flight control for a flight path angle command with aeroelastic mode suppression and drag minimization demonstrates the effectiveness of the proposed solution. In-flight structural loads are also an important consideration. As wing flexibility increases, maneuver load and gust load responses can be significant and therefore can pose safety and flight control concerns. In this paper, we will extend the multi-objective flight control framework to include load alleviation control. The study will focus initially on maneuver load minimization control, and then subsequently will address gust load alleviation control in future work.
    Keywords: Aircraft Stability and Control
    Type: ARC-E-DAA-TN38210 , AIAA SciTech Forum; Jan 09, 2017 - Jan 13, 2017; Grapevine, TX; United States
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  • 54
    Publication Date: 2019-07-13
    Description: Aeroelastic stability and control derivatives for the X-56A Multi-Utility Technology Testbed (MUTT), in the stiff-wing configuration, were estimated from flight test data using the output-error method. Practical aspects of the analysis are discussed. The orthogonal phase-optimized multisine inputs provided excellent data information for aeroelastic modeling. Consistent parameter estimates were determined using output error in both the frequency and time domains. The frequency domain analysis converged faster and was less sensitive to starting values for the model parameters, which was useful for determining the aeroelastic model structure and obtaining starting values for the time domain analysis. Including a modal description of the structure from a finite element model reduced the complexity of the estimation problem and improved the modeling results. Effects of reducing the model order on the short period stability and control derivatives were investigated.
    Keywords: Aircraft Stability and Control
    Type: NF1676L-24692 , AIAA SciTech 2017; Jan 09, 2017 - Jan 13, 2017; Dallas, TX; United States
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  • 55
    Publication Date: 2021-05-19
    Description: This work includes a study of the ecological characteristics and of the distribution of floristic and faunistic communities in a muddy lagoon with large fluctuations of salinity.
    Description: Ce travail est une étude des conditions écologiques générales et de la répartition des peuplements végétaux et animaux dans une lagune envasée soumise à de grandes fluctuations de salinité.
    Description: Published
    Keywords: Salinity ; Lakes ; Climate ; Limnology ; Water analysis ; Sediment analysis ; Freshwater ecology ; Brackish ; Freshwater
    Repository Name: AquaDocs
    Type: Journal Contribution , Refereed
    Format: pp 115-124
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  • 56
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    American Association for the Advancement of Science (AAAS)
    In: Science
    Publication Date: 2016-09-09
    Description: Author: Jake Yeston
    Keywords: Inorganic Chemistry
    Print ISSN: 0036-8075
    Electronic ISSN: 1095-9203
    Topics: Biology , Chemistry and Pharmacology , Geosciences , Computer Science , Medicine , Natural Sciences in General , Physics
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  • 57
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    American Association for the Advancement of Science (AAAS)
    In: Science
    Publication Date: 2016-11-11
    Description: Author: Jake Yeston
    Keywords: Inorganic Chemistry
    Print ISSN: 0036-8075
    Electronic ISSN: 1095-9203
    Topics: Biology , Chemistry and Pharmacology , Geosciences , Computer Science , Medicine , Natural Sciences in General , Physics
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  • 58
    Publication Date: 2019-07-13
    Description: A method for estimating dynamic model parameters from flight data with unknown time skews is described and demonstrated. The method combines data reconstruction, nonlinear optimization, and equation-error parameter estimation in the frequency domain to accurately estimate both dynamic model parameters and the relative time skews in the data. Data from a nonlinear F-16 aircraft simulation with realistic noise, instrumentation errors, and arbitrary time skews were used to demonstrate the approach. The approach was further evaluated using flight data from a subscale jet transport aircraft, where the measured data were known to have relative time skews. Comparison of modeling results obtained from time-skewed and time-synchronized data showed that the method accurately estimates both dynamic model parameters and relative time skew parameters from flight data with unknown time skews.
    Keywords: Aircraft Stability and Control
    Type: NF1676L-21730 , 2016 AIAA SciTech Forum and Exposition; Jan 04, 2016 - Jan 08, 2016; San Diego, CA; United States
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  • 59
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    In:  CASI
    Publication Date: 2019-07-13
    Description: NASA is in the process of qualifying the mid-size Super Pressure Balloon (SPB) to provide constant density altitude flight for science investigations at polar and mid-latitudes. The status of the development of the 18.8 million cubic foot SPB capable of carrying one-tonne of science to 110,000 feet, will be given. In addition, the operating considerations such as launch sites, flight safety considerations, and recovery will be discussed.
    Keywords: Aircraft Stability and Control
    Type: GSFC-E-DAA-TN32079 , 2016 Scientific Ballooning Technologies Workshop; May 09, 2016 - May 11, 2016; Minneapolis, MN; United States
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  • 60
    Publication Date: 2019-07-13
    Description: The NASA Airborne Subscale Transport Aircraft Research Unmanned Aerial System project's capabilities were expanded by updating the system design and concept of operations. The new remotely piloted airplane system design was flight tested to assess integrity and operational readiness of the design to perform flight research. The purpose of the system design is to improve aviation safety by providing a capability to validate, in high-risk conditions, technologies to prevent airplane loss of control. Two principal design requirements were to provide a high degree of reliability and that the new design provide a significant increase in test volume (relative to operations using the previous design). The motivation for increased test volume is to improve test efficiency and allow new test capabilities that were not possible with the previous design and concept of operations. Three successful test flights were conducted from runway 4-22 at NASA Goddard Space Flight Center's Wallops Flight Facility.
    Keywords: Aircraft Stability and Control
    Type: NF1676L-23006 , 2016 AIAA SciTech Conference; Jan 04, 2016 - Jan 08, 2016; San Diego, CA; United States
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  • 61
    Publication Date: 2019-07-13
    Description: Distributed engine control architecture presents a significant increase in complexity over traditional implementations when viewed from the perspective of system simulation and hardware design and test. Even if the overall function of the control scheme remains the same, the hardware implementation can have a significant effect on the overall system performance due to differences in the creation and flow of data between control elements. A Hardware-in-the-Loop (HIL) simulation system is under development at NASA Glenn Research Center that enables the exploration of these hardware dependent issues. The system is based on, but not limited to, the Commercial Modular Aero-Propulsion System Simulation 40k (C-MAPSS40k). This paper describes the step-by-step conversion from the self-contained baseline model to the hardware in the loop model, and the validation of each step. As the control model hardware fidelity was improved during HIL system development, benchmarking simulations were performed to verify that engine system performance characteristics remained the same. The results demonstrate the goal of the effort; the new HIL configurations have similar functionality and performance compared to the baseline C-MAPSS40k system.
    Keywords: Aircraft Stability and Control
    Type: GRC-E-DAA-TN28906 , AIAA SciTech 2016; Jan 04, 2016 - Jan 08, 2016; San Diego, CA; United States
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  • 62
    Publication Date: 2019-07-13
    Description: This paper considers an approach for modelling transport aircraft trajectories that can facilitate their rapid evaluation and modification, either en route or in terminal control areas, with the goal of efficiently making use of airspace and runways by a large population of vehicles without pairwise violation of separation criteria.
    Keywords: Aircraft Stability and Control
    Type: NF1676L-24516 , AIAA Aviation Technology, Integration, and Operations Conference; Jun 13, 2016 - Jun 17, 2016; Washington, DC; United States
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  • 63
    Publication Date: 2019-07-13
    Description: A real-time method was demonstrated for determining accurate uncertainty levels of stability and control derivatives estimated using recursive least squares and time-domain data. The method uses a recursive formulation of the residual autocorrelation to account for colored residuals, which are routinely encountered in aircraft parameter estimation and change the predicted uncertainties. Simulation data and flight test data for a subscale jet transport aircraft were used to demonstrate the approach. Results showed that the corrected uncertainties matched the observed scatter in the parameter estimates, and did so more accurately than conventional uncertainty estimates that assume white residuals. Only small differences were observed between batch estimates and recursive estimates at the end of the maneuver. It was also demonstrated that the autocorrelation could be reduced to a small number of lags to minimize computation and memory storage requirements without significantly degrading the accuracy of predicted uncertainty levels.
    Keywords: Aircraft Stability and Control
    Type: NF1676L-21676 , AIAA 2016 SciTech Forum and Exposition; Jan 04, 2016 - Jan 08, 2016; San Diego, CA; United States
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  • 64
    Publication Date: 2019-07-13
    Description: Flight testing and modeling techniques were developed to accurately identify global nonlinear aerodynamic models for aircraft in real time. The techniques were developed and demonstrated during flight testing of a remotely-piloted subscale propeller-driven fixed-wing aircraft using flight test maneuvers designed to simulate a Learn-To-Fly scenario. Prediction testing was used to evaluate the quality of the global models identified in real time. The real-time global nonlinear aerodynamic modeling algorithm will be integrated and further tested with learning adaptive control and guidance for NASA Learn-To-Fly concept flight demonstrations.
    Keywords: Aircraft Stability and Control
    Type: NF1676L-21688 , 2016 AIAA SciTech Conference; Jan 04, 2016 - Jan 08, 2016; San Diego, CA; United States
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  • 65
    Publication Date: 2019-07-13
    Description: First steps have been taken to qualify a family of parafoil systems capable of increasing the survivability and reusability of high-altitude balloon payloads. The research is motivated by the common risk facing balloon payloads where expensive flight hardware can often land in inaccessible areas that make them difficult or impossible to recover. The Autonomously Navigated Experimental Lander (ANGEL) flight test introduced a commercial Guided Parachute Aerial Delivery System (GPADS) to a previously untested environment at 108,000ft MSL to determine its high-altitude survivability and capabilities. Following release, ANGEL descended under a drogue until approximately 25,000ft, at which point the drogue was jettisoned and the main parachute was deployed, commencing navigation. Multiple data acquisition platforms were used to characterize the return-to-point technology performance and help determine its suitability for returning future scientific payloads ranging from 180 to 10,000lbs to safer and more convenient landing locations. This report describes the test vehicle design, and summarizes the captured sensor data. Various post-flight analyses are used to quantify the system's performance, gondola load data, and serve as a reference point for subsequent missions.
    Keywords: Aircraft Stability and Control
    Type: GRC-E-DAA-TN28393 , AIAA SciTech 2016; Jan 04, 2016 - Jan 08, 2016; San Diego, CA; United States
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  • 66
    Publication Date: 2019-07-13
    Description: The paper presents an algorithm for control and safe landing of impaired multi-rotor drones when one or more motors fail simultaneously or in any sequence. It includes three main components: an identification block, a reconfigurable control block, and a decisions making block. The identification block monitors each motor load characteristics and the current drawn, based on which the failures are detected. The control block generates the required total thrust and three axis torques for the altitude, horizontal position and/or orientation control of the drone based on the time scale separation and nonlinear dynamic inversion. The horizontal displacement is controlled by modulating the roll and pitch angles. The decision making algorithm maps the total thrust and three torques into the individual motor thrusts based on the information provided by the identification block. The drone continues the mission execution as long as the number of functioning motors provide controllability of it. Otherwise, the controller is switched to the safe mode, which gives up the yaw control, commands a safe landing spot and descent rate while maintaining the horizontal attitude.
    Keywords: Aircraft Stability and Control
    Type: ARC-E-DAA-TN24294 , AIAA Science and Technology Forum and Exposition (SciTech 2016); Jan 04, 2016 - Jan 08, 2016; San Diego, CA; United States
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  • 67
    Publication Date: 2019-07-13
    Description: The study described in this paper had two objectives. The first objective was to investigate if a different weighting of heave motion components decomposed at the center of gravity, allowing for a higher fidelity of individual components, would result in pilot manual pitch control behavior and performance closer to that observed with full aircraft motion. The second objective was to investigate if decomposing the heave components at the aircraft's instantaneous center of rotation rather than at the center of gravity could result in additional improvements in heave motion fidelity. Twenty-one general aviation pilots performed a pitch attitude control task in an experiment conducted on the Vertical Motion Simulator at NASA Ames under different hexapod motion conditions. The large motion capability of the Vertical Motion Simulator also allowed for a full aircraft motion condition, which served as a baseline. The controlled dynamics were of a transport category aircraft trimmed close to the stall point. When the ratio of center of gravity pitch heave to center of gravity heave increased in the hexapod motion conditions, pilot manual control behavior and performance became increasingly more similar to what is observed with full aircraft motion. Pilot visual and motion gains significantly increased, while the visual lead time constant decreased. The pilot visual and motion time delays remained approximately constant and decreased, respectively. The neuromuscular damping and frequency both decreased, with their values more similar to what is observed with real aircraft motion when there was an equal weighting of the heave of the center of gravity and heave due to rotations about the center of gravity. In terms of open- loop performance, the disturbance and target crossover frequency increased and decreased, respectively, and their corresponding phase margins remained constant and increased, respectively. The decomposition point of the heave components only had limited effects on pilot manual control behavior and performance.
    Keywords: Aircraft Stability and Control
    Type: ARC-E-DAA-TN32614 , AIAA Aviation 2016 Conference; Jun 13, 2016 - Jun 17, 2016; Washington, DC; United States
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  • 68
    Publication Date: 2019-07-12
    Description: Calculated numerical values for some aerodynamic terms and stability Derivatives for several different wings in unseparated inviscid incompressible flow were made using a discrete vortex method involving a limited number of horseshoe vortices. Both longitudinal and lateral-directional derivatives were calculated for steady conditions as well as for sinusoidal oscillatory motions. Variables included the number of vortices used and the rotation axis/moment center chordwise location. Frequencies considered were limited to the range of interest to vehicle dynamic stability (kb 〈.24 ). Comparisons of some calculated numerical results with experimental wind-tunnel measurements were in reasonable agreement in the low angle-of-attack range considering the differences existing between the mathematical representation and experimental wind-tunnel models tested. Of particular interest was the presence of induced drag for the oscillatory condition.
    Keywords: Aircraft Stability and Control
    Type: NASA/TM-2016-219349 , L-20759 , NF1676L-25593
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  • 69
    Keywords: Aquatic ecosystem monitoring ; Aquatic ecosystem assessment ; Aquatic ecosystem management ; Aquatic ecosystem services ; Aquatic ecosystem policy ; Restoration ; Conservation ; Biological indicators ; Streams/ Rivers/ Lakes/ Wetlands ; Aquatic ecology ; Ecohydrology ; Limnology
    Description / Table of Contents: Today, sustainability of a healthy freshwater ecosystem and its associated ecosystem services are hot issues with ever-growing attention placed upon them. We are increasingly recognizing that they are crucial for the survival of the aquatic biota and human beings on our planet. The efficient monitoring of water resources is fundamental for effective management of water quality and aquatic ecosystems. The first stage in sustainable ecosystem management is the evaluation of the current status of target ecosystems. Traditionally, and even today, physico-chemical parameters have mainly been used to evaluate the quality of water resources. However, they have a large limit to grab the wholeness of water system, particularly in the sense of ecosystem health and integrity, for which ecological monitoring should be based on biological factors. Various approaches are applicable to ecosystem health assessment at different levels of the biological hierarchy, from genes to ecosystems. This Special Issue is designed to improve scientific understanding and strategies for sound aquatic ecosystem management and services for researchers, decision makers, and stakeholders.
    Pages: Online-Ressource (XVI, 422 Seiten)
    Edition: Printed Edition of the Special Issue Published in Water
    ISBN: 9783038422679
    Language: English
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  • 70
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    Ministry of Environment and Natural Resources, LVEMP Water Quality Component | Kisumu, Kenya
    Publication Date: 2021-05-19
    Description: Sampling for nutrients, Chrolophyll-a and total suspended solids was done in 9 in-lake stations in the Kenyan part of Lake Victoria between December 2000 and October 2001. In-situ measurements of temperature, dissolved oxygen and water transparency were also carried out. PO4-P was found to range from 0.007mg/l to 0.057 mg/l and was higher in the pelagic stations than in littoral stations. NO3-N concentrations of 0.005-0.037 mg/l were recorded and were found to be relatively higher in the littoral stations than in the pelagic stations. TN:TP ration of the lake was found to be 6.78 indicating a possibility of heterocystous blue-green algae dominating. The ratio of 8.6 in the littoral stations showed a potential for higher photosynthetic rates in this part of the lake than in the pelagic zones. SRSi levels in the pelagic zones were found to have reduced significantly compared to those reported by Talling (1965), whereas those in the littoral zone was within the reported range. Water temperature was found to have increased and transparency values decreased compared to those measured by Worthington (1930) for both the open waters and within the gulf. Anoxic conditions (DO 〈1mg/l) were measured in depths of up to 30m.
    Description: Published
    Keywords: Water quality ; Limnology ; Nutrients (mineral)
    Repository Name: AquaDocs
    Type: Report , Not Known
    Format: 11pp.
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  • 71
    Publication Date: 2021-05-19
    Description: The objectives of the Lake Victoria environment monitoring were to obtain data for: (1) Determination of the present state of the lake water quality and ecosystem. (2) Analysis of the relative importance of the biological processes and limiting factors in the eutrophication of the lake. (3) Calibration of the Lake Victoria Water Quality Framework Model. (4) Long -term monitoring of changes taking place in the lake. To achieve these objectives a programme for monthly lake monitoring on the lake was established to gather data on the quality of the waters of the lake and the lake’s limnology through in-situ measurements, and laboratory analysis of samples.
    Description: Published
    Keywords: Water quality ; Urbanization ; Eutrophication ; Limnology
    Repository Name: AquaDocs
    Type: Book Section , Not Known
    Format: pp.164- 212 [Chapter 8]
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  • 72
    Publication Date: 2021-05-19
    Description: This paper reports on the major limnological and water quality findings in Lake Victoria, Kenya and offers suggestions on sustainable management of lake water quality.
    Description: Published
    Keywords: Water quality ; Eutrophication ; Resource management ; Limnology
    Repository Name: AquaDocs
    Type: Book Section , Not Known
    Format: pp.239-261 [Chapter 10]
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  • 73
    Publication Date: 2019-07-13
    Description: A new formulation of the filter-error method for estimating aerodynamic parameters in nonlinear aircraft dynamic models during turbulence was developed and demonstrated. The approach uses an estimate of the measurement noise covariance to identify the model parameters, their uncertainties, and the process noise covariance, in a relaxation method analogous to the output-error method. Prior information on the model parameters and uncertainties can be supplied, and a post-estimation correction to the uncertainty was included to account for colored residuals not considered in the theory. No tuning parameters, needing adjustment by the analyst, are used in the estimation. The method was demonstrated in simulation using the NASA Generic Transport Model, then applied to the subscale T-2 jet-engine transport aircraft flight. Modeling results in different levels of turbulence were compared with results from time-domain output error and frequency- domain equation error methods to demonstrate the effectiveness of the approach.
    Keywords: Aircraft Stability and Control
    Type: NF1676L-20186 , AIAA Atmospheric Flight Mechanics Conference; Jun 22, 2015 - Jun 26, 2015; Dallas,TX; United States
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  • 74
    Publication Date: 2019-07-13
    Description: The implementation and evaluation of an efficient method for estimating safe aircraft maneuvering envelopes are discussed. A Bayesian approach is used to produce a deterministic algorithm for estimating aerodynamic system parameters from existing noisy sensor measurements, which are then used to estimate the trim envelope through efficient high- fidelity model-based computations of attainable equilibrium sets. The safe maneuverability limitations are extended beyond the trim envelope through a robust reachability analysis derived from an optimal control formulation. The trim and maneuvering envelope limits are then conveyed to pilots through three axes on the primary flight display. To evaluate the new display features, commercial airline crews flew multiple challenging approach and landing scenarios in the full motion Advanced Concepts Flight Simulator at NASA Ames Research Center, as part of a larger research initiative to investigate the impact on the energy state awareness of the crew. Results show that the additional display features have the potential to significantly improve situational awareness of the flight crew.
    Keywords: Aircraft Stability and Control
    Type: ARC-E-DAA-TN19341 , AIAA Infotech 2015; Jan 05, 2015 - Jan 09, 2015; Kissimmee, FL; United States
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  • 75
    Publication Date: 2019-07-13
    Description: No abstract available
    Keywords: Aircraft Stability and Control
    Type: AFRC-E-DAA-TN25157 , South Korean Delegration; Jul 16, 2015; Edwards AFB California; United States
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  • 76
    Publication Date: 2019-07-12
    Description: This report introduces a modeling and simulation tool for aeroservoelastic analysis of rectangular wings with trailing-edge control surfaces. The inputs to the code are planform design parameters such as wing span, aspect ratio, and number of control surfaces. Using this information, the generalized forces are computed using the doublet-lattice method. Using Roger's approximation, a rational function approximation is computed. The output, computed in a few seconds, is a state space aeroservoelastic model which can be used for analysis and control design. The tool is fully parameterized with default information so there is little required interaction with the model developer. All parameters can be easily modified if desired. The focus of this report is on tool presentation, verification, and validation. These processes are carried out in stages throughout the report. The rational function approximation is verified against computed generalized forces for a plate model. A model composed of finite element plates is compared to a modal analysis from commercial software and an independently conducted experimental ground vibration test analysis. Aeroservoelastic analysis is the ultimate goal of this tool, therefore, the flutter speed and frequency for a clamped plate are computed using damping-versus-velocity and frequency-versus-velocity analysis. The computational results are compared to a previously published computational analysis and wind-tunnel results for the same structure. A case study of a generic wing model with a single control surface is presented. Verification of the state space model is presented in comparison to damping-versus-velocity and frequency-versus-velocity analysis, including the analysis of the model in response to a 1-cos gust.
    Keywords: Aircraft Stability and Control
    Type: NASA/TM-2015-218875 , DFRC-E-DAA-TN25358
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  • 77
    Publication Date: 2019-08-13
    Description: The X-56A Multi-Utility Technology Testbed is an experimental aircraft designed to study active control of flexible structures. The vehicle is easily reconfigured to allow for testing of different configurations. The vehicle is being used to study new sensor, actuator, modeling and controls technologies. These new technologies will allow for lighter vehicles and new configurations that exceed the efficiency currently achievable. A description of the vehicle and the current research efforts that it enables are presented.
    Keywords: Aircraft Stability and Control
    Type: AFRC-E-DAA-TN27228 , 2015 IFAR Young Researcher Conference; Oct 04, 2015 - Oct 10, 2015; Moffett Field, CA; United States
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  • 78
    Publication Date: 2019-08-28
    Description: A method and system are provided to weaken shock wave strength at leading edge surfaces of a vehicle in atmospheric flight. One or more flight-related attribute sensed along a vehicle's outer mold line are used to control the injection of a non-heated, non-plasma-producing gas into a local external flowfield of the vehicle from at least one leading-edge surface location along the vehicle's outer mold line. Pressure and/or mass flow rate of the gas so-injected is adjusted in order to cause a Rankine-Hugoniot Jump Condition along the vehicle's outer mold line to be violated.
    Keywords: Aircraft Stability and Control
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  • 79
    Publication Date: 2019-07-13
    Description: A 2015 NASA Aeronautics Mission "Seedling" Proposal is described for a Severe-Environment UAV (SE-UAV) that can perform in-situ measurements in hazardous atmospheric conditions like lightning, volcanic ash and radiation. Specifically, this paper describes the design of a proof-of-concept vehicle and measurement system that can survive lightning attachment during flight operations into thunderstorms. Elements from three NASA centers draw together for the SE-UAV concept. 1) The NASA KSC Genesis UAV was developed in collaboration with the DARPA Nimbus program to measure electric field and X-rays present within thunderstorms. 2) A novel NASA LaRC fiber-optic sensor uses Faraday-effect polarization rotation to measure total lightning electric current on an air vehicle fuselage. 3) NASA AFRC's state-of-the-art Fiber Optics and Systems Integration Laboratory is envisioned to transition the Faraday system to a compact, light-weight, all-fiber design. The SE-UAV will provide in-flight lightning electric-current return stroke and recoil leader data, and serve as a platform for development of emerging sensors and new missions into hazardous environments. NASA's Aeronautics and Science Missions are interested in a capability to perform in-situ volcanic plume measurements and long-endurance UAV operations in various weather conditions. (Figure 1 shows an artist concept of a SE-UAV flying near a volcano.) This paper concludes with an overview of the NASA Aeronautics Strategic Vision, Programs, and how a SE-UAV is envisioned to impact them. The SE-UAV concept leverages high-value legacy research products into a new capability for NASA to fly a pathfinder UAV into hazardous conditions, and is presented in the SPIE DSS venue to explore teaming, collaboration and advocacy opportunities outside NASA.
    Keywords: Aircraft Stability and Control
    Type: SPIE Paper 9468-28 , NF1676L-21134 , SPIE DSS 2015 - Defense and Security Meeting; Apr 20, 2015 - Apr 24, 2015; Baltimore, MD; United States
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  • 80
    Publication Date: 2019-07-13
    Description: This paper describes a transfer-of-training study performed in the NASA Ames Vertica lMotion Simulator. The purpose of the study was to investigate the effect of false tilt cues on training and transfer of training of manual roll control skills. Of specific interest were the skills needed to control unstable roll dynamics of a mid-size transport aircraft close to the stall point. Nineteen general aviation pilots trained on a roll control task with one of three motion conditions: no motion, roll motion only, or reduced coordinated roll motion. All pilots transferred to full coordinated roll motion in the transfer session. A novel multimodal pilot model identification technique was successfully applied to characterize how pilots' use of visual and motion cues changed over the course of training and after transfer. Pilots who trained with uncoordinated roll motion had significantly higher performance during training and after transfer, even though they experienced the false tilt cues. Furthermore, pilot control behavior significantly changed during the two sessions, as indicated by increasing visual and motion gains, and decreasing lead time constants. Pilots training without motion showed higher learning rates after transfer to the full coordinated roll motion case.
    Keywords: Aircraft Stability and Control
    Type: AIAA Paper 2015-0655 , ARC-E-DAA-TN20112 , AIAA SciTech 2015; Jan 05, 2015 - Jan 09, 2015; Kissimmee, FL; United States
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  • 81
    Publication Date: 2019-07-13
    Description: Safety of unmanned aerial systems (UAS) is paramount, but the large number of dynamically changing controller parameters makes it hard to determine if the system is currently stable, and the time before loss of control if not. We propose a hierarchical statistical model using Treed Gaussian Processes to predict (i) whether a flight will be stable (success) or become unstable (failure), (ii) the time-to-failure if unstable, and (iii) time series outputs for flight variables. We first classify the current flight input into success or failure types, and then use separate models for each class to predict the time-to-failure and time series outputs. As different inputs may cause failures at different times, we have to model variable length output curves. We use a basis representation for curves and learn the mappings from input to basis coefficients. We demonstrate the effectiveness of our prediction methods on a NASA neuro-adaptive flight control system.
    Keywords: Aircraft Stability and Control
    Type: ARC-E-DAA-TN23968 , Society for Industrial and Applied Mathematics (SIAM) Conference on Control and Its Applications; Jul 08, 2015 - Jul 10, 2015; Paris; France
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  • 82
    Publication Date: 2019-07-12
    Description: This report documents a case study on the application of Reliability Engineering techniques to achieve an optimal balance between performance and robustness by tuning the functional parameters of a complex non-linear control system. For complex systems with intricate and non-linear patterns of interaction between system components, analytical derivation of a mathematical model of system performance and robustness in terms of functional parameters may not be feasible or cost-effective. The demonstrated approach is simple, structured, effective, repeatable, and cost and time efficient. This general approach is suitable for a wide range of systems.
    Keywords: Aircraft Stability and Control
    Type: NASA/TM-2015-218795 , L-20574 , NF1676L-21781
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  • 83
    Electronic Resource
    Electronic Resource
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1018-1027 
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Bei nochmaliger Untersuchung der Umsetzung von CCl4 mit Si/Cu-Gemischen werden, wie bereits bekannt, SiCl4, C2Cl4 und Si2Cl6 gefunden. Darüber hinaus lief eine direkte Synthese. Sie führte wahrscheinlich zur Bildung des allerdings dabei nicht nachgewiesenen Cl3C·SiCl3. Dagegen wurde die nach der direkten Synthese entstandene Verbindung C(SiCl3)4 erstmalig aufgefunden.  -  Die Entstehung der ebenfalls nachgewiesenen Verbindungen Cl3SiC·C⋮CC·SiCl3 und Cl3SiC·(Cl)C:C(Cl)C·SiCl3 wird durch Dechlorierungen des Cl3CC·SiCl3 mit Kupfer erklärt.  -  Für die neuen Verbindungen wurden Strukturbeweise geführt. Es wurden C2Cl4 und Cl3CC·SiCl3 mit Si/Cu-Gemischen umgesetzt. Die letzte Umsetzung ergab dieselben Reaktionsprodukte wie das CCl4, so daß auch bei diesem eine direkte Synthese über das Cl3CC·SiCl3 glaubhaft gemacht ist.
    Additional Material: 2 Ill.
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  • 84
    Electronic Resource
    Electronic Resource
    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1048-1055 
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Eigenschaften von tert.-Butylthionitrit, Triphenylmethylthionitrit und tert.-Butylthionitrat werden Rückschlüsse auf die Elektronenstruktur der schwefelhaltigen Gruppe gezogen.
    Additional Material: 2 Tab.
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  • 85
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Als weiteres Beispiel für die präparative Überlegenheit der säurekatalysierten Aldolreaktionen des Formaldehyds gegenüber den OH⊖-katalysierten wird über die Synthese der bisher unbekannten Bisanhydro-ennea-heptose, die das Ringsystem des 3.7-Dioxa-bicyclo-[1.3.3]-nonans enthält, berichtet.  -  Bei der Untersuchung des Verhaltens der Bisanhydro-ennea-heptose gegen Alkalien machten sich in der Abspaltbarkeit der Hydroxymethylgruppen charakteristische Unterschiede geltend, deren Erklärung in den konstitutionell-konstellativen Gegebenheiten zu suchen ist.  -  Bei dem Versuch einer Ringerweiterung an der Anhydro-ennea-heptose mit Diazomethan bildet sich eine Verbindung C9H16O5, die wahrscheinlich kein Derivat des Oxa-cycloheptanons-(4), sondern ein Derivat des Tetrahydro-γ-pyrons ist.
    Additional Material: 4 Ill.
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  • 86
    Electronic Resource
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    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1092-1101 
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Substituierte Ammoniumsalze vom Typ I liefern mit Abkömmlingen des Phenylglyoxals in Methanol in glatter Reaktion Lactolid-Basen vom Typ II. Aus diesen lassen sich verschiedene Octa- bzw. Decahydroisochinolin-Derivate darstellen, die in 1-Stellung einen substituierten Benzylrest tragen.
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  • 87
    Electronic Resource
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    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1115-1117 
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Die jodometrische Bestimmung der Hydroperoxyde von Benzolkohlenwasserstoffen kann durch katalytische Wirkung von Kupferionen verbessert werden.
    Additional Material: 1 Ill.
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  • 88
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    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1135-1139 
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Die Umsetzung von Tetraacetyl-α-D-glucopyranosylbromid und Tetraacetyl-6-trityl-β-D-glucopyranose mit Silberperchlorat oder Silberfluoroborat in Nitromethan liefert in guter Ausbeute Octaacetyl-β-gentiobiose. Die gleiche Umsetzung mit einem Überschuß an Tetraacetyl-α-D-glucopyranosylbromid und Silberperchlorat führt zur Octaacetyl-α-gentiobiose. Es wird eine Deutung des Reaktionsablaufs gegeben.
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  • 89
    Electronic Resource
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    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1126-1129 
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Tachysterin2 wurde mit durch Glas gefiltertem Quecksilberdampflicht in Präcalciferol2 umgewandelt.
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  • 90
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    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1152-1158 
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Um eine Aussage über den Reaktionsmechanismus bei der Mercurierung des Ammonium-Ions in wäßrigen Lösungen machen zu können, wurde Quecksilber-(II)-diamminchlorid, Hg(NH3)2Cl2, mit wäßriger Ammoniumacetat-Lösung zum sog. „unschmelzbaren Präzipitat“, HgNH2Cl, umgesetzt. Die Lösung enthielt 1 Mol. 203Hg(CH3CO2)2 pro Mol. des Diammoniakates.Die beiden heterogenen Austauschreaktionen Hg(NH3)2Cl2/[203Hg(NH3)4]2⊕ und HgNH2Cl/[203Hg(NH3)4]2⊕ wurden in Abhängigkeit von der Temperatur untersucht.
    Additional Material: 3 Ill.
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  • 91
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    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1158-1163 
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Von den sechs möglichen Isomeren des Decalindiols-(1.4) wurden zwei der Reihe des cis-Decalins und zwei der Reihe des trans-Decalins angehörende Diole durch Reduktion von cis- und trans-Decalindion-(1.4) sowie durch katalyt. Hydrierung von Naphthohydrochinon-(1.4) und ar-Tetralindiol-(5.8) mit Raney-Nickel im Autoklaven erhalten, eindeutig der cis- und trans-Reihe zugeordnet und durch Derivate charakterisiert.
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  • 92
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    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1184-1188 
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Die Einwirkung von Aryldiazoniumsalzen auf verschiedene monoalkylierte Dihydroresorcine wurde untersucht. Dabei wurden im glatten Reaktionsverlauf δ-Keto-δ-arylhydrazono-carbonsäuren erhalten. Die gleiche Reaktion führte beim 2-Acetamino-dihydroresorcin infolge einer sekundär verlaufenden Wasserabspaltung zu einem Derivat des 1.2.4-Triazols, dessen Konstitution bewiesen wurde.
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  • 93
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    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1206-1212 
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Durch Umsetzung von Alkylhydroperoxyden oder Wasserstoffperoxyd mit Formaldehyd und sekundären Aminen werden nach Art der Mannich-Reaktion Aminoalkylperoxyde erhalten. In mineralsaurer Lösung gelingt auch die Umsetzung von Benzamid oder Harnstoff mit Formaldehyd und Alkylhydroperoxyden.
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  • 94
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    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1216-1223 
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Die Einführung der Carbonsäurechloridgruppe in 1- bzw. 3-Stellung des Azulensystems gelingt durch Substitution mittels Phosgens ohne Friedel-Crafts-Katalysatoren. Befindet sich in Nachbarstellung zur Carbonsäurechloridgruppe am 7-Ring kein Substituent, so lassen sich die Verbindungen zu den freien Carbonsäuren hydrolysieren, andernfalls tritt Decarboxylierung ein. Die Säurechloride lassen sich in Ester, Amide und Anilide überführen. Die spektralen Verschiebungen gegenüber den zugrunde liegenden Azulenen werden diskutiert.
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  • 95
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    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1195-1205 
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Die Hydrierung des Adrenalins mit Raney-Nickel liefert keine brauchbaren Ergebnisse. Das Hexahydro-adrenalin (Xb) wird deshalb synthetisch aus Tetrahydro-benzaldehyd in 5 Stufen in guter Ausbeute dargestellt. Es wird gezeigt, daß das synthetische Produkt eine sterisch weitgehend einheitliche Verbindung ist und die 3(trans).4(cis)-Konfiguration besitzt.
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  • 96
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    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1212-1215 
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Aus cyclischen Ketonen und sekundären Aminen erhältliche α.β-ungesättigte Amine addieren Wasserstoffperoxyd an der Doppelbindung und geben kristalline Peroxyde.
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  • 97
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    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1237-1237 
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
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  • 98
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    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1239-1246 
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Tetrahydroxy-p-benzochinon zeigt einige Eigenschaften, die es als „doppeltes aci-Redukton“ erscheinen lassen. So erleidet es „Diazo-Spaltung“ unter Bildung von Mesoxalsäure-bis-arylhydrazid. Diazomethan verwandelt es in den Tetramethyläther, der leicht, sogar durch den Ausgangsstoff, zum entspr. Hydrochinon reduziert wird. Es werden noch Acetyl- und Aminoderivate des Tetrahydroxy-p-benzochinons und seines Dimethyläthers beschrieben sowie die UV- und IR-Spektren diskutiert.
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  • 99
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    Weinheim : Wiley-Blackwell
    Berichte der deutschen chemischen Gesellschaft 92 (1959), S. 1276-1287 
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Ausgehend von den in der ersten Veröffentlichung(1) beschriebenen Substanzen wurden Derivate der folgenden Peptide synthetisiert: Glycyl-L-glutaminsäure, Glycyl-glycyl-L-glutaminsäure, γ-L-Glutamyl-glycin, α- und γ-L-Glutamylglycyl-L-glutaminsäure, α- und γ-L-Glutamyl-α-L-glutamyl-glycin und α-L-Glutamyl-L-tyrosin. Auch einige freie Peptide konnten erhalten werden. Als interessante Nebenprodukte der Peptidsynthese über gemischte Anhydride mit Kohlensäure-halbestern wurden in zwei Fällen Diacylimide erhalten.
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  • 100
    ISSN: 0009-2940
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Notes: Beim Behandeln von N-Benzoyl-D-glucosamin (IV) mit chlorwasserstoffhaltigem Aceton entsteht das Acetonderivat VII eines Phenyloxazolins, welches Furanosestruktur besitzt. Dieses wird mit chlorwasserstoffhaltigem Methanol in das entsprechende Aceton-β-methylfuranosid IX und anschließend in das acetonfreie β-Methylfuranosid X umgewandelt.  -  Behandeln von O-Tetraacetyl-N-carbobenzoxy-D-glucosamin (XI) mit TiCl4 oder mit AlCl3/PCl5 führt unter Abspaltung von Benzylchlorid zur Bildung eines Oxazolonderivates (XIII).
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