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  • Engineering  (47)
  • SPACECRAFT DESIGN, TESTING AND PERFORMANCE  (45)
  • Inorganic Chemistry
  • 2020-2022
  • 2010-2014
  • 1985-1989  (125)
  • 1950-1954
  • 1930-1934
  • 1920-1924
  • 1988  (125)
Collection
Keywords
Publisher
Years
  • 2020-2022
  • 2010-2014
  • 1985-1989  (125)
  • 1950-1954
  • 1930-1934
    • +
Year
  • 1
    Electronic Resource
    Electronic Resource
    Two dimensional combined convection in vertical parallel plate ducts, including situations of flow reversal (1988)
    Chichester [u.a.] : Wiley-Blackwell
    International Journal for Numerical Methods in Engineering 26 (1988), S. 1645-1664 
    Details
    ISSN: 0029-5981
    Keywords: Engineering ; Engineering General
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Mathematics , Technology
    Notes: Numerical solutions are presented for the problem of steady laminar combined convection flows in vertical parallel plate ducts. Axial diffusion is neglected in the analysis and the resulting governing equations, which are of a parabolic nature, are expressed in an implicit finite difference scheme using a vorticity-stream function formulation and are solved using a marching technique. A constant wall temperature boundary condition is used and investigations are restricted to the case Pr = 0.72. A large range of values of the ratio Gr/Re is considered, -300 ≤ Gr/Re ≤ 70, and comparisons are made with the case of pure forced convection. For large values of the ratio |Gr/Re| reverse flow occurs in the duct. A modification to the standard marching technique is introduced and complete solutions are achieved for these situations for the first time. Results are presented in terms of velocity profiles, Nusselt numbers, friction factors and temperature distributions.
    Additional Material: 10 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/nme.1620260713
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    Paper (German National Licenses)
    Fulltext
  • 2
    Electronic Resource
    Electronic Resource
    Darstellung und Reaktionen von methylenverbrückten Phosphor(III)-Phosphor(V)-Verbindungen (1988)
    Weinheim : Wiley-Blackwell
    Zeitschrift für anorganische Chemie 566 (1988), S. 90-102 
    Details
    ISSN: 0044-2313
    Keywords: Chemistry ; Inorganic Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology
    Description / Table of Contents: Preparation and Reactions of Methylene-bridged Phosphorus(III)-Phosphorus(V) CompoundsThe synthesis of methylene-bridged diphosphorus compounds of the type Y2PCH2P(S)X2 (with Y = F, Cl, OPri, NMe2, Ph) is reported. Reactions of these compounds with bicycloheptadiene-metaltetracarbonyls to form complexes of the type (L—L′)M(CO)4 and (L—L′)2M(CO)4, respectively, as well as some oxidation reactions and the conversion of the phosphine F2PCH2P(S)F2 to the cyclotetraphosphine [PCH2P(S)F2]4 are described.
    Notes: Über die Darstellung von methylenverbrückten Diphosphorverbindungen der Zusammensetzung Y2PCH2P(S)X2 (mit Y = F, Cl, OPri, NMe2, Ph; X = F, OPri, NMe2, Ph) wird berichtet. Umsetzungen der erhaltenen Verbindungen mit Bicycloheptadien-Metalltetracarbonylen zu Komplexen des Typs (L—L′)M(CO)4 bzw. (L—L′)2M(CO)4 (mit M = Cr, Mo, W), einige Oxidationsreaktionen und die Umwandlung des Phosphans F2PCH2P(S)F2 zum Cyclotetraphosphan [PCH2P(S)F2]4 werden beschrieben.
    Additional Material: 1 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/zaac.19885660113
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    Paper (German National Licenses)
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  • 3
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    Optimal experiment design for identification of large space structures (1988)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: The optimal experiment design for on-orbit identification of modal frequency and damping parameters in large flexible space structures is discussed. The main result is a separation principle for D-optimal design which states that under certain conditions the sensor placement problem is decoupled from the input design problem. This decoupling effect significantly simplifies the overall optimal experiment design determination for large MIMO structural systems with many unknown modal parameters. The error from using the uncoupled design is estimated in terms of the inherent damping of the structure. A numerical example is given, demonstrating the usefulness of the simplified criteria in determining optimal designs for on-orbit Space Station identification experiments.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Automatica (ISSN 0005-1098); 24; 357-364
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Navigation and pointing timeline development for an autonomous free-flying Shuttle payload (1988)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Guidance, Control, and Dynamics (ISSN 0731-5090); 11; 110-118
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Calculation of space station infrared irradiance from atmosphere-induced emissions (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The excitation mechanisms and radiance estimates over the 1 to 10 micron region for CO2(v), H2O(v), CO(v), OH(v), NO2(2B-2A) and N2(B3 pi - A3 sigma) are discussed. The infrared irradiance of the Space Station at an altitude of 460 km was estimated. The surface material was presumed to be non-carbonaceous and inert. The determined number densities of the various gases relevant to the Space Station from both ambient and outgassing sources are presented. A model for the production of and emission from the infrared active molecules was constructed that considers two classes of production processes: (1) gas phase excitation of molecules in the near Station environment by collision with ambient flux; and (2) surface processes that lead to molecular excitation. A composite spectrum of all major emitting species shows that the observed irradiance is non-uniform over the 1 to 8 micron region. The comparison of predicted irradiance with the zodiacal background indicates that the Space Station infrared background from atmosphere-induced emissions may be a problem of consequence.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA, Langley Research Center, A Study of Space Station Contamination Effects; p 61-69
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    An application of high authority/low authority control and positivity (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Control Dynamics Company (CDy), in conjunction with NASA Marshall Space Flight Center (MSFC), has supported the U.S. Air Force Wright Aeronautical Laboratory (AFWAL) in conducting an investigation of the implementation of several DOD controls techniques. These techniques are to provide vibration suppression and precise attitude control for flexible space structures. AFWAL issued a contract to Control Dynamics to perform this work under the Active Control Technique Evaluation for Spacecraft (ACES) Program. The High Authority Control/Low Authority Control (HAC/LAC) and Positivity controls techniques, which were cultivated under the DARPA Active Control of Space Structures (ACOSS) Program, were applied to a structural model of the NASA/MSFC Ground Test Facility ACES configuration. The control systems design were accomplished and linear post-analyses of the closed-loop systems are provided. The control system designs take into account effects of sampling and delay in the control computer. Nonlinear simulation runs were used to verify the control system designs and implementations in the facility control computers. Finally, test results are given to verify operations of the control systems in the test facility.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-100338 , NAS 1.15:100338
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Simulation of launch and re-entry acceleration profiles for testing of Shuttle and unmanned microgravity research payloads (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: A procedure was developed for the simulation of the launch and reentry acceleration profiles of the Space Shuttle (3.3 and 1.7 g maximum, respectively) and of two versions of NASA's proposed materials research Reusable Reentry Satellite (RRS) (8 and 4 g maximum, respectively). With a 7-m centrifuge, the time dependence of five different acceleration episodes was simulated for payload masses up to 59 kg. Test results obtained for the Materials Dispersion Apparatus, a commercial low-cost payload device, are presented.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Advances in Space Research (ISSN 0273-1177); 8; 12 1; 141-146
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Microprocessor controlled force actuator (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Guidance, Control, and Dynamics (ISSN 0731-5090); 11; 230-236
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    A new momentum management controller for the Space Station (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A new approach to CMG (control moment gyro) momentum management and attitude control of the Space Station is developed. The control algorithm utilizes both the gravity-gradient and gyroscopic torques to seek torque equilibrium attitude in the presence of secular and cyclic disturbances. Depending upon mission requirements, either pitch attitude or pitch-axis CMG momentum can be held constant; yaw attitude and roll-axis CMG momentum can be held constant, while roll attitude and yaw-axis CMG momentum cannot be held constant. As a result, the overall attitude and CMG momentum oscillations caused by cyclic aero-dynamic disturbances are minimized. A state feedback controller with minimal computer storage requirement for gain scheduling is also developed. The overall closed-loop system is stable for + or - 30 percent inertia matrix variations and has more than + or - 10 dB and 45 deg stability margins in each loop.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 88-4132 , AIAA Guidance, Navigation and Control Conference; Aug 15, 1988 - Aug 17, 1988; Minneapolis, MN; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    An intelligent, free-flying robot (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The ground-based demonstration of EVA Retriever, a voice-supervised, intelligent, free-flying robot, is designed to evaluate the capability to retrieve objects (astronauts, equipment, and tools) which have accidentally separated from the Space Station. The major objective of the EVA Retriever Project is to design, develop, and evaluate an integrated robotic hardware and on-board software system which autonomously: (1) performs system activation and check-out, (2) searches for and acquires the target, (3) plans and executes a rendezvous while continuously tracking the target, (4) avoids stationary and moving obstacles, (5) reaches for and grapples the target, (6) returns to transfer the object, and (7) returns to base.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Space Station Automation IV; Nov 07, 1988 - Nov 09, 1988; Cambridge, MA; United States
    Format: text
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    NASA TECHNICAL REPORTS
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