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  • 1
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    Change Detection Experiments Using Low Cost UAVs (2005)
    In:  CASI
    Details
    Publication Date: 2019-07-27
    Description: This paper presents the progress in the development of a low-cost change-detection system. This system is being developed to provide users with the ability to use a low-cost unmanned aerial vehicle (UAV) and image processing system that can detect changes in specific fixed ground locations using video provided by an autonomous UAV. The results of field experiments conducted with the US Army at Ft. A.P.Hill are presented.
    Keywords: Aircraft Design, Testing and Performance
    Type: Infotech@Aerospace; 26-29 Sept. 2005; Arlington, VA; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Design, Development, and Testing of a Compound Wing V/TOL small UAS (2015)
    In:  CASI
    Details
    Publication Date: 2019-07-19
    Description: This paper discusses the development and testing of an innovative small UAS (Unmanned Aircraft System). The design of the vehicle was driven by the need to both have long endurance yet still have the convenience of V/TOL (Vertical Take-Off and Landing) operation. The paper discusses some of the design considerations and configurations evaluated in searching for a configuration that met the demanding mission requirements. The paper also discusses some aspects of the compound wing and experimental testing conducted to discern the optimum parameters for the wing's design. The paper discusses the results of the preliminary flight testing and outlines further research to be conducted.
    Keywords: Aircraft Design, Testing and Performance
    Type: NF1676L-19089 , SciTech 2015; Jan 05, 2015 - Jan 09, 2015; Kissimmee, FL; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Proceedings of the Non-Linear Aero Prediction Requirements Workshop (1994)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The purpose of the Non-Linear Aero Prediction Requirements Workshop, held at NASA Langley Research Center on 8-9 Dec. 1993, was to identify and articulate requirements for non-linear aero prediction capabilities during conceptual/preliminary design. The attendees included engineers from industry, government, and academia in a variety of aerospace disciplines, such as advanced design, aerodynamic performance analysis, aero methods development, flight controls, and experimental and theoretical aerodynamics. Presentations by industry and government organizations were followed by panel discussions. This report contains copies of the presentations and the results of the panel discussions.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CP-10138 , NAS 1.55:10138 , Dec 08, 1993 - Dec 09, 1993; Hampton, VA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Examination of Frameworks for Safe Integration of Intelligent Small UAS into the NAS (2012)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper discusses a proposed framework for the safe integration of small unmanned aerial systems (sUAS) into the National Airspace System (NAS). The paper briefly examines the potential uses of sUAS to build an understanding of the location and frequency of potential future flight operations based on the future applications of the sUAS systems. The paper then examines the types of systems that would be required to meet the application-level demand to determine "classes" of platforms and operations. A framework for categorization of the "intelligence" level of the UAS is postulated for purposes of NAS integration. Finally, constraints on the intelligent systems are postulated to ensure their ease of integration into the NAS.
    Keywords: Aircraft Design, Testing and Performance
    Type: AIAA 2012-0960 , NF1676L-12923 , 50th AIAA Aerospace Sciences Meeting and Exhibit; Jan 09, 2012 - Jan 12, 2012; Nashville, TN; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    A Framework for Safe Integration of Small UAS Into the NAS (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper discusses a proposed framework for the safe integration of small unmanned aerial systems (sUAS) into the National Airspace System (NAS). The paper examines the potential uses of sUAS to build an understanding of the location and frequency of potential future flight operations based on the future applications of the sUAS systems. The paper then examines the types of systems that would be required to meet the application-level demand to determine classes of platforms and operations. Finally, a framework is proposed for both airworthiness and operations that attempts to balance safety with utility for these important systems.
    Keywords: Air Transportation and Safety
    Type: NF1676L-12194 , 11th AIAA Aviation Technology, Integration, and Operations (ATIO) Conference; Sep 20, 2011 - Sep 22, 2011; Virginia Beach, VA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Compound Wing Vertical Takeoff and Landing Small Unmanned Aircraft System (2017)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Systems, methods, and devices are provided that enable robust operations of a small unmanned aircraft system (sUAS) using a compound wing. The various embodiments may provide a sUAS with vertical takeoff and landing capability, long endurance, and the capability to operate in adverse environmental conditions. In the various embodiments a sUAS may include a fuselage and a compound wing comprising a fixed portion coupled to the fuselage, a wing lifting portion outboard of the fixed portion comprising a rigid cross member and a controllable articulating portion configured to rotate controllable through a range of motion from a horizontal position to a vertical position, and a freely rotating wing portion outboard of the wing lifting portion and configured to rotate freely based on wind forces incident on the freely rotating wing portion.
    Keywords: Aircraft Design, Testing and Performance; Cybernetics, Artificial Intelligence and Robotics
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Development of Micro Air Reconnaissance Vehicle as a Test Bed for Advanced Sensors and Electronics (2002)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper describes the development of a Micro/Mini Air Reconnaissance Vehicle for advanced sensors and electronics at NASA Langley Research Center over the last year. This vehicle is expected to have a total weight of less than four pounds, a design velocity of 40 mph, an endurance of 15-20 minutes, and a maximum range of 5km. The vehicle has wings that are simple to detach yet retain the correct alignment. The upper fuselage surface has a quick release hatch used to access the interior and also to mount the varying propulsion systems. The sensor suite developed for this vehicle consists of a Pitot-static measurement system for determining air speed, an absolute pressure measurement for determining altitude, magnetic direction measurement, and three orthogonal gyros to determine body angular rates. Swarming GPS-guidance and in-flight maneuvering is discussed, as well as design and installation of some other advance sensors like MEMS microphones, infrared cameras, GPS, humidity sensors, and an ultrasonic sonar sensor. Also low cost, small size, high performance control and navigation system for the Micro Air Vehicle is discussed. At the end, laboratory characterization of different sensors, motors, propellers, and batteries will be discussed.
    Keywords: Aircraft Design, Testing and Performance
    Type: AIAA Paper 2002-3411 , 1st AIAA Unmanned Aerospace Vehicles, Systems, Technologies and Operations Technical Conference and Workshop; May 20, 2002 - May 23, 2002; Portsmouth, VA; United States
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    NASA TECHNICAL REPORTS
  • 8
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    Small UAV Research and Evolution in Long Endurance Electric Powered Vehicles (2007)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper describes recent research into the advancement of small, electric powered unmanned aerial vehicle (UAV) capabilities. Specifically, topics include the improvements made in battery technology, design methodologies, avionics architectures and algorithms, materials and structural concepts, propulsion system performance prediction, and others. The results of prototype vehicle designs and flight tests are discussed in the context of their usefulness in defining and validating progress in the various technology areas. Further areas of research need are also identified. These include the need for more robust operating regimes (wind, gust, etc.), and continued improvement in payload fraction vs. endurance.
    Keywords: Aircraft Propulsion and Power
    Type: AIAA 2007-2730 , Infotech@Aerospace 2007 Conference and Exhibit; May 07, 2007 - May 10, 2007; Rohnert Park, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    An assessment of mission and configuration variations on multi-role fighter/attack aircraft concepts (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This paper presents the results of a series of configuration studies conducted in connection with the NASA agility design study project. The purpose of these in-house studies was to develop a parametric data base of configuration concepts and resulting mission performances for a variety of notional fighter/attack missions. This data base will then be used to assess the impact of the imposition of agility requirements on these configurations. Three vehicle concepts were evaluated, and resulting vehicle sizes, weights, and mission performances were compared. Each configuration was then optimized for varying mission requirements and technology levels. It was found that small variations in mission requirements can have significant impact on the design choices. It was also found that optimization of engine cycle variables results in significant improvements in take-off gross weight and vehicle performance regardless of the concept being explored. Finally, results indicate that signature considerations such as internal vs. external weapons carriage can cause dramatic changes in vehicle size, weight, and mission performance.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 93-1177 , ; 8 p.|AIAA, AHS, and ASEE, Aerospace Design Conference; Feb 16, 1993 - Feb 19, 1993; Irvine, CA; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Experimental Optimization of a Free-to-Rotate Wing for Small UAS (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper discusses an experimental investigation conducted to optimize a free-to-rotate wing for use on a small unmanned aircraft system (UAS). Although free-to-rotate wings have been used for decades on various small UAS and small manned aircraft, little is known about how to optimize these unusual wings for a specific application. The paper discusses some of the design rationale of the basic wing. In addition, three main parameters were selected for "optimization", wing camber, wing pivot location, and wing center of gravity (c.g.) location. A small apparatus was constructed to enable some simple experimental analysis of these parameters. A design-of-experiment series of tests were first conducted to discern which of the main optimization parameters were most likely to have the greatest impact on the outputs of interest, namely, some measure of "stability", some measure of the lift being generated at the neutral position, and how quickly the wing "recovers" from an upset. A second set of tests were conducted to develop a response-surface numerical representation of these outputs as functions of the three primary inputs. The response surface numerical representations are then used to develop an "optimum" within the trade space investigated. The results of the optimization are then tested experimentally to validate the predictions.
    Keywords: Aerodynamics
    Type: AIAA Paper 2014-2273 , NF1676L-17724 , AIAA Applied Aerodynamics Conference; Jun 16, 2014 - Jun 20, 2014; Atlanta, GA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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