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  • 1
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    Enabling Advanced Wind-Tunnel Research Methods Using the NASA Langley 12-Foot Low Speed Tunnel (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Design of Experiment (DOE) testing methods were used to gather wind tunnel data characterizing the aerodynamic and propulsion forces and moments acting on a complex vehicle configuration with 10 motor-driven propellers, 9 control surfaces, a tilt wing, and a tilt tail. This paper describes the potential benefits and practical implications of using DOE methods for wind tunnel testing - with an emphasis on describing how it can affect model hardware, facility hardware, and software for control and data acquisition. With up to 23 independent variables (19 model and 2 tunnel) for some vehicle configurations, this recent test also provides an excellent example of using DOE methods to assess critical coupling effects in a reasonable timeframe for complex vehicle configurations. Results for an exploratory test using conventional angle of attack sweeps to assess aerodynamic hysteresis is summarized, and DOE results are presented for an exploratory test used to set the data sampling time for the overall test. DOE results are also shown for one production test characterizing normal force in the Cruise mode for the vehicle.
    Keywords: Aircraft Design, Testing and Performance
    Type: AIAA Paper-2014-3000 , NF1676L-17827 , AIAA Aviation Technology, Integration and Operations (ATIO) Conference; Jun 16, 2014 - Jun 20, 2014; Atlanta, GA; United States|AIAA Aviation and Aeronautics Forum and Exposition (AVIATION 2014); Jun 16, 2014 - Jun 20, 2014; Atlanta, GA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    The Aerial Regional-Scale Environmental Surveyor (ARES): New Mars Science to Reduce Human Risk and Prepare for the Human Exploration (2012)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Obtaining critical measurements for eventual human Mars missions while expanding upon recent Mars scientific discoveries and deriving new scientific knowledge from a unique near surface vantage point is the focus of the Aerial Regional-scale Environmental Surveyor (ARES) exploration mission. The key element of ARES is an instrumented,rocket-powered, well-tested robotic airplane platform, that will fly between one to two kilometers above the surface while traversing hundreds of kilometers to collect and transmit previously unobtainable high spatial measurements relevant to the NASA Mars Exploration Program and the exploration of Mars by humans.
    Keywords: Lunar and Planetary Science and Exploration
    Type: Paper No. 4086 , NF1676L-14788 , Workshop on Concepts and Approaches for Mars Exploration; Jun 12, 2012 - Jun 14, 2012; Houston, TX; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Flight Simulation of ARES in the Mars Environment (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: A report discusses using the Aerial Regional- scale Environmental Survey (ARES) light airplane as an observation platform on Mars in order to gather data. It would have to survive insertion into the atmosphere, fly long enough to meet science objectives, and provide a stable platform. The feasibility of such a platform was tested using the Langley Standard Real- Time Simulation in C++. The unique features of LaSRS++ are: full, six-degrees- of-freedom flight simulation that can be used to evaluate the performance of the aircraft in the Martian environment; capability of flight analysis from start to finish; support of Monte Carlo analysis of aircraft performance; and accepting initial conditions from POST results for the entry and deployment of the entry body. Starting with a general aviation model, the design was tweaked to maintain a stable aircraft under expected Martian conditions. Outer mold lines were adjusted based on experience with the Martian atmosphere. Flight control was modified from a vertical acceleration control law to an angle-of-attack control law. Navigation was modified from a vertical acceleration control system to an alpha control system. In general, a pattern of starting with simple models with well-understood behaviors was selected and modified during testing.
    Keywords: Man/System Technology and Life Support
    Type: LAR-17458 , NASA Tech Briefs, August 2011; 33
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Aircraft Configured for Flight in an Atmosphere Having Low Density (2012)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: An aircraft is configured for flight in an atmosphere having a low density. The aircraft includes a fuselage, a pair of wings, and a rear stabilizer. The pair of wings extends from the fuselage in opposition to one another. The rear stabilizer extends from the fuselage in spaced relationship to the pair of wings. The fuselage, the wings, and the rear stabilizer each present an upper surface opposing a lower surface. The upper and lower surfaces have X, Y, and Z coordinates that are configured for flight in an atmosphere having low density.
    Keywords: Aircraft Design, Testing and Performance
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    NASA Langley Distributed Propulsion VTOL Tilt-Wing Aircraft Testing, Modeling, Simulation, Control, and Flight Test Development (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Control of complex Vertical Take-Off and Landing (VTOL) aircraft traversing from hovering to wing born flight mode and back poses notoriously difficult modeling, simulation, control, and flight-testing challenges. This paper provides an overview of the techniques and advances required to develop the GL-10 tilt-wing, tilt-tail, long endurance, VTOL aircraft control system. The GL-10 prototype's unusual and complex configuration requires application of state-of-the-art techniques and some significant advances in wind tunnel infrastructure automation, efficient Design Of Experiments (DOE) tunnel test techniques, modeling, multi-body equations of motion, multi-body actuator models, simulation, control algorithm design, and flight test avionics, testing, and analysis. The following compendium surveys key disciplines required to develop an effective control system for this challenging vehicle in this on-going effort.
    Keywords: Aircraft Stability and Control
    Type: AIAA Paper 2014-2999 , NF1676L-17842 , AIAA Aviation Technology, Integration and Operations (ATIO) 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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