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  • 1
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    SIZE AND SHAPE FROM STELLAR OCCULTATION OBSERVATIONS OF THE DOUBLE JUPITER TROJAN PATROCLUS AND MENOETIUS (2015)
    Institute of Physics
    Details
    Publication Date: 2015-02-26
    Print ISSN: 0004-6256
    Electronic ISSN: 1538-3881
    Topics: Physics
    Published by Institute of Physics
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    PAPER CURRENT
  • 2
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    Evolution of C iv Absorbers. I. The Cosmic Incidence (2020)
    Institute of Physics
    Details
    Publication Date: 2020-11-20
    Print ISSN: 0004-637X
    Electronic ISSN: 1538-4357
    Topics: Physics
    Published by Institute of Physics
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    PAPER CURRENT
  • 3
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    Comparison of X-31 flight, wind-tunnel, and water-tunnel yawing moment asymmetries at high angles of attack (1994)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The X-31 aircraft are being used in the enhanced fighter maneuverability (EFM) research program, which is jointly funded by the (U.S.) Advanced Research Projects Agency (ARPA) and Germany's Federal Ministry of Defense (FMOD). The flight test portion of the program, which involves two aircraft, is being conducted by an International Test Organization (ITO) comprising the National Aeronautics and Space Administration (NASA), the U.S. Navy, the U.S. Air Force, Rockwell International, and Deutsche Aerospace (DASA). The goals of the flight program are to demonstrate EFM technologies, investigate close-in-combat exchange ratios, develop design requirements, build a database for application to future fighter aircraft, and develop and validate low-cost prototype concepts. For longitudinal control the X-31 uses canards, symmetrical movement of the trailing-edge flaps, and pitch deflection of the thrust vectoring system. The trim, inertial coupling, and engine gyroscopic coupling compensation tasks are performed primarily by the trailing-edge flaps. For lateral-directional control the aircraft uses differential deflection of the trailing-edge flaps for roll coordination and a conventional rudder combined with the thrust vectoring system to provide yaw control. The rudder is only effective up to about 40 deg angle of attack (alpha), after which the thrust vectoring becomes the primary yaw control effector. Both the leading-edge flaps and the inlet lip are scheduled with the angle of attack to provide best performance.
    Keywords: AERODYNAMICS
    Type: NASA. Dryden Flight Research Center, Fourth High Alpha Conference, Volume 1; p 21
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Comparison of X-31 Flight and Ground-Based Yawing Moment Asymmetries at High Angles of Attack (2003)
    In:  CASI
    Details
    Publication Date: 2018-06-28
    Description: Significant yawing moment asymmetries were encountered during the high-angle-of-attack envelope expansion of the two X-31 aircraft. These asymmetries caused position saturations of the thrust-vectoring vanes and trailing-edge flaps during some stability-axis rolling maneuvers at high angles of attack. The two test aircraft had different asymmetry characteristics, and ship 2 has asymmetries that vary as a function of Reynolds number. Several aerodynamic modifications have been made to the X-31 forebody with the goal of minimizing the asymmetry. These modifications include adding transition strips on the forebody and noseboom, using two different length strakes, and increasing nose bluntness. Ultimately, a combination of forebody strakes, nose blunting, and noseboom transition strips reduced the yawing moment asymmetry enough to fully expand the high-angle-of-attack envelope. Analysis of the X-31 flight data is reviewed and compared to wind-tunnel and water-tunnel measurements. Several lessons learned are outlined regarding high-angle-of-attack configuration design and ground testing.
    Keywords: Aircraft Design, Testing and Performance
    Type: Symposium on Advanced Flow Management. Part A: Vortex Flows and High Angle of Attack for Military Vehicles. Part B: Heat Transfer and Cooling in Propulsion and Power Systems; RTO-MP-069(I)-Pt-A-B
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Design of the ARES Mars Airplane and Mission Architecture (2006)
    In:  CASI
    Details
    Publication Date: 2018-06-11
    Description: Significant technology advances have enabled planetary aircraft to be considered as viable science platforms. Such systems fill a unique planetary science measurement gap, that of regional-scale, near-surface observation, while providing a fresh perspective for potential discovery. Recent efforts have produced mature mission and flight system concepts, ready for flight project implementation. This paper summarizes the development of a Mars airplane mission architecture that balances science, implementation risk and cost. Airplane mission performance, flight system design and technology maturation are described. The design, analysis and testing completed demonstrates the readiness of this science platform for use in a Mars flight project.
    Keywords: Lunar and Planetary Science and Exploration
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Dynamic model testing of the X-31 configuration for high-angle-of-attack flight dynamics research (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: High-angle-of-attack flight dynamics of the X-31 configuration were studied using dynamic model test techniques. These tests identified phenomena including wing rock, spins, and departures that could dominate the high-alpha behavior of the configuration and restrict its usable flight envelope. Results of these tests have been used to design flight control concepts and configuration modifications to minimize adverse effects of these phenomena. The conclusion of the high-alpha envelope expansion flight tests of the X-31 aircraft will complete the database against which the dynamic model results can be correlated.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 93-3674 , In: AIAA Atmospheric Flight Mechanics Conference, Monterey, CA, Aug. 9-11, 1993, Technical Papers (A93-48301 20-08); p. 488-506.
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Use of the updated NASA Langley radio-controlled drop-model technique for high-alpha studies of the X-29A configuration (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper presents an overview of the radio-controlled drop-model technique used for low-speed flight dynamics research at the NASA Langley Research Center. The overall test methodology is reviewed and the major elements of the system are discussed including model construction and equipment, the closed-loop control system, and the flight test facility. To illustrate the capabilities of the technique, selected results from an ongoing program to study the high-angle-of-attack flight dynamics of the X-29A configuration are reviewed. Three research areas are highlighted: motion prediction, control system effects, and motion analysis and modeling. Finally, several current upgrades to the overall technique are discussed along with the enhanced test capability that they will provide.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 87-2559
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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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
  • 9
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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
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    NASA TECHNICAL REPORTS
  • 10
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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
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