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  • 1
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    Development and flight test of a deployable precision landing system (1994)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: A joint NASA Dryden Flight Research Facility and Johnson Space Center program was conducted to determine the feasibility of the autonomous recovery of a spacecraft using a ram-air parafoil system for the final stages of entry from space that included a precision landing. The feasibility of this system was studied using a flight model of a spacecraft in the generic shape of a flattened biconic that weighed approximately 150 lb and was flown under a commercially available, ram-air parachute. Key elements of the vehicle included the Global Positioning System guidance for navigation, flight control computer, ultrasonic sensing for terminal altitude, electronic compass, and onboard data recording. A flight test program was used to develop and refine the vehicle. This vehicle completed an autonomous flight from an altitude of 10,000 ft and a lateral offset of 1.7 miles that resulted in a precision flare and landing into the wind at a predetermined location. At times, the autonomous flight was conducted in the presence of winds approximately equal to vehicle airspeed. Several novel techniques for computing the winds postflight were evaluated. Future program objectives are also presented.
    Keywords: AIRCRAFT COMMUNICATIONS AND NAVIGATION
    Type: Journal of Aircraft (ISSN 0021-8669); 31; 5; p. 1101-1108
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    A Correlation Between Flight-Determined Derivatives and Wind-Tunnel Data for the X-24B Research Aircraft (1997)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Longitudinal and lateral-directional estimates of the aerodynamic derivatives of the X-24B research aircraft were obtained from flight data by using a modified maximum likelihood estimation method. Data were obtained over a Mach number range from 0.35 to 1.72 and over an angle of attack range from 3.5 deg. to 15.7 deg. Data are presented for a subsonic and transonic configuration. The flight derivatives were generally consistent and documented the aircraft well. The correlation between the flight data and wind-tunnel predictions is presented and discussed.
    Keywords: Aircraft Stability and Control
    Type: NASA-TM-113084 , H-2173 , NAS 1.15:113084
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Flight characteristics of a modified Schweizer SGS1-36 sailplane at low and very high angles of attack (1990)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A manned flight research program using a modified sailplane was conducted to very high angles of attack at the NASA-Ames. Piloting techniques were established that enabled the pilot to attain and stabilize on an angle of attack in the 30 to 72 deg range. Aerodynamic derivatives were estimated from the flight data for both low and very high angles of attack and are compared to wind tunnel data. In addition, limited performance and trim data are presented.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TP-3022 , H-1563 , NAS 1.60:3022
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Flight characteristics of the AD-1 oblique-wing research aircraft (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The AD-1 is a low-speed oblique-wing research airplane. This report reviews the vehicle's basic flight characteristics, including many aerodynamic, stability, and control effects that are unique to an oblique-wing configuration. These effects include the change in sideforce with angle of attack, moment changes with angle of attack and load factor, initial stall on the trailing wing, and inertial coupling caused by a roll-pitch cross product of inertia. An assessment of the handling qualities includes pilot ratings and comments. Ratings were generally satisfactory through 30 deg of wing sweep but degraded with increased sweep. A piloted simulation study indicated that a basic rate feedback control system could be used to improve the handling qualities at higher wing sweeps.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TP-2223 , H-1180 , NAS 1.60:2223
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    The development and flight test of a deployable precision landing system for spacecraft recovery (1993)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A joint NASA Dryden Flight Research Facility and Johnson Space Center program was conducted to determine the feasibility of the autonomous recovery of a spacecraft using a ram-air parafoil system for the final stages of entry from space that included a precision landing. The feasibility of this system was studied using a flight model of a spacecraft in the generic shape of a flattened biconic which weighed approximately 150 lb and was flown under a commercially available, ram-air parachute. Key elements of the vehicle included the Global Positioning System guidance for navigation, flight control computer, ultrasonic sensing for terminal altitude, electronic compass, and onboard data recording. A flight test program was used to develop and refine the vehicle. This vehicle completed an autonomous flight from an altitude of 10,000 ft and a lateral offset of 1.7 miles which resulted in a precision flare and landing into the wind at a predetermined location. At times, the autonomous flight was conducted in the presence of winds approximately equal to vehicle airspeed. Several techniques for computing the winds postflight were evaluated. Future program objectives are also presented.
    Keywords: SPACE TRANSPORTATION
    Type: NASA-TM-4525 , H-1933 , NAS 1.15:4525
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Modeling, simulation, and flight characteristics of an aircraft designed to fly at 100,000 feet (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A manned real time simulation of a conceptual vehicle, the stratoplane, was developed to study the problems associated with the flight characteristics of a large, lightweight vehicle. Mathematical models of the aerodynamics, mass properties, and propulsion system were developed in support of the simulation and are presented. The simulation was at first conducted without control augmentation to determine the needs for a control system. The unaugmented flying qualities were dominated by lightly damped dutch roll oscillations. Constant pilot workloads were needed at high altitudes. Control augmentation was studied using basic feedbacks. For the longitudinal axis, flight path angle, and pitch rate feedback were sufficient to damp the phugoid mode and to provide good flying qualities. In the lateral directional axis, bank angle, roll rate, and yaw rate feedbacks were sufficient to provide a safe vehicle with acceptable handling qualities. Intentionally stalling the stratoplane to very high angles of attack (deep stall) was studied as a means of enable safe and rapid descent. It was concluded that the deep stall maneuver is viable for this class of vehicle.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TM-104236 , H-1731 , NAS 1.15:104236
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Further development and flight test of an autonomous precision landing system using a parafoil (1994)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: NASA Dryden Flight Research Center and NASA Johnson Space Center are jointly conducting a phased program to determine the feasibility of the autonomous recovery of a spacecraft using a ram-air parafoil system for the final stages of entry from space to a precision landing. The feasibility is being studied using a flight model of a spacecraft in the generic shape of a flattened biconic that weighs approximately 120 lb and is flown under a commercially available ram-air parafoil. Key components of the vehicle include the global positioning system (GPS) guidance for navigation, a flight control computer, an electronic compass, a yaw rate gyro, and an onboard data recorder. A flight test program is being used to develop and refine the vehicle. The primary flight goal is to demonstrate autonomous flight from an altitude of 3,000 m (10,000 ft) with a lateral offset of 1.6 km (1.0 mi) to a precision soft landing. This paper summarizes the progress to date. Much of the navigation system has been tested, including a heading tracker that was developed using parameter estimation techniques and a complementary filter. The autoland portion of the autopilot is still in development. The feasibility of conducting the flare maneuver without servoactuators was investigated as a means of significantly reducing the servoactuator rate and load requirements.
    Keywords: AERODYNAMICS
    Type: NASA-TM-4599 , H-1987 , NAS 1.15:4599 , AIAA PAPER 94-2141 , Biennial Flight Test Conference; Jun 20, 1994 - Jun 23, 1994; Colorado Springs, CO; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    A Correlation Between Flight-Determined Derivatives and Wind-Tunnel Data for the X-24B Research Aircraft (1976)
    In:  CASI
    Details
    Publication Date: 2019-08-26
    Description: Longitudinal and lateral-directional estimates of the aerodynamic derivatives of the X-24B research aircraft were obtained from flight data by using a modified maximum likelihooa estimation method. Data were obtained over a Mach number range from 0.35 to 1.72 and over an angle of attack range from 3.5deg to 15.7deg. Data are presented for a subsonic and a transonic configuration. The flight derivatives were generally consistent and documented the aircraft well. The correlation between the flight data and wind-tunnel predictions is presented and discussed.
    Keywords: Aerodynamics
    Type: NASA-SX-3371 , F-791
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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