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  • 1
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    NASA Ames Active Control Aircraft flight experiments (ACA) program (1975)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: The objectives of the Ames ACA program are to develop the active control technology (ACT) for short-haul aircraft, to evaluate existing methods, to develop new techniques, and to demonstrate the readiness of the technology in operational environment. Two concepts are basic to ACT: integrated aircraft design and integrated flight-control-system design.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: Systems Reliability Issues for Future Aircraft; p 21-26
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Nonlinear systems approach to control system design (1984)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Consider some of the control system design methods for plants with nonlinear dynamics. If the nonlinearity is weak relative to the size of the operating region, then the linear methods apply directly. Fixed-gain design may be feasible even for significant nonlinearities. It may be possible to find a single gain which provides adequate control of the linear models at several perturbation points. If the nonlinearity is restricted to a sector, that fact may be used to obtain a fixed-gain controller. Otherwise, a gain may have to be associated with each perturbation point Pi. A gain schedule K(p(v)) is obtained by connecting the perturbation points by a function, say p(v), of the scheduling parameter v (i.e., speed). When the scheduling parameter must be multidimensional, this approach is difficult; the objective is to develop an easier procedure.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA. Langley Research Center NASA Aircraft Controls Research, 1983; p 329-341
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Application of Nonlinear Systems Inverses to Automatic Flight Control Design: System Concepts and Flight Evaluations (1981)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: A practical method for the design of automatic flight control systems for aircraft with complex characteristics and operational requirements, such as the powered lift STOL and V/STOL configurations, is presented. The method is effective for a large class of dynamic systems requiring multi-axis control which have highly coupled nonlinearities, redundant controls, and complex multidimensional operational envelopes. It exploits the concept of inverse dynamic systems, and an algorithm for the construction of inverse is given. A hierarchic structure for the total control logic with inverses is presented. The method is illustrated with an application to the Augmentor Wing Jet STOL Research Aircraft equipped with a digital flight control system. Results of flight evaluation of the control concept on this aircraft are presented.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AGARD Theory and Appl. of Optimal Control in Aerospace Systems; 29 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Methodology for design of active controls for V/STOL aircraft (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: An effort to develop techniques for the design of integrated, fully automatic flight control systems for powered lift STOL and VTOL aircraft is described. The structure is discussed of the control system which has been developed to deal with the strong nonlinearities inherent in this class of aircraft, to admit automatic coupling with the advanced ATC requiring accurate execution of complex trajectories, and to admit a variety of active control tasks. The specific case considered is the Augmentor Wing Research Aircraft.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: Advanced Control Technol. and its Potential for Future Transport Aircraft; p 923-931
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Nonlinear control of aircraft (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Transformations of nonlinear systems were used to design automatic flight controllers for vertical and short takeoff aircraft. Under the assumption that a nonlinear system can be mapped to a controllable linear system, a method using partial differential equations was constructed to approximate transformations in cases where exact ones cannot be found. An application of the design theory to a rotorcraft, the UH-1H helicopter, was presented.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TM-89225 , NAS 1.15:89225
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Aircraft automatic-flight-control system with inversion of the model in the feed-forward path using a Newton-Raphson technique for the inversion (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A new automatic flight control system concept suitable for aircraft with highly nonlinear aerodynamic and propulsion characteristics and which must operate over a wide flight envelope was investigated. This exact model follower inverts a complete nonlinear model of the aircraft as part of the feed-forward path. The inversion is accomplished by a Newton-Raphson trim of the model at each digital computer cycle time of 0.05 seconds. The combination of the inverse model and the actual aircraft in the feed-forward path alloys the translational and rotational regulators in the feedback path to be easily designed by linear methods. An explanation of the model inversion procedure is presented. An extensive set of simulation data for essentially the full flight envelope for a vertical attitude takeoff and landing aircraft (VATOL) is presented. These data demonstrate the successful, smooth, and precise control that can be achieved with this concept. The trajectory includes conventional flight from 200 to 900 ft/sec with path accelerations and decelerations, altitude changes of over 6000 ft and 2g and 3g turns. Vertical attitude maneuvering as a tail sitter along all axes is demonstrated. A transition trajectory from 200 ft/sec in conventional flight to stationary hover in the vertical attitude includes satisfactory operation through lift-cure slope reversal as attitude goes from horizontal to vertical at constant altitude. A vertical attitude takeoff from stationary hover to conventional flight is also demonstrated.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TM-88209 , A-2-86092 , NAS 1.15:88209
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Flight tests of the total automatic flight control system (Tafcos) concept on a DHC-6 Twin Otter aircraft (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Flight control systems capable of handling the complex operational requirements of the STOL and VTOL aircraft designs as well as designs using active control concepts are considered. Emphasis is placed on the total automatic flight control system (TACOS) (TAFCOS). Flight test results which verified the performance of the system concept are presented.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TP-1513 , A-7901
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Application of the concept of dynamic trim control to automatic landing of carrier aircraft (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results of a simulation study of an alternative design concept for an automatic landing control system are presented. The alternative design concept for an automatic landing control system is described. The design concept is the total aircraft flight control system (TAFCOS). TAFCOS is an open loop, feed forward system that commands the proper instantaneous thrust, angle of attack, and roll angle to achieve the forces required to follow the desired trajector. These dynamic trim conditions are determined by an inversion of the aircraft nonlinear force characteristics. The concept was applied to an A-7E aircraft approaching an aircraft carrier. The implementation details with an airborne digital computer are discussed. The automatic carrier landing situation is described. The simulation results are presented for a carrier approach with atmospheric disturbances, an approach with no disturbances, and for tailwind and headwind gusts.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TP-1512 , A-7801
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    A formal structure for advanced automatic flight-control systems (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Techniques were developed for the unified design of multimode, variable authority automatic flight-control systems for powered-lift STOL and VTOL aircraft. A structure for such systems is developed to deal with the strong nonlinearities inherent in this class of aircraft, to admit automatic coupling with advanced air traffic control, and to admit a variety of active control tasks. The aircraft being considered is the augmentor wing jet STOL research aircraft.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TN-D-7940 , A-5710
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Application of nonlinear transformations to automatic flight control (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The theory of transformations of nonlinear systems to linear ones is applied to the design of an automatic flight controller for the UH-1H helicopter. The helicopter mathematical model is described and it is shown to satisfy the necessary and sufficient conditions for transformability. The mapping is constructed, taking the nonlinear model to canonical form. The performance of the automatic control system in a detailed simulation on the flight computer is summarized.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: Automatica (ISSN 0005-1098); 20; 103-107
    Format: text
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    NASA TECHNICAL REPORTS
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