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  • 1
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    Robust, Decoupled, Flight Control Design with Rate Saturating Actuators (1997)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Techniques for the design of control systems for manually controlled, high-performance aircraft must provide the following: (1) multi-input, multi-output (MIMO) solutions, (2) acceptable handling qualities including no tendencies for pilot-induced oscillations, (3) a tractable approach for compensator design, (4) performance and stability robustness in the presence of significant plant uncertainty, and (5) performance and stability robustness in the presence actuator saturation (particularly rate saturation). A design technique built upon Quantitative Feedback Theory is offered as a candidate methodology which can provide flight control systems meeting these requirements, and do so over a considerable part of the flight envelope. An example utilizing a simplified model of a supermaneuverable fighter aircraft demonstrates the proposed design methodology.
    Keywords: Aircraft Stability and Control
    Type: NASA/CR-97-207152 , NAS 1.26:207152 , AIAA Paper 97-3778
    Format: application/pdf
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  • 2
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    Nonlinear inversion flight control for a supermaneuverable aircraft (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: Journal of Guidance, Control, and Dynamics (ISSN 0731-5090); 15; 4 Ju; 976-984
    Format: text
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  • 3
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    Flight Control System Design with Rate Saturating Actuators (1997)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Actuator rate saturation is an important factor adversely affecting the stability and performance of aircraft flight control systems. It has been identified as a catalyst in pilot-induced oscillations, some of which have been catastrophic. A simple design technique is described that utilizes software rate limiters to improve the performance of control systems operating in the presence of actuator rate saturation. As described, the technique requires control effectors to be ganged such that any effector is driven by only a single compensated error signal. Using an analysis of the steady-state behavior of the system, requirements are placed upon the type of the loop transmissions and compensators in the proposed technique. Application of the technique to the design of a multi-input/multi-output, lateral-directional control system for a simple model of a high-performance fighter is demonstrated as are the stability and performance improvements that can accrue with the technique.
    Keywords: Aircraft Stability and Control
    Type: NASA/CR-97-207117 , NAS 1.26:207117 , Journal of Guidance, Control and Dynamics; 20; 1; 90-96
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  • 4
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    Optimization of lateral-directional dynamics for an aircraft operating at high angle of attack (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: In this paper, the control laws for the lateral-directional dynamics of a supermaneuverable aircraft is analyzed with a view to reducing the levels of lateral acceleration and sideslip, which are encountered during aggressive rolling maneuvers at high angles of attack. The analysis uses a linearized model of the lateral-directional dynamics and thus H-free-flow techniques can be applied. It is shown that trade-offs exist between simultaneously minimizing lateral acceleration measured at the pilot's station, ny(p), minimizing sideslip and minimizing tracking errors between the roll-rate about the velocity vector and its command. The paper concludes that a significant reduction in ny(p) is only attainable by compromising the roll-rate performance.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 91-2711 , AIAA Guidance, Navigation and Control Conference; Aug 12, 1991 - Aug 14, 1991; New Orleans, LA; United States
    Format: text
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  • 5
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    Preliminary assessment of the robustness of dynamic inversion based flight control laws (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Dynamic-inversion-based flight control laws present an attractive alternative to conventional gain-scheduled designs for high angle-of-attack maneuvering, where nonlinearities dominate the dynamics. Dynamic inversion is easily applied to the aircraft dynamics requiring a knowledge of the nonlinear equations of motion alone, rather than an extensive set of linearizations. However, the robustness properties of the dynamic inversion are questionable especially when considering the uncertainties involved with the aerodynamic database during post-stall flight. This paper presents a simple analysis and some preliminary results of simulations with a perturbed database. It is shown that incorporating integrators into the control loops helps to improve the performance in the presence of these perturbations.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 92-4330 , AIAA Guidance, Navigation and Control Conference; Aug 10, 1992 - Aug 12, 1992; Hilton Head Island, SC; United States
    Format: text
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  • 6
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    Nonlinear feedback control of highly manoeuvrable aircraft (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: This paper describes the application of nonlinear quadratic regulator (NLQR) theory to the design of control laws for a typical high-performance aircraft. The NLQR controller design is performed using truncated solutions of the Hamilton-Jacobi-Bellman equation of optimal control theory. The performance of the NLQR controller is compared with the performance of a conventional P + I gain scheduled controller designed by applying standard frequency response techniques to the equations of motion of the aircraft linearized at various angles of attack. Both techniques result in control laws which are very similar in structure to one another and which yield similar performance. The results of applying both control laws to a high-g vertical turn are illustrated by nonlinear simulation.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: International Journal of Control (ISSN 0020-7179); 56; 4; p. 799-812.
    Format: text
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