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Gain Scheduling with Guardian Maps for Longitudinal Flight control

JOURNAL OF GUIDANCE control AND DYNAMICS 2011年第4期34卷 1045-1059页

作者： Saussie, David Saydy, Lahcen Akhrif, Ouassima Berard, Caroline Ecole Polytech Montreal Dept Elect Engn Montreal PQ H3T 1J4 Canada Ecole Technol Super Dept Elect Engn Montreal PQ H3C 1K3 Canada Inst Super Aeronaut & Espace Dept Math Comp Sci & Control Theory F-31000 Toulouse France

A new approach to gain scheduling of linear controllers is proposed and applied to a longitudinal flight control problem. Traditionally, gain scheduling is done a posteriori by the interpolation of controller gains designed for several operating points or conditions. The method proposed here is based on guardian maps and does not require as many linear controller syntheses as there are design points. Rather, it extends the performance of an initial single controller carried out on an arbitrary operating point to the entire domain while ensuring generalized stability all along the process. The method, which uses a given fixed architecture controller, is successfully applied on the longitudinal flight control of a business jet aircraft.

关键词： Flight control Design Linear Time Invariant Downwash Angle Elevator Business Jets Aircrafts Flight Envelope Handling Qualities control augmentation system Polynomial Interpolation Damping Ratio

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Robust flight control system design using H_∞ loop-shaping and recessive trait crossover genetic algorithm

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EXPERT systemS WITH APPLICATIONS 2011年第1期38卷 169-174页

作者： El-Mahallawy, A. A. Yousef, H. A. El-Singaby, M. I. Madkour, A. A. Youssef, A. M. Sultan Qaboos Univ Dept Elect & Comp Engn Muscat 123 Oman Mil Tech Coll Cairo 11787 Egypt Arab Acad Sci & Technol Coll Engn & Technol Alexandria Egypt

A proposed approach to robust controller design is introduced. This approach combines the recessive trait crossover genetic algorithm with the loop-shaping design procedure using H-infinity synthesis. The requirements, design and simulation of a flight control system for precision tracking task are considered. The proposed method is applied to design a control system for the F-16 fighter aircraft model. The flight simulations reveal that the desired performance objectives are achieved and that the controller provides acceptable performance in spite of modeling errors and plant parameter variations. (C) 2010 Elsevier Ltd. All rights reserved.

关键词： Recessive trait crossover genetic algorithm H-infinity loop-shaping Flight simulations control augmentation system

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Non-linear simulation of controller for longitudinal control augmentation system of F-16 using numerical approach

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INFORMATION SCIENCES 2004年第1-4期164卷 47-60页

作者： Rachman, E Jaam, JM Hasnah, AM Univ Qatar Dept Comp Sci Coll Sci Doha Qatar Univ Sci Malaysia Sch Aerosp Engn George Town 14300 Malaysia

The non-linear simulation of controller for automatic flight control system is an essential part of the complete control design process. After using the linear approach in the design and simulation of the controller (control laws), it is important to simulate the controller on the non-linear real aircraft model. This simulation allows us to evaluate its functional performance during the real-time flight on the computer. The results of that process are used to determine whether the designed controller meets the design requirement and objective or not. The paper deals with application of numerical method fourth-order Runge-Kutta to simulate the function of the longitudinal-CAS controller that is embedded into the non-linear, six degree of freedom model of fighter F-16. A computer program is made to implement the numerical approach and to illustrate the result of that simulation on the computer. (C) 2003 Elsevier Inc. All rights reserved.

关键词： numerical method non-linear simulation control augmentation system

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Comparison of control and display augmentation for perspective flight-path displays

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JOURNAL OF GUIDANCE control AND DYNAMICS 2006年第3期29卷 564-578页

作者： Lam, T. M. Mulder, M. van Paassen, M. M. Mulder, J. A. Delft Univ Technol Fac Aerosp Engn Control & Stimulat Div NL-2629 HS Delft Netherlands

Manually performed piloting tasks with a perspective flight-path display require considerable effort. To improve this, display augmentation is used: additional symbology such as a flight-path predictor is added. An alternative approach would be to use control augmentation, using fly-by-wire techniques to simplify the control task of the pilot. A control-theoretical analysis of different display and control augmentation concepts is presented. It is shown how design techniques for flight directors can be applied to the analysis of display augmentation. The different concepts have also been tested in a piloted experiment, conducted in a high-fidelity moving-base flight simulator. Experimental results confirm the findings from the control-theoretical analysis. Overall, the control augmentation concepts outperform the display augmentation concepts: Pilot workload and control activity are strongly reduced with equal or better performance. These benefits become more apparent as the task difficulty increases.

关键词： Flight Path Display Test Pilots Flying Wires Flight Simulators Longitudinal control control augmentation system Flight control system Atmospheric Turbulence Aircraft Dynamics Feedback control Loop

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A STRATEGY FOR VEHICLE control augmentation VIA control BANDWIDTH PHASE SHAPING APPROACH

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IFAC Proceedings Volumes 2005年第1期38卷 313-318页

作者： Atsushi Satoh Kenji Sugimoto Graduate School of Information Science Nara Institute of Science and Technology 8916-5 Takayama Ikoma 630-0192 JAPAN

This paper discusses a vehicle control augmentation strategy bringing into focus the phase property, and proposes a control bandwidth phase shaping technique which is applicable to control augmentation system design. This paper points out that the problem setting of the control augmentation system design and structure/control integrated design has similarity. As expected from the similarity it is observed that the phase crossover bandwidth of vehicle dynamics has crucial effect to the tracking performance for pilot control input. Furthermore, a finite bandwidth phase shaping technique via dissipative control theory is proposed. Namely, the phase shaping in control bandwidth is achieved with no phase constraint in the higher frequency range. Therefore, a control augmentation system which achieves the phase shaping in the control bandwidth is easily designed by the presented technique.

关键词： Phase Crossover Bandwidth Finite Bandwidth Loop Shaping Integrated Design Dissipative control control augmentation system

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Phugoid damping control

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JOURNAL OF GUIDANCE control AND DYNAMICS 2002年第3期25卷 517-527页

作者： Pachter, M Schindeler, NJ USAF Inst Technol Dept Elect & Comp Engn Wright Patterson AFB OH 45433 USA

A novel phugoid damping control design methodology is developed, based on the use of wind axes and a point-mass aircraft model. The state variables are air speed, flight-path angle, and heading angle;the control variables are thrust setting, angle of attack, bank angle, and sideslip angle;and the command signals are air speed, flight-path angle, and heading angle or heading rate. All of the variables and parameters are nondimensionalized. A multivariable set point controller is developed that consists of the following: First, it consists of a trim calculation-based nonlinear feedforward control computer;thus, given a commanded new trim state (air speed, flight-path angle, and yaw rate), the required trim thrust setting and trim angle of attack, bank angle, and sideslip angle inputs are determined. Second, the controller consists of a small signal linear feedback regulator. The equations of motion linearized about the trim condition of wings level and constant altitude flight, which simplify the dynamics to allow separation between the lateral and longitudinal control channels, are used, and a small-signal linear multivariable regulator is designed. The linear compensator also entails integral action. Thus, the controller consists of a strongly nonlinear feedforward module and a linear small-signal compensator. The novel proposed multivariable and nonlinear set point controller encompasses full three-axes autopilot functions. Moreover, this controller is used as a tracking controller, also known as a phugoid damping controller, provided that the bandwidth of the command signal is substantially less than the bandwidth of the closed-loop flight control system. The phugoid damping controller's performance is examined in extensive simulations, and its wide operational envelope is demonstrated.

关键词： Phugoid Longitudinal control Aerodynamic Angle Autopilot control systems Bank to Turn Heading Angle Sideslip Angle Yaw control augmentation system

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Angular momentum control in nonlinear flight

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JOURNAL OF AIRCRAFT 2000年第3期37卷 448-453页

作者： Lee, DC Nagati, MG Wichita State Univ Dept Aeronaut Engn Wichita KS 67260 USA

A rational approach to control angular motion of aircraft in highly nonlinear flight regimes is presented. The method seeks to change the angular velocity by directing the aerodynamic moment so that it is most effective in achieving this objective. Validation of the method is presented by simulating two spins of a light aircraft. The approach is shown to be successful in stopping the rotation for effecting spin recovery.

关键词： Aerodynamic Angle Ailerons Aerodynamic Characteristics Sideslip Angle Light Aircraft Pilot National Transportation Safety Board control augmentation system Nonlinear Programming Newton's Second Law

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Aeroservoelastic analysis of the B-2 bomber

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JOURNAL OF AIRCRAFT 2000年第5期37卷 745-752页

作者： Britt, RT Jacobson, SB Arthurs, TD Northrop Grumman Corp Mil Aircraft Syst Div Pico Rivera CA 90660 USA

In the early stages of the development of the B-2 bomber, the technical challenges posed by the aeroelastic characteristics of the all-wing aircraft were recognized. The configuration's near-neutral pitch stability and light wing loading made the aircraft highly responsive to atmospheric turbulence. This dictated the requirement for an active digital Eight control system to provide both stability augmentation and gust load alleviation. The gust load alleviation flight control system was designed by a multidisciplinary team using a combination of optimal and classical control design techniques. The analytical models included linearized approximations of the digital control law mechanization. Flight-test data analysis included the extraction of the vehicle open-loop response, which compared well with the analytical predictions. The multidisciplinary design approach resulted in the successful development of a control augmentation system that provides the B-2 with superb handling characteristics, acceptable low-altitude ride quality, and substantial alleviation of gust loads on the airframe.

关键词： Modern control Theory Aerodynamic Damping control augmentation system Structural Load Flight Testing control systems Aircraft Structures Wing Loading Mean Aerodynamic Chord Pitch Stability

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KEEP EAGLE F-15E high angle-of-attack flight test program

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JOURNAL OF AIRCRAFT 1997年第3期34卷 265-270页

作者： Sitz, DM Nelson, DC Carpenter, MR MCDONNELL DOUGLAS CORP AEROSPDEPT 281EDWARDS AFBCA 93523

The KEEP EAGLE night test program was conducted from August 1994 until August 1995 at Edwards Air Force Base by a combined government/contractor test team to evaluate improvements to F-15E high angle-of-attack and spin recovery characteristics. This paper traces the program from its inception in 1992 until its conclusion in 1995, with emphasis on the test approach and flight test techniques employed for this high-risk program, Specifically, the test approach included novel assessments of spin recovery control power early in the night test program using controlled buildups in yaw rate. The program also used simulation effectively to improve test efficiency and maintain test team proficiency with normal and emergency procedures. These techniques allowed a relatively aggressive night test program without compromising safety. A total of 18 different aircraft configurations were successfully tested, with 146 developed spins completed throughout the course of 81 program flights.

关键词： Angle of Attack Flight Test Programme control Surfaces Angle of Sideslip Edwards Air Force Base Conformal Fuel Tank control augmentation system Stabilator Crew Member Digital Electronic Engine control

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Bifurcation analysis of a highly augmented aircraft model

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JOURNAL OF GUIDANCE control AND DYNAMICS 1997年第4期20卷 754-759页

作者： Avanzini, G deMatteis, G POLITECN TORINO DEPT AEROSP ENGN I-10129 TURIN ITALY

Bifurcation theory is used to analyze the dynamics of a modern high-performance aircraft. An F-16 lighter aircraft model, which includes a full authority control system, is considered. The vehicle is a basically unstable configuration, and its response modes are tailored by the Eight control system according to different mission tasks. The steady states of the F-16 are computed by a numerical continuation method. The classical application of this technique to trace the steady states of the system as continuous functions of control deflections or control force is to be reconsidered when the use of maneuver demand control in highly augmented aircraft provides zero stick force for most of the trimmed flight conditions of the vehicle. The practical worth of bifurcation theory for the design and analysis of high performance aircraft is evaluated. Such aspects of the problem as the selection of meaningful parameters for the continuation procedure and the interpretation of the bifurcation diagrams are discussed for the different modes of operation of the flight control system. The behavior of the aircraft model at high angle of attack is predicted when the alpha limiter is disengaged to simulate the effects of possible failure conditions.

关键词： High Performance Aircraft Angle of Attack Sidestick controller Stabilator control augmentation system Airframes Bifurcation Theory Longitudinal control Negative Static Stability Sideslip Angle

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