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

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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CROSS COUPLING IN PILOT-VEHICLE systemS

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JOURNAL OF GUIDANCE control AND DYNAMICS 1986年第6期9卷 614-620页

作者： HESS, RA WATSON, DC University of California Davis California

Multiloop pilot-vehicle analysis is applied to the problem of determining crossfeed techniques that may be employed by pilots in minimizing the effects of vehicle cross coupling. Herein, cross coupling refers to unwanted vehicle motion, which occurs in one control axis or loop as the result of pilot control actuation in another control axis or loop. The minimization or elimination of such cross coupling can significantly affect the "workload" associated with tasks such as nap-of-the-Earth helicopter flight. In contrast, situations arise in which pilots may use vehicle cross coupling to improve performance by coordinating two control actuations in the control of a single response variable. A crossfeed model is developed based upon simple control system design principles and configured in a manner amenable to pursuit or precognitive pilot control activity. A handling-qualities theory developed to analyze single-loop tasks is applied to the multiloop problem. The crossfeed model is applied to five different vehicles/configurations ranging from helicopters to fighter aircraft. Results indicate that relatively simple crossfeed commands can significantly reduce cross coupling and, in some cases, improve handling qualities as predicted by the single-loop theory. © 1986 American Institute of Aeronautics and Astronautics, Inc.

关键词： Pilot Handling Qualities Rotor systems Pilot control Fighter Aircraft Earth control system Design Structural Modeling control augmentation system Pilot Modeling

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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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Batch simulation environment for integrated batch and piloted air combat analysis

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JOURNAL OF AIRCRAFT 1995年第6期32卷 1263-1268页

作者： Goodrich, KH McManus, JW Chappell, AR NASA Langley Research Center Hampton Virginia 23681 Lockheed Engineering and Sciences Company Inc. Hampton Virginia 23666

A batch air combat simulation environment known as the tactical maneuvering simulator (TMS) is presented. The TMS serves as a tool for developing and evaluating tactical maneuvering logics. The environment can also be used to evaluate the tactical implications of perturbations to aircraft performance or supporting systems. The TMS is capable of simulating air combat between any number of engagement participants, with practical limits imposed by computer memory and processing power. Aircraft are modeled using equations of motion, control laws, aerodynamics, and propulsive characteristics equivalent to those used in high-fidelity piloted simulation. Databases representative of a modern high-performance aircraft with and without thrust-vectoring capability are included. To simplify the task of developing and implementing maneuvering logics in the TMS, an outer-loop control system known as the tactical autopilot (TA) is implemented in the aircraft simulation model. The TA converts guidance commands issued by computerized maneuvering logics in the form of desired angle of attack and wind axis-bank angle into inputs to the inner-loop control augmentation system of the aircraft. This article describes the capabilities and operation of the TMS.

关键词： control augmentation system Angle of Attack Aerodynamic Force control systems High Performance Aircraft Autopilot Aircraft Performance Thrust Vectoring Computer Memory control Surfaces

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Transforming Civil Helicopters into Personal Aerial Vehicles: Modeling, control, and Validation

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JOURNAL OF GUIDANCE control AND DYNAMICS 2017年第10期40卷 2481-2495页

作者： Geluardi, Stefano Venrooij, Joost Olivari, Mario Buelthoff, Heinrich H. Pollini, Lorenzo Max Planck Inst Biol Cybernet POB 2169 D-72076 Tubingen Germany Korea Univ Dept Brain & Cognit Engn Seoul South Korea Univ Pisa Dipartimento Ingn Informaz I-56126 Pisa Italy

This paper presents the implementation of robust control strategies to augment an identified state-space model of a civil light helicopter. The aim of this study is to augment the helicopter model to achieve response types and handling qualities of a new category of aircraft called personal aerial vehicles, which can be flown even by inexperienced pilots. Two control methods are considered to augment the helicopter model, H-infinity and mu synthesis. Differences, advantages, and limitations of the implemented control architectures are highlighted with respect to the personal aerial vehicle reference dynamics in terms of robust stability, nominal performance, and handling qualities. Furthermore, results are presented of an experiment performed with the Max Planck Institute CyberMotion Simulator. The aim of the experiment is to assess the discrepancies between the two augmented systems and the personal aerial vehicle reference model. The experiment consists of piloted closed-loop control tasks performed by participants without any prior flight experience. The results show that the two implemented augmented systems allow inexperienced pilots to achieve workload and performance levels comparable to those defined for personal aerial vehicles.

关键词： Helicopters Handling Qualities State Space Representation Pilot Analysis of Variance Rudder Helicopter controls Flight Testing Helicopter Dynamics control augmentation system

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Flight control Design using Incremental Nonlinear Dynamic Inversion with Fixed-lag Smoothing Estimation

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INTERNATIONAL JOURNAL OF AERONAUTICAL AND SPACE SCIENCES 2020年第4期21卷 1047-1058页

作者： Cervantes, Tito J. Ludena Choi, Seong H. Kim, Byoung S. Gyeongsang Natl Univ Aerosp Dept Jinju 52828 Gyeongsangnam D South Korea

In this study, a flight control design strategy based on incremental nonlinear dynamic inversion (INDI) and smoothing algorithm is presented. The INDI is an enhanced version of the nonlinear dynamic inversion technique with a better robust performance. It reduces the aircraft model dependence via the feedback information of the state derivative, that is, angular acceleration for the aircraft attitude motion (or angular velocity related to the wind axis parameters). However, the state derivatives cannot always be obtained by direct measurement, thus they need to be estimated on-line. Moreover, taking into account that INDI requires one-step delay of state derivative and the fact that the inertial measurement unit (IMU) operates faster than the flight control computer (FCC), there will be additional information that can be used to improve the estimation. Therefore, a fixed-lag smoothing algorithm based on a discrete Kalman filter is proposed for angular velocity and angular acceleration estimation. The smoother utilizes the state variable from the sensor measurement and thus dealing with noise and delay.

关键词： Incremental nonlinear dynamic inversion Smoothing algorithm control augmentation system

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Gain Scheduling with Guardian Maps for Longitudinal Flight control

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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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COOPERATIVE SYNTHESIS OF control AND DISPLAY augmentation

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JOURNAL OF GUIDANCE control AND DYNAMICS 1989年第1期12卷 54-61页

作者： GARG, S SCHMIDT, DK Purdue University West Lafayette Indiana

The cooperative control synthesis technique, previously developed to synthesize control augmentation so as to optimize the human operator’s subjective rating, is extended to the synthesis of display augmentation for closed-loop manual control tasks. The procedure allows for simultaneously augmenting the display dynamics as well as plant or controlled element dynamics via feedback, and explicitly includes task-related and pilot-centered requirements in the design objectives. Connections are made between the proposed technique and classical manual control theory, and the new methodology is demonstrated by considering a compensatory tracking task for a generic controlled element. Analytical evaluations of the various control and display augmentation results and comparisons with the results of previous experimental studies are discussed. © 1989 American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

关键词： Pilot Loop Transfer Function control augmentation system Flight Director Feedback control Optimal control control Guidance Flight control Mathematical Optimization Lagrange Multipliers

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Utilizing Reinforcement Learning to Continuously Improve a Primitive-Based Motion Planner

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JOURNAL OF AEROSPACE INFORMATION systemS 2022年第7期19卷 468-479页

作者： Goddard, Zachary C. Wardlaw, Kenneth Williams, Kyle Parish, Julie Mazumdar, Anirban Georgia Inst Technol Woodruff Sch Mech Engn Atlanta GA 30332 USA Sandia Natl Labs Pathfinder Technologies Albuquerque NM 87123 USA

This paper describes how the performance of motion primitive-based planning algorithms can be improved using reinforcement learning. Specifically, we describe and evaluate a framework that autonomously improves the performance of a primitive-based motion planner. The improvement process consists of three phases: exploration, extraction, and reward updates. This process can be iterated continuously to provide successive improvement. The exploration step generates new trajectories, and the extraction step identifies new primitives from these trajectories. These primitives are then used to update rewards for continued exploration. This framework required novel shaping rewards, development of a primitive extraction algorithm, and modification of the Hybrid A* algorithm. The framework is tested on a navigation task using a nonlinear F-16 model. The framework autonomously added 91 motion primitives to the primitive library and reduced average path cost by 21.6 s, or 35.75% of the original cost. The learned primitives are applied to an obstacle field navigation task, which was not used in training, and reduced path cost by 16.3 s, or 24.1%. Additionally, two heuristics for the modified Hybrid A* algorithm are designed to improve effective branching factor.

关键词： Reinforcement Learning Motion Planning Nonlinear Programming Search Algorithm Neural Networks control augmentation system Optimal control JSBSim Fixed Wing Aircraft Angle of Attack

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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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