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Handling Qualities Requirements for Future Personal Aerial Vehicles

JOURNAL OF GUIDANCE control AND DYNAMICS 2015年第12期38卷 2386-2398页

作者： Perfect, Philip Jump, Michael White, Mark D. Univ Liverpool Sch Engn Ctr Engn Dynam Liverpool L69 3BX Merseyside England

This paper describes research to develop handling qualities guidelines and criteria for a new category of aircraft: the personal aerial vehicle, which it is envisaged will demand no more skill to fly than that associated with driving a car today. Testing of concept personal aerial vehicle response types has been conducted with inexperienced "pilots" ranging from private pilot's license holders through to those with no prior flight experience. The objective was to identify, for varying levels of flying skill, the personal aerial vehicle response type requirements that will ensure safe and precise flight. Conventional rotorcraft response types such as "rate command", "attitude command/attitude hold" are unsuitable for likely personal aerial vehicle pilots. However, response types such as "translational rate command" and "acceleration command, speed hold" permit "flight-naive" pilots to perform demanding tasks repeatably and with the required precision.

关键词： Handling Qualities Private Pilot Licence Rotorcrafts Test Pilots Longitudinal control Airspeed VTOL Flight Path Angle Helicopters stability and control augmentation system

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Optimized Fuzzy-Proportional/Integral/Derivative controller for Aircraft Pitch control

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JOURNAL OF AEROSPACE INFORMATION systemS 2013年第8期10卷 414-429页

作者： Ting, Eric Ayoubi, Mohammad A. Santa Clara Univ Dept Mech Engn Santa Clara CA 95053 USA

This paper presents a simple-structured fuzzy-proportional/integral/derivative controller for pitch control of a linearized full-scale generic transport aircraft model. Particle swarm optimization is applied to offline optimize the fuzzy-proportional/integral/derivative controller scaling gains as well as simultaneously optimize parameters within the first-order Takagi-Sugeno-type inference system. The performance of the controller is tested against a baseline state feedback and fine-tuned proportional/integral/derivative (particle swarm optimization-proportional/integral/derivative) controller. Numerical simulations are conducted comparing the fuzzy-proportional/integral/derivative controller to the other linear controllers when linear and nonlinear models of uncertainty are added post-optimization. The results demonstrate the robustness of the proposed nonlinear offline optimized fuzzy-proportional/integral/derivative controller.

关键词： Model Reference Adaptive control Aircraft Pitch control Particle Swarm Optimization Numerical Simulation Transport Aircraft Elevator Deflection Fuzzy control Roll control Flight control system stability and control augmentation system

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IDENTIFICATION OF XV-15 AEROELASTIC MODES USING FREQUENCY SWEEPS

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JOURNAL OF AIRCRAFT 1989年第7期26卷 667-674页

作者： ACREE, CW TISCHLER, MB NASA Ames Research Center Moffett Field California U. S. Army Aviation Research and Technology Activity Moffett Field California

The XV-15 tilt-rotor wing has six major aeroelastic modes that are close in frequency. To precisely excite individual modes during flight test, dual flaperon exciters with automatic frequency-sweep controls were installed. The resulting structural data were analyzed in the frequency domain (Fourier-transformed). Modal frequencies and damping were determined by performing curve fits to frequency-response magnitude and phase data. Results are given for the XV-15 with its original metal rotor blades. Frequency and damping values are also compared with predictions by two different programs, CAMRAD and ASAP. © 1989 American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

关键词： Aeroelastic stability Flight Testing Frequency Response Flaperon Tilt Rotor Wing Rotor Blades Knots True Airspeed Flight Data stability and control augmentation system Structural Analysis

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GENERALIZED TECHNIQUE FOR INVERSE SIMULATION APPLIED TO AIRCRAFT MANEUVERS

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JOURNAL OF GUIDANCE control AND DYNAMICS 1991年第5期14卷 920-926页

作者： HESS, RA GAO, C WANG, SH UNIV CALIF DAVIS DEPT ELECT ENGN & COMP SCIDAVISCA 95616

Inverse simulation techniques are computational methods that determine the control inputs to a dynamic system that produce desired system outputs. Such techniques can be powerful tools for the analysis of problems associated with maneuvering flight. An algorithm is developed that serves as an efficient inverse simulation tool for analyzing maneuvering flight. As opposed to current inverse simulation methods, which require numerical time differentiation in their implementation, the generalized technique offered is essentially an integration algorithm. Examples of inverse solutions for a large-amplitude aircraft maneuver and a nap-of-the-Earth helicopter maneuver are presented.

关键词： Aircraft Maneuvers Helicopters Computational Methods Earth Integration Algorithm stability and control augmentation system Aileron Roll Singular Value Decomposition Inverse Problems Aircraft Flight control system

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Analysis of Flexible Aircraft Dynamics Using Bifurcation Methods

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JOURNAL OF GUIDANCE control AND DYNAMICS 2011年第3期34卷 795-809页

作者： Baghdadi, N. Lowenberg, M. H. Isikveren, A. T. Univ Bristol Dept Aerosp Engn Bristol BS8 1TR Avon England

Modern commercial aircraft designs are continuously driven towards more slender wing configurations in order to meet performance and general mission requirements. Consequently, these aircraft are characterized by flexible structures that undergo large deformations, and in turn the frequency separation between the flexible and rigid-body modes is greatly reduced. The associated coupling can, in the presence of nonlinearities, introduce effects on the flight dynamics of such vehicles that conventional methods may not adequately predict, leading to the potential of degraded handling qualities. This paper evaluates the effects of flexibility on the dynamics, stability, and control of elastic aircraft using an analysis framework based on bifurcation and continuation tools, linked to classical analysis methods. Results based on variations of a Rockwell B1 model demonstrate the suitability of the approach in revealing dynamic coupling between rigid-body and flexible modes in regions of the flight envelope in which nonlinearities are significant. Furthermore, the efficiency of this approach relative to traditional nonlinear simulation is discussed. The robustness of idealized control law designs to unmodeled elastic modes is also investigated.

关键词： Aircraft Dynamics Handling Qualities Aircraft Flight Dynamics Sweep Angle Flexible Structures Commercial Aircraft Mean Aerodynamic Chord stability and control augmentation system Aerodynamic Coefficients Angle of Attack

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TIME-PERIODIC control OF A MULTIBLADE HELICOPTER

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JOURNAL OF GUIDANCE control AND DYNAMICS 1991年第6期14卷 1301-1308页

作者： WEBB, SG CALICO, RA WIESEL, WE USAF INST TECHNOLWRIGHT PATTERSON AFBOH 45433

The equations of motion for a rigid helicopter containing four blades free to flap and lag are control techniques are developed which stabilize the entire system for a variety of flight conditions. A modal control technique, based on Floquet theory, is used to eliminate multiple-blade instabilities by controlling pairs of unstable roots at a specific design point. Another modal controller is designed for the resulting new system which shifts a second pair of unstable roots to desired locations. This process is repeated until all instabilities are eliminated. Numerical inaccuracies, however, limit the number of possible repetitions of this procedure.

关键词： Heavy Lift Helicopters Airframes Linear Quadratic Regulator stability and control augmentation system Angle of Attack Rotor Blades Collective Pitch control Feedback control Blade Pitch control Aerodynamic Force

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Adaptive model inversion flight control for tilt-rotor aircraft

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JOURNAL OF GUIDANCE control AND DYNAMICS 1999年第3期22卷 402-407页

作者： Rysdyk, RT Calise, AJ Georgia Inst Technol Sch Aerosp Atlanta GA 30332 USA

Neural-network augmented model inversion control is used to provide a civilian tilt-rotor aircraft with consistent response characteristics throughout its operating envelope, including conversion flight. The implemented response type is Attitude Command Attitude Hold in the longitudinal channel. Conventional methods require extensive gain scheduling with tilt-rotor nacelle angle and speed. A control architecture that can alleviate this requirement, and thus has the potential to reduce development time and cost, is developed. This architecture also facilitates the implementation of desired handling qualities and permits compensation for partial failures. One of the powerful aspects of the controller architecture is the accommodation of uncertainty in control as well as in the states. It includes an online, i.e., learning-while-controlling, neural network that is initialized with all weights equal to zero. Lyapunov analysis guarantees the boundedness of tracking errors and network parameters. Performance of the controller is demonstrated using a nonlinear generic tilt-rotor simulation code.

关键词： Aeroplane Tilt Rotor Flight control stability and control augmentation system Rotor systems Longitudinal control Neural Networks Nacelles Handling Qualities Pilot

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stability Analysis of an Airplane with MIMO control system Based on Frequency Methods

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AUTOMATION AND REMOTE control 2021年第7期82卷 1271-1280页

作者： Bazhenov, S. G. Kozyaichev, A. N. Korolev, V. S. Cent Aerohydrodynam Inst Zhukovskii 140180 Moscow Oblast Russia

Various methods of stability analysis of an airplane with a MIMO control system are considered in the framework of frequency analysis. They assume that the control system is open for selected signal with other loops closed or that system is open for all signals of selected loops and allow solving the stability equation and calculating the eigenvalues of the matrix of transfer functions. It is shown that all methods deal with different forms of the same equation, and thus the equivalence of methods considered for calculating closed-loop stability domains is proved. The application of methods is demonstrated for calculation of stability domains for an airplane equipped with MIMO stability and control augmentation system in lateral motion that uses ailerons and rudder as control surfaces. It is shown that in the case of a MIMO system, an open-loop transfer function that defines closed-loop stability is a nonlinear function of control system gains;this introduces uncertainty to the concept of amplitude and phase margins.

关键词： MIMO system open-loop transfer function matrix of transfer functions stability margin airliner stability and control augmentation system

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Design and Testing of a Low-Order Flight control system for Quad-Tilt-Wing UAV

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JOURNAL OF GUIDANCE control AND DYNAMICS 2016年第10期39卷 2423-2430页

作者： Totoki, Hironori Ochi, Yoshimasa Sato, Masayuki Muraoka, Koji Natl Def Acad Dept Aerosp Engn 1-10-20 Hashirimizu Yokosuka Kanagawa 2398686 Japan Japan Aerosp Explorat Agcy Flight Res Ctr 6-13-1 Osawa Mitaka Tokyo 1810015 Japan

Researchers propose new stability and control augmentation systems (S/CAS) design methods to improve the control performance. A linear matrix inequality (LMI) formulation for static output feedback (SOF) control is employed in the SAS design and a newcontroller reduction method is applied to the CAS design. The introduction of a new decision variable to the LMIs reduces conservativeness and makes it possible to design a structured gain matrix and to improve linear quadratic (LQ) control performance, as compared with similar methods.

关键词： UAV Flight control system stability and control augmentation system Linear Quadratic Regulator Flight Testing Feedback control Pilot Attitude Tracking VTOL control Surfaces

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Two-timescale-integration method for inverse simulation

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JOURNAL OF GUIDANCE control AND DYNAMICS 1999年第3期22卷 395-401页

作者： Avanzini, G de Matteis, G de Socio, LM Politecn Torino Dept Aerosp Engn I-10129 Turin Italy Univ Roma La Sapienza Dept Mech & Aeronaut I-00184 Rome Italy

The integration method is extensively applied in the inverse simulation of aircraft motion where control inputs are determined once a maneuver or flight task is assigned. In many circumstances the presence of multiple timescales and right half-plane transmission zeros in aircraft dynamics introduces problems of accuracy and stability in the numerical algorithm. This paper presents a formulation for inverse simulation problems where the concept of timescale separation is merged into an integration technique and a constrained optimization method. Two subscale problems are solved separately for the slow and fast timescales and a numerical algorithm is devised that presents significant advantages in terms of numerical efficiency and robustness. The technique accounts for the issue of control saturation and lends itself to applications where the aircraft trajectory is given as a function of time. The results of the study show the improved performances of the technique in comparison with an integration method that is based on the local optimization concept.

关键词： Roll control Inverse Problems stability and control augmentation system Aerodynamic Moments Helicopters Numerical Integration Solution Algorithm Angle of Attack Sideslip Angle Aileron Roll

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