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OBLIQUE WING aircraft flight control-system

JOURNAL OF GUIDANCE control AND DYNAMICS 1989年第2期12卷 201-208页

作者： CLARK, RN LETRON, XJY AEROSPATIALE FRANCE TOULOUSEFRANCE

A design procedure for a command and stability augmentation system (CSAS) for the oblique wing research airplane (OWRA) is presented. Three flight conditions are considered in which the wing skew angle is 0, 55, and 65 deg. The wing skew angle in the latter two cases induces severe asymmetrical dynamic behavior of the airframe. Five primary flight control surfaces are used to decouple the longitudinal motions from the lateral motions. The CSAS must accept conventional three-axis stick and rudder inputs from the pilot and translate these, along with feedback signals from the airframe, into the five airframe control surface commands. The design procedure combines eigenstructure design principles with an optimization scheme, providing a closed-loop response to both pilot inputs and to initial conditions that approximate those obtained with the wing in the unskewed position.

关键词： Lift to Drag Ratio aircraft flight control system Airframes Pilot control Surfaces Aeroplane Stability Augmentation systems Transient Response Multivariable control Handling Qualities

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A New Method for control Allocation of aircraft flight control system

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IEEE TRANSACTIONS ON AUTOMATIC control 2020年第4期65卷 1413-1428页

作者： Yang, Yuanchao Gao, Zichen Northwestern Polytech Univ Sch Aeronaut Xian 710072 Peoples R China Aviat Ind Corp China Flight Automat Control Res Inst Xian 710076 Peoples R China

The next generation of aircraft with a large number of effectors will require advanced methods for control allocation (CA) to compute the effectors' commands needed to follow the desired objective while respecting associated constraints. Currently, the main challenge of the CA is to achieve low enough computation time with a deterministically optimal result for a real-time application. In this paper, at first, we cast the CA as a nonlinear convex programming problem which depicts the desired objective function subject to three-axis moment demands and the limits of effectors' movement;then we develop a computationally tractable method for real-time application on the CA of the aircraft flight control system. The method can analytically and deterministically give one optimal solution for the CA and prove this optimal solution to be guaranteed within a certainly maximal computation time. Numerical testing results based on Boeing C-17 transport aircraft and Lockheed-Martin tailless fighter models demonstrate that the method is effective in terms of its computational efficiency, accuracy, and reliability.

关键词： Aerospace control aircraft Resource management Aerodynamics Linear programming Real-time systems Computational efficiency aircraft flight control system control allocation (CA) convex optimization digital control system real-time method

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BUFFET-INDUCED STRUCTURAL flight-control system INTERACTION OF THE X-29A aircraft

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JOURNAL OF aircraft 1994年第2期31卷 441-442页

作者： VORACEK, DF CLARKE, R NASA Dry den Flight Research Facility Edwards California 93523

aircraft design trends have led to increasing occurrences of the flight control system dynamics interacting with the aeroelastic response of the aircraft. Such interations involving the X-29A aircraft are discussed.

关键词： aircraft flight control system X 29A aircraft Angle of Attack control Surfaces Flaperon Power Spectral Density flight Test Programme Vertical Stabilisers flight Envelope Accelerometer

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Design and Optimization of a Piecewise flight controller for VTOL UAVs

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JOURNAL OF aircraft 2025年第1期62卷 180-190页

作者： Su, Shanfei Yu, Peng Wang, Hao Shan, Xiaowen Southern Univ Sci & Technol Dept Mech & Aerosp Engn Shenzhen 518055 Peoples R China Southern Univ Sci & Technol Dept Mech & Aerosp Engn Guangdong Prov Key Lab Turbulence Res & Applicat Shenzhen 518055 Peoples R China BNU HKBU United Int Coll Inst Adv Study Zhuhai 519087 Peoples R China

The dynamic systems of unmanned aerial vehicles (UAVs) are susceptible to parametric uncertainties, unmodeled dynamics, and external vibrational disturbances during motion control. Although proportional-integral-derivative (PID) controllers are widely used in UAVs, the manual tuning process is time-consuming, and the resultant control performance is vulnerable to uncertainties in varying flight conditions, leading to suboptimal flight control throughout the entire hovering flight envelope. To address this issue, the present study designs and optimizes a novel piecewise flight controller based on a hybrid data-driven approach combining gradient-based methods and pattern search algorithms. The optimization process is validated through comprehensive flight testing, comparing the piecewise controller with the baseline controller across a wide range of flight conditions. The study examines the objective functions and design parameters, demonstrating the robustness of the optimized piecewise controller in the presence of disturbances. The results reveal significant variations in the system model under different flight conditions, and the piecewise optimized controller demonstrates a response that is more than twice as fast as the benchmark, with acceptable overshoots and steady-state errors under the predefined trajectories. The salient features of the proposed piecewise flight controller and design optimization process are verified through flight testing, which is expected to provide a framework for future UAV flight control designs.

关键词： Multidisciplinary Design Optimization Vertical Takeoff and Landing flight Testing Nonlinear Model Predictive control Unmanned Aerial Vehicle aircraft flight control system Search Algorithm Autopilot flight control Surfaces aircraft Design

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Switched Model-Predictive-control-Based Trajectory Tracking of Fixed-Wing aircraft for Payload Dropping

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JOURNAL OF GUIDANCE control AND DYNAMICS 2025年第3期48卷 679-688页

作者： Li, Yunpeng Zhang, Lixian Wu, Tong Han, Yuejiang Zhang, Yuxuan Harbin Inst Technol Sch Astronaut Harbin 150001 Peoples R China

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Optimal Sliding Gaussian control of Quadrotor with a Flexible Structure

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JOURNAL OF GUIDANCE control AND DYNAMICS 2025年第4期48卷 781-792页

作者： Smith, Christopher S. Sinha, Alok Penn State Univ Appl Res Lab Penn State University Pk PA 16802 USA Penn State Univ Mech Engn University Pk PA 16802 USA

Optimal sliding Gaussian control of a quadrotor aerial vehicle with a flexible structure has been demonstrated in six-degree-of-freedom flight simulation to be more robust to structural excitation than a standard proportional-derivative control scheme. A general derivation of the optimal sliding Gaussian controller, including an optimal gain selection algorithm and observer design, is presented. Additionally, a brief development of the equations of motion for a quadrotor with a flexible structure is provided as background for the nonlinear six-degree-of-freedom flight simulation results. Robustness properties of the optimal sliding Gaussian controller are evaluated using singular value analysis of linearized models of the closed-loop quadrotor with a flexible structure. flight simulation and singular value analysis results illustrate the robustness improvements of optimal sliding Gaussian control over the standard proportional-derivative controller design.

关键词： Flexible and Active Structures Quadcopter Proportional Derivative controller flight Simulation Structural Kinematics and Dynamics Feedback Linearization aircraft flight control system Mechanical and Structural Vibrations Single Input Single Output system Sliding Mode control

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Line-of-Sight-Constrained Multicopter Interceptability

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JOURNAL OF GUIDANCE control AND DYNAMICS 2025年第4期48卷 951-960页

作者： Yang, Kun Bai, Chenggang Quan, Quan Beihang Univ Sch Automat Sci & Elect Engn Beijing 100191 Peoples R China

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GENERATING PARITY RELATIONS FOR DETECTING AND IDENTIFYING control-system COMPONENT FAILURES

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JOURNAL OF GUIDANCE control AND DYNAMICS 1988年第1期11卷 60-65页

作者： MASSOUMNIA, MA VANDERVELDE, WE Massachusetts Institute of Technology Cambridge Massachusetts

The monitoring of control system sensors and actuators for failures is presently undertaken by means of an exceptionally simple form of generalized parity relations based on a discrete-time model of the dynamics of linear, time-invariant systems. These generalized parity relations are constructed by recourse to a transfer matrix-description of the system that is additionally useful in the interpretation of their properties. Attention is given to a novel method for constructing the parity relation of minimum length that depends on the output of only a single sensor. (O.C.)

关键词： control system Sensors Sensors Actuators Linear Time Invariant system Computing Fault Tolerance aircraft flight control system Nuclear Power Plant Space Structures

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LITERAL SINGULAR-VALUE-BASED flight control-system DESIGN TECHNIQUES

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JOURNAL OF GUIDANCE control AND DYNAMICS 1989年第6期12卷 913-919页

作者： MCRUER, DT MYERS, TT THOMPSON, PM Systems Technology Inc. Hawthorne California

Recent control system research has resulted in new methods for assessing stability and performance robustness with respect to plant and controller uncertainty. The emphasis has been on using frequency domain matrix singular values for multi-input/multi-output systems. Problems originating from aircraft flight control systems have been an important motivation for these developments, and applications are currently being carried out at government research centers and in industry. These new robustness methods are, however, only slowly becoming part of the working flight control designer′s practical tools. Before becoming routine, means must be provided for better physical insight. This paper presents a distinctly different interpretation based on literal (symbolic) formulations of singular values. This approach is an outgrowth of and is related to classical multivariable control systems methods based on coupling numerators. A lateral-directional flight control system design for an advanced fighter is used as an example. Robustness of stability with respect to input uncertainties is first assessed using standard numerical techniques. Literal approximations are then given for open- and closed-loop singular values. The literal approximations are consistent with the numerical results. More importantly, they provide a means for decomposing and diagnosing robustness problems by providing explicit connections to critical aircraft and controller parameters. Both unstructured and structured uncertainties are treated, using respectively literal approximations of regular and structured singular values. © 1989 American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

关键词： aircraft flight control system Closed Loop Pole Frequency Domain Single Input Single Output Multivariable control system Roll control aircraft Dynamics Stability Derivatives Aeroplane aircraft Configurations

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ROBUSTNESS EVALUATION OF A FLEXIBLE aircraft control-system

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JOURNAL OF GUIDANCE control AND DYNAMICS 1993年第3期16卷 564-571页

作者： ANDERSON, MR Virginia Polytechnic Institute and State University Blacksburg Virginia 24061

The structured singular value analysis technique is used to generate stability and performance robustness guidelines for multivariable, flexible aircraft flight control systems. A stability augmentation and structural mode control system, designed using the same classical technique as on the original production aircraft, is evaluated to produce the new guidelines. Stability margins are computed for simultaneous gain and phase uncertainty in each of the control system feedback loops. Performance weighting filters are chosen specifically from military flying qualities specifications. The results of this research define exactly how robust a control system of this type should be, such that any performance improvements achieved using more advanced design techniques can be compared directly.

关键词： Stability Augmentation aircraft flight control system control system Design Feedback control system aircraft Flying Qualities aircraft control Closed Loop control Elevator Power Spectral Density Fuselages

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