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An attitude control system limiting value design method, storage medium and server
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A design method and limiting technology, applied in the field of aerospace, to achieve the effect of improving stability, improving robustness, and improving solution efficiency
Active Publication Date: 2021-11-16
BEIJING LANDSPACETECH CO LTD
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[0004] The purpose of the present invention is to solve the limit value design problem of the proportional term and the differential term in the control law of the aircraft attitude control system when the control is limited
Method used
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example 1
[0039] Take the design of pitch channel attitude control law of an aircraft as an example. The limit value design method of the limit item includes the following steps:
[0040] 1. Establish a small deviation dynamics model of an aircraft moving longitudinally around the center of mass, as follows:
[0041]
[0042] in, , , ,
[0043] , , represents an increment, represents the angle of attack,
[0045] Denotes the derivative of the lift force with respect to the angle of attack, Indicates the lift pair derivative of
[0046] represents the mass of the aircraft, represents the acceleration of gravity, represents the ballistic inclination,
[0047] Indicates the moment of inertia of the aircraft around the z-axis of the arrow system, represents the speed of the aircraft,
[0048] Denotes the derivative of the pitching moment wit...
example 2
[0066] Take the design of pitch channel attitude control law of an aircraft as an example. The limit value design method of the limit item includes the following steps:
[0067] 1. Establish a small deviation dynamics model of an aircraft moving longitudinally around the center of mass, as follows:
[0068]
[0069] in, , , ,
[0070] , , represents an increment, represents the angle of attack,
[0071] represents the pitch angular velocity, Indicates the pitch channel control amount, means thrust,
[0072] Denotes the derivative of the lift force with respect to the angle of attack, Indicates the lift pair derivative of
[0073] represents the mass of the aircraft, represents the acceleration of gravity, represents the ballistic inclination,
[0074] Indicates the moment of inertia of the aircraft around the z-axis of the arrow system, represents the speed of the aircraft,
[0075] Denotes the derivative of the pitching moment wit...
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Abstract
The present invention provides a design method for limit value of an attitude controlsystem, a storage medium and a server. This method aims at the stability control problem of the aircraft attitude controlsystem in the control-limited situation, and establishes the control-limited model of the attitude system, and transforms the limit value design problem of the proportional term and the differential term in the control law into an input subject to nested The domain-of-attraction optimization problem of the control system with saturation constraints, and thus by solving the optimization problem with LMI constraints, the design method of the limit value of the proportional control item and the differential control item when the control is limited is given. Using the limiting value of the proportional term and differential term in the optimal control law can improve the stability of the control system under large uncertainties and strong disturbances, and improve the robustness of the control system when the control is limited; Or the disadvantages of the lack of theoretical basis and time-consuming iterations for the amplitude constraint of adjusting the feedback amount in the simulation results of shooting, which significantly improve the solution efficiency.
Description
technical field [0001] The present invention relates to the field of aerospace technology, in particular to aircraft control technology, and specifically relates to a design method for a limiting value of an attitude control system, a storage medium and a server. Background technique [0002] In actual engineering, the deflection range of the aircraft servo mechanism is constrained. The flight control system is a nonlinear system, and its stability is related to the flight state, the limit of the servodeflection angle, and the limit processing of each feedback item in the control law. [0003] When the saturation of the control quantity is not considered, the robustness and performance of the control system can be considered at the same time, and the control gain of the proportional item and the differential item can be selected optimally; In order to improve the robustness of the control system, improve the stability of the control system, and avoid control saturation as m...
Claims
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