Elastic aircraft robust finite time control method based on singular perturbation analysis
A technology with finite time and control method, applied in the field of flight control, can solve the problems that the learning speed cannot be guaranteed, the elastic mode stabilization cannot be guaranteed, and it is difficult to obtain satisfactory tracking performance.
Inactive Publication Date: 2019-11-15
NORTHWESTERN POLYTECHNICAL UNIV
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However, simply considering it as uncertainty in elastic body dynamics lacks in-depth analysis, and cannot guarantee the stability of the elastic mode, and only adjusting the neural network based on the tracking error cannot guarantee the learning speed, and it can only guarantee the tracking error and learning error. Bounded, difficult to achieve satisfactory tracking performance
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[0107] Now in conjunction with embodiment, accompanying drawing, the present invention will be further described:
[0108] refer to figure 1 , the present invention's robust finite-time control of elastic aircraft based on singular perturbation analysis is applied to a class of elastic hypersonic aircraft dynamics model, and is realized by the following steps:
[0109] (a) Consider the elastic hypersonic vehicle longitudinal channel dynamic model:
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[0116] The kinematic model is composed of seven state quantities and two control inputs U=[δ e ,Φ] T Composition; where, V represents velocity, h represents height, γ represents track inclination, α represents angle of attack, q represents pitch angle velocity, η and Indicates the elastic mode, δ e Indicates rudder deflection angle, Φ indicates throttle valve opening; m, I yy and g denote the mass, the moment of inertia of the pitch axis, and the accele...
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The invention relates to an elastic aircraft robust finite time control method based on singular perturbation analysis. Aiming at a slow subsystem representing a rigid body, dynamic surface control isused for designing a rudder deflection angle controller; uncertain information of the system is estimated by using a neural network; learning assessment information is introduced into a neural network weight update law and learning error finite time convergence is achieved through building a first-order filter and an auxiliary signal, and meanwhile, an error fractional order item is added into acontrol law to ensure the convergence of tracking error finite time; and aiming at a fast change subsystem representing a system elasticity modulus, a sliding-mode control algorithm is designed for suppressing the elasticity modulus. A PID controller is designed aiming at a speed subsystem to achieve speed tracking.
Description
technical field [0001] The invention relates to an aircraft control method, in particular to a robust finite-time control method for an elastic aircraft based on singular perturbation analysis, and belongs to the field of flight control. Background technique [0002] Due to the extensive use of lightweight composite materials and the design of special shapes such as slender bodies, lifting bodies, and large aspect ratios, modern aircraft have more prominent effects of elastic modes than traditional aircraft. Ignoring the elastic mode design of flight control laws may lead to Aircraft performance degrades and even flight instability. [0003] Most of the existing studies on elastic body control of aircraft regard the elastic mode as self-stabilization and directly design the controller for the rigid body, which cannot meet the requirements of high precision control; some scholars regard the elastic mode as a disturbance, and realize the elastic Partial control, however, this...
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IPC IPC(8): G05B13/04
CPCG05B13/042
Inventor 许斌郭雨岩梁捷袁源
Owner NORTHWESTERN POLYTECHNICAL UNIV