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Design method of terminal sliding mode controller for hypersonic vehicle

A hypersonic, design method technology, applied in design optimization/simulation, geometric CAD, sustainable transportation, etc., can solve the problem that the convergence speed is difficult to meet the requirements of the rapid response of the aircraft

Active Publication Date: 2020-03-13
BEIJING UNIV OF TECH
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  • Application Information

AI Technical Summary

Problems solved by technology

An adaptive sliding mode controller is designed for the longitudinal model of a hypersonic vehicle, which proves the effectiveness of the sliding mode control. However, the sliding mode surface used is a traditional linear sliding mode surface, and its state converges exponentially with time, and the convergence speed is difficult to meet Requirements for rapid response of aircraft under high-speed flight conditions

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  • Design method of terminal sliding mode controller for hypersonic vehicle
  • Design method of terminal sliding mode controller for hypersonic vehicle
  • Design method of terminal sliding mode controller for hypersonic vehicle

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Embodiment Construction

[0119] In order to verify the effect of the designed controller and achieve an effective comparison, the cruise conditions of the aircraft will be simulated and verified by using the data and units given in the literature, as shown in Table 1:

[0120] In the simulation, the values ​​of the parameters in formula (25) are shown in Table 2 below. Suppose the given system command signal is: V d (t) = 15160ft / s, that is, the speed increases by 100ft / s, and investigates the performance of the designed controller.

[0121] Compared with many referenced documents, the system convergence time is 30s or more, while our convergence time is less than 20s. The sliding surface can converge in a limited time and improve the tracking speed of the system. Simulation results show that the proposed design method is feasible and effective.

[0122] Suppose the given system command signal is: h d (t) = 112000ft, that is, the height is increased by 2000ft, and the performance of the designed co...

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Abstract

The invention relates to a method for designing a Terminal sliding mode controller of a hypersonic vehicle. The Terminal sliding mode control has an advantage that a system on a sliding mode surface can be converged within limited time. In order to keep the nonlinearity of a model and to facilitate the design of a control system, an input-output linearization method is used for processing the model in the paper, after that, state variables are reselected according to the design requirements of the Terminal sliding mode control, and a nonlinear sliding mode surface is designed; a sliding mode control law is designed for the designed Terminal nonlinear sliding mode surface, to ensure that the system can reach the sliding mode surface, and to prove the stability of the system; finally, the given control law is subjected to simulation verification, and the results show that the designed sliding mode controller can realize the effective control of the hypersonic vehicle.

Description

technical field [0001] The invention relates to a design method for a terminal sliding mode controller of a hypersonic aircraft, and belongs to the technical field of aviation controller regulation. Background technique [0002] Hypersonic vehicles have attracted the attention of countries all over the world because of their advantages such as fast flight speed, strong maneuverability, and large payload, and have become the focus of the research and development of next-generation aircraft. However, because the aircraft itself adopts the integrated design of the fuselage and engine, the state of the aircraft engine and the flight state are coupled with each other; and the flight envelope of the hypersonic aircraft is large, the flight conditions are complex, and its overall dynamics model has serious nonlinearity. The uncertainty of parameters and external disturbances cannot be ignored, which makes it difficult to design a controller that meets its performance requirements s...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/20
CPCG06F30/15G06F30/367Y02T90/00
Inventor 姬庆庆杨祎陈楠石莹李晨宇
Owner BEIJING UNIV OF TECH
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