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A hypersonic vehicle attitude control design method with preset adjustment time

A hypersonic and time-adjusting technology, applied in the aerospace field, can solve problems such as large control gain of robust control law, increase of controller gain, and increase of adaptive law estimate value

Active Publication Date: 2021-01-29
HARBIN INST OF TECH
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Problems solved by technology

[0003] The purpose of the present invention is to provide a hypersonic aircraft attitude control design method with preset adjustment time, which can make the system attitude angle error reach the specified accuracy requirement within the preset adjustment time; and the method can solve most robust control problems. The problem that the law control gain is large and the estimated value of most adaptive laws continues to increase, so that the gain of the controller increases as needed

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  • A hypersonic vehicle attitude control design method with preset adjustment time
  • A hypersonic vehicle attitude control design method with preset adjustment time
  • A hypersonic vehicle attitude control design method with preset adjustment time

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specific Embodiment approach 1

[0125] A hypersonic vehicle attitude control design method with preset adjustment time, comprising the following steps:

[0126] Step 1: The design task of the control system is clarified, and the purpose of the control system design is given to make the attitude angle signal of the hypersonic vehicle track the reference command signal within a predetermined time; Step 2: Establish a second-order nonlinear mathematical model of the attitude system of the hypersonic vehicle ; Step 3: Define the sliding mode surface, and design the adaptive sliding mode control law based on the sliding mode surface; Step 4: Use the computer numerical simulation tool Matlab / Simulink to test the performance of the closed-loop system. After the above steps, the design ends.

[0127] Specific steps are as follows:

[0128] Step 1. Clarify the design task of the control system

[0129] The design task of the control system is: Given a reference signal x d , the preset adjustment time T f = 2s and...

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Abstract

The invention discloses a hypersonic aircraft attitude control design method capable of presetting adjustment time, and belongs to the field of aerospace, and the specific scheme comprises the following steps: 1, defining a design task of a control system; 2, establishing a hypersonic aircraft attitude system mathematical model; 3, designing a self-adaptive sliding mode control law; 4, analyzing aclosed-loop system; and 5, carrying out performance test on the closed-loop system by utilizing a computer numerical simulation tool Matlab / Simulink. According to the designed method, the attitude angle of the hypersonic flight vehicle meets the precision requirement within the limited time, and the required adjustment time can be preset according to the performance index requirement. Besides, the control law can also enable the estimated value of the uncertain item to be increased as required, the gain of the controller is also reduced, and the conservative property of general robust controland self-adaptive control design is overcome to a great extent.

Description

technical field [0001] The invention belongs to the field of aerospace, and in particular relates to an adaptive sliding mode control law design method which can preset adjustment time and enable the attitude angle error of a hypersonic vehicle to converge to a specified accuracy within a specified time. Background technique [0002] In the control of a hypersonic vehicle, it is necessary to ensure that the attitude angle of the vehicle tracks the reference command signal, otherwise it is difficult to realize the flight mission of the vehicle. At present, for the control of hypersonic vehicles, most of them only ensure that the attitude angle converges to the specified reference value within an infinite time, and a few can guarantee the convergence within a limited time, but the adjustment time cannot be preset. In order to solve the uncertainty problem in control, most of the robust control laws currently used generally need to choose a larger control gain; and most of the ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G05D1/08
Inventor 侯明哲郑文全谭峰
Owner HARBIN INST OF TECH
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