Anti-delay high-precision active disturbance rejection attitude control method based on fixed time differentiator prediction

A fixed time, attitude control technology, applied in attitude control, vehicle position/route/height control, non-electric variable control and other directions, can solve problems such as falling into a hysteretic loop state, poor performance, and attitude reciprocating oscillation

Active Publication Date: 2020-05-26
HARBIN INST OF TECH
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Problems solved by technology

[0003] However, reducing the production cost of the aircraft means using low-cost but poor-performance components, which puts forward higher requirements for the design of the airborne software system. How to use high-quality navigation, guidance, control and other algorithms to realize the Effective compensation for hardware system performance loss is the key technology to realize low-cost a

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  • Anti-delay high-precision active disturbance rejection attitude control method based on fixed time differentiator prediction
  • Anti-delay high-precision active disturbance rejection attitude control method based on fixed time differentiator prediction
  • Anti-delay high-precision active disturbance rejection attitude control method based on fixed time differentiator prediction

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Embodiment 1

[0052] An anti-time-delay high-precision self-disturbance rejection attitude control method based on fixed time differentiator prediction, the anti-time-delay high-precision attitude control method includes the following steps:

[0053] Step 1: Design a fixed-time convergent differentiator and obtain the attitude change rate observations. The detailed process is:

[0054] Step 1: Use the rate gyroscope to obtain the attitude information of the aircraft with a time delay of kh Where h represents the sampling period, k represents the number of delay cycles, represents the pitch angle, is the yaw angle, is the roll angle;

[0055] Step 2: Construct a third-order fixed-time convergent differentiator as shown below for the three channels of pitch, yaw and roll respectively:

[0056]

[0057] where the subscript Respectively represent the parameters corresponding to the pitch, yaw and roll channels; y i (t) represents the measured values ​​of different channels (i.e. ...

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Abstract

The invention discloses an anti-delay high-precision active disturbance rejection attitude control method based on fixed time differentiator prediction, which belongs to the technical field of guidance and control. The specific scheme is as follows: the anti-delay high-precision active disturbance rejection attitude control method based on the fixed time differentiator comprises the following steps of: 1, designing a fixed time convergence differentiator and obtaining an attitude change rate observation value, 2, predicting a real-time flight state based on the fixed time convergence differentiator, 3, constructing an aircraft three-channel attitude error tracking model, and 4, constructing an active disturbance rejection control system, and generating a real-time pneumatic rudder swing instruction through the active disturbance rejection control system by utilizing the real-time flight state of the aircraft. Development and production cost of aircrafts in China can be effectively reduced, and technical support is provided for improving aviation strength in China.

Description

technical field [0001] The invention belongs to the technical field of guidance and control, and relates to a time-delay-resistant and high-precision self-disturbance rejection attitude control method based on fixed-time differentiator prediction. Background technique [0002] The use of high-performance components is an important guarantee for the high-quality flight of the aircraft. However, the high cost brought by high-performance components has also brought a heavy burden to the national finances. While ensuring the flight quality of aircraft, reducing the production cost of aircraft and improving the cost-effectiveness of aircraft mission execution are effective ways to enhance my country's aviation strength. [0003] However, reducing the production cost of the aircraft means using low-cost but poor-performance components, which puts forward higher requirements for the design of the airborne software system. How to use high-quality navigation, guidance, control and o...

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Application Information

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IPC IPC(8): G05D1/08
CPCG05D1/0825
Inventor 韦常柱浦甲伦李源许河川米长伟
Owner HARBIN INST OF TECH
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