Ground target staring anti-saturation tracking control method of microsatellite

A micro-satellite, tracking and control technology, applied in attitude control and other directions, can solve problems such as system time lag

Inactive Publication Date: 2014-12-31
SHANGHAI XINYUE METER FACTORY
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  • Abstract
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  • Application Information

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Problems solved by technology

[0006] The invention aims to solve the problem of the system time lag caused by the torque saturation of the ac

Method used

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  • Ground target staring anti-saturation tracking control method of microsatellite
  • Ground target staring anti-saturation tracking control method of microsatellite
  • Ground target staring anti-saturation tracking control method of microsatellite

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Embodiment Construction

[0035] By reading the detailed description of the non-limiting embodiment done with reference to the following accompanying drawings, the anti-saturation tracking control method for the micro-satellite staring at the ground includes the following steps:

[0036] 1) Establish a micro-satellite attitude tracking dynamic model;

[0037] The attitude dynamic equation of the rigid body spacecraft is:

[0038] which is:

[0039] In the formula: is the microsatellite inertia matrix; is the attitude angular velocity of the micro-satellite body coordinate system relative to the inertial coordinate system; is the control torque acting on the tracking star body; is the external disturbance moment acting on the tiny stellar body. Take the state quantity as:

[0040]

[0041] The state equation is:

[0042] in

[0043]

[0044] is the dynamic noise, the Perform linearization and go to the first-order approximation to get:

[0045]

[0046] According to the m...

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Abstract

Provided in the invention is a ground target staring anti-saturation tracking control method of a microsatellite. The method comprises the following steps: establishing a microsatellite attitude tracking dynamical model; constructing an appropriate Lyapunov functional unit and carrying out processing on an execution mechanism saturation model by using an additional matrix method; designing a feedback controller; and calculating an estimation range of an attraction domain. Therefore, problems of state time delay and execution mechanism output torque saturation during the satellite attitude tracking process can be solved; closed-loop system stability during the spacecraft staring tracking process can be ensured; and the ground target staring or space target reconnoiter task can be completed. Compared with the prior art, the influence on the attitude control system by time delay caused by system state data obtaining and processing can be eliminated and a design problem of a controller having execution mechanism saturation non-linear system can be solved; and attraction domain estimation can be completed with a low conservative property. The method can be applied to designs of other controllers having execution mechanism saturation and state time delay systems as well as attraction domain estimation.

Description

[0001] technical field [0002] The invention relates to micro-satellite attitude tracking control technology, belongs to the field of spacecraft control, in particular to a micro-satellite staring anti-saturation tracking control method for the ground. Background technique [0003] Micro-satellites have become increasingly popular in various aerospace equipment and space due to their fast and flexible ability to adapt to tasks, low-cost and fast access to space, strong survivability in distributed applications, and superior time and space coverage characteristics. An important part of the application system. Using micro-satellites to control the attitude is relatively easy and the response is fast. The observation camera is fixedly installed on the micro-satellite, and the camera observation axis is stared at the ground with the help of satellite attitude control, which can be used for land census, ocean census, natural disaster forecast, crop census, and weather forecast. ...

Claims

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Application Information

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IPC IPC(8): G05D1/08
Inventor 顾玥侯建文吴猛张志伟刘宇谭天乐
Owner SHANGHAI XINYUE METER FACTORY
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