Different-surface crossover quick-change track fixed time stable posture pointing direction tracking control method

An out-of-plane crossing and fixed-time technology, which is applied in the direction of space navigation vehicle guidance devices, space navigation equipment, and observation of space navigation vehicles, etc. problem, to achieve the effect of saving space, high-precision attitude tracking and pointing, and reducing complexity

Active Publication Date: 2015-04-22
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0008] The purpose of the present invention is to solve the problem that the prior art does not consider the uncertainty of the inertia of the spacecraft, depends on the initial value of the state, and cannot freely adjust the convergence time, and the

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  • Different-surface crossover quick-change track fixed time stable posture pointing direction tracking control method
  • Different-surface crossover quick-change track fixed time stable posture pointing direction tracking control method
  • Different-surface crossover quick-change track fixed time stable posture pointing direction tracking control method

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specific Embodiment approach 1

[0036] Specific implementation mode 1: Combination figure 1 In this embodiment, the method for tracking fixed-time stable attitude pointing and tracking for different-plane crossing fast-changing orbits is characterized in that: the method for tracking fixed-time stable attitude pointing and tracking for different-plane crossing fast-changing orbits specifically follows the following steps:

[0037] Step 1. Assuming that the tracking star and the target star are in a cross orbit, the tracking star needs to detect the position of the target star autonomously. In order to make the laser transmitter or observation equipment of the tracking star always point to the target star, first determine the desired attitude;

[0038] Step 2. Design of desired attitude tracking control law;

[0039] Step 3: Eliminate the chattering of the desired attitude tracking control law;

[0040] Step 4. The desired attitude of the orbital intersection of the tracking star and the target star varies with the d...

specific Embodiment approach 2

[0041] Specific embodiment two: This embodiment is different from specific embodiment one in that it is characterized in that in the first step, the tracking star and the target star are located in different cross orbits, and the tracking star needs to detect the target's position autonomously. The laser transmitter or observation device of the tracking star always points to the target star. First, determine the desired attitude. The specific process is:

[0042] The unit vector of each coordinate axis of the desired attitude coordinate system is determined by the following formula in the inertial system:

[0043] i = r t - r c | r t - r c |

[0044] j = i X r c | i X r c | - - - ( 1 )

[0045] k=i×j

[0046] Where r t With r c Are the position vectors of the tracking star and the target star in the geocentric inertial coordinate system;

[0047] If the cosine transformation matrix of the d...

specific Embodiment approach 3

[0050] Specific embodiment three: This embodiment is different from specific embodiments one or two in that it is characterized in that the design of the desired attitude tracking control law in the second step, the specific steps are:

[0051] Calculate the desired attitude angle and the body attitude angle under the unit vector of each coordinate axis of the desired attitude coordinate system:

[0052] Record the desired attitude angle and the body attitude angle as a d And a b , Their difference is Euler's attitude angle error, denoted as e, that is, e=a b -a d , Let the system state be Can write linearized state equation

[0053] e ‾ e - - = 0 1 0 0 e e ‾ + 0 1 I ‾ ( u - a - - d I ) - - - ( 3 )

[0054] Where I is the principal inertia of the corresponding axis, and the expected angular acceleration of the attitude is bounded during at...

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Abstract

The invention relates to a different-surface crossover quick-change track fixed time stable posture pointing direction tracking control method. The different-surface crossover quick-change track fixed time stable posture pointing direction tracking control method aims at solving the problems that the uncertainty of inertia of a spacecraft is not considered in the prior art, the convergence time can not be freely adjusted depending on the state initial value, and compensating moment generated in the singular direction of a flywheel needs to be designed artificially. The method comprises the particular steps that 1, a tracking satellite and a target satellite are supposed to be located on a different-surface crossover track, and the expected posture needs to be determined; 2, an expected posture tracking control rule is designed; 3, buffeting of the expected posture tracking control rule is eliminated; 4, the expected posture of the crossed points of the tracking satellite and the target satellite changes along with distance between the crossed points of the tracking satellite and the target satellite, a configuration scheme of an execution mechanism is determined according to the expected posture tracking control rule, and the expected posture control torque is solved. The different-surface crossover quick-change track fixed time stable posture pointing direction tracking control method is applied to the field of satellite control.

Description

Technical field [0001] The invention relates to a method for tracking and tracking a stable posture in a fast-changing orbit of different planes. Background technique [0002] In 1957, the former Soviet Union launched its first man-made earth satellite, which marked a big step forward in human exploration of space. Nowadays, aerospace technology has become one of the most interesting technologies in the world. It promotes the advancement of human science and technology and expands the field of human activities from the atmosphere to the outer space. Among them, various scientific satellites and application satellites serving scientific research, national economy and military affairs have been greatly developed. Satellites have been used in various fields of life, such as meteorological satellites, remote sensing satellites, reconnaissance satellites, navigation satellites, earth resources satellites, etc. . And the abundant space resources have also caused competition among cou...

Claims

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Application Information

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IPC IPC(8): B64G1/24B64G3/00
Inventor 孙延超马广富刘昱晗赵文锐朱津津李传江李卓
Owner HARBIN INST OF TECH
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