Flywheel rotating speed optimization method in remote sensing satellite imaging period

An optimization method and technology of remote sensing satellites, applied in the field of aerospace, can solve problems such as unstable attitude and low flywheel, and achieve the effect of avoiding severe shaking of attitude

Pending Publication Date: 2021-12-07
CHANGGUANG SATELLITE TECH CO LTD
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Problems solved by technology

[0008] In order to solve the problem of attitude instability caused by too low flywheel rotation speed during satellite imaging, the invention proposes a flywheel rotation speed optimization method according to the principle of angular momentum conservation without adding additional flywheels and other attitude control stand-alone machines, which avoids imaging During the flywheel rotation speed is too low, the invention provides a flywheel rotation speed optimization method during remote sensing satellite imaging, the invention provides the following technical solutions:

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  • Flywheel rotating speed optimization method in remote sensing satellite imaging period
  • Flywheel rotating speed optimization method in remote sensing satellite imaging period
  • Flywheel rotating speed optimization method in remote sensing satellite imaging period

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specific Embodiment 1

[0045] according to Figure 1 to Figure 6 As shown, the specific optimization technical scheme adopted by the present invention for solving the above-mentioned technical problems is: a method for optimizing flywheel speed during remote sensing satellite imaging, comprising the following steps:

[0046] Step 1: Establish satellite body coordinate system, including satellite body coordinate system, orbital coordinate system, desired coordinate system, sun-aligning coordinate system, and earth inertial coordinate system J2000;

[0047] The step 1 is specifically:

[0048] Establish the satellite body coordinate system. The satellite body coordinate system refers to the ObXbYbZb rectangular coordinate system fixed to the satellite. The coordinate origin Ob is at the center of mass of the satellite. The +X axis is in the same direction as the satellite’s flight direction, and the +Z axis is perpendicular to the satellite docking ring and The docking surface of the transition secti...

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Abstract

The invention relates to a flywheel rotating speed optimization method in a remote sensing satellite imaging period. According to the method, a satellite body coordinate system is established and comprises a satellite body coordinate system, an orbital coordinate system, an expected coordinate system, a sun coordinate system and an earth inertial coordinate system J2000; establishing flywheel expected angular momentum during an imaging task; and performing flywheel rotating speed optimization during imaging. The satellite is in a conventional mode during a non-task period, and the flywheel angular momentum in the mode is managed by using the magnetic torquer, so that when the satellite is converted into an earth imaging attitude at any moment, the rotating speed of the three-axis flywheel is close to the expected rotating speed, and the severe attitude jittering caused by the too low rotating speed of the flywheel is avoided. The method is suitable for the situation with space environment interference, and the satellite attitude in a conventional mode is not required to be always in inertial space stability.

Description

technical field [0001] The invention relates to the field of aerospace and the technical field of attitude control of spacecraft, and relates to a method for optimizing the rotational speed of a flywheel during remote sensing satellite imaging. Background technique [0002] In order to optimize the flywheel speed during satellite imaging, avoid affecting the imaging quality due to too low flywheel speed. During the imaging mission of remote sensing satellites, the satellites are required to have high attitude stability. The satellites with the reaction flywheel as the main control actuator, when the flywheel speed crosses zero, due to the sudden reversal of the friction torque, the satellite attitude will vibrate violently, thus Therefore, it is of great significance to prevent the flywheel from being in the low speed range when the satellite is imaging. [0003] According to the principle of conservation of angular momentum, the rotational speed of the satellite's three-ax...

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Application Information

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IPC IPC(8): G06F30/15G06F30/17G06F30/20B64G1/24B64G1/28G06F119/14
CPCG06F30/15G06F30/17G06F30/20B64G1/244B64G1/283G06F2119/14
Inventor韩霜雪范林东钟兴戴路刘洁冰
OwnerCHANGGUANG SATELLITE TECH CO LTD