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Method for carrying out on-satellite high-precision calculation on deviations of semi-major axes of double satellites

A semi-major axis, high-precision technology, applied in vehicle position/route/altitude control, non-electric variable control, instruments, etc., can solve problems such as large errors and periodic changes, and achieve a clear process, simple algorithm implementation, The effect of improving calculation accuracy

Active Publication Date: 2019-01-11
SHANGHAI AEROSPACE CONTROL TECH INST
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Problems solved by technology

[0004] At present, the deviation of the semi-major axis of the double satellite is usually obtained by direct navigation filtering calculation of the relative position and velocity output by the GPS receiver on the star. The influence of other factors has a larger error

Method used

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  • Method for carrying out on-satellite high-precision calculation on deviations of semi-major axes of double satellites

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Embodiment Construction

[0023] The present invention will be further described below through specific embodiments in conjunction with the accompanying drawings. These embodiments are only used to illustrate the present invention, and are not intended to limit the protection scope of the present invention.

[0024] Such as figure 1 Shown is a schematic diagram of the offset L and the semi-major axis deviation Δa in the formation dynamics model. The invention provides a method for calculating the semi-major axis deviation of double satellites with high precision on a satellite, and the method is applied in a satellite attitude and orbit control sub-system. The method for calculating the deviation of the semi-major axis of the double star with high precision on the star specifically includes:

[0025] Step 1: Determine the data update time Δt, the data can be modified by the number of notes on the star;

[0026] The data refers to the current moment t(k) and the offset L(k); k is the kth data, and k i...

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Abstract

The invention discloses a method for carrying out on-satellite high-precision calculation on deviations of semi-major axes of double satellites. The method comprises the following steps of: firstly carrying out navigation filter calculation to obtain a deviation between opposite orbital elements of the double satellites according to opposite position information of the current satellites; carryingout calculation to obtain a tangential diversion central offset L (k) between the double satellites at the current moments t(k); and inversely calculating a deviation of a semi-major axis by utilizing a deviation drift rate of the offset, so as to greatly improving the precision of the deviation of the semi-major axis. The method is capable of improving the semi-major axis deviation obtaining precision without increasing extra hardware resources, and is simple in calculation and easy to realize.

Description

technical field [0001] The invention relates to the technical field of satellite orbit navigation and control, in particular to a method for calculating the semi-major axis deviation of a double satellite with high precision on a satellite. Background technique [0002] Spacecraft formation flight is a new space operation mode of spacecraft that appeared in the late 1980s with the development of microsatellites. Compared with a single spacecraft, satellite formation flight has very prominent advantages, and has been favored by all aerospace powers in the world since the concept was born. [0003] In order to ensure formation configuration, formation navigation and control are required. Among them, the binary star dynamic model of formation navigation is based on the theoretical basis that the semi-major axes of the two stars should be exactly the same. In actual engineering, due to the influence of orbital perturbation and formation control residuals, the semi-major axes o...

Claims

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Application Information

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IPC IPC(8): G05D1/10
CPCG05D1/104
Inventor 王文妍崔佳杨盛庆贾艳胜王禹訾海峰杨超孙英梅翟文涛
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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