Calculation Method of Orbit Control Thrust Fitting Coefficients Based on Xia's Least Squares
A technology of orbit control and least squares, applied in the direction of complex mathematical operations, design optimization/simulation, special data processing applications, etc., can solve the error between theoretical speed increment and actual speed increment, difficulty in formulating orbit control strategy, no effective Using previous track control data to optimize calculations and other issues to achieve simple calculations, high prediction accuracy, and high calculation efficiency
Active Publication Date: 2022-05-17
中国人民解放军63789部队
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[0003] The traditional orbit control speed increment calculation only uses the calibration coefficient of the previous thruster as the calculation basis, and the thrust coefficient remains unchanged. It does not effectively use the previous orbit control data for optimal calculation, resulting in an unmeasurable error between the theoretical speed increment and the actual speed increment. , which brings certain difficulties to the formulation of orbital control strategies
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[0022] The present invention will be further described below in conjunction with the accompanying drawings and embodiments, and the present invention includes but not limited to the following embodiments.
[0023] Using the relationship between momentum and impulse during satellite orbit control, define the input quantities: tank pressure P (unit: Mpa) before orbit control, thrust action time Δt (unit: s), absolute temperature T of tank before orbit control x (Unit: K), theoretically calculated speed change ΔV x * (The subscript "x" represents the number of the fuel tank, x=1, 2), define the output: the actual speed change ΔV (unit: m / s), and establish the thrust fitting coefficient identification model. Through n sets of measurement data, the deviation in the least squares trajectory is gradually eliminated through an alternate solution algorithm that improves the accuracy of the deviation term successively, so as to obtain the estimated coefficient. The specific process is...
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The present invention provides a calculation method of orbit control thrust fitting coefficient based on Xia's least squares, which comprehensively analyzes the correlation of previous orbit control theoretical speed increments, actual speed increments, and orbit control thrust coefficients, and adopts Xia's least squares Multiply the estimated fitting coefficient characterizing the thrust, build a model that can imitate the real system behavior, and use the current measurable system input and output to predict the future evolution of the system output. The present invention uses historical track control data as input, and uses Charpy's method generalized least squares to calculate the actual thrust fitting coefficient. Therefore, the calculation of this method is relatively simple, and the prediction accuracy is high.
Description
technical field [0001] The invention relates to the field of measurement, control and management of in-orbit spacecraft, and is suitable for fitting calculation of thrust coefficient during orbit control of near-earth satellites. Background technique [0002] Due to the orbit attenuation caused by atmospheric resistance, the near-Earth satellite's ground trajectory will gradually deviate from the set trajectory. It is necessary to periodically maintain the orbit through the orbit control thruster so that the satellite's ground trajectory always meets the design requirements of the trajectory network. The thrust of the satellite orbit control thruster is a polynomial function with the pressure of the propellant tank as the independent variable, and its coefficient is a binding constant, which remains constant throughout the life of the satellite. With the increase of satellite orbit control times, the pressure of the propellant tank keeps decreasing, and there is a large erro...
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IPC IPC(8): G06F30/20G06F30/15G06F17/16
CPCG06F17/16G06F30/15G06F30/20
Inventor 卞燕山王西京陈军崔鹏张莹李伟张雷
Owner 中国人民解放军63789部队