An On-orbit Estimation Method of Discharge Imbalance Coefficient of Spacecraft Tank System

Abstract

The invention relates to an on-orbit estimation method for the discharge unbalance coefficient of a storage tank system of a spacecraft, comprising: recording the initial state of the spacecraft, wherein the initial state of the spacecraft includes the initial weight M of the spacecraft s0 , the centroid position (X 0 , Y 0 ,Z 0 ), main engine thrust vector nominal value F As (F As‑x , F As‑y , F As‑z ), the installation location of the main oxygen tank (X O10 , Y O10 ,Z O10 ); record the state of the spacecraft at the first moment at the end of the first on-orbit control, wherein the state at the first moment includes the mass M of the entire vehicle at the first moment s1 , the disturbance moment T at the first moment As1 and the propellant consumption at the first moment m sp1 ;Record the status of the jth moment of the spacecraft at the end of the jth on-orbit control, and estimate the discharge imbalance coefficient for the jth moment state based on the initial state of the whole device and the first moment state, wherein the jth moment state includes The quality of the whole machine M at the jth moment sj , the disturbance moment T at the jth moment Asj and the propellant consumption m at the jth moment spj , and j>1.

Description

technical field [0001] The invention relates to the field of aerospace, in particular to an on-orbit estimation method for the discharge unbalance coefficient of a tank system of a spacecraft. Background technique [0002] For a spacecraft performing a large range of orbital maneuvers, it usually needs to carry multiple tanks for storing oxidizers and combustion agents. But because the tank used is a surface tension tank. To keep the internal gas and liquid from being separated, an additional arrangement of pressurized gas (usually helium) is required to be in direct contact with the propellant, and the propellant management device (PMD) near the outlet of the liquid circuit of the tank must be used to ensure the separation of gas and liquid and provide the fuel for the engine. Provides a propellant that does not entrain gas. [0003] Due to the differences in the air resistance of the pressurized gas path upstream of each storage tank, the PMD of each storage tank, and th...

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Problems solved by technology

[0004] The object of the present invention is to provide an on-orbit estimation method of the discharge imbalance coefficient of the spacecraft storage tank system, which is used to solve the problem that it is difficult to obtain the discharge imbalance coefficient of the storage tank during the flight mission

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