On-orbit estimation method for emission imbalance coefficient of storage tank system of spacecraft

Abstract

The invention relates to an on-orbit estimation method for an emission imbalance coefficient of a storage tank system of a spacecraft. The method comprises the steps that the whole aircraft initial states of the spacecraft are recorded, and the whole aircraft initial states comprise the whole aircraft initial weight M<s0>, mass center position (X<0>, Y<0>, Z<0>), main engine thrust vector nominalvalue FAs (F<As-x>, F<As-y>, F<As-z>) and main oxygen storage tank installation position (X<O10>, Y<O10>, Z<O10>) of the spacecraft; the first moment state of the spacecraft at a first on-orbit control end moment is recorded, and the first moment state comprises first moment whole aircraft mass Ms1, first moment disturbance torque TAs1 and first moment propellant consumption msp1; and the j moment state of the spacecraft at a j on-orbit control end moment is recorded, wherein the j moment state comprises j moment whole aircraft mass M<sj>, j moment disturbance torque T<Asj>and j moment propellant consumption amount m<spj>, and j is larger than 1, and the emission imbalance coefficient of the j moment state based on the whole aircraft initial state and the firstmoment state is estimated.

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...

AI Technical Summary

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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