Comprehensive balance discharge adjustment method for parallel tank propulsion system

A technology of comprehensive balance and adjustment methods, which is applied in the directions of propulsion system devices, control/regulation systems, and space navigation equipment of space navigation vehicles. And other issues

Active Publication Date: 2019-12-03
CHINA ACADEMY OF SPACE TECHNOLOGY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The actual installation positions of the parallel storage tanks of different spacecraft will be different, so the remaining propellant mass of the two storage tanks after adjustment is independent from the mass before adjustment, and it is diverse, but it only adapts to the adjustment volume (after multiplying the density i.e. mass) is a special case of adjusting half of the volume difference of the remaining

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  • Comprehensive balance discharge adjustment method for parallel tank propulsion system
  • Comprehensive balance discharge adjustment method for parallel tank propulsion system
  • Comprehensive balance discharge adjustment method for parallel tank propulsion system

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Embodiment Construction

[0115] The present invention will be described in further detail below in conjunction with the accompanying drawings.

[0116] Such as figure 1 As shown, the spacecraft parallel storage tank chemical propulsion system generally includes 4 storage tanks, including 2 oxygen tanks and 2 fuel tanks, which are oxygen tank a MON-a, oxygen tank b MON-b, fuel tank a MMH- a. Fuel tank b MMH-b. The oxidant is discharged in parallel between the two oxygen tanks, that is, the downstream propellant outlets of oxygen tank a MON-a and oxygen tank b MON-b are respectively provided with self-locking valves LV5 and LV7 downstream of the storage tanks, and then connected together, and lead to the engine Eng An oxidant inlet to supply oxidant to the engine Eng. The upstream gas inlets of oxygen tank aMON-a and oxygen tank b MON-b are respectively provided with upstream self-locking valves LV1 and LV3 of the storage tanks, and then communicated together.

[0117] The combustion agent is dischar...

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Abstract

The invention discloses a comprehensive balance discharge adjustment method for a parallel tank propulsion system. The adjustment method comprises the following steps of (1), setting state parametersbefore adjustment, (2) performing oxygen tank balance discharge adjustment, and (3) performing fuel tank balance discharge adjustment. According to the comprehensive balance discharge adjustment method, the fact that the actual installation positions of spacecraft parallel tanks are discrepant is considered, and the mass of residual propellant in the two tanks after adjustment is independent of the mass before adjustment in the process of balance discharge adjustment of the parallel tank propulsion system so that comprehensive balance adjustment requirements of 'propellant mass * tank axis distance' can be realized and adapted. A main process and a sub process are fully parameterized, and an iterative cycle, an interpretation branch and other calculation methods are introduced so as to facilitate programming of the calculation program, thus reducing the time for determining control parameters.

Description

technical field [0001] The invention relates to a comprehensive balance discharge adjustment method of a parallel storage tank propulsion system, which uses the state parameters before system adjustment, the adjustment target parameters, the inherent design parameters of the storage tank, and the property parameters of the working medium as input quantities to accurately and quickly calculate the Integrated balanced discharge regulation requires an inflated tank and an inflated pressure. Background technique [0002] The two-component parallel tank chemical propulsion system of a spacecraft uses two working fluids, oxidizer and combustion agent, as propellants. The propulsion system generally consists of four parts: a high-pressure gas circuit module, a propellant storage module, an engine module, and an electronic circuit module. The function of the high-pressure gas circuit module is to store high-pressure gas and provide a stable flow of pressurized gas to the propellant...

Claims

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Application Information

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IPC IPC(8): B64G1/40G05D16/02
CPCB64G1/402G05D16/028
Inventor 孙恒超李峰吕红剑李静涛刘敏王莉娜
Owner CHINA ACADEMY OF SPACE TECHNOLOGY
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