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Propelling system mixing ratio control method considering parallel storage tank pressure difference

A technology of a propulsion system and a control method, which is applied in the direction of differential pressure control, fluid pressure control, and propulsion system devices of space navigation vehicles, etc., can solve the problems such as inconvenience of system state changes

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

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Problems solved by technology

[0007] 2) It is not clear how to calculate the specific value of the system mixing ratio before and after the control, which is not convenient enough to evaluate the change of the system state before and after the control

Method used

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  • Propelling system mixing ratio control method considering parallel storage tank pressure difference
  • Propelling system mixing ratio control method considering parallel storage tank pressure difference
  • Propelling system mixing ratio control method considering parallel storage tank pressure difference

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Embodiment Construction

[0121] The present invention will be described in further detail below in conjunction with the accompanying drawings.

[0122] like 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.

[0123] The combustion agent is discharged...

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Abstract

The invention discloses a propelling system mixing ratio control method considering parallel storage tank pressure difference. The method comprises the following steps of (1) setting a state parameterbefore controlling; (2) calculating the balance pressure of parallel oxidant tanks; (3) calculating the balance pressure of parallel combustion agent tanks; and (4) controlling the mixing ratio. According to the method, the actual on-orbit working condition that the pressure between the two parallel storage tanks is imbalance before the mixing ratio of a spacecraft parallel storage tank propelling system is controlled is considered, the calculation flow of the balance pressure between the two parallel storage tanks before mixing ratio control is given, the method is suitable for the state that the on-orbit pressure of the parallel storage tank propelling system is unbalanced, and the on-orbit efficient utilization of propellant is realized; and the main process and the sub-process are all-parametric, iterative loop, interpretation branch and other calculation modes are introduced, so that a calculation program is convenient to compile, and then the time for determining a control parameter is reduced.

Description

technical field [0001] The invention relates to a method for controlling the mixing ratio of a propulsion system considering the pressure difference of parallel storage tanks. The state parameters before the system mixing ratio control, the control target parameters, the inherent design parameters of the engine and storage tanks, and the property parameters of the working fluid are used as input quantities, which are accurate, Quickly calculates which tank to fill and the pressure to fill for system mix ratio control. 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 pr...

Claims

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Application Information

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IPC IPC(8): B64G1/40G05D16/02
CPCB64G1/402G05D16/028
Inventor 孙恒超吕红剑李峰刘敏裴胜伟王莉娜
Owner CHINA ACADEMY OF SPACE TECHNOLOGY
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