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A method for regulating and balancing emissions based on a gas bypass-free propulsion system

A propulsion system, gas-free technology, which is applied to the propulsion system devices of space navigation vehicles, jet propulsion devices, and space navigation equipment, etc., can solve the problems of high system complexity, high hardware cost, and heavy system weight, etc.

Active Publication Date: 2019-06-18
BEIJING INST OF CONTROL ENG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, the dual-component propulsion system with a gas bypass has many problems such as high system complexity, high system weight, and high hardware cost.

Method used

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  • A method for regulating and balancing emissions based on a gas bypass-free propulsion system
  • A method for regulating and balancing emissions based on a gas bypass-free propulsion system
  • A method for regulating and balancing emissions based on a gas bypass-free propulsion system

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Embodiment Construction

[0023] The present invention will be described in further detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the present invention, but not to limit the present invention. In addition, it should be noted that, for the convenience of description, only some structures related to the present invention are shown in the drawings but not all structures.

[0024] figure 1 is a structural diagram of a gas-bypass bicomponent propulsion system in an embodiment of the present invention, such as figure 1 As shown, a typical spacecraft propulsion system with a parallel storage tank structure without gas bypass is basically composed of a gas cylinder 1, a pressure sensor 2, a discharge valve 3, a pressure reducer 4, a one-way valve 5, and a self-locking valve 6 , a propellant storage tank 7, an orbital control engine 8 and an attitude control thruster 9; wherein, the gas ...

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Abstract

The invention discloses a balanced discharging adjustment method based on an air-bypath-free propulsion system. The balanced discharging adjustment method comprises the steps that at a satellite orbittransfer ending moment, self-locking valves LV1, LV2 and LV3 are turned off for two storage boxes MON-A and MON-B arranged in the air-bypath-free double-component propulsion system in parallel and containing the same propellant, a self-locking valve LV4 is turned on, and the storage box pressures of the two storage boxes and the mass and density of the residual propellant are obtained respectively; the target regulation pressure point of the storage box MON-B containing more propellant is calculated; the self-locking valve LV3 corresponding to the MON-B is turned on, the pressure of the storage box MON-B is increased to the target regulation pressure point, and then the self-locking valve LV3 is turned off; the self-locking valve LV2 is turned on, and the propellants in the two storage boxes are balanced by utilizing pressure difference. The purpose of adjusting balanced discharging of the parallelly connected storage boxes of the air-bypath-free double-component propulsion system isachieved by adopting the balanced discharging adjustment method.

Description

technical field [0001] The invention relates to the technology of a spacecraft dual-component propulsion system, in particular to a method for adjusting and balancing discharge based on a gas-free bypass propulsion system. Background technique [0002] The dual-component propulsion system of the satellite uses MON-1 (oxidant) and MMH (combustion agent) as the working fluid. The dual-component propulsion system of the truss satellite requires at least 4 propellant tanks, and 2 MON-1, 2 tanks for MMH, these 4 tanks are arranged symmetrically in the satellite, and the same kind of propellant is used in parallel to ensure that the center of mass of the propellant is on the central axis of the satellite. When the balance discharge of the parallel tanks deviates, the deviation of the remaining propellant in the tanks will gradually increase, which will affect the center of mass of the satellite and increase the disturbance moment during the orbit change process. At this time, it i...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K9/44B64G1/40
CPCB64G1/402
Inventor 尹文娟宋涛丁凤林梁军强林震马云华王猛杰焦焱李铁虎王贺
Owner BEIJING INST OF CONTROL ENG
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