Small satellite liquefied gas constant pressure propulsion system and method

Abstract

The invention provides a system and method for liquefied gas constant-pressure propulsion of a small satellite. The system comprises a storage box, wherein ammonia is stored in the storage box in a gas-liquid two-phase form; a temperature sensor is installed on a shell of the storage box, and a high-pressure sensor is installed at an outlet pipe of the storage box and used to detect temperatures and pressures in the storage box; a heater is installed on the storage box and used to increase the storage box temperature and adjust the pressure of a propellant in the storage box; the storage box outlet pipe is equipped with a filling valve, and the filling valve is used to fill an ammonia propellant into the storage box; an output pipeline of the storage box is connected to a pressure reduction valve and used for throttling and temperature reduction of liquidated ammonia as well as stabilization of the downstream pressure; an output pipeline of the pressure reduction valve is connected to an evaporator, and the evaporator is installed on the storage box, is used for heat exchange with the high-temperature liquidated ammonia inside the storage box, and ensures that the gaseous propellant exists at an engine entrance; a low-pressure sensor is installed on an output pipeline of the evaporator and used to detect the pressure at the engine entrance; and an air-conditioning engine installed on the output pipeline of the evaporator provides push force and impulse needed by the satellite so as to satisfy demands for demands of functions including satellite attitude control and orbit control.

Description

technical field [0001] The invention relates to propulsion equipment for small satellites, in particular to a liquefied gas constant pressure propulsion system and method for small satellites. Background technique [0002] Due to the simple structure and mature system of liquefied gas-cooled propulsion equipment, it is widely used in the propulsion system of micro-satellites below 100 kilograms. At present, most liquefied gas-cooled propulsion systems use drop pressure systems, and the engine inlet is in a full liquid state or a gas-liquid mixed state, and the specific impulse of the engine is low. If you want to increase the total impact of the satellite, you can only increase the volume and weight of the storage tank, and you must reduce the payload of the micro-satellite. However, the payload generally cannot be reduced according to user requirements, and this problem is always difficult to solve. Contents of the invention [0003] In view of the defects in the prior a...

AI Technical Summary

Problems solved by technology

[0003] Aiming at the defects in the prior art, the object of the present invention is to provide a small satellite liquefied gas constant pressure propulsion system and method to solve the contradiction between the low specific impulse of the liquefied gas cold air propulsion equipment in the prior art and the high demand for the total impulse of the satellite

Utilizing the propellant throttling and cooling gasification and constant pressure propulsion technology of the present invention can solve the problem of small specific impulse of the liquefied gas propulsion system, thereby meeting the application requirements of small satellites

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