Autonomous vaporization management method and liquid ammonia micro-propulsion system

Abstract

The invention discloses an autonomous vaporization management method and a liquid ammonia micro-propulsion system. The method is implemented in a way that a storage tank, a cut-off valve and a vaporizer are sequentially connected to form a vaporization device, the vaporizer is heated to completely vaporize a liquid ammonia propellant in the vaporizer, and thus constant pressure vaporization or pressurized vaporization is realized. The system applies the method to a propulsion system, the vaporizer which completely vaporizes the liquid ammonia propellant is arranged in the system, and thus the propellant is finally completely output at a relatively high specific impulse through a thruster in the gaseous form; heating is performed to adjust the pre-thrust pressure, and thus the output thrust is controlled. According to the micro-propulsion system, the thrust can be accurately and stably controlled, and furthermore, the problem of difficulty in precisely measuring the remaining propellant of the liquid ammonia propulsion system is solved by using the specific heat characteristic of liquid, and reusing heating of the storage tank, and a temperature-collecting pressure-collecting device. The system can improve the in-orbit maneuver capability of micro / nano-satellites and has great significances on expanding the space application of micro-nano satellites.

Description

technical field [0001] The invention relates to the technical field of micro-nano-satellite orbit control, in particular to a micro-nano-satellite-based autonomous vaporization management method and a liquid ammonia micro-propulsion system. Background technique [0002] The on-orbit maneuverability of micro-nano-satellites is an important factor in determining their mission functions, and the micro-propulsion system is the core actuator for implementing orbital maneuvers. Micro-nano satellites have limited overall star resources, and the structure, volume, power consumption, and propulsion fluid of their propulsion systems are all subject to high constraints, which are obviously inferior to conventional satellites. Therefore, the performance of conventional propulsion systems is difficult to meet the needs of micro-nano satellites, which has become the main limiting condition for the expansion of on-orbit applications of micro-nano satellites. [0003] As one of the mature ...

AI Technical Summary

Problems solved by technology

Part of the propulsion system directly uses the superheated flash characteristics of liquefied gas to generate thrust. This method will cause the propellant jet to be mixed with liquid droplets, the thrust is not stable enough and the specific impulse is low; the propulsion system with its own vaporization heating device, usually in the vaporization process With the drop pressure design, the drop pressure ratio is usually high, and the thrust is not easy to control

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