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Integrated cold air propulsion system

A propulsion system and air-conditioning technology, applied in the direction of aerospace vehicle propulsion system devices, etc., can solve the problems of large system volume and weight, high heating power, large space occupation, etc., and achieve high propulsion efficiency, easy implementation, and compact structure.

Active Publication Date: 2019-09-24
深圳市魔方卫星科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Existing cold gas propulsion systems mainly contain propellants such as nitrogen, liquid ammonia, butane, etc., and conduits are used to connect various components, which require on-site connection and coordination of pipelines. The stability of the system is not good, it takes up a lot of space, the installation efficiency is low, the airtightness is not enough, and the problem of valve leakage is prone to occur
In addition, the specific impulse of the nitrogen cold air propulsion system is small, it is difficult to liquefy, the system volume and weight are large, and it is easy to leak; the liquid ammonia cold air propulsion system has a small specific impulse, high heating power, poisonous, flammable and explosive; Small specific impulse, flammable and explosive, large system volume, easy to leak

Method used

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Embodiment Construction

[0025] In order to make the object, technical solution and advantages of the present invention clearer, the present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described here are only used to explain the present invention, not to limit the present invention.

[0026] In order to make the description of the present disclosure more detailed and complete, the following provides an illustrative description of the implementation modes and specific examples of the present invention; but this is not the only form for implementing or using the specific embodiments of the present invention. The description covers features of various embodiments as well as method steps and their sequences for constructing and operating those embodiments. However, other embodiments can also be used to achieve the same or equivalent functions and step sequences.

[0027] T...

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Abstract

The invention relates to the technical field of micro satellite propulsion system control, in particular to an integrated cold air propulsion system. The integrated cold air propulsion system comprises a storage tank, a liquid cavity, an air cavity, a propellant management device and a propulsion device, the built-in design is adopted in the propellant management device and the propulsion device, and the propellant management device and the propulsion device are packaged in the storage tank, so that connection pipelines between the devices are eliminated, the structure is more compact, the occupied space is reduced, and meanwhile, the connection is more stable and reliable. The liquid cavity is connected with the air cavity by the propellant management device, and the liquid cavity and the air cavity are controlled to be isolated or connected. During connection, the propellant management device controls a liquid R134a single-component propellant to be converted into a gaseous R134a single-component propellant, the gaseous R134a single-component propellant is output to the air cavity to ensure that the propellant of the air cavity is purely gaseous, and higher propulsion efficiency is achieved. The R134a single-component propellant is adopted, the integrated cold air propulsion system is non-toxic, safe and environmentally friendly. Vaporization and liquefaction are easily achieved at a normal temperature, and large thrust and large specific impulse are achieved.

Description

technical field [0001] The invention relates to the technical field of micro-satellite propulsion system control, in particular to an integrated cold air propulsion system. Background technique [0002] The propulsion system is mainly used in the satellite control system, which has the functions of adjusting the satellite attitude and orbit. In the micro-satellite control system, the propulsion systems used mainly include cold air propulsion system, chemical propulsion system, and electric propulsion system. Existing cold gas propulsion systems mainly contain propellants such as nitrogen, liquid ammonia, butane, etc., and conduits are used to connect various components, which require on-site connection and coordination of pipelines. The stability of the system is not good, it takes up a lot of space, the installation efficiency is low, the airtightness is not enough, and the problem of valve leakage is prone to occur. In addition, the specific impulse of the nitrogen cold a...

Claims

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Application Information

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IPC IPC(8): B64G1/40
CPCB64G1/40
Inventor 丁强强滕浩黄国龙张浩翔陈豪智
Owner 深圳市魔方卫星科技有限公司
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