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Propulsion system and method based on interaction between space atomic oxygen and substance

A propulsion system, atomic oxygen technology, applied in the direction of aerospace vehicle propulsion system devices, space navigation equipment, space navigation vehicles, etc., to achieve the effect of protecting the risk of erosion

Inactive Publication Date: 2017-05-17
BEIJING INST OF SPACECRAFT ENVIRONMENT ENG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] At present, there is no propulsion technology that uses atomic oxygen in low earth orbit as an oxidant, uses alkaline metals or their hydrides as fuel, and uses the chemical reaction between the two to achieve propulsion

Method used

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  • Propulsion system and method based on interaction between space atomic oxygen and substance
  • Propulsion system and method based on interaction between space atomic oxygen and substance
  • Propulsion system and method based on interaction between space atomic oxygen and substance

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Embodiment approach 1

[0024] see figure 1 , figure 1 It is a structural schematic diagram of a propulsion system for interaction between atomic oxygen and matter according to an embodiment of the present invention. In this specific embodiment, the propulsion system of the present invention mainly consists of a trumpet-like atomic oxygen collection device 2, a chemical reaction chamber 3, an atomic oxygen reflection control device 4, a chemical propellant 5, and a thrust direction control device 6, The atomic oxygen collection device is in the shape of a bell mouth and is arranged at the bottom of the front end of the spacecraft 1, and its closing part is connected with two relatively inclined side walls of the chemical reaction chamber 3, and chemical propellants 5 are respectively arranged on the two side walls, and the atomic oxygen passes through After the atomic oxygen collection device 2 flows into the chemical reaction chamber, an atomic oxygen reflection control device 4 is arranged in the ...

Embodiment approach 2

[0026] see figure 2 , figure 2 It is a structural schematic diagram of a propulsion system for interaction between atomic oxygen and matter according to another embodiment of the present invention. This implementation mode and implementation mode one (see figure 1 ) The main difference lies in the atomic oxygen reflection control device 4. figure 1 The atomic oxygen reflection device in the method controls the amount of atomic oxygen reflected on the reactant by changing the angle between the two reflectors. figure 2 In the embodiment, the included angle of the single atomic oxygen reflector is controlled to control the quantity of atomic oxygen incident on the reactant. Others are the same as the first embodiment.

Embodiment approach 3

[0028] see image 3 , image 3 It is a structural schematic diagram of a propulsion system for interaction between atomic oxygen and matter according to another embodiment of the present invention. This implementation mode and implementation mode one (see figure 1 ) with the main difference in device 4, figure 1 The device 4 in is an atomic oxygen reflection device, image 3 The device 4 in the formula is a control device for the amount of atomic oxygen entering, and by adjusting the distance between the device 4 and the inlet of atomic oxygen, the control of the amount of atomic oxygen entering is realized, and then the reaction heat and the gas generation rate are realized. Others are the same as the first embodiment.

[0029] Specifically, the atomic oxygen collection device is in the shape of a bell mouth, with the purpose of collecting atomic oxygen on the windward side; at the same time, the size of the bell mouth is designed according to the needs, and placed on the...

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Abstract

The invention discloses a propulsion system and method based on the interaction between space atomic oxygen and a substance. The propulsion system comprises an atomic oxygen collecting front end, a chemical reaction chamber and a propulsion direction control device, wherein the chemical reaction chamber comprises an atomic oxygen reflection control device and a chemical reaction device; the atomic oxygen collecting front end is positioned on the windward side of a spacecraft; the atomic oxygen collected by the atomic oxygen collecting front end is reflected to the chemical reaction device through the atomic oxygen reflection control device after entering the reaction chamber; the atomic oxygen has chemical reaction with an alkaline substance to generate high temperature particle flows; and the number of the particle flows can be realized through a reflection angle of the atomic oxygen reflection control device. Compared with the traditional propulsion mode, the propulsion system based on the interaction between the space atomic oxygen and the substance is advantaged in that the waste is turned into wealth, the atomic oxygen harmful to the spacecraft is changed into a fuel source of the propulsion, and a continuous power is provided to orbit maneuver of the spacecraft on a low earth orbit while the spacecraft is protected against being eroded by the atomic oxygen.

Description

technical field [0001] The present invention relates to the field of propulsion technology for spacecraft in low earth orbit, specifically, the present invention relates to a propulsion system and method based on the interaction between space atomic oxygen and matter, especially atomic oxygen is used as a fuel source for propulsion, and it is used to combine with alkali The chemical reaction of alkaline substances is easy to occur. By controlling the amount of atomic oxygen that reacts with alkaline substances, the amount of thrust generated on low-orbit spacecraft is controlled, and the direction of thrust is realized by controlling the injection direction of chemical reactants. control. Background technique [0002] At altitudes of 200km to 700km in low Earth orbit, the main components of the remnant atmosphere are atomic oxygen O and molecular nitrogen N 2 , wherein the atomic oxygen content is about 80%, and the molecular nitrogen content is about 20%. The atomic oxyge...

Claims

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Application Information

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IPC IPC(8): B64G1/40
CPCB64G1/40B64G1/402B64G1/409
Inventor 沈自才刘业楠丁义刚白羽王志浩马子良
Owner BEIJING INST OF SPACECRAFT ENVIRONMENT ENG