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Solar heat thruster

A technology of solar thermal and thruster, which is applied in the direction of solar thermal power generation, mechanical power generated by solar energy, jet propulsion device, etc. It can solve the problems of uneven heating of the concentrator, easy breakage, high heat source absorption rate, etc., and achieve improved convective conversion. Thermal effect, prevention of even cracking, effect of high specific impulse

Active Publication Date: 2014-08-27
NAT UNIV OF DEFENSE TECH
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Problems solved by technology

However, when the solar thermal thruster is working, the absorption cavity becomes a high-temperature heat source, and the concentrator has a high absorption rate of the heat source at this wavelength, which makes the concentrator easy to break due to uneven heating, and appropriate cooling measures are required

Method used

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Embodiment Construction

[0046] The specific embodiments of the present invention will be further described below in conjunction with the accompanying drawings. It should be noted here that the descriptions of these embodiments are used to help understand the present invention, but are not intended to limit the present invention.

[0047] A solar thermal thruster, including a thruster body 4, and laminated heat exchange cores 14, absorbers 1, uniformly distributed sleeves 3, and concentrators 2, etc., which are sequentially fixed on it, such as figure 2 Shown; the three-dimensional section view of the thruster is shown in image 3 As shown, the partial enlarged view of the heat exchange core part of the laminate is shown in Figure 4 shown.

[0048] The concentrator 2 is a refraction secondary concentrator, made of sapphire single crystal material, the upper part is a spherical surface, the middle part is a gyrotron, and the lower part is a triangular pyramid structure. It is fixed on the thruster ...

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Abstract

The invention discloses a solar heat thruster with high efficiency and high specific impulse, and belongs to the technical field of spacecraft space propulsion. According to the solar heat thruster, the secondary condenser regenerative cooling technology and the laminate heating efficient heat exchange core technology are adopted, a propellant is preheated, cracks caused by hot stress concentration of a secondary condenser are avoided, and the solar utilization rate of a system is improved through laminate heating efficient heat exchange. According to the solar heat thruster, under the same solar incident power, the heating efficiency of the solar heat thruster for the propellant is improved, the heating temperature of the propellant is increased, and the solar heat thruster has the advantages of high efficiency and high specific impulse.

Description

technical field [0001] The invention belongs to the technical field of spacecraft space propulsion, and in particular relates to a novel solar heat thruster with high efficiency and high specific impulse. Background technique [0002] Solar thermal propulsion technology uses the propellant to absorb heat from the heat source to generate high-temperature gas, which is then expanded and injected through the pneumatic nozzle to generate thrust. This technology uses small molecular weight gas (such as hydrogen) as the propellant, which can obtain a high specific impulse of 600-900s, which is An important development direction of space propulsion. The solar thermal propulsion system can realize the upper stage propulsion and the space main propulsion of the orbital maneuvering vehicle, especially for the orbital rapid maneuvering of satellites. [0003] The composition of the existing solar thermal thruster includes: the thruster body, the concentrator installed on it, the absor...

Claims

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Application Information

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IPC IPC(8): F03G6/06
CPCY02E10/46F02K9/42F02K9/52F02K9/60
Inventor 黄敏超程谋森邢宝玉
Owner NAT UNIV OF DEFENSE TECH
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