Air suction type solar heat micro thruster

A micro-thrust, solar energy technology, which is applied in solar thermal power generation, mechanical power generation with solar energy, machines/engines, etc., can solve the problems of large thrust value that cannot meet the precise control of satellite attitude, low operating orbit, and large power consumption, etc. Achieve the effect of enhancing orbital maneuverability, reducing weight and increasing thrust

Active Publication Date: 2016-07-13
NAT UNIV OF DEFENSE TECH
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Problems solved by technology

[0002] The operable orbit of modern satellites is getting lower and lower, and there are even ultra-low orbit satellites operating in the atmosphere 120-300km from the ground. These satellites need attitude control and resistance compensation during operation. Conventional chemical propulsion technology burns propellants by Ther

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  • Air suction type solar heat micro thruster
  • Air suction type solar heat micro thruster
  • Air suction type solar heat micro thruster

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Embodiment Construction

[0039] Specific implementation plan

[0040] The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative work shall fall within the protection scope of the present invention.

[0041] The whole of the micro thruster is in a cubic configuration, and its top view is as Figure 14 As shown, its size is 1.80m×1.10m×1.10m (length×width×height). First, a concave rotating paraboloid is machined on the upper and bottom surface, such as Figure 15 As shown, the cube is then cut into two symmetrical parts along the axis 1.2, and the shapes of the inlet, diffuser and nozzle, as well as ...

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Abstract

The invention provides an air suction type solar heat micro thruster. The air suction type solar heat micro thruster mainly comprises a main body, an air intake channel, a diffuser pipe, a light collecting system, a heat exchange structure and a spraying pipe. The air suction type solar heat micro thruster has the advantages that the air suction type solar heat micro thruster can be applied to an ultra-low orbit satellite in an atmospheric layer which is 120-300km away from ground, air entering the micro thrust is heated by collected solar energy to obtain high-temperature air, the high-temperature air is sprayed out by the spraying pipe to produce about 0.02-2N thrust, and the thrust is very suitable for the attitude adjusting and drag compensation of the satellite; because a working medium of the micro thruster is mainly thin air, and the solar energy is used for heating, an aircraft only carries a small amount of propellant, thus the weight of the thruster is reduced, the maneuverability of an orbit is improved, the effective load of the aircraft is increased, and the on-orbit time of the aircraft is prolonged; by supplementing the propellant, the thrust produced by a thrusting system is increased, and the space application range of the aircraft is expanded.

Description

Technical field [0001] The invention belongs to the technical field of spacecraft propulsion systems, and particularly relates to an air-breathing solar thermal micro-thruster. Background technique [0002] The operable orbit of modern satellites is getting lower and lower, and there are even ultra-low orbit satellites operating in the atmosphere at a distance of 120 to 300 km from the ground. Such satellites require attitude control and resistance compensation during operation. Conventional chemical propulsion technology uses combustion propellant Thermal energy is converted into kinetic energy to generate thrust to propel the orbiting satellite to change its orbit, but the generated thrust value is too large to meet the precise adjustment of the satellite's attitude; the thrust value of electric propulsion ranges from 0.1 to 0.005N, and the thrust value is too small, when the satellite changes orbit It takes a long time to consume a lot of power. At present, the orbiting satel...

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Application Information

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IPC IPC(8): F03G6/06
CPCY02E10/46F03G6/06
Inventor 黄敏超杜运良李印
Owner NAT UNIV OF DEFENSE TECH
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