A variable nozzle micro solid rocket motor and its manufacturing method
A technology for a solid rocket and a manufacturing method, which is applied in the aerospace field, can solve the problems that the thrust of a micro solid motor cannot be further improved, the processing process is dangerous, the nozzle layer structure is damaged, etc., and the manufacturing process is safe and reliable, the structure is simple, and the thrust is increased. the effect of
Active Publication Date: 2017-09-29
BEIHANG UNIV
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Problems solved by technology
[0011] The purpose of the present invention is to solve the problem that the existing miniature solid rocket motor has complicated processing technology, high processing precision, high difficulty, high risk in the processing process and many equipments required, easy to cause damage to the structure of the nozzle layer, poor stability of the whole mechanism, The precision shape is insufficient, and only the nozzle layer with a specific nozzle angle can be processed, which cannot further improve the thrust of the micro solid engine, and cannot meet the different requirements of different engines for the nozzle angle
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[0038] The specific implementation manners of the present invention will be further described in detail below in conjunction with the accompanying drawings and examples. The following examples are used to illustrate the present invention, but are not intended to limit the scope of the present invention.
[0039] In the description of the present invention, it should be noted that the orientation or positional relationship indicated by the terms "upper", "lower", "inner", "outer", "top", "bottom" etc. are based on the Orientation or positional relationship is only for the convenience of describing the present invention and simplifying the description, and does not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as a limitation of the present invention.
[0040]In the description of the present invention, it should be noted that, unless otherwise clearl...
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The invention relates to the technical field of spaceflight, in particular to a nozzle-variable micro solid rocket engine and a manufacturing method of the engine. Through a dry etching technology, the surface of a power layer is etched, and the aim that the nozzle-variable micro solid rocket engine can be wholly and transversely arranged on the power layer; the processing flow is greatly simplified, the machining precision is high, the manufacturing process is safe and reliable, and the integration is high; when a shape of an engine groove to be manufactured is etched on a mask, the machining slope of an exhaust nozzle is changed according to needs, and nozzle-variable micro solid rocket engines produced in the same batch can meet the machining requirement of exhaust nozzle structures of different engines; and optimal design of the exhaust nozzle is achieved, thrust is improved, flexibility of processing and manufacturing is improved, industrialized production is greatly promoted, and the manufacturing cost is reduced.
Description
technical field [0001] The invention relates to the field of aerospace technology, in particular to a miniature solid rocket motor with a variable nozzle and a manufacturing method thereof. Background technique [0002] Microsatellites have gradually become a new direction for future aerospace research due to their low price, standardized, and mass-produced advantages. As the core technical system of micro-satellite, the micro-power system, its reliability, fast response, high precision and high reliability and cost factors become the key to the successful development of micro-satellite. [0003] Traditional micro-electric propulsion technology, micro-cooled air propulsion technology and micro-plasma propulsion technology have relatively large defects in volume and quality, resulting in high launch costs for micro-satellites, which limits their application prospects on micro-spacecraft . In order to develop a low-cost, high-reliability micro-aircraft power system, countrie...
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IPC IPC(8): F02K9/34F02K9/97
CPCF02K9/34F02K9/97
Inventor 陶智李秋实李海旺纪国圣吴弘涛田腾跃
Owner BEIHANG UNIV