Gas thrust vector control structure and method of hybrid rocket engine

A solid-liquid rocket, vector control technology, applied in rocket engine devices, machines/engines, jet propulsion devices, etc., can solve the problems of limited installation space, large thrust loss, constant loss, etc., and achieve a large thrust adjustment ratio, Easy and precise control, long life effect

Inactive Publication Date: 2018-01-30
BEIHANG UNIV
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Problems solved by technology

The size and weight of low-altitude anti-missile missiles and air-to-air missiles are relatively small, and the installation space is very limited. At present, the choke deflection type (gas rudder, gas slurry, spoiler, deflector ring) thrust vector with simple structure and relatively mature technology is mostly used. Control system, the thrust loss is large and there is a constant loss, and the rudder surface ablation problem is prominent

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  • Gas thrust vector control structure and method of hybrid rocket engine

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Embodiment Construction

[0024] specific implementation plan

[0025] The present invention will be described in further detail below in conjunction with the accompanying drawings.

[0026] The solid-liquid rocket engine gas injection vector control method of the present invention, wherein the solid-liquid rocket engine comprises a catalytic bed assembly 1, a front combustion chamber assembly 2, a combustion chamber 3, a rear combustion chamber assembly 4, a rear head assembly 5 and a nozzle 6, such as figure 1 shown.

[0027] The catalytic bed assembly 1 includes an engine head 101, a catalytic bed shell 102, a liquid injection panel 103 and a gas injection panel 104, all made of 1Cr18Ni9Ti stainless steel. Wherein, a port is coaxially opened on the engine head 101 as the inlet of the liquid propellant. The catalytic bed shell 102 is filled with catalyst, and the catalytic bed shell 102 and the engine head 101 are coaxially fixed and installed by bolts and nuts, and an O-shaped rubber is arranged b...

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Abstract

The invention discloses a hybrid rocket engine structure and method applicable to vector control. Secondary jet injection orifices are formed in the side wall of a front burning chamber of the hybridrocket engine; meanwhile second jet holes are evenly formed in the expansion segment of a spraying pipe in the circumference direction, and injectors are mounted in the secondary jet holes; the secondary jet injection orifices are communicated with the injectors through conveying pipes; the injectors are communicated with the interior of the spraying pipe through spraying and injecting passages formed in a thermal insulation layer of the spraying pipe; mixed gas in the front burning chamber is introduced to the expansion segment of the spraying pipe to conduct secondary spraying through the conveying pipes with the help of the secondary jet injection orifices. The mechanical mechanism is low in design mass, long in service life and suitable for long-time work; spraying gas is sprayed out from the spraying pipe, the engine performance is improved, and specific impulse loss caused by thrust adjustment is reduced.

Description

technical field [0001] The invention belongs to the technical field of thrust vector control, and designs a solid-liquid mixed rocket engine gas thrust vector control structure and method. Background technique [0002] Thrust vector control technology is closely related to the development of aerospace field. Because it can effectively improve the maneuverability of the engine, reduce the flight resistance and weight of the rocket, and improve the stealth ability, safety and survivability, it has become a key technology in the development of rocket engines and is being studied as a specialized technology. [0003] Most of the mechanical thrust vector control adopts hydraulic or mechanical actuating parts, and the thrust vector is generated through the steering control of the nozzle, nozzle adjustment piece or baffle plate, which increases the weight of the engine and increases the cost. Complex actuating parts and structures increase the complexity of the system. In high tem...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/82F02K9/72
Inventor 朱浩俞南嘉曹彬彬张源俊鞠梦贤
Owner BEIHANG UNIV
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