Flow positioning adjustable direct-current injector for high-concentration hydrogen peroxide variable-thrust hybrid rocket engine
A technology of hydrogen peroxide and solid-liquid rockets, which is applied in the direction of rocket engine devices, machines/engines, mechanical equipment, etc., can solve the problems of system reliability reduction, mixing ratio fluctuations, complex structures, etc., and achieve strong versatility and injection The effect of small pressure drop and fast response
Active Publication Date: 2016-08-17
BEIHANG UNIV
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Problems solved by technology
Although the improved double-needle valve injector has improved the problems of large fluctuations in the mixing ratio and unreliable shutdown to a certain extent, the structure is more complicated and the reliability of the system is reduced.
Method used
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[0024] The present invention will be further described in detail with reference to the accompanying drawings and embodiments.
[0025] The present invention is a flow positioning adjustable direct current injector suitable for high-concentration hydrogen peroxide variable-thrust solid-liquid rocket engines, such as figure 1 As shown, it includes a head cover 1 , an injector housing 2 , a valve core 3 , an upper cover 4 , an inlet joint 5 and an impact nut 6 .
[0026] like figure 2 As shown, the head cover 1 is a cylindrical structure with an inner cavity 101 inside; an engine mounting flange 102 is designed around the bottom end of the head cover 1 for the connection between the head cover 1 and the engine. There is a propellant inlet 103 on the top surface of the skull 1, and the inlet joint 5 is fixed at the propellant inlet 103, so that the inlet joint 5 communicates with the inner cavity 101 of the skull 1; the inlet joint 5 is fixed by welding for connecting the propel...
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The invention discloses a flow positioning adjustable direct-current injector for a high-concentration hydrogen peroxide variable-thrust hybrid rocket engine. The flow positioning adjustable direct-current injector for the high-concentration hydrogen peroxide variable-thrust hybrid rocket engine comprises a head cover, an injector shell, a valve element, an upper cover and an inlet joint. The inlet joint is mounted on the top of the head cover and is fixed in a cavity of the head cover; a gap is formed between the inlet joint and the head cover; a propellant inlet is formed in the outer wall of the injector shell; a propellant outlet is formed in the bottom end of the injector shell; and the upper cover is further mounted on the top of the injector shell. The valve element is arranged in a cavity of the injection shell; a propellant which enters the cavity of the head cover from the inlet joint enters the cavity of the injector shell via the propellant inlet; the valve element is driven to act through a spring and gas-liquid pressure difference; the valve element is separated from the propellant outlet; and the propellant is sprayed out. The flow positioning adjustable direct-current injector for the high-concentration hydrogen peroxide variable-thrust hybrid rocket engine is simple and reliable, small in injection pressure drop, small in size and quick in response, and can keep relatively small injection pressure drop change when flow adjustment is relatively large by matching with an adjustable venturi tube.
Description
technical field [0001] The invention relates to a flow positioning adjustable direct current injector. The invention is an injector suitable for a variable-thrust solid-liquid rocket engine using high-concentration hydrogen peroxide as an oxidant. Background technique [0002] The variable thrust rocket engine can provide controllable power for the propulsion and control of the spacecraft, and increase the adaptability and maneuverability of the spacecraft to the mission and orbit. It is an ideal choice for the power system of the aerospace vehicle. With the increase of human space exploration activities year by year, the importance of developing variable thrust propulsion technology becomes more and more obvious. According to the working principle of the rocket engine, the thrust is related to factors such as propellant flow rate, nozzle exit area and nozzle throat area. Due to limited conditions, it is very difficult to change the nozzle exit area and nozzle throat area....
Claims
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Login to View More IPC IPC(8): F02K9/32
CPCF02K9/32
Inventor 俞南嘉赵博王珏
Owner BEIHANG UNIV