Detachable ablation test device for nozzle throat liner of solid rocket engine
An engine nozzle and solid rocket technology, which is applied in the direction of chemical analysis using combustion, can solve the problems of difficult simulation of the working process environment of the engine nozzle, and achieves the effects of simple structure, high controllability and convenient disassembly
Pending Publication Date: 2020-05-08
NANJING UNIV OF SCI & TECH
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Problems solved by technology
[0005] In order to solve the above problems, the present invention provides a detachable solid rocket motor nozzle throat liner ablation test device, which solves the problem that the working environment of the engine nozzle is difficult to simulate. The test device uses the same solid propellant as the real engine agent, the working conditions of the real engine are simulated by scaling the engine, so that the ablation of the nozzle throat liner is close to the real state
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[0024] In order to make the object, technical solution and advantages of the present invention clearer, the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the present invention, not to limit the present invention.
[0025] The implementation of the present invention will be described in detail below in conjunction with specific embodiments.
[0026] like Figure 1-4 As shown, a detachable solid rocket motor nozzle throat liner ablation test device includes a test engine unit and a nozzle unit, and the test engine unit includes an engine top cover 1, an engine combustion chamber casing 2 and an engine combustion chamber Liner 3, the engine top cover 1 is connected to the other end of the engine combustion chamber casing 2 by screws, and the powder column 4 is housed in the engine combustion chamber casing 2, a...
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The invention discloses a detachable ablation test device for a nozzle throat liner of a solid rocket engine. The detachable ablation test device comprises a test engine unit and a nozzle unit, wherein the test engine unit comprises an engine combustion chamber shell body, the nozzle unit comprises a nozzle front-section shell body and a nozzle rear section shell body, one end of the engine combustion chamber shell body is detachably connected to one end of the nozzle front-section shell body, the other end of the nozzle front-section shell body is detachably connected to one end of the nozzlerear-section shell body, the nozzle unit forms a throat part at a joint of the nozzle front-section shell body and the nozzle rear-section shell body, and a throat liner is arranged on the inner wallof the throat part. The problem that the environment is difficult to simulate in the working process of the engine nozzle is solved, the detachable ablation test device adopts a solid propellant thesame as that of a real engine, the working condition of the real engine is simulated by means of a scaling engine, and the ablation condition of the nozzle throat liner is close to the real state.
Description
technical field [0001] The invention relates to the technical field of solid rocket motor testing, in particular to a detachable solid rocket motor nozzle throat lining ablation test device. Background technique [0002] Due to its simple structure, low cost, convenient and quick maintenance, and strong rapid response capability, solid rocket motors are used as the main power device for missile propulsion devices and rocket weapon systems at home and abroad. As an important component of energy conversion in solid rocket motors, the nozzle can convert gas thermal energy and pressure potential energy into flow kinetic energy. [0003] The Laval nozzle consists of a converging section, a throat, and a diverging section, which realizes the continuous change from subsonic flow to supersonic flow. During the working process of the solid rocket motor, due to the effects of thermochemical ablation and mechanical erosion, the ablation behavior of the engine nozzle will be caused, wh...
Claims
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Login to View More IPC IPC(8): G01N31/12
CPCG01N31/12
Inventor 刘万励陈雄李映坤
Owner NANJING UNIV OF SCI & TECH