A heat-proof and flow-conducting structure for a small liquid engine
An engine and liquid technology, applied in the direction of machines/engines, rocket engine devices, mechanical equipment, etc., can solve problems affecting the normal operation of spacecraft products, low heat conduction, etc., and achieve light weight, low emissivity, and good economical effect
Active Publication Date: 2018-07-06
SHANGHAI AEROSPACE SYST ENG INST
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Problems solved by technology
The present invention adopts the technical solution of ablation-resistant and low-thermal-conduction composite material molding integral molding to solve the problem of ablation and heat generation of surrounding products caused by high-temperature tail flame jet flow of the engine and expansion of tail flame in vacuum state when working in the liquid engine compartment. After radiation, it will affect the normal operation of spacecraft products
Method used
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[0014] The present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments.
[0015] figure 1 The heat-proof and flow-guiding structure of the small liquid engine shown includes: a flow-guiding tube 1, a fire baffle A2, a fire baffle B3, combined with figure 2 , image 3 As shown, the fire baffle A2 and the fire baffle B3 are installed on the flange of the guide tube 1 by screws. The guide tube 1 is provided with two flange surfaces, the arc flange A and the end flange B; the arc flange A is connected with the cabin body, and the end flange B is connected with the fire baffle A2 and the fire baffle B3.
[0016] The inner diameter of the guide tube must be designed according to the diameter of the engine nozzle to ensure a reasonable gap between the two; the inner diameter of the fire baffle must be smaller than the diameter of the engine nozzle to prevent backfire when the exhaust flame of the engine expands rapidly ...
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The invention relates to a heatproof flow guiding structure of a small liquid engine. The heatproof flow guiding structure comprises a flow guiding cylinder and an anti-backfire baffle plate, is formed by adopting a method for mold pressing of a high-silica phenolic resin composite material, is mounted at the nozzle outlet of the small liquid attitude and orbit control engine in a cabin, is connected with the cabin through flanges at the body part, and is used for guiding tail flame jet flow of the engine out of the cabin; and fireproof plates are mounted on the end surface of the heatproof flow guiding structure, thereby preventing the impact of backfire caused after tail frame expansion of the engine in the vacuum state on the normal operation of the heatproof flow guiding structure in the cabin. When being mounted, the heatproof flow guiding structure provided by the invention is prevented from being in direct contact with an engine nozzle; meanwhile, the heatproof flow guiding structure is low in heat conductivity and resistant to ablation; and the problem that when the small liquid engine which has to be mounted in the cabin works, the normal operation of the heatproof flow guiding structure is impacted by the tail flame jet flow is solved.
Description
technical field [0001] The invention relates to a heat-preventing and conducting structure, in particular to a heat-preventing and conducting structure for a small liquid engine used in a launch vehicle. Background technique [0002] The engines responsible for stabilizing the attitude of launch vehicles and missiles are generally arranged on the outer wall of the sub-stage cabin, the bottom of the outer box of the cabin, or the engine rack. The engine arranged on the outer wall of the cabin must be provided with a protective cover on the outside, which will cause aerodynamic interference to the flight process; the engine arranged on the bottom of the outer box of the cabin or on the engine rack, in order to avoid the impact of the engine jet on the surrounding products, only After the work of the next level is finished, the work starts after the separation between the levels. A certain type of rapid launch launch vehicle in my country uses a built-in attitude control engin...
Claims
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IPC IPC(8): F02K9/60
Inventor 向长征孙培杰曾玉琴韩伟周遇仁吴辉
Owner SHANGHAI AEROSPACE SYST ENG INST