Nozzle joint heat-proof ring and processing method adapted to lateral overload
A processing method and heat protection technology, applied to jet propulsion devices, machines/engines, rocket engine devices, etc., can solve the problems of large negative mass, large margin, unreasonable design, etc., and achieve optimal margin and low negative mass , the effect of reducing weight
Active Publication Date: 2020-08-18
XIAN AEROSPACE PROPULSION TECH INST
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Problems solved by technology
The traditional heat protection ring is a rotary structure, such as figure 1 As shown, the heat insulation thickness in all directions is the same. For large lateral overload missiles, this leads to insufficient margin of the joint heat protection ring in the lateral overload direction, large margin in the non-transverse overload direction, unreasonable design, and large negative mass, which is not conducive to solid rockets. Enhanced engine performance
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[0019] The present invention will be described in detail below with reference to the accompanying drawings and examples.
[0020] The invention provides a nozzle joint heat-proof ring and a processing method adapted to lateral overload. The heat-proof ring of the joint is composed of high silicon oxide cloth / phenolic aldehyde in the inner layer and carbon cloth / phenolic aldehyde in the outer layer. The eccentric structure of the thickness is obtained by the following processing methods:
[0021] Step 1, without considering the lateral overload, according to the engine pressure, working time, swing angle and other working condition parameters and the overall requirements of the missile, the ablation heat transfer calculation of the joint heat protection ring is carried out to determine the size of the joint heat protection ring under the condition of no lateral overload, The thickness of the thermal protection ring of the joint under the condition of no lateral overload is reco...
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The invention discloses a spray pipe joint heat prevention ring adaptive to transverse overload and a machining method. The spray pipe joint heat prevention ring adaptive to transverse overload is characterized in that the central axis of the inner shape of the joint heat prevention ring is an axis I, the central axis of the outer shape of the heat prevention ring is an axis II, the axis I is parallel to the axis II, and the axis II is away from the axis I by a set distance in the transverse overload direction. According to the spray pipe joint heat prevention ring adaptive to transverse overload and the machining method, the heat resistance of the joint heat prevention ring can be enhanced in the transverse overload influence direction, and the structure mass can be obviously reduced.
Description
technical field [0001] The invention relates to the technical field of solid rocket motor nozzles, in particular to a heat-proof ring for a nozzle joint adapting to lateral overload and a processing method thereof. Background technique [0002] The flexible nozzle of the solid rocket motor is located at the tail of the combustion chamber. It is composed of a fixed body, a throat liner assembly, a joint heat-proof ring and an expansion section. The high pressure of the gas is mainly supported by metal parts, and the metal parts must be Thermal protection to prevent it from losing its strength due to heat. The joint heat-proof ring of the nozzle is the heat protection part of the front flange of the flexible joint, which has better ablation resistance and heat insulation capacity. During the working process of the engine, the front flange of the flexible joint will not be caused by excessive temperature rise. And lose strength. [0003] At present, both anti-missile missiles...
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IPC IPC(8): F02K9/97
CPCF02K9/97
Inventor 李国才李鑫史宏斌吕江彦卢颖刘雨李耿安春利屈转利孙展鹏
Owner XIAN AEROSPACE PROPULSION TECH INST