Heat-proof device for swing type rocket engine nozzle

A rocket engine, swing type technology, applied in rocket engine units, jet propulsion units, machines/engines, etc., can solve the problems of high stiffness, flame backflow, poor ablation resistance, etc., and achieve a high barrier to good gas flow good ablative properties, and the effect of avoiding burnt equipment

Pending Publication Date: 2020-06-26
TIANJIN ISTAR ADVANCED MATERIAL TECH CO LTD
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The object of the present invention is to provide a heat-proof device for the nozzle of a swinging rocket engine to solve the problem in the prior art that the skirt of the swinging engine is made of metal or composite material and has poor ablation resistance; The structure of the conical surface has a high rigidity, which can easily cause the jet flame to flow back, burn the internal equipment, and cause the technical problem of skirt plate fracture

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  • Heat-proof device for swing type rocket engine nozzle
  • Heat-proof device for swing type rocket engine nozzle
  • Heat-proof device for swing type rocket engine nozzle

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Embodiment Construction

[0060] It should be noted that the embodiments of the present invention and the features in the embodiments can be combined with each other if there is no conflict.

[0061] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "transverse", "upper", "lower", "front", "rear", "left", "right", " The orientation or positional relationship indicated by "vertical", "horizontal", "top", "bottom", "inner", "outer" etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and The description is simplified, rather than indicating or implying that the pointed device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation of the present invention. In addition, the terms "first", "second", etc. are only used for descriptive purposes, and cannot be und...

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Abstract

The invention discloses a heat-proof device for a swing type rocket engine nozzle, and belongs to the technical field of heat-proof and insulation devices for space launch. The heat-proof device for the swing type rocket engine nozzle comprises a nozzle flange, a cabin shell rear end cover and a heat-proof telescopic apron board; the nozzle flange is connected with an inner ring end surface of theheat-proof telescopic apron board, and the cabin shell rear end cover is connected with an outer ring end surface of the heat-proof telescopic apron board; the section of the heat-proof telescopic apron board is of a corrugated structure; and the heat-proof telescopic apron board is made of flexible ablation-resistant heat-proof materials. The problems that the structure is cracked due to poor ductility, and internal equipment is burnt by flame backflow since the apron board is of a flat plate type or conical surface heat insulation structure made of metal or composite materials are solved. The heat-proof telescopic apron board is made of flexible ablation-resistant heat-proof materials, and the section is of the corrugated structure, the flame of an engine can be prevented from flowing back to the interior of a cabin body, the returned flame is blocked from entering the cabin body, and the heat-proof device has high barrier property on ablation property and gas flow.

Description

Technical field [0001] The invention relates to the technical field of aerospace launch anti-heat insulation device, in particular to a heat protection device for a swinging rocket engine nozzle. Background technique [0002] At the moment of ignition, the engines of spacecraft such as rockets will eject high-temperature flames and gas streams. The instantaneous temperature range will reach between 3000K and 4000K, accompanied by high-speed particle erosion. During the injection process, the high-temperature gas flow injected along the nozzle of the engine will also produce a local flame backflow, which directly washes the outside of the nozzle of the engine and the end of the tail section shell. A lot of equipment is installed inside, therefore, skirt boards need to be installed for heat insulation protection. [0003] With the development of rocket engine technology, swing engines have been widely used in special occasions. In the prior art, the installation position of the noz...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/97
CPCF02K9/97
Inventor 唐占文刘含洋麻永帅王志勇
Owner TIANJIN ISTAR ADVANCED MATERIAL TECH CO LTD
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