Supersonic air inlet channel plugging cap device

A technology of air inlet and supersonic speed, which is applied in jet propulsion devices, gas turbine devices, ramjet engines, etc., can solve the problems of complex structure of blocking cap devices, unfavorable protection of carrier aircraft safety, and generation of projectiles, etc., to achieve increased The effect of strength and rigidity, uniform force, and easy maintenance

Active Publication Date: 2019-03-19
JIANGXI HONGDU AVIATION IND GRP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] Most of the air intake caps currently used are split-type caps or mechanical caps. Although ideal results have been achieved in the process of upgrading and daily maintenance, there are still many problems. The existing problems are as follows: One is that throwing objects will be produced during the transfer process, which is not conducive to protecting the safety of the carrier aircraft; the other is that the process of opening the cover will greatly disturb the missile; the third is that the structure of the blocking device is complicated

Method used

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  • Supersonic air inlet channel plugging cap device
  • Supersonic air inlet channel plugging cap device
  • Supersonic air inlet channel plugging cap device

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Embodiment Construction

[0018] The present invention will be further described in detail below in conjunction with examples, but the embodiments of the present invention are not limited thereto.

[0019] A supersonic air inlet plugging device of the present invention comprises a plugging body 1, a damping member 2, a support rod 3, a drive motor 4, a detonator 5, and a cable 6, such as figure 1 shown.

[0020] A plurality of damping parts 2 are evenly distributed and fixedly sleeved around the main body 1 of the plugging cover. After the damping parts 2 are extruded, they are closely matched with the inner wall surface 7 of the air intake duct. The main body 1 of the plugging cover is provided with a driving motor 4 and a detonator 5. The driving motor 4 and The detonator 5 is installed on the outer wall surface 8 of the air inlet, two pairs of support rods 3 are respectively arranged in the middle of the front and rear sides of the main body of the plugging cover 1, and the two drive motors 4 are r...

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Abstract

The invention relates to a supersonic air inlet channel plugging cap device. The supersonic air inlet channel plugging cap device comprises a plugging cap body (1), a damping piece (2), a supporting rod (3), a driving motor (4), an exploder (5) and a cable (6). The supersonic air inlet channel plugging cap device has the definite mounting position and the quite good fastening and damping effects,mounting and demounting operation can be conducted conveniently and quickly, disturbance to a missile in the cap opening process is small, force bearing is uniform, ejecta is not generated after blasting, the safety of an aerial carrier is facilitated, the number of structural pieces is small, and maintenance is easy.

Description

technical field [0001] The invention belongs to the field of supersonic air inlet blocking cover, in particular to an air inlet inlet blocking device for a supersonic missile ramjet engine. Background technique [0002] The inlet capping device is one of the key components in the process of supersonic missile ramjet conversion, and plays a key role in connecting the booster stage to the ramjet stage. Its main function is that when the booster is working, it must be able to withstand the wind load at the inlet of the inlet, and work stably in a short period of time under the condition of heat accumulation during the acceleration process, so as to avoid panting of the inlet during acceleration. Vibration, when the ramjet engine is working, the inlet cover of the air inlet should be opened in time to allow air to flow into the afterburning chamber. [0003] Most of the air intake caps currently used are split-type caps or mechanical caps. Although ideal results have been achie...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C7/057F02K7/14
CPCF02C7/057F02K7/14F05D2220/10
Inventor 张邦楚刘涛赵胜海孙子杰张林袁晓昱王啸雄邓波江海涛余文锋马少杰龙海燕刘剑
Owner JIANGXI HONGDU AVIATION IND GRP
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