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Aircraft gun pod exhaust gas diversion device

A technology of a deflector and a cannon, which is applied to the combustion, transportation and packaging of the air intake of the power unit, and the configuration of military equipment, etc., can solve the engine surge fault, reduce the purity of the engine intake, and affect the performance of the engine. and other problems, to achieve the effect of low cost, reduction of air gun exhaust gas, and light weight

Active Publication Date: 2019-03-29
JIANGXI HONGDU AVIATION IND GRP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The exhaust gas of the aircraft gun entering the air intake of the aircraft reduces the purity of the intake air of the engine, thereby affecting the normal working performance of the engine, and even causing the engine to have a surge failure

Method used

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  • Aircraft gun pod exhaust gas diversion device
  • Aircraft gun pod exhaust gas diversion device
  • Aircraft gun pod exhaust gas diversion device

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Embodiment Construction

[0019] In order to make the technical means, creative features, objectives and effects achieved by the present invention easy to understand, the present invention will be further described below in conjunction with specific illustrations.

[0020] like Figure 1 ~ Figure 2 As shown, the muzzle cap 1 of the ordinary aircraft gun is installed outside the main body 2 of the aircraft gun pod. When the gun is fired, part of the exhaust gas of the aircraft gun is discharged to both sides along the horizontal direction, and it is easy to enter the air inlets 3 on both sides of the aircraft, thereby affecting the normal operation of the engine. Work.

[0021] see Figure 3 to Figure 9 An aircraft gun pod exhaust gas diversion device, including an inverted concave shape structure composed of an arc surface and a semi-open diversion channel 5, in order to reduce the impact of the aircraft gun exhaust gas on the engine, it is installed at the front end of the aircraft gun pod main body ...

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PUM

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Abstract

An exhaust gas diversion device for an aircraft gun pod, comprising an inverted concave structure formed by an arc surface and a semi-open diversion channel, the inverted concave structure is installed on the front end of the main body of the aircraft gun pod and covers the muzzle cap, and The inverted concave structure forms a three-sided semi-open surround on the muzzle cap, thereby preventing the exhaust gas from the aircraft gun from diffusing to the air intakes on both sides of the aircraft; under the action of the incoming air in front, the exhaust gas from the aircraft gun is guided along the exhaust gas The channel spreads backward and downward. In the present invention, the waste gas guide device of the cannon pod is added to build a diversion channel and then change the flow direction of the cannon exhaust gas, thereby achieving the goal of reducing the amount of cannon exhaust gas entering the air intakes on both sides of the aircraft at the minimum cost, ensuring normal operation of the engine.

Description

technical field [0001] The invention relates to the technical field of aircraft aerodynamic diversion, in particular to an exhaust gas diversion device for an aircraft gun pod. Background technique [0002] Mounting the cannon pod is one of the standing external capabilities of fighter jets. When the cannon pod is mounted in front of the air intake on the belly of the aircraft, the exhaust gas generated by the cannon enters the air intakes on both sides of the aircraft backwards. The exhaust gas from the aircraft gun that enters the air intake of the aircraft reduces the purity of the intake air of the engine, thereby affecting the normal working performance of the engine, and even causing the engine to surge. Contents of the invention [0003] The technical problem to be solved by the present invention is to provide an exhaust gas guiding device for a cannon pod to solve the above-mentioned shortcomings in the background technology. [0004] The technical problem solved ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64D33/02B64D7/00
CPCB64D7/00B64D33/02
Inventor 谭洪开刘卓闫会明蒋黄滔程太明何明清辛荣提王石山潘应雄杨帆吴德广吴宝林姜亚楠
Owner JIANGXI HONGDU AVIATION IND GRP