A non-pyrotechnic missile with diversion air intake structure

A technology with air intake structure and non-pyrotechnics, which is applied in the direction of self-propelled bombs, offensive equipment, projectiles, etc., can solve the problems of limited application fields, high cost, and inability to use, so as to broaden application fields, reduce operating costs, The effect of expanding the field of use

Active Publication Date: 2020-04-07
西安恒宇众科空间技术有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] In the field of aviation, defense of important places, and important occasions, in order to prevent terrorists from using drones to carry out terrorist attacks, it is necessary to use missiles to counter terrorism. At present, solid-fuel missiles are commonly used, and solid-fuel missiles are pyrotechnic products. High risk, storage and transportation require special qualifications
In addition, the flight time of pyrotechnic missiles is short, and the ballistic trajectory is single during the flight process. There is only one interception opportunity, and they cannot be recycled and reused. The cost is high and it will cause serious collateral damage.
[0003] Although pyrotechnic missiles have high speed and fast response, their application fields are severely limited due to their inherent shortcomings, and they cannot be used in many occasions. At present, it is basically the way of wireless interference
There are shortcomings such as serious lack of mobility, poor effect, and high dependence on personnel

Method used

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  • A non-pyrotechnic missile with diversion air intake structure
  • A non-pyrotechnic missile with diversion air intake structure
  • A non-pyrotechnic missile with diversion air intake structure

Examples

Experimental program
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Effect test

Embodiment 1

[0021] A kind of non-pyrotechnic guided missile of the present invention has diversion air intake structure, such as figure 1 As shown, it includes a missile body 1 and a ducted engine 3 coaxially arranged front and rear, and an air inlet channel is formed between the missile body 1 and the ducted engine 3; the end of the missile body 1 is the front end, and when starting, the air enters the channel Enter the ducted engine 3, discharge after compression, and generate thrust to make them fly or move; the inside of the missile body 1 is a hollow cavity, and the rear part is used as an instrument compartment, and a controller is placed in it. The use of pressurized air to provide power avoids the use of traditional solid fuel combustion to provide power, and there will be no risk of explosion. The rear section of the missile body 1 is set in a spindle shape for guiding air into the ducted motor 3 . During the flight of the missile, the external gas enters the ducted engine along...

Embodiment 2

[0032] The difference between this embodiment and embodiment 1 is that, as figure 2 As shown, the rear end of the duct housing 3-1 is also connected with an external cavity 4, and the inner wall of the external cavity 4 is provided with air rudders 5 at intervals around its circumference. The air rudder 5 is arranged on the outer wall through the rotating shaft, and under the impact of the external air flow, the air rudder 5 rotates around the rotating shaft to ensure the flight direction of the missile. As long as there is airflow passing through, the air rudder 5 works in real time to adjust the attitude of the missile.

[0033] In its working process, after the missile is started, when there is air flow passing through, the air rudder 5 can adjust the attitude and flight direction of the missile at any time.

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PUM

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Abstract

The invention discloses a non-initiating-explosive-device guided missile with a flow-guiding air inlet structure. The non-initiating-explosive-device guided missile with the flow-guiding air inlet structure comprises a missile body and a duct engine coaxially arranged front and back, wherein an air inlet passage is formed between the missile body and the duct engine; the end on which the missile body is the front end; when starting, air enters the duct engine through the air inlet channel and is discharged after being compressed so as to produce the thrust for enabling the missile to fly or act; and a hollow cavity is arranged in the missile body, the rear section of the missile body is used as an instrument cabin, and a controller is placed in the missile body. The non-initiating-explosive-device guided missile with the flow-guiding air inlet structure is powered by air so as not to be exploded, and can stay in air for a longer time.

Description

technical field [0001] The invention belongs to the technical field of missile manufacturing, and in particular relates to a non-explosive missile with a diversion air intake structure. Background technique [0002] In the field of aviation, defense of important places, and important occasions, in order to prevent terrorists from using drones to carry out terrorist attacks, it is necessary to use missiles to counter terrorism. At present, solid-fuel missiles are commonly used, and solid-fuel missiles are pyrotechnic products. High risk, storage and transportation require special qualifications. In addition, the flight time of pyrotechnic missiles is short, and the ballistic trajectory is single during the flight. There is only one chance of interception, and they cannot be recycled and reused. The cost is high and it will cause relatively serious collateral damage. [0003] Although pyrotechnic missiles have high speed and fast response, their application fields are severel...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F42B15/00F41H13/00
CPCF41H13/00F42B15/00
Inventor 陈昊明张宝生马永刚李爱华
Owner 西安恒宇众科空间技术有限公司
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