CN108955423B

CN108955423B - Non-priming-tool missile with diversion air inlet structure

Info

Publication number: CN108955423B
Application number: CN201810676471.2A
Authority: CN
Inventors: 陈昊明; 张宝生; 马永刚; 李爱华
Original assignee: Xi'an Hengyu Zhongke Space Technology Co ltd
Current assignee: Xi'an Hengyu Zhongke Space Technology Co ltd
Priority date: 2018-06-27
Filing date: 2018-06-27
Publication date: 2020-04-07
Anticipated expiration: 2038-06-27
Also published as: CN108955423A

Abstract

The invention discloses a non-priming-tool missile with a flow-guiding air inlet structure, which comprises a missile body and a ducted engine, wherein the missile body and the ducted engine are coaxially arranged in front and back, and an air inlet channel is formed between the missile body and the ducted engine; the missile body end is the front end, when the missile body end is started, air enters the ducted engine through the air inlet channel, is compressed and then is discharged, and thrust for flying or acting is generated; the missile body is internally provided with a hollow cavity, the rear section of the missile body is used as an instrument bin, and a controller is placed in the instrument bin. The non-explosive missile with the diversion air inlet structure provides power by air, does not explode, and can stay in the air for a longer time.

Description

Non-priming-tool missile with diversion air inlet structure

Technical Field

The invention belongs to the technical field of missile manufacturing, and particularly relates to a non-priming-tool missile with a flow guide air inlet structure.

Background

In the aviation field, defense to land and important occasions, in order to prevent terrorists from using unmanned aerial vehicles to carry out terrorist attack, missile anti-terrorism needs to be used, at present, the missiles which are commonly used are solid fuel missiles, the solid fuel missiles are initiating explosive devices, the danger is high, and special qualifications are needed for storage and transportation. In addition, the missile of the initiating explosive device has short flight time, single trajectory in the flight process, one-time interception opportunity, incapability of being recycled and reused, high cost and serious collateral damage.

Although the initiating explosive device missile is high in speed and quick in response, the application field of the initiating explosive device missile is severely limited due to inherent defects of the initiating explosive device missile, the initiating explosive device missile cannot be used in many occasions, for example, when anti-smuggling activities are carried out in a border, an aircraft needs to be captured to retain corresponding evidence, and at present, a wireless interference mode is basically adopted. Has the defects of serious mobility, poor effect, high dependence on personnel and the like.

Disclosure of Invention

The invention aims to solve the technical problem of providing a non-explosive work missile with a flow guide air inlet structure aiming at the defects of the prior art. Adopt air to provide power, can not explode, and strike the mode various.

In order to solve the technical problem, the invention adopts the technical scheme that the non-explosive-work missile with the flow guide air inlet structure comprises a missile body and a ducted engine which are coaxially arranged from front to back, wherein an air inlet channel is formed between the missile body and the ducted engine; the missile body end is the front end, when the missile body end is started, air enters the ducted engine through the air inlet channel, is compressed and then is discharged, and thrust for flying or acting is generated; the missile body is internally provided with a hollow cavity, the rear section of the missile body is used as an instrument bin, and a controller is placed in the instrument bin.

Further, the rear section of the missile body is arranged to be in a spindle body shape and used for guiding air to flow into the ducted engine.

Further, this duct engine includes the duct casing, the front end of duct casing is tubaeform import, tubaeform import's front end extends to the outside, forms the border of evagination, the wall of border is by preceding smooth transition to the back.

Furthermore, the rear end of the duct shell is also connected with an external cavity, the external cavity gradually shrinks along the flow direction of the air flow, and air rudders are arranged on the outer wall of the external cavity at intervals around the circumference of the external cavity.

Furthermore, the rear end of the duct shell is also connected with an external cavity, and air rudders are arranged on the inner wall of the external cavity at intervals around the circumference of the external cavity.

Further, the number of the air vanes is 4, and they are arranged at equal intervals.

Further, this guided missile body and duct engine are connected through connecting device, and connecting device is including the mounting disc of cover on guided missile body and duct engine are located, is connected through a plurality of supporting beams that axial set up between two mounting discs.

Further, the front end of the missile body is conical.

Furthermore, a duct paddle is arranged in the duct shell around the circumference of the duct shell, and the duct paddle is arranged on the motor rotating shaft which is axially arranged.

Further, the front end of the motor rotating shaft is conical.

The invention relates to a non-priming guided missile with a flow guide air inlet structure, which has the following advantages: 1. compared with an initiating explosive device missile, the air-powered missile is safe and cannot explode. 2. No special requirement on transportation and no qualification requirement on a transport company, reduces the operation cost of enterprises and widens the application field of the enterprises. 3. The missile can move in the air in a large posture by controlling the air rudder of the missile. 4. By controlling the forward and reverse rotation of the ducted propellers, the missile can hover in the air, so that the missile has longer dead time and has multiple hitting opportunities for low, small and slow targets. Due to the long dead time, strong interference such as sunlight can be effectively avoided and the target can be hit more effectively through a flexibly designed trajectory. 5. The rear end of the missile body is in a shape of a simulated hammer body, a special diversion air inlet structure is formed, and the air input of the ducted engine is guaranteed on the premise of effectively reducing wind resistance. 6. On the premise of obtaining the same flight speed, the volume of the engine and the missile body is smaller, and the wind resistance is reduced in the flight process. 7. The required components are few, the mass is small, and the engine power is reduced. 8. Flexible and various striking modes can adopt various killing means such as net spraying, impacting, approaching wireless interference and the like, and the application field is enlarged. 9. The missile can be recovered, and when a working mode of catching a target or interfering the like is adopted, the missile can automatically fly back to a launching point to realize safe recovery for the next use after the missile completes a hitting task.

Drawings

FIG. 1 is a schematic structural view of example 1 of the present invention.

FIG. 2 is a schematic structural view of example 2 of the present invention.

Fig. 3 is a schematic structural view of a ducted engine in the present invention.

Wherein: 1. a missile body; 2. a support beam; 3. a ducted engine; 3-1, a ducted housing; 3-2, a horn-shaped inlet; 3-3 ducted paddles; 3-4. a motor rotating shaft; 4. the outer is connected with the cavity; 5. an air rudder; 6. and (7) mounting a disc.

Detailed Description

Example 1

The invention relates to a non-priming-article missile with a diversion air inlet structure, which comprises a missile body 1 and a ducted engine 3 which are coaxially arranged in front and back as shown in figure 1, wherein an air inlet channel is formed between the missile body 1 and the ducted engine 3; the missile body 1 end is the front end, when the missile body is started, air enters the ducted engine 3 through the air inlet channel, is compressed and then is discharged, and thrust for flying or acting is generated; the missile body 1 is internally provided with a hollow cavity, the rear section of the hollow cavity is used as an instrument bin, and a controller is arranged in the instrument bin. The pressurized air is used for providing power, so that the conventional solid fuel combustion is avoided for providing power, and the explosion risk is avoided. The rear section of the missile body 1 is arranged in a spindle shape and used for guiding air to flow into the ducted engine 3. In the process of flying the missile, the outside air flows down along the outer wall of the missile body 1 under the guidance of the rear section of the spindle body and enters the ducted engine. In order to reduce the resistance, the front end of the missile body 1 is conical.

As shown in fig. 3, the ducted engine 3 includes a ducted housing 3-1, the front end of the ducted housing 3-1 is a trumpet-shaped inlet 3-2, the front end of the trumpet-shaped inlet 3-2 extends outward to form an outward convex edge, the wall surface of the edge is in smooth transition from front to back, and the incoming air flow impinges on the wall surface of the edge, so that the incoming air flow smoothly enters the ducted engine 3 to play a role in guiding and stabilizing the flow. The ducted casing 3-1 is internally provided with ducted paddles 3-3 around the circumference thereof, and the ducted paddles 3-3 are all arranged on a motor rotating shaft 3-4 which is axially arranged. In order to reduce flight resistance, the front end of the motor rotating shaft 3-4 is conical. The motor is connected with the controller. The motor controls the forward rotation or the reverse rotation of the ducted propellers 3-3 to realize the stay and the action of the missile in the air.

The rear end of the duct shell 3-1 is also connected with an external cavity 4, in order to ensure the thrust of the discharged gas, the external cavity 4 gradually shrinks along the flow direction of the air flow, and air rudders 5 are arranged on the outer wall of the external cavity 4 at intervals around the circumference of the external cavity. The air rudder 5 is arranged on the outer wall through a rotating shaft, and under the impact of external airflow, the air rudder 5 rotates around the rotating shaft to ensure the flight direction of the missile. The air vanes 5 are preferably 4 and equally spaced between them. The air rudder 5 is controlled by a steering engine control unit, the steering engine control unit is connected with a main controller, and when the air rudder 5 is under the impact of air flow, the steering engine control unit adjusts the position of the air rudder in real time. The air vane 5 can be selected to be in a parallelogram shape, has a certain thickness, is vertical to the wall surface, has a cambered surface on the side surface opposite to the incoming flow, and is smoothly transited from front to back and becomes thinner from the thickness.

This guided missile body 1 and duct engine 3 are connected through connecting device, connecting device is including the mounting disc 6 of cover locating on guided missile body 1 and duct engine 3, is connected through a plurality of axial setting's a supporting beam 2 between two mounting discs 6.

In actual work, a ground station is arranged on the ground, a guidance control combination system is arranged in a missile instrument bin, the ground station sends an instruction to the guidance control combination system, and the guidance control combination system controls a motor to change the working state of the motor.

During actual work, the ground control station is provided with a guidance control combination system and is in wireless communication connection with the controller, and the staff transmits the instruction to the controller through the guidance control combination system so as to adjust and control the flight of the missile in real time.

The invention relates to a non-priming-article missile with a flow-guiding air inlet structure, which can adopt different attack modes according to different use scenes and different hitting targets. When a target needs to be captured, a capture net is arranged in the front section of the missile body 1, a gas generator is used for providing power for ejecting the capture net, the capture net is arranged at a gas outlet of the gas generator, when the missile approaches the target and needs to be captured by a spraying net, the gas generator works, and the generated pressure ejects the capture net to net the target.

When the target needs to be interfered, a wireless interference device is arranged in the front section of the missile body 1, the wireless interference device uses radio frequency interference, and when the target is approached, the controller controls the wireless interference device to work, so that the target is interfered.

In addition, the missile can also be used for destroying a target, at the moment, explosives can also be placed in the front section of the missile body 1, and explosion is started when the missile body approaches the target. The ignition and killing device can also be placed to spray solidified gasoline to be adhered to a target object to be ignited and burned to destroy the target object.

The invention relates to a non-priming-article missile with a flow-guiding air inlet structure, which comprises the following working processes: the motor is started, the ducted propeller 3-2 works under the driving of the rotating shaft 3-3, air enters the ducted engine 3 and is discharged after being pressurized, and thrust for flying the missile is generated. After the missile flies, the air rudder 5 can adjust the posture and the flying direction of the missile at any time. When approaching the target, the target is hit. If the missile does not hit the target, the motive machine is turned off after the missile climbs to the height, the missile turns over the missile body by means of the pneumatic structure of the missile body, the warhead faces downwards, reverse thrust is started at the moment, the missile is suspended in the air, and the target is hit again in a diving attack mode according to target information sent by the ground station.

Example 2

The difference between this embodiment and embodiment 1 is that, as shown in fig. 2, the rear end of the bypass casing 3-1 is further 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 a rotating shaft, and under the impact of external airflow, the air rudder 5 rotates around the rotating shaft to ensure the flight direction of the missile. As long as airflow passes through, the air rudder 5 works in real time to adjust the posture of the missile.

In the working process of the missile, after the missile is started, when airflow passes through the air rudder 5, the posture and the flight direction of the missile can be adjusted at any time.

Claims

1. A non-priming-article missile with a flow-guiding air inlet structure is characterized by comprising a missile body (1) and a ducted engine (3) which are coaxially arranged in front and back, wherein an air inlet channel is formed between the missile body (1) and the ducted engine (3);

the missile body (1) end is the front end, when the missile body is started, air enters the ducted engine (3) from the air inlet channel, is compressed and then discharged, and generates thrust for flying or acting the air;

the missile body (1) is internally provided with a hollow cavity, the rear section of the hollow cavity is used as an instrument bin, and a controller is placed in the instrument bin;

the rear section of the missile body (1) is in a spindle shape and used for guiding air to flow into the ducted engine (3).

2. The non-explosive missile with the diversion air inlet structure as claimed in claim 1, wherein the rear end of the duct shell (3-1) is further connected with an external cavity (4), and air rudders (5) are arranged on the inner wall of the external cavity (4) at intervals around the circumference of the external cavity.

3. The non-pyrotechnic missile with the diversion air intake structure as claimed in claim 2, wherein the ducted engine (3) comprises a ducted shell (3-1), the front end of the ducted shell (3-1) is a trumpet-shaped inlet (3-2), the front end of the trumpet-shaped inlet (3-2) extends outwards to form a convex edge, and the wall surface of the edge is in smooth transition from front to back.

4. A non-explosive missile with a flow guiding and air inlet structure according to claim 3, wherein the rear end of the ducted shell (3-1) is further connected with an external cavity (4), the external cavity (4) is gradually contracted along the airflow direction, and the outer wall of the external cavity (4) is provided with air rudders (5) at intervals around the circumference thereof.

5. The non-pyrotechnic work missile with the diversion air intake structure as claimed in claim 4 wherein the number of the air rudders (5) is 4 and they are equally spaced.

6. The non-pyrotechnic work missile with the flow-guiding air-intake structure as claimed in claim 5, wherein the missile body (1) and the ducted engine (3) are connected through a connecting device, the connecting device comprises mounting discs (6) sleeved on the missile body (1) and the ducted engine (3), and the two mounting discs (6) are connected through a plurality of axially arranged support beams (2).

7. The non-pyrotechnic work missile with the flow guiding and air inlet structure as claimed in claim 6, wherein the front end of the missile body (1) is conical.

8. The non-pyrotechnic missile with the diversion air intake structure as claimed in claim 2, wherein the ducted shell (3-1) is internally provided with ducted paddles (3-3) around the circumference thereof, and the ducted paddles (3-3) are all arranged on an axially arranged motor rotating shaft (3-4).

9. The non-pyrotechnic missile with the flow-guiding air inlet structure as claimed in claim 8, wherein the front end of the motor rotating shaft (3-4) is conical.