CN211626280U

CN211626280U - Four-duct propelling type small missile

Info

Publication number: CN211626280U
Application number: CN202020065555.5U
Authority: CN
Inventors: 李哲; 吴丹
Original assignee: Xi'an Sentton Intelligent Control Technology Co ltd
Current assignee: Xi'an Sentton Intelligent Control Technology Co ltd
Priority date: 2020-01-13
Filing date: 2020-01-13
Publication date: 2020-10-02
Anticipated expiration: 2030-01-13

Abstract

The utility model discloses a small-size guided missile of four duct impulse types, the utility model discloses a seeker, the seeker rear is provided with combat portion, and combat portion rear is provided with the control cabin, and control cabin rear is provided with the rudder cabin, is provided with a plurality of missile wings on the outer wall of combat portion, and the tip of missile wing all is provided with electric duct, is provided with missile-borne computer and lithium cell in the control cabin, and missile-borne computer control lithium cell is the power supply of electric duct. The utility model discloses an electricity duct provides power for the conductor, and the relative solid rocket engine of thrust that the electricity duct produced is a less but long duration's power, so can not make the guided missile produce great overload, the utility model discloses an electricity duct can reduce the weight of guided missile power supply, makes the quality of warhead strengthen in order to improve the guided missile power, the utility model discloses an electricity duct has reduced the cost of guided missile engine as power device, and the lithium cell does not have the initiating explosive device as the power supply, and production and storage security improve for the whole bullet.

Description

Four-duct propelling type small missile

Technical Field

The utility model belongs to the guided missile field, concretely relates to four duct impulse type small-size guided missiles.

Background

Missiles as a precise weapon play an increasingly important role in modern battlefields. The traditional missile taking a fighter and a missile launcher as platforms is large in size, complex in structure, high in cost and large in damage, and can only be used for hitting important military targets. Small targets and targets with small hitting ranges need to be accurately hit by a small missile mounted by an unmanned aerial vehicle.

The existing unmanned aerial vehicle air-ground missile uses a solid rocket engine as boosting power, and is a guided bomb without power. Because of the short range of guided bombs, it is desirable to have the drone as close to the target as possible to hit, which increases the difficulty of firing weapons and makes the drone vulnerable to ground threats. Missiles with solid rocket engines as power are also deficient in their engines. The solid rocket engine generates power by combustion of solid gunpowder, and has certain potential safety hazards in production and storage; secondly, the thrust generated by the combustion of gunpowder is large, and the requirement on the strength of the projectile body is high, so that the weight reduction is not facilitated by using some non-metallic materials as structural members; thirdly, the gunpowder burns fast, because small-size bullet volume and weight restriction can't hold more medicine, so the engine only can work for a short time for a few seconds, has restricted the range of guided missile.

Disclosure of Invention

The utility model aims to overcome the solid rocket engine of current guided missile to small-size guided missile, weight is big, and combustion time is short, and there is the potential safety hazard in production and the storage, problem with high costs provides a four duct impulse type small-size guided missile.

In order to achieve the purpose, the utility model discloses a seeker, seeker rear are provided with warhead, and warhead rear is provided with the control cabin, and the control cabin rear is provided with the rudder cabin, is provided with a plurality of missile wings on the outer wall of warhead, and the tip of missile wing all is provided with electric duct, is provided with missile-borne computer and lithium cell in the control cabin, and the power supply of missile-borne computer control lithium cell for electric duct.

The outside parcel of electric duct has the duct radome fairing, duct radome fairing and missile wing fixed connection.

The missile wing and the ducted fairing are integrally formed by composite materials, and fillet transition is adopted between the missile wing and the ducted fairing.

The warhead adopts aviation-grade aluminum alloy.

The outer wall of the warhead is provided with a lifting lug.

The outer wall of the warhead is provided with a release and insertion device.

A steering engine is arranged in the rudder cabin, and a plurality of rudders driven by the steering engine are arranged on the outer wall of the rudder cabin.

The seeker is fixedly connected with the warhead through a screw.

Compared with the prior art, the utility model discloses an electric duct provides power for the conductor, and the relative solid rocket engine of thrust that the electric duct produced is a less but long duration's power, so can not make the guided missile produce great overload, the utility model discloses a weight that electric duct can reduce the guided missile power supply makes the quality of warhead increase in order to improve the guided missile power, the utility model discloses an electric duct has reduced the cost of guided missile engine as power device, and the lithium cell does not have the initiating explosive device as the power supply, and production and storage security improve.

Drawings

Fig. 1 is a schematic structural view of the present invention;

the device comprises a seeker 1, a warhead 2, a warhead 3, a lifting lug 4, an electric duct 5, a duct fairing 6, a missile wing 7, a control cabin 8, a release and insertion device 9, a rudder cabin 10 and a rudder.

Detailed Description

The present invention will be further explained with reference to the accompanying drawings.

Referring to fig. 1, the utility model discloses a seeker 1, seeker 1 rear are provided with

warhead

2, and 2 backs in warhead are provided with

control cabin

7, and 7 backs in control cabin are provided with rudder cabin 9, are provided with a plurality of missile wings 6 on the outer wall of warhead 2, and the tip of missile wing 6 all is provided with electric duct 4, is provided with missile-borne computer and lithium cell in the control cabin 7, and missile-borne computer control lithium cell is the power supply of electric duct 4. The outside of the electric duct 4 is wrapped with a duct fairing 5, and the duct fairing 5 is fixedly connected with the missile wing 6. The power cord of the electric duct 4 passes through the inside of the missile wing 6 and enters the control cabin 7, the missile wing 6 and the duct fairing 5 are integrally formed by composite materials, and fillet transition is adopted between the missile wing 6 and the duct fairing 5.

The seeker 1 is fixedly connected with the warhead 2 through eight screws.

The root of the missile wing 6 is provided with a T-shaped flange, the missile wing 6 is fixed on the warhead part 2 through eight countersunk head screws, the control cabin 7 is connected with the warhead part 2 through eight screws, and the rudder cabin 9 is connected with the control cabin 7 through eight screws.

Adopt welded connected mode between lug 3 and the warhead 2, lug 3 and warhead 2 all adopt the aviation level aluminum alloy.

The outer wall of the warhead 2 is provided with a lifting lug 3 and a release and insertion 8, and the release and insertion 8 is used as an electrical interface for communicating with an upper computer.

The rudder cabin 9 is internally provided with 4X-shaped distributed steering engines, and the outer wall of the rudder cabin 9 is provided with a plurality of rudders 10 driven by the steering engines.

Claims

1. The four-duct propelled small missile is characterized by comprising a seeker (1), wherein a warhead (2) is arranged behind the seeker (1), a control cabin (7) is arranged behind the warhead (2), a rudder cabin (9) is arranged behind the control cabin (7), a plurality of missile wings (6) are arranged on the outer wall of the warhead (2), electric ducts (4) are arranged at the end parts of the missile wings (6), an missile-borne computer and a lithium battery are arranged in the control cabin (7), and the missile-borne computer controls the lithium battery to supply power to the electric ducts (4).

2. The four-duct propelling small missile according to claim 1, wherein the electric duct (4) is wrapped by a duct fairing (5), and the duct fairing (5) is fixedly connected with the missile wing (6).

3. The small four-duct propelling missile according to claim 2, wherein the missile wing (6) and the duct fairing (5) are integrally formed by adopting a composite material, and the missile wing (6) and the duct fairing (5) adopt fillet transition.

4. A four duct propelled missile as claimed in claim 1 wherein the warhead (2) is of aviation grade aluminium alloy.

5. A four duct propelled missile as claimed in claim 1 wherein the outer wall of the warhead (2) is provided with lifting lugs (3).

6. A four duct propelled missile as claimed in claim 1 wherein the outer walls of the warhead (2) are provided with a release and insertion means (8).

7. The small four-duct propelling missile according to claim 1, wherein a steering engine is arranged in the rudder cabin (9), and a plurality of rudders (10) driven by the steering engine are arranged on the outer wall of the rudder cabin (9).

8. A four duct propelled missile as claimed in claim 1 wherein the guidance head (1) is fixedly attached to the warhead (2) by screws.