CN107702594B

CN107702594B - Missile decoy and missile vehicle

Info

Publication number: CN107702594B
Application number: CN201710999978.7A
Authority: CN
Inventors: 刘云鹏; 赵红超; 李冬梅
Original assignee: Beijing Yunchuang Taihe Technology Co ltd
Current assignee: Beijing Yunchuang Taihe Technology Co ltd
Priority date: 2017-10-24
Filing date: 2017-10-24
Publication date: 2023-07-04
Anticipated expiration: 2037-10-24
Also published as: CN107702594A

Abstract

The invention relates to a missile false target and a missile vehicle, wherein the missile false target comprises a main body support, the main body support comprises a missile guide head (1) and a cylinder body (2), the missile head (1) is slidably arranged at one end of the cylinder body (2), and the missile false target can be pulled out from the cylinder body (2) to a preset position when a missile is erected and pushed back into the cylinder body (2) when the missile is required to be withdrawn. The missile false target can be pulled out from the cylinder to a preset position when the missile is erected, achieves the size and shape close to those of a true target, has high simulation degree, and is pushed back into the cylinder when the missile false target is required to be withdrawn and transported, so that the missile false target is convenient to transport. The missile false target can save the time for erecting and withdrawing the missile, has strong maneuverability and flexibly meets the tactical requirements in military; the missile erection and retraction can be realized by manpower without depending on hoisting equipment, so that the logistic workload can be effectively reduced; in addition, the missile false target has long service life and is convenient to maintain.

Description

Missile decoy and missile vehicle

Technical Field

The invention relates to the technical field of military camouflage, in particular to a missile decoy and a missile vehicle.

Background

Military camouflage technology has long history, is invisible and fake-indicating, is two aspects which form the indivisible military camouflage, and is beneficial to ensuring the concealment of targets, dispersing and attracting the attention and firepower of enemies and improving the military and economic benefits. During the second battle period, because high altitude reconnaissance equipment such as airplanes and airships are widely used, huge pressure is brought to the two parties of the battle, therefore, each battle state dispute is in a specific area, various cheap materials are adopted to manufacture a simple military target model, the simple military target model is used for confusing military reconnaissance of enemies, the enemies are induced to carry out firepower attack, and the aims of protecting own military targets and consuming enemy battle resources are achieved. This is an early decoy.

Since the occurrence of the end of the second warfare, missiles rapidly develop into backbone members for attacking and defending weapons, and missile equipping and control automation are the main stream directions of military development in the current world. The missile vehicle serving as a land-based missile carrier is a missile maneuvering and launching carrier, is also an important target for attack by enemies, and is a military target needing important protection. Thus, the military creates a great demand for missile vehicle decoys. Aiming at military reconnaissance at the time, the earliest false target is simply processed by wood or hard paper shells, and the purposes of trapping enemy to fire, confusing enemy and hiding oneself are well achieved.

With the development of basic industries such as materials, machinery and the like, various types of decoys are continuously emerging, wherein the inflatable decoys are rapidly popularized due to the simple design and manufacture, low cost and excellent technical performance of technical stations. Currently, active decoys in countries around the world are still mainly inflatable, and in addition, missile decoys of framework skin type, rapid expansion type, assembly type and the like are equipped with a small amount of equipment.

Early decoys were designed primarily for enemy optical detection, pursuing only similarity of the apparent optical features of the target. Along with the rapid development of novel reconnaissance technology, particularly the application of radar and satellite technology, microwave and infrared reconnaissance gradually become the main stream of modern reconnaissance technology, and traditional optical decoy is obviously different from a true missile vehicle in the aspects of material, internal structure and the like, so that the radar reflection sectional area and infrared emission characteristics of the traditional optical decoy are obviously different from those of the true missile vehicle, and the traditional optical decoy is more and more difficult to adapt to the requirements of the current war only by pursuing the similarity of the outline and the visible light wave band.

Currently, the international munitions market presents some products that can simulate the radar, infrared features of a real target to a certain extent. However, the decoys are made of modified polymer materials, and the radar reflection characteristics and the infrared characteristics of the decoys are simulated by adding related materials to a material matrix or arranging equipment inside the decoys. Because of a certain limitation of a high polymer material improvement technology or a surface modification technology, the electromagnetic performance of the material is obviously different from that of a metal material used by a true missile vehicle, so that the reality of the novel false target is also a certain defect compared with that of the true missile vehicle.

The decoy generally requires light weight, firm and simple structure, and is convenient for transportation, erection and withdrawal. The false target is divided into inflatable, assembly, foaming expansion, and convenient material model according to the manufacturing material and the forming mode. The inflatable false object is composed of plastic, rubber film or composite inflatable piece of fabric and rubber. The device has certain shape fidelity, is favorable for simulating parts such as round tubes, curved surfaces and the like of targets, and has light weight and small volume. The fabricated false target is formed by combining wood, metal, glass fiber reinforced plastic, plastic and other parts and part of fabric skin. The high-fidelity plastic composite material has high shape fidelity, is easy to use part of components as a whole, is easy to combine with convenient materials, and is easy to repair and replace after the parts are damaged, so that the high-fidelity plastic composite material is widely applied. However, most of the assembled decoys have larger overall size, which brings certain difficulty to erection and withdrawal, and has larger problems in transportation after withdrawal.

Disclosure of Invention

The invention aims to provide a missile false target and a missile vehicle, which can quickly realize the erection and withdrawal of the missile false target so as to flexibly meet the use requirement.

In order to achieve the above object, a first aspect of the present invention provides a missile decoy, including a main body support, where the main body support includes a missile guide head and a barrel, and the missile guide head is slidably disposed at one end of the barrel along a length direction of the barrel, and can be pulled out to a preset position from the barrel when a missile is erected, and pushed back into the barrel when the missile needs to be withdrawn.

Further, the missile head can be pushed back into the barrel entirely.

Further, a guiding mechanism is arranged between the outer wall of the missile guide head and the inner wall of the barrel body and used for guiding the movement of the missile guide head.

Further, the guide mechanism comprises a groove-shaped guide rail and a vertical pulley embedded in the groove-shaped guide rail, the groove-shaped guide rail is arranged at the upper and lower positions of the inner wall of the cylinder along the length direction of the cylinder, and the vertical pulley is arranged at the upper and lower positions of the outer wall of the missile head.

Further, the guiding mechanism further comprises a horizontal guide rail and a horizontal pulley which is arranged on the horizontal guide rail, the horizontal guide rail is arranged at the left and right positions of the inner wall of the cylinder body along the length direction of the cylinder body, and the horizontal pulley is arranged at the left and right positions of the outer wall of the missile head.

Further, the guiding mechanism comprises at least two groups of horizontal pulleys, and the at least two groups of horizontal pulleys are respectively positioned at two sides of the vertical pulleys along the length direction of the missile head.

Further, a first limiting structure is arranged between the missile guide head and the barrel and used for limiting the missile guide head to push back to the limiting position in the barrel; and/or

And a second limiting structure is arranged between the missile guide head and the barrel body and used for limiting the limiting position of the missile guide head when the missile guide head is pulled out.

Further, the missile false target further comprises a fixing piece, the missile guide head and the barrel are respectively provided with a first hole and a second hole, the missile head is pushed back inwards or pulled out outwards to the limit position, the positions of the first hole and the second hole are corresponding, and the fixing piece can penetrate through the first hole and the second hole to fix the missile head and the barrel.

Further, the free end of the bullet guide head is in a truncated cone shape, a screw is arranged at the center of the top of the truncated cone and used for being connected with a missile cap arranged outside, and the missile cap is matched with the truncated cone.

Further, the main body support further comprises a missile tail, the missile tail is detachably arranged at the other end of the barrel, and the missile tail can be placed into the barrel after being detached.

Further, the main body support further comprises an installation seat, the tail part of the missile is connected to the other end of the barrel through the installation seat, and a support seat used for being hinged with a false target of the missile vehicle is arranged on the installation seat.

Further, the missile decoy also comprises a decoration, wherein the decoration is detachably arranged on the cylinder body, and the decoration can be placed into the cylinder body after being detached.

Further, the cylinder body comprises a fixing ring and a plurality of cylinder body sections, and the adjacent cylinder body sections are connected through the fixing ring.

Further, the missile decoy also comprises a skin surrounding the outer part of the main body bracket, wherein the skin is made of a 5A05 aluminum-plastic plate; and/or the cylinder is made of Q235 or Q345 steel.

In order to achieve the above object, a second aspect of the present invention provides a missile vehicle, including a vehicle body decoy and the missile decoy described in the above embodiments.

Based on the technical scheme, the missile false target can be pulled out from the cylinder to a preset position when the missile is erected, the external dimension and the shape close to the true target are achieved, the simulation degree is high, and the missile false target is pushed back into the cylinder when being required to be withdrawn and transported, so that the missile false target is convenient to transport. The missile false target can save the time for erecting and withdrawing the missile, and has strong maneuverability; the missile erection and retraction can be realized by manpower without depending on hoisting equipment, so that the logistical workload can be effectively reduced; in addition, the missile false target has long service life and is convenient to maintain.

Drawings

The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this application, illustrate embodiments of the invention and together with the description serve to explain the invention and do not constitute a limitation on the invention. In the drawings:

FIG. 1 is a schematic view of the structure of a missile decoy of the present invention mounted on a missile vehicle;

FIG. 2 is a schematic exterior view of one embodiment of a missile decoy of the present invention;

FIG. 3 is a schematic structural view of one embodiment of a cartridge;

FIG. 4 is a side view of the cartridge of FIG. 3;

FIG. 5 is a schematic diagram of an embodiment of a missile head;

fig. 6a and 6b are schematic views of mounting structures of a vertical pulley and a horizontal pulley, respectively, wherein fig. 6b is an enlarged view at a in fig. 5;

FIG. 7 is a schematic structural view of one embodiment of a missile head internal skeleton;

FIG. 8 is an enlarged view of the structure at B in FIG. 7;

FIG. 9 is a top view of the inner skeleton of the warhead of FIG. 7;

fig. 10 is a C-C cross-sectional view of fig. 9.

Description of the reference numerals

1. A bullet guide head; 2. a cylinder; 3. a missile tail; 4/5, ornamental pieces; 6. a mounting base; 7. a channel rail; 8. a horizontal guide rail; 11. a skeleton; 12. a vertical pulley; 13. a horizontal pulley; 14. a missile cap; 15. a screw; 16. a first limit structure; 17. a first hole; 21. a barrel section; 22. a fixing ring; 61. and a supporting seat.

Detailed Description

The present invention is described in detail below. In the following paragraphs, the different aspects of the embodiments are defined in more detail. Aspects so defined may be combined with any other aspect or aspects unless explicitly stated to be non-combinable. In particular, any feature or features may be combined with one or more other features may be desired and advantageous.

The terms "first," "second," and the like in the present invention are merely for convenience of description to distinguish between different constituent components having the same name, and do not denote a sequential or primary or secondary relationship.

In the description of the present invention, it should be understood that the terms "length," "width," "height," "upper," "lower," "left," "right," "front" and "rear," etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the present invention, and do not indicate or imply that the device in question must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the scope of the present invention.

Referring to fig. 1 to 10, the invention provides a missile decoy, which is an assembled simulation model missile. In an exemplary embodiment, the missile decoy comprises a main body support, the main body support comprises a missile head 1 and a barrel 2, the missile head 1 and the barrel 2 are independent modules, and the barrel 2 adopts a hard hollow structure. The missile guide head 1 is slidably arranged at one end of the barrel 2 along the length direction of the barrel 2, and the missile guide head 1 can be pulled out from the barrel 2 to a preset position when a missile needs to be erected and pushed back into the barrel 2 when the missile needs to be removed. Preferably, the entire length of the bullet guide head 1 can be pushed back into the barrel 2. If necessary, only part of the length of the bullet guide head 1 may be pushed back into the cylinder 2.

After the bullet guide head 1 is pulled out to a preset position, the external dimension of the missile false target is high in similarity with that of a true military product, and in order to enable the false target to be vivid, the setting position of the false target is consistent with tactical and technical requirements of the true target, and a certain safety distance is kept between the false target and the true target. After the bullet guide head 1 is pushed back to the cylinder body 2 inwards, the whole appearance size of the missile can meet the allowable range of transportation conditions, for example, the missile can be filled into a container, the transportation is convenient, the maneuverability is strong, the retraction can be manually completed in a short time, the crane equipment is not needed, and the flexible transformation of tactics can be matched. The modular design of the bullet guide head 1 and the barrel 2 is also convenient for controlling the weight and operability of each module, and is easy to maintain.

In order to enable the missile guide head 1 to flexibly slide in the barrel 2, jamming in the movement process is prevented, reliability of missile decoys erected in tactics is improved, and a guide mechanism is arranged between the outer wall of the missile guide head 1 and the inner wall of the barrel 2 and used for guiding movement of the missile guide head 1 along the length direction of the barrel 2. The guide mechanism may take a variety of forms, such as an inner and outer rail fit, a slide bearing fit with a linear rail, a pulley fit with a rail, etc.

Preferably, the guide means are symmetrically arranged in the cross section of the cylinder 2 in left-right and/or up-down positions. The device has the advantages that the device can integrally play a role in bearing and guiding, plays a role in balancing, pushing and guiding, ensures that the bullet guide head 1 smoothly completes drawing action, and avoids the phenomenon that the bullet guide head 1 is inclined in the drawing process due to uneven force so as to be blocked in the barrel 2.

Here, a specific structure of the guide mechanism is provided, as shown in fig. 5, the guide mechanism includes two grooved rails 7 and two vertical pulleys 12, referring to fig. 6a, the vertical pulleys 12 are embedded in the grooved rails 7, two side walls of the grooved rails 7 can play a role in limiting the missile head 1 leftwards and rightwards, and the grooved rails 7 guide the sliding track of the vertical pulleys 12. The two groove-shaped guide rails 7 are respectively arranged at the upper and lower positions of the inner wall of the cylinder body 2 along the length direction of the cylinder body 2, the length of the groove-shaped guide rails 7 is not less than the whole movement stroke of the missile head 1, and the two vertical pulleys 12 are respectively arranged at the upper and lower positions of the outer wall of the missile head 1 in the same cross section.

Still referring to fig. 5, the guiding mechanism may further comprise two horizontal rails 8 and at least one set of horizontal pulleys 13, the horizontal pulleys 13 are mounted on the horizontal portion of the horizontal rails 8, the horizontal rails 8 support the horizontal pulleys 13, and the horizontal pulleys 13 can slide on the horizontal rails 8. Referring to fig. 6b, the horizontal pulley 13 adopts a structure in which a guide bush is provided outside a bearing. The two horizontal guide rails 8 are respectively arranged at the left and right positions of the inner wall of the cylinder 2 along the length direction of the cylinder 2, and the two horizontal pulleys 13 are arranged at the left and right positions of the outer wall of the bullet guide head 1 in the same cross section. In fig. 5, in order to facilitate the simultaneous illustration of the horizontal pulley 13 and the vertical pulley 12, the horizontal pulley 13 is also illustrated in the cross section of the vertical pulley 12, but in reality the horizontal pulley 13 is located at a left-right position of the outer wall of the warhead 1.

Preferably, as shown in fig. 5, the guiding mechanism comprises at least two sets of horizontal pulleys 13, and the at least two sets of horizontal pulleys 13 are respectively positioned at two sides of the vertical pulley 12 along the length direction of the missile head 1, that is, the horizontal pulleys 13 and the vertical pulley 12 are arranged at intervals along the length direction of the missile head 1 so as to obtain stable support along the length direction, and provide an effective guiding effect for the missile head 1.

The vertical pulley 12 and the horizontal pulley 13 are combined, the movement of the missile head 1 can be more stable and flexible by increasing the constraint mode, and the horizontal pulley 13 and the horizontal guide rail 8 are matched for use, so that the overconstraining of the pulley can be avoided, and the phenomenon of clamping stagnation caused by insufficient constraint of the relative movement of the missile head 1 and the barrel 2 is prevented. In embodiments where the projectile head 1 is formed by joining the carcass 11, the pulleys may be secured to the carcass 11 by welding.

Further, the missile head 1 can be limited in the process of drawing out and pushing back. A first limit structure 16 is arranged between the bullet guide head 1 and the cylinder 2 and is used for limiting the bullet guide head 1 to be pushed back to the limit position in the cylinder 2. As shown in fig. 7, a baffle is disposed at one end of the missile head 1 near the barrel 2, and a baffle (not shown) is disposed at the inner end of the groove-shaped guide rail 7 in the barrel 2, so that when the missile head 1 moves inward until the two baffles contact, the missile head 1 stops sliding inward, the missile head 1 is prevented from sliding into the barrel 2 too far to be pulled out, and too much space is occupied in the barrel 2, so that a sufficient space is provided in the barrel 2 to accommodate decoration parts and the like.

On the basis, the missile false target also comprises a fixing piece, as shown in a C-C diagram shown in fig. 10, wherein a first hole 17 is formed in the side wall of the missile head 1, a second hole is formed in the side wall of the barrel 2, the missile head 1 is pushed back to the limit position in the barrel 2, the positions of the first hole 17 and the second hole correspond to each other, and the fixing piece can be arranged in the first hole 17 and the second hole in a penetrating manner to fix the missile head 1 and the barrel 2, so that the missile head 1 is prevented from falling out after being withdrawn and retracted, and unnecessary damage caused in the transportation process is avoided.

Further, a second limiting structure is arranged between the missile head 1 and the barrel 2 and used for limiting the limiting position of the missile head 1 when being pulled out. For example, a blocking member is disposed at one end of the missile head 1 near the barrel 2, and a blocking member (not shown) is disposed at one end of the barrel 2 near the missile head 1, when the missile head 1 is pulled out until the two blocking members contact, the missile head 1 just reaches a preset position, and at this time, the pulling out cannot be continued.

On the basis that the missile head 1 is pulled out in place, the missile head 1 can be fixed through the fixing pieces, for example, holes can be formed in the baffle plate and the barrel 2 of the missile head 1 respectively, and the fixing pieces are arranged in the two holes in a penetrating manner, so that the phenomenon that the missile head slides off and the overall high similarity of the missile can not occur when the tactical appointed action of the missile is completed.

Specific structures that can be employed for the bullet guide head 1 and the barrel 2 are given here.

As shown in fig. 5 and 7, the bullet guide head 1 is formed by a framework 11, and can achieve higher strength while reducing weight, and a main body part of the bullet guide head 1 near one end of the cylinder 2 is enclosed into a cylindrical shape, and as can be seen from fig. 7, an inclined rod can be further arranged in the framework 11 for reinforcement. The free end of the bullet guide head 1 is in a truncated cone shape, a screw 15 is arranged at the center of the top of the truncated cone and used for being connected with a missile cap 14 arranged outside, and the missile cap 14 is matched with the truncated cone. The truncated cone enables the missile cap 14 to mate tightly with the missile head 1.

In fig. 5, the front part skeleton 11 of the warhead 1 is covered with a skin, and a part of the rear part which is not covered with the skin is embedded in the cylinder 2, and when the warhead 1 is pushed into the cylinder 2, the part covered with the skin also enters the cylinder 2 as a part of the warhead 1 connected with the cylinder 2.

As shown in fig. 3, the barrel 2 is cylindrical, and comprises a fixing ring 22 and a plurality of barrel sections 21, wherein the adjacent barrel sections 21 are connected through the fixing ring 22, so that missile decoys can be disassembled into smaller units when the transportation conditions are limited, and the missile decoys can be replaced conveniently when the parts are damaged.

On the basis of the above embodiment, as shown in fig. 2, the main body support further includes a missile tail 3, where the missile tail 3 is detachably disposed at the other end of the barrel 2, and the missile tail 3 can be also detached and placed into the hollow cavity of the barrel 2 when the missile tail 3 needs to be withdrawn or transported, or placed at other positions, so as to further reduce the overall length of the missile.

Further, as shown in fig. 3, the main body support further includes a mounting seat 6, the missile tail 3 is connected to the other end of the barrel 2 through the mounting seat 6, and a support seat 61 for hinging with a missile vehicle false target is arranged on the mounting seat 6. Through articulated connection, missile decoys can be nimble in the regional rotation between horizontal state and vertical state to nimble adaptation various tactics.

Still referring to fig. 2, the missile decoy may further include decorative pieces 4, 5, the decorative pieces 4, 5 being detachably provided on the main body support, the decorative pieces 4, 5 being detachable and placed in the barrel 2 during withdrawal or transportation of the decoy, so that the missile occupies a smaller volume.

And the outside of the main body support can be surrounded by a skin, so that the simulation degree of the missile is improved. The skin can be made of metal aluminum and polyethylene composite aluminum plastic plates, such as 5A05 aluminum plastic plates and the like, so that the self weight of the skin can be reduced, and the total weight of the whole missile vehicle is 8% of that of a true missile vehicle; and the reality of the outline of the false target of the missile can be improved, and the reflection characteristics of visible light and radar are consistent with those of a true missile. The framework 11 and the cylinder body 2 of the bullet guide head 1 are made of Q235 or Q345 steel, such as seamless steel pipes, so that the strength of the missile main body structure is ensured, the stability of the structure can be kept when the wind force is large or the external impact is large, the disassembly and assembly are convenient, and the logistical task amount is greatly reduced. The missile false target adopts the materials and the surface treatment process, so that the product has no vulnerable parts, long service life, no short-term repeated construction and no frequent maintenance.

As described above, the assembled simulation model missile of the present invention can flexibly simulate the construction practice and operation time of a real target, and is similar to the shape and size of the real target, and the thermal radiation characteristic, the electric wave reflection characteristic, the acousto-optic characteristic and the activity trace are similar. In addition, the missile decoy of the invention can crush the main body bracket and the skin when the enemy bombs so as to generate the same fragment effect as a true missile vehicle.

Next, a specific process of installing and withdrawing the missile decoy shown in fig. 2 is given.

When the missile needs to be removed, firstly, the ornamental pieces 4 and 5 on the missile are taken down; then the bullet guide head 1 is pushed into the cylinder 2 until the baffle plate on the bullet guide head 1 is contacted with the baffle plate on the groove-shaped guide rail 7 in the cylinder 2, and then the fixing piece is penetrated and arranged in the first hole 17 of the bullet guide head 1 and the second hole of the cylinder 2 for fixing; and then the missile tail 3 is detached from the barrel 2, the decorating parts 4 and 5 are arranged in the barrel 2 from the matching holes of the missile tail 3 and the barrel 2, and then the missile tail 3 is arranged in the barrel 2, so that the missile is in a retracted or transportation state.

When the missile is required to be erected, the missile tail 3 and the decoration pieces 4 and 5 are taken out of the barrel 2, the decoration pieces 4 and 5 are arranged at reserved positions on the missile respectively, and the missile tail 3 is arranged on the mounting seat 6. Then the fixing piece for fixing the bullet guide head 1 is removed, the bullet guide head 1 is pulled outwards until the bullet guide head 1 contacts with the blocking piece on the barrel 2, the bullet guide head 1 is pulled to the preset position, and the positions of the bullet guide head 1 and the barrel 2 are fixed by adopting the fixing piece. And erecting the missile, and finishing the erection of the missile.

In addition, the invention also provides a missile vehicle, as shown in fig. 1, comprising the missile vehicle decoy and the missile decoy in the above embodiments. The missile vehicle has higher simulation degree, can flexibly simulate tactical actions of a true target according to military tactical requirements, is convenient to evacuate from the field after being used, and is convenient to maintain.

The missile decoy and the missile vehicle provided by the invention are described in detail. The principles and embodiments of the present invention have been described herein with reference to specific examples, which are intended to be merely illustrative of the methods of the present invention and their core ideas. It should be noted that it will be apparent to those skilled in the art that various modifications and adaptations of the invention can be made without departing from the principles of the invention and these modifications and adaptations are intended to be within the scope of the invention as defined in the following claims.

Claims

1. The missile dummy is characterized by comprising a main body support, wherein the main body support comprises a missile guide head (1) and a barrel (2), the missile guide head (1) is slidably arranged at one end of the barrel (2) along the length direction of the barrel (2), and can be pulled out to a preset position from the barrel (2) when a missile is erected and pushed back into the barrel (2) when the missile is required to be withdrawn;

a guiding mechanism is arranged between the outer wall of the missile head (1) and the inner wall of the barrel (2) and is used for guiding the movement of the missile head (1);

the missile dummy further comprises a fixing piece, wherein a first hole (17) and a second hole are respectively formed in the missile head (1) and the barrel (2), and the positions of the first hole (17) and the second hole correspond to each other when the missile head (1) is pushed back inwards or pulled out to the limit position, and the fixing piece can be arranged in the first hole (17) and the second hole in a penetrating mode to fix the missile head (1) and the barrel (2);

the main body support further comprises a missile tail (3) and a mounting seat (6), the missile tail (3) is detachably arranged at the other end of the barrel (2), and the missile tail (3) can be placed into the barrel (2) after being detached; the missile tail (3) is connected to the other end of the barrel (2) through the mounting seat (6), and a supporting seat (61) used for being hinged with a missile vehicle false target is arranged on the mounting seat (6).

2. Missile decoy according to claim 1, characterized in that the missile head (1) can be pushed back into the barrel (2) entirely.

3. Missile decoy according to claim 1, characterized in that the guiding mechanism comprises a groove-shaped guide rail (7) and a vertical pulley (12) embedded in the groove-shaped guide rail (7), the groove-shaped guide rail (7) is arranged at the upper and lower positions of the inner wall of the barrel (2) along the length direction of the barrel (2), and the vertical pulley (12) is arranged at the upper and lower positions of the outer wall of the missile head (1).

4. A missile decoy according to claim 3, characterized in that the guiding mechanism further comprises a horizontal guide rail (8) and a horizontal pulley (13) mounted on the horizontal guide rail (8), the horizontal guide rail (8) is arranged at the left and right positions of the inner wall of the barrel (2) along the length direction of the barrel (2), and the horizontal pulley (13) is arranged at the left and right positions of the outer wall of the missile head (1).

5. Missile decoy according to claim 4, characterized in that the guiding mechanism comprises at least two groups of horizontal pulleys (13), at least two groups of horizontal pulleys (13) being located on both sides of the vertical pulley (12) in the length direction of the missile head (1).

6. A missile decoy according to claim 3, characterized by a first limit structure (16) arranged between the missile head (1) and the barrel (2) for limiting the missile head (1) to push back to the limit position in the barrel (2); and/or

A second limiting structure is arranged between the missile head (1) and the barrel (2) and used for limiting the limiting position of the missile head (1) when the missile head is pulled out.

7. Missile decoy according to claim 1, characterized in that the free end of the missile head (1) is in the shape of a truncated cone, a screw (15) is arranged at the top center of the truncated cone and used for being connected with an externally arranged missile cap (14), and the missile cap (14) is matched with the truncated cone.

8. Missile decoy according to claim 1, characterized by further comprising a decorative piece (4; 5), the decorative piece (4; 5) being removably provided on the barrel (2), the decorative piece (4; 5) being insertable into the barrel (2) after removal.

9. Missile decoy according to claim 1, characterized in that the barrel (2) comprises a fixing ring (22) and a plurality of barrel sections (21), adjacent barrel sections (21) being connected by the fixing ring (22).

10. The missile decoy of claim 1, further comprising a skin surrounding the exterior of the body mount, the skin being a 5a05 aluminum-plastic panel; and/or the cylinder (2) adopts Q235 or Q345 steel.

11. A missile vehicle comprising a missile vehicle decoy and a missile decoy as claimed in any one of claims 1 to 10.