CN111306994A - Reusable composite missile carrier - Google Patents

Abstract

The invention discloses a reusable composite material missile holder, which belongs to the technical field of launching weapon support devices. A reusable composite missile holder, including a ring holder, a support beam and a mover fixing device; the annular groove of the ring holder is used to connect the missile body, and the ring holder is connected to one end face of the support beam; the mover is fixed The device is connected to the other end face of the support beam corresponding to one end face, and the mover fixing device is used to fix the mover. It solves the problem that the missile bracket adopts a split-lobed connection structure, which cannot withstand high overload, and adopts a cylindrical barrel structure, which is easy to cause interference to the missile; and it is all one-time use, resulting in high use costs and inability to respond quickly. The invention adopts the structure of assembly connection, improves the stability of the overall installation structure, can withstand high overload force, avoids interference to the missile, and can be reused many times, reduces the use cost of the missile holder, and meets the needs of rapid response.

Description

Reusable composite missile carrier

technical field

The invention relates to the technical field of launching weapon support devices, in particular to a reusable composite material missile holder.

Background technique

The missile holder refers to the auxiliary support component that guides the missile body to move in the barrel on the missile. Missile mounts are usually made of steel, aluminum alloy, magnesium alloy, plastic and other materials. When in use, after the missile is ejected from the barrel, the missile holder uses airflow resistance and centrifugal force to fly out with the missile body; since the missile holder belongs to the "passive" mass of the missile, the mass of the missile holder should be as light as possible; at the same time, The missile holder is also subjected to high overload force. If its own mass is too large, it will also cause overload damage to itself. When the missile flies away from the barrel, the missile holder is required to fly out with the missile body quickly, so that the missile holder can fly out together. The interference of the seat to the missile is minimized.

The current missile holder mainly has two structures: the first type of missile holder uses a plurality of arc-shaped plates to be clamped on the missile body, and the missile body is supported along the radial direction of the missile body, and its structure is relatively simple. , and the missile holder is made of composite materials, which achieves the purpose of light weight. However, the missile holder adopts the above-mentioned split-lobed connection structure, and since the weight of the missile holder is usually set relatively light, it cannot bear high axial load.

The second type of missile holder is a cylindrical barrel structure, which is directly sleeved on the missile body to support the missile body along the axial direction of the missile body, and this missile holder is made of metal materials. Made to withstand high overload forces. However, the metal material will cause the structure of the missile holder to be relatively thick and heavy, and the overall weight will be relatively heavy, which will cause great interference to the missile during use.

In addition, when the existing missile holder is used, it needs to fly away together with the projectile body, so it is a disposable consumable and cannot be reused. Therefore, the above-mentioned structural design will also result in a high cost of use of the missile holder and cannot meet the needs of rapid response.

SUMMARY OF THE INVENTION

The purpose of the present invention is to provide a reusable composite material missile holder, so as to solve the problem in the prior art that the missile holder adopts the structure of split connection, the weight is relatively light, and it cannot bear high axial load; The missile holder adopts a cylindrical barrel structure, and the weight setting is relatively heavy, which is easy to cause interference to the missile; and the above two structures are one-time use, resulting in high cost of use of the missile holder, which cannot meet the needs of rapid response technology. question.

The invention provides a reusable composite material missile holder, which comprises an annular holder, a support beam and a mover fixing device;

The annular groove of the annular bracket is used to connect the missile body, and the annular bracket is connected to one end face of the support beam;

The mover fixing device is connected to the other end surface of the support beam corresponding to one end surface, and the mover fixing device is used for fixing the mover.

Further, the end face of the annular bracket connected to the missile body is provided with a radial escape groove that is consistent with the radial direction of the missile body;

The radial escape groove is used to protect the fixing mechanism in the radial direction of the outer peripheral surface of the missile projectile.

Further, the outer peripheral surface of the annular bracket is provided with an axial escape groove parallel to the axial direction of the missile body;

The axial escape groove is used to protect the fixing mechanism in the axial direction of the outer peripheral surface of the missile projectile.

Further, the inner peripheral surface of the annular bracket is connected with an axial guide block, and an axial guide groove is formed between the axial guide block and the inner peripheral surface of the annular bracket;

The axial guide groove is used to guide the axial movement of the projectile body along the annular groove.

Further, one end of the axial guide block is connected with a first folding plate, and the first folding plate is connected with one end of the inner peripheral surface of the annular bracket;

The other end of the axial guide block is connected with a second folded plate, and the second folded plate is connected with the other end of the inner peripheral surface of the annular bracket.

Further, an adapter block is connected to the outer peripheral surface of the annular bracket;

The adapter block is used to support the fixing mechanism in the axial direction of the outer peripheral surface of the missile missile.

Further, the mover fixing device includes a fixing plate, a side rib and a stopper;

The fixing plate is connected to the other end face corresponding to one end face of the support beam, the side rib is connected to the fixing plate, and a limit groove for accommodating the mover is formed between the side rib and the fixing plate;

The stopper is connected to the side rib and arranged in the limit groove.

Further, the stop block is provided with a weight reduction groove.

Further, the number of weight reduction grooves is multiple, and partitions are arranged between adjacent weight reduction grooves.

Further, the cross section of the weight reduction groove is any one of triangle, square and irregular shape.

Compared with the prior art, the reusable composite missile carrier of the present invention has the following advantages:

The annular groove of the annular bracket of the present invention is used to connect the missile body to limit the connection position of the missile body; the annular bracket is connected to one end face of the support beam, and the mover fixing device is connected to the support beam and one end face. The corresponding other end face, the annular bracket and the mover fixing device are respectively arranged on two end faces of the support beam; the mover fixing device is used to fix the mover, and the installation position of the mover is limited; the annular bracket of the present invention , The support beam and the mover fixing device adopt an assembly connection structure to ensure the installation position accuracy of the entire missile bracket; the projectile body is connected to the annular bracket at the upper end, and the mover is connected to the lower end of the mover fixing device. When in use, under the push of the mover, the missile holder bears the high overload force together with the projectile body, and then accelerates the shooting movement along the axis of the annular holder. The missile holder is separated from the projectile body by the mover brake to avoid the Interference of missiles; the missile holder of the present invention does not fly out with the projectile body, can be recycled and used repeatedly, reduces the use cost of the missile holder, and can meet the needs of rapid response.

Description of drawings

In order to illustrate the specific embodiments of the present invention or the technical solutions in the prior art more clearly, the following briefly introduces the accompanying drawings that need to be used in the description of the specific embodiments or the prior art. Obviously, the accompanying drawings in the following description The drawings are some embodiments of the present invention. For those of ordinary skill in the art, other drawings can also be obtained based on these drawings without creative efforts.

FIG. 1 is a schematic structural diagram of the upper position of the reusable composite missile holder provided by an embodiment of the present invention;

Fig. 2 is the enlarged view of A part in Fig. 1;

3 is a schematic structural diagram of an outer side surface of an axial guide block provided by an embodiment of the present invention;

4 is a schematic structural diagram of an inner side surface of an axial guide block provided by an embodiment of the present invention;

FIG. 5 is a schematic structural diagram of the lower part of the reusable composite missile holder provided by an embodiment of the present invention;

6 is a schematic structural diagram of the upper position of the annular bracket provided by an embodiment of the present invention;

FIG. 7 is a schematic structural diagram of the lower position of the annular bracket provided by an embodiment of the present invention;

8 is a schematic structural diagram of a support beam provided by an embodiment of the present invention;

FIG. 9 is a schematic structural diagram of the upper position of the mover fixing device according to an embodiment of the present invention;

10 is a schematic structural diagram of the lower position of the mover fixing device provided by the embodiment of the present invention;

11 is a left side view of a mover fixing device provided by an embodiment of the present invention;

FIG. 12 is a front view of a mover fixing device according to an embodiment of the present invention.

Description of reference numbers:

100-ring bracket; 200-support beam;

300-Motor fixing device; 400-Motor;

101-annular groove; 102-radial escape groove;

103-Axial avoidance groove; 104-Axial guide block;

105-axial guide groove; 106-first folding plate;

107-Second folding plate; 108-Adapter block;

301-fixed plate; 302-side rib;

303-stop block; 304-limit groove;

305 - weight reduction tank; 306 - partition.

Detailed ways

It should be noted that the embodiments of the present invention and the features of the embodiments may be combined with each other under the condition of no conflict.

In the description of the present invention, it should be understood that the terms "center", "portrait", "horizontal", "top", "bottom", "front", "rear", "left", "right", " The orientation or positional relationship indicated by vertical, horizontal, top, bottom, inner, outer, etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and The description is simplified rather than indicating or implying that the device or element referred to must have a particular orientation, be constructed and operate in a particular orientation, and therefore should not be construed as limiting the invention. In addition, the terms "first", "second", etc. are used for descriptive purposes only, and should not be construed as indicating or implying relative importance or implying the number of indicated technical features. Thus, a feature defined as "first", "second", etc., may expressly or implicitly include one or more of that feature. In the description of the present invention, unless otherwise specified, "plurality" means two or more.

In the description of the present invention, it should be noted that the terms "installed", "connected" and "connected" should be understood in a broad sense, unless otherwise expressly specified and limited, for example, it may be a fixed connection or a detachable connection Connection, or integral connection; can be mechanical connection, can also be electrical connection; can be directly connected, can also be indirectly connected through an intermediate medium, can be internal communication between two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood through specific situations.

The present invention will be described in detail below with reference to the accompanying drawings and in conjunction with the embodiments.

As shown in FIGS. 1 to 10 , a reusable composite missile holder provided by the present invention includes an annular holder 100 , a support beam 200 and a mover fixing device 300 ;

The annular groove 101 of the annular bracket 100 is used to connect the missile body, and the annular bracket 100 is connected to one end surface of the support beam 200;

The mover fixing device 300 is connected to the other end surface of the support beam 200 corresponding to one end surface, and the mover fixing device 300 is used for fixing the mover 400 .

In an embodiment of the present invention, as shown in FIGS. 1 , 2 , 5 , and 8 , the annular bracket 100 has a cylindrical structure; an annular groove 101 is formed in the middle of the annular bracket 100 , and the annular groove 101 It is an annular through groove; the missile body is installed in the annular groove 101, and the installation position of the missile body is locked.

In this embodiment, the support beam 200 is a hollow structure, and adopts the structure of a well-shaped beam, and the well-shaped beam is connected and fixed by a hollow square tube.

In other embodiments, the support beam 200 can also be set to other structures according to actual needs, for example, a support beam formed by connecting a plurality of cross beams, or a plurality of ring-shaped inner and outer sleeves in sequence. Support beams formed by beam connections, etc.

In this embodiment, the upper end of the annular bracket 100 is provided with an upper flange, and the lower end is provided with a lower flange, so as to be connected and fixed with other equipment; the lower flange of the annular bracket 100 is connected to the upper end surface of the support beam 200 by bolts , the mover fixing device 300 is connected to the lower end face of the support beam 200 by bolts, so that the annular bracket 100, the support beam 200 and the mover fixing device 300 are separated and separately formed structures, and then mechanically connected by fastening bolts The assembly method simplifies the molding difficulty of the entire missile bracket, ensures the dimensional assembly accuracy, reduces the overall weight to a certain extent, and can withstand high overload force.

The mover fixing device 300 is used to fix the mover 400 and lock the installation position of the mover 400 .

In the process of use, when the projectile is launched, under the push of the mover 400 in the mover fixing device 300, the entire missile holder bears a high overload force together with the projectile. At this time, the load is greater than 4 tons and the acceleration is greater than 8g. , and then accelerate to move along the shooting direction, that is, move along the axial direction of the annular bracket 100; when the projectile reaches a certain stroke, the mover 400 starts to brake, and the mover 400 starts to brake through the stopper 303 of the mover fixing device 300 and the mover. The interaction between 400 can realize the high acceleration stop of the entire missile holder. At this time, the acceleration is >40g to avoid interference to the missile; and after the missile body is detached, the entire missile holder will not fly out with the missile body. , and can continue to be used repeatedly, which meets the requirements of rapid response and repeated use in the future, and reduces the use cost of the missile holder.

Further, the end face of the annular bracket 100 connected to the missile body is provided with a radial escape groove 102 that is consistent with the radial direction of the missile body;

The radial escape groove 102 is used to protect the fixing mechanism in the radial direction of the outer peripheral surface of the missile missile.

In one embodiment of the present invention, as shown in FIG. 6 , the missile body is installed in the annular groove 101 on the upper end surface of the annular bracket 100 , and the radial escape groove 102 is provided on the upper end surface of the annular bracket 100 to avoid radial The groove 102 is a downwardly concave arc-shaped groove formed on the upper end surface of the annular bracket 100. The diameter direction of the arc-shaped groove is consistent with the diameter direction of the missile body. Therefore, after the missile body is installed, due to the There are fixing mechanisms formed on the radial direction of the outer peripheral surface, and the concave arc-shaped grooves can form a kind of protection for these fixing mechanisms, so as to avoid wear on the outer peripheral surface of the missile body.

In a specific embodiment, the upper end surface of the annular bracket 100 is formed with two oppositely arranged radial avoidance grooves 102, and the two radial avoidance grooves 102 are used to respectively fix the two opposite positions of the outer peripheral surface of the missile body. It is protected so as to avoid the wear of the outer peripheral surface fixing mechanism of the missile body along its radial direction.

In other embodiments, the number of the radial avoidance grooves 102 can also be set to other numbers according to the number of fixing mechanisms on the outer peripheral surface of the missile body. Set the position of the fixing mechanism on the surface accordingly.

Further, the outer peripheral surface of the annular bracket 100 is provided with an axial escape groove 103 parallel to the axial direction of the missile body;

The axial escape groove 103 is used to protect the fixing mechanism in the axial direction of the outer peripheral surface of the missile missile.

In an embodiment of the present invention, as shown in FIGS. 6 and 7 , an axial escape groove 103 is provided along the outer peripheral surface of the annular bracket 100 , and the axial escape groove 103 is formed on the outer peripheral surface of the annular bracket 100 . The arc groove is recessed inward, and the axial direction of the arc groove is parallel to the axial direction of the missile body. Therefore, after the missile body is installed, a fixing mechanism will be formed on the outer peripheral surface of the missile body in the axial direction. The arc-shaped grooves can form a kind of protection for these fixing mechanisms and avoid wear on the outer peripheral surface of the missile body.

In a specific embodiment, the outer peripheral surface of the arc-shaped bracket 100 forms two oppositely arranged axial escape grooves 103, and the two axial escape grooves 103 are used to respectively fix two opposite positions on the outer peripheral surface of the missile body. The mechanism protects the outer peripheral surface of the missile body from wearing along its axial direction.

In other embodiments, the number of the axial escape grooves 103 can also be set to other numbers according to the number of fixing mechanisms on the outer peripheral surface of the missile body. Set the position of the fixing mechanism on the surface accordingly.

Further, the inner peripheral surface of the annular bracket 100 is connected with an axial guide block 104, and an axial guide groove 105 is formed between the axial guiding block 104 and the inner peripheral surface of the annular bracket 100;

The axial guide groove 105 is used to guide the axial movement of the missile body along the annular groove 101 .

In one embodiment of the present invention, as shown in FIGS. 1 and 2 , an axial guide block 104 is bolted to the inner peripheral surface of the annular bracket 100 to form a shooting guide block; as shown in FIGS. 3 and 4 , the section of the axial guide block 104 is U-shaped, so that an axial guide groove 105 is formed between the axial guide block 104 and the inner peripheral surface of the annular bracket 100; the axial guide groove 105 is a square through-groove structure, In order to guide the projectile and increase the guiding area of the projectile.

Further, one end of the axial guide block 104 is connected with a first folding plate 106, and the first folding plate 106 is connected with one end of the inner peripheral surface of the annular bracket 100;

The other end of the axial guide block 104 is connected with a second folding plate 107 , and the second folding plate 107 is connected with the other end of the inner peripheral surface of the annular bracket 100 .

In an embodiment of the present invention, as shown in FIG. 1 , FIG. 2 , FIG. 3 , and FIG. 4 , a first folded plate 106 is formed on the upper end of the axial guide block 104 , and the first folded plate 106 and the annular bracket 100 are formed. The upper flanges of the inner peripheral surface of the inner peripheral surface are connected by bolts, which increases the connection area between the upper end of the axial guide block 104 and the upper end of the inner peripheral surface of the annular bracket 100; Two folded plates 107, the second folded plate 107 and the lower flange of the inner peripheral surface of the annular bracket 100 are fixedly connected by bolts, and the lower end of the axial guide block 104 and the inner peripheral surface of the annular bracket 100 are added. The connection area between the lower ends.

Further, an adapter block 108 is connected to the outer peripheral surface of the annular bracket 100;

The adapter block 108 is used to support the fixing mechanism in the axial direction of the outer peripheral surface of the missile missile.

In one embodiment of the present invention, as shown in FIG. 6 and FIG. 7 , an adapter block 108 is connected to the outer peripheral surface of the annular bracket 100 by bolts. The adapter block 108 is in the shape of a strip. The axial directions of the bracket 100 are arranged in parallel.

In this embodiment, the number of the adapter blocks 108 is plural, and the plurality of adapter blocks 108 are respectively bolted to the outer peripheral surface of the annular bracket 100 near the two sides of the radial relief groove 102 and close to the axial relief groove. The two sides of the 103 and the two sides of the axial guide block 104 are used to reinforce the two sides of the radial escape groove 102, the two sides of the axial escape groove 103, and the axial guide block by using a plurality of adapter blocks 108. Both sides of 104.

The adapter block 108 and the annular bracket 100 are connected by bolts, which is convenient for disassembly and replacement.

Further, the mover fixing device 300 includes a fixing plate 301, a side rib 302 and a stop block 303;

The fixing plate 301 is connected to the other end surface corresponding to one end surface of the support beam 200, the side rib 302 is connected to the fixing plate 301, and a limit groove 304 for accommodating the mover 400 is formed between the side rib 302 and the fixing plate 301;

The stop block 303 is connected to the side rib 302 and arranged in the limiting groove 304 .

In an embodiment of the present invention, as shown in FIG. 9 , FIG. 10 , FIG. 11 , and FIG. 12 , the fixing plate 301 is a rectangular plate, and the front and rear ends of the rectangular plate are arc structures so as to be in contact with the lower end surface of the support beam 200 . The fixed plate 301 is connected to the lower end surface of the supporting beam 200 by bolts to lock the installation position of the fixed plate 301; and the cross-section of the side rib 302 is a triangular structure, so as to form a support and fixation for the lower end surface of the fixing plate 301; An inverted U-shaped limit slot 304 is formed between the plates 301 so that the mover 400 can be accommodated in the limit slot 304 ; the number of stop blocks 303 is two, and bolts are used on the inner side of each side rib 302 A stop block 303 is connected. The cross-section of the stop block 303 is a triangular structure. The stop block 303 is used to limit the mover 400 in the limit slot 304. Since the stop block 303 is a wearing part, it is easy to disassemble by using a bolt connection. Replacement.

Further, the stop block 303 is provided with a weight reduction groove 305 .

Further, the number of the weight reduction grooves 305 is multiple, and partitions 306 are arranged between adjacent weight reduction grooves 305 .

In one embodiment of the present invention, as shown in FIG. 10 , a weight reduction groove 305 is provided on the lower end surface of the stopper block 303 , and the weight reduction groove 305 is a groove recessed inward along the lower end surface of the stopper block 303 . The arrangement of 305 can reduce the weight of the entire stopper 303 .

In a specific embodiment of the present invention, a weight reduction groove 305 is provided on the lower end surface of the stop block 303, and the slotting direction of the weight reduction groove 305 is parallel to the movement direction of the mover 400; There are threaded holes, so that the side wall of the stop block 303 can be fixed on the side rib 302 by bolts.

In another specific embodiment of the present invention, a plurality of weight-reducing grooves 305 are provided on the lower end surface of the stop block 303, and the slotting direction of the weight-reducing grooves 305 is parallel to the moving direction of the mover 400; the plurality of weight-reducing grooves 305 Evenly distributed, and the adjacent weight-reducing grooves 305 are not connected, they are arranged at intervals through the partition plate 306, so that each weight-reducing groove 305 is provided with threaded holes, so that the side wall of the stop block 303 can be fixed on the side by bolts. on the rib 302.

In another specific embodiment of the present invention, a weight reduction groove 305 is formed on the front end surface of the left side of the stop block 303 in FIG. 10 . The slotting direction of the weight-reducing groove 305 is perpendicular to the moving direction of the mover 400 ; a plurality of threaded holes are arranged in the weight-reducing groove 305 to facilitate fixing the side wall of the stop block 303 on the side rib 302 by screws.

Further, the cross section of the weight reduction groove 305 is any one of a triangle, a square, and an irregular shape.

In one embodiment of the present invention, the cross section of the weight reduction groove 305 is triangular, so as to be compatible with the triangular structure of the stopper block 303 and ensure the weight reduction inside the stopper block 303 .

In other embodiments of the present invention, the cross section of the weight reduction groove 305 may also be set to be square, irregular, etc., as long as the purpose of reducing the internal weight of the stop block 303 can be achieved.

In the above-mentioned embodiment of the present invention, the annular bracket 100, the supporting beam 200, the fixing plate 301, and the side rib plate 302 are all made of carbon fiber composite material, and the stopper 303 is made of aluminum alloy or titanium alloy material. The missile holder adopts the above-mentioned connection structure, the main body is made of composite material, and the part is made of metal material. Under the condition of being able to withstand high overload force, it will not cause interference to the missile, and it can be used multiple times, saving costs.

The above descriptions are only preferred embodiments of the present invention, and are not intended to limit the present invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the scope of the present invention. within the scope of protection.

Claims (10)

1. A reusable composite material missile bracket, characterized by comprising an annular bracket (100), a support beam (200) and a rotor fixture (300);

the annular groove (101) of the annular bracket (100) is used for connecting missile bodies, and the annular bracket (100) is connected with one end face of the support beam (200);

the rotor fixing device (300) is connected with the supporting beam (200) and the other end face corresponding to one end face, and the rotor fixing device (300) is used for fixing the rotor (400).

2. -reusable composite missile bracket according to claim 1 wherein the end face of the annular bracket (100) that connects to the missile hull is provided with a radial escape slot (102) coinciding with the radial direction of the missile hull;

the radial avoidance groove (102) is used for protecting a fixing mechanism of the missile body in the radial direction of the outer peripheral surface.

3. A reusable composite missile bracket according to claim 1 wherein the outer circumferential surface of the annular bracket (100) is provided with axial evasion slots (103) parallel to the axial direction of the missile body;

the axial avoidance groove (103) is used for protecting a fixing mechanism of the missile body in the axial direction of the outer peripheral surface.

4. The reusable composite material missile bracket of claim 1, wherein an axial guide block (104) is attached to an inner circumferential surface of the annular bracket (100), an axial guide slot (105) being formed between the axial guide block (104) and the inner circumferential surface of the annular bracket (100);

the axial guide groove (105) is used for guiding the missile body to move along the axial direction of the annular groove (101).

5. The reusable composite missile bracket of claim 4 wherein the axial guide block (104) has a first flap (106) attached to one end of the axial guide block, the first flap (106) being attached to one end of the inner circumferential surface of the annular bracket (100);

the other end of the axial guide block (104) is connected with a second turnover plate (107), and the second turnover plate (107) is connected with the other end of the inner peripheral surface of the annular bracket (100).

6. The reusable composite material missile bracket of claim 1 wherein an adapter block (108) is attached to the outer circumferential surface of the annular bracket (100);

the adaptation block (108) is used for supporting a fixing mechanism of the missile body in the axial direction of the peripheral surface.

7. The reusable composite missile bracket of claim 1, wherein the rotor fixture (300) comprises a fixture plate (301), side ribs (302), and stops (303);

the fixing plate (301) is connected to the other end face corresponding to one end face of the supporting beam (200), the side rib plate (302) is connected to the fixing plate (301), and a limiting groove (304) for accommodating the rotor (400) is formed between the side rib plate (302) and the fixing plate (301);

the stop block (303) is connected to the side rib plate (302) and is arranged in the limit groove (304).

8. The reusable composite missile bracket of claim 7 wherein the stop block (303) is provided with weight reduction slots (305).

9. The reusable composite missile bracket of claim 8 wherein the number of weight-reducing slots (305) is a plurality and a spacer plate (306) is disposed between adjacent weight-reducing slots (305).

10. The reusable composite missile bracket of claim 8 wherein the weight-reduction slots (305) are any one of triangular, square and irregular in cross-section.

Images