阅读说明：本技术 一种小型战术导弹助推分离装置 (Small-size tactics guided missile boosting separator ) 是由 任宏光 张俊安 李斯宇 杨晓光 陈钢 王维强 于 2021-08-23 设计创作，主要内容包括：本发明涉及一种小型战术导弹助推分离装置,属于战术导弹用助推分离领域。本发明多个锁钩和连接板及调节螺柱等配合,将舱段连接的锁钩,固定在单个爆炸螺栓上,与传统机械式锁钩结构相比,机构大幅简化,零件数量减小,质量减轻；通过大幅减小机构数量,优化舱体内空间结构,使整个舱体占用长度空间最小,对小型导弹缩短长度空间十分有利；助推分离装置整体结构可达性好,装配操作环节少,安装方便快捷；利用单个爆炸螺栓与锁钩等机构配合,实现多个舱段锁制点同时解脱；同时利用锁钩的杠杆结构减小了爆炸螺栓的受力,可以减少爆炸螺栓装药,减小分离冲击。(The invention relates to a small tactical missile boosting separation device, and belongs to the field of boosting separation for tactical missiles. According to the invention, the plurality of lock hooks are matched with the connecting plate, the adjusting stud and the like, and the lock hooks connected with the cabin sections are fixed on a single explosion bolt; the number of mechanisms is greatly reduced, and the space structure in the cabin is optimized, so that the length and the space occupied by the whole cabin are minimized, and the length and the space shortened by the small missile are very facilitated; the boosting separation device has good accessibility of the whole structure, few assembling operation links and convenient and quick installation; the locking points of a plurality of cabin sections are simultaneously released by utilizing the matching of a single explosion bolt and mechanisms such as a lock hook; meanwhile, the lever structure of the lock hook is utilized to reduce the stress of the explosive bolt, the explosive charging of the explosive bolt can be reduced, and the separation impact is reduced.)

1. A small tactical missile boosting separation device is characterized by comprising a boosting separation cabin shell (1), a support (2), a lock hook (3), a pin (4), a mounting plate (5), an adjusting stud (6), a connecting plate (7), an explosion bolt (8), a connecting nut (9) and a protection device (10); the support (2) is arranged on the wall of the shell of the separation cabin body (1), and the lock hook (3) is fixed on the support through a pin (4) and can rotate around the pin (4); the inclined plane at the front end of the lock hook (3) hooks the inclined plane of the boss of the shell at the tail end of the preceding-stage missile (12); 4 groups of supports (2), lock hooks (3) and pins (4) are uniformly distributed and installed on the boosting separation device; the mounting plate (5) is mounted on the boosting separation cabin shell (1), 4 groups of notches are formed in the circumference of the mounting plate (5), the positions of the notches correspond to the mounting positions of the lock hooks (3), the connecting plate (7) abuts against the rear of the mounting plate (5), holes are formed in the middles of the connecting plate (7) and the mounting plate (5), the explosive bolts (8) penetrate through the holes, the connecting plate (7) is connected with the mounting plate (5) through connecting nuts (9), and the heads of the explosive bolts (8) are mounted at the front end; 4 inclined plane bosses are arranged on the mounting plate (5), corresponding to the mounting position of the lock hook (3), threaded holes are machined in the bosses, and the adjusting stud (6) is abutted against the inclined plane at the tail end of the lock hook (3) through the threaded holes to restrain the lock hook (3) from rotating; the protection device (10) is arranged on the outer side of the head of the explosion bolt (8) and fixed on the mounting plate (5), so that damage to the structure of the front-stage missile (12) caused by detonation and separation of the explosion bolt (8) is avoided.

2. A compact tactical missile thrust assist separation unit as in claim 1 wherein the thrust separation pod housing (1) is fixedly attached to the missile booster (11) and separates as a unit when separated.

3. The small tactical missile boosting separation device according to claim 1, wherein when the boosting separation device is connected to the preceding missile (12), the connecting plate (7) and the mounting plate (5) are kept in a contact state by the explosion bolt (8) and the connecting nut (9), and the adjusting stud (6) is adjusted so that the front end of the locking hook (3) can be retracted into the boosting separation capsule shell (1).

4. The small tactical missile boosting separation device according to claim 3, wherein the front end of the boosting separation cabin shell (1) is in sleeve fit with the tail end of the front-end missile (12), the adjusting stud (6) is adjusted to enable inclined hook surfaces at the front ends of the multiple groups of lock hooks (3) to be in contact with a boss inclined surface at the tail end of the front-end missile (12), and the connecting structure of the blasting bolt (8) is fixed in a fixed force mode through the connecting nut (9).

5. The small tactical missile separation booster of any of claims 1 to 4, wherein in the state of the missile separation booster linked to the preceding missile (12) and locked, the inclined plane of the rear end of the latch hook (3) is perpendicular to the threaded hole of the inclined plane boss on the connection plate (7), ensuring that the force of the adjusting stud (6) acts directly on the inclined plane of the latch hook (3).

6. The small tactical missile boosting separation device as claimed in claim 5, wherein the locking state of the locking hook (3) is acted by the contact counterforce of the inclined plane at the tail end of the preceding missile (12) and the constraint force of the adjusting stud (6), the counterforce received by the adjusting stud (6) is transmitted to the explosive bolt (8) through the connecting plate (7), and the bearing capacity of the whole mechanism is calculated to meet the requirement that the missile is not damaged under various load conditions in the using, maintaining and launching processes.

7. The small tactical missile boosting separation device of claim 5, wherein the stress lever ratio of the structure of the locking hook (3) is reasonably designed, the force transmitted to the explosive bolt (8) by the adjusting stud (6) through the connecting plate (7) is reduced, and the requirements on the bearing capacity of the explosive bolt (8) and the explosion impact resistance of the mechanism are reduced.

8. The compact tactical missile thrust aid separation device of claim 7 wherein the latch hook (3) configuration has a force lever ratio of 1: 3.

9. The compact tactical missile thrust aid separation device of claim 7 wherein the latch hook (3) configuration has a force lever ratio of 1: 4.

10. The small tactical missile boosting separation device of claim 1 wherein upon separation the detonation bolt (8) is activated and the detonation bolt (8) is sheared, thereby releasing the connection between the connection plate (7) and the mounting plate (5), the connection plate (7) losing its constraint and moving backwards under the impact of the detonation bolt (8) causing the adjusting stud (6) to lose its position-limiting function and all the locking hooks (3) to lose their constraint simultaneously; the lock hook (3) moves inwards under the action of aerodynamic force, the restraint between the preceding stage missile (12) and the boosting separation cabin shell (1) is released, and the separation between cabin sections is completed.

Technical Field

The invention belongs to the field of boosting separation for tactical missiles, and particularly relates to a small-sized boosting separation device for tactical missiles.

Background

In order to increase the range of tactical missiles or to make the missiles reach a certain initial speed, a mode of additionally arranging a booster at the tail of the missiles is generally adopted. The booster boosts the missile to a certain speed, after the boosting engine burns, the booster is thrown off, the pneumatic resistance is reduced, the invalid mass is reduced, and the engine of the missile ignites to continue flying, so that the aim of increasing the range of the missile is fulfilled.

The boosting separation generally adopts an initiating explosive device separation mode, a separation signal needs to be given out in an aerial system, and a power supply ignites the initiating explosive device for separation. The initiating explosive device separation mode is divided into point separation and line separation according to the initiating explosive device, and the point separation initiating explosive device mainly adopts an explosive bolt, a separation bolt, an explosive nut and the like. The point separation is relatively simple in structure, but the separation synchronism is poor, and the separation impact overload is large. The line separation mode adopted on the tactical missile is less, and the main reasons are that the small tactical missile line separation device is difficult to assemble and detect, large impact and serious pollution (gas leakage) exist, a weak ring which is easy to cut needs to be arranged on the missile body, and the missile body strength of the tactical missile is reduced.

At present, a mechanical linkage locking hook boosting separation device applied to a small tactical missile locks the missile and a booster through a locking hook device, an explosion bolt is detonated during separation, a plurality of locking hook devices are simultaneously released from restraint, and the missile and the booster are reliably separated under the action of pneumatic power. The lock hook device is composed of a multistage lever mechanism, the number of parts of a locking mechanism is large, the length space of a missile is occupied, and the assembly and debugging procedure is complex.

Aiming at the defects of the technical scheme, the invention provides a novel linkage lock hook boosting separation mechanism, which greatly simplifies the structural design, simplifies the assembly of a separation cabin and shortens the space occupied by the whole mechanism. The technical scheme has the greatest universality, and a feasible solution can be provided for the boosting separation of various tactical missiles.

Disclosure of Invention

Technical problem to be solved

The invention aims to solve the technical problem of how to provide a small tactical missile boosting separation device to solve the problems that the existing lock hook device is composed of a multi-stage lever mechanism, the number of locking mechanism parts is large, the occupied length space of a missile is large, and the assembly and debugging procedure is complex.

(II) technical scheme

In order to solve the technical problem, the invention provides a small tactical missile boosting separation device which comprises a boosting separation cabin shell (1), a support (2), a lock hook (3), a pin (4), a mounting plate (5), an adjusting stud (6), a connecting plate (7), an explosion bolt (8), a connecting nut (9) and a protection device (10); the support (2) is arranged on the wall of the shell of the separation cabin body (1), and the lock hook (3) is fixed on the support through a pin (4) and can rotate around the pin (4); the inclined plane at the front end of the lock hook (3) hooks the inclined plane of the boss of the shell at the tail end of the preceding-stage missile (12); 4 groups of supports (2), lock hooks (3) and pins (4) are uniformly distributed and installed on the boosting separation device; the mounting plate (5) is mounted on the boosting separation cabin shell (1), 4 groups of notches are formed in the circumference of the mounting plate (5), the positions of the notches correspond to the mounting positions of the lock hooks (3), the connecting plate (7) abuts against the rear of the mounting plate (5), holes are formed in the middles of the connecting plate (7) and the mounting plate (5), the explosive bolts (8) penetrate through the holes, the connecting plate (7) is connected with the mounting plate (5) through connecting nuts (9), and the heads of the explosive bolts (8) are mounted at the front end; 4 inclined plane bosses are arranged on the mounting plate (5), corresponding to the mounting position of the lock hook (3), threaded holes are machined in the bosses, and the adjusting stud (6) is abutted against the inclined plane at the tail end of the lock hook (3) through the threaded holes to restrain the lock hook (3) from rotating; the protection device (10) is arranged on the outer side of the head of the explosion bolt (8) and fixed on the mounting plate (5), so that damage to the structure of the front-stage missile (12) caused by detonation and separation of the explosion bolt (8) is avoided.

Further, the boosting separation cabin shell (1) and the missile booster (11) are fixedly connected together and are separated as a whole during separation.

Furthermore, when the boosting separation device is connected with a preceding-stage missile (12), the connecting plate (7) and the mounting plate (5) are kept in a contact state through the explosive bolt (8) and the connecting nut (9), and the adjusting stud (6) is adjusted to enable the front end of the lock hook (3) to be capable of being retracted into the boosting separation cabin shell (1).

Furthermore, the front end of the boosting separation cabin shell (1) is in sleeve fit with the tail end of a front-end missile (12), and the adjusting stud (6) is adjusted to enable the inclined hook surface at the front end of the multiple groups of lock hooks (3) to be in contact with the boss inclined surface at the tail end of the front-stage missile (12), and the connecting structure of the explosion bolt (8) is fixed in a fixed force mode through a connecting nut (9).

Furthermore, in the state that the missile boosting separation device is connected and locked with a preceding-stage missile (12), the inclined plane at the rear end of the lock hook (3) is vertical to the threaded hole of the inclined plane boss on the connecting plate (7), and the acting force of the adjusting stud (6) is ensured to directly act on the inclined plane of the lock hook (3).

Furthermore, the locking state of the locking hook (3) is acted by the contact counterforce of the inclined plane at the tail end of the front-stage missile (12) and the restraining force of the adjusting stud (6), the counterforce received by the adjusting stud (6) is transmitted to the explosive bolt (8) through the connecting plate (7), and the bearing capacity of the whole mechanism is calculated to meet the requirement that the missile is not damaged under various load conditions in the using, maintaining and launching processes.

Furthermore, the stress lever ratio of the structure of the lock hook (3) is reasonably designed, the force transmitted to the explosive bolt (8) by the adjusting stud (6) through the connecting plate (7) is reduced, and the requirements on the bearing capacity of the explosive bolt (8) and the explosion impact resistance of the mechanism are reduced.

Further, the stress lever ratio of the structure of the lock hook (3) is 1: 3.

Further, the stress lever ratio of the structure of the lock hook (3) is 1: 4.

Furthermore, when the adjusting bolt is separated, the explosion bolt (8) is excited, the explosion bolt (8) is sheared off, so that the connection between the connecting plate (7) and the mounting plate (5) is released, the connecting plate (7) loses constraint and moves backwards under the impact action of the explosion bolt (8), the adjusting stud (6) loses a limiting function, and all the lock hooks (3) lose constraint simultaneously; the lock hook (3) moves inwards under the action of aerodynamic force, the restraint between the preceding stage missile (12) and the boosting separation cabin shell (1) is released, and the separation between cabin sections is completed.

(III) advantageous effects

The invention provides a boosting separation device for small tactical missiles, which has the remarkable characteristics of simple structure, small volume, smooth appearance, good separation synchronism, small separation impact, simplicity in assembly and debugging and high reliability, and has universality for boosting separation of various small tactical missiles. The invention has the following remarkable advantages:

the structure is simple: according to the invention, a plurality of lock hooks (3) are matched with a connecting plate (7) and an adjusting stud (6) and the like, and the lock hooks (3) connected with the cabin section are fixed on a single explosion bolt (8).

The occupied space is small: the number of mechanisms is greatly reduced, and the space structure in the cabin is optimized, so that the occupied length and space of the whole cabin are minimized, and the length and space shortening of the small missile is facilitated.

The installation and operation are convenient: the boosting separation device has good accessibility of the whole structure, few assembling operation links and convenient and quick installation.

Good synchronism and small separation impact: a single explosion bolt (8) is matched with mechanisms such as a lock hook (3) and the like, so that locking points of a plurality of cabin sections are released simultaneously; meanwhile, the lever structure of the lock hook is utilized to reduce the stress of the explosive bolt (8), the explosive charge of the explosive bolt (8) can be reduced, and the separation impact is reduced.

Drawings

FIG. 1 is a schematic view of the structure of the boosting separation mechanism of the present invention

FIG. 2 is a structural configuration diagram of a boosting separation mechanism

FIG. 3 is a schematic diagram of a connection plate structure

The method comprises the following steps of 1-boosting a separation cabin shell, 2-a support, 3-a lock hook, 4-a pin, 5-a mounting plate, 6-an adjusting stud, 7-a connecting plate, 8-an explosion bolt, 9-a connecting nut, 10-a protection device, 11-a booster and 12-a preceding missile.

Detailed Description

In order to make the objects, contents and advantages of the present invention clearer, the following detailed description of the embodiments of the present invention will be made in conjunction with the accompanying drawings and examples.

The invention belongs to a boosting separation technology for tactical missiles, and provides a novel linkage lock hook boosting separation mechanism, which greatly simplifies the structural design, simplifies the assembly of a separation cabin, shortens the space occupied by the whole mechanism and improves the reliability.

The missile boosting separation device mainly comprises a boosting separation cabin shell (1), a support (2), a lock hook (3), a pin (4), a mounting plate (5), an adjusting stud (6), a connecting plate (7), an explosion bolt (8), a connecting nut (9) and a protection device (10). The support (2) is arranged on the wall of the shell of the separation cabin body (1), and the locking hook (3) is fixed on the support through a pin (4) and can rotate around the pin (4). The inclined plane at the front end of the lock hook (3) hooks the inclined plane of the boss of the shell at the tail end of the preceding stage missile (12). 4 groups of support (2) lock hooks (3) and pins (4) are generally uniformly distributed and installed on the boosting separation device. The mounting plate (5) is mounted on the boosting separating cabin shell (1), 4 groups of notches are arranged on the circumference of the mounting plate (5), and the positions of the notches correspond to the mounting positions of the lock hooks (3). The connecting plate (7) is abutted against the mounting plate (5), a hole is formed in the middle of the connecting plate (7) and the mounting plate (5), the explosion bolt (8) penetrates through the hole, the connecting plate (7) and the mounting plate (5) are connected together through a connecting nut (9), and the head of the explosion bolt (8) is mounted at the front end. 4 inclined plane bosses are arranged on the mounting plate, corresponding to the mounting positions of the lock hooks (3), threaded holes are machined in the bosses, and the adjusting studs (6) are abutted to the inclined planes at the tail ends of the lock hooks (3) through the threaded holes to restrain the lock hooks (3) from rotating. The protection device (10) is arranged on the outer side of the head of the explosion bolt (8) and fixed on the mounting plate (5), so that damage to the structure of the front-stage missile (12) caused by detonation and separation of the explosion bolt (8) is avoided.

When the boosting separation device is connected with a preceding-stage missile (12), the connecting plate (7) and the mounting plate (5) are kept in a contact state through the explosive bolt (8) and the connecting nut (9), and the adjusting stud (6) is adjusted to enable the front end of the lock hook (3) to be capable of being collected into the boosting separation cabin shell (1). The front end of the boosting separation cabin shell (1) is in sleeve fit with the tail end of a front-end guided missile (12), and the adjusting stud (6) is adjusted to enable the inclined hook surface at the front end of the plurality of groups of lock hooks (3) to be in contact with the boss inclined surface at the tail end of a front-stage guided missile (12). The connecting structure of the explosion bolt (8) is fixed by a connecting nut (9) with a fixed force.

In the state that the missile boosting separation device is connected and locked with a preceding-stage missile (12), the inclined plane at the rear end of the lock hook (3) is vertical to the threaded hole of the inclined plane boss on the connecting plate (7), and the acting force of the adjusting stud (6) is ensured to directly act on the inclined plane of the lock hook (3).

Through the stress lever ratio of the reasonable design latch hook (3) structure, the force transmitted to the explosive bolt (8) by the adjusting stud (6) through the connecting plate (7) is reduced, and the requirements on the bearing capacity of the explosive bolt (8) and the explosion impact resistance of the mechanism are reduced.

Technical scheme of the invention

The novel missile booster separation technology has the remarkable characteristics of simple structure, small size, smooth appearance, good separation synchronism, small separation impact, simplicity in assembly and debugging and high reliability, and has universality on the boosting separation of various small tactical missiles.

The missile boosting separation device comprises a boosting separation cabin shell (1), a support (2), a lock hook (3), a pin (4), a mounting plate (5), an adjusting stud (6), a connecting plate (7), an explosion bolt (8), a connecting nut (9) and a protection device (10). The support (2) is arranged on the wall of the shell of the separation cabin body (1), and the locking hook (3) is fixed on the support through a pin (4) and can rotate around the pin (4). The inclined plane at the front end of the lock hook (3) hooks the inclined plane of the boss of the shell at the tail end of the preceding stage missile (12). 4 groups of supports (2), lock hooks (3) and pins (4) are generally uniformly distributed and installed on the boosting separation device. The mounting plate (5) is mounted on the boosting separating cabin shell (1), 4 groups of notches are arranged on the circumference of the mounting plate (5), and the positions of the notches correspond to the mounting positions of the lock hooks (3). The connecting plate (7) is abutted against the mounting plate (5), a hole is formed in the middle of the connecting plate (7) and the mounting plate (5), the explosion bolt (8) penetrates through the hole, the connecting plate (7) and the mounting plate (5) are connected together through a connecting nut (9), and the head of the explosion bolt (8) is mounted at the front end. 4 inclined plane bosses are arranged on the mounting plate (5), corresponding to the mounting positions of the lock hooks (3), threaded holes are machined in the bosses, and the adjusting studs (6) are abutted to the inclined planes at the tail ends of the lock hooks (3) through the threaded holes to restrain the lock hooks (3) from rotating. The protection device (10) is arranged on the outer side of the head of the explosion bolt (8) and fixed on the mounting plate (5), so that damage to the structure of the front-stage missile (12) caused by detonation and separation of the explosion bolt (8) is avoided.

The boosting separation cabin shell (1) is fixedly connected with the missile booster (11) and is separated as a whole during separation. When the boosting separation device is connected with a preceding-stage missile (12), the connecting plate (7) and the mounting plate (5) are kept in a contact state through the explosive bolt (8) and the connecting nut (9), and the adjusting stud (6) is adjusted to enable the front end of the lock hook (3) to be capable of being collected into the boosting separation cabin shell (1). The front end of the boosting separation cabin shell (1) is in sleeve fit with the tail end of a front-end guided missile (12), and the adjusting stud (6) is adjusted to enable the inclined hook surface at the front end of the plurality of groups of lock hooks (3) to be in contact with the boss inclined surface at the tail end of a front-stage guided missile (12). The connecting structure of the explosion bolt (8) is fixed by a connecting nut (9) with a fixed force. And finally, the boosting separation device and the booster (11) are assembled and fixedly connected together.

In the state that the missile boosting separation device is connected and locked with the missile, the inclined plane at the rear end of the lock hook (3) is vertical to the threaded hole of the inclined plane boss on the connecting plate (7), and the acting force of the adjusting stud (6) is ensured to directly act on the inclined plane of the lock hook (3).

The locking state of the lock hook (3) is acted by the contact counterforce of the inclined plane at the tail end of the front-stage missile (12) and the restraining force of the adjusting stud (6), the counterforce borne by the adjusting stud (6) is transmitted to the explosion bolt (8) through the connecting plate (7), and the bearing capacity of the whole mechanism must meet the requirement that the missile is not damaged under various load conditions in the using, maintaining and launching processes. Through the stress lever ratio of the reasonable design latch hook (3) structure, the force transmitted to the explosive bolt (8) by the adjusting stud (6) through the connecting plate (7) can be reduced, and the requirements on the bearing capacity of the explosive bolt and the explosion impact resistance of the mechanism are reduced.

When the adjusting bolt is separated, the explosion bolt (8) is excited, the explosion bolt (8) is cut off, so that the connection between the connecting plate (7) and the mounting plate (5) is released, the connecting plate (7) loses constraint and moves backwards under the impact action of the explosion bolt (8), the adjusting stud (6) loses a limiting function, and all the lock hooks (3) lose constraint simultaneously. The lock hook (3) moves inwards under the action of aerodynamic force, the restraint between the preceding stage missile (12) and the boosting separation cabin shell (1) is released, and the separation between cabin sections is completed.

The invention has the advantages that:

the invention has the following remarkable advantages:

the structure is simple: according to the invention, a plurality of lock hooks (3) are matched with a connecting plate (7) and an adjusting stud (6) and the like, and the lock hooks (3) connected with the cabin section are fixed on a single explosion bolt (8).

The occupied space is small: the number of mechanisms is greatly reduced, and the space structure in the cabin is optimized, so that the occupied length and space of the whole cabin are minimized, and the length and space shortening of the small missile is facilitated.

The installation and operation are convenient: the boosting separation device has good accessibility of the whole structure, few assembling operation links and convenient and quick installation.

Good synchronism and small separation impact: a single explosion bolt (8) is matched with mechanisms such as a lock hook (3) and the like, so that locking points of a plurality of cabin sections are released simultaneously; meanwhile, the lever structure of the lock hook is utilized to reduce the stress of the explosive bolt (8), the explosive charge of the explosive bolt (8) can be reduced, and the separation impact is reduced.

Example 1

A small missile is provided, in order to increase the range, a booster is additionally arranged at the rear end. The missile boosting separation device mainly comprises a boosting separation cabin shell (1), a support (2), a lock hook (3), a pin (4), a mounting plate (5), an adjusting stud (6), a connecting plate (7), an explosion bolt (8), a connecting nut (9) and a protection device (10). The support (2) is arranged on the wall of the shell of the separation cabin body (1), and the locking hook (3) is fixed on the support through a pin (4) and can rotate around the pin (4). The inclined plane at the front end of the lock hook (3) hooks the inclined plane of the boss of the shell at the tail end of the preceding stage missile (12). 4 groups of support (2) lock hooks (3) and pins (4) are generally uniformly distributed and installed on the boosting separation device. The mounting plate (5) is mounted on the boosting separating cabin shell (1), 4 groups of notches are arranged on the circumference of the mounting plate (5), and the positions of the notches correspond to the mounting positions of the lock hooks (3). The connecting plate (7) is abutted against the mounting plate (5), a hole is formed in the middle of the connecting plate (7) and the mounting plate (5), the explosion bolt (8) penetrates through the hole, the connecting plate (7) and the mounting plate (5) are connected together through a connecting nut (9), and the head of the explosion bolt (8) is mounted at the front end. 4 inclined plane bosses are arranged on the connecting plate (7), corresponding to the installation position of the lock hook (3), threaded holes are machined in the bosses, and the adjusting stud (6) is abutted to the inclined plane at the tail end of the lock hook (3) through the threaded holes to restrain the lock hook (3) from rotating. The protection device (10) is arranged on the outer side of the head of the explosion bolt (8) and fixed on the mounting plate (5), so that damage to the structure of the front-stage missile (12) caused by detonation and separation of the explosion bolt (8) is avoided.

The boosting separation cabin shell body (1) is fixedly connected with the missile booster (11) and is separated as a whole during separation. When the boosting separation device is connected with a preceding-stage missile (12), the connecting plate (7) and the mounting plate (5) are kept in a contact state through the explosive bolt (8) and the connecting nut (9), and the adjusting stud (6) is adjusted to enable the front end of the lock hook (3) to be capable of being collected into the boosting separation cabin shell (1). The front end of the boosting separation cabin shell (1) is in sleeve fit with the tail end of a front-end guided missile (12), and the adjusting stud (6) is adjusted to enable the inclined hook surface at the front end of the plurality of groups of lock hooks (3) to be in contact with the boss inclined surface at the tail end of a front-stage guided missile (12). The connecting structure of the explosion bolt (8) is fixed by a connecting nut (9) with a fixed force. And finally, the boosting separation device and the booster (11) are assembled and fixedly connected together.

In the state that the missile boosting separation device is connected and locked with a preceding-stage missile (12), the inclined plane at the rear end of the lock hook (3) is vertical to the threaded hole of the inclined plane boss on the connecting plate (7), and the acting force of the adjusting stud (6) is ensured to directly act on the inclined plane of the lock hook (3).

The locking state of the lock hook (3) is acted by the contact counterforce of the inclined plane at the tail end of the front-stage missile (12) and the restraining force of the adjusting stud (6), the counterforce borne by the adjusting stud (6) is transmitted to the explosion bolt (8) through the connecting plate (7), and the bearing capacity of the whole mechanism is calculated to meet the requirement that the missile is not damaged under various load conditions in the using, maintaining and launching processes. The stress lever ratio of the optimized design latch hook (3) structure is 1:3 or 1:4, thereby reducing the force transmitted to the explosive bolt by the adjusting stud (6) through the connecting plate (7), and reducing the requirements on the bearing capacity of the explosive bolt (8) and the explosion impact resistance of the mechanism.

When the adjusting bolt is separated, the explosion bolt (8) is excited, the explosion bolt (9) is sheared, so that the connection between the connecting plate (7) and the mounting plate (5) is released, the connecting plate (7) loses constraint and moves backwards under the impact action of the explosion bolt (8), the adjusting stud (6) loses a limiting function, and all the lock hooks (3) lose constraint simultaneously. The lock hook (3) moves inwards under the action of aerodynamic force, the restraint between the preceding stage missile (12) and the boosting separation cabin shell (1) is released, and the separation between cabin sections is completed.

The above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, several modifications and variations can be made without departing from the technical principle of the present invention, and these modifications and variations should also be regarded as the protection scope of the present invention.