CN112361895A

CN112361895A - Retention type missile tail cover

Info

Publication number: CN112361895A
Application number: CN202011139269.XA
Authority: CN
Inventors: 王俊善; 丁伟; 周凯; 王富生; 赵双龙; 吴穹
Original assignee: General Designing Institute of Hubei Space Technology Academy
Current assignee: General Designing Institute of Hubei Space Technology Academy
Priority date: 2020-10-22
Filing date: 2020-10-22
Publication date: 2021-02-12
Anticipated expiration: 2040-10-22
Also published as: CN112361895B

Abstract

The application relates to a detention type missile tail cover, which relates to the technical field of missile launching and comprises a tail cover main body, a detention mechanism and a thrust balancing structure, wherein the tail cover main body comprises an open end, and the open end is used for covering an missile body; the detention mechanism is assembled on the opening end and can move along the axial direction of the bullet barrel to abut against the inner wall of the bullet barrel so as to cause the tail cover main body to be detained in the bullet barrel after being separated from the bullet body; the thrust balancing structure is arranged on the outer surface of the tail cover main body and comprises an annular first separation cover, and the first separation cover is formed by protruding the opening end in the circumferential direction away from the retention mechanism. In can preventing that the air current from flowing into the space that forms between the inner wall of tail cover main part and the outer wall of a play section of thick bamboo, a play section of thick bamboo can not receive the air current and assault and produce vibration and beat, guarantees the steady of projectile and tail cover main part separation process, does not influence the play section of thick bamboo gesture of projectile.

Description

Retention type missile tail cover

Technical Field

The application relates to the technical field of missile launching, in particular to a detention type missile tail cover.

Background

The tail cover is an important component of the missile launching device, is used for bearing huge airflow impact force generated by the missile launching device, and has the characteristics of high temperature, high pressure and high speed, and the use requirements of heavy load, good sealing property, high strength and high rigidity.

At present, after a tail cover and a projectile body are ejected out of a launching tube together, the tail cover and the projectile body are separated from the projectile body in a side-push and spin-throwing separation mode, wherein an explosion bolt is unlocked firstly in the side-push mode, and an engine is pushed to start after the tail cover is separated from the projectile body, so that the tail cover avoids the engine jet flow of the projectile body; in the rotary throwing mode, the tail cover and the projectile body are restrained by the hinge mechanism, the tail cover is unlocked and rotates for a certain angle around the hinge shaft, then the hinge is unlocked, and the tail cover is far away from the projectile body under the inertia effect.

However, the two modes are both the scheme that the tail covers are separated after being taken out of the barrel, and a large number of tail covers are thrown into the air during intensive launching and are easy to collide with subsequently launched missiles. Therefore, the separation mode of the tail cover and the projectile body does not meet the use requirement of missile intensive type launching.

In the correlation technique, adopt and install metal shearing sheet group in the launching tube outside, adopt the mode of cuting the sheetmetal to realize the buffering braking of tail cover, but there is certain impact when every layer of sheetmetal of this mode cuts off, braking process is steady inadequately, leads to launching tube vibration and beat, and the body has not left the barrel this moment, leads to the body to go out before the barrel with launching tube slight collision, influence a posture.

Disclosure of Invention

The embodiment of the application provides a formula of detaining guided missile tail cover to tail cover is unstable at the buffering braking process among the solution correlation technique, leads to launch canister vibration and beat, and the projectile body has not left the barrel this moment, leads to the projectile body to go out before the barrel with launch canister slight collision easily, influences the problem of a posture.

In a first aspect, there is provided a detaining missile tail shroud comprising:

the tail cover body comprises an opening end, and the opening end is used for covering the projectile body;

the detention mechanism is assembled on the opening end and can move along the axial direction of the bullet barrel to abut against the inner wall of the bullet barrel so as to cause the tail cover main body to be detained in the bullet barrel after being separated from the bullet body;

the thrust balancing structure is arranged on the outer surface of the tail cover main body and comprises an annular first separation cover, and the first separation cover is formed by protruding the opening end in the circumferential direction away from the retention mechanism.

In some embodiments, the thrust equalizing structure further includes an annular second divider shroud disposed coaxially with the first divider shroud and dividing the outer surface of the aft shroud body into a secondary impingement region located between the first and second divider shrouds and a primary impingement region located inboard of the second divider shroud.

In some embodiments, the thrust equalizing structure further includes an annular third divider shroud positioned inboard of and coaxially with the second divider shroud, and the third divider shroud divides the main impact region into a first sub-impact region positioned between the third divider shroud and the second divider shroud, and a second sub-impact region positioned inboard of the third divider shroud.

In some embodiments, the thrust equalizing structure further comprises a first reinforcing structure in a net shape, and the first reinforcing structure is disposed in the first sub-impact region and is used for reinforcing the impact strength of the first sub-impact region.

In some embodiments, a cushioning material is disposed within the mesh of the first reinforcing structure.

In some embodiments, the thrust equalizing structure further comprises an annular fourth divider shroud located inboard of and coaxially disposed with the third divider shroud, and the fourth divider shroud divides the second sub-impingement region into a third sub-impingement region located between the fourth divider shroud and the third divider shroud, and a fourth sub-impingement region located inboard of the fourth divider shroud.

In some embodiments, an end of the third separation cowl remote from the aft cowl body is lower than an end of the fourth separation cowl remote from the aft cowl body.

In some embodiments, the thrust balancing structure further includes a second reinforcing structure in a mesh shape, and the second reinforcing structure is disposed in the fourth sub-impact region and is configured to reinforce the impact strength of the fourth sub-impact region.

In some embodiments:

the inner wall of the cartridge is provided with a braking part, and the top end of the braking part is convexly provided with a propping end;

the detention mechanism comprises a plurality of guide pieces which are distributed at intervals along the circumferential direction of the opening end; the bottom of the guide piece is fixed on the opening end, and the top of the guide piece is used for abutting against the abutting end.

In some embodiments:

one side of the braking element, which is far away from the inner wall of the cartridge, forms an inclined braking surface towards the center of the cartridge;

the top of the guide piece forms an inclined guide surface towards the center of the tail cover main body, and the guide surface is matched with the braking surface.

The beneficial effect that technical scheme that this application provided brought includes: prevent the air current to flow into in the space that forms between the inner wall of tail hood main part and the outer wall of a play section of thick bamboo, a play section of thick bamboo can not receive the air current impact and produce vibration and beat, guarantees the steady of projectile and tail hood main part separation process, does not influence the play section of thick bamboo gesture of projectile.

The embodiment of the application provides a detain formula guided missile tail-hood, because in the projectile body launch process of this application embodiment, detain the mechanism in the tail-hood main part along the axial displacement of a bullet section of thick bamboo to support and hold on the inner wall of a bullet section of thick bamboo to make the tail-hood main part with the projectile body separation back, be detained in a bullet section of thick bamboo, prevent that the projectile body of follow-up transmission from colliding with the tail-hood main part. And the circular arc-shaped outer surface of the tail cover main body is impacted by airflow, and the airflow flows along the circumferential direction and the radial direction of the tail cover main body. Because the first separating cover is formed by the protruding arrangement of the opening end along the circumferential direction towards the direction far away from the detention mechanism, the gas flowing along the circumferential direction is guided to the whole arc-shaped surface enclosed by the first separating cover, and the effect of balancing the gas acting force is achieved; and the first separation cover can basically resist all the airflow flowing towards the first separation cover along the radial direction to enter an area surrounded by the first separation cover, and the airflow is reflected to the center of the tail cover main body to be gathered, so that the airflow is prevented from flowing into a gap formed between the inner wall of the tail cover main body 1 and the outer wall of the cartridge, and the cartridge cannot be impacted by the airflow to generate vibration and deflection. And the centre of a circle of first partition cover is located the axis of tail-hood main part, therefore first partition cover can will strike the outer surface of tail-hood main part on the air current push to the center of tail-hood main part evenly, guarantee the stability of projectile and tail-hood main part separation process, do not influence the play section of thick bamboo gesture of projectile.

Drawings

In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings needed to be used in the description of the embodiments are briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.

FIG. 1 is a top view of a detention missile tail cap provided by an embodiment of the present application;

FIG. 2 is a bottom view of a detention missile tail cap provided by an embodiment of the present application;

FIG. 3 is a front view of a detention missile tail cap provided by an embodiment of the present application;

fig. 4 is a schematic diagram of a braking process of the detaining missile tail cover provided by the embodiment of the application.

In the figure: 1. a tail cap body; 10. an open end; 2. a retention mechanism; 20. a guide member; 200. a guide surface; 3. a cartridge; 30. a stopper; 300. a holding end; 301. a braking surface; 4. a thrust balancing structure; 40. a first separation hood; 41. a second separation hood; 42. a secondary impact region; 43. a primary impact region; 44. a third separation cover; 430. a first sub-impact region; 431. a second sub-impingement area; 432. a third sub-impact region; 433. a fourth sub-impact region; 45. a first reinforcing structure; 46. a fourth separation cover; 47. a second reinforcing structure.

Detailed Description

In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are some embodiments of the present application, but not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.

Referring to fig. 1 and 2, the embodiment of the application provides a detention type missile tail cover, which comprises a tail cover main body 1, a detention mechanism 2 and a thrust balancing structure 4, wherein the tail cover main body 1 comprises an open end 10, and the open end 10 is used for covering a missile body; the detention mechanism 2 is assembled on the opening end 10 and can move along the axial direction of the bullet barrel 3 to be abutted against the inner wall of the bullet barrel 3, so that the tail cover main body 1 is separated from the bullet body and then is detained in the bullet barrel 3; the thrust balancing structure 4 is arranged on the outer surface of the tail cover main body 1, and comprises an annular first separation cover 40, wherein the first separation cover 40 is formed by protruding the opening end 10 in the circumferential direction towards the direction far away from the retention mechanism 2.

In the embodiment of the application, before the projectile body is launched, the tail cover body 1 is bowl-shaped, covers the projectile body through the opening end 10, and is accommodated in the cartridge 3 together with the projectile body. In the process of launching the projectile body, the retention mechanism 2 on the tail cover main body 1 moves along the axial direction of the projectile barrel 3 to be abutted against the inner wall of the projectile barrel 3, so that the tail cover main body 1 is retained in the projectile barrel 3 after being separated from the projectile body, and the subsequent launched projectile body is prevented from colliding with the tail cover main body 1. And the arc-shaped outer surface of the tail cover main body 1 is impacted by airflow, and the airflow flows along the circumferential direction and the radial direction of the tail cover main body 1. Because the first separating hood 40 is formed by the opening end 10 which is convexly arranged along the circumferential direction towards the direction far away from the detention mechanism 2, the gas flowing along the circumferential direction is guided to the whole arc-shaped surface enclosed by the first separating hood 40, and the effect of balancing the acting force of the gas is achieved; and the first separating hood 40 can basically prevent all the airflow flowing towards the first separating hood 40 along the radial direction from entering the area enclosed by the first separating hood 40, and the airflow is reflected to be gathered to the center of the tail hood main body 1, so that the airflow is prevented from flowing into a gap formed between the inner wall of the tail hood main body 1 and the outer wall of the cartridge 3, and the cartridge 3 cannot be impacted by the airflow to generate vibration and deflection. And the centre of a circle of first partition cover 40 is located the axis of tail hood main part 1, therefore first partition cover 40 can will strike on the surface of tail hood main part 1 the air current push to the center of tail hood main part 1 evenly, guarantee the stability of projectile and tail hood main part 1 separation process, do not influence the play section of thick bamboo gesture of projectile.

Optionally, the thrust equalizing structure 4 further includes an annular second partition cover 41, the second partition cover 41 being disposed coaxially with the first partition cover 40 and partitioning the outer surface of the tail cover body 1 into a secondary impact region 42 located between the first partition cover 40 and the second partition cover 41, and a primary impact region 43 located inside the second partition cover 41.

In the embodiment of the present application, according to simulation, the area of the tail cover main body 1 that is mainly subjected to the impact of the airflow is determined, and the area is surrounded by the second partition cover 41, and the main impact area 43 is divided. The second partition case 41 pushes the airflow in the main impact region 43 to the center of the tail cover body 1, and prevents the large impact airflow in the main impact region 43 from flowing to the sub impact region 42, thereby reducing the airflow strength in the sub impact region 42, and further reducing the risk of the airflow flowing into the gap formed between the inner wall of the tail cover body 1 and the outer wall of the barrel 3.

Preferably, the thrust equalizing structure 4 further includes an annular third partition cover 44, the third partition cover 44 being located inside the second partition cover 41 and coaxially disposed with the second partition cover 41, and the third partition cover 44 partitioning the main impact region 43 into a first sub-impact region 430 located between the third partition cover 44 and the second partition cover 41, and a second sub-impact region 431 located inside the third partition cover 44.

In the present embodiment, the main impingement area 43 is divided into the first sub-impingement area 430 and the second sub-impingement area 431 by the third separation hood 44, the airflow in the first sub-impingement area 430 flows in the circumferential direction and the radial direction, and the airflow flowing in the radial direction is reflected back and forth by the second separation hood 41 and the third separation hood 44, so that the energy is greatly reduced. The airflow in the second sub-impingement area 431 enclosed in the third partition cover 44 also flows in the circumferential direction and the radial direction, and the airflow flowing in the radial direction in this area is pushed by the third partition cover 44 to be gathered at the center of the tail cover main body 1 without flowing outward. The partitioning of the main impact area 43 is more beneficial to the partitioning weakening and concentration of the energy of the main impact airflow, and prevents the airflow from spreading into the gap formed between the inner wall of the tail cover main body 1 and the outer wall of the barrel 3.

Further, the thrust balancing structure 4 further includes a first reinforcing structure 45 having a net shape, and the first reinforcing structure 45 is disposed in the first sub-impact region 430 and is used for reinforcing the impact strength of the first sub-impact region 430.

The embodiment of the application adopts the first mesh reinforcing structure 45 to reinforce the first sub-impact area 430 so as to resist the airflow impact suffered in the first sub-impact area 430 and improve the impact strength of the tail hood main body 1.

Further, the meshes of the first reinforcing structure 45 are provided with a cushioning material.

The airflow within the first sub-impact region 430 is substantially absorbed by the cushioning material within the mesh of the first reinforcing structure 45, substantially reducing the airflow impact force experienced by the first sub-impact region 430 and enhancing the impact resistance of the first sub-impact region 430.

Preferably, the thrust equalizing structure 4 further comprises an annular fourth partition cowl 46, the fourth partition cowl 46 being located inside the third partition cowl 44 and coaxially arranged with the third partition cowl 44, and the fourth partition cowl 46 dividing the second sub-impact area 431 into a third sub-impact area 432 located between the fourth partition cowl 46 and the third partition cowl 44 and a fourth sub-impact area 433 located inside the fourth partition cowl 46.

In the embodiment of the present application, according to the simulation results, the fourth sub-impingement area 433 and the first sub-impingement area 430 are the most dominant impingement areas of the airflow, so that the first sub-impingement area 430 is divided by the second partition hood 41 and the third partition hood 44, and the fourth sub-impingement area 433 is divided by the fourth partition hood 46. The airflow in the third sub-impingement area 432 and the fourth sub-impingement area 433 both flow in the circumferential and radial directions, and the airflow in the third sub-impingement area 432 is reflected back and forth by the third and

fourth divider hoods

44, 46, with a substantial reduction in energy. The radially flowing air flow in the fourth sub-impingement region 433 is pushed by the fourth divider shroud 46 to gather in the center of the tail shroud body 1, and does not flow outward. Through four separation covers, divide the air current impact area to promote most air current to the center of tail-hood main part 1, prevent that the air current from diffusing to in the space that forms between the inner wall of tail-hood main part 1 and the outer wall of the shell barrel 3, arouse the vibration of shell barrel 3. And by separating the fourth sub-impact area 433 with the largest airflow impact and the first sub-impact area 430, the partition gently weakens the energy of the airflow, and the stability of the separation process of the projectile body and the tail cover main body 1 is ensured.

Referring to FIG. 3, further, the end of the third partition cowl 44 that is away from the tail cowl body 1 is lower than the end of the fourth partition cowl 46 that is away from the tail cowl body 1.

This prevents the airflow impacting the second sub-impact area 431 from being reflected by the fourth partition cover 46 into the first sub-impact area 430, so as to converge the airflow in the second sub-impact area 431 toward the center of the tail cover main body 1.

Furthermore, the thrust balancing structure 4 further includes a second reinforcing structure 47 in a net shape, and the second reinforcing structure 47 is disposed in the fourth sub-impact region 433 and is used for reinforcing the impact strength of the fourth sub-impact region 433.

The embodiment of the application adopts the second net-shaped reinforcing structure 47 to reinforce the fourth sub-impact area 433 so as to resist the airflow impact suffered in the fourth sub-impact area 433 and improve the impact strength of the tail hood main body 1. And cushioning material is provided within the mesh of the second reinforcing structure 47. The airflow within the fourth sub-impact region 433 is substantially absorbed by the cushioning material within the mesh of the second reinforcing structure 47, which substantially reduces the airflow impact force experienced by the fourth sub-impact region 433 and enhances the impact resistance of the fourth sub-impact region 433.

Referring to fig. 4, alternatively: a braking piece 30 is arranged on the inner wall of the cartridge 3, and the top end of the braking piece 30 is convexly arranged to form a propping end 300; the retention mechanism 2 includes a plurality of guides 20, the plurality of guides 20 being spaced apart along the circumferential direction of the open end 10; the guide member 20 has a bottom fixed to the opening end 10 and a top for abutting against the abutting end 300.

In this application embodiment, the inner wall of tail cover main part 1 near open end 10 is gone up to protruding the establishing along the circumferencial direction and is formed with the plummer, and the plummer is used for supporting the support ring of elastomer afterbody, and has seted up the pinhole on the plummer, and the elastomer is connected with the plummer through the round pin axle.

When the projectile body is launched, the tail cover main body 1 and the projectile body move upwards together, the guide piece 20 moves on the braking piece 30 along the axis direction of the projectile barrel 3 to abut against the abutting end 300, at the moment, the projectile body continues to move upwards, the tail cover main body 1 is abutted by the abutting end 300 and does not move upwards any more, the pin shaft is separated from the pin hole on the bearing table, and the separation of the tail cover main body 1 and the projectile body is realized.

Preferably, the side of the braking member 30 away from the inner wall of the cartridge 3 forms an inclined braking surface 301 toward the center of the cartridge 3; the top of the guide member 20 forms an inclined guide surface 200 toward the center of the tail cover body 1, and the guide surface 200 is fitted with the braking surface 301.

Specifically, the method comprises the following steps:

the guide member 20 is trapezoidal, and the top of the guide member 20 forms an inclined guide surface 200 toward the center of the tail cover body 1; the stopper 30 has a wedge shape whose inner diameter is gradually reduced in the axial direction of the cartridge 3. The guiding surface 200 of the guiding element 20 is matched with the braking surface 301 of the braking element 30, so that the braking force can be increased, the braking of the push disc within 200mm can be guaranteed, and the braking effect is good.

The braking process is as follows: the guide member 20 contacts and presses the stopper 30 of the inner wall of the cartridge 3 during the upward movement of the tail cover body 1. When the guide surface 200 contacts the braking surface 301, a frictional force is generated, and the tail cover body 1 enters a braking state. The friction force is continuously increased along with the movement of the tail cover main body 1, the speed of the tail cover main body 1 is rapidly reduced, at the braking limit stroke, the guide member 20 which is decelerated to the low-speed state collides with the abutting end 300, and the tail cover main body 1 is completely braked to the static state, so that the retention of the tail cover main body 1 is realized.

Further, the tail hood main body 1 of the embodiment of the application comprises a cylindrical section and an arc-shaped section which are connected with each other, the open end 10 is arranged at the top end of the cylindrical section, and a piston ring groove is formed in the cylindrical section between the open end 10 and the first separation hood 40; the detained missile tail cover also comprises a sealing ring, the sealing ring is arranged on the piston ring groove and comprises a first air ring and a second air ring, and the notches of the first air ring and the second air ring are inclined openings; the section of the first gas ring is in an arc ring shape, so that the sealing performance is better; the cross section of the second air ring is in a rectangular ring shape, and the second air ring has good heat conductivity. The arrangement of the two air rings ensures good sealing performance between the tail cover main body 1 and the bullet tube 3.

In the description of the present application, it should be noted that the terms "upper", "lower", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, which are only for convenience in describing the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and operate, and thus, should not be construed as limiting the present application. Unless expressly stated or limited otherwise, the terms "mounted," "connected," and "connected" are intended to be inclusive and mean, for example, that they may be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art as appropriate.

It is noted that, in the present application, relational terms such as "first" and "second", and the like, are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.

The above description is merely exemplary of the present application and is presented to enable those skilled in the art to understand and practice the present application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the application. Thus, the present application is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A detention missile tail shroud, comprising:

the tail cover comprises a tail cover body (1) and a tail cover body, wherein the tail cover body comprises an opening end (10), and the opening end (10) is used for covering the projectile body;

the detention mechanism (2) is arranged on the opening end (10) and can move along the axial direction of the bullet tube (3) to abut against the inner wall of the bullet tube (3) so as to cause the tail cover main body (1) to be detained in the bullet tube (3) after being separated from the bullet body;

the thrust balancing structure (4) is arranged on the outer surface of the tail cover main body (1) and comprises an annular first separation cover (40), and the first separation cover (40) is formed by protruding the opening end (10) towards the direction far away from the retention mechanism (2) along the circumferential direction.

2. The retentate missile tail shroud according to claim 1, characterized in that the thrust equalizing structure (4) further comprises an annular second shroud (41), the second shroud (41) being arranged coaxially with the first shroud (40) and dividing the outer surface of the tail shroud body (1) into a secondary impact region (42) between the first shroud (40) and the second shroud (41), and a primary impact region (43) inside the second shroud (41).

3. The detaining missile tail cover according to claim 2, characterized in that the thrust equalising structure (4) further comprises an annular third partition cover (44), which third partition cover (44) is located inside the second partition cover (41) and is arranged coaxially with the second partition cover (41), and which third partition cover (44) divides the main impact area (43) into a first sub-impact area (430) located between the third partition cover (44) and the second partition cover (41), and a second sub-impact area (431) located inside the third partition cover (44).

4. The detaining missile tail cover according to claim 3, characterized in that the thrust equalising structure (4) further comprises a first reinforcing structure (45) in the form of a net, the first reinforcing structure (45) being provided in the first sub-impact region (430) and serving to reinforce the impact strength of the first sub-impact region (430).

5. The detaining missile tail cover according to claim 4, characterized in that the meshes of the first reinforcement structure (45) are provided with a cushioning material.

6. The detaining missile tail cover according to claim 3, characterized in that the thrust equalising structure (4) further comprises an annular fourth partition shield (46), the fourth partition shield (46) being located inside the third partition shield (44) and being arranged coaxially with the third partition shield (44), and the fourth partition shield (46) dividing the second sub-impact region (431) into a third sub-impact region (432) located between the fourth partition shield (46) and the third partition shield (44), and a fourth sub-impact region (433) located inside the fourth partition shield (46).

7. The detaining missile tail cover according to claim 6, characterized in that the end of the third partition cover (44) remote from the tail cover body (1) is lower than the end of the fourth partition cover (46) remote from the tail cover body (1).

8. The detaining missile tail cover according to claim 6, characterized in that the thrust equalising structure (4) further comprises a second reinforcing structure (47) in the form of a net, the second reinforcing structure (47) being provided in the fourth sub-impact region (433) and serving to reinforce the impact strength of the fourth sub-impact region (433).

9. The detented missile tail cap of claim 1, wherein:

a braking piece (30) is arranged on the inner wall of the bullet barrel (3), and the top end of the braking piece (30) is convexly arranged to form a propping end (300);

the detention mechanism (2) comprises a plurality of guide pieces (20), and the guide pieces (20) are distributed at intervals along the circumferential direction of the opening end (10); the bottom of the guide piece (20) is fixed on the opening end (10), and the top of the guide piece is used for abutting against the abutting end (300).

10. The detented missile tail cap of claim 9, wherein:

one side of the braking piece (30) far away from the inner wall of the cartridge (3) forms an inclined braking surface (301) towards the center of the cartridge (3);

the top of the guide piece (20) forms an inclined guide surface (200) towards the center of the tail cover main body (1), and the guide surface (200) is matched with the braking surface (301).