CN104089546B - The variable aerodynamic arrangement structure of body - Google Patents

Abstract

The invention discloses a variable aerodynamic layout structure of a projectile, in particular to a variable aerodynamic layout structure capable of taking into account the stability of the projectile in the uncontrolled flight stage and the hit accuracy in the correction stage. The variable aerodynamic shape scheme is adopted. In the initial uncontrolled flight section of the ballistic trajectory, the tail is locked in a small tail aerodynamic layout, which can not only ensure the flight stability of the projectile, but also reduce resistance and increase the range; The layout increases the static stability of the projectile, so that the attitude angle oscillation of the projectile caused by the pulse force can quickly converge, which meets the requirements of the control system. The invention takes into account the advantages of both the aerodynamic layout of the fixed tail and the aerodynamic layout of the large tail, which can not only meet the static stability requirements of the projectile, reduce the influence of the attitude angle oscillation of the projectile caused by the pulse force on the control system, but also ensure the range and correction accuracy Requirements, multiple range test verification shows that the program is feasible.

Description

Variable aerodynamic layout structure of projectile

technical field

The invention relates to the field of missile control, in particular to a variable aerodynamic layout structure of a missile body.

Background technique

In modern warfare, the use of conventional weapons platforms to develop low-cost smart guided missiles can not only greatly improve the combat effectiveness of conventional weapons, but also equip a large number of troops. It has become one of the development directions of guided missiles in various countries. At present, with the development of electronic technology, optoelectronic technology, micro-processing technology and guidance technology, the miniaturization of guidance components and the improvement of high overload resistance have made the technical conditions for the guidance of conventional missiles more mature. The scale has also gradually expanded, and its role in the war has become more and more important.

The simple modified projectile controlled by the pulse engine can effectively improve the shooting accuracy compared with the standard mortar, and can greatly reduce the consumption of the projectile under the same combat conditions; Compared with the steering gear control system, the structure is simple, and the manufacturing and maintenance costs are relatively low, so it can be equipped in large quantities. However, the existing projectile aerodynamic layout scheme still has the following technical defects:

(1) The aerodynamic structure layout of the traditional standard projectile adopts the aerodynamic layout scheme of fixed tail, that is, the tail of the projectile is fixed, the tail area is small, and the drag coefficient is small, but it cannot meet the stability requirements, especially after the impact of the impulse engine at the end of the trajectory , resulting in a large range of angle of attack. Due to the low static stability of the projectile, the convergence of the angle of attack is slow, which cannot meet the requirements of the control system, resulting in low correction accuracy.

(2) According to the stability requirements of the final correction section, the aerodynamic layout scheme of the large tail fin is designed, that is, the tail fin of the projectile body is relatively large. During ignition, the angle of attack converges to the allowable range of the control system, which meets the control requirements. However, compared with the aerodynamic layout of the fixed tail, the drag coefficient of the projectile with the aerodynamic layout of the large tail is increased, and the range is reduced, which cannot meet the requirements of simple correction of the projectile range.

Due to the existence of the above-mentioned problems, the inventors conducted in-depth research on the existing aerodynamic layout structure of projectiles in order to solve the problems of low correction accuracy and reduced shooting range of projectiles.

Contents of the invention

In order to overcome the above-mentioned problems, the present inventor has carried out intensive research, and found that by designing a projectile body that can change the structure of the empennage, that is, designing a projectile structure with a variable aerodynamic layout scheme, during the flight process of the projectile body, the When appropriate, change the aerodynamic layout structure of the projectile so that when the projectile is in the initial uncontrolled flight stage of the ballistic trajectory, the sleeve locks the empennage to form a body structure with a fixed empennage. The flight of the body is stable, and the resistance can be reduced to increase the range; in the final stage of the ballistic flight, the control device controls the movement of the sleeve, so that the tail fixed by the sleeve bounces off and becomes a large tail, forming a large tail aerodynamic layout, increasing the The static stability of the projectile can quickly converge the attitude angle oscillation of the projectile caused by the pulse force, meet the requirements of the control system, complete the control of the flight stage of the projectile, and accurately hit the target, thereby completing the present invention.

The main purpose of the present invention is to provide the following aspects:

(1) The variable aerodynamic layout structure of the projectile is characterized in that the projectile tail 1 of the projectile is cylindrical in shape, the projectile tail is covered with a sleeve 2, and the end of the projectile tail 1 is provided with fins The fixed seat 4 is equipped with fins 5 on the fin fixed seat 4,

The sleeve is in the shape of a cylinder with two ends open, and the sleeve 2 is fixed on the body tail 1 through the positioning pin 3. If the positioning pin 3 is removed, the sleeve can slide on the body tail along the direction of the body axis. An air outlet hole 21 is provided on the wall of the cylinder 2, and an outwardly protruding fin restricting ring 22 is provided at the rear end of the sleeve, that is, the end away from the warhead;

Described fin 5 is the strip plate that metal material is made, and a plurality of fins 5 are evenly installed around body tail 1, and the plate surface direction of fin 5 is perpendicular to the cylindrical surface of body tail, namely body axis. The center is located on the plane where the plate surface of the fin is located. The installation method of the fin is as follows: the rear end of the fin is fixed on the fin holder 4 of the missile body through the pin shaft 6, and the front end of the fin is embedded in the fin on the sleeve. In the limit ring 22, the fins are fixed on the projectile body by the sleeve and the pin shaft;

The inside of the projectile tail 1 is provided with an explosive device 7, fuel is placed in the explosive device 7, and a vent pipe 8 is connected on the explosive device 7, and the vent pipe 8 is T-shaped, and the vent pipe 8 is not connected with the explosive device The other two ends of the sleeve extend into the gap between the sleeve and the body tail 1;

Wherein, a spring device is sleeved outside the pin shaft, and the spring device includes a torsion spring. When the fin restricting ring 22 locks the fin, the fin presses the torsion spring to store force in the torsion spring. When the sleeve moves forward , when the front end of the fin comes out of the fin restricting ring 22, the torsion spring drives the fin to rotate around the pin shaft 6; after the rotation stops, the wing sweep angle of the fin is 55° to 65°;

The flight process of the projectile can be divided into the uncontrolled flight stage at the beginning of the trajectory and the controlled correction stage at the end of the trajectory;

When the projectile is stored and at the initial uncontrolled flight stage of the ballistic trajectory, the sleeve fixes the wings, and the projectile is a projectile with a fixed empennage, that is, the aerodynamic layout of the projectile at this time is the aerodynamic layout of the fixed empennage;

During the flight, when the projectile enters the stage of controlled correction at the end of the ballistic trajectory, the sleeve slides forward, and the spring device bounces off the wings. The projectile is a projectile with a large tail, that is, the aerodynamic layout of the projectile is large Aerodynamic layout of the rear wing.

(2) According to the variable aerodynamic layout structure of the projectile described in the above (1), it is characterized in that when the projectile enters the controlled correction stage at the end of the trajectory, the explosive device is ignited, and the generated high-temperature gas is transported to the In the gap between the sleeve and the body tail 1, break the positioning pin 3 and push the sleeve to slide forward and slide towards the front end of the body.

(3) According to the variable aerodynamic layout structure of the missile body described in the above (1), it is characterized in that, during the flight process of the missile body, the time point when the missile body enters the controlled correction stage at the end of the trajectory is the programming time, and the ground control system The loading time is calculated according to the trajectory, and passed to the projectile information binder, and the projectile information binder transmits the information to the projectile to be launched.

(4) According to the variable aerodynamic layout structure of the projectile described in (1) above, it is characterized in that the sweep angle of the projectile is 60° when the projectile enters the stage of controlled correction and forms the projectile structure with a large tail.

(5) According to the variable aerodynamic layout structure of the missile body described in the above (1), it is characterized in that the installation angle range of the fins relative to the bomb shaft is 2° to 3°, so as to ensure that the rotational speed of the missile body is controlled at 5-3°. 10 rev/s range.

(6) According to the variable aerodynamic layout structure of the projectile described in the above (1), it is characterized in that, the middle part of the fin holder 4 is provided with a plate groove 41 for the fin 5 to extend into, and the pin shaft 6 passes through the plate groove The through hole on the fin 5 connects the fin holder 4 and the fin (5) as a whole.

(7) According to the variable aerodynamic layout structure of the projectile described in (1) above, it is characterized in that there are six fins 5 in total, and each fin is arranged at intervals of 60°.

(8) The variable aerodynamic layout structure of the projectile according to the above (1), characterized in that the diameter of the part of the projectile tail 1 inside the sleeve is smaller than the diameter of other parts of the projectile tail 1 .

(9) The variable aerodynamic layout structure of the projectile according to the above (1), characterized in that there are two positioning pins 3, and the positioning pins 3 are made of aluminum material, which is easy to break.

The aerodynamic layout scheme of the present invention takes into account the advantages of both the aerodynamic layout of the fixed tail and the aerodynamic layout of the large tail, and skillfully changes the aerodynamic layout structure through the bounce of the tail, so as to meet the static stability requirements of the projectile and reduce the impact caused by the pulse force. The attitude angle oscillation of the projectile has an influence on the control system, and it can also ensure the range and correction accuracy requirements.

Description of drawings

Fig. 1 shows a schematic structural view of a fixed tail missile body in which the vanes of the variable aerodynamic layout structure of the missile body are fixed by sleeves according to a preferred embodiment of the present invention;

Fig. 2 shows a schematic diagram of the structure of a projectile with a variable aerodynamic layout according to a preferred embodiment of the present invention;

Fig. 3 shows a schematic structural diagram of the enlarged tail of the projectile according to the variable aerodynamic layout structure of the projectile according to a preferred embodiment of the present invention;

Fig. 4 shows a schematic diagram of a partial cross-sectional structure of the tail of the projectile according to a preferred embodiment of the present invention with a variable aerodynamic layout structure of the projectile;

Fig. 5 shows a schematic structural diagram of the sleeve restricting fins of the variable aerodynamic layout structure of the projectile according to a preferred embodiment of the present invention

Fig. 6 shows the drag coefficient curve of the fixed empennage aerodynamic layout of the variable aerodynamic layout structure of the projectile according to a preferred embodiment of the present invention;

Fig. 7 shows the drag coefficient curve of the aerodynamic layout of the large empennage;

Fig. 8 shows the simulation curve of the angle of attack of the large empennage aerodynamic layout projectile of the variable aerodynamic layout structure of the projectile according to a preferred embodiment of the present invention;

Fig. 9 shows the identification angle of attack curve of the flight test identification of the aerodynamic layout of the large empennage of the variable aerodynamic layout structure of the projectile according to a preferred embodiment of the present invention.

Explanation of reference numbers:

1- body tail

2-sleeve

3- Locating pin

4-Wing Mount

5-wing

6-pin shaft

7- Explosive device

8-Snorkel

21-air outlet

22-wing limit circle

41-plate groove

Detailed ways

The following describes the present invention in detail, and the features and advantages of the present invention will become more clear and definite along with these descriptions.

The word "exemplary" is used exclusively herein to mean "serving as an example, embodiment, or illustration." Any embodiment described herein as "exemplary" is not necessarily to be construed as superior or better than other embodiments. While various aspects of the embodiments are shown in drawings, the drawings are not necessarily drawn to scale unless specifically indicated.

The front end among the present invention refers to the direction that warhead points, and the rear end is opposite to the front end, and the front end and the rear end are two directions along the axis of the projectile body. As can be seen from Fig. 1 and Fig. 2, the front end refers to the The left side in the figure, the rear end refers to the right side in the figure.

In a preferred embodiment of the variable aerodynamic layout structure of the projectile provided according to the present invention, as shown in Figure 1 or 2, the shape of the projectile tail 1 of the projectile is cylindrical, and a sleeve The barrel 2 is provided with a fin fixing seat 4 at the end of the body tail, and a fin 5 is installed on the fin fixing seat, wherein the sleeve is placed in the middle of the body tail, and the fin fixing seat is located at the At the very end of the tail, there is a certain gap between the sleeve and the fin holder.

In a preferred embodiment, as shown in Fig. 1, Fig. 2, Fig. 3 and Fig. 4, the sleeve is in the shape of a cylinder with two ends open, the sleeve is fixed on the tail of the projectile through the positioning pin 3, and the positioning pin is removed , the sleeve can slide on the tail of the projectile along the axial direction of the projectile, and an air outlet 21 is opened on the wall of the sleeve, and an outwardly protruding fin restricting ring is provided at the rear end of the sleeve, that is, the end far away from the projectile 22; Among them, the sleeve slides forward along the axial direction of the projectile body, and the fin restricting ring is formed by protruding from the tail of the sleeve, integrally formed with the sleeve, and its diameter is larger than that of the sleeve, which is used to fix or restrict the fins .

In a preferred embodiment, as shown in Fig. 1, Fig. 2, Fig. 3, Fig. 4 and Fig. 5, the fins 5 are strip-shaped plates made of metal materials, and a plurality of fins 5 are evenly installed on the spring. Around the body tail, the direction of the plate surface of the fin is perpendicular to the cylindrical surface of the body tail, that is, the axis of the projectile body is located on the plane where the plate surface of the fin is located, and the installation method of the fin is: the rear end of the fin passes through the pin shaft 6 It is fixed on the fin fixing seat of the projectile body, and the front end of the fin is embedded in the fin restricting ring 22 on the sleeve, that is, the fin is fixed on the projectile body through the sleeve and the pin shaft; wherein, the number of fins is preferably Select 6 pieces, each fin is set at an interval of 60°, the front end of the fin is smaller than the rear end, which is convenient to extend into the fin restricting circle 22, if the fin restricting circle 22 does not move, the fin is firmly fixed , will not move.

In a preferred embodiment, as shown in Fig. 1, Fig. 2, Fig. 3 and Fig. 4, an explosive device 7 is arranged inside the body tail 1, fuel is placed in the explosive device, and on the explosive device 7 Connected with a vent pipe 8, the vent pipe 8 is T-shaped, and the other two ends of the vent pipe 8 that are not connected to the explosive device extend into the gap between the sleeve and the tail 1 of the projectile body. It takes a lot of force to break the positioning pin under pressure. Generally, the two outlet ends of the ventilation pipe are placed closer to the positioning pin, so as to break the positioning pin in the shortest time and push the sleeve to slide forward.

In the present invention, the power generated by the explosive device is selected to control the opening of the empennage fins, which has stable performance and high reliability.

In a preferred embodiment, as shown in Fig. 1, Fig. 2, Fig. 3 and Fig. 5, a spring device is sleeved on the outside of the pin shaft, and the spring device includes a torsion spring, and the fin restricting ring 22 locks the fin When the fins press the torsion springs, the torsion springs are charged. When the sleeve moves forward and the front ends of the fins escape from the fin restricting ring 22, the torsion springs drive the fins to rotate around the pin shaft 6; After the rotation stops, the sweep angle of the wings of the fins is 55° to 65°, and the sweep angle of the wings of 60° is preferably selected in the present invention.

In a preferred embodiment, the projectile flight process can be divided into the initial uncontrolled flight stage of the ballistic trajectory and the controlled correction stage at the end of the ballistic trajectory; Time, before launch, the ground command and control system calculates the loading time through the ballistic, and transmits it to the projectile information binder through the cable, and the stapler binds the information to the projectile to be launched. Projectile parameters such as launch angle, initial velocity, etc. are related when launching.

When the missile body is stored and at the initial uncontrolled flight stage of the ballistic trajectory, the locking sleeve fixes the fins, and the missile body is a missile body with a fixed empennage, that is, the aerodynamic layout of the missile body is a fixed empennage aerodynamic layout at this time.

During the flight, when the projectile enters the stage of controlled correction at the end of the ballistic trajectory, the lock sleeve is opened, and the spring device bounces off the wings. The projectile is a projectile with a large tail, that is, the aerodynamic layout of the projectile is a large tail layout.

In a preferred embodiment, the control device of the projectile is based on preset instructions. When the projectile enters the controlled correction stage at the end of the trajectory, the explosive device is ignited, and the high-temperature gas generated is transported to the sleeve and the projectile through the vent pipe. In the gap between the tails, break the positioning pin and push the sleeve to slide forward, that is, to slide toward the front end of the projectile body, the fins will come out from the fin restricting circle, and the high temperature gas generated by the fins will drive the sleeve to slide forward, and then The wings pop up.

In a further preferred embodiment, before the projectile is launched, according to the distance to the target, the time for the projectile to be in the uncontrolled flight stage after launch is determined, and when the uncontrolled flight stage ends, a preset command is issued, through The wings of the control device are deployed, and the projectile body enters the stage of controlled correction. The control instructions in the present invention are stored by the computer system inside the projectile and sent to the control device at a predetermined time.

In a preferred embodiment, the fins can be made in various forms, as long as the fins can spring up when entering the controlled correction stage, it is enough to change the aerodynamic layout structure of the projectile, for example, the fixing of the projectile can be changed. When changing the sweep angle, changing the length and thickness of the fins, etc.

In a preferred embodiment, the installation angle range of the fins relative to the bomb shaft is 2-3°, so as to ensure that the rotational speed of the bomb body is controlled within the range of 5-10 revolutions/s.

In a preferred embodiment, before the flaps bounce up, the spring device is compressed, and when the sleeve releases the flaps, the spring device drives the flaps to bounce up to reach the limit position of the flaps; the spring device in the present invention It can be set on the pin shaft, that is, the main part of the spring device is a torsion spring, and the torsion spring is sleeved on the pin shaft; When the compression spring is compressed between the fins and the body; the spring device can also be arranged behind the fins, that is, the main part of the spring device is a tension spring, which is stretched during storage, and when the lock sleeve is released, The extension spring pulls the wing to rotate, and preferably a torsion spring is used in the present invention.

In a preferred embodiment, a plate groove 41 is provided in the middle of the fin fixing seat for the fin to extend into, and the pin shaft passes through the plate groove and the through hole on the fin to connect the fin fixing seat and the fin as a whole.

In a preferred embodiment, the diameter of the part of the missile tail 1 inside the sleeve is smaller than the diameter of other parts of the missile tail, so that the gap between the sleeve and the missile tail is larger.

In a preferred embodiment, there are two positioning pins 3 in common, and the two positioning pins are arranged symmetrically. The positioning pins 3 are made of aluminum material, which is easy to break.

In the present invention, during the initial uncontrolled flight stage of the ballistic trajectory, the fins are locked. At this time, the missile body is an aerodynamic layout missile body with a fixed empennage. The static stability of the missile body is 15%, and the drag coefficient varies with the angle of attack and the Mach number. As shown in Figure 6, the drag coefficient of the large tail aerodynamic layout projectile with the same structure varies with the attack angle and Mach number as shown in Figure 7. It can be seen that the aerodynamic layout of the fixed tail in the uncontrolled flight stage can not only ensure the The flight of the body is stable, and the resistance can be reduced to improve the range; the large tail aerodynamic layout projectile with the same structure means that the overall structure of the projectile is compared with the aerodynamic layout projectile with the above-mentioned fixed tail, only the tail structure is different, and other structures same.

In the present invention, during the controlled correction stage at the end of the ballistic trajectory, the wings are unfolded, and the projectile body becomes a projectile body with a large tail aerodynamic layout. The six-degree-of-freedom model of the projectile is used for simulation, and the controlled projectile with a large tail aerodynamic layout is The simulation curve of the angle of attack in the correction stage is shown in Figure 8. It can be seen from the figure that after a single pulse force is applied, the resulting angle of attack is small; due to the increase in static stability, the angle of attack converges faster, and the next pulse engine ignition When , the angle of attack converges to the allowable range of the control system, that is, within 2°, which meets the control requirements.

Through the identification of the flight test data of the controlled missile, the angle-of-attack curve of the flight test identification of the controlled missile with the aerodynamic layout of the large tail in the correction stage is obtained. As shown in Figure 9, the missile with the aerodynamic layout of the fixed tail cannot meet the terminal correction requirements The required static stability and dynamic characteristic parameters; according to the control requirements of the controlled correction stage, through the simulation calculation of the control system, the static stability of the projectile should be greater than 30%. The aerodynamic layout of the large tail increases the static stability of the projectile, and the static stability The degree is about 35%. The results of mathematical simulation and flight test data identification fully demonstrate that the airframe with large tail fin aerodynamic layout can meet the control requirements in the control correction stage.

The aerodynamic layout described in the present invention refers to the empennage design position or the form of missile body, and variable aerodynamic layout refers to the empennage design form that can change missile body; Angle of attack refers to the projection of velocity vector V on the longitudinal symmetry plane and missile The angle between the longitudinal axes; the static stability of the projectile refers to the ratio of the distance from the aerodynamic center to the center of gravity of the projectile to the projectile length. Generally, the static stability of the aerodynamic center is positive after the center of gravity; the Mach number refers to a point in the flow field The ratio of the speed of , to the local speed of sound at that point.

The present invention has been described in detail above in conjunction with specific implementations and exemplary examples, but these descriptions should not be construed as limiting the present invention. Those skilled in the art understand that without departing from the spirit and scope of the present invention, various equivalent replacements, modifications or improvements can be made to the technical solutions and implementations of the present invention, all of which fall within the scope of the present invention. The protection scope of the present invention shall be determined by the appended claims.

Claims (9)

1. the variable aerodynamic arrangement structure of body, it is characterized in that, afterbody (1) profile of this body is cylindric, sleeve (2) is had at afterbody overcoat, the end of afterbody (1) is provided with fin holder (4), fin holder (4) is provided with fin (5)

Described sleeve is the tubular of both ends open, sleeve (2) is fixed on afterbody (1) by alignment pin (3), remove alignment pin (3), sleeve can slide on afterbody along elastomer axis direction, sleeve (2) barrel offers venthole (21), is namely provided with outwardly fin circle band (22) away from one end of bullet in sleeve rear end;

The stripe board that described fin (5) is made for metal material, multiple fin (5) is installed on afterbody (1) around equably, the direction, plate face of fin (5) and the cylinder of afterbody perpendicular, namely body axle center is positioned in the plane at place, plate face of fin, the mounting means of fin is: fin rear end is fixed on the fin holder (4) of body by bearing pin (6), fin front end is embedded in the fin circle band (22) on sleeve, is namely fixed on body by sleeve and bearing pin by fin;

The inside of afterbody (1) is provided with fiery device (7), fuel is placed in described fiery device (7), fiery device (7) is connected with breather pipe (8), described breather pipe (8) is T-shaped, and the other two ends that breather pipe (8) is not connected with fiery device extend in the space between sleeve and afterbody (1);

Wherein, spring assembly is provided with in bearing pin outer cover, described spring assembly comprises torsionspring, during fin circle band (22) locking tabs, fin compressing turns torsion spring, makes torsionspring store power, when sleeve moves forward, when fin front end is deviate from fin circle band (22), torsionspring drives fin to rotate around bearing pin (6); After described rotation stops, the missile wing angle of sweep of fin is 55 ° ~ 65 °;

The nothing control mission phase that projectile flight process can be divided into trajectory initial and having of Trajectory-terminal control the correction stage;

Body when storing and trajectory initial without control mission phase time, sleeve fixed tab, body is the fixing body of empennage, and namely now the aerodynamic arrangement of body is fixing empennage aerodynamic arrangement;

Body in flight course, enter Trajectory-terminal have control the correction stage time, sleeve slides forward, fin flicks by spring assembly, and body is the body of large empennage, and namely now the aerodynamic arrangement of body is large empennage aerodynamic arrangement.

2. the variable aerodynamic arrangement structure of body according to claim 1, it is characterized in that, body enter Trajectory-terminal have control the correction stage time, fiery device igniting, the high-temperature gas produced is delivered in the space between sleeve and afterbody (1) through breather pipe, fracture alignment pin (3) promote sleeve slides forward and namely slide towards extreme direction before body, and fin is deviate from fin circle band (22), and fin (5) is upspring.

3. the variable aerodynamic arrangement structure of body according to claim 1, it is characterized in that, in projectile flight process, the time point in control correction stage that has entering Trajectory-terminal is journey ETL estimated time of loading, ground Combat Command System draws journey ETL estimated time of loading according to ballistic computation, and passing to body information attachment means, information is passed to armed body by body information attachment means.

4. the variable aerodynamic arrangement structure of body according to claim 1, is characterized in that, when body is with the control correction stage and forms large empennage body structure, missile wing angle of sweep is 60 °.

5. the variable aerodynamic arrangement structure of body according to claim 1, is characterized in that, the established angle scope that fin plays axle is relatively 2 ° ~ 3 °, to ensure body rotating speed to control within the scope of 5 ~ 10 turns/s.

6. the variable aerodynamic arrangement structure of body according to claim 1, it is characterized in that, fin holder (4) middle part is provided with the board slot (41) stretched into for fin (5), and fin holder (4) and fin (5) connect as one through the through hole on board slot and fin (5) by bearing pin (6).

7. the variable aerodynamic arrangement structure of body according to claim 1, is characterized in that, fin (5) shares six, the setting of 60 °, each fin interval.

8. the variable aerodynamic arrangement structure of body according to claim 1, is characterized in that, the diameter that afterbody (1) is positioned at the part of sleeve is less than the diameter of afterbody (1) other parts.

9. the variable aerodynamic arrangement structure of body according to claim 1, is characterized in that, alignment pin (3) has two, and alignment pin (3) is made up of aluminum material, is easy to fracture.