CN113670139B

CN113670139B - Rotation reducing device for guided projectile and tail of guided projectile

Info

Publication number: CN113670139B
Application number: CN202110882354.3A
Authority: CN
Inventors: 王良明; 付梦印; 苏中; 刘宁; 邓志红; 沈凯; 刘福朝
Original assignee: Nanjing University of Science and Technology; Beijing Institute of Technology BIT; Beijing Information Science and Technology University
Current assignee: Nanjing University of Science and Technology; Beijing Institute of Technology BIT; Beijing Information Science and Technology University
Priority date: 2021-08-02
Filing date: 2021-08-02
Publication date: 2022-08-16
Anticipated expiration: 2041-08-02
Also published as: CN113670139A

Abstract

The invention provides a rotation reducing device for a guided projectile and a guided projectile stern. The rotation reducing device for guided cannonball comprises: the base is connected with a stern shell of the guided projectile; the wing pieces are arranged on one side of the base, which faces away from the stern shell, at even intervals around the axis of the base, and the wing pieces are movably arranged relative to the base in the radial direction of the base, so that the wing pieces are provided with a first position close to the axis of the base and a second position far away from the axis of the base. The rotation reducing device for the guided projectile in the technical scheme can effectively reduce the rotation of the guided projectile in a high-speed rotation state.

Description

Rotation reducing device for guided projectile and tail of guided projectile

Technical Field

The invention relates to the technical field of guided projectiles, in particular to a rotation reducing device for guided projectiles and a guided projectile stern.

Background

Compared with the conventional cannonball, the guided cannonball has the advantages of first shooting hit, high cost effectiveness ratio, capability of dealing with static and moving targets and the like; compared with the missile with a complex launching and guiding system, the guided missile has a simpler launching platform and a simpler guiding mechanism, and has lower price and better guiding precision. The guidance of the cannonball becomes a necessary means for improving the hitting precision of the cannonball, and the premise of accurate hitting is provided. The key point of the guided projectile capable of realizing accurate striking is to accurately acquire the posture of the projectile in real time. The measurement of motion parameters of the guided projectile in the flying process has important significance on pneumatic parameter identification, outer ballistic characteristic research, guidance system design and the like of the projectile, and the measurement of the motion parameters of the projectile with high rotating speed has many difficulties.

The rotating speed of the cannonball launched by the barrel is usually more than 30 revolutions per second, and the control parameters meeting the requirement of guidance control are difficult to obtain by the prior art means. The roll angle rate of the guided projectile can reach hundreds of revolutions per second, which causes great difficulty in real-time measurement of the movement parameters of the projectile body, so that the movement parameter measurement of the guided projectile at high rotating speed is one of bottlenecks seriously restricting the guidance of the projectile, and a device capable of reducing the rotation of the guided projectile is urgently needed to be researched.

In the prior art, the modes for reducing the rotating speed of the cannonball comprise: (1) increasing a sliding type missile belt to reduce the rotating speed of a muzzle and increasing a rudder wing to further reduce the rotation in the middle section of an outer trajectory; (2) the sliding type gas-closing ring is arranged, so that the rotating speed of a projectile body can be reduced under the action of the sliding type gas-closing ring when ammunition is launched. The rotation reducing device has low rotation reducing effect on the guided cannonball in a high-speed rotation state.

Disclosure of Invention

The invention mainly aims to provide a rotation reducing device for a guided projectile and a guided projectile stern, wherein the rotation reducing device for the guided projectile can effectively reduce the rotation of the guided projectile in a high-speed rotation state.

In order to achieve the above object, according to an aspect of the present invention, there is provided a rotation reducing device for a guided projectile, including: the base is connected with a stern shell of the guided projectile; the wing pieces are arranged on one side of the base, which faces away from the stern shell, at even intervals around the axis of the base, and the wing pieces are movably arranged relative to the base in the radial direction of the base, so that the wing pieces are provided with a first position close to the axis of the base and a second position far away from the axis of the base.

Further, the rotation reducing device for the guided projectile further comprises a plurality of mounting seats corresponding to the fins, the mounting seats and the fins are located on the same side of the base, each mounting seat comprises a body and a mounting groove penetrating through the body, the body is connected with the base, part of the fins are located in the mounting groove, and the fins are slidably arranged in the mounting groove.

Further, the fin includes the main part and sets up in the slider of one side of main part, and the mount pad still includes the spout that corresponds the setting with the slider, spout and mounting groove intercommunication, slider and spout sliding fit.

Further, the mount pad still includes the locating part that sets up in the body, and the locating part is located the one side of keeping away from the axis of base of spout to prevent that the fin from deviating from in the mounting groove.

Further, be equipped with the installation through-hole on the base, the guidance shell is with subtracting rotary device still include with installation through-hole complex close the gas lid, a plurality of fins set up around closing the gas lid interval, close one side of gas lid towards the base and be equipped with the draw-in groove, the one end of the axis that is close to the base of the main part of fin is equipped with the buckle, when the fin is in the primary importance, buckle and draw-in groove joint cooperation.

Further, the air-tight cover includes: the cover body is matched with the mounting through hole; a connection part connected with the cover body; the sleeve is located the periphery of part lid, and telescopic one end is connected with connecting portion, and the sleeve passes through connecting portion and is connected with the lid, has the interval between the internal face of sleeve and the outer wall of lid, and the interval forms the draw-in groove.

Further, be equipped with the first pinhole with the mounting groove intercommunication on the body, first pinhole is located the one end of keeping away from the axis of base of body, and has the contained angle between the central axis of first pinhole and the direction of lining up of mounting groove, and the guidance shell is with subtracting rotary device still including setting up the round pin axle in first pinhole, and the fin is still including setting up the second pinhole in the main part of fin, and when the fin was in the second position, the second pinhole can with round pin axle cooperation.

Further, the fin still includes the guiding groove of setting on the main part, and the guiding groove communicates with the second pinhole, and round pin axle sets up for the guiding groove slidable, and along the direction that is close to the second pinhole, the degree of depth size of guiding groove reduces gradually.

Furthermore, the main body is provided with a first side surface, a second side surface and a guide surface for connecting the first side surface and the second side surface, the guide surface comprises a plurality of inclined surfaces which are sequentially connected, an included angle is formed between every two adjacent inclined surfaces, the sliding block is arranged on the first side surface, and the included angle between the first side surface and the adjacent inclined surfaces is an obtuse angle; or, the slider is U type structure, and the slider includes two slider bodies that set up relatively and is used for connecting the linkage segment of two slider bodies, and two slider bodies are located the relative both sides of main part respectively, and the mount pad includes two spouts that correspond the setting with two slider bodies.

According to another aspect of the invention, there is provided a guided projectile stern comprising a stern shell and a rotation reducing device for guided projectiles as described above arranged on the stern shell.

By applying the technical scheme of the invention, the plurality of fins are arranged on the base connected with the tail of the shell and can move along the radial direction of the base, so that after the shot is taken out of the chamber, under the action of a centrifugal force at a high rotating speed, the fins can move along the radial direction of the base and towards the direction far away from the axis of the base, namely the fins can be switched from the first position to the second position, so that part of the fins are popped out of the base, and in the rotating process of the fins, air can generate larger resistance to the fins, so that rolling resistance torque is formed under the action of air resistance, the fins are prevented from rotating, the rotating speed of the guided shell can be further reduced, and thus, the rotation reducing device can effectively perform transient rotation reduction on the guided shell in a high-speed rotating state, so that the motion parameters of the guided shell can be measured and controlled more easily.

Drawings

The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:

FIG. 1 shows a schematic structural view of a rotation reducing apparatus for a guided munition according to an embodiment of the invention;

FIG. 2 shows a schematic structural view of a mounting block of the rotation reducing apparatus for a guided munition of FIG. 1;

FIG. 3 shows a structural schematic view of one direction of fins of the de-rotation apparatus for a guided munition of FIG. 1;

FIG. 4 is a structural schematic view showing another direction of the fins of the de-rotation apparatus for a guided munition of FIG. 1;

figure 5 shows a schematic view of the gas-containment cap of the rotation reduction apparatus for a guided munition of figure 1.

Wherein the figures include the following reference numerals:

10. a stern shell; 20. a base; 30. a fin; 31. a main body; 311. a first side surface; 312. a second side surface; 313. a guide surface; 32. a slider; 33. buckling; 34. a second pin hole; 35. a guide groove; 40. a mounting seat; 41. a body; 42. mounting grooves; 43. a chute; 44. a limiting member; 45. a first pin hole; 50. an airtight cover; 51. a card slot; 52. a cover body; 53. a connecting portion; 54. a sleeve.

Detailed Description

It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.

The spin reduction known to the inventors also includes: (1) the navigation system and the projectile body are isolated by the rolling isolation mechanism, the navigation system and the projectile body can rotate relatively, the relative rotation rate is controllable, the projectile body maintains a high-rotation-speed state, and the navigation system does not roll along with the projectile body, so that the problem of direct measurement of the movement parameters of the projectile body is solved; (2) the semi-strapdown inertial measurement unit is used for measuring the motion parameters, and the mechanical rotation reducing structure is used to prevent the rolling shaft of the measurement unit from rotating at high speed along with the carrier, so that the influence of the implanted rotation on the measurement precision of the motion parameters is avoided.

The rotation reducing device related to the rotation reducing mode is complex in structure, large in modification to the projectile and high in manufacturing cost, and rotation reduction of the novel guided projectile is not facilitated. Therefore, the invention provides the rotation reducing device for the guided projectile, which has the advantages of simple structure, convenience in processing and obvious rotation reducing effect.

The rotation reduction fin according to the embodiment of the present invention is not operated by other power devices or power sources, but is operated by centrifugal force generated when the guided projectile rotates at high speed.

It is noted that as shown in fig. 1, the stern of the guided projectile generally comprises a stern shell 10 and a tail cover connected to the stern shell 10, and the base 20 of the embodiment of the present invention is the tail cover.

As shown in fig. 1, an embodiment of the present invention provides a spin reduction apparatus for guided munitions. The de-rotation device includes a base 20 and a plurality of fins 30. Wherein the base 20 is connected with the stern shell of the guided projectile; a plurality of fins 30 are provided on the side of the base 20 facing away from the stern shell, the plurality of fins 30 being evenly spaced about the axis of the base 20, the fins 30 being movably arranged relative to the base 20 in a radial direction of the base 20 such that the fins 30 have a first position close to the axis of the base 20 and a second position remote from the axis of the base 20.

In the above technical solution, by providing a plurality of fins 30 on the base 20 connected with the tail of the shell, and the plurality of fins 30 are each movable in a radial direction of the base 20, so that, after the projectile is discharged, under the centrifugal force at high rotation speed, the fins 30 will move in the radial direction of the base 20 and in the direction away from the axis of the base 20, i.e., the flap 30, can be switched from the first position to the second position, so that a portion of the flap 30 is ejected from the base 20, during rotation of the airfoil 30, the air may provide a greater resistance to the airfoil 30, thereby creating a roll resistance torque under the air resistance, preventing the airfoil 30 from rotating, and further, the rotation speed of the guided cannonball can be reduced, so that the rotation reducing device can effectively carry out transient rotation reduction on the guided cannonball in a high-speed rotation state, and the motion parameters of the guided cannonball can be measured and controlled easily.

Specifically, in the embodiment of the present invention, the plurality of fins 30 are evenly spaced about the axis of the base 20, so that the plurality of fins 30 can be subjected to even air resistance to avoid an unbalanced condition of the guided projectile.

Preferably, in the embodiment of the present invention, the number of the fins 30 is four, four fins 30 are arranged on the base 20 in a cross shape, and an included angle between each two fins among the four fins is 90 °. Of course, in alternative embodiments not shown in the drawings, the number of fins 30 may also be five or six, etc.

Preferably, in an embodiment of the present invention, the fins 30 are made of a titanium alloy sheet material having good ductility and high fatigue resistance. Therefore, the fins 30 can resist tensile fracture and low-stress brittle fracture under the action of high rotating speed and centrifugal force, and have high reliability.

As shown in fig. 1 and 2, in the embodiment of the invention, the rotation reducing device for guided cannonball further comprises a plurality of mounting seats 40 corresponding to the plurality of fins 30, the mounting seats 40 and the fins 30 are positioned on the same side of the base 20, the mounting seats 40 comprise a body 41 and mounting grooves 42 penetrating the body 41, the body 41 is connected with the base 20, part of the fins 30 are positioned in the mounting grooves 42, and the fins 30 are slidably arranged in the mounting grooves 42.

With the above arrangement, the fin 30 can be mounted on the end surface of the base 20 through the mounting seat 40, and the fin 30 can be slidably arranged in the mounting groove 42, so that the fin 30 can move relative to the base 20 along the radial direction of the base 20, and the fin 30 can be switched from the first position to the second position to derotation the guided projectile.

Further, the mounting seat 40 functions to fix the wing 30 and transmit the torque to the base 20, thereby achieving the torque reduction effect of the whole device.

Specifically, in the embodiment of the present invention, the mounting seat 40 is fixed to the base 20 by a countersunk head screw.

As shown in fig. 2 and 3, in the embodiment of the present invention, the wing 30 includes a main body 31 and a sliding block 32 disposed on the main body 31, the sliding block 32 is disposed on one side of the main body 31, the mounting seat 40 further includes a sliding groove 43 disposed corresponding to the sliding block 32, the sliding groove 43 is communicated with the mounting groove 42, and the sliding block 32 is in sliding fit with the sliding groove 43.

In the above technical solution, by providing the sliding block 32 and the sliding groove 43 in sliding fit, the fin 30 can move more smoothly along the extending direction of the mounting seat 40.

Further, the sliding groove 43 can limit the movement of the slider 32 in the up-down direction in fig. 2 to prevent the wing 30 from shaking in the up-down direction in fig. 1, and the sliding groove 43 can limit the movement of the slider 32 in the left-right direction in fig. 2 to prevent the wing 30 from shaking in the circumferential direction of the base 20 in fig. 1.

As shown in fig. 1 and fig. 2, in the embodiment of the invention, the mounting seat 40 further includes a limiting member 44 disposed on the body 41, and the limiting member 44 is located on one side of the sliding slot 43 away from the axis of the base 20 to prevent the wing 30 from coming out of the mounting slot 42.

With the above arrangement, when the wing 30 is acted by centrifugal force and moves along the radial direction of the base 20 and to a position far away from the center of the base 20, the limiting member 44 can limit the limit position of the slider 32, that is, when the wing 30 is at the second position, the limiting member 44 abuts against the slider 32 to prevent the wing 30 from being removed from the mounting groove 42.

It should be noted that, as shown in fig. 1, in the embodiment of the present invention, the sliding groove 43 does not extend through the body 41, and one end of the sliding groove 43 is closed, so that a limiting member 44 can be formed, thereby preventing the wing 30 from coming out of the mounting groove 42.

As shown in fig. 1, 3 and 5, in the embodiment of the present invention, a mounting through hole is provided on the base 20, the rotation reducing device for a guided projectile further includes an air-tight cover 50 engaged with the mounting through hole, a plurality of fins 30 are spaced around the air-tight cover 50, a locking groove 51 is provided on a side of the air-tight cover 50 facing the base 20, a locking buckle 33 is provided on an end of the main body 31 of the fin 30 close to the axis of the base 20, and the locking buckle 33 is engaged with the locking groove 51 when the fin 30 is in the first position.

Through the above arrangement, when the ammunition is not launched, the buckle 33 is matched with the clamping groove 51 in a clamping manner, the wing 30 can be limited at the first position, then the guided ammunition is discharged from the chamber, and the air closing cover 50 is separated from the base 20 under the action of the engine, so that the slide block 32 on the wing 30 can slide outwards along the sliding groove 43 and be thrown out until the slide block moves to the second position under the action of high-speed centrifugal force, and the wing 30 at the second position generates rolling resistance torque under the action of radial air resistance, thereby achieving the effect of rotation reduction.

As shown in fig. 5, in the embodiment of the present invention, the air closing cap 50 includes a cap body 52, a connecting portion 53, and a sleeve 54. The cover 52 is fitted with the mounting through-hole; the connecting portion 53 is connected to the lid 52; the sleeve 54 is located on the outer periphery of a part of the cover 52, one end of the sleeve 54 is connected to the connecting portion 53, the sleeve 54 is connected to the cover 52 through the connecting portion 53, and the inner wall surface of the sleeve 54 and the outer wall surface of the cover 52 are spaced to form the engaging groove 51.

With the above arrangement, the annular catch 51 may be formed such that the plurality of catches 33 of the plurality of tabs 30 spaced around the airtight cover 50 may each cooperate with the catch 51 to lock the plurality of tabs 30 in the first position.

In the embodiment of the invention, as shown in fig. 2 and 3, the body 41 is provided with a first pin hole 45 communicated with the mounting groove 42, the first pin hole 45 is positioned at one end of the body 41 far away from the axis of the base 20, an included angle is formed between the central axis of the first pin hole 45 and the penetrating direction of the mounting groove 42, the rotation reducing device for the guided cannonball further comprises a pin shaft arranged in the first pin hole 45, the fin 30 further comprises a second pin hole 34 arranged on the main body 31 of the fin 30, and when the fin 30 is in the second position, the second pin hole 34 can be matched with the pin shaft.

Through the arrangement, under the action of high-speed centrifugal force, the sliding block 32 on the wing 30 can slide outwards along the sliding groove 43 until the sliding block moves to the second position, and the pin shaft can be matched with the second pin hole 34, so that the wing 30 can be locked at the second position, the wing 30 is prevented from shaking when being positioned at the second position, the formation of rolling resistance torque is influenced, and the wing 30 can enter into a rotation reduction working state.

As shown in fig. 3, in the embodiment of the present invention, the wing 30 further includes a guide groove 35 provided on the main body 31, the guide groove 35 communicates with the second pin hole 34, the pin shaft is slidably provided with respect to the guide groove 35, and the depth dimension of the guide groove 35 is gradually reduced in a direction approaching the second pin hole 34.

Through the above arrangement, the guide groove 35 can provide a guide function for the pin shaft, so that the pin shaft can slide more smoothly relative to the wing 30.

Specifically, in the embodiment of the present invention, the depth of the guide groove 35 gradually decreases from the left side to the right side in fig. 3, so that when the pin moves along the guide groove 35, the distance between the pin and the bottom wall of the guide groove 35 gradually decreases until the pin moves to the position where the second pin hole 34 is located and then fits with the second pin hole 34.

As shown in fig. 3 and 4, in the embodiment of the present invention, the main body 31 has a first side 311, a second side 312 and a guide surface 313 for connecting the first side 311 and the second side 312, the guide surface 313 includes a plurality of inclined surfaces connected in sequence, and an included angle is formed between two adjacent inclined surfaces, the slider 32 is disposed on the first side 311, and the included angle between the first side 311 and the adjacent inclined surfaces is an obtuse angle.

With the above arrangement, when the fins 30 are in the second position and the fins 30 can provide a sufficient radial resistance moment, the airflow flowing in the axial direction of the guided projectile can flow along the guide surfaces 313, so that the axial air resistance generated by the fins 30 can be reduced to avoid affecting the range of the guided projectile and provide a suitable low-speed working environment for the measuring device of the guided projectile.

Further, as shown in fig. 3, the included angle between the first side 311 and the adjacent inclined surface is an obtuse angle, so that the guide surface 313 may be inclined upward to perform a flow guiding function.

It should be noted that, in the embodiment of the present invention, the rotation reducing effect of the wing 30 is related to the rotation reducing torque, and the factors influencing the rotation reducing torque are mainly the length of the wing 30 and the shape of the wing 30.

Specifically, the airfoil 30 of the present embodiment is of sufficient length to provide sufficient radial resistance torque and yet the strength of the airfoil 30 is satisfactory without failure.

Preferably, as shown in fig. 3, in an embodiment of the present invention, the fins 30 may have an irregular trapezoidal structure.

As shown in fig. 4, in the embodiment of the present invention, the sliding block 32 is a U-shaped structure, the sliding block 32 includes two sliding block bodies disposed oppositely and a connecting section for connecting the two sliding block bodies, the two sliding block bodies are respectively located at two opposite sides of the main body 31, and the mounting seat 40 includes two sliding grooves 43 disposed correspondingly to the two sliding block bodies.

Among the above-mentioned technical scheme, through setting up two slider bodies and two spouts 43 corresponding with two slider bodies, like this, can make fin 30 slide in mounting groove 42 more smoothly.

As shown in fig. 1, an embodiment of the invention provides a guided projectile stern. The stern of the guided cannonball comprises a stern shell and the rotation reducing device for the guided cannonball, which is arranged on the stern shell. The stern of the guided projectile has all the advantages of the rotation reducing device, and the description is omitted.

From the above description, it can be seen that the above-described embodiments of the present invention achieve the following technical effects: through set up a plurality of fins on the base of being connected with the shell stern, and a plurality of fins all can be along the radial displacement of base, like this, after the shot goes out the thorax, under the centrifugal force effect of high rotational speed, the fin can be along the radial of base and to the direction removal of the axis of keeping away from the base, the fin can be switched into the second position by first position promptly, so that partial fin pops out the base, in the rotatory in-process of fin, the air can produce great resistance to the fin, thereby form roll resistance moment under the effect of air resistance, in order to prevent the fin rotation, and then can make the guidance shell reduce the rotational speed, like this, the derotation device can carry out the transient derotation to the guidance shell under the high-speed rotation state effectively, so that the motion parameter of guidance shell can be easier measurement and control.

The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. A spin reduction apparatus for guided munitions, comprising:

a base (20) connected to the stern shell of the guided projectile;

a plurality of fins (30) arranged on a side of the base (20) facing away from the stern shell, the plurality of fins (30) being arranged at regular intervals around the axis of the base (20), the fins (30) being movably arranged relative to the base (20) in a radial direction of the base (20) such that the fins (30) have a first position close to the axis of the base (20) and a second position away from the axis of the base (20);

the mounting seats (40) are arranged corresponding to the fins (30), the mounting seats (40) and the fins (30) are positioned on the same side of the base (20), each mounting seat (40) comprises a body (41) and a mounting groove (42) penetrating through the body (41), the body (41) is connected with the base (20), part of the fins (30) are positioned in the mounting grooves (42), and the fins (30) are slidably arranged in the mounting grooves (42);

the wing piece (30) comprises a main body (31) and a sliding block (32) arranged on one side of the main body (31), the mounting seat (40) further comprises a sliding groove (43) correspondingly arranged with the sliding block (32), the sliding groove (43) is communicated with the mounting groove (42), and the sliding block (32) is in sliding fit with the sliding groove (43);

the mounting seat (40) further comprises a limiting piece (44) arranged on the body (41), and the limiting piece (44) is positioned on one side of the sliding groove (43) far away from the axis of the base (20) so as to prevent the wing piece (30) from being separated from the mounting groove (42);

the rotary reduction device for the guided cartridge is characterized in that a mounting through hole is formed in the base (20), the rotary reduction device further comprises an air-blocking cover (50) matched with the mounting through hole, the fins (30) are arranged around the air-blocking cover (50) at intervals, a clamping groove (51) is formed in one side, facing the base (20), of the air-blocking cover (50), a buckle (33) is arranged at one end, close to the axis of the base (20), of a main body (31) of each fin (30), and when the fins (30) are located at the first position, the buckle (33) is in clamping fit with the clamping groove (51);

the airtight cover (50) includes:

a cover (52) fitted with the mounting through-hole;

a connecting portion (53) connected to the lid (52);

the sleeve (54) is positioned on the periphery of part of the cover body (52), one end of the sleeve (54) is connected with the connecting part (53), the sleeve (54) is connected with the cover body (52) through the connecting part (53), a gap is formed between the inner wall surface of the sleeve (54) and the outer wall surface of the cover body (52), and the gap forms the clamping groove (51).

2. A rotation reducing device for a guided projectile as claimed in claim 1, wherein the body (41) is provided with a first pin hole (45) communicating with the mounting groove (42), the first pin hole (45) is located at an end of the body (41) remote from the axis of the base (20) and an included angle is formed between a central axis of the first pin hole (45) and a penetrating direction of the mounting groove (42), the rotation reducing device for a guided projectile further comprises a pin shaft disposed in the first pin hole (45), the fin (30) further comprises a second pin hole (34) disposed in the main body (31) of the fin (30), and the second pin hole (34) is capable of being engaged with the pin shaft when the fin (30) is in the second position.

3. The rotation reducing apparatus for guided projectiles of claim 2 wherein the fin (30) further comprises a guide groove (35) provided in the body (31), the guide groove (35) communicating with the second pin hole (34), the pin being slidably disposed with respect to the guide groove (35), the guide groove (35) having a depth dimension that gradually decreases in a direction approaching the second pin hole (34).

4. The rotation reducing device for guided projectiles of any one of claims 1 to 3, wherein the body (31) has a first side surface (311), a second side surface (312) and a guide surface (313) for connecting the first side surface (311) and the second side surface (312), the guide surface (313) comprises a plurality of inclined surfaces which are connected in sequence, and an included angle is formed between two adjacent inclined surfaces, the slider (32) is arranged on the first side surface (311), and the included angle between the first side surface (311) and the adjacent inclined surfaces is an obtuse angle; or, slider (32) are U type structure, slider (32) including two slider bodies that relative setting with be used for connecting two the linkage segment of slider body, two slider body is located respectively the relative both sides of main part (31), mount pad (40) include with two slider body corresponds two the spout (43) that sets up.

5. A guided projectile stern, characterized by comprising a stern shell (10) and a rotation reducing device for guided projectiles as claimed in any one of claims 1 to 4 provided to said stern shell (10).