CN114136157A

CN114136157A - Guidance projectile body that 40mm rocket tube sought with general strapdown

Info

Publication number: CN114136157A
Application number: CN202010918753.6A
Authority: CN
Inventors: 郝渊; 蒋军
Original assignee: Beijing Hengxing Jianxiang Technology Co ltd
Current assignee: Beijing Hengxing Jianxiang Technology Co ltd
Priority date: 2020-09-04
Filing date: 2020-09-04
Publication date: 2022-03-04

Abstract

The invention provides a universal strapdown target-seeking guidance projectile body for a 40mm rocket launcher, which comprises a seeker, a war guidance cabin, a rudder cabin, a rotary folding rudder piece, a control cabin, a range extending engine, a flight engine and a tail wing assembly, wherein the seeker is connected with the missile cabin through a connecting piece; the seeker, the missile cabin, the rudder cabin, the control cabin, the range-extending engine, the flight engine and the empennage assembly are sequentially connected to form a guidance projectile body, and the seeker and the range-extending engine are located on the super-caliber section; the rotary folding rudder piece is arranged on the rudder cabin and the position of the rotary folding rudder piece is adjustable; the rotary folding rudder piece is locked at an initial position when being folded, and the rotary folding rudder piece is moved to a short-range operation position or a long-range operation position to be locked after being unfolded; during short-range combat, the range-extended engine does not work; during long-range combat, the control cabin sets the ignition time of the range-extended engine according to the target distance; the control cabin is used for resolving target space position information given by the seeker and generating a control instruction to drive the rotary folding rudder piece so as to control the guided missile body to fly. The invention has high tracking and guidance precision.

Description

Guidance projectile body that 40mm rocket tube sought with general strapdown

Technical Field

The invention relates to the technical field of small-caliber guided munitions, in particular to a universal strapdown seeking guided projectile for a 40mm rocket tube.

Background

Active seeking guidance or semi-active seeking guidance is a main terminal guidance system for realizing high-precision hitting on a medium and long range target by a current guided weapon, and is particularly suitable for hitting a moving target. The seeker for guidance is generally divided into a platform type seeker and a strap-down type seeker. The platform type seeker can directly output the rotation angular velocity of the line of the bullet eyes, and high-precision proportional guidance is achieved. The strapdown seeker is fixedly connected with a projectile body, the rotational angular velocity of a missile line cannot be output under the general condition due to the coupling between the missile body and the attitude of the projectile body during flying, in this case, in order to obtain the rotational angular velocity of the missile line required by proportional guidance, a high-precision inertial navigation system needs to be additionally arranged on the projectile, a mathematical calculation platform is established, and the rotational angular velocity of the missile line is solved by fusing the seeker and inertial navigation information. If the strapdown seeker does not adopt inertial navigation cooperation, a missile tracking guidance law can only be adopted generally, and the guidance law has very high requirements on the overall structure and the pneumatic design for ensuring the guidance precision and must ensure that a missile in closed-loop flight keeps a very small attack angle state.

For the development of a guided rocket for a 40mm rocket tube, low cost is a strict constraint condition, so that a platform type guide head and a high-precision inertial navigation system cannot be used in scheme design. A viable technical approach is to achieve higher precision projectile tracking guidance through high-level overall structural and aerodynamic layout designs. Therefore, the technical scheme of the universal strapdown search projectile body for the 40mm rocket tube is provided.

Disclosure of Invention

In view of the above, the invention provides a universal strapdown seeking guidance projectile for a 40mm rocket launcher, which is high in projectile tracking guidance precision.

The technical scheme adopted by the invention is as follows:

a40 mm rocket launcher is with general guidance projectile body that the strapdown seeks, the said guidance projectile body includes the seeker, draws the war cabin, rudder cabin, rotary folding rudder piece, control cabin, increases journey engine, flight engine and empennage assembly;

the seeker, the missile cabin, the rudder cabin, the control cabin, the range-extending engine, the flight engine and the tail wing assembly are sequentially connected to form a guidance projectile body, and the seeker, the missile cabin, the rudder cabin, the control cabin and the range-extending engine are all positioned on the ultra-caliber section at the front part of the projectile body;

the rotary folding rudder piece is arranged on the rudder cabin and is adjustable in position; the rotating folding rudder sheet is locked at an initial position when being folded, and the rotating folding rudder sheet is moved to a short-range operation position or a long-range operation position to be locked after being unfolded, so that the center of gravity of a rudder surface of a projectile body at the tail end of a flight trajectory and the center of mass of the projectile body are positioned on the same projectile body section;

during short-range combat, the range-extended engine does not work; during long-range combat, the control cabin sets the ignition time of the range-extending engine according to the target distance and provides thrust required by range extension for the guided projectile body;

the control cabin is used for resolving target space position information given by the seeker and generating a control instruction to drive the rotary folding rudder piece so as to control the guided projectile to fly.

Further, a sliding track is arranged on the rudder cabin, and the rotary folding rudder piece moves from an initial position to a short-range operation position or a long-range operation position along the sliding track; the sliding rail is a T-shaped rail, the horizontal rail is parallel to the axis of the projectile body, and the vertical rail is perpendicular to the axis of the projectile body; two ends of the horizontal track are respectively a short-range combat position and a long-range combat position, and the short-range combat position is far away from the head of the projectile body; the end of the vertical rail away from the intersection is the initial position.

Furthermore, the rotary folding rudder piece comprises a rudder surface, a rotating shaft, a set screw, a positioning pin, a jackscrew, a spring I and a moving seat;

the rudder cabin is characterized in that a through hole is axially formed in the moving seat, the top end of the moving seat is used for being connected with a rudder surface, the bottom end of the moving seat is used for being installed in a matched mode with the rudder cabin body, two pairs of fixing grooves with different axial lengths are formed in the inner wall of the top end of the through hole and respectively comprise a pair of long fixing grooves and a pair of short fixing grooves, the two long fixing grooves are oppositely arranged, the two short fixing grooves are oppositely arranged, and an included angle formed by the two adjacent long fixing grooves and the two adjacent short fixing grooves and an axis connecting line is 90 degrees; meanwhile, the upper end of the movable seat is provided with a radial through hole and a groove penetrating through the end part, the open end of the groove is positioned on the end surface of the top end of the movable seat, the top end of the short fixed groove is lower than the bottom end of the groove, and the top end of the long fixed groove is higher than the bottom end of the groove; the radial through hole is used for being matched with the set screw; the jackscrew is arranged inside the bottom end of the through hole of the movable seat;

the control surface is fixed at one end of the rotating shaft, the axial direction of the rotating shaft is parallel to the control surface, the other end of the rotating shaft is matched with the through hole of the moving seat through a positioning pin, the positioning pin is vertical to the axial direction of the moving seat, and a jackscrew arranged at the end part of the other end of the rotating shaft presses the spring I in the through hole of the moving seat;

when the control surface is in a folded state, the rotating shaft is horizontally placed in a groove at the top end of the moving seat, the axis of the rotating shaft is perpendicular to the axis of the moving seat, and meanwhile, the rotating shaft is positioned at the top end of the long fixing groove by the positioning pin under the action of the spring I and is limited by the fastening screw; when the control surface is in the expansion state, the axis of the rotating shaft is parallel to the axis of the movable seat, and the rotating shaft is positioned at the top end of the short fixing groove by the positioning pin under the action of the spring I and is limited by the fastening screw.

Furthermore, an annular boss is arranged on the outer circumference of the movable seat, two blind holes are arranged on the annular boss, and the two blind holes are positioned in the same radial direction; a spring II and a positioning shaft are sequentially arranged in the blind hole from inside to outside; the bottom end of the through hole of the movable seat is connected with the plug screw thread;

the initial position, the short-range combat position or the long-range combat position of the rudder cabin are provided with step through holes communicated with the outside of the cabin body and used for being matched with the blind holes in the movable seat;

when the movable seat is arranged in the mounting groove of the rudder cabin, the outer circumferential surface of the annular boss is in contact with the inner wall surface of the mounting groove; when the rotary folding rudder piece is locked at the initial position, the blind hole is opposite to the step through hole at the initial position of the rudder cabin, the positioning shaft pops out and is limited at the large-diameter part of the blind hole and the step through hole under the action of the spring II, and the rotation of the movable seat is limited by the screw plug to complete the locking; when the rotary folding rudder piece is locked at a short-range operation position or a long-range operation position, the blind hole is opposite to the step through hole of the short-range operation position or the long-range operation position of the rudder cabin, the positioning shaft pops out of the large-diameter part limited by the blind hole and the step through hole under the action of the spring II, and at the moment, the bottom surface of the annular boss is contacted with the bottom surface of the installation groove of the rudder cabin to limit the rotation of the movable seat to complete locking.

Furthermore, the seeker adopts a laser semi-active seeker or a television seeker or an infrared seeker or a millimeter wave seeker.

Has the advantages that:

1. the rudder cabin is arranged on the ultra-caliber projectile body section, and the ultra-caliber projectile body section is not limited by a rocket tube structure, so that the designable control surface is sufficiently large, the position adjustable space of the steering engine is large, and the control surface pressure center and the projectile body mass center are configured on the same projectile body section by adopting the position adjustable control surface, so that the direct lateral force control on the projectile body mass center movement can be realized, and the minimum attack angle in the flight process is ensured; meanwhile, considering that a range-extended engine needs to be added to a medium-long range rocket projectile, and the center of mass of the projectile body changes to a certain extent before and after the engine works, the position-adjustable control surface structure is adopted, in the actual use process, the working ignition time of the range-extended engine on the trajectory can be set according to the target distance, the range-extended engine moves to the short-range operation position or the long-range operation position according to the change rule of the center of mass and is locked, and the center of gravity and the center of mass of the rudder surface of the missile at the tail end of the flight trajectory are strictly on the same projectile body section. Therefore, the action point of the control force of the final guide section on the projectile body is always coincided with the mass center of the projectile body, in the process of generating the control force by deflection of the control surface, the control moment cannot be generated on the projectile body, the bullet axis and the speed direction can keep good consistency, the projectile body flies at a zero attack angle or a very small attack angle, and the flying speed direction of the projectile body is directly changed by the control force in the control process by combining a two-stage engine scheme of a flying engine and a range-extending engine. The precision of the guidance law for tracking the projectile body by adopting the strapdown type seeker is greatly improved, conditions are provided for developing a low-cost high-precision guidance rocket projectile with remote accurate attack on a 40mm rocket launcher platform, and the fighting efficiency of the 40mm rocket launcher platform can be greatly improved.

2. The rotary folding rudder sheet has an ingenious structure, and is easy to fold, unfold and rotate.

3. The universal strapdown seeking guidance projectile body can be used for laser semi-active, television, infrared, millimeter wave and other strapdown guidance heads, and is widely applicable.

Drawings

FIG. 1 is a schematic view of the overall structure of the present invention;

FIG. 2 is a schematic structural view of a slide rail;

FIG. 3(a) is a schematic view showing a structure that a rotary folded rudder blade is locked at an initial position when folded, FIG. 3(b) is a sectional view of FIG. 3(a), and FIG. 3(c) is a partially enlarged view of FIG. 3 (b);

fig. 4(a) is a schematic view showing a state where the swivel-folded rudder blade is prepared to move after being unfolded, fig. 4(b) is a sectional view of fig. 4(a), and fig. 4(c) is a partially enlarged schematic view of fig. 4 (b);

FIG. 5 is a schematic diagram (a) showing a locking state of the unfolded rotary folded rudder sheet, FIG. 5(b) showing a cross-sectional view of FIG. 5(a), and FIG. 5(c) showing a partial enlarged view of FIG. 5 (b);

FIG. 6 is a cross-sectional view of the rotary folding rudder sheet;

FIG. 7 is an exploded view of a three-dimensional structure of a rotary folding rudder sheet;

FIG. 8 is a schematic three-dimensional structure of the movable base;

FIG. 9 is a cross-sectional view of the motion stage;

FIG. 10 is a schematic view of the connection structure of the movable base and the rotary foldable rudder sheet;

wherein, 1-a wind cap, 2-an infrared seeker, 3-a missile cabin, 4-a rotary folding rudder sheet, 5-a sliding track, 6-a rudder cabin, 7-a control cabin, 8-a missile-borne computer, 9-a range-extending engine, 10-a flight engine, 11-a tail rod, 12-a tail wing, 13-a rolling angle measuring device, 14-a missile power supply, 15-an initial position, 16-a short range operation position, 17-a long range operation position, 18-a horizontal track, 19-a vertical track, 20-a plug screw, 21-a positioning shaft, 22-a spring II, 23-a surface, 24-B surface, 25-C surface, 26-D surface, 27-a rudder surface, 28-a rudder surface connecting screw, 29-a rudder shaft and 30-a fixing screw, 31-rotating shaft, 32-positioning pin, 33-top plate, 34-spring I, 35-top thread, 36-moving seat, 37-fastening screw, 38-long fixing groove, 39-groove and 40-short fixing groove.

Detailed Description

The invention is described in detail below by way of example with reference to the accompanying drawings.

The embodiment provides a universal strapdown search guided missile body for a 40mm rocket tube, which comprises a seeker, a missile cabin 3, a rudder cabin 6, a rotary folding rudder 4, a control cabin 7, a range extending engine 9, a flight engine 10 and a tail 12 as shown in figure 1. In addition, the weapon system also comprises a ground guidance instrument.

The components of the seeker, the missile cabin 3, the rudder cabin 6, the control cabin 7, the range-extending engine 9, the flight engine 10 and the empennage 12 are sequentially connected from head to tail to form a guidance projectile body, the rocket projectile body positioned outside the rocket barrel is an ultra-caliber cabin section, and the seeker, the missile cabin 3, the rudder cabin 6, the control cabin 7 and the range-extending engine 9 are all positioned on the ultra-caliber section at the front part of the projectile body.

The infrared seeker 2 is adopted as the seeker, and is used for sensing target radiation, automatically measuring and outputting motion parameters of the target. A laser semi-active seeker or a television seeker or a millimeter wave seeker may also be employed. The outside of the seeker is provided with a hood 1.

The fuse warfare cabin 3 consists of an external shell, a fuse, a security mechanism, a detonating tube and a warhead.

The rudder cabin 6 comprises a transmission mechanism, a motor and a driver, the driver receives a projectile body control instruction given by the control cabin 7 to control the motor to work, and the motor drives the transmission mechanism to drive the rudder piece to act to generate control force and control torque, so that the rocket projectile flies to a target.

As shown in fig. 6 and 7, the rotary foldable rudder sheet 4 includes a rudder surface 27, a rudder surface connecting screw 28, a rudder shaft 29, a fixing screw 30, a rotating shaft 31, a set screw 37, a positioning pin 32, a top plate 33, a top thread 35, a spring i 34, a spring ii 22, a positioning shaft 21 and a movable base 36.

A through hole is axially formed in the movable seat 36, the top end of the movable seat 36 is used for being connected with the control surface 27, the bottom end of the movable seat is used for being installed in a matching mode with a mounting groove of the rudder cabin 6, as shown in fig. 8 and 9, two pairs of fixing grooves with different axial lengths are formed in the inner wall of the top end of the through hole, namely a pair of long fixing grooves 38 and a pair of short fixing grooves 40, and are correspondingly folded and unfolded, the two long fixing grooves 38 are oppositely arranged, the two short fixing grooves 40 are oppositely arranged, and an included angle formed by the connecting line of the two adjacent long fixing grooves 38 and the short fixing grooves 40 and the axis is 90 degrees; meanwhile, the upper end of the movable seat 36 is provided with a radial through hole and a groove 39 penetrating through the end part, the open end of the groove 39 is positioned on the end surface of the top end of the movable seat 36, the top end of the short fixing groove 40 is lower than the bottom end of the groove 39, and the top end of the long fixing groove 38 is higher than the bottom end of the groove 39; the radial through hole is intended to cooperate with a set screw 37; in a preferred embodiment, a radial through hole is provided above the short fixation groove 40, the groove 39 being opposite to the radial through hole.

An annular boss is arranged on the outer circumference of the movable seat 36, two blind holes are arranged on the annular boss, and the two blind holes are positioned in the same radial direction; a spring II 22 and a positioning shaft 21 are sequentially arranged in the blind hole from inside to outside. The internal portion of the bottom end of the through hole of the movable seat 36 is provided with a jackscrew 35, and the bottom end of the through hole is in threaded connection with the plug screw 20.

The rudder shaft 29 is of a U-shaped fork structure, the rudder surface 27 is fixed at the opening end of the U-shaped fork through a rudder surface connecting screw 28, the closed end of the U-shaped fork is fixedly connected with one end of a rotating shaft 31 through a fixing screw 30, the axial direction of the fixing screw 30 is parallel to the axial direction of the rotating shaft 31, the axial direction of the rotating shaft 31 is parallel to the rudder surface 27, the other end of the rotating shaft 31 is matched with a through hole of a moving seat 36 through a positioning pin 32, the positioning pin 32 is vertical to the axial direction of the moving seat 36, and a top plate 33 and a spring I34 are pressed in the through hole of the moving seat 36 through a top screw 35 installed at the end part of the other end of the rotating shaft 31.

When the rudder surface 27 is in a folded state, as shown in fig. 10, the rotating shaft 31 is horizontally placed in the groove 39 at the top end of the movable seat 36, at the moment, the axis of the rotating shaft 31 is vertical to the axis of the movable seat 36, and the rotating shaft 31 is positioned at the top end of the long fixing groove 38 by the positioning pin 32 under the action of the spring I34 and is limited by the set screw 37; when the rudder face 27 is in the unfolded state, the axis of the rotating shaft 31 is parallel to the axis of the movable seat 36, and the rotating shaft 31 is positioned at the top end of the short fixing groove 40 by the positioning pin 32 under the action of the spring I34 and is limited by the set screw 37.

When the rotary folding rudder sheet 4 is changed from a folded state to an unfolded state, the set screw 37 is firstly unscrewed, then the rudder surface 27 and the rotating shaft 31 are turned over to be parallel to the axis of the moving seat 36, then the rudder surface 27 is pressed downwards, the positioning pin 32 is separated from the long fixing groove 38, then the rudder surface 27 is rotated by 90 degrees, the positioning pin 32 is positioned at the short fixing groove 40, then the rudder surface 27 is loosened, and the positioning pin 32 is bounced into the short fixing groove 40 under the action of the spring I34, so that the function of folding and rotating the rudder sheet is completed.

The rotary folding rudder piece 4 is arranged on the rudder cabin 6 and the position of the rotary folding rudder piece is adjustable; the rudder trunk 6 is provided with a sliding rail 5, and the rotary folding rudder piece 4 moves to an initial position 15, a short-range operation position 16 or a long-range operation position 17 along the sliding rail 5.

As shown in fig. 2, the sliding rail 5 is a t-shaped rail, the horizontal rail 18 is parallel to the axis of the projectile, and the vertical rail 19 is perpendicular to the axis of the projectile; two ends of the horizontal track 18 are respectively a short-range combat position 16 and a long-range combat position 17, and the short-range combat position 16 is far away from the head of the projectile body; the end of the vertical rail 19 remote from the point of intersection is the initial position 15. The rotary folding rudder sheet 4 is locked at an initial position 15 when being folded, and the rotary folding rudder sheet 4 is locked at a short-range combat position 16 or a long-range combat position 17 after being unfolded, so that the center of pressure of a control surface 27 and the center of mass of a projectile body are positioned on the same projectile body section in the flight process.

The initial position 15, the short-range combat position 16 or the long-range combat position 17 of the rudder cabin 6 are all provided with step through holes communicated with the outside of the cabin body and used for being matched with the blind holes in the movable seat 36.

When the movable seat 36 is installed in the installation groove (the installation groove is the sliding track 5) of the rudder cabin 6, the outer circumferential surface of the annular boss is in contact with the inner wall surface of the installation groove, namely the inner wall surface A surface 23 of the installation groove is attached to the outer circumferential surface B surface 24 of the annular boss, as shown in fig. 3(a), 3(B) and 3(c), when the rotary folding rudder piece 4 is locked at the initial position 15, the blind hole is opposite to the stepped through hole at the initial position 15 of the rudder cabin 6, the positioning shaft 21 is popped out and limited at the large-diameter part of the blind hole and the stepped through hole under the action of the spring II 22, the movable seat 36 is limited by the screw plug 20 not to rotate around the positioning shaft 21, and locking is completed; when the rotary folding rudder sheet 4 is locked at the short-range operation position 16 or the long-range operation position 17, the blind hole is opposite to the step through hole of the short-range operation position 16 or the long-range operation position 17 of the rudder cabin 6, the positioning shaft 21 pops out and is limited at the large-diameter part of the blind hole and the step through hole under the action of the spring II 22, and at the moment, the bottom surface of the annular boss contacts with the bottom surface of the mounting groove of the rudder cabin 6 to limit the rotation of the movable seat 36 to complete locking.

When the position of the rotary folding rudder sheet 4 is adjusted, after the rotary folding rudder sheet is unfolded and rotated by 90 degrees to a proper position, the positioning shaft 21 is propped against the outside of the cabin body of the rudder cabin 6 by a thimble through the small diameter part of the step through hole, the positioning shaft 21 is compressed, and when the positioning shaft is compressed to a certain position, the positioning shaft 21 is separated from the step through hole, as shown in fig. 4(a), 4(b) and 4(c), and then moves downwards along the vertical track 19. When the positioning shaft 21 moves to the horizontal rail 18, the movement is finished, at this time, the bottom surface C25 of the annular boss of the moving seat 36 is attached to the bottom surface D26 of the mounting groove, and the moving seat 36 is completely sunk into the mounting groove of the rudder cabin 6. The entire swivel-folding rudder blade 4 is then moved along the horizontal rail 18 by means of the positioning shaft 21 to the short range combat position 16 or the long range combat position 17, respectively. When the whole rotary folding rudder sheet 4 moves on the horizontal track 18 through the positioning shaft 21, when the positioning shaft 21 passes through the step through hole of the short-range operation position 16 or the long-range operation position 17, the positioning shaft 21 pops up under the elastic force of the spring II 22 to be clamped at the step through hole, so that the whole mechanism is locked, as shown in figures 5(a), 5(b) and 5 (c).

And a control cabin 7: including an outer housing and an internal roll angle measuring device 13, on-board computer 8 and on-board power supply 14. The roll angle measuring device 13 consists of a Hall geomagnetic sensitive sensor and a signal resolving circuit and is used for outputting a roll attitude angle of the rocket projectile in the flight process; the missile-borne computer 8 is used for resolving target motion parameters given by the infrared seeker 2 and combining projectile body control instructions given by the roll angle measuring device 13; the pop-up power supply 14 employs a thermal battery, activated by a launch overload, for powering the pop-up electrical system.

The range-extended engine 9: the ignition device comprises a shell, spray pipes arranged on two sides of the shell of the engine, a range-extending propellant, an ignition explosive package and a delay igniter, and the delay ignition is realized by adopting an ignition mode of activating the delay igniter by emitting overload; the range-extending engine 9 provides continuous thrust for the flying projectile body so as to ensure that the projectile body platform has the flying capacity of more than 5000 m. During short-range combat, the range-extended engine 9 does not work; during long-range combat, the control cabin 7 sets the ignition time of the range-extending engine 9 according to the target distance, and provides thrust required by range extension for the guided projectile body.

The flight engine 10: the projectile body platform is used for providing primary speed increasing for the projectile body platform after being launched.

The tail wing 12 assembly is composed of a tail rod 11 and a tail wing 12 and is used for stabilizing the flying state of the rocket projectile.

Ground fire control appearance: the method is used for setting corresponding information for the guided missile before launching.

The working principle is as follows:

after the shooter enters a position, a short-range working mode or a long-range working mode of the range-extended engine 9 is selected according to the target distance, parameters such as the target distance are fixed to the guided projectile body platform through the ground fire control instrument, and the ignition time of the range-extended engine 9 is determined according to the parameters such as the target distance. In one embodiment, if the target is at the range of 1500-5000 m and belongs to a remote working mode, the range-extended engine 9 works during the flight process, the center of mass of the full missile moves forwards, and the control surface 27 is locked by sliding towards the direction of the head of the missile during the ground setting of parameters. If the target is within the range of 1500m, the range-extended engine 9 does not need to work, the center of mass of the full projectile is basically kept unchanged, and the control surface 27 is locked by sliding towards the tail direction of the projectile body when the ground is provided with the parameters. And then the guided projectile body is loaded into a rocket tube, the rocket tube is placed on the shoulder, a target is searched and aimed through a white light/infrared aiming channel of a ground fire control instrument, after stable aiming, a hand is fired to trigger, and the propellant powder of the rocket projectile is ignited. High-pressure gas generated after the propellant powder is ignited acts on the projectile body to push the guided rocket projectile out of the rocket tube. And meanwhile, a thermal battery in the missile-borne control module is activated under the action of launching overload. In the process of missile flight, the on-board computer 8 sets the working ignition time of the range-extended engine 9 according to set parameters, so that the pressure center and the mass center of the missile control surface 27 at the tail end of a flight trajectory are strictly on the same missile body section, the tail end proportion guidance is realized, and the target is accurately hit.

In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. 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. A40 mm rocket launcher is with general guidance projectile body that the strapdown seeks, characterized by that, the said guidance projectile body includes seeker, draws fight cabin, rudder cabin, rotary folding rudder piece, control cabin, increases journey engine, flight engine and empennage assembly;

2. The 40mm rocket launcher universal strapdown homing guidance projectile of claim 1 wherein said rudder trunk has a sliding track along which a rotary folding rudder piece is moved from an initial position to a short range operational position or a long range operational position; the sliding rail is a T-shaped rail, the horizontal rail is parallel to the axis of the projectile body, and the vertical rail is perpendicular to the axis of the projectile body; two ends of the horizontal track are respectively a short-range combat position and a long-range combat position, and the short-range combat position is far away from the head of the projectile body; the end of the vertical rail away from the intersection is the initial position.

3. The universal strapdown homing guidance projectile for a 40mm rocket tube as claimed in claim 1, wherein said rotary foldable rudder piece comprises a control surface, a rotary shaft, a set screw, a positioning pin, a jackscrew, a spring i and a movable base;

4. The universal strapdown search guidance projectile for a 40mm rocket launcher according to claim 3, wherein an annular boss is provided on an outer circumference of said movable base, two blind holes are provided on said annular boss, and said two blind holes are located in a same radial direction; a spring II and a positioning shaft are sequentially arranged in the blind hole from inside to outside; the bottom end of the through hole of the movable seat is connected with the plug screw thread;

5. The guide projectile for universal strapdown homing for a 40mm rocket launcher according to claim 1 wherein said guidance head is a laser semi-active guidance head or a television guidance head or an infrared guidance head or a millimeter wave guidance head.