A general strapdown homing missile body for a 40mm rocket launcher

Abstract

The present invention provides a general strapdown homing guided missile body for a 40mm rocket launcher, which includes a seeker, a warhead and fuse compartment, a steering gear compartment, rotary folding fins, a control compartment, an extended-range engine, a flight engine and a tail fin assembly; the seeker, the warhead and fuse compartment, the steering gear compartment, the control compartment, the extended-range engine, the flight engine and the tail fin assembly are sequentially connected to form the guided missile body, and the seeker to the extended-range engine are all located in the super-caliber section; the rotary folding fins are installed on the steering gear compartment and the position is adjustable; when the rotary folding fins are folded, they are locked in the initial position, and after the rotary folding fins are deployed, they are moved to the short-range combat position or the long-range combat position and locked; during short-range combat, the extended-range engine does not work; during long-range combat, the control compartment sets the ignition time of the extended-range engine according to the target distance; the control compartment is used to solve the target space position information given by the seeker and generate a control command to drive the rotary folding fins so as to control the flight of the guided missile body. The present invention has high tracking and guidance accuracy.

Description

Technical Field

[0001] The present invention relates to the technical field of small-caliber guided ammunition, and particularly relates to a general strapdown homing warhead for a 40mm rocket launcher. Background Art

[0002] Active homing guidance or semi-active homing guidance is the main terminal guidance system for current guided weapons to achieve high-precision strikes on medium- and long-range targets, especially suitable for striking moving targets. The seeker of homing guidance is generally divided into two types: platform type and strapdown type. The platform type seeker can directly output the angular velocity of the line-of-sight rotation between the missile and the target, realizing high-precision proportional guidance. Due to the fact that the strapdown type seeker is fixedly connected to the missile body and is coupled with the missile body attitude during flight, generally, it cannot output the angular velocity of the line-of-sight rotation between the missile and the target. In this case, in order to obtain the angular velocity of the line-of-sight rotation required for proportional guidance, a high-precision inertial navigation system needs to be installed on the missile, a mathematical calculation platform is established, and the angular velocity of the line-of-sight rotation between the missile and the target is solved by fusing the information of the seeker and the inertial navigation. If the strapdown seeker does not adopt inertial navigation cooperation, generally, only the missile body tracking guidance law can be adopted. To ensure the guidance accuracy, this guidance law has very high requirements for the overall structure and aerodynamic design, and it is necessary to ensure that the missile body maintains a very small angle of attack state during closed-loop flight.

[0003] For the development of guided rockets for 40mm rocket launchers, low cost is a strict constraint condition. Therefore, neither the platform type seeker nor the high-precision inertial navigation system can be used in the scheme design. A feasible technical approach is to achieve a relatively high-precision missile body tracking guidance through a high-level overall structure and aerodynamic layout design. For this purpose, a technical scheme of a general strapdown homing warhead for a 40mm rocket launcher is proposed. Summary of the Invention

[0004] In view of this, the present invention provides a general strapdown homing warhead for a 40mm rocket launcher, which has high missile body tracking guidance accuracy.

[0005] The technical solution adopted by the present invention is as follows:

[0006] A general strapdown homing warhead for a 40mm rocket launcher, the guided warhead includes a seeker, a fuse and warhead compartment, a steering engine compartment, a rotating and folding steering vane, a control compartment, an extended-range engine, a flight engine and a tail fin assembly;

[0007] The seeker, the fuse and warhead compartment, the steering engine compartment, the control compartment, the extended-range engine, the flight engine and the tail fin assembly are sequentially connected to form the guided warhead, and the seeker, the fuse and warhead compartment, the steering engine compartment, the control compartment, and the extended-range engine are all located in the front over-caliber section of the missile body;

[0008] The rotary folding rudder fin is installed on the rudder nacelle and its position is adjustable; when the rotary folding rudder fin is folded, it is locked in the initial position, and after the rotary folding rudder fin is deployed, it moves to the short-range combat position or the long-range combat position and is locked, so that the center of pressure of the rudder surface and the center of mass of the projectile body are located on the same cross-section of the projectile body at the end of the flight trajectory;

[0009] During short-range combat, the range extension engine does not work; during long-range combat, the control cabin sets the ignition time of the range extension engine according to the target distance to provide the thrust required for range extension for the guided projectile body;

[0010] The control cabin is used to calculate the target spatial position information given by the seeker, generate control commands to drive the rotary folding rudder fin, and thus control the flight of the guided projectile body.

[0011] Furthermore, a sliding track is provided on the rudder nacelle, and the rotary folding rudder fin moves along the sliding track from the initial position to the short-range combat position or the long-range combat position; the sliding track is a T-shaped track, the horizontal track is parallel to the axis of the projectile body, and the vertical track is perpendicular to the axis of the projectile body; both ends of the horizontal track are the short-range combat position and the long-range combat position respectively, and the short-range combat position is far from the head of the projectile body; the end of the vertical track away from the intersection point is the initial position.

[0012] Furthermore, the rotary folding rudder fin includes a rudder surface, a rotating shaft, a set screw, a positioning pin, a top screw, a spring I and a moving seat;

[0013] A through hole is axially arranged inside the moving seat. The top end of the moving seat is used to connect the rudder surface, and the bottom end is used to cooperate with the rudder nacelle body for installation. On the inner wall of the top end of the through hole, there are two pairs of fixing grooves with different axial lengths, namely a pair of long fixing grooves and a pair of short fixing grooves, corresponding to the two states of folding and unfolding. The two long fixing grooves are arranged oppositely, the two short fixing grooves are arranged oppositely, and the included angle between the adjacent long and short fixing grooves and the axis connection line is 90°; at the same time, a radial through hole and a groove penetrating the end are provided at the upper end of the moving seat. The open end of the groove is located at the top end face of the moving seat. The top end of the short fixing groove is lower than the bottom end of the groove, and the top end of the long fixing groove is higher than the bottom end of the groove; the radial through hole is used to cooperate with the set screw; the top screw is installed inside the bottom end of the through hole of the moving seat;

[0014] The rudder surface is fixed to one end of the rotating shaft. The axis direction of the rotating shaft is parallel to the rudder 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 perpendicular to the axial direction of the moving seat, and the top screw installed at the end of the other end of the rotating shaft presses the spring I into the through hole of the moving seat;

[0015] When the rudder surface is in the folded state, the rotating shaft is horizontally placed in the top groove of the moving seat. The axis of the rotating shaft is perpendicular to the axis of the moving seat. At the same time, under the action of spring I, the rotating shaft is positioned at the top of the long fixing groove by the positioning pin and limited by the set screw. When the rudder surface is in the unfolded state, the axis of the rotating shaft is parallel to the axis of the moving seat. Under the action of spring I, the rotating shaft is positioned at the top of the short fixing groove by the positioning pin and limited by the set screw.

[0016] Furthermore, an annular boss is provided on the outer circumference of the moving seat. There are two blind holes on the annular boss, and the two blind holes are located in the same radial direction. A spring II and a positioning shaft are successively arranged in the blind hole from the inside to the outside. The bottom end of the through hole of the moving seat is threadedly connected with a plug screw.

[0017] Step through holes communicating with the outside of the cabin are provided at the initial position, the short-range combat position or the long-range combat position of the rudder engine room for cooperating with the blind holes on the moving seat.

[0018] When the moving seat is installed in the installation groove of the rudder engine room, the outer circumferential surface of the annular boss contacts the inner wall surface of the installation groove. When the rotary folding rudder blade is locked in the initial position, the blind hole is opposite to the step through hole at the initial position of the rudder engine room. The positioning shaft pops out under the action of spring II and is limited in the large-diameter part of the blind hole and the step through hole, and the rotation of the moving seat is restricted by the plug screw to complete the locking. When the rotary folding rudder blade is locked in the short-range combat position or the long-range combat position, the blind hole is opposite to the step through hole at the short-range combat position or the long-range combat position of the rudder engine room. The positioning shaft pops out under the action of spring II and is limited in the large-diameter part of the blind hole and the step through hole. At this time, the bottom surface of the annular boss contacts the bottom surface of the installation groove of the rudder engine room to restrict the rotation of the moving seat to complete the locking.

[0019] Furthermore, the seeker adopts a laser semi-active seeker or a television seeker or an infrared seeker or a millimeter-wave seeker.

[0020] Beneficial effects:

[0021] 1. In the present invention, the rudder nacelle is arranged in the over-caliber projectile section. Since there is no restriction of the rocket launcher structure in the over-caliber section, the rudder surface can be designed to be sufficiently large. At the same time, there is a large space for adjusting the position of the rudder actuator. By using a rudder surface with adjustable position, the pressure center of the rudder surface and the mass center of the projectile are arranged on the same projectile cross-section, so that the direct lateral force control of the mass center movement of the projectile can be realized, thereby ensuring that the angle of attack reaches the minimum during the flight process. At the same time, considering that mid- and long-range rockets need to add range extension engines, before and after the engine works, the mass center of the projectile will change to a certain extent. By using the rudder surface structure with adjustable position in the present invention, during the actual use process, the ignition time of the range extension engine on the ballistic trajectory can be set according to the target distance, and it can be moved to the short-range combat position or the long-range combat position and locked according to the law of mass center change, ensuring that the pressure center of the rudder surface of the missile and the mass center are strictly on the same projectile cross-section at the end of the flight trajectory. Thus, the acting point of the control force in the terminal guidance section always coincides with the mass center of the projectile. During the process of generating the control force by the deflection of the rudder surface, no control moment will be generated on the projectile, and the projectile axis and the velocity direction will maintain a very good consistency. The projectile will fly at a zero angle of attack or a very small angle of attack. Combined with the two-stage engine scheme of the flight engine plus the range extension engine, the control force directly changes the flight speed direction of the projectile during the control process. This will greatly improve the accuracy of the projectile tracking guidance law using the strapdown seeker, providing conditions for the development of low-cost and high-precision guided rockets with long-range and precise attacks for the 40mm rocket launcher platform, and can greatly improve the combat effectiveness of the 40mm rocket launcher platform.

[0022] 2. The rotating and folding rudder vane structure of the present invention is ingenious and is easy to realize the folding, unfolding and rotation of the rudder vane.

[0023] 3. The general strapdown homing guided projectile of the present invention can be used in the schemes of strapdown seekers such as laser semi-active, television, infrared, millimeter wave, etc., and has a wide range of applications. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 is a schematic diagram of the overall structure of the present invention;

[0025] Figure 2 is a schematic diagram of the structure of the sliding track;

[0026] Figure 3(a) is a schematic diagram of the structure of the rotating and folding rudder vane locked at the initial position when folded, Figure 3(b) is a cross-sectional view of Figure 3(a), and Figure 3(c) is a partial enlarged schematic diagram of Figure 3(b);

[0027] Figure 4(a) is a schematic diagram of the state of the rotating and folding rudder vane ready to move after unfolding, Figure 4(b) is a cross-sectional view of Figure 4(a), and Figure 4(c) is a partial enlarged schematic diagram of Figure 4(b);

[0028] Figure 5(a) is a schematic diagram of the locked state after the rotationally folding rudder blade is deployed, Figure 5(b) is a sectional view of Figure 5(a), and Figure 5(c) is a partially enlarged schematic diagram of Figure 5(b);

[0029] Figure 6 is a sectional view of the rotationally folding rudder blade;

[0030] Figure 7 is an exploded three-dimensional structure diagram of the rotationally folding rudder blade;

[0031] Figure 8 is a three-dimensional structure diagram of the moving seat;

[0032] Figure 9 is a sectional view of the moving seat;

[0033] Figure 10 is a schematic diagram of the connection structure between the moving seat and the rotationally folding rudder blade;

[0034] Among them, 1 - wind cap, 2 - infrared seeker, 3 - warhead and fuse compartment, 4 - rotationally folding rudder blade, 5 - sliding track, 6 - rudder engine compartment, 7 - control compartment, 8 - on-board computer, 9 - range extension engine, 10 - flight engine, 11 - tail rod, 12 - tail fin, 13 - roll angle measuring device, 14 - on-board power supply, 15 - initial position, 16 - short-range combat position, 17 - long-range combat position, 18 - horizontal track, 19 - vertical track, 20 - plug screw, 21 - positioning shaft, 22 - spring II, 23 - surface A, 24 - surface B, 25 - surface C, 26 - surface D, 27 - rudder surface, 28 - rudder surface connecting screw, 29 - rudder shaft, 30 - fixing screw, 31 - rotating shaft, 32 - positioning pin, 33 - top piece, 34 - spring I, 35 - setscrew, 36 - moving seat, 37 - locking screw, 38 - long fixing groove, 39 - groove, 40 - short fixing groove. Detailed implementation manners

[0035] The following combines the accompanying drawings and gives examples to describe the present invention in detail.

[0036] This embodiment provides a general strapdown homing guided missile body for a 40mm rocket launcher, as Figure 1 shown, including a seeker, a warhead and fuse compartment 3, a rudder engine compartment 6, a rotationally folding rudder blade 4, a control compartment 7, a range extension engine 9, a flight engine 10, and a tail fin 12 assembly. In addition, the weapon system also includes a ground guidance device.

[0037] The seeker, the warhead and fuse compartment 3, the rudder engine compartment 6, the control compartment 7, the range extension engine 9, the flight engine 10, and the tail fin 12 assembly are sequentially connected from the head to the tail to form the guided missile body. The rocket body located outside the rocket launcher is an over-caliber section. The seeker, the warhead and fuse compartment 3, the rudder engine compartment 6, the control compartment 7, and the range extension engine 9 are all located in the front over-caliber section of the missile body.

[0038] The seeker uses an infrared seeker 2 to sense the target radiation, automatically measure and output the motion parameters of the target. A laser semi-active seeker, a television seeker, or a millimeter-wave seeker can also be used. A wind cap 1 is provided outside the seeker.

[0039] The warhead section 3 is composed of an outer shell, a fuse, a safety and arming mechanism, a detonator tube, and a warhead.

[0040] The rudder nacelle 6 includes a transmission mechanism, a motor, and a driver. The driver receives the missile body control instructions given by the control cabin 7 to control the operation of the motor. The motor drives the transmission mechanism to drive the rudder vane to act to generate a control force and a control torque, so that the rocket projectile flies towards the target.

[0041] Such as Figure 6 、 Figure 7 As shown, the rotary folding rudder vane 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 piece 33, a set screw 35, a spring I 34, a spring II 22, a positioning shaft 21, and a moving seat 36.

[0042] The moving seat 36 is provided with a through hole along the axial direction inside. The top end of the moving seat 36 is used to connect the rudder surface 27, and the bottom end is used to be installed in cooperation with the installation groove of the rudder nacelle 6. As shown in Figure 8 、 Figure 9 As shown, there are two pairs of fixing grooves with different axial lengths on 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, corresponding to the two states of folding and unfolding. The two long fixing grooves 38 are arranged oppositely, the two short fixing grooves 40 are arranged oppositely, and the included angle between the connection lines of the adjacent two long fixing grooves 38, short fixing grooves 40 and the axis is 90°; at the same time, the upper end of the moving seat 36 is provided with a radial through hole and a groove 39 penetrating the end. The open end of the groove 39 is located at the top end face of the moving 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 used to cooperate with the set screw 37; in a preferred embodiment, the radial through hole is arranged above the short fixing groove 40, and the groove 39 is opposite to the radial through hole.

[0043] The outer circumference of the moving seat 36 is provided with an annular boss, and there are two blind holes on the annular boss, and the two blind holes are located in the same radial direction; a spring II 22 and a positioning shaft 21 are sequentially arranged in the blind hole from the inside to the outside. A set screw 35 is installed inside the bottom end of the through hole of the moving seat 36, and the bottom end of the through hole is threadedly connected with a plug screw 20.

[0044] The rudder shaft 29 is of a U-shaped fork structure. The rudder surface 27 is fixed at the open end of the U-shaped fork through the rudder surface connecting screw 28. The closed end of the U-shaped fork is fixedly connected to one end of the rotating shaft 31 through the fixing screw 30. The axis direction of the fixing screw 30 is parallel to the axis of the rotating shaft 31. The axis direction of the rotating shaft 31 is parallel to the rudder surface 27. The other end of the rotating shaft 31 is in fit with the through hole of the moving seat 36 through the positioning pin 32. The positioning pin 32 is perpendicular to the axial direction of the moving seat 36. And the set screw 35 installed at the end of the other end of the rotating shaft 31 presses the top piece 33 and the spring I 34 into the through hole of the moving seat 36.

[0045] As Figure 10 shown, when the rudder surface 27 is in the folded state, the rotating shaft 31 is horizontally placed in the top groove 39 of the moving seat 36. At this time, the axis of the rotating shaft 31 is perpendicular to the axis of the moving seat 36. At the same time, the rotating shaft 31 is positioned at the top of the long fixing groove 38 by the positioning pin 32 under the action of the spring I 34 and is limited by the set screw 37. When the rudder surface 27 is in the unfolded state, the axis of the rotating shaft 31 is parallel to the axis of the moving seat 36. The rotating shaft 31 is positioned at the top of the short fixing groove 40 by the positioning pin 32 under the action of the spring I 34 and is limited by the set screw 37.

[0046] When the rotary folding rudder vane 4 changes from the folded state to the unfolded state, first loosen the set screw 37, then flip the rudder surface 27 and the rotating shaft 31 so that they are parallel to the axis of the moving seat 36. Then press down the rudder surface 27 to make the positioning pin 32 leave the long fixing groove 38. Then rotate the rudder surface 27 by 90°, so that the positioning pin 32 is at the short fixing groove 40. Then release the rudder surface 27. Under the action of the spring I 34, the positioning pin 32 pops into the short fixing groove 40 to complete the function of folding and rotating the rudder vane.

[0047] The rotary folding rudder vane 4 is installed on the rudder nacelle 6 and its position is adjustable. There is a sliding track 5 on the rudder nacelle 6. The rotary folding rudder vane 4 moves along the sliding track 5 to the initial position 15, the short-range combat position 16 or the long-range combat position 17.

[0048] As Figure 2 shown, the sliding track 5 is a T-shaped track. The horizontal track 18 is parallel to the axis of the projectile body. The vertical track 19 is perpendicular to the axis of the projectile body. The two ends of the horizontal track 18 are respectively the short-range combat position 16 and the long-range combat position 17. And the short-range combat position 16 is far from the head of the projectile body. The end of the vertical track 19 far from the intersection point is the initial position 15. The rotary folding rudder vane 4 is locked at the initial position 15 when folded and is locked at the short-range combat position 16 or the long-range combat position 17 after unfolding, so that the pressure center of the rudder surface 27 and the center of mass of the projectile body are located on the same cross-section of the projectile body during flight.

[0049] The initial position 15, the short-range combat position 16 or the long-range combat position 17 of the rudder engine room 6 are all provided with stepped through holes communicating with the outside of the cabin body, which are used to cooperate with the blind holes on the moving seat 36.

[0050] When the moving seat 36 is installed in the installation groove of the rudder engine room 6 (the installation groove is the sliding track 5), the outer circumferential surface of the annular boss contacts the inner wall surface of the installation groove, that is, the A surface 23 of the inner wall surface of the installation groove fits with the B surface 24 of the outer circumferential surface of the annular boss, as Figure 3(a) 、 3(b) 、shown in Fig. 3(c), when the rotary folding rudder blade 4 is locked in the initial position 15, the blind hole is opposite to the stepped through hole at the initial position 15 of the rudder engine room 6. The positioning shaft 21 pops out under the action of the spring II 22 and is limited in the large-diameter part of the blind hole and the stepped through hole. The plug screw 20 restricts the moving seat 36 from rotating around the positioning shaft 21 to complete the locking; when the rotary folding rudder blade 4 is locked in the short-range combat position 16 or the long-range combat position 17, the blind hole is opposite to the stepped through hole at the short-range combat position 16 or the long-range combat position 17 of the rudder engine room 6. The positioning shaft 21 pops out under the action of the spring II 22 and is limited in the large-diameter part of the blind hole and the stepped through hole. At this time, the bottom surface of the annular boss contacts the bottom surface of the installation groove of the rudder engine room 6 to restrict the rotation of the moving seat 36 to complete the locking.

[0051] When adjusting the position of the rotary folding rudder blade 4, after it is unfolded and rotated 90° in place, use a thimble to push against the positioning shaft 21 from the outside of the cabin body of the rudder engine room 6 through the small-diameter part of the stepped through hole to compress it. When compressed to a certain position, the positioning shaft 21 disengages from the stepped through hole, as Figure 4(a) 、 4(b) 、shown in Fig. 4(c), and then move downward along the vertical track 19. When the positioning shaft 21 moves to the horizontal track 18, the movement ends. At this time, the C surface 25 of the bottom surface of the annular boss of the moving seat 36 fits with the D surface 26 of the bottom surface of the installation groove, and the moving seat 36 is completely sunk into the installation groove of the rudder engine room 6. Then the entire rotary folding rudder blade 4 moves along the horizontal track 18 under the action of the positioning shaft 21 and can be moved to the short-range combat position 16 or the long-range combat position 17 respectively. When the entire rotary folding rudder blade 4 moves on the horizontal track 18 through the positioning shaft 21, when the positioning shaft 21 passes through the stepped through hole at the short-range combat position 16 or the long-range combat position 17, the positioning shaft 21 pops out under the elastic force of the spring II 22 and gets stuck at the stepped through hole to lock the entire mechanism, as Figure 5(a) 、 5(b) 、shown in Fig. 5(c).

[0052] Control cabin 7: It includes an external shell and an internal roll angle measuring device 13, an on-board computer 8, and an on-board power supply 14 inside. The roll angle measuring device 13 consists of a Hall geomagnetic sensor and a signal resolution circuit, and is used to output the roll attitude angle of the rocket during flight; the on-board computer 8 is used to resolve the target motion parameters given by the infrared seeker 2 and combine the control instructions of the missile body given by the roll angle measuring device 13; the on-board power supply 14 uses a thermal battery, which is activated by the launch overload and is used to supply power to the on-board electrical system.

[0053] Range extension engine 9: It consists of a shell, nozzles arranged on both sides of the engine shell, range extension propellant, an ignition charge package, and a delay ignition device. It adopts the ignition method of activating the delay ignition device by the launch overload to achieve delayed ignition; the range extension engine 9 provides continuous thrust for the flying missile body to ensure that the missile body platform has the flight ability of more than 5000m. During short-range combat, the range extension engine 9 does not work; during long-range combat, the control cabin 7 sets the ignition time of the range extension engine 9 according to the target distance and provides the thrust required for range extension for the guided missile body.

[0054] Flight engine 10: It is used to provide the first-stage speed increase for the missile body platform after the missile body platform is launched.

[0055] The fin 12 assembly consists of a fin rod 11 and fins 12, and is used to stabilize the flight state of the rocket.

[0056] Ground fire control instrument: It is used to set corresponding information for the guided missile before launch.

[0057] Working principle:

[0058] After the shooter enters the position, select the "short-range" or "long-range" working mode of the extended-range engine 9 according to the target distance, and at the same time set parameters such as the target distance to the guided missile body platform through the ground fire control instrument. The ignition time of the extended-range engine 9 is determined by parameters such as the target distance. In an embodiment, if the target is within a range of 1500 - 5000m, which belongs to the long-range working mode, the extended-range engine 9 works during the flight, and the total missile mass center moves forward. When setting the parameters on the ground, the control surface 27 should be slid and locked towards the head direction of the missile body. If the target is within a range of 1500m, the extended-range engine 9 does not need to work, and the total missile mass center remains basically unchanged. When setting the parameters on the ground, the control surface 27 should be slid and locked towards the tail direction of the missile body. Then, place the guided missile body into the rocket launcher, place the rocket launcher on the shoulder, search and aim at the target through the white light / infrared aiming channel of the ground fire control instrument. After stable aiming, the shooter pulls the trigger to ignite the rocket propellant. The high-pressure gas generated after the propellant is ignited acts on the missile body, pushing the guided rocket out of the rocket launcher. At the same time, the thermal battery in the on-board control module is activated under the action of the launch overload. During the missile flight, the on-board computer 8 sets the ignition time of the extended-range engine 9 according to the set parameters to ensure that the pressure center of the control surface 27 and the mass center of the missile are strictly on the same missile body cross-section at the end of the flight trajectory, realizing terminal proportional guidance and accurately hitting the target.

[0059] In summary, the above are only the preferred embodiments of the present invention and are not used to limit the protection scope of the present invention. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. A general strapdown homing guided missile body for a 40mm rocket launcher, characterized in that, The guided missile body includes a seeker, a warhead cabin, a rudder cabin, rotary folding rudder fins, a control cabin, a range extension engine, a flight engine, and a tail fin assembly; The seeker, the warhead cabin, the rudder cabin, the control cabin, the range extension engine, the flight engine, and the tail fin assembly are sequentially connected to form the guided missile body, and the seeker, the warhead cabin, the rudder cabin, the control cabin, and the range extension engine are all located in the front super-caliber section of the missile body; The rotary folding rudder fins are installed on the rudder cabin and are position-adjustable; when the rotary folding rudder fins are folded, they are locked in the initial position. After the rotary folding rudder fins are deployed, they move to the short-range combat position or the long-range combat position and are locked, so that the center of pressure of the rudder surface and the center of mass of the missile body are located on the same cross-section of the missile body at the end of the flight trajectory; During short-range combat, the range extension engine does not work; during long-range combat, the control cabin sets the ignition time of the range extension engine according to the target distance to provide the thrust required for range extension for the guided missile body; The control cabin is used to calculate the target space position information given by the seeker and generate control commands to drive the rotary folding rudder fins to control the flight of the guided missile body.

2. The general strapdown homing guided missile body for a 40mm rocket launcher according to claim 1, characterized in that, A sliding track is provided on the rudder cabin, and the rotary folding rudder fins move along the sliding track from the initial position to the short-range combat position or the long-range combat position; the sliding track is a T-shaped track, the horizontal track is parallel to the axis of the missile body, and the vertical track is perpendicular to the axis of the missile body; both ends of the horizontal track are the short-range combat position and the long-range combat position respectively, and the short-range combat position is far from the head of the missile body; the end of the vertical track far from the intersection point is the initial position.

3. The general strapdown homing guided missile body for a 40mm rocket launcher according to claim 1, characterized in that, The rotary folding rudder fins include a rudder surface, a rotating shaft, a set screw, a positioning pin, a top screw, a spring I, and a moving seat; A through hole is axially provided inside the moving seat. The top end of the moving seat is used to connect the rudder surface, and the bottom end is used to cooperate with the rudder cabin body for installation. There are two pairs of fixing grooves with different axial lengths on the inner wall of the top end of the through hole, namely a pair of long fixing grooves and a pair of short fixing grooves, corresponding to the two states of folding and unfolding. The two long fixing grooves are arranged oppositely, the two short fixing grooves are arranged oppositely, and the included angle between the adjacent long and short fixing grooves and the axis connection line is 90°; at the same time, a radial through hole and a groove penetrating the end are provided at the upper end of the moving seat. The open end of the groove is located at the top end face of the moving seat. The top end of the short fixing groove is lower than the bottom end of the groove, and the top end of the long fixing groove is higher than the bottom end of the groove; the radial through hole is used to cooperate with the set screw; the top screw is installed inside the bottom end of the through hole of the moving seat; The rudder surface is fixed to one end of the rotating shaft. The axis direction of the rotating shaft is parallel to the rudder 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 perpendicular to the axial direction of the moving seat, and the top screw installed at the end of the other end of the rotating shaft presses the spring I into the through hole of the moving seat; When the rudder surface is in the folded state, the rotating shaft is horizontally placed in the top groove of the moving seat, the axis of the rotating shaft is perpendicular to the axis of the moving seat. At the same time, the rotating shaft is positioned at the top of the long fixing groove by the positioning pin under the action of the spring I and is limited by the set screw; when the rudder surface is in the unfolded state, the axis of the rotating shaft is parallel to the axis of the moving seat, and the rotating shaft is positioned at the top of the short fixing groove by the positioning pin under the action of the spring I and is limited by the set screw.

4. The general strapdown homing guided missile body for a 40mm rocket launcher according to claim 3, characterized in that, An annular boss is provided on the outer circumference of the moving seat, and two blind holes are provided on the annular boss, and the two blind holes are located in the same radial direction; a spring II and a positioning shaft are sequentially arranged in the blind hole from the inside to the outside; the bottom end of the through hole of the moving seat is threadedly connected with a plug screw; A stepped through hole communicating with the outside of the cabin body is provided at the initial position, the short-range combat position or the long-range combat position of the rudder engine room for cooperating with the blind hole on the moving seat; When the moving seat is installed in the installation groove of the rudder engine room, the outer circumferential surface of the annular boss contacts the inner wall surface of the installation groove; when the rotary folding rudder blade is locked in the initial position, the blind hole is opposite to the stepped through hole at the initial position of the rudder engine room, and the positioning shaft pops out under the action of the spring II and is limited in the large-diameter part of the blind hole and the stepped through hole, and the rotation of the moving seat is restricted by the plug screw to complete the locking; When the rotary folding rudder blade is locked in the short-range combat position or the long-range combat position, the blind hole is opposite to the stepped through hole at the short-range combat position or the long-range combat position of the rudder engine room, and the positioning shaft pops out under the action of the spring II and is limited in the large-diameter part of the blind hole and the stepped through hole. At this time, the bottom surface of the annular boss contacts the bottom surface of the installation groove of the rudder engine room to restrict the rotation of the moving seat to complete the locking.

5. The general strapdown homing guided missile body for a 40mm rocket launcher according to claim 1, characterized in that, The seeker adopts a laser semi-active seeker or a television seeker or an infrared seeker or a millimeter wave seeker.

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