Traction type simulated missile launching vehicle

Abstract

The utility model discloses a pull-type simulated missile launching vehicle and belongs to the technical field of launching vehicles. Comprising a bottom frame, a front axle suspension, a rear axle suspension, a supporting anchoring mechanism and a launching frame, the front axle suspension, the rear axle suspension, the supporting anchoring mechanism and the launching frame are installed on the bottom frame, the launching frame is controlled to be erected and laid down through a rotary driver connected with the launching frame, and a front bracket, a booster bracket and a rear bracket are sequentially installed at the front end, the middle rear portion and the tail end of the launching frame. The launching and releasing structure of the system is reasonable in design, the trailer drags the launching vehicle to transfer flexibly, the supporting and anchoring mechanism is convenient and reliable to unfold, the simulated projectile is horizontally hoisted and placed on the front bracket and the rear bracket of the launching rack and is safely, simply and conveniently butted with the projectile body, and the launching rack is erected and put down easily and freely. The simulated missile launch release take-off section flies stably, missile carrier separation is normal, no safety accident occurs in the whole launch process, all functional parts are used normally, the launch release separation structure is not damaged by huge thrust borne by the simulated missile during launch, and the structural rigidity and the separation performance are safe and reliable.

Description

TECHNICAL FIELD

[0001] The utility model belongs to the technical field of launching vehicle, especially relates to a traction type simulated bomb launching vehicle. BACKGROUND

[0002] The existing launching vehicle moves to the launching position by using self power, relies on the electrical and hydraulic system to complete the anchoring support and the launching frame erection before the missile launching, and the commander issues the launching instruction to complete the missile launching process, and it is the main application platform for the missile launching, and the launching vehicle of the mode has high manufacturing and maintenance cost and complex structure, and cannot adapt to the needs of the scene maneuvering and random launching of the simulated bomb. SUMMARY

[0003] In view of the defects in the prior art, the utility model aims at providing a traction type simulated bomb launching vehicle.

[0004] The utility model adopts the technical scheme of a traction type simulated bomb launching vehicle, and the technical points are as follows: the traction type simulated bomb launching vehicle comprises a chassis, a front axle suspension and a rear axle suspension which are installed on the chassis, the chassis is supported on the ground through front tires installed on the outer side of the front axle suspension hub and rear tires installed on the outer side of the rear axle suspension hub, support anchoring mechanisms are arranged at the rear side of the front tires and the rear tires of the chassis respectively, a launching frame is installed on the upper surface of the chassis, the launching frame is operated to be erected and lowered through a rotary drive machine connected with the launching frame, a front bracket, a booster bracket and a rear bracket are sequentially installed at the front end, the middle rear part and the tail end of the launching frame, a fixed shear force separation mechanism is further installed on the rear bracket, and a socket pulling and lodging mechanism is installed on the side of the launching frame, and the socket pulling and lodging mechanism is used for connecting the communication cable before the simulated bomb launching and disconnecting the connection after the launching instruction is issued.

[0005] In the above scheme, the front axle suspension mainly comprises a steel plate spring structure installed on the inner side of the front hub, the rear axle suspension mainly comprises another steel plate spring structure installed on the inner side of the rear hub, the steel plate spring damping structure is formed by stacking and binding steel plates of different lengths together, the middle part is installed on the front axle shaft and the rear axle shaft through a U-shaped screw rod, the two ends of the uppermost layer of steel plates are bent into cylindrical hinge holes, and the cylindrical hinge holes are respectively installed on the swing rocker arms in the front plate spring support and the rear plate spring support on the side of the chassis 1.

[0006] In the above scheme, the support anchoring mechanism comprises a fixed support fixed on the chassis, a rotating support rod is installed in the fixed support, the fixed support is hingedly connected with the rotating support rod through a bolt, a lifting hand wheel is installed in a semicircular clamping groove at the bottom of the swing end of the rotating support rod, an anchoring plate is connected with the bottom of the rotating support rod swing end and the lifting hand wheel threaded hole, and the bottom is connected with the anchoring plate abutting the ground.

[0007] In the above scheme, the anchoring plate lower end has a wave-shaped sharp spike which is inserted into the ground.

[0008] In the above scheme, the front bracket includes two symmetrically arranged bracket columns and an arc-shaped bracket. The two bracket columns and the arc-shaped bracket adopt an integral structure. The top of the bracket column is connected to a clamping device that locks the simulated bullet onto the front bracket. Two sets of torsion spring assemblies are installed at the spline hole at the bottom of the bracket column.

[0009] In the above scheme, a pin is installed on the arc-shaped bracket to mate with the positioning hole of the simulated projectile body. The pin is inserted into the positioning hole of the projectile body to position the simulated projectile.

[0010] In the above scheme, the booster bracket includes a lifting support, an arc-shaped support plate is slidably connected to the inner wall groove of the lifting support, a connecting boss is provided on the outer side of the lifting support, the lifting support is connected to the support rocker arms symmetrically arranged on both sides through the connecting boss, and the height of the lifting support can be adjusted by sliding up and down along the support rocker arm groove, the two support rocker arms are connected by a support plate to form a booster bracket support structure, and two sets of torsion spring assemblies are installed at the spline hole at the lower end of the support rocker arm.

[0011] In the above scheme, the socket release and tilting mechanism includes a spline shaft support and a tilting support rod. A spline shaft is installed inside the spline shaft support, and a spline hole at the bottom of the tilting support rod is installed on the spline shaft. A push rod motor is connected to the top of the tilting support rod, and a release traction rod is connected to the push rod of the push rod motor. The release traction rod is connected to the communication cable plug. The push rod motor pulls the release traction rod to move and cause the communication cable plug to separate from the socket. A set of torsion spring assemblies is installed inside the spline shaft support.

[0012] In the above scheme, the torsion spring assembly includes a splined shaft, on which a tapered bearing, a bearing baffle, a torsion spring, and a torsion spring baffle are sequentially installed. A torsion spring pressure plate is provided at the bottom end of the torsion spring. The torsion spring pressure plate is used to lock the torsion spring, the bearing baffle presses the bearing, and the torsion spring baffle prevents the torsion spring from sliding out during extension and retraction. A gap is left between the bearing baffle and the torsion spring baffle for the extension and retraction of the torsion spring.

[0013] In the above scheme, a fixed shear force separation mechanism is installed on the rear bracket, including a swing arm, a shearing rod, and a shearing pin for accumulating force and releasing force.

[0014] The beneficial effects of this utility model are as follows: This towed simulated missile launcher includes a chassis and front and rear axle suspensions, a support and anchoring mechanism, and a launcher connected to the chassis. The launcher is raised and lowered by a rotary drive motor connected to it. The front bracket, booster bracket, and rear bracket are sequentially installed at the front, middle, rear, and tail ends of the launcher. The launcher has completed prototype production and ground-based testing. The entire launch system has a reasonable structural design, is highly maneuverable with trailer towing, and the docking operation between the simulated missile and the launcher is simple. The support and anchoring mechanism is easy and reliable to deploy, and the launcher is easy and convenient to raise and lower. In nine launches conducted by the simulated missile launcher, the simulated missile's launch and release phases were stable, the missile launcher separated normally, no safety accidents occurred during launch, all functional components functioned normally, and the launch and release structure was not damaged by the enormous thrust exerted during the simulated missile launch. The structural rigidity and separation performance are safe and reliable. Attached Figure Description

[0015] To more clearly illustrate the technical solutions in the embodiments of this utility model or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this utility model. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0016] Figure 1 This is a front view of the towed simulated missile launcher in an embodiment of this utility model;

[0017] Figure 2 This is a top view of the towed simulated missile launcher in an embodiment of this utility model;

[0018] Figure 3 This is a view of the towed simulated missile launcher from direction A in this embodiment of the present invention;

[0019] Figure 4 This is a view from direction B of the towed simulated missile launcher in this embodiment of the present invention;

[0020] Figure 5 The following is a schematic diagram of the launcher structure in an embodiment of this utility model: (a) is a front view; (b) is a side view; and (c) is a top view.

[0021] Figure 6 This is a view of the launcher from direction C in an embodiment of this utility model;

[0022] Figure 7 This is a front view of the front axle suspension in an embodiment of the present invention, wherein (a) is the front view; (b) is the top view; and (c) is the side view.

[0023] Figure 8This is a schematic diagram of the rear axle suspension structure in an embodiment of the present utility model, wherein (a) is a front view; (b) is a side view; and (c) is a top view.

[0024] Figure 9 This is a schematic diagram of the base frame structure in an embodiment of the present utility model, wherein (a) is a front view; (b) is a side view; and (c) is a top view.

[0025] Figure 10 This is a schematic diagram of the supporting anchoring mechanism in an embodiment of the present invention, wherein (a) is a front view and (b) is a side view;

[0026] Figure 11 This is a schematic diagram of the booster bracket structure in an embodiment of the present invention, wherein (a) is a front view; (b) is a side view; and (c) is a top view.

[0027] Figure 12 This is a schematic diagram of the front bracket structure in an embodiment of the present invention, wherein (a) is a front view; (b) is a side view; and (c) is a top view.

[0028] Figure 13 This is a schematic diagram of the rear bracket structure in an embodiment of the present utility model, wherein (a) is a front view; (b) is a side view; and (c) is a top view.

[0029] Figure 14 This is a schematic diagram of the socket release and collapse mechanism in an embodiment of the present utility model. (a) is the front view; (b) is the side view.

[0030] Figure 15 The following is a schematic diagram of the fixed shear force separation mechanism in the embodiment of this utility model: (a) is the front view; (b) is the top view.

[0031] The meanings of each number are as follows: 1. Base frame, 2. Front axle suspension, 3. Rear axle suspension, 4. Support and anchoring mechanism, 5. Launcher, 6. Front bracket, 7. Rear bracket, 8. Booster bracket, 9. Socket release and collapse mechanism, 10. Fixed shear force separation mechanism, 11. Rotary drive motor, 12. Lifting handwheel, 13. Anchor plate, 14. Clamping device, 15. Pin, 16. Push rod motor, 17. Swing rod, 18. Shearing lever, 19. Shearing pin, 20. Ratchet wrench 21 Launcher mounting bracket, 22 Anchoring strut, 23 Pin, 24 Rotating strut, 25 Bracket column, 26 Movable clamping plate, 27 Arc bracket, 28 Torsion spring support, 29 Splined shaft, 30 Torsion spring, 31 Torsion spring pressure plate, 32 Torsion spring baffle, 33 Bearing baffle, 34 Protective cover, 35 Support rocker arm, 36 Lifting support, 37 Support plate, 38 Arc bracket, 39 Collapsing support rod, 40 Boosting torsion spring support. Detailed Implementation

[0032] To make the above-mentioned objectives, features and advantages of this utility model more apparent and understandable, the following description is provided in conjunction with the appendix. Figures 1-15 The present invention will be further described in detail below with reference to specific embodiments.

[0033] The towed simulated missile launcher of this embodiment includes a chassis 1, a front axle suspension 2 connected to the front end of the chassis 1, and a rear axle suspension 3 connected to the rear end of the chassis 1. The front tires are connected to both sides of the front axle suspension 2 via front wheel hubs, and the rear tires are connected to both sides of the rear axle suspension 3 via rear wheel hubs. The chassis 1 is supported on the ground by the front and rear tires. Four sets of support and anchoring mechanisms 4 are installed on the rear sides of the front and rear tires of the chassis 1, respectively. A launcher 5 is installed on the upper surface of the chassis 1. The drive shaft of the launcher 5 is connected to a rotary drive motor 11, which operates the raising and lowering of the launcher. The front bracket 6, booster bracket 8, and rear bracket 7 are respectively installed at the front, middle and rear, and tail ends of the launcher 5. The head and tail of the simulated missile are respectively hoisted and placed on the front bracket 6 and rear bracket 7. The booster for launching the simulated missile is supported by the booster bracket 8. The rear bracket 7 is also equipped with a fixed shear force separation mechanism 10, which is the energy storage and release device for the simulated missile. The booster, together with the adapter, is connected and locked to the launcher 5 through a swing arm, a shear pull rod, and a shear pin. When the booster is ignited, the thrust is activated. When the shear pin breaks due to shearing tension, the shear pin breaks and releases the simulated missile, which then flies away from the launcher 5. The launcher 5 is also connected to a socket release and collapse mechanism 9 on its side. The socket release and collapse mechanism is connected to the communication interface socket of the simulated missile through the launch communication cable plug. Before the simulated missile is launched and released, the push rod motor starts and drives the release traction rod to pull out the communication cable plug. The socket release and collapse mechanism is unlocked, and the collapse support rod 39 collapses laterally in the launch direction under the action of the torsion spring, thus completing the preparation for the launch and release of the simulated missile.

[0034] In this embodiment, the connections between the front and rear crossbeams, left and right longitudinal beams, and the intermediate supporting crossbeams of the base frame 1 are all riveted assembly frame structures. A launcher mounting bracket 21 is fixed to the rear end of the base frame 1, and the launcher 5 is connected to the launcher mounting bracket 21 via a drive shaft. In this embodiment, the launcher 5 is the main load-bearing component supporting and adjusting the launch attitude of the simulated missile. The main structural longitudinal beams and connecting trusses are made of bent manganese steel plates and are bolted together. The drive shaft in this embodiment is also connected to a rotary drive motor 11, which is mounted on the mounting plate of the base frame 1. Turning the ratchet wrench 20 on the rotary drive motor 11 drives the launcher 5 to stand up and lower. The rotary drive motor 11 has a built-in worm gear transmission mechanism. The worm gear transmission has a reverse self-locking function, which can lock the output shaft rotation at any point to avoid safety accidents during operation. The ratchet wrench 20 drives the worm gear to rotate, thereby rotating the drive shaft connected to the launcher 5 and realizing the standing up and lowering of the launcher 5.

[0035] The front axle suspension 2 and rear axle suspension 3 employ a leaf spring damping structure. This structure consists of five steel plates of different lengths stacked and bundled together, with U-shaped screws connecting them to the front and rear axle shafts. The top layer of steel plates has cylindrical hinge holes at both ends, which are installed in the front and rear leaf spring supports on the side of the base frame 1, respectively, on swing rockers. These rockers are used to adjust the installation position when the leaf springs are compressed and extended. Each steel plate stacked on each set of leaf springs is pre-bent to a different radius along its length. After the five steel plates are stacked and clamped, they are quenched and shaped at high temperature, giving each plate the elasticity to resist bending and straighten and restore its original bending curvature. The two sets of leaf springs are installed inside the front wheel hub to form the front axle suspension 2, and the two sets of leaf springs are installed inside the rear wheel hub to form the rear axle suspension 3. When the tires mounted on both sides of the front axle suspension 2 and the rear axle suspension 3 bounce and jolt, the impact force generated by this bounce is instantly transmitted to each steel plate. Each steel plate will undergo elastic deformation due to this impact force. The rebound force of each steel plate against the elastic deformation will absorb and buffer the impact of this bump on the chassis 1, thereby achieving the purpose of shock absorption and reducing the degree of bump.

[0036] In this embodiment, the front axle suspension 2 and rear axle suspension 3 use leaf springs for shock absorption and are equipped with solid rubber tires, which is more conducive to the launch vehicle traveling on rugged roads such as the Gobi Desert and other deserts. The steering tie rod can control the front wheel tires to swing within a 40° turning angle range to the left and right, making it easier for the simulated missile launch vehicle to turn, travel, and avoid obstacles.

[0037] The support and anchoring mechanism 4 in this embodiment includes a fixed support mounted on the base frame 1. A rotating support rod 24 is installed inside the fixed support. The fixed support is connected to the rotating support rod via a pin 23. The swing end of the rotating support rod is connected to an anchoring support rod 22 passing through it. The anchoring support rod also passes through a threaded hole in the middle of the lifting handwheel 12. The bottom of the anchoring support rod is connected to an anchoring plate 13 that is in contact with the ground. The lower end of the anchoring plate is provided with spikes that can be driven into the ground, facilitating the launch vehicle's stopping and deployment on rugged terrain such as the Gobi Desert and other deserts. The support and anchoring mechanism achieves the horizontal adjustment function of the base frame by rotating the lifting handwheel to move the anchoring support rod up and down. The anchoring support rod is provided with a T-shaped thread, and the threaded hole in the lifting handwheel engages with the thread on the anchoring support rod. The lifting handwheel is embedded in the semi-circular groove at the bottom of the rotating support rod through the stepped shaft at the edge of the threaded hole. When the lifting handwheel is rotated, since the lifting handwheel can only rotate within the embedded semi-circular groove, the upward thrust generated by the lifting handwheel thread will be transmitted to the anchoring screw connected to it, causing the anchoring support rod to extend and retract, and synchronously supporting the base frame to rise and fall.

[0038] In this embodiment, the front bracket 6 includes two symmetrically arranged bracket columns 25. A clamping device 14 is connected to each bracket column. The clamping device includes two movable clamping plates 26, each connected to a corresponding bracket column 25. One of the movable clamping plates has a quick-clamping device connected to its edge, which engages with the edge of the other movable clamping plate. The two bracket columns 25 and the arc-shaped bracket 27 are integrally formed. The arc-shaped bracket supports the head of the simulated projectile and uses the clamping device 14 to lock the simulated projectile onto the front bracket. In this embodiment, a pin 15 is installed in the middle of the arc-shaped bracket 27. During the hoisting of the simulated projectile, the pin 15 is inserted into a positioning hole on the simulated projectile for positioning. The splined holes at the lower ends of the two bracket columns 25 are aligned with the bearing holes of the torsion spring support 28 fixed inside the launcher. The short shaft ends of the two sets of splined shafts 29 pass through the bearing holes above the torsion spring support 28 and the splined holes at the bottom of the bracket column, and are then fixed by nuts. The connection structure is a splined transmission structure. The long shaft end of the splined shaft 29 is sequentially fitted with a tapered bearing, a bearing baffle 33, a torsion spring pressure plate 31, a torsion spring 30, and a torsion spring baffle 32. The bearing baffle 33 is fixed in the square hole of the torsion spring support 28 with screws to press the bearing. The torsion spring pressure plate 32 is fixed on the outside of the bearing baffle with screws. The torsion spring baffle presses the torsion spring and is connected to the long shaft end of the splined shaft with screws. The protective cover 34 is fitted on the outside of the torsion spring 28 and fixed with screws. The lower end of the torsion spring support 28 is inserted with a locking pin to fix the front bracket. In this embodiment, two sets of symmetrically arranged torsion springs are used to twist the front bracket forward and tilt it down. When the locking pin is pulled out and the front bracket is supported to rotate vertically around the spline axis, the two ends of each torsion spring will generate a rotational elastic force to restore the state before the torsion due to the change in the relative torsion angle. The rotational elastic force is synchronously transmitted to the bracket column connected together through the spline shaft. When the hands supporting the front bracket are released, the rotational elastic force generated by the two torsion springs will drive the integrated front bracket to rotate forward and tilt down to avoid collision.

[0039] The clamping device installed on the rear bracket 7 in this embodiment is similar to that of the front bracket 6, also including two symmetrically arranged bracket columns and a second clamping device connected to the top of the bracket columns. The two movable plates of the second clamping device are respectively connected to the corresponding bracket columns, and the edge of one movable plate is connected to a quick clamp, which engages and locks with the edge of the other movable plate. The two bracket columns will respectively support the tail of the simulated projectile on both sides, and the second clamping device will lock the simulated projectile onto the rear bracket.

[0040] The constant shear force separation mechanism 10 includes a swing arm 17, a shearing rod 18, and a shearing pin 19 mounted on the rear bracket 7. Different specifications of shearing pins can be selected and installed in the constant shear force separation mechanism to enable differentiated launches of simulated missiles. In this embodiment, the magnitude of the shearing pin's breaking stress can be differentiated according to the launch flight parameters of simulated missiles of different weights. By adjusting and changing the diameter of the shearing pin's breaking section, the ultimate tensile force required for the shearing pin to break can be changed, adapting to the launch needs of simulated missiles with different release and takeoff thrust requirements, thus achieving differentiated launch requirements for simulated missiles.

[0041] In this embodiment, the booster bracket 8 includes a lifting support 36, and an arc-shaped support plate 38 is connected to a groove on the inner wall of the lifting support and slides back and forth. The lifting support 36 is provided with connecting bosses on both sides, and the lifting support is connected to the support rocker arms 35 symmetrically arranged on both sides through the connecting bosses, and the height of the lifting support 36 can be adjusted by sliding up and down along the groove on the support rocker arm. A support plate 37 is connected between the two support rocker arms 35. The support plate is connected to the support rocker arms 35 with screws. The lifting screw installed on the support plate is connected to the bottom of the lifting support 36, which can pull the lifting support to move up and down. The bottom of the support rocker arm 35 is provided with a spline transmission hole. The two spline shafts are simultaneously inserted into the bearing hole of the booster torsion spring support and the above-mentioned spline transmission hole from both sides and locked with nuts. A tapered bearing, a bearing baffle, a torsion spring pressure plate, a torsion spring and a torsion spring baffle are sequentially installed at the long shaft end of the spline shaft. The bearing baffle is fixed to the outer shell of the booster torsion spring support 40 with bolts. The torsion spring is pressed at one end by the torsion spring pressure plate and fixed to the outside of the bearing baffle with screws. The torsion spring baffle is connected to the head of the long shaft end of the spline shaft to prevent the torsion spring from sliding out during extension and retraction. The booster torsion spring support 40 is fixedly installed on the crossbeam at the tail of the launch pad. When the support booster bracket rotates upward around the spline axis, the two ends of the torsion spring will generate a rotational force to restore the torsion angle due to the change in the relative torsion angle. The rotational force is synchronously transmitted to the two support rocker arms through the connected spline shaft, and at the same time, it drives the connected booster support structure to rotate forward to achieve the same rotation.

[0042] The socket release and tilting mechanism 9 is installed on the side of the launcher 5, including a splined shaft support and a tilting support rod 39. A splined hole at the bottom of the tilting support rod is installed on the splined shaft. A push rod motor 16 is installed at the top of the tilting support rod. A release traction rod is connected to the push rod of the push rod motor, and the release traction rod is connected to the communication cable plug. The push rod motor 16 pulls the release traction rod to move and cause the communication cable plug to separate from the communication interface socket of the simulated missile. The splined shaft support contains the same tapered bearing, bearing cap, torsion spring pressure plate, torsion spring, and torsion spring baffle as the torsion spring support at the bottom of the front bracket, which can apply a rotational torque to tilt the tilting support rod to one side. When the tilting support rod is held vertically, releasing the supporting hands allows the tilting support rod to tilt to one side along the splined axis under the rotational torque of the torsion spring.

[0043] The working process of the towed simulated missile launcher in this embodiment is as follows:

[0044] When hoisting the simulated missile, the front bracket 6 is fixed to the launcher 5 by the locking pin. The mobile crane is operated to align the positioning hole under the head of the simulated missile with the pin 15 in the middle of the arc-shaped bracket. Then, the simulated missile is slowly moved and placed on the front and rear brackets. The ratchet wrench on the rotary drive is pulled to raise the launcher. The support rod on the base frame 1 is flipped to lock the launcher 5 in the tilted firing position. The locking pin on the torsion spring support at the bottom of the front bracket is pulled out. The front bracket 6 will not fall forward due to the weight of the simulated missile. The pin 15 locks the simulated missile body so that it will not slide backward due to the tilted placement of the missile body. The booster and adapter are lifted and inserted into the docking interface on the belly of the simulated missile. The booster bracket is flipped and swung backward to the position of the limit screw. The booster tail tube is placed on the arc-shaped support. At this time, the booster bracket will rely on the weight of the booster and adapter to maintain the tilted support state. The collapsing support rod of the socket release mechanism is brought vertically close to the missile's communication interface. The launch communication cable plug is inserted into the communication interface socket of the simulated missile. The release traction rod is connected to the tail of the communication cable plug and the connecting pin is locked. At this time, the collapsing support rod will rely on the clamping force between the plug and the socket to maintain the vertical docking communication state.

[0045] After the commander issues the ignition command, the engine ignites and starts. The push rod motor on the socket release and collapse mechanism pulls the release lever to pull out the communication cable plug. The socket release and collapse mechanism automatically unlocks and separates. The collapse support rod of the socket release and collapse mechanism will rely on the torsion spring's rotational torque to flip and collapse to the left to avoid the impact. After the engine completes the stage transition and acceleration, the commander issues the launch command again. At this time, the booster ignites and ejects the plug. When the booster thrust reaches the shear pin set by the shearing tension installed in the fixed shear force separation mechanism, the shear pin breaks, releasing the simulated missile and flying away from the launcher. The shearing lever in the fixed shear force separation mechanism, along with the broken shear pin, unfolds to both sides to avoid the impact. At the same time, the front bracket supporting the missile body unlocks its support state, and the pin on the arc-shaped bracket separates from the missile body. The front bracket flips forward to avoid the booster tail tube by the torsion spring's rotational torque. The booster bracket unlocks its tilt support state and, with the torsion spring's rotational torque, collapses and separates forward along with the booster tail tube.

[0046] The above description is merely a specific embodiment of this utility model, but the protection scope of this utility model is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this utility model should be included within the protection scope of this utility model. Therefore, the protection scope of this utility model should be determined by the protection scope of the claims.

Claims

1. A towed simulated missile launcher, characterized in that, The system includes a base frame and front and rear axle suspensions mounted on the base frame. The base frame is supported on the ground by front tires mounted on the outside of the front axle suspension wheel hubs and rear tires mounted on the outside of the rear axle suspension wheel hubs. Support and anchoring mechanisms are respectively provided on the rear sides of the front and rear tires of the base frame. A launcher is mounted on the upper surface of the base frame. The launcher is raised and lowered by a rotary drive motor connected to it. The front bracket, booster bracket, and rear bracket are sequentially installed at the front, middle and rear, and tail ends of the launcher. A fixed shear force separation mechanism is also installed on the rear bracket. A socket release and collapse mechanism is installed on the side of the launcher. The socket release and collapse mechanism is used to connect the communication cable before the simulated missile is launched and to disconnect the connection after the launch command is issued.

2. The towed simulated missile launcher as described in claim 1, characterized in that, The front axle suspension is mainly composed of a leaf spring structure installed inside the front wheel hub, and the rear axle suspension is mainly composed of another leaf spring structure installed inside the rear wheel hub. The leaf spring damping structure is made by stacking and bundling steel plates of different lengths together, and installing them on the front axle and rear axle rods with U-shaped screws in the middle. The two ends of the top layer of steel plates are bent into cylindrical hinge holes, which are respectively installed in the front leaf spring support and the swing rocker in the rear leaf spring support on the side of the base frame 1.

3. The towed simulated missile launcher as described in claim 1, characterized in that, The aforementioned support and anchoring mechanism includes a fixed support fixed on the base frame, a rotating support rod installed in the fixed support, the fixed support being hinged to the rotating support rod via a pin, a lifting handwheel installed in a semi-circular groove at the bottom of the swing end of the rotating support rod, and an anchoring support rod passing through the swing end of the rotating support rod and the threaded hole of the lifting handwheel, with its bottom connected to an anchoring plate that is in contact with the ground.

4. The towed simulated missile launcher as described in claim 3, characterized in that, The lower end of the anchor plate has wavy spikes that can be driven into the ground.

5. The towed simulated missile launcher as described in claim 1, characterized in that, The front bracket includes two symmetrically arranged bracket columns and an arc-shaped bracket. The two bracket columns and the arc-shaped bracket are integrated into one structure. The top of the bracket column is connected to a clamping device that locks the simulated bullet onto the front bracket. Two sets of torsion spring assemblies are installed at the spline hole at the bottom of the bracket column.

6. The towed simulated missile launcher as described in claim 5, characterized in that, A pin is installed on the arc-shaped bracket to align with the positioning hole of the simulated projectile. The pin is inserted into the positioning hole to position the simulated projectile.

7. The towed simulated missile launcher as described in claim 1, characterized in that, The booster bracket includes a lifting support, an arc-shaped support plate that is slidably connected to the inner wall groove of the lifting support, a connecting boss on the outer side of the lifting support, the lifting support being connected to the support rocker arms symmetrically arranged on both sides through the connecting boss, and the height of the lifting support can be adjusted by sliding up and down along the support rocker arm groove, the two support rocker arms are connected by a support plate to form a booster bracket support structure, and two sets of torsion spring assemblies are installed at the spline hole at the lower end of the support rocker arm.

8. The towed simulated missile launcher as described in claim 1, characterized in that, The socket release and tilting mechanism includes a spline shaft support and a tilting support rod. A spline shaft is installed inside the spline shaft support. The spline hole at the bottom of the tilting support rod is installed on the spline shaft. A push rod motor is connected to the top of the tilting support rod. A release traction rod is connected to the push rod of the push rod motor. The release traction rod is connected to the communication cable plug. The push rod motor pulls the release traction rod to move and cause the communication cable plug to separate from the socket. A set of torsion spring assemblies is installed inside the spline shaft support.

9. The towed simulated missile launcher as described in claim 7 or 8, characterized in that, The torsion spring assembly includes a splined shaft, on which a tapered bearing, a bearing baffle, a torsion spring, and a torsion spring baffle are sequentially mounted. A torsion spring pressure plate is provided at the bottom end of the torsion spring. The torsion spring pressure plate is used to lock the torsion spring. The bearing baffle presses the bearing tightly and prevents the torsion spring from sliding out during extension and retraction. A gap is left between the bearing baffle and the torsion spring baffle for the extension and retraction of the torsion spring.

10. The towed simulated missile launcher as described in claim 1, characterized in that, The rear bracket is equipped with a fixed shear force separation mechanism, which includes a swing arm, a shearing rod, and a shearing pin for accumulating force and releasing force.

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