Simulated bomb launcher

Abstract

A simulated bomb launcher belongs to the technical field of simulated bomb launching. The tail nozzle bracket, the booster support, the pulling support, the missile wing support and the bottom frame inclined strut are sequentially connected from the tail end to the front end of the bottom frame, and the lower end of the bottom frame inclined strut is connected with an anchoring steel chisel through an anchoring plate to be supported on the ground. The simulated bomb launcher is suitable for conducting simulated bomb maneuvering launching on the rugged ground such as gobi and desert, the anchoring plate can be anchored to the ground after a steel chisel is hit into the anchoring plate, and the simulated bomb launcher has the functions of simulated bomb launching supporting, posture correction, booster lifting, plug pulling-out and ignition cable shearing and the like. The bottom frame is of a leap-type scissor supporting structure, anchoring and level adjusting can be carried out on the uneven ground, transition maneuvering and rapid launching of a simulated missile are facilitated, an engine ignition cable plug is pulled out through inertia drawing separation, a booster ignition cable is pulled out through inertia cutting separation, and the launcher is simple and light in structural design and suitable for batch configuration.

Description

Technical Field

[0001] This invention belongs to the field of simulated missile launching technology, and specifically relates to a simulated missile launcher. Background Technology

[0002] The existing fixed launcher base is a rectangular frame structure. The regular basic frame structure provides a reliable guarantee for supporting the projectile, which is conducive to the adjustment and installation of the support structure. During launch preparation, the launcher can be directly moved to a flat ground and anchored. It is suitable for installation and use on a fixed launch platform in a test range. If the simulated projectile is to be launched in the field, the launch site needs to be leveled in advance, which is not conducive to the rapid deployment and mobile arrangement of the launcher. Summary of the Invention

[0003] In view of the shortcomings of the existing technology, the purpose of this invention is to provide a simulated missile launcher.

[0004] The technical solution adopted in this invention is as follows: a simulated missile launcher, the key technical points of which are: it includes an inclined base frame, from which a tail nozzle bracket, a booster support, a release bracket, a missile wing bracket, and a base frame diagonal brace are sequentially connected from the tail end to the front end of the base frame; both the missile wing bracket and the base frame diagonal brace are foldably connected to the tail end of the base frame, and are located on the upper and lower sides of the tail end of the base frame; a shear support is also installed on the base frame, the shear support includes a shear seat and a shear pressure plate, the shear seat is fixedly connected to the inner side of the longitudinal beam of the base frame, the upper side of the shear seat has a sliding groove, the bottom of the shear seat has a clearance groove, the shear pressure plate is inserted into the shear seat through the sliding groove to press the ignition cable passing through the clearance groove, and a blade is provided at the contact point between the shear pressure plate and the ignition cable.

[0005] Preferably, the wing support includes a support rod installed in a stable support on the base frame and a wing bracket connected to the top support of the support rod, with an anti-slip rubber plate attached to the supporting surface of the wing bracket.

[0006] Preferably, the release bracket includes a release support mounted on the left longitudinal beam of the base frame, a release support rod installed inside the release support, a locking plate fixedly connected to the top of the release support rod by bolts, and a traction steel cable passing through the thread hole of the locking screw head and then being pressed into the square hole of the locking plate by a nut.

[0007] Preferably, the bottom end of the base frame diagonal brace is connected to an anchor plate, and the anchor plate is connected to an anchoring steel rod for supporting and anchoring the base frame to the ground.

[0008] Preferably, the tail nozzle bracket includes a bracket support rod and a pair of diagonal braces hinged together. An arc-shaped support for supporting the tail shell of the simulated projectile is connected to the top of the tail nozzle bracket. The tail end of the arc-shaped support is provided with a boss to prevent the tilted simulated projectile from sliding backward. A protective cover is also installed on the arc-shaped support.

[0009] The beneficial effects of this invention are as follows: The simulated missile launcher includes an inclined base frame, from which a tail nozzle bracket, booster support, pull-out bracket, missile wing bracket, and base frame diagonal brace are sequentially connected from the tail end to the front end. The missile wing bracket and base frame diagonal brace can be folded and fitted onto the upper and lower surfaces of the front end of the base frame, respectively. The base frame diagonal brace is connected to an anchoring steel rod via an anchoring plate, making it suitable for mobile launch of simulated missiles on rugged terrain such as the Gobi Desert and other deserts. The anchoring plate, driven into the steel rod, can be anchored to the ground and adjusted horizontally, providing functions such as launch support, booster lifting, plug pull-out, and ignition cable cutting. The system frame adopts a straddle-type scissor support structure, which can be deployed and anchored on uneven ground, facilitating the mobile deployment and rapid deployment and launch of the simulated missile. The engine ignition cable plug is separated by inertial pull-out, and the booster ignition cable is separated by inertial cutting. The structural design is simple and lightweight, suitable for mass production. Attached Figure Description

[0010] To more clearly illustrate the technical solutions in the embodiments of the present invention 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 the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0011] Figure 1 This is a front view of a novel simulated missile launcher according to an embodiment of the present invention, wherein (a) is a front view of the launcher; and (b) is a side view of the launcher.

[0012] Figure 2 This is a side view of a novel simulated missile launcher according to an embodiment of the present invention;

[0013] Figure 3 This is a top view of a novel simulated missile launcher folded in an embodiment of the present invention;

[0014] Figure 4 This is a view from direction A of a novel simulated missile launcher according to an embodiment of the present invention;

[0015] Figure 5 This is a structural diagram of the base frame in an embodiment of the present invention, wherein (a) is a front view of the base frame; and (b) is a top view of the base frame.

[0016] Figure 6 This is a schematic diagram of the base frame diagonal brace structure in an embodiment of the present invention, wherein (a) is a front view of the base frame diagonal brace; (b) is a side view of the base frame diagonal brace; and (c) is a top view of the base frame diagonal brace.

[0017] Figure 7 This is a schematic diagram of the nozzle bracket structure in an embodiment of the present invention, wherein (a) is a front view of the nozzle bracket; and (b) is a side view of the nozzle bracket.

[0018] Figure 8 This is a partial enlarged view of the shearing slider in an embodiment of the present invention;

[0019] Figure 9 This is a schematic diagram of the wing support structure in an embodiment of the present invention, wherein (a) is a front view of the wing support; and (b) is a side view of the release support.

[0020] Figure 10 This is a schematic diagram of the detachment stent structure in an embodiment of the present invention, wherein (a) is a front view of the detachment stent; and (b) is a side view of the detachment stent.

[0021] Figure 11 This is a schematic diagram of the booster support structure in an embodiment of the present invention, wherein (a) is a front view of the booster support; and (b) is a side view of the booster support.

[0022] Figure 12 This is a schematic diagram of the anchoring steel rod structure in an embodiment of the present invention, wherein (a) is a front view of the anchoring steel rod; and (b) is a side view of the anchoring steel rod.

[0023] Figure 13 This is a schematic diagram of the protective nut structure in an embodiment of the present invention, wherein (a) is a front view of the protective nut; and (b) is a side view of the protective nut.

[0024] Figure 14 This is a schematic diagram of the shear support structure in an embodiment of the present invention, wherein (a) is a front view of the shear support; and (b) is a side view of the shear support.

[0025] The meanings of each serial number are as follows:

[0026] 1. Base frame, 2. Base frame diagonal brace, 3. Tail nozzle bracket, 4. Missile wing bracket, 5. Booster support, 6. Pull-out bracket, 7. Shear support, 8. Anchoring steel rod, 9. Protective nut, 10. Anchoring plate, 11. Hinge seat, 12. Support lug, 13. Stabilizing support, 14. Mounting plate, 15. Support beam, 16. Booster support, 17. Adapter plate, 18. Clamp, 19. Protective cover, 20. Shear slider, 21. Shear pin, 22. Support rod, 23. Missile wing bracket, 24. Locking plate, 25. Locking screw, 26. Traction cable, 27. Shear seat, 28. Shear pressure plate, 29. Tilting support rod, 30. Bracket strut, 31. Diagonal brace, 32. Arc-shaped support, 33. Diagonal brace rod. Detailed Implementation

[0027] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the following description is provided in conjunction with the accompanying drawings. Figures 1-14 The present invention will be further described in detail below with reference to specific embodiments.

[0028] Figure 1-4This is an assembly diagram of a novel simulated missile launcher used in this embodiment. It includes an inclined base frame 1, which consists of six supporting crossbeams 15 and two longitudinal beams. The base frame's diagonal bracing 2 includes diagonal bracing rods 33 and flip-up support rods 29. The diagonal bracing rods 33 are composed of an upper crossbeam, a lower crossbeam, and left and right diagonal beams connecting the two crossbeams on either side. A left vertical connecting end is integrally formed at the junction of the upper crossbeam and the left diagonal beam, and a right vertical connecting end is integrally formed at the junction of the upper crossbeam and the right diagonal beam. Adapter plates 17 are connected to both the left and right vertical connecting ends. The diagonal bracing rods 33 are hinged to a mounting plate 14 connected to the front end of the base frame 1 via the adapter plate 17 at their top. An anchoring plate 10 is connected to the bottom end of the diagonal bracing rods 33. The flip-up support rods 29 consist of V-shaped diagonal supports, with the tops of the two supports connected by clamps 18. In this embodiment, anchoring steel rods 8 are inserted into the anchoring plate 10. A protective nut 9 is installed on the top of the anchoring steel rods 8 for driving them into the ground and for pulling them out for retrieval. The threaded connection at the top of the anchoring steel rods 8 is also used for adjusting the horizontal attitude of the launcher. The base frame 1 is anchored to the ground by four anchoring steel rods 8. The head of the protective nut has a traction hole. In this embodiment, the base frame 1 and the base frame diagonal brace 2 adopt a straddle-type scissor support structure. The diagonal brace 33 of the base frame diagonal brace 2 extends outwards and is supported on the ground by the anchoring plate 10 and the anchoring steel rods 8. A flip support rod 29 is installed on the support beam 15 by clamps 18. By rotating the flip support rod 29 backwards and upwards, it unfolds to form a scissor support structure with the diagonal brace 33. Removing the mounting screws on the clamps 18 allows the diagonal brace 33 and the flip support rod 29 to be folded and retracted onto the lower surface of the base frame 1. Utilizing independent anchoring support points that extend forward in a straddle manner, the launcher can be deployed and arranged on uneven and rugged ground. The support frame structure is simple and lightweight, and can be transported and arranged by two people. It is quick and efficient in relocation, mobility and deployment, targeting the low-cost simulated missile launch market.

[0029] The nozzle bracket 3 is installed at the rear end of the longitudinal beam of the base frame and includes a bracket support rod 30 and a diagonal brace 31 connected to each other. The bottom of the bracket support rod 30 is installed in the hinge seat 11 of the base frame 1, and one end of the diagonal brace 31 is installed in the middle lug of the bracket support rod 30, and the other end is installed on the lug 12 of the base frame 1, forming a stable support structure for the nozzle bracket. After removing the mounting screws at the connection end of the diagonal brace 31 to the base frame 1, the nozzle bracket 3 can be folded and stored together with the diagonal brace 31 on the upper surface of the base frame 1. An arc-shaped support 32 supporting the tail shell of the simulated projectile is connected to the top of the nozzle bracket 3. A groove is made in the middle of the arc-shaped support 32, and a shearing slider 20 that can move back and forth along the groove is installed in the groove. A traction screw is connected to the tail of the shearing slider 20. Rotating the traction screw can pull the shearing slider 20 to move back and forth along the groove. The shearing pin 21 is inserted into the positioning hole in the shearing slider 20 and connected and locked with the threaded hole of the simulated projectile body. In this embodiment, a protective cover 19 is also connected to the arc-shaped support 32. A certain gap is maintained between the protective cover 19 and the shell of the simulated missile tail nozzle to prevent the simulated missile, which is placed at an angle, from accidentally slipping off during the launch preparation process.

[0030] In this embodiment, the wing support 4 is installed in the stabilizing support 13 at the front end of the longitudinal beam of the base frame. It includes a support rod 22 and a wing bracket 23 connected to the top of the support rod 22. The support rod 22 and the wing bracket 23 can be folded and snugly attached to the upper surface of the base frame 1. In this embodiment, an anti-slip rubber plate is attached to the supporting surface of the wing bracket 23.

[0031] In this embodiment, the booster support 5 includes a booster bracket 16 mounted on the base frame 1. The booster bracket 16 is connected to the booster support rod via a rotating shaft, and a torsion spring is mounted on the rotating shaft. A limit screw is provided at the top of the booster bracket 16, which is arranged on the rotation path of the booster support rod to lock and adjust the rotation stroke of the booster support rod. When the booster support 5 is held by both hands and flipped upward against the limit screw, the torsion spring is in a torsional storage state. When the hands are released, the booster support 5 can complete the forward flipping and falling action with the help of the rebound torque of the torsion spring and the eccentric gravity. The top of the booster support rod is also connected to a support seat for lifting the booster and adjusting its height.

[0032] In this embodiment, the release bracket 6 is installed on the release support in the middle of the base frame, including a release support rod installed in the release support. The locking plate 24 is connected to the top of the release support rod by screws. After one end of the traction cable 26 passes through the wire hole on the locking screw 25, the head of the locking screw 25 is fixed to the locking plate 24 with a nut to press the traction cable 26. The other end of the traction cable 26 is fixed to the power cable plug. When using the aforementioned pull-out bracket 6, first insert the power cable plug into the power socket on the side of the simulated missile casing. Fix one end of the traction cable 26 to the root of the power cable plug, and straighten the other end by passing it through the wire hole on the locking screw 25. Use a nut to press and fix the locking screw 25 and the traction cable 26 together onto the locking plate 24. Suspend one end of the avoidance tension spring at the tail of the power cable plug and the other end on the locking plate 24. Adjust the tension of the tension spring to ensure that the power cable plug will not be pulled out. At the moment the simulated missile is launched and flies away from the launch pad, the takeoff inertia will pull the power cable plug fixed to the head of the traction cable out of the socket. The rebound tension of the tension spring will drive the power cable and plug to the side to avoid collision with the missile body, thus completing the separation and avoidance of the communication cable.

[0033] The shear support 7 in this embodiment includes a shear seat 27 and a shear pressure plate 28. The shear seat 27 is fixedly connected to the inner side of the longitudinal beam of the base frame. The shear pressure plate 28 is inserted into the groove on the side wall of the shear seat 27 to press the booster ignition cable. The cable is then sheared off by inertia as it flies backward. During launch preparation, the shear pressure plate 28 is removed from the shear support 27, and the energized end of the ignition cable on the booster tail nozzle is placed into the clearance groove at the bottom of the shear seat 27. The shear pressure plate 28 is then inserted along the groove on the side wall of the shear seat to press the ignition cable, completing the preparation for shearing the ignition cable. The other end of the ignition cable passes through the plug and is connected to the solid propellant inside the booster. When the simulated missile is launched, the booster ignites and ejects the plug, pulling the ignition cable backward. The inertial force of the flight acts on the blade where the ignition cable contacts the shear pressure plate, cutting the cable connected to the plug, thus achieving the separation of the booster ignition cable.

[0034] In this embodiment, the base frame 1, base frame diagonal brace 2, tail nozzle bracket 3, and missile wing bracket 4 adopt a welded and assembled structure, while the pull-out bracket 6, booster support 5, and shear support 7 adopt a machined and assembled structure.

[0035] During the hoisting of the simulated missile, the engine exhaust pipe at the tail of the simulated missile is first placed on the arc-shaped support inside the protective shield 19, and the missile wings are placed on the missile wing bracket 23. The shear pin 21 is inserted into the shear slider 20 to lock the simulated missile. The booster and adapter are lifted and inserted into the interface on the belly of the simulated missile. The booster support rod is flipped backward to fit against the head of the limit screw. The booster tail tube is supported and placed on the support seat at the top of the booster support rod. The lifting screw is rotated to adjust the height of the support seat and confirm the booster pushing angle. At this time, the booster support 5 will be supported by the weight of the booster and adapter. In the simulated missile power socket, insert the engine power cable plug into the power socket, straighten the traction cable 26 suspended on the socket, insert it into the wire hole on the locking screw 25, and then tighten it on the locking plate 24 with a nut. Hang one end of the avoidance tension spring on the tail of the power cable plug and the other end on the locking plate. Adjust the tension of the tension spring to ensure that the power cable plug will not be pulled out. Take out the shearing pressure plate 28 in the shear seat 27, put the booster ignition cable into the bottom groove of the shear seat 27, and insert the shearing pressure plate 28 along the side wall groove into the shear seat 27 to press the ignition cable.

[0036] When the simulated missile is launched, the booster ignites and ejects the plug, causing the traction ignition cable to be thrown backward and cut off by the shearing plate blade. When the booster ignition thrust reaches the shearing force set by the shearing pin, the shearing pin breaks, releasing the simulated missile from the launch pad. The traction cable connected to the cable plug on the release bracket pulls out the energized cable plug due to the inertia of the simulated missile as it flies away. The tension spring at the end of the plug pulls the energized cable plug to the side and rear to avoid it. Under the action of the torsion spring's rebound torque and the eccentric gravity of the support rod itself, the booster support 5 flips forward along with the booster tail tube to avoid it.

[0037] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention 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 the present invention should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A simulated missile launcher, characterized in that, The system includes an inclined underframe, from which a tail nozzle bracket, booster support, release bracket, missile wing bracket, and underframe diagonal brace are sequentially connected from the rear to the front. Both the missile wing bracket and the underframe diagonal brace are foldable and connected to the rear of the underframe, and are located on the upper and lower sides of the rear of the underframe. A shear support is also installed on the underframe, which includes a shear seat and a shear pressure plate. The shear seat is fixedly connected to the inner side of the longitudinal beam of the underframe. The upper side of the shear seat has a sliding groove, and the bottom of the shear seat has a clearance groove. The shear pressure plate is inserted into the shear seat through the sliding groove to press the ignition cable that passes through the clearance groove. A blade is provided at the contact point between the shear pressure plate and the ignition cable.

2. The simulated missile launcher as described in claim 1, characterized in that, The aforementioned wing support includes a support rod installed in a stable support on the base frame and a wing bracket connected to a support at the top of the support rod. An anti-slip rubber plate is attached to the supporting surface of the wing bracket.

3. The simulated missile launcher as described in claim 1, characterized in that, The aforementioned release bracket includes a release support mounted on the left longitudinal beam of the base frame, a release support rod installed inside the release support, a locking plate fixedly connected to the top of the release support rod by bolts, and a traction steel cable passing through the thread hole of the locking screw head and then being tightened in the square hole of the locking plate by a nut.

4. A simulated missile launcher as described in claim 1, characterized in that, An anchor plate is connected to the bottom end of the base frame diagonal brace, and anchoring steel rods are connected to the anchor plate to support and anchor the base frame to the ground.

5. A simulated missile launcher as described in claim 1, characterized in that, The tail nozzle bracket includes a bracket support rod and a pair of diagonal braces hinged together. An arc-shaped support is connected to the top of the tail nozzle bracket to support the tail shell of the simulated projectile. The tail end of the arc-shaped support is provided with a boss to prevent the tilted simulated projectile from sliding backward. A protective cover is also installed on the arc-shaped support.

Images