Simple launcher for simulated bomb

Abstract

The utility model discloses a simple simulated bomb launcher and belongs to the technical field of simulated bomb launching. The booster bracket comprises a missile wing front bracket for supporting a simulated missile and an exhaust nozzle bracket, the booster bracket is mounted in the middle of the underframe, and the booster bracket overturns along with the booster by utilizing torsional force generated by a torsional spring arranged in a support rotating shaft; a draw bar and a plug on the top of the socket pulling-out support are matched with a socket of the simulation bullet in an inserted mode and fall towards the side face of the launching direction of the simulation bullet under the action of eccentric gravity after being separated from the socket. The launcher adopts a fixed support structure, has the characteristics of light weight, convenience in transition and movement, simplicity in operation and the like, reduces the launching preparation time and operation links, changes the existing exercise confrontation mode, and provides a brand-new application platform for simulated striking training of simulated bullets.

Description

Technical Field

[0001] This utility model belongs to the field of simulated missile launching technology, and specifically relates to a simple simulated missile launching rack. Background Technology

[0002] Simulated missiles are typically launched from launch vehicles, which are the main application platform for simulated missile launches. Although they are much simpler to operate than missile launch vehicles, their convenience, stability, and applicability still cannot meet the ever-changing needs of simulated missiles for simulated strike and combat training. Summary of the Invention

[0003] In view of the shortcomings of the existing technology, the purpose of this utility model is to provide a simple launcher for simulated missiles.

[0004] The technical solution adopted by the utility model is as follows: a simple launcher for a simulated missile, the key technical points of which are: a base frame and a wing front support, a booster bracket, a socket release bracket, and a tail nozzle bracket connected to the base frame; the wing front support and the tail nozzle bracket are respectively located at the head and tail of the base frame, and the booster bracket and the socket release bracket are located between the two; brackets supporting the simulated missile wing surfaces are symmetrically installed on both sides of the top of the wing front support; the booster bracket is rotatably connected to the base frame support and rotates with the booster using the torsional force generated by the torsion spring set on the pivot of the support; the top traction rod and plug of the socket release bracket are inserted and engaged with the socket of the simulated missile, and after being separated from the socket, it falls to the side in the direction of simulated missile launch under the action of eccentric gravity.

[0005] Furthermore, the tail nozzle bracket includes a main support and an arc-shaped support connected to the top of the main support. The arc-shaped support has a groove, and a shearing slider that slides along the groove is provided in the groove. A locking screw is embedded in the shearing slider and pulls the shearing slider to move back and forth.

[0006] Furthermore, the shear pin protrudes from the shearing surface of the shearing slider and is connected to the connecting hole in the belly of the simulated projectile by a thread, which is used to position and lock the simulated projectile.

[0007] Furthermore, the tail nozzle bracket also includes a secondary bracket hinged to the main bracket, and the main bracket, the secondary bracket, and the base frame support are hinged to form a tail nozzle support structure.

[0008] Furthermore, the booster bracket includes a booster support mounted on the base frame. The booster support is connected to the booster support rod via a pivot. A torsion spring is mounted on the pivot and provides a torsional force that moves with the booster during launch.

[0009] Furthermore, the socket release bracket includes a support fixed on the base frame, a support rod installed on the support, a push rod motor connected to the top of the support rod, a release traction rod connected to the push rod of the push rod motor, the release traction rod connected to the plug, and the push rod motor controlling the separation of the plug from the socket.

[0010] Furthermore, it also includes a rear wing support, wherein the front wing support is hinged to the rear wing support to form a simulated wing surface support structure.

[0011] Furthermore, a reference plate for correcting the position of the simulated projectile is installed at the front end of the bracket.

[0012] The beneficial effects of this utility model are as follows: The simplified launcher for the simulated missile includes a front support bracket for the missile wings and a tail nozzle bracket to support the simulated missile. The booster bracket is rotatably connected to the base support and rotates with the booster using the torsional force generated by the torsion spring installed in the support. The traction rod and plug at the top of the socket release bracket are engaged with the simulated missile socket and, after separating from the socket, fall to the side in the direction of simulated missile launch under the action of eccentric gravity. The launcher adopts a fixed support structure, which is lightweight, easy to move and operate, and reduces launch preparation time and operation steps. It changes the existing exercise confrontation mode and provides a brand-new application platform for simulated missile strike training. Attached Figure Description

[0013] 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.

[0014] Figure 1 This is a front view of the simplified launcher for the simulated missile in an embodiment of this utility model;

[0015] Figure 2 This is a top view of the simplified launcher for the simulated missile folded in an embodiment of this utility model;

[0016] Figure 3 This is a side view of a simplified launcher for a simulated missile in an embodiment of this utility model;

[0017] Figure 4 This is a view from direction A of the simplified launcher for the simulated missile in this embodiment of the present invention;

[0018] Figure 5 This is a front view of the base frame in an embodiment of this utility model;

[0019] Figure 6 This is a side view of the base frame in an embodiment of the present utility model;

[0020] Figure 7 This is a top view of the base frame in an embodiment of this utility model;

[0021] Figure 8 This is a front view of the missile wing front support in an embodiment of this utility model;

[0022] Figure 9 This is a side view of the front support of the missile wing in an embodiment of this utility model;

[0023] Figure 10 This is a front view of the rear support bracket of the missile wing in an embodiment of this utility model;

[0024] Figure 11 This is a side view of the rear support bracket of the missile wing in an embodiment of this utility model;

[0025] Figure 12 This is a front view of the simulated missile tail nozzle bracket in an embodiment of this utility model;

[0026] Figure 13 This is a side view of the simulated missile tail nozzle bracket in an embodiment of this utility model;

[0027] Figure 14 This is a partial enlarged view of the shearing slider in an embodiment of this utility model;

[0028] Figure 15 This is a front view of the booster bracket in an embodiment of the present invention;

[0029] Figure 16 This is a side view of the booster bracket in an embodiment of the present invention;

[0030] Figure 17 This is a front view of the socket release bracket in an embodiment of this utility model;

[0031] Figure 18 This is a side view of the socket release bracket in an embodiment of the present invention;

[0032] The meanings of each number are as follows: 1. Base frame, 2. Front wing support, 3. Rear wing support, 4. Tail nozzle bracket, 5. Booster bracket, 6. Socket release bracket, 7. Anchoring steel rod, 8. Protective nut, 9. Anchoring plate, 10. Irregular support, 11. Hinge support, 12. Support, 13. Booster support, 14. Bracket, 15. Reference plate, 16. Locking screw, 17. Shearing slider, 18. Shearing pin, 19. Torsion spring, 20. Push rod motor, 21. Protective cover, 22. Arc-shaped support, 23. Booster support rod, 24. Rotary shaft, 25. Limiting screw, 26. Support base. Detailed Implementation

[0033] 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 1-18The present invention will be further described in detail below with reference to specific embodiments.

[0034] The simplified launcher for the simulated missile in this embodiment includes a base frame 1 and a front wing support 2, a rear wing support 3, a tail nozzle bracket 4, a booster bracket 5, and a socket release bracket 6 connected to the base frame 1. The base frame 1, front wing support 2, rear wing support 3, and tail nozzle bracket 4 are welded structures, while the socket release bracket 6 and booster bracket 5 are machined and assembled structures. The front wing support 2 is connected to the front end of the base frame 1, and the tail nozzle bracket 4 is connected to the rear end of the base frame 1. The head of the simulated missile is supported by the front wing support 2, and the tail is supported by the tail nozzle bracket 4. The booster bracket 5 and the socket release bracket 6 are positioned between the front wing support 2 and the tail nozzle bracket 4.

[0035] In this embodiment, an anchor plate 9 is installed at the bottom of the base frame 1. The anchor plate 9 serves as a support point for the launcher. Anchor steel rods 7 are inserted into the anchor plate 9, and the base frame 1 is anchored to the ground by the anchor steel rods 7. In this embodiment, the top of the anchor steel rods 7 is protected by a protective nut 8 to prevent thread damage. The horizontal adjustment of the base frame 1 is achieved by adjusting the relative length of the anchor steel rods 7 passing through the anchor plate 9. This is suitable for simulating missile launches in Gobi or desert terrain. After the anchor plate 9 is driven into the anchor steel rods 7, it can be anchored to the ground and the base frame 1 can be leveled, providing support for simulated missile launches and correcting launch attitude.

[0036] In this embodiment, the wing-front support 2 is mounted on the front edge of the base frame 1. Its structure includes two symmetrically arranged vertical arms and at least two horizontal arms connecting the two vertical arms. The wing-front support 2 is a one-piece welded structure. The width between the two vertical arms is wider at the bottom and narrower at the top. The top of each vertical arm is a free end connected to a bracket 14, which supports the simulated wing surface. In this embodiment, the supporting surface is adapted to the width of the simulated wing to prevent the wing from slipping and falling. This width can be adjusted according to the width of the simulated wing. A reference plate 15 is also installed at the front end of the bracket 14, which is used to correct the position of the simulated missile. The lower ends of the two vertical arms are respectively mounted in two irregularly shaped supports 10 via pins. The two irregularly shaped supports 10 are located on the front edge of the base frame 1. In this embodiment, the wing-front support 2 is hinged to the wing-rear support 3, forming a stable triangular support structure with the base frame 1. In this embodiment, the rear support 3 of the missile wing is mainly composed of two symmetrically arranged vertical rods and a horizontal rod connecting the two vertical rods. The upper end of the vertical rod is hinged to the lugs respectively provided on the two vertical arms of the front support 2 of the missile wing. The lower end of the vertical rod of the rear support 3 of the missile wing is installed in the hinge support 11 located on the base frame 1 through a pin. The hinge support 11 and the irregular support 10 are respectively fixed on the frame and the crossbeam arranged in front and behind on the base frame 1.

[0037] The tail nozzle bracket 4 in this embodiment includes a main bracket, a secondary bracket, and an arc-shaped support. The main bracket and the secondary bracket are hinged to form a stable triangular support structure. The main bracket includes two symmetrically arranged pillars. The bottoms of the two pillars are respectively installed in the irregular support 10 at the tail of the base frame 1. The two secondary brackets are respectively hinged to the corresponding pillars of the main bracket. The bottoms of the secondary brackets are installed in the support 12 at the tail of the base frame 1. The irregular support 10 and the support 12 are respectively fixed to the frame and the crossbeam on the base frame 1. An arc-shaped support 22 supporting the tail of the simulated projectile is installed on the top of the main bracket. A groove is made on the arc-shaped support 22. A shearing slider 17 that can move along the groove is provided in the groove. A locking screw 16 is embedded in the shearing slider 17. Rotating the locking screw 16 can pull the shearing slider 17 to move back and forth along the groove. After the position is determined, the shearing pin 18 can pass through the shearing surface on the shearing slider 17 and the arc-shaped support 22 and be inserted into the threaded hole on the belly of the simulated projectile to lock the simulated projectile.

[0038] In this embodiment, a protective cover 21 is provided on the upper part of the arc-shaped support 22, and the tail of the simulated missile is placed inside the protective cover 21 to prevent accidental slippage during the hoisting, technical support and electrical debugging of the simulated missile.

[0039] The booster bracket 5 in this embodiment includes a booster support 13 mounted on the base frame 1. The booster support 13 is connected to the booster support rod 23 via a pivot 24, and a torsion spring 19 is mounted on the pivot 24. Releasing the support arms allows the booster bracket 5 to flip forward using the torsion spring 19. A limit screw 25 is also provided on the booster support 13, which limits and locks the travel of the booster support rod 23 along its rotational path. A support seat 26 for supporting the booster's vertical movement is also connected to the top of the booster support rod 23.

[0040] The socket release bracket 6 in this embodiment includes a support rod with weight-reducing holes. The bottom of the support rod is installed in a support in the middle of the base frame 1. One end of a limiting chain is connected to the side wall of the support, and the other end of the limiting chain is connected to the support rod. The limiting chain can prevent the socket release bracket 6 from directly impacting the ground and damaging the push rod motor after it flips over. A push rod motor 20 is installed at the top of the support rod. A release traction rod is connected to the push rod of the push rod motor 20. The release traction rod is connected to the release plug. The push rod motor 20 can pull the release traction rod to move and cause the plug to separate from the socket. When the support is released, the socket release bracket 6 can rotate along the axis and fall to the left under the action of eccentric gravity.

[0041] The working process of the simplified launcher for the simulated missile in this embodiment is as follows:

[0042] During the hoisting of the simulated missile, the tail nozzle of the simulated missile is first placed on the arc-shaped support inside the protective cover 21, and the missile wings are placed on the bracket 14. Because the support point of the missile wings is very close to the center of mass of the simulated missile, it is necessary to install shear pins 18 to lock the simulated missile to prevent the simulated missile from shaking due to excessive wind force or engine ignition thrust fluctuations during launch. The booster and adapter are lifted and inserted into the interface on the belly of the simulated missile. The booster bracket 5 is flipped to the position of the limit screw. The booster tail tube is supported and placed on the support 12. The lifting screw is rotated to adjust the push angle of the booster. At this time, the booster bracket 5 will be supported by the weight of the booster and adapter. After the communication cable plug is inserted, the socket disconnect bracket 6 will be supported by the clamping force set between the plug and the simulated missile socket to maintain the vertical connection.

[0043] After the simulated missile engine ignites and enters the launch state, the push rod motor 20 located at the top of the socket release bracket 6 is activated first to pull out the plug, the socket release bracket 6 is unlocked, the support rod of the socket release bracket 6 rotates along the pivot and falls to the left to avoid it. When the booster ignition thrust reaches the shearing force set by the shear pin 18, the shear pin breaks and releases the simulated missile to fly away from the launcher. The booster bracket 5 follows the booster and flips to avoid it.

[0044] 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 simple launcher for simulating projectiles, characterized in that, The system includes a base frame and a wing forward support, a booster bracket, a socket release bracket, and a tail nozzle bracket connected to the base frame. The wing forward support and tail nozzle bracket are respectively located at the head and tail of the base frame, while the booster bracket and socket release bracket are located between them. Brackets supporting the simulated missile wing surfaces are symmetrically arranged on both sides of the top of the wing forward support. The booster bracket is connected to a support on the base frame and rotates in the direction of booster launch using the torsional force generated by a torsion spring on the support shaft. The traction rod and plug at the top of the socket release bracket are inserted into the socket of the simulated missile and, after separating from the socket, fall to the side in the direction of simulated missile launch under the action of eccentric gravity.

2. The simplified launcher for simulated projectiles according to claim 1, characterized in that: The tail nozzle bracket includes a main support and an arc-shaped support connected to the top of the main support. The arc-shaped support has a groove, and a shearing slider that moves along the groove is provided in the groove. A locking screw is embedded in the shearing slider and pulls the shearing slider to move back and forth.

3. The simplified launcher for simulated projectiles according to claim 2, characterized in that: After passing through the shearing surface of the shearing slider, the shearing pin connects to the assembly hole on the belly of the simulated projectile, which is used to position and lock the simulated projectile.

4. The simplified launcher for simulated projectiles according to claim 2, characterized in that: The tail nozzle bracket also includes a secondary bracket hinged to the main bracket. The main bracket, secondary bracket, and base frame supports are hinged to form a tail nozzle support structure.

5. The simplified launcher for simulated projectiles according to claim 1, characterized in that: The booster bracket includes a booster support mounted on the base frame. The booster support is connected to the booster support rod via a pivot. A torsion spring is mounted on the pivot of the booster support, providing a torsional force that moves synchronously with the booster when it moves.

6. The simplified launcher for simulated projectiles according to claim 1, characterized in that: The socket release bracket includes a support fixed on a base frame, a support rod installed on the support, a push rod motor connected to the top of the support rod, a release traction rod connected to the front end of the push rod of the push rod motor, the release traction rod connected to the plug, and the push rod motor controlling the separation of the plug from the socket.

7. The simplified launcher for simulated projectiles according to any one of claims 1-6, characterized in that: It also includes a rear wing support, wherein the front wing support is hinged to the rear wing support to form a wing support structure.

8. The simplified launcher for simulated projectiles according to claim 7, characterized in that: The bracket has a reference plate installed at its front end for correcting the position of the simulated projectile.

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