A down-hung rocket lock

Abstract

The application discloses a lower-hung rocket locking device, and relates to the field of rocket transportation and launching, which comprises a shell, a guide rail with a sliding groove arranged at the bottom, a rocket sliding block fixedly connected to the rocket body and slidably connected in the sliding groove, a rear locking mechanism connected in the sliding groove and used for blocking the movement of the rocket sliding block away from the rocket launching direction, and a front locking mechanism comprising a locking mechanism, a locking mechanism, and a stopper rotatably connected to the shell, wherein the locking mechanism is used for locking the side of the rocket sliding block away from the rear locking mechanism through the stopper and releasing the locking of the rocket sliding block when the rocket body is launched, and the locking mechanism is used for locking the rocket sliding block when the rocket body is launched and automatically releasing the locking of the rocket sliding block under the driving of the rocket thrust after the rocket body is ignited. The mechanism is adapted to the structure of the lower-hung guide rail launching, can realize the functions of blocking the rocket and locking, and can complete the transportation support locking and obtain reliable locking force during launching. After launching, the mechanism can be reused by re-installing the shear pin.

Description

TECHNICAL FIELD

[0001] The application relates to a lower-hung rocket locking device, which is installed on a launching device guide rail director of lower-hung launching and relates to the technical field of rocket transportation and launching. BACKGROUND

[0002] In the process of small missile / rocket transportation on a rack, in order to prevent falling, sliding and other phenomena caused by vibration in the transportation process and gravity of the rocket, an arrow blocking mechanism needs to be designed. In the process of rocket launching, sometimes in order to obtain a high initial speed, a locking mechanism is designed to control the locking force of the rocket, so as to ensure that the launching off-orbit speed is high and the off-orbit disturbance is small. The present application combines the arrow blocking mechanism and the locking mechanism. The structure is simple, and the arrow blocking function in the transportation process and the locking function in the launching process are completed.

[0003] The traditional rocket arrow blocking mechanism is to fix the front end or the rear end of the rocket support leg with a baffle, then use a screw rod to press against the other end, and then use an arc-shaped seat or a belt to fix in the ring direction. The locking mechanism uses a spring steel structure to limit the movement of the front end of the rocket support leg. The balance of the rocket thrust and the elastic force is used to obtain the locking force. Moreover, it is mostly used on the upper-hung guide rail director. Although it can meet the requirements, the operation timing is more, the structure installation is complex, the test process period is long and the cost is high. Moreover, the above-mentioned situation is basically used for the upper-hung guide rail. SUMMARY

[0004] The technical problem solved by the present application is to overcome the shortcomings of the prior art and provide a lower-hung rocket locking device which is suitable for the structure and appearance of the rocket launched by the lower-hung guide rail, high-efficiency, simple and capable of realizing the arrow blocking and locking functions, so as to complete the transportation support locking, obtain reliable locking force in the launching process and complete the rocket launching task.

[0005] The technical solution of the present application is:

[0006] A lower-hung rocket locking device comprises:

[0007] A shell is provided with a guide rail with a sliding groove at the bottom, and a rocket sliding block connected to a rocket body is slidably connected in the sliding groove;

[0008] A rear locking mechanism is connected in the sliding groove and is used to block the movement of the rocket sliding block away from the rocket launching direction;

[0009] A front locking mechanism comprises a locking mechanism, a locking mechanism, a blocking block rotatably connected to the shell, the locking mechanism is used to lock the blocking block on the side of the rocket sliding block away from the rear locking mechanism and to release the locking of the rocket sliding block when the rocket body is launched, and the locking mechanism is used to lock the rocket sliding block when the rocket body is launched and to automatically release the locking of the rocket sliding block after the rocket body is ignited.

[0010] The rear locking mechanism comprises a rear baffle connected to the sliding groove and fixed to the orienter shell by locking screws.

[0011] The locking mechanism is a transport locking pin which is screwed to the shell, the axis of the transport locking pin is parallel to the length direction of the sliding groove, and the rotation axis of the block is perpendicular to the axis of the transport locking pin and the length direction of the sliding groove.

[0012] The locking mechanism comprises a push rod, a shear pin, an adjusting rod connected to the shell, the shear pin is connected between the push rod and the adjusting rod, the shell is provided with a through hole parallel to the sliding groove, the push rod and the adjusting rod pass through the through hole and are in sliding connection with the shell, the end of the push rod away from the shear pin is in sliding and rotating connection with the block so as to make the block rotate and the push rod slide along the through hole synchronously.

[0013] The locking mechanism further comprises an energy storage spring sleeved on the outer wall of the push rod, the outer wall of the push rod is connected with a positioning protrusion, one end of the energy storage spring abuts against the positioning protrusion and the other end abuts against the shell, so that after the shear pin is pulled off, the energy storage spring drives the push rod to push the block to rotate.

[0014] The end of the adjusting rod out of the shell is screwed with an adjusting nut.

[0015] The end of the push rod away from the shear pin is connected with a tension rod, the tension rod is parallel to the rotation axis of the block, the side of the block facing the push rod is provided with an insertion slot, and the block is provided with a U-shaped hole, the insertion slot is in communication with the U-shaped hole, and the push rod passes through the insertion slot and the tension rod is located in the U-shaped hole.

[0016] The front locking mechanism further comprises a positioning mechanism for positioning the position of the block; the positioning mechanism comprises a locking screw, a locking spring, a steel ball and a positioning slot, the positioning slot is provided on the two side surfaces of the block, the shell is provided with a positioning mounting hole, along the direction away from the positioning slot, the steel ball, the locking spring and the locking screw are sequentially located in the positioning mounting hole, and the locking screw is screwed in the positioning mounting hole.

[0017] The positioning slot of the block is provided with at least two positions, the two positions are the position of the block blocking the side of the rocket sliding block away from the rear locking mechanism and the position of the block disengaging the rocket sliding block.

[0018] The shell is provided with an operation window for operating the locking mechanism.

[0019] In summary, the present application at least has the following beneficial technical effects:

[0020] (1) The mechanism adopts the combination of the shear pin, the block, the push rod, the steel ball and the spring to realize the accurate force control and the positioning of the block. The structure is good in coordination and the operation procedure is simple.

[0021] (2) The storage and transportation stage and the launching stage are divided into two independent mechanisms, which do not affect each other. The two working positions are adjustable, which facilitates eliminating the instability caused by the structural error of the rocket;

[0022] (3) The locking mechanism is triggered when it moves after the rocket is ignited, and does not need other external driving force, and has no risk of electrical control failure. It can meet the launching requirements of different types of rockets;

[0023] (4) The entire limiting part and the force transmission part are all designed inside the mechanism and the body of the director. The movement is reliable and more secure. There is no mechanical and safety human risk caused by splashing during rocket loading, transportation and launching. BRIEF DESCRIPTION OF DRAWINGS

[0024] Figure 1 It is a schematic diagram of the overall structure of the locking mechanism;

[0025] Figure 2 It is a schematic diagram of the overall structure of the transport locking pin of the locking mechanism;

[0026] Figure 3 a is a cross-sectional view of the locking mechanism through the axis of the rocket body, Figure 3 b is a cross-sectional view of the locking mechanism perpendicular to the rocket body and through the rotating shaft;

[0027] Figure 4 a is a transport locking state diagram, Figure 4 b is Figure 4 a is a simplified diagram;

[0028] Figure 5 a is a launching state layout diagram, Figure 5 b is a schematic diagram of the stop block being positioned.

[0029] BRIEF DESCRIPTION OF DRAWINGS: 1, housing; 2, stop block; 3, rotating shaft; 4, transport locking pin; 5, energy storage spring; 6, push rod; 7, shear pin; 8, adjusting nut; 9, rear baffle; 10, rocket slider; 11, set screw; 12, locking spring; 13, steel ball; 14, guide rail; 15, positioning groove; 16, lug; 17, first plate body; 18, second plate body; 19, adjusting rod; 20, positioning protrusion; 21, tensioning rod. DETAILED DESCRIPTION

[0030] The application will be described in further detail below in conjunction with the drawings and specific embodiments:

[0031] The embodiment of the application discloses a lower hanging type rocket locking device, like Figure 1 and Figure 2As shown, it comprises a shell 1, a stopper 2, a rotating shaft 3, a transport locking pin 4, an energy storage spring 5, a push rod 6, a shear pin 7, an adjusting nut 8, a backstop 9, a rocket slider 10, a set screw 11, a locking spring 12, a steel ball 13 and a guide rail 14. The locking mechanism is installed on the body of the launcher's director, and realizes the functions of transport arrow blocking, launch locking and post-firing stopper positioning.

[0032] The shell 1 is provided at the bottom with a guide rail 14 having a sliding slot, and the rocket body is fixedly connected with a rocket slider 10 which is slidingly connected in the sliding slot. The backstop 9 is connected in the sliding slot and is fixed to the shell 1 by a locking screw, for blocking the movement of the rocket slider 10 away from the rocket launching direction.

[0033] As shown in Figure 2 and Figure 3 a, Figure 3 b, two lugs 16 are arranged in the shell 1, and the stopper 2 is rotatably connected between the two lugs 16 by the rotating shaft 3. The shell 1 is internally provided with a first plate body 17 and a second plate body 18, which are perpendicular to the length direction of the sliding slot. The first plate body 17 and the second plate body 18 are located on the side of the stopper 2 facing the backstop 9, and the first plate body 17 is located between the stopper 2 and the second plate body 18. The transport locking pin 4 is threadedly connected to the first plate body 17, and the end of the transport locking pin 4 is opposite to the part of the stopper 2 above the rotating shaft 3. The axis of the transport locking pin 4 is parallel to the length direction of the sliding slot, and the rotating shaft 3 of the stopper 2 is perpendicular to the axis of the transport locking pin 4 and the length direction of the sliding slot. When the stopper 2 is rotated to abut against the rocket slider 10 on the side away from the backstop 9, the transport locking pin 4 is tightened until it abuts against the stopper 2, thereby locking the rocket slider 10 by the stopper 2, and realizing the function of transport arrow blocking. The shell 1 is provided with an operation window through which the transport locking pin 4 can be operated.

[0034] As shown in Figure 4 a, Figure 4As shown in FIG. 2b, the shearing pin 7 is in sliding connection between the push rod 6 and the adjusting rod 19 through a hole shaft, the housing 1 is provided with a through hole parallel to the sliding groove, the push rod 6 and the adjusting rod 19 pass through the through hole and are in sliding connection with the housing 1, the outer wall of the push rod 6 is connected with a positioning protrusion 20, one end of the energy storage spring 5 abuts against the positioning protrusion 20 and the other end abuts against the second plate body 18, so that after the shearing pin 7 is pulled off, the energy storage spring 5 drives the push rod 6 to push the stop block 2 to rotate. The end of the adjusting rod 19 passing out of the housing 1 is threadedly connected with the adjusting nut 8. The end of the push rod 6 away from the shearing pin 7 is in sliding and rotating connection with the stop block 2 through the tension rod 21 on the push rod 6, so that the stop block 2 rotates and the push rod 6 slides along the through hole synchronously. Specifically, the end of the push rod 6 away from the shearing pin 7 is connected with the tension rod 21, the tension rod 21 is parallel to the rotating shaft 3 of the stop block 2, the side of the stop block 2 facing the push rod 6 is provided with an insertion slot, and the stop block 2 is provided with a U-shaped hole, the insertion slot is in communication with the U-shaped hole, the push rod 6 passes through the insertion slot and the tension rod 21 is located in the U-shaped hole.

[0035] As shown in FIG. 2a, Figure 5 a、 Figure 5 b, the two sides of the stop block 2 facing the lugs 16 are provided with positioning slots 15, the lugs 16 are provided with positioning mounting holes, along the direction away from the positioning slots 15, the steel ball 13, the locking spring 12 and the locking screw 11 are sequentially located in the mounting positioning holes, and the locking screw 11 is threadedly connected in the mounting positioning hole. When the locking screw 11 is loosened, the steel ball 13 cannot be positioned with the stop block 2 by cooperating with the positioning slot 15; the positioning slot 15 of the stop block 2 is provided with at least two positions, the two positions are that the stop block 2 blocks the side of the rocket slider 10 away from the rear locking mechanism and the position that the stop block 2 is separated from the rocket slider 10. When in the two positions, the locking spring 12 is compressed to have a spring force, so that the steel ball 13 is compressed in the positioning slot 15, so that the stop block 2 cannot continue to rotate.

[0036] The main function of the mechanism is to block the rocket during the transportation process after the rocket is filled, to ensure that the rocket can be reliably transported on the rack; and to have a reliable locking effect during launching, to provide a certain initial speed for the rocket through the accurate locking force, so as to reduce the off-orbit disturbance.

[0037] Under the premise that the rear stop plate 9 ensures the fixation of the rocket support, the mechanism uses the lever principle to block the front end of the rocket support by the stop block 2 to complete the transportation fixation. When launching, the transportation locking pin is unscrewed, the shearing pin 7 and the push rod 6 and the reset spring are installed, and the adjusting nut 8 is tightened, so that the front end of the rocket support is in contact with the stop block 2. During launching, the rocket overcomes the action force of the shearing pin 7 to leave the orbit at a certain initial speed. The mechanism is mainly suitable for the rocket launching storage and launching working conditions of the lower hanging type. After launching, the mechanical device can be reused by replacing the shearing pin 7.

[0038] It has small volume and light weight, and meets the use requirements of storage and transportation and launching. After launching, it is separated automatically, and is locked reliably, and does not collide with the rocket cabin.

[0039] The implementation principle of the present application is:

[0040] According to the actual rocket structure shape and locking force requirements and other conditions, the installation position of the locking mechanism and the structure design of the shear pin and the positioning steel ball are determined, the installation mode is optimized, and the rationality of assembly of each component is performed. First, the rocket is filled from the rear end to the position, then the rear baffle 9 is installed, then the stop block 2, the rotating shaft 3, the locking screw 11, the locking spring 12, the steel ball 13 are installed, then the push rod 6, the energy storage spring 5, the shear pin 7, the adjusting rod 19 are installed, and finally the transportation locking pin 4 is installed to the position.

[0041] In the transportation state, after the rear baffle 9 is installed to the position, the rocket is filled, the locking screw 11 is loosened, the stop block is released, and then the transportation locking pin 4 is tightened, so that the stop block contacts the front end face of the rocket slider. Since the rear end of the rocket slider is constrained by the rear baffle 9, the stop block is elastically deformed, and is clamped front and rear, so that the transportation fixing is realized. As shown in Figure 4 .

[0042] In the launching state, the transportation locking pin 4 is loosened, the push rod, the shear pin and the energy storage spring are assembled to the position, the adjusting nut 8 is manually twisted, the push rod 6 is pulled tightly, the shear pin 7 is in a tension state, and the locking of the rocket slider is completed.

[0043] After the rocket is ignited, when the thrust of the rocket body is greater than the shearing force, the shear pin 7 is sheared, at this time the rocket slider 10 loses the constraint, and smoothly leaves the orbit. After the shear pin 7 is broken, the push rod 6 moves to the left under the action of the energy storage spring, drives the stop block 2 to rotate to the specified position, and is self-locked by the two groups of locking springs 12 and the steel ball 13. As shown in Figure 5 a、 Figure 5 b, collision with the rocket body or other parts of the launching device during launching is avoided. After launching, as long as the shear pin is reinstalled, it can be reused.

[0044] The undisclosed technology of the present application belongs to the common knowledge of those skilled in the art.

[0045] Although the present application is disclosed with the preferred embodiments as above, it is not intended to limit the present application, and any person skilled in the art can make possible changes and modifications without departing from the spirit and scope of the present application, therefore, the protection scope of the present application should be limited by the scope defined by the claims of the present application.

Claims

1. A downward-hung rocket lockout device, characterized by, The utility model relates to a rocket launcher, which comprises: a shell (1) provided with a guide rail (14) having a sliding slot at the bottom, a rocket sliding block (10) fixedly connected to the rocket body slidingly connected in the sliding slot; a rear locking mechanism connected in the sliding slot through a rear baffle (9) for blocking the movement of the rocket sliding block (10) away from the rocket launching direction; a front locking mechanism comprising a locking mechanism, a locking mechanism, a stop block (2) rotatably connected to the shell (1), the locking mechanism is used for locking the stop block (2) on the side of the rocket sliding block (10) away from the rear locking mechanism and releasing the locking of the rocket sliding block (10) when the rocket body is launched, the locking mechanism is used for locking the rocket sliding block (10) when the rocket body is launched and automatically releasing the locking of the rocket sliding block (10) under the action of the rocket thrust after the rocket body is ignited; the locking mechanism comprises a push rod (6), a shear pin (7), an adjusting rod (19) connected to the shell (1), the shear pin (7) is connected between the push rod (6) and the adjusting rod (19), the shell (1) is provided with a through hole parallel to the sliding slot, the push rod (6) and the adjusting rod (19) pass through the through hole and are slidingly connected with the shell (1), the end of the push rod (6) away from the shear pin (7) is slidingly and rotatably connected with the stop block (2) to make the stop block (2) rotate and the push rod (6) slide along the U-shaped through hole synchronously.

2. A downward-hung rocket lock set as claimed in claim 1, characterized in that: the rear locking mechanism comprises a rear baffle (9) connected in the sliding slot and fixed to the shell (1) through a locking screw.

3. The underhung rocket lockout device of claim 1, wherein: the locking mechanism is a transport locking pin (4) threadedly connected to the shell (1), the axis of the transport locking pin (4) is parallel to the length direction of the sliding slot, the rotation shaft (3) of the stop block (2) is perpendicular to the axis of the transport locking pin (4) and the length direction of the guide rail sliding slot.

4. The underhung rocket lockout device of claim 1, wherein: the locking mechanism further comprises an energy storage spring (5) sleeved on the outer wall of the push rod (6), the outer wall of the push rod (6) is connected with a positioning protrusion (20), one end of the energy storage spring (5) abuts against the positioning protrusion (20) and the other end abuts against the shell (1), so that after the shear pin (7) is pulled off under the action of the rocket thrust, the energy storage spring (5) drives the push rod (6) to push the stop block (2) to rotate.

5. The underhung rocket lockout device of claim 1, wherein: the end of the adjusting rod (19) passing out of the shell (1) is threadedly connected with an adjusting nut (8), and the other end of the adjusting rod (19) is connected through the shear pin (7) and the push rod (6).

6. A downwardly hanging rocket locking device according to claim 1, characterized in that: the end of the push rod (6) away from the shear pin (7) is connected with a tension rod parallel to the rotation shaft (3) of the stop block (2), the side of the stop block (2) facing the push rod (6) is provided with an insertion slot, and the stop block (2) is provided with a U-shaped hole, the insertion slot is communicated with the U-shaped hole, the push rod (6) passes through the insertion slot and the tension rod is located in the U-shaped hole.

7. The underhung rocket lockout device of claim 1, wherein: The front locking mechanism further comprises a positioning mechanism for positioning the position of the stopper (2); the positioning mechanism comprises a locking spring (12), a steel ball (13), a positioning slot (15) and a locking screw (11); the positioning slot (15) is arranged on the stopper (2); the housing (1) is provided with a positioning installation hole; along the direction away from the positioning slot (15), the steel ball (13), the locking spring (12) and the locking screw (11) are sequentially arranged in the positioning installation hole; and the locking screw (11) is threadedly connected in the positioning installation hole.

8. A downward-firing rocket lock device as in claim 7, wherein: The positioning slot (15) of the stopper (2) is provided with at least two positions, which are respectively a position where the stopper (2) blocks the side of the rocket sliding block (10) away from the rear locking mechanism and a position where the stopper (2) is separated from the rocket sliding block (10).

9. The underhung rocket lockout device of claim 1, wherein: The housing (1) is provided with an operation window for operating the locking mechanism.

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