Rocket second stage separation anti-rebound device and installation method thereof

Abstract

The application provides a rocket second-stage pulling anti-rebound device, which comprises a transverse adjusting device composed of two parallel transverse rods, a longitudinal adjusting device installed on the transverse adjusting device, a pulling device installed in the middle of the longitudinal adjusting device, and a connector connected to the top of the pulling device through a pulling steel wire rope; and an anti-rebound device is further installed on the side of the pulling device and connected to the connector through the pulling steel wire rope. The application also provides a rocket second-stage pulling anti-rebound device installation method. The application has the advantages of simple structure, no need for welding and additional processing of the structure, simple connection of the installation interface of the launching frame, fast installation and connection, simple and convenient operation of all adjusting components, fast operation, saved operation time before launching of the rocket, improved launching efficiency, no need for additional customization of components, and simple and convenient electric control program.

Description

Technical Field

[0001] This invention relates to a rocket second-stage detachment anti-rebound device and its installation method, belonging to the field of mechanical design. Background Technology

[0002] After the rocket is erected on the launch pad, the ground power supply equipment usually needs to provide power to the rocket body through a cable. One end of the cable is connected to an electrical connector plug, and the other end is laid through the launch pad to connect to the ground power supply equipment. When power is needed to supply power to the rocket, the plug is inserted into the socket on the rocket to connect and turn on the power. Before the rocket is launched into the air, the electrical connector plug on the rocket needs to be disconnected to stop the power supply.

[0003] Currently, the primary method for detaching electrical connector plugs from rocket sockets is automatic electrical disconnection, supplemented by mechanical release. However, the mechanical release mechanism is typically fixed to the launch pad and lacks adjustability. Within its effective pulling force range, the angle between the mechanical release force direction and the plug's axial direction is generally no greater than 10°. During propellant loading, the rocket is subject to static deformation, requiring multiple vertical adjustments. After these adjustments, the angle between the plug's axial direction and the mechanical release pull direction may shift by more than 10°. This increases the risk of mechanical release failure should electrical disconnection fail.

[0004] In the aforementioned method of detaching the plug from the rocket socket, when the plug detaches, the traction cable connecting the pulling device and the plug will pull the plug away from the rocket. During this movement, the plug will fall downwards in a pendulum-like arc around the traction point, and its path of motion cannot be controlled. Therefore, during the downward fall, the plug is very likely to collide with the launch pad and be damaged. After detaching from the socket, disregarding wind load, under its own weight, the traction cable will cause the plug to swing in a pendulum-like arc around the traction point during its downward fall. If the traction cable is too long, the plug will spring back, further increasing the risk of collision with the rocket. Summary of the Invention

[0005] To solve the above-mentioned technical problems, the present invention provides a rocket second-stage detachment anti-rebound device, which can effectively prevent the plug from rebounding or making pendulum-like arc movements around the traction point, thus avoiding the plug from hitting the launch pad or colliding with the rocket.

[0006] The present invention is achieved through the following technical solutions.

[0007] The present invention provides a rocket second stage detachment anti-rebound device, comprising a lateral adjustment device consisting of two parallel transverse rods, a longitudinal adjustment device installed on the lateral adjustment device, a traction device installed in the middle of the longitudinal adjustment device, and a connector connected to the top of the traction device via a traction steel wire rope; an anti-rebound device is also installed on the side of the traction device, and the anti-rebound device is connected to the connector via a traction steel wire rope.

[0008] The connector consists of a matching plug and a socket, with multiple plugs connected in a row on the socket, and a cable connected to the rear end of each plug.

[0009] The end of the horizontal bar is fixed to a support plate, and the bottom of the support plate has a mounting base structure, which is fixed to the launcher.

[0010] The longitudinal adjustment device has a symmetrical structure; the longitudinal adjustment device consists of two parallel longitudinal support components, and the ends of the longitudinal support components have hinged clamps that fit onto the transverse rods. The two ends of the hinged clamps are fastened by hinged screws and pins, respectively, and the pins have cotter pins; the hinged screws allow the hinged clamps to have an adjustment margin of ±200mm.

[0011] The pulling device consists of an electric push rod and a base adjustment device. The base adjustment device is fixed on the launch frame, the electric push rod is vertically fixed in the middle of the base adjustment device, and a fixing clamp is vertically fixed on the side of the base adjustment device. The fixing clamp is fixed to the longitudinal adjustment device, and the anti-rebound device is installed on the fixing clamp. The top of the electric push rod is used to connect the pulling steel wire rope.

[0012] The electric push rod consists of an explosion-proof motor. The output end of the explosion-proof motor is connected to the lead screw through a reduction gearbox. The top of the lead screw is used for connection. A cam limit switch is installed on the opposite end of the explosion-proof motor. The cam limit switch is used to receive the position feedback signal of the lead screw and realize the forward and reverse rotation and emergency stop control of the explosion-proof motor.

[0013] The anti-rebound device consists of a rotating rocker arm. The upper end of the rotating rocker arm is fixed with a slewing rod by a locking nut. The lower end of the rotating rocker arm is mounted on a mounting base by a guide rod. The mounting base is fixed to the traction device by a wing nut. Springs are installed on the guide rod and the mounting base. The two ends of the springs are limited by limit rings and fixed bases. The guide rod and the rotating rocker arm are fixed by a pin. A retaining ring with a hole is fitted on the pin.

[0014] The pulling wire rope is composed of steel wire ropes, with the two ends of the steel wire ropes clamped together by clamps and cores to form a loop. The cores and clamps are fixed by nuts.

[0015] The present invention also provides a method for installing a rocket second-stage detachment anti-rebound device, for installing the rocket second-stage detachment anti-rebound device as described above, comprising the following steps:

[0016] ① Install the lateral adjustment device onto the launch pad;

[0017] ② Pre-connect the longitudinal adjustment device and the lateral adjustment device, and install the traction device and anti-rebound device on the longitudinal adjustment device;

[0018] ③ Adjust the positions of the longitudinal adjustment device and the transverse adjustment device so that the axial angle between the electric push rod in the pulling device and the plug in the connector is no greater than 10°.

[0019] ④ Connect and secure the lateral adjustment device, longitudinal adjustment device, and traction device;

[0020] ⑤ The tension wire rope connecting the tensioning device and the connector;

[0021] ⑥ Compress the spring in the anti-rebound device, rotate the rotating rod in the anti-rebound device 90° relative to the guide rod, connect the plug and cable, and connect the tension wire rope between the anti-rebound device and the connector.

[0022] In step ⑤, the length of the traction wire rope is greater than the sum of the maximum sway of the rocket relative to the axis and the maximum sway of the launch pad at the secondary disengagement installation position; the length of the traction wire rope is the sum of the maximum sway of the rocket relative to the axis and the maximum sway of the launch pad at the secondary disengagement installation position plus 100mm.

[0023] The advantages of this invention are as follows: the structural components are simple and do not require additional processing after welding; the connection with the launch pad mounting interface is simple and quick; all adjustment components are simple and convenient to operate, enabling rapid operation, saving pre-launch operation time and improving launch efficiency; the technical benefits are far greater than other single-function pull-out devices or anti-rebound devices, effectively utilizing the synergistic effect of the combined pull-out device and anti-rebound device to achieve both the pull-out device effect and the anti-rebound device effect; no additional customization of components is required, the electrical control program is not complex, and operation is simple and convenient. Attached Figure Description

[0024] Figure 1 This is a schematic diagram of the structure of at least one embodiment of the present invention;

[0025] Figure 2 for Figure 1 A schematic diagram of the lateral adjustment device.

[0026] Figure 3 for Figure 1 A schematic diagram of the longitudinal adjustment device;

[0027] Figure 4 for Figure 1 Schematic diagram of the traction device;

[0028] Figure 5 for Figure 1 Schematic diagram of the anti-rebound device;

[0029] Figure 6 for Figure 1 Schematic diagram of the structure of the tension steel wire rope;

[0030] Figure 7 for Figure 4 Schematic diagram of the structure of the electric linear actuator;

[0031] Figure 8 for Figure 1 A schematic diagram of the connector structure.

[0032] In the diagram: 1- Lateral adjustment device, 11- Lateral rod, 12- Mounting base plate, 13- Support plate, 2- Longitudinal adjustment device, 21- Longitudinal support assembly, 22- Pin, 23- Hinge clamp, 24- Hinge screw, 25- Cotter pin, 3- Pulling device, 31- Electric push rod, 32- Fixed clamp, 33- Base adjustment device, 4- Anti-rebound device, 41- Rotary rod, 42- Locking nut, 43- Rotating swing arm, 44- Guide. 45-Pin, 46-Limit ring, 47-Spring, 48-Fixed seat, 49-Mounting seat, 411-Wing nut, 412-Hole retaining ring, 5-Pull wire rope, 51-Wire rope, 52-Core clamp, 53-Clamping plate, 54-Nut, 31-Electric push rod, 311-Gearbox, 312-Explosion-proof motor, 313-Lead screw, 314-Cam limit switch, 6-Connector, 61-Plug, 62-Socket, 63-Cable. Detailed Implementation

[0033] The technical solution of the present invention is further described below, but the scope of protection is not limited to what is described.

[0034] Example 1

[0035] like Figures 1 to 8 The rocket second stage detachment anti-rebound device shown includes a lateral adjustment device 1 composed of two parallel lateral rods 11. The device is characterized in that a longitudinal adjustment device 2 is installed on the lateral adjustment device 1, a traction device 3 is installed in the middle of the longitudinal adjustment device 2, and the top of the traction device 3 is connected to a connector 6 through a traction steel wire rope 5; an anti-rebound device 4 is also installed on the side of the traction device 3, and the anti-rebound device 4 is connected to the connector 6 through the traction steel wire rope 5.

[0036] Therefore, the main method for the electrical connector plug to detach from the rocket socket is automatic electrical disconnection of the plug, supplemented by mechanical disconnection using a two-stage anti-rebound device. A pull-off pin is installed in the Φ2.2mm hole of the central pull rod at the handwheel end of the electrical connector plug. That is, when the plug fails to disconnect electrically, the two-stage disconnection pulling device is used to forcibly pull to achieve mechanical separation of the plug and socket. When both electrical and mechanical separation fail, the pull-off pin is broken first when the pulling force is greater than 196N, preventing the rocket body from becoming unstable and tipping over.

[0037] The two-stage pull-out anti-rebound device is installed on the launch pad. After the rocket is propelled, it can adjust the angle between the pulling force direction of the pulling device and the axial direction of the plug by means of the longitudinal adjustment device, the base adjustment device and the mounting seat adjustment device mechanism, so that the angle is no more than 10°, which improves the reliability of the electrical connector plug disengagement.

[0038] After the plug detaches, the pulling device and the anti-rebound device activate together. Under its own weight, the anti-rebound device causes the rotating arm to rotate downwards around the axis of rotation. During the rotation of the rotating arm, the plug is pulled down by the steel wire rope. When the rotating arm is aligned with the guide shaft, the spring changes from a compressed state to an extended state. During the extension of the spring, the limiting ring moves downwards, which can quickly lock the rotating arm and the guide rod, thereby preventing the plug from hitting the rocket during its downward swing.

[0039] When the anti-rebound device locks and the traction device retracts, the plug reaches the predetermined position between the anti-rebound device traction point and the electric push rod traction point. This effectively prevents the plug from rebounding or making pendulum-like arc movements around the traction point, thus avoiding the plug hitting the launch pad or colliding with the rocket.

[0040] Example 2

[0041] Based on embodiment 1, connector 6 consists of matching plugs 61 and sockets 62, with multiple plugs 61 connected in a row on socket 62, and cables 63 connected to the rear end of plugs 61.

[0042] Furthermore, the end of the horizontal rod 11 is fixedly supported by a vertical plate 13, and the bottom of the vertical plate 13 has a mounting base 12 structure, which is fixed to the launcher.

[0043] Furthermore, the longitudinal adjustment device 2 has a symmetrical structure; the longitudinal adjustment device 2 consists of two parallel longitudinal support components 21, and the ends of the longitudinal support components 21 have hinged clamps 23 that are fitted onto the transverse rod 11. The two ends of the hinged clamps 23 are fastened by hinged screws 24 and pins 22 respectively, and the pins 22 have cotter pins 25; the hinged screws 24 allow the hinged clamps 23 to have an adjustment margin of ±200mm.

[0044] Furthermore, the tension wire rope 5 is composed of wire rope 51. The two ends of the wire rope 51 are clamped by clamping plates 53 and cores 52 to form a loop. The cores 52 and clamping plates 53 are fixed by nuts 54.

[0045] Furthermore, the anti-rebound device 4 consists of a rotating rocker arm 43. The upper end of the rotating rocker arm 43 is fixed with a rotating rod 41 by a locking nut 42. The lower end of the rotating rocker arm 43 is mounted on a mounting base 49 by a guide rod 44. The mounting base 49 is fixed to the pulling device 3 by a wing nut 411. A spring 47 is installed on the guide rod 44 and the mounting base 49. The two ends of the spring 47 are limited by a limiting ring 46 and a fixing base 48. The guide rod 44 and the rotating rocker arm 43 are fixed by a pin 45. A retaining ring 412 with a hole is fitted on the pin 45.

[0046] All of the above components adopt a lightweight design. The weight of the rotating lever is much less than the minimum pull-out force of the plug. Moreover, the models of each component are commercially available products and do not need to be customized. The electronic control program is not complicated and the operation is simple and convenient.

[0047] Example 3

[0048] Based on Embodiment 1, the traction device 3 consists of an electric push rod 31 and a base adjustment device 33. The base adjustment device 33 is fixed on the launcher, the electric push rod 31 is vertically fixed in the middle of the base adjustment device 33, and a fixing clamp 32 is vertically fixed on the side of the base adjustment device 33. The fixing clamp 32 is fixed to the longitudinal adjustment device 2, and the anti-rebound device 4 is installed on the fixing clamp 32. The top of the electric push rod 31 is used to connect the traction steel wire rope 5.

[0049] Furthermore, the electric push rod 31 is composed of an explosion-proof motor 312. The output end of the explosion-proof motor 312 is connected to the lead screw 313 through a reduction gearbox 311. The top end of the lead screw 313 is used for connection. A cam limit switch 314 is installed on the opposite end of the explosion-proof motor 312. The cam limit switch 314 is used to receive the position feedback signal of the lead screw 313 and realize the forward and reverse rotation and emergency stop control of the explosion-proof motor 312.

[0050] Example 4

[0051] Based on the above embodiments, the lateral adjustment device 1 has a symmetrical structure, and both ends are fixed to the launcher by the mounting base plate 12.

[0052] The longitudinal adjustment device 2 is mainly composed of a longitudinal support component 21, a pin 22, a hinge clamp 23, a hinge screw 24, and a cotter pin 25. The longitudinal adjustment device 2 has a symmetrical structure, and both ends are fixedly connected to the transverse adjustment device 1 by a combination of hinge clamp 23 and hinge screw 24. It can achieve an adjustment of ±200mm in the transverse adjustment device 1.

[0053] The traction device 3 mainly consists of an electric push rod 31, a fixing clamp 32, and a base adjustment device 33. The base adjustment device 33 has a symmetrical structure, and its two ends are installed onto the longitudinal adjustment device 2 by the fixing clamp 32, wing nuts, and bolts. The electric push rod 31 provides an installation support interface for the traction wire rope 5. Adjustments of ±200mm can be achieved on the longitudinal adjustment device 2.

[0054] The anti-rebound device 4 consists of a rotating rod 41, a locking nut 42, a rotating swing rod 43, a guide rod 44, a pin 45, a limit ring 46, a spring 47, a fixed seat 48, a mounting seat 49, a wing nut 411, and a retaining ring for the hole 412. The fixed base 48 is fixed to the mounting base 49 by bolts; the guide rod 44 has a slot at one end and a threaded hole at the other end. The end with the threaded hole is screwed to the fixed base 48, and the end with the slot is connected to the rotating rocker arm 43 by a pin 45; the spring 47 and the limiting ring 46 are placed on the guide rod 44, wherein one end of the spring 47 abuts against the mounting base 49 and the other end abuts against the limiting ring 46. The relative movement of the spring 47 and the limiting ring 46 can realize the locking and unlocking of the rotating rocker arm 43. When locked, it is difficult to unlock under the action of external force, but it can be easily unlocked manually; one end of the rotary rod 41 is connected to the rotating rocker arm 43 by a screw, and the other end has a wire rope traction point. The threaded section of the rotary rod can be extended and shortened on the rotating rocker arm. During the adjustment, it can be locked and unlocked by rotating the nut.

[0055] The tension wire rope 5 is mainly composed of wire rope 51, core 52, clamping plate 53, and nut 54. One end of the core 52 has a U-shaped hole and the other end has a thread. The wire rope 51 can be adjusted in length through the U-shaped hole of the core under the action of clamping plate 53 and nut 54.

[0056] Connector 6 is mainly composed of plug 61, socket 62 and cable 63. Socket 62 is fixed to the rocket as a whole. When the launch pad is tilted from the rear to the front, plug 61 and socket 62 need to be separated and the power is cut off. One end of the pulling steel wire rope 5 is connected to the pull-off pin hole of plug 61.

[0057] The electric push rod 31 mainly consists of a gearbox 311, an explosion-proof motor 312, a lead screw 313, and a cam limit switch 314. The pulling force is 500N, the push rod stroke is greater than 160mm, and the pulling speed is 30mm / s. A cam limit switch 314 is installed at the input opposite end of the explosion-proof motor 312. Its main function is to reliably receive feedback signals from the lead screw 313 when it extends and retracts to the correct position, so as to achieve a stop when the position is reached. At the same time, it can realize the forward and reverse rotation of the motor and emergency stop control.

[0058] Example 5

[0059] A method for installing a rocket second-stage pullback anti-rebound device as described in the above embodiment includes the following steps:

[0060] ① Install the lateral adjustment device 1 onto the launch pad;

[0061] ② Pre-connect the longitudinal adjustment device 2 and the lateral adjustment device 1, and install the traction device 3 and the anti-rebound device 4 on the longitudinal adjustment device 2;

[0062] ③ Adjust the positions of the longitudinal adjustment device 2 and the transverse adjustment device 1 so that the axial angle between the electric push rod 31 in the pulling device 3 and the plug 61 in the connector 6 is no greater than 10°.

[0063] ④ Connect and secure the lateral adjustment device 1, longitudinal adjustment device 2, and traction device 3;

[0064] ⑤ The tension wire rope 5 connects the tensioning device 3 and the connector 6;

[0065] ⑥ Compress the spring 47 in the anti-rebound device 4, rotate the rotating rod 41 in the anti-rebound device 4 by 90° relative to the guide rod 44, connect the plug 61 and the cable 63, and connect the tension wire rope 5 between the anti-rebound device 4 and the connector 6.

[0066] In step ⑤, the length of the traction wire rope 5 is greater than the sum of the maximum sway of the rocket relative to the axis and the maximum sway of the launch pad at the second stage disengagement installation position; the length of the traction wire rope 5 is the sum of the maximum sway of the rocket relative to the axis and the maximum sway of the launch pad at the second stage disengagement installation position plus 100mm.

[0067] The lateral adjustment device 1 is installed on the launch pad and serves as a support and fixation device; the longitudinal adjustment device 2 can drive the whole to make left and right displacement adjustments; the anti-rebound device 4 can drive the plug to fall during the rotation and falling process, which can effectively prevent the plug from rebounding or making pendulum arc motion around the traction point, thus avoiding the plug from colliding with the erector or rocket during the pulling and pulling process.

Claims

1. A rocket second-stage detachment anti-rebound device, comprising a lateral adjustment device (1) consisting of two parallel transverse rods (11), characterized in that, A longitudinal adjustment device (2) is installed on the lateral adjustment device (1), and a pulling device (3) is installed in the middle of the longitudinal adjustment device (2). The top of the pulling device (3) is connected to the connector (6) through the pulling wire rope (5). An anti-rebound device (4) is also installed on the side of the pulling device (3). The anti-rebound device (4) is connected to the connector (6) through the pulling wire rope (5). The end of the horizontal bar (11) is fixed to the support plate (13), and the bottom of the support plate (13) has a mounting base plate (12) structure, which is fixed to the launcher. The longitudinal adjustment device (2) has a symmetrical structure; the longitudinal adjustment device (2) consists of two parallel longitudinal support components (21), and the ends of the longitudinal support components (21) have hinged clamps (23) that fit onto the transverse rod (11). The two ends of the hinged clamps (23) are fastened by hinged screws (24) and pins (22) respectively. Pins (22) have cotter pins (25); the hinged screws (24) allow the hinged clamps (23) to have an adjustment margin of ±200mm; The pulling device (3) consists of an electric push rod (31) and a base adjustment device (33). The base adjustment device (33) is fixed on the launcher. The electric push rod (31) is vertically fixed in the middle of the base adjustment device (33). A fixing clamp (32) is vertically fixed on the side of the base adjustment device (33). The fixing clamp (32) is fixed to the longitudinal adjustment device (2). The anti-rebound device (4) is installed on the fixing clamp (32). The top of the electric push rod (31) is used to connect the pulling steel wire rope (5). The electric push rod (31) consists of an explosion-proof motor (312). The output end of the explosion-proof motor (312) is connected to the lead screw (313) through the gearbox (311). The top of the lead screw (313) is used for connection. A cam limit switch (314) is installed on the opposite end of the explosion-proof motor (312). The cam limit switch (314) is used to receive the position feedback signal of the lead screw (313) and realize the forward and reverse rotation and emergency stop control of the explosion-proof motor (312). The anti-rebound device (4) consists of a rotating rod (41), a locking nut (42), a rotating rocker arm (43), a guide rod (44), a second pin (45), a limiting ring (46), a spring (47), a fixed seat (48), a mounting seat (49), a wing nut (411), and a retaining ring (412). The second pin (45) is fitted with a retaining ring (412). The upper end of the rotating rocker arm (43) is fixed to the rotating rod (41) by the locking nut (42). The fixed seat (48) is fixed to the mounting seat (49) by bolts. The mounting seat (49) is open to the ground. The butterfly nut (411) is fixed on the traction device (3); the guide rod (44) has a slot at one end and a threaded hole at the other end. The end with the threaded hole is screwed to the fixed seat (48), and the end with the slot is connected to the rotating swing rod (43) through the pin (45); the spring (47) and the limiting ring (46) are placed on the guide rod (44), wherein one end of the spring (47) abuts against the mounting seat (49), and the other end abuts against the limiting ring (46). The relative movement of the spring (47) and the limiting ring (46) realizes the locking and unlocking of the rotating swing rod (43).

2. The rocket second-stage pullback anti-rebound device as described in claim 1, characterized in that, The connector (6) consists of a matching plug (61) and a socket (62), with multiple plugs (61) connected in a row on the socket (62), and a cable (63) connected to the rear end of the plug (61).

3. The rocket second-stage pullback anti-rebound device as described in claim 1, characterized in that, The pulling wire rope (5) is composed of wire rope (51). The two ends of the wire rope (51) are clamped by clamping plates (53) and cores (52) to form a ring. The cores (52) and clamping plates (53) are fixed by nuts (54).

4. A method for installing a rocket second-stage detachment anti-rebound device, characterized in that, The method for installing the rocket second-stage pullback anti-rebound device as described in any one of claims 1 to 3 includes the following steps: ① Install the lateral adjustment device (1) onto the launch pad; ② Connect the longitudinal adjustment device (2) and the lateral adjustment device (1) in advance, and install the traction device (3) and the anti-rebound device (4) on the longitudinal adjustment device (2). ③ Adjust the positions of the longitudinal adjustment device (2) and the transverse adjustment device (1) so that the axial angle between the electric push rod (31) in the traction device (3) and the plug (61) in the connector (6) is no greater than 10°; ④ Connect and tighten the lateral adjustment device (1), longitudinal adjustment device (2), and traction device (3); ⑤ Connecting the traction device (3) and the connector (6) with the traction wire rope (5); ⑥ Compress the spring (47) in the anti-rebound device (4), rotate the rotating rod (41) in the anti-rebound device (4) 90° relative to the guide rod (44), connect the plug (61) and the cable (63), and connect the tension wire rope (5) between the anti-rebound device (4) and the connector (6).

5. The installation method of the rocket second-stage detachment anti-rebound device as described in claim 4, characterized in that, In step ⑤, the length of the pulling wire rope (5) is greater than the sum of the maximum sway of the rocket relative to the axis and the maximum sway of the launch pad secondary disengagement installation position; the length of the pulling wire rope (5) is the sum of the maximum sway of the rocket relative to the axis and the maximum sway of the launch pad secondary disengagement installation position plus 100mm.

Images