Launch vehicle nose fairing mechanism for triplane launch system

Abstract

The application provides a launch vehicle front-end protection mechanism for a three-plane launch system, comprising a base, wherein the base is provided with a push rod motor reducer, a screw push rod, a clamping assembly and a supporting assembly; the push rod motor reducer is hingedly installed on the base, and one end of the screw push rod is in transmission connection with an output end of the motor reducer; the clamping assembly comprises a clamping arm, a clamping block and a pressure sensor, the clamping arm is hingedly connected with the base, the other end of the screw push rod is hingedly connected with the clamping arm, the hinging axis of the clamping arm and the base and the hinging axis of the clamping arm and the screw push rod are parallel, the clamping block is arranged on the clamping arm, and the pressure sensor is arranged between the clamping block and the clamping arm; the supporting assembly comprises a supporting frame, the supporting frame supports a missile body, and the supporting frame and the clamping block cooperatively clamp the missile body. The technical scheme can avoid the problems of clamping not in place or over-clamping, and is helpful to improve the safety of the missile body.

Description

Technical Field

[0001] This application relates to the field of aerospace technology, and more specifically, to a front-end protection mechanism for a launch vehicle used in a three-plane launch system. Background Technology

[0002] The three-horizontal launch mode for launch vehicles requires horizontal transport, horizontal assembly, and horizontal testing, culminating in the use of an erector to equip the rocket to a vertical position for launch. During horizontal transport, the rocket needs to be supported and secured. The rear support point is typically designed with a pin-shaft clamping method, while the front support is a front-end protective mechanism. This mechanism must both support and secure the rocket body to prevent damage from bumps during transport. Existing clamping devices struggle to control the clamping force, easily leading to inadequate or excessive clamping. To meet the protection requirements of the three-horizontal launch system's erector, it is necessary to provide a front-end protective mechanism that reliably supports and secures the rocket body. Summary of the Invention

[0003] In view of the deficiencies in the prior art, the purpose of this application is to provide a front-end protection mechanism for a launch vehicle in a three-plane launch system.

[0004] According to the present application, a launch vehicle front protection mechanism for a three-plane launch system includes a base, on which are configured: a push rod motor reducer, a lead screw push rod, a clamping assembly, and a support assembly;

[0005] The push rod motor reducer is hinged to the base, and one end of the screw-type push rod is connected to the output end of the motor reducer.

[0006] The clamping assembly includes a clamping arm, a clamping block, and a pressure sensor. The clamping arm is hinged to the base, and the other end of the lead screw is hinged to the clamping arm. The hinge axis between the clamping arm and the base and the hinge axis between the clamping arm and the lead screw are parallel. The clamping block is disposed on the clamping arm, and the pressure sensor is disposed between the clamping block and the clamping arm.

[0007] The support assembly includes a support frame that supports the arrow body, and the support frame and the clamping block cooperate to hold the arrow body.

[0008] Preferably, the clamping assembly further includes a clamping block guiding mechanism, which is disposed between the clamping block and the clamping arm.

[0009] Preferably, the other end of the lead screw push rod is hinged to the arm through a shaft hole and a lead screw shaft;

[0010] The arm has an arc-shaped structure, and one end of the arc is hinged to the upper end of the base through a second rotating shaft and a shaft hole.

[0011] The axial direction of the lead screw shaft is parallel to the axial direction of the second shaft.

[0012] Preferably, the pressure sensor is in the form of two, serving as a backup for each other.

[0013] Preferably, the support assembly further includes a spiral lifting mechanism, which drives the support frame to reciprocate in the vertical direction.

[0014] Preferably, the support assembly further includes a support frame guide cylinder and a support frame guide rod;

[0015] The support frame guide cylinder is fixedly installed on the base. The lower end of the support frame guide rod extends into the support frame guide cylinder and can move along the axial direction of the support frame guide cylinder. The upper end of the support frame guide rod is fixedly connected to the bottom of the support frame.

[0016] Preferably, the support frame is an arc-shaped clamp with the opening facing upwards.

[0017] Preferably, the support assembly further includes a proximity switch bracket;

[0018] The proximity switch bracket is fixedly installed on the base. The proximity switch sensor is integrated on the proximity switch bracket. The proximity switch sensing iron plate is installed on the support frame. The proximity switch sensor is electrically coupled to the proximity switch sensing iron plate.

[0019] Compared with the prior art, this application has the following beneficial effects:

[0020] 1. This application achieves reliable clamping of the rocket's front end by using a push rod motor reducer, clamping arm, clamping block, and pressure sensor in conjunction with a support frame. This avoids problems of inadequate or excessive clamping and helps improve the safety of the rocket body.

[0021] 2. This application adopts a support component that can be flexibly adjusted according to the rocket's support centerline, which is highly adaptable and ensures that the rocket receives sufficient support during the erection process, thus avoiding centerline deviation.

[0022] 3. This application incorporates a torque limiter through system design to prevent excessive pressure or mechanical impact from damaging the rocket during the clamping process. Attached Figure Description

[0023] Other features, objects, and advantages of this application will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0024] Figure 1 This application mainly presents a schematic diagram of the front-end protection mechanism of a launch vehicle used in a three-plane launch system.

[0025] The figure shows: 1. Base; 2. Push rod motor reducer; 3. Torque limiter; 4. Lead screw type push rod; 5. Lead screw shaft; 6. Arm; 7. Arm block; 8. Pressure sensor; 9. Arm block guide mechanism; 10. Support frame; 11. Support frame guide rod; 12. Proximity switch bracket; 13. Screw lifting mechanism; 14. Support frame guide cylinder; 15. Second shaft. Detailed Implementation

[0026] The present application will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present application, but do not limit the present application in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present application. These all fall within the protection scope of the present application.

[0027] According to this application, a launch vehicle front protection mechanism for a three-platform launch system includes a base 1, on which are mounted: a push rod motor reducer 2, a lead screw type push rod 4, a clamping assembly, and a support assembly. The push rod motor reducer 2 is hinged to the base 1, and one end of the lead screw type push rod 4 is connected to the output end of the motor reducer 2.

[0028] The clamping assembly includes a clamping arm 6, a clamping block 7, and a pressure sensor 8. The clamping arm 6 is hinged to the base 1, and the other end of the lead screw push rod 4 is hinged to the clamping arm 6. The hinge axes of the clamping arm 6 and the base 1, and the hinge axes of the clamping arm 6 and the lead screw push rod 4 are parallel. The clamping block 7 is disposed on the clamping arm 6, and the pressure sensor 8 is disposed between the clamping block 7 and the clamping arm 6. The support assembly includes a support frame 10, which supports the arrow body, and the support frame 10 and the clamping block 7 cooperate to clamp the arrow body.

[0029] The push rod motor reducer 2 is hinged on the base 1, the torque limiter 3 is installed at the output end of the push rod motor reducer 2, one end of the lead screw type push rod 4 is connected to the output end of the push rod motor reducer 2, and the other end of the lead screw type push rod 4 is hinged to the arm 6 through the shaft hole and the lead screw shaft 5.

[0030] This application provides a specific clamping component, as follows:

[0031] The clamping assembly includes a clamping arm 6, a clamping block 7, a pressure sensor 8, and a clamping block guide mechanism 9. The clamping arm 6 has an arc-shaped structure, and one end of the arc is hinged to the upper end of the base 1 through a second rotating shaft 15 and a shaft hole. The axis of the second rotating shaft 15 is the rotation axis of the clamping arm 6. The shaft hole on the clamping arm 6 that mates with the lead screw shaft 5 is located on the outer wall of the clamping arm 6. The axial direction of the lead screw shaft 5 is parallel to the axial direction of the second rotating shaft 15, and the linear distance between the lead screw shaft 5 and the second rotating shaft 15 can be adjusted according to actual conditions.

[0032] The clamping block 7 is shaped like a clamp with its opening facing downwards. The clamping block 7 is positioned at the other end of the arc-shaped clamping arm 6. Both the pressure sensor 8 and the clamping block guide mechanism 9 are located between the clamping block 7 and the clamping arm 6. The clamping block guide mechanism 9 provides cushioning during the operation of the clamping block 7, and the pressure sensor 8 detects the pressure borne by the clamping block 7. It should be noted that the clamping block guide mechanism 9 in this application can be a specific elastic rod, such as an elastic telescopic rod.

[0033] During operation, the lead screw type push rod 4 is initially at its minimum stroke. After the push rod motor reducer 2 starts, it drives the lead screw type push rod 4 to extend, causing the clamping arm 6 to move around the second rotating shaft 15, which in turn drives the clamping block 7 to move, thus realizing the clamping action of the clamping assembly. After the clamping block 7 clamps the rocket body, the clamping pressure is transmitted to the pressure sensor 8 through the clamping block 7. When the pressure sensor 8 detects that the force acting on the rocket has reached the set pressure value, it sends a signal to stop the push rod motor reducer 2 from working.

[0034] In a preferred embodiment, there are two pressure sensors 8, which serve as backups for each other. To prevent excessive pressure on the arrow body from the clamping mechanism in case of failure, a torque limiter 3 is installed at the output end of the push rod motor reducer 2. When the torsional torque reaches the set value of the torque limiter 3, the push rod motor reducer 2 idles and does not output torque to the lead screw push rod 4.

[0035] This application provides a specific support component, as follows:

[0036] The support frame guide cylinder 14 is fixedly installed on the base 1. The lower end of the support frame guide rod 11 extends into the support frame guide cylinder 14 and can move axially along the support frame guide cylinder 14. The upper end of the support frame guide rod 11 is fixedly connected to the bottom of the support frame 10. The support frame 10 is an arc-shaped clamp with the opening facing upward.

[0037] A screw lifting mechanism 13 is also configured on the base 1, which drives the support frame 10 to reciprocate in the vertical direction. In one feasible embodiment, the screw lifting mechanism 13 includes a motor and a threaded screw pair. The motor can be located inside the base 1, and the output shaft of the motor is coaxially and fixedly connected to the screw of the threaded screw pair. When the motor starts, it drives the screw of the threaded screw pair to rotate, thereby driving the slider structure of the threaded screw pair to reciprocate along the axial direction of the screw. The slider structure of the threaded screw pair is fixedly connected to the bottom of the support frame 10, thereby realizing that the screw lifting mechanism 13 on the base 1 drives the support frame 10 to move in the vertical direction. Preferably, the slider structure of the threaded screw pair is connected to the middle of the bottom of the support frame 10, which can increase the balance of the movement of the support frame 10. It should be noted that the screw lifting mechanism 13 of this application can also be any drive device in the prior art that can realize linear reciprocating drive.

[0038] The proximity switch bracket 12 is fixedly installed on the base 1. The proximity switch sensor is integrated on the proximity switch bracket 12. The proximity switch sensing iron piece is installed on the support frame 10. The proximity switch sensor is electrically coupled to the proximity switch sensing iron piece.

[0039] The screw lifting mechanism drives the support frame 10 to move up and down. When the proximity switch sensor detects the proximity switch sensing iron plate, it sends a stop rotation signal to the motor of the screw lifting mechanism. In a preferred embodiment, two proximity switch sensors are provided to detect the signal when the support frame 10 rises to the correct position and the signal when the support frame 10 descends to the correct position, respectively.

[0040] During operation, the screw lifting mechanism 13 moves to achieve the raising and lowering of the support frame 10. When the proximity switch sensing plate triggers the proximity switch sensor, the proximity switch sensor sends a raising / lowering completion signal, and the motor of the screw lifting mechanism 13 stops rotating. The support frame guide rod 11 and the support frame guide cylinder 14 are used to ensure that the support frame 10 rises and falls flexibly and moves along the correct path, preventing the support frame 10 from deviating from its arc-shaped posture.

[0041] Working principle:

[0042] In the initial state: the lead screw push rod 4 and the screw lifting mechanism 13 are both at their minimum stroke, the clamping assembly is open, and the support assembly is at its lowest position. Before the rocket is hoisted onto the erecting frame, the control system sends an adjustment signal to the support assembly, and the screw lifting mechanism 13 drives the support frame 10 to rise and fall to complete the adjustment of the rocket's support centerline. After the rocket is hoisted onto the erecting frame, the support assembly supports the rocket body, and the control system sends a clamping signal to the clamping assembly. The push rod motor reducer 2 drives the lead screw push rod 4 to extend, causing the clamping arm 6 to rotate around the central axis of the second pin 15, which drives the clamping block 7 to achieve the clamping action of the clamping assembly. When the pressure between the clamping block 7 and the rocket body reaches the specified value, the push rod motor reducer 2 stops working, achieving effective clamping of the rocket body.

[0043] In the description of this application, it should be understood that the terms "upper", "lower", "front", "horizontal", "inner", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this application.

[0044] The specific embodiments of this application have been described above. It should be understood that this application is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the substantive content of this application. Unless otherwise specified, the embodiments and features described in the embodiments of this application can be arbitrarily combined with each other.

Claims

1. A protective mechanism for the front end of a launch vehicle used in a three-plane launch system, characterized in that, Includes a base (1), on which are configured: a push rod motor reducer (2), a lead screw push rod (4), a clamping assembly and a support assembly; The push rod motor reducer (2) is hinged on the base (1), and one end of the screw type push rod (4) is connected to the output end of the motor reducer (2). The clamping assembly includes a clamping arm (6), a clamping block (7), and a pressure sensor (8). The clamping arm (6) is hinged to the base (1), and the other end of the screw-type push rod (4) is hinged to the clamping arm (6). The hinge axis of the clamping arm (6) and the base (1) and the hinge axis of the clamping arm (6) and the screw-type push rod (4) are parallel to each other. The clamping block (7) is disposed on the clamping arm (6), and the pressure sensor (8) is disposed between the clamping block (7) and the clamping arm (6). The support assembly includes a support frame (10) that supports the arrow body, and the support frame (10) and the clamping block (7) work together to hold the arrow body.

2. The launch vehicle front protection mechanism for a three-plane launch system as described in claim 1, characterized in that, The clamping assembly also includes a clamping block guide mechanism (9), which is disposed between the clamping block (7) and the clamping arm (6).

3. The launch vehicle front protection mechanism for a three-plane launch system as described in claim 1, characterized in that, The other end of the lead screw push rod (4) is hinged to the arm (6) through the shaft hole and the lead screw shaft (5); The arm (6) is arc-shaped, and one end of the arm (6) is hinged to the upper end of the base (1) through the second rotating shaft (15) and the shaft hole; The axial direction of the lead screw shaft (5) is parallel to the axial direction of the second shaft (15).

4. The launch vehicle front protection mechanism for a three-plane launch system as described in claim 1, characterized in that, The pressure sensor (8) is in the form of two, serving as a backup for each other.

5. The launch vehicle front protection mechanism for a three-plane launch system as described in claim 1, characterized in that, The support assembly also includes a spiral lifting mechanism (13), which drives the support frame (10) to reciprocate in the vertical direction.

6. The launch vehicle front protection mechanism for a three-plane launch system as described in claim 1, characterized in that, The support assembly also includes a support frame guide cylinder (14) and a support frame guide rod (11). The support frame guide cylinder (14) is fixedly installed on the base (1). The lower end of the support frame guide rod (11) extends into the support frame guide cylinder (14) and can move along the axial direction of the support frame guide cylinder (14). The upper end of the support frame guide rod (11) is fixedly connected to the bottom of the support frame (10).

7. The launch vehicle front protection mechanism for a three-plane launch system as described in claim 1, characterized in that, The support frame (10) is an arc-shaped clamp with the opening facing upwards.

8. The launch vehicle front protection mechanism for a three-plane launch system as described in claim 1, characterized in that, The support assembly also includes a proximity switch bracket (12); The proximity switch bracket (12) is fixedly installed on the base (1). The proximity switch sensor is integrated on the proximity switch bracket (12). The proximity switch sensing iron plate is installed on the support frame (10). The proximity switch sensor is electrically coupled to the proximity switch sensing iron plate.

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