Overturn-preventing arm auxiliary closing mechanism of seaborne launch rocket stabilizing device

Abstract

The utility model provides an anti-overturning arm auxiliary closing mechanism of a seaborne launch rocket stabilizing device. The anti-overturning arm auxiliary closing mechanism comprises a first anti-overturning arm auxiliary closing mechanism and a second anti-overturning arm auxiliary closing mechanism. The first anti-overturning arm auxiliary closing mechanism and the second anti-overturning arm auxiliary closing mechanism are arranged at the bottom of a first anti-overturning device and the bottom of a second anti-overturning device of the seaborne launch rocket stabilizing device correspondingly. When the first anti-overturning device is in an overturning state, the first anti-overturning arm auxiliary closing mechanism adjusts the first anti-overturning device to be in a vertical state; and when the second anti-overturning device is in an overturning state, the second anti-overturning arm auxiliary closing mechanism adjusts the second anti-overturning device to be in a vertical state. According to the supporting device, in-place supporting of the marine launch rocket stabilizing device is achieved, the anti-overturning arm auxiliary closing mechanism and the anti-overturning arm of the marine launch rocket stabilizing device can be switched to be in a supporting state or a separation state, and the reliability, stability and safety of the marine launch rocket stabilizing device are improved.

Description

Technical Field

[0001] The present application relates to the field of rocket launching technology, and in particular to an auxiliary closing mechanism for an anti-overturning arm of a stabilizing device for launching a rocket at sea. Background Art

[0002] Currently, sea-based rocket launches have become an important method, offering greater planning flexibility and safer geographical applicability than land-based launches, and relatively mature and stable offshore launch platforms. However, sea launch conditions are affected by sea conditions and climate. The uncertainty of sea waves causes the ship's hull to roll and pitch, which is transmitted to the launch platform, affecting the stability of the rocket before and after erection. After erection, the rocket is less stable when parked on the launch platform. The large overturning moment caused by the ship's swaying can easily lead to structural failure or even overturning of the rocket. Excessive inclination of the rocket not only affects launch control accuracy but can also cause it to tip over, resulting in launch failure or even an accident. Maintaining a stable and safe free-standing attitude for the rocket before ignition is crucial.

[0003] Existing patent publication number CN117950302A provides a support and control system for a rocket offshore hot launch platform. This system effectively protects the platform, improving the capability of offshore hot launch missions and offering high reliability. However, this system only supports and controls the platform, but does not support or stabilize the rocket, nor prevent it from tipping over.

[0004] At present, the sea-launched rocket stabilizing device does not have an anti-overturning arm auxiliary closing mechanism to achieve the closing of the auxiliary anti-overturning arm of the sea-launched rocket stabilizing device and switch between the support state and the separation state.

[0005] Therefore, the technical problem that urgently needs to be solved is: how to provide an anti-overturning arm auxiliary closing mechanism for a sea-launched rocket stabilizing device to achieve full support for the sea-launched rocket stabilizing device, and to switch the anti-overturning arm auxiliary closing mechanism and the anti-overturning arm of the sea-launched rocket stabilizing device to a supporting state or a separated state, thereby improving the reliability, stability and safety of the sea-launched rocket stabilizing device. Utility Model Content

[0006] The purpose of this application is to provide an anti-overturning arm auxiliary closing mechanism for a sea-launched rocket stabilizing device, so as to achieve full support for the sea-launched rocket stabilizing device, and to switch the anti-overturning arm auxiliary closing mechanism and the anti-overturning arm of the sea-launched rocket stabilizing device to a supporting state or a separated state, thereby improving the reliability, stability and safety of the sea-launched rocket stabilizing device.

[0007] To achieve the above-mentioned purpose, the present application provides an anti-overturning arm auxiliary closing mechanism of a sea-launched rocket stabilizing device, wherein the anti-overturning arm auxiliary closing mechanism includes two groups of anti-overturning arm auxiliary closing mechanisms, namely a first anti-overturning arm auxiliary closing mechanism and a second anti-overturning arm auxiliary closing mechanism; the first anti-overturning arm auxiliary closing mechanism and the second anti-overturning arm auxiliary closing mechanism are respectively arranged at the bottom of the first anti-overturning device and the second anti-overturning device of the sea-launched rocket stabilizing device; when the first anti-overturning device is in a tilted state, the first anti-overturning arm auxiliary closing mechanism adjusts the first anti-overturning device to a vertical state; when the second anti-overturning device is in a tilted state, the second anti-overturning arm auxiliary closing mechanism adjusts the second anti-overturning device to a vertical state.

[0008] The anti-overturning arm auxiliary closing mechanism of the sea-launched rocket stabilizing device as described above, wherein the sea-launched rocket stabilizing device includes: a first anti-overturning device and a second anti-overturning device, the first anti-overturning device and the second anti-overturning device are fixedly connected to the launch platform, and the first anti-overturning device and the second anti-overturning device are respectively supported and connected on both sides of the rocket; the first anti-overturning device and the second anti-overturning device have the same structure; the rocket is vertically arranged on the launch platform; the first anti-overturning device and the second anti-overturning device both include: an anti-overturning device base frame, an anti-overturning arm and a bracket; the bottom end of the anti-overturning arm is installed on the anti-overturning device base frame, the bracket is fixedly connected to the top end of the anti-overturning arm, and the bracket is used to fix and hold the side of the rocket body connected to the rocket.

[0009] The anti-overturning arm auxiliary closing mechanism of the sea-launched rocket stabilizing device as described above, wherein the first anti-overturning arm auxiliary closing mechanism and the second anti-overturning arm auxiliary closing mechanism are arranged on the anti-overturning device base frame, and the first anti-overturning arm auxiliary closing mechanism and the second anti-overturning arm auxiliary closing mechanism are arranged at the bottom of the anti-overturning arm.

[0010] The anti-overturning arm auxiliary closing mechanism of the sea-launched rocket stabilizing device as described above, wherein the first anti-overturning arm auxiliary closing mechanism and the second anti-overturning arm auxiliary closing mechanism both include an erecting cylinder and an auxiliary support cylinder; one end of the erecting cylinder is connected to the anti-overturning device base frame, and the other end is connected to the bottom of the anti-overturning arm; the auxiliary support cylinder is obliquely supported and connected to the side of the erecting cylinder, one end of the auxiliary support cylinder is connected to the anti-overturning device base frame, and the other end is connected to the erecting cylinder.

[0011] As described above, the anti-overturning arm auxiliary closing mechanism of the sea-launched rocket stabilizing device, wherein the bottom of the erecting cylinder is connected to the anti-overturning device base frame through a first hinge support, and the top is connected to the anti-overturning arm through a third hinge support.

[0012] The anti-overturning arm auxiliary closing mechanism of the sea-launched rocket stabilizing device as described above, wherein the top of the erecting cylinder is connected to the third hinge support through a pin, and the pin is inserted into the through hole of the third hinge support and the through hole at the top of the erecting cylinder to connect the third hinge support and the erecting cylinder together.

[0013] As described above, the anti-overturning arm auxiliary closing mechanism of the sea-launched rocket stabilizing device, wherein the end of the latch is connected to the latch cylinder; the latch cylinder is fixedly connected to the bottom of the anti-overturning arm through a fixed connecting seat.

[0014] As described above, the anti-overturning arm auxiliary closing mechanism of the sea-launched rocket stabilizing device, wherein the latch cylinder is coaxially arranged with the latch, and the latch cylinder drives the latch to move along its axial direction.

[0015] As described above, the anti-overturning arm auxiliary closing mechanism of the sea-launched rocket stabilizing device, wherein the bottom end of the auxiliary support cylinder is connected to the anti-overturning device base frame through a second hinge support, and the top end is rotatably connected to the side wall of the erecting cylinder.

[0016] The anti-overturning arm auxiliary closing mechanism of the sea-launched rocket stabilizing device as described above, wherein, when the anti-overturning arm needs to be opened, the anti-overturning arm auxiliary closing mechanism is closed, the telescopic rod of the latch cylinder is retracted, the latch is pulled out from the through hole of the third hinge support and the through hole at the top end of the erecting cylinder, the erecting cylinder is separated from the anti-overturning arm, and the anti-overturning arm is released.

[0017] The beneficial effects achieved by this application are as follows:

[0018] (1) The auxiliary closing mechanism of the anti-overturn arm of the present application is supported and connected to the bottom of the anti-overturn arm, which supports and adjusts the anti-overturn arm. When the anti-overturn arm is in a tilting state, the auxiliary closing mechanism of the anti-overturn arm will raise the anti-overturn arm to a vertical state, thereby achieving a good fit between the anti-overturn arm and the rocket body, ensuring the anti-overturn effect of the anti-overturn arm on the rocket.

[0019] (2) The telescopic rod of the latch cylinder of the present application retracts, and the telescopic rod of the latch cylinder drives the latch in the through hole of the erection cylinder and the through hole of the third hinge support at the bottom of the anti-rollover arm to be pulled out, and the auxiliary closing mechanism of the anti-rollover arm is unlocked from the anti-rollover arm, thereby releasing the anti-rollover arm without affecting the launch of the rocket. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments recorded in this application. For those skilled in the art, other drawings can also be obtained based on these drawings.

[0021] Figure 1 This is a structural schematic diagram of the connection between the anti-overturning arm auxiliary closing mechanism and the rocket of a sea-launched rocket stabilization device in an embodiment of the present application.

[0022] Figure 2 This is a structural schematic diagram of the anti-overturning arm auxiliary closing mechanism of a sea-launched rocket stabilization device in an embodiment of the present application.

[0023] Figure markings: 1-first anti-overturning device; 2-second anti-overturning device; 3-rocket; 4-launching platform; 11-anti-overturning device chassis; 12-anti-overturning arm; 13-anti-overturning arm auxiliary closing mechanism; 15-support; 131-erecting cylinder; 132-auxiliary supporting cylinder; 133-latch; 134-latch cylinder; 135-first hinge support; 136-second hinge support; 137-third hinge support; 138-fixed connecting seat. DETAILED DESCRIPTION

[0024] The following is a clear and complete description of the technical solutions in the embodiments of the present application in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without making creative efforts are within the scope of protection of this application.

[0025] like Figure 1-2As shown, the present application provides an anti-overturning arm auxiliary closing mechanism for a sea-launched rocket stabilizing device. The sea-launched rocket stabilizing device includes: a first anti-overturning device 1 and a second anti-overturning device 2. The first anti-overturning device 1 and the second anti-overturning device 2 are fixedly connected to the launch platform 4. The first anti-overturning device 1 and the second anti-overturning device 2 are respectively supported and connected to both sides of the rocket 3; the first anti-overturning device 1 and the second anti-overturning device 2 have the same structure; the rocket 3 is vertically arranged on the launch platform 4. The first anti-overturning device 1 and the second anti-overturning device 2 both include: an anti-overturning device chassis 11, an anti-overturning arm 12 and a bracket 15; the bottom end of the anti-overturning arm 12 is mounted on the anti-overturning device chassis 11, and the bracket 15 is fixedly connected to the top end of the anti-overturning arm 12. The bracket 15 is used to fix and hold the side of the rocket body connected to the rocket 3. The bottom end of the anti-overturning arm 12, close to the rocket 3, is rotatably connected to the anti-overturning device chassis 11. The first and second anti-overturning devices 1 and 2 are positioned on either side of the rocket body, capable of withstanding the horizontal overturning force of the rocket 3 in sea conditions up to level 4. To accommodate both near- and far-sea launches, the first and second anti-overturning devices 1 and 2 reliably support the rocket body before launch, preventing it from capsizing. During launch, the rocket body can be quickly deployed before leaving the launch pad 4, ensuring unimpeded flight.

[0026] As a specific embodiment of the present invention, the anti-overturning device chassis 11 includes a horizontal chassis and a vertical support frame, the vertical support frame is vertically fixedly connected to the horizontal chassis, and the bottom end of the anti-overturning arm 12 close to the rocket 3 is rotatably connected to the vertical support frame via a rotating shaft. When the anti-overturning arm 12 needs to be supported on both sides of the rocket 3, the bottom end of the anti-overturning arm 12 away from the rocket 3 is supported by the support device, and the anti-overturning arm 12 cannot rotate around the rotating shaft rotatably connected to the anti-overturning arm 12 and the vertical support frame. When the rocket 3 needs to be launched, the support device at the end of the bottom of the anti-overturning arm 12 away from the rocket 3 is unlocked, and no support is provided for the end of the bottom of the anti-overturning arm 12 away from the rocket 3. The anti-overturning arm 12 can rotate around the rotating shaft rotatably connected to the anti-overturning arm 12 and the vertical support frame. The anti-overturning arm 12 is no longer tightly fixed to the rocket 3, thereby releasing the rocket 3, and the rocket 3 can be launched smoothly.

[0027] As a specific embodiment of the present invention, the anti-overturning arm 12 adopts an overall truss structure, which offers advantages such as high rigidity and excellent stability. A counterweight is mounted on the end of the anti-overturning arm 12, away from the arrow body. The counterweight increases the gravity at this end of the anti-overturning arm 12. Without support from a supporting device, the counterweight enables the anti-overturning arm 12 to passively open quickly, resulting in a fast response. The counterweight is an existing product.

[0028] like Figure 1As shown, the anti-overturning arm auxiliary closing mechanism 13 is arranged on the anti-overturning device chassis 11, and the anti-overturning arm auxiliary closing mechanism 13 is arranged at the bottom of the anti-overturning arm 12. The anti-overturning arm auxiliary closing mechanism 13 is vertically arranged at the bottom of the anti-overturning arm 12, and the anti-overturning arm auxiliary closing mechanism 13 is vertically supported and connected to the bottom of the anti-overturning arm 12, so that the bottom frame of the anti-overturning arm 12 is in a horizontal state, and the anti-overturning arm 12 is in a vertical state as a whole, so that the anti-overturning arm 12 is tightly connected to the side of the rocket 3, supporting and preventing the rocket 3 from overturning. The anti-overturning arm auxiliary closing mechanism 13 is used to make the anti-overturning arm 12 stand up from the tilted state to the vertical state; when the anti-overturning arm 12 needs to be tilted back, the anti-overturning arm auxiliary closing mechanism 13 is unlocked from the anti-overturning arm 12, and the anti-overturning arm auxiliary closing mechanism 13 is no longer supported at the bottom of the anti-overturning arm 12.

[0029] like Figure 1 As shown, the anti-rollover arm auxiliary closing mechanism 13 includes two groups: a first anti-rollover arm auxiliary closing mechanism and a second anti-rollover arm auxiliary closing mechanism. The first and second anti-rollover arm auxiliary closing mechanisms have the same structure and are symmetrically arranged. Both the first and second anti-rollover arm auxiliary closing mechanisms are connected to the anti-rollover device chassis 11.

[0030] like Figure 1 As shown, a first anti-tip arm auxiliary closing mechanism and a second anti-tip arm auxiliary closing mechanism are respectively provided at the bottom of the first anti-tip device 1 and the second anti-tip device 2. The first anti-tip arm auxiliary closing mechanism is used to support the first anti-tip device 1 so that the first anti-tip device 1 can be adjusted to a vertical state when it is tilted, and the second anti-tip arm auxiliary closing mechanism supports the second anti-tip device 2 so that the second anti-tip device 2 can be adjusted to a vertical state when it is tilted. When x needs to tilt the first anti-tip device 1 or the second anti-tip device 2, the first anti-tip arm auxiliary closing mechanism or the second anti-tip arm auxiliary closing mechanism is unlocked. After the first anti-tip arm auxiliary closing mechanism is unlocked, the first anti-tip arm auxiliary closing mechanism is no longer supported on the bottom of the first anti-tip device 1. After the second anti-tip arm auxiliary closing mechanism is unlocked, the second anti-tip arm auxiliary closing mechanism is no longer supported on the bottom of the second anti-tip device 2.

[0031] like Figure 2As shown, the anti-rollover arm auxiliary closing mechanism 13 includes an erecting cylinder 131 and an auxiliary supporting cylinder 132; that is, the first anti-rollover arm auxiliary closing mechanism and the second anti-rollover arm auxiliary closing mechanism both include an erecting cylinder 131 and an auxiliary supporting cylinder 132, one end of the erecting cylinder 131 is connected to the anti-rollover device base frame 11, and the other end is connected to the bottom of the anti-rollover arm 12; the erecting cylinder 131 is arranged perpendicular to the anti-rollover device base frame 11; the auxiliary supporting cylinder 132 is obliquely supported and connected to the side of the erecting cylinder 131, one end of the auxiliary supporting cylinder 132 is connected to the anti-rollover device base frame 11, and the other end is connected to the erecting cylinder 131.

[0032] like Figure 2 As shown, the bottom of the erecting cylinder 131 is connected to the anti-overturning device base frame 11 via a first hinge support 135, and the top is connected to the anti-overturning arm 12 via a third hinge support 137. The first hinge support 135 is fixedly connected to the anti-overturning device base frame 11, and the third hinge support 137 is fixedly connected to the bottom of the anti-overturning arm 12.

[0033] like Figure 2 As shown, the top of the erecting cylinder 131 is connected to the third hinge support 137 through a pin 133, and the pin 133 is inserted into the through hole of the third hinge support 137 and the through hole at the top of the erecting cylinder 131, thereby connecting the third hinge support 137 and the erecting cylinder 131 together.

[0034] like Figure 2 As shown, the auxiliary support cylinder 132 is tilted and arranged beside the erecting cylinder 131. The auxiliary support cylinder 132 is connected to the erecting cylinder 131. The erecting cylinder 131 extends and supports the anti-rollover arm 12. During the closing process, the erecting cylinder 131 directly extends and adjusts the anti-rollover arm 12 to a vertical state, and the auxiliary support cylinder 132 is in a follow-up extendable state. After the erecting cylinder 131 supports the anti-rollover arm 12 and closes it in place (i.e., after the anti-rollover arm 12 holds the rocket body tightly) or when the anti-rollover arm 12 needs to be tilted, the latch cylinder 134 drives the latch 133 to retract, the erecting cylinder 131 and the anti-rollover arm 12 are unlocked, the auxiliary support cylinder 132 retracts, and drives the erecting cylinder 131 to fall back.

[0035] like Figure 2 As shown, the bottom end of the auxiliary support cylinder 132 is connected to the anti-overturning device chassis 11 through a second hinge support 136, and the top end is rotatably connected to the side wall of the erecting cylinder 131. The second hinge support 136 is fixedly connected to the anti-overturning device chassis 11.

[0036] like Figure 2As shown, the end of the latch 133 is connected to the latch cylinder 134; the latch cylinder 134 is fixedly connected to the bottom of the anti-overturning arm 12 through a fixed connection seat 138. The latch cylinder 134 is used to pull the latch 133 so that the latch 133 is inserted into or removed from the through hole of the third hinge support 137 and the through hole at the top of the erecting cylinder 131.

[0037] As a specific embodiment of the present invention, the latch cylinder 134 is coaxially arranged with the latch 133, and the latch cylinder 134 drives the latch 133 to move along its axis. As a specific embodiment of the present invention, the erecting cylinder 131, the auxiliary support cylinder 132 and the latch cylinder 134 are all existing cylinders.

[0038] As a specific embodiment of the present invention, when the anti-overturning arm 12 needs to be tilted, the telescopic rod of the latch cylinder 134 retracts, driving the latch 133 to be pulled out from the through hole of the third hinge support 137 and the through hole at the top end of the erecting cylinder 131, and the latch 133 disengages from the through hole of the third hinge support 137 and the through hole at the top end of the erecting cylinder 131, so that the top end of the erecting cylinder 131 is separated from the third hinge support 137, and then the erecting cylinder 131 is separated from the anti-overturning arm 12, thereby releasing the anti-overturning arm 12, and the erecting cylinder 131 no longer supports the anti-overturning arm 12.

[0039] As a specific embodiment of the present utility model, the anti-overturning device chassis 11 has a fixed structure connected to the deck of the launch platform 4, thereby achieving a fixed connection with the launch platform 4.

[0040] As a specific embodiment of the present invention, before the anti-overturn arm auxiliary closing mechanism 13 is closed, the anti-overturn arm 12 is in a tilted state. The anti-overturn arm auxiliary closing mechanism 13 is activated to adjust the anti-overturn arm 12 to a vertical state. After the anti-overturn arm 12 is aligned with the arrow body, the erecting cylinder 131 includes a fixed tube and a telescopic rod. The telescopic rod is telescopically connected within the fixed tube. The fixed tube is connected to the anti-overturn device chassis 11. The telescopic rod of the erecting cylinder 131 has a through hole. The third hinge support 137 fixedly connected to the bottom of the anti-overturn arm 12 also has a through hole. The through hole of the telescopic rod of the erecting cylinder 131 is coaxially connected to the through hole of the third hinge support 137 fixedly connected to the bottom of the anti-overturn arm 12. The erecting cylinder 131 is connected to the anti-overturning arm 12 through a pin shaft 133. After the erecting cylinder 131 is extended until the anti-overturning arm 12 is in contact with the arrow body, the anti-overturning arm 12 is in a vertical state as a whole, and the erecting cylinder 131 supports the anti-overturning arm 12.

[0041] As a specific embodiment of the present invention, the process of the anti-overturning arm auxiliary closing mechanism 13 of the present invention erecting the anti-overturning arm is as follows:

[0042] Adjust the length of the erecting cylinder 131 and the auxiliary support cylinder 132;

[0043] The through hole of the erecting oil cylinder 131 is coaxially connected to the through hole of the third hinge support 137 at the bottom of the anti-overturning arm 12 via a latch 133;

[0044] The auxiliary support cylinder 132 switches to the follow-up mode;

[0045] The erecting cylinder 131 is extended until the anti-overturning arm 12 is erected into place.

[0046] As a specific embodiment of the present invention, the unlocking and reversing process of the anti-overturning arm auxiliary closing mechanism 13 and the anti-overturning arm 12 is as follows:

[0047] The auxiliary support cylinder 132 switches to active mode;

[0048] The telescopic rod of the latch cylinder 134 is retracted, and the latch 133 in the through hole of the erecting cylinder 131 and the through hole of the third hinge support 137 at the bottom of the anti-overturning arm 12 is pulled out, and the anti-overturning arm auxiliary closing mechanism 13 is unlocked from the anti-overturning arm 12;

[0049] The erecting cylinder 131 retracts;

[0050] The auxiliary supporting cylinder 132 retracts, driving the erecting cylinder 131 to fall back.

[0051] The beneficial effects achieved by this application are as follows:

[0052] (1) The auxiliary closing mechanism of the anti-overturn arm of the present application is supported and connected to the bottom of the anti-overturn arm, which supports and adjusts the anti-overturn arm. When the anti-overturn arm is in a tilting state, the auxiliary closing mechanism of the anti-overturn arm will raise the anti-overturn arm to a vertical state, thereby achieving a good fit between the anti-overturn arm and the rocket body, ensuring the anti-overturn effect of the anti-overturn arm on the rocket.

[0053] (2) The telescopic rod of the latch cylinder of the present application retracts, and the telescopic rod of the latch cylinder drives the latch in the through hole of the erection cylinder and the through hole of the third hinge support at the bottom of the anti-rollover arm to be pulled out, and the auxiliary closing mechanism of the anti-rollover arm is unlocked from the anti-rollover arm, thereby releasing the anti-rollover arm without affecting the launch of the rocket.

[0054] In the description of this application, the terms "first" and "second" are used for descriptive purposes only and should not be understood to indicate or imply relative importance or implicitly specify the number of the technical features indicated. Therefore, a feature specified as "first" or "second" may explicitly or implicitly include one or more of the described features. In the description of this application, "plurality" means two or more, unless otherwise specifically specified.

[0055] In the description of this application, the word "for example" is used to mean "used as an example, illustration or explanation". Any embodiment described as "for example" in this application is not necessarily to be construed as being more preferred or advantageous than other embodiments. The following description is given to enable any person skilled in the art to implement and use the present invention. In the following description, details are listed for the purpose of explanation. It should be understood that a person of ordinary skill in the art can recognize that the present invention can be implemented without using these specific details. In other examples, well-known structures and processes will not be elaborated in detail to avoid obscuring the description of the present invention with unnecessary details. Therefore, the present invention is not intended to be limited to the embodiments shown, but is consistent with the widest scope consistent with the principles and features disclosed in this application.

[0056] The above description is merely an embodiment of the present invention and is not intended to limit the present invention. Those skilled in the art will readily appreciate that various modifications and variations of the present invention are possible. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present invention are intended to be included within the scope of the claims of the present invention.

Claims

1. An auxiliary closing mechanism for an anti-overturning arm of a sea-launched rocket stabilizing device, characterized in that: The anti-overturning arm auxiliary closing mechanism includes two groups of anti-overturning arm auxiliary closing mechanisms, namely a first anti-overturning arm auxiliary closing mechanism and a second anti-overturning arm auxiliary closing mechanism; The first anti-overturning arm auxiliary closing mechanism and the second anti-overturning arm auxiliary closing mechanism are respectively arranged at the bottom of the first anti-overturning device and the second anti-overturning device of the sea-launched rocket stabilizing device; When the first anti-overturning device is in a tilted state, the first anti-overturning arm auxiliary closing mechanism adjusts the first anti-overturning device to a vertical state; When the second anti-overturning device is in a tilted state, the second anti-overturning arm auxiliary closing mechanism adjusts the second anti-overturning device to a vertical state.

2. The anti-overturning arm auxiliary closing mechanism of the sea-launched rocket stabilizing device according to claim 1 is characterized in that: The sea-launched rocket stabilizing device includes: a first anti-overturning device and a second anti-overturning device, the first anti-overturning device and the second anti-overturning device are fixedly connected to the launch platform, and the first anti-overturning device and the second anti-overturning device are respectively supported and connected on both sides of the rocket; the first anti-overturning device and the second anti-overturning device have the same structure; the rocket is vertically set on the launch platform; The first anti-overturning device and the second anti-overturning device each include: an anti-overturning device chassis, an anti-overturning arm and a bracket; The bottom end of the anti-overturning arm is mounted on the anti-overturning device chassis, and the bracket is fixedly connected to the top end of the anti-overturning arm. The bracket is used to fix and tightly connect to the side of the rocket body.

3. The anti-overturning arm auxiliary closing mechanism of the sea-launched rocket stabilizing device according to claim 2 is characterized in that: The first anti-rollover arm auxiliary closing mechanism and the second anti-rollover arm auxiliary closing mechanism are arranged on the anti-rollover device chassis, and the first anti-rollover arm auxiliary closing mechanism and the second anti-rollover arm auxiliary closing mechanism are arranged at the bottom of the anti-rollover arm.

4. The anti-overturning arm auxiliary closing mechanism of the sea-launched rocket stabilizing device according to claim 3 is characterized in that: The first anti-overturning arm auxiliary closing mechanism and the second anti-overturning arm auxiliary closing mechanism each include an erecting oil cylinder and an auxiliary supporting oil cylinder; One end of the erecting oil cylinder is connected to the base frame of the anti-overturning device, and the other end is connected to the bottom of the anti-overturning arm; The auxiliary supporting oil cylinder is connected to the side of the erecting oil cylinder with an oblique support. One end of the auxiliary supporting oil cylinder is connected to the anti-overturning device chassis, and the other end is connected to the erecting oil cylinder.

5. The anti-overturning arm auxiliary closing mechanism of the sea-launched rocket stabilizing device according to claim 4 is characterized in that: The bottom of the erecting oil cylinder is connected to the anti-overturning device chassis through a first hinge support, and the top is connected to the anti-overturning arm through a third hinge support.

6. The anti-overturning arm auxiliary closing mechanism of the sea-launched rocket stabilizing device according to claim 5, characterized in that: The top of the erecting cylinder is connected to the third hinge support through a pin, and the pin is inserted into the through hole of the third hinge support and the through hole at the top of the erecting cylinder to connect the third hinge support and the erecting cylinder together.

7. The anti-overturning arm auxiliary closing mechanism of the sea-launched rocket stabilizing device according to claim 6 is characterized in that: The end of the latch is connected to the latch cylinder; The latch oil cylinder is fixedly connected to the bottom of the anti-overturning arm through a fixed connecting seat.

8. The anti-overturning arm auxiliary closing mechanism of the sea-launched rocket stabilizing device according to claim 7, characterized in that: The latch oil cylinder is coaxially arranged with the latch, and the latch oil cylinder drives the latch to move along the axis direction thereof.

9. The anti-overturning arm auxiliary closing mechanism of the sea-launched rocket stabilizing device according to claim 4, characterized in that: The bottom end of the auxiliary supporting oil cylinder is connected to the bottom frame of the anti-overturning device through a second hinge support, and the top end is rotatably connected to the side wall of the erecting oil cylinder.

10. The anti-overturning arm auxiliary closing mechanism of the sea-launched rocket stabilizing device according to claim 7, characterized in that: When the anti-overturning arm needs to be opened, the auxiliary closing mechanism of the anti-overturning arm is closed, the telescopic rod of the latch cylinder is retracted, the latch is pulled out from the through hole of the third hinge support and the through hole at the top end of the erecting cylinder, the erecting cylinder is separated from the anti-overturning arm, and the anti-overturning arm is released.

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