Marine rocket launching stabilizing device

Abstract

The invention provides an offshore launch rocket stabilizing device which comprises 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 with a launching pad, and the first anti-overturning device and the second anti-overturning device are connected to the two sides of a rocket in a supporting mode correspondingly; the first anti-overturning device and the second anti-overturning device are the same in structure; each of the first anti-overturning device and the second anti-overturning device comprises an anti-overturning device underframe, an anti-overturning arm and a bracket; the bottom end of the anti-overturning arm is installed on the anti-overturning device bottom frame, the bracket is fixedly connected to the top end of the anti-overturning arm, and the bracket is used for being fixedly connected to the side portion of a rocket body of a rocket in a clasping mode. The end, close to the rocket, of the bottom of the anti-overturning arm is rotationally connected with the anti-overturning device underframe, and the other end of the anti-overturning arm is supported on the anti-overturning device underframe through a supporting and rapid separating mechanism. After the rocket is erected and parked on the launching platform, the rocket body is stabilized, the rocket is prevented from toppling over, and the stability and safety of the rocket are improved.

Description

Technical Field

[0001] The present application relates to the field of rocket launching technology, and in particular to a device for stabilizing a rocket launched at sea. Background Art

[0002] At present, launching rockets at sea has become an important method. Compared with launching on land, it has higher planning flexibility and safer geographical applicability, and the construction of launch platforms at sea is relatively mature and stable. However, the conditions for launching at sea are affected by sea conditions and climate. Due to the uncertainty of sea waves, the hull rolls and pitches, which are transmitted to the launch platform, thus affecting the stability of the rocket before and after erection. After the rocket is erected, it has poor stability when parked on the launch platform. Due to the large overturning moment of the rocket body caused by the shaking of the ship, it is easy to cause the rocket body structure to fail, or even the rocket to overturn. The excessive inclination of the rocket will not only affect the launch control accuracy, but may also cause the rocket to tip over, resulting in launch failure or even launch accidents. It is crucial to keep the rocket in a stable and safe posture during the free standing period before the launch ignition.

[0003] The existing patent publication number is: CN117950302A, which provides a support control system for a rocket offshore thermal launch platform, which can provide effective protection for the rocket offshore thermal launch platform, improve the ability of offshore thermal launch missions, and has high reliability. However, it only provides support control for the rocket offshore thermal launch platform, and cannot provide support and stabilization for the rocket, and cannot prevent the rocket from tipping over.

[0004] Therefore, the technical problem that urgently needs to be solved is: how to provide a stabilizing device for sea-launched rockets to stabilize the rocket body after the rocket is erected and parked on the launch platform, prevent the rocket from tipping over, and improve the stability and safety of the rocket. Summary of the invention

[0005] The purpose of the present application is to provide a device for stabilizing a rocket launched at sea, which can stabilize the rocket body after the rocket is erected and parked on the launch platform, prevent the rocket from tipping over, and improve the stability and safety of the rocket.

[0006] To achieve the above-mentioned purpose, the present application provides a stabilizing device for launching a rocket at sea, comprising: 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, 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 comprise: an anti-overturning device chassis, an anti-overturning arm and a bracket; the bottom end of the anti-overturning arm is installed on the anti-overturning device chassis, 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 arrow body connected to the rocket.

[0007] As described above, in the sea-launched rocket stabilizing device, one end of the bottom of the anti-overturning arm close to the rocket is rotatably connected to the anti-overturning device chassis, and the other end is supported on a support and quick separation mechanism, and the support and quick separation mechanism is connected to the anti-overturning device chassis.

[0008] The sea-launched rocket stabilizing device as described above, wherein the first anti-overturning device and the second anti-overturning device also include an anti-overturning arm auxiliary closing mechanism and a shock-absorbing and anti-rebound mechanism; the anti-overturning arm auxiliary closing mechanism and the shock-absorbing and anti-rebound mechanism are both connected to the anti-overturning device chassis; the anti-overturning arm auxiliary closing mechanism is supported and connected to the bottom of the anti-overturning arm; the anti-overturning arm auxiliary closing mechanism is used to make the anti-overturning arm stand up from a tilted state to a vertical state, and after the support and quick separation mechanism supports the anti-overturning arm; the anti-overturning arm auxiliary closing mechanism is unlocked and retracted from the anti-overturning arm to release the anti-overturning arm; the shock-absorbing and anti-rebound mechanism is used to play a buffering role when the anti-overturning arm is opened into place, and to prevent the anti-overturning arm from rebounding.

[0009] The sea-launched rocket stabilizing device as described above, wherein the anti-overturning arm auxiliary closing mechanism includes an erecting cylinder, a latch cylinder and an auxiliary supporting cylinder; one end of the erecting cylinder is connected to the anti-overturning device chassis, and the other end is connected to the bottom of the anti-overturning arm through a latch pushed by the latch cylinder; the auxiliary supporting cylinder is obliquely supported and connected to the side of the erecting cylinder, one end of the auxiliary supporting cylinder is connected to the anti-overturning device chassis, and the other end is connected to the erecting cylinder.

[0010] The sea-launched rocket stabilizing device as described above, wherein the shock-absorbing and anti-rebound mechanism includes: an inclined pressure rod and an elastic support rod; the end of the inclined pressure rod is rotatably connected to the anti-overturning device base frame, and the elastic support rod is obliquely supported and connected to the side of the inclined pressure rod; when the anti-overturning arm tilts to a certain angle, the side surface of the anti-overturning arm fits against the inclined pressure rod, and the elastic support rod is compressed, thereby playing a buffering role for the anti-overturning arm; when the anti-overturning arm falls back into place, the inclined pressure rod limits the anti-overturning arm due to the support force of the inclined pressure rod.

[0011] The sea-launched rocket stabilizing device as described above, wherein the support and quick separation mechanism is connected to the anti-overturning device chassis; the support and quick separation mechanism is supported at the bottom of the anti-overturning arm at one end away from the rocket; the support and quick separation mechanism is used to support the anti-overturning arm before the rocket is launched, and when the rocket is ignited, the support and quick separation mechanism is passively unlocked, and the anti-overturning arm opens under the action of gravity.

[0012] The sea-launched rocket stabilizing device as described above, wherein the support and quick separation mechanism includes a two-stage load-reducing support mechanism, a transition zone, an aluminum strip connecting mechanism, an aluminum strip recovery mechanism and an aluminum strip; both ends of the aluminum strip are connected to the anti-overturning device chassis through the aluminum strip connecting mechanism, the aluminum strip recovery mechanism, the transition zone and the two-stage load-reducing support mechanism; the aluminum strip connecting mechanism is connected to the end of the aluminum strip, one end of the aluminum strip recovery mechanism is connected to the aluminum strip connecting mechanism, and the other end is connected to the transition zone, and the end of the transition zone away from the aluminum strip recovery mechanism is connected to the two-stage load-reducing support mechanism; the two-stage load-reducing support mechanism is connected to the anti-overturning device chassis and supported at the bottom of the anti-overturning arm, so that the force transmitted to the aluminum strip by the anti-overturning arm is proportionally reduced.

[0013] The sea-launched rocket stabilizing device as described above, wherein the support and quick separation mechanism also includes: an aluminum belt tensioning mechanism; the aluminum belt tensioning mechanism is connected to the side of the two-stage load-reducing support mechanism and is connected to the transition belt, and the aluminum belt tensioning mechanism is used to tighten the transition belt and the aluminum belt, so that the two-stage load-reducing support mechanism presses against the anti-overturning arm, and the anti-overturning arm firmly holds the rocket body.

[0014] In the sea-launched rocket stabilizing device as described above, a tension sensor is connected between the aluminum belt tensioning mechanism and the transition belt, and the tension sensor is used to detect whether the aluminum belt is in a tensioned state, so as to determine whether the anti-overturning arm is closed in place to hold the rocket body.

[0015] As described above, in the sea-launched rocket stabilizing device, when the rocket is ignited, the impact force of the rocket tail flame breaks the aluminum strip, the two-stage load-reducing support mechanism is unlocked, the anti-overturning arm is released, and the anti-overturning arm overturns.

[0016] The beneficial effects achieved by this application are as follows:

[0017] (1) The first anti-overturning device and the second anti-overturning device of the present application can reliably support the rocket body to prevent overturning before the rocket is launched. When the rocket is launched, the rocket body can be quickly opened before leaving the launch pad without hindering the flight of the rocket body.

[0018] (2) The shock-absorbing and anti-rebound mechanism of the present application can play a buffering role when the anti-rollover arm is fully opened, reduce the vibration impact generated when the anti-rollover arm is opened, and prevent the anti-rollover arm from rebounding. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in the present application. For those skilled in the art, other drawings can also be obtained based on these drawings.

[0020] Figure 1 This is a structural schematic diagram of a rocket stabilization device for sea-launched rocket connected to a rocket in an embodiment of the present application.

[0021] Figure 2 This is a schematic structural diagram of a rocket stabilization device for sea-launched rockets according to an embodiment of the present application.

[0022] Figure 3 This is a schematic diagram of the structure of the support and rapid separation mechanism of a stabilizing device for sea-launched rockets in an embodiment of the present application.

[0023] Figure 4 It is a schematic diagram of the installation of the anti-overturning arm auxiliary closing mechanism and the shock-absorbing and anti-rebound mechanism of an embodiment of the present application.

[0024] Figure numerals: 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; 14-shock-absorbing and anti-rebound mechanism; 15-support; 16-support and quick separation mechanism; 131-erecting cylinder; 132-auxiliary supporting cylinder; 141-elastic supporting rod; 142-tilting pressure rod; 161-aluminum belt; 162-aluminum belt connecting mechanism; 163-aluminum belt recovery mechanism; 164-transition belt; 165-two-stage load-reducing support mechanism; 166-aluminum belt tensioning mechanism; 167-reverse limiting structure. DETAILED DESCRIPTION

[0025] 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 creative work are within the scope of protection of the present application.

[0026] like Figure 1-4 As shown, the present application provides a stabilizing device for launching a rocket at sea, comprising: 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 a launch platform 4, and the first anti-overturning device 1 and the second anti-overturning device 2 are respectively supported and connected on both sides of a rocket 3; the first anti-overturning device 1 and the second anti-overturning device 2 have the same structure; and 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 comprise: 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, and the bracket 15 is used to fix and hold the side of the rocket body of the rocket 3. The bottom of the anti-overturning arm 12 is rotatably connected to the anti-overturning device chassis 11 at one end close to the rocket 3, and the other end is supported against and supported on a support and quick separation mechanism 16, and the support and quick separation mechanism 16 is connected to the anti-overturning device chassis 11. The first anti-overturning device 1 and the second anti-overturning device 2 are arranged on both sides of the rocket body, respectively, and can withstand the horizontal overturning force of the rocket 3 under the fourth-level sea condition. In order to adapt to near-sea and far-sea launches, the first anti-overturning device 1 and the second anti-overturning device 2 can reliably support the rocket body to prevent overturning before the rocket 3 is launched, and can be quickly opened before the rocket body leaves the launch platform 4 when the rocket 3 is launched, so as not to hinder the flight of the rocket body.

[0027] like Figure 2 As shown, the bottom end of the anti-overturning arm 12 close to the rocket 3 is rotatably connected to the anti-overturning device chassis 11, and the other end is abutted against the support and quick separation mechanism 16, which is connected to the anti-overturning device chassis 11. When the rocket 3 is ignited, the support and quick separation mechanism 16 can be passively unlocked quickly, and the support and quick separation mechanism 16 does not support the bottom end of the anti-overturning arm 12 away from the rocket 3, so that the anti-overturning arm 12 is quickly opened under the action of gravity.

[0028] 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, the bottom end of the anti-overturning arm 12 close to the rocket 3 is rotatably connected to the vertical support frame through 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 supporting 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 supporting device at the end of the bottom of the anti-overturning arm 12 away from the rocket 3 is unlocked, and does not play a supporting role 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, and the anti-overturning arm 12 does not hold the rocket 3 tightly and fixedly connected, thereby releasing the rocket 3, and the rocket 3 can be launched smoothly.

[0029] As a specific embodiment of the present invention, the anti-overturning arm 12 adopts a truss structure as a whole, which has the advantages of high rigidity and good stability. A counterweight is installed at the end of the bottom of the anti-overturning arm 12 away from the arrow body, and the counterweight increases the gravity of the end of the bottom of the anti-overturning arm 12 away from the arrow body. When there is no support device at the end of the bottom of the anti-overturning arm 12 away from the arrow body, the counterweight can realize the rapid passive opening of the anti-overturning arm 12, which has the advantages of fast response speed, etc.

[0030] like Figure 2 As shown, the first anti-overturning device 1 and the second anti-overturning device 2 also include an anti-overturning arm auxiliary closing mechanism 13 and a shock-absorbing anti-rebound mechanism 14; the anti-overturning arm auxiliary closing mechanism 13 and the shock-absorbing anti-rebound mechanism 14 are both connected to the anti-overturning device chassis 11; the anti-overturning arm auxiliary closing mechanism 13 is supported and connected to the bottom of the anti-overturning arm 12; the anti-overturning arm auxiliary closing mechanism 13 is used to make the anti-overturning arm 12 stand up from a tilted state to a vertical state; after the support and quick separation mechanism supports the anti-overturning arm 12; the anti-overturning arm auxiliary closing mechanism 13 is unlocked and retracted from the anti-overturning arm 12, releasing the anti-overturning arm 12; the shock-absorbing anti-rebound mechanism 14 is used to play a buffering role when the anti-overturning arm 12 is opened into place, and to prevent the anti-overturning arm 12 from rebounding. After the support of the anti-rollover arm 12 is switched from the anti-rollover arm auxiliary closing mechanism 13 to the support and quick separation mechanism 16, the anti-rollover arm auxiliary closing mechanism 13 is unlocked from the anti-rollover arm 12, and the anti-rollover arm auxiliary closing mechanism 13 falls back.

[0031] like Figure 4As shown, the anti-rollover arm auxiliary closing mechanism 13 includes an erecting cylinder 131 and an auxiliary supporting cylinder 132, a latch and a latch cylinder; the latch and the latch cylinder are installed at the bottom of the anti-rollover arm 12, and the latch is used to insert into the connecting hole between the top of the erecting cylinder 131 and the bottom of the anti-rollover arm 12, so as to realize the connection between the erecting cylinder 131 and the anti-rollover arm 12. When the latch is pulled out from the connecting hole between the top of the erecting cylinder 131 and the bottom of the anti-rollover arm 12, the erecting cylinder 131 and the anti-rollover arm 12 are unlocked (not connected), and the latch cylinder is connected to the latch, and the latch cylinder is used to drive the latch to move along its axial direction, so as to realize the connection between the erecting cylinder 131 and the anti-rollover arm 12. The latch is inserted into (or pulled out of) the connecting hole between the top of the erecting cylinder 131 and the bottom of the anti-rollover arm 12; one end (bottom end) of the erecting cylinder 131 is connected to the anti-rollover device chassis 11; the other end (top end) of the erecting cylinder 131 is connected to the bottom of the anti-rollover arm 12 through a latch, and the latch is driven by the latch cylinder to achieve the connection and unlocking of the anti-rollover arm auxiliary closing mechanism 13 and the anti-rollover arm 12; the auxiliary supporting cylinder 132 is connected to the side of the erecting cylinder 131 with an inclined support, and one end of the auxiliary supporting cylinder 132 is connected to the anti-rollover device chassis 11, and the other end is connected to the erecting cylinder 131. When the erecting cylinder 131 extends and supports the anti-rollover arm 12 to close, the auxiliary supporting cylinder 132 is in a follow-up extendable state; after the erecting cylinder 131 supports the anti-rollover arm 12 to close in place, the latch cylinder drives the latch to retract, the erecting cylinder 131 and the anti-rollover arm 12 are unlocked, and the auxiliary supporting cylinder 132 retracts, driving the erecting cylinder 131 to fall back.

[0032] like Figure 4 As shown, the shock-absorbing and anti-rebound mechanism 14 includes: an inclined pressure rod 142 and an elastic support rod 141; the end of the inclined pressure rod 142 is rotatably connected to the anti-overturning device base frame 11, and the elastic support rod 141 is obliquely supported and connected to the side of the inclined pressure rod 142; when the anti-overturning arm 12 tilts to a certain angle, the side of the anti-overturning arm 12 fits with the inclined pressure rod 142, and the elastic support rod 141 is compressed, which plays a buffering role for the anti-overturning arm 12; when the anti-overturning arm 12 falls back into place, the inclined pressure rod 142 limits the anti-overturning arm 12 due to the support force of the inclined pressure rod 142.

[0033] like Figure 2 As shown, the first anti-overturning device 1 and the second anti-overturning device 2 also include a supporting and quick-separating mechanism 16, which is connected to the anti-overturning device chassis 11; the supporting and quick-separating mechanism 16 is supported and connected to the bottom of the anti-overturning arm 12; the supporting and quick-separating mechanism 16 is used to support the anti-overturning arm 12 before the rocket 3 is launched, and when the rocket 3 is ignited, the supporting and quick-separating mechanism 16 is passively unlocked, and the anti-overturning arm 12 opens under the action of gravity.

[0034] like Figure 3As shown, the support and quick separation mechanism 16 includes a two-stage load-reducing support mechanism 165, a transition zone 164, an aluminum belt connecting mechanism 162, an aluminum belt recycling mechanism 163 and an aluminum belt 161; the aluminum belt 161 is horizontally arranged below the rocket 3, one side of the aluminum belt 161 is connected to the first anti-overturning device 1, and the other side is connected to the second anti-overturning device 2, and both ends of the aluminum belt 161 are connected to the anti-overturning device chassis 11 through the aluminum belt connecting mechanism 162, the aluminum belt recycling mechanism 163, the transition zone 164, and the two-stage load-reducing support mechanism 165; the aluminum belt 161 is connected to the anti-overturning device chassis 11 through the aluminum belt The recovery mechanism 163 is connected to the transition band 164 of the anti-overturning device on both sides of the arrow body; the aluminum strip connecting mechanism 162 is connected to the end of the aluminum strip 161, one end of the aluminum strip recovery mechanism 163 is connected to the aluminum strip connecting mechanism 162, and the other end is connected to the transition band 164, and the end of the transition band 164 away from the aluminum strip recovery mechanism 163 is connected to the two-stage load-reducing support mechanism 165; the two-stage load-reducing support mechanism 165 is connected to the anti-overturning device chassis 11, and is supported at the bottom of the anti-overturning arm 12, so that the force transmitted to the aluminum strip 161 by the anti-overturning arm 12 is reduced proportionally.

[0035] like Figure 3 As shown, the support and quick separation mechanism 16 also includes: an aluminum belt tensioning mechanism 166 and a reverse limiting structure 167; the aluminum belt tensioning mechanism 166 is connected to the side of the two-stage load-reducing support mechanism 165 and is connected to the transition belt 164. The aluminum belt tensioning mechanism 166 is used to tighten the transition belt 164 and the aluminum belt 161, so that the two-stage load-reducing support mechanism 165 presses against the anti-overturning arm 12, and the anti-overturning arm 12 firmly holds the arrow body. The aluminum belt tensioning mechanism 166 transmits the pulling force to the aluminum belt 161 by pulling the transition belt 164, so that the aluminum belt 161 tightens the two-stage load-reducing support mechanism 165 of the anti-overturning device on both sides, and the two-stage load-reducing support mechanism 165 reliably supports the anti-overturning arm 12. The reverse limiting structure 167 is fixedly connected to the anti-overturning device chassis 11. The reverse limiting structure 167 is arranged beside the two-stage load reduction support mechanism 165 and is located on the side of the two-stage load reduction support mechanism 165 close to the rocket 3. It plays a limiting role on the side of the two-stage load reduction support mechanism 165 close to the rocket 3, avoiding the two-stage load reduction support mechanism 165 from deflecting to the side close to the rocket 3, thereby avoiding the reverse transmission of force to the rocket body.

[0036] As a specific embodiment of the present invention, a tension sensor is connected between the aluminum belt tensioning mechanism 166 and the transition belt 164, and the tension sensor is used to detect whether the aluminum belt 161 is in a tensioned state to determine whether the anti-overturning arm 12 is closed in place to hold the arrow body.

[0037] As a specific embodiment of the present invention, the top surface of the two-stage load relief support mechanism 165 is in contact with the anti-rollover arm 12, and the end of the top surface of the two-stage load relief support mechanism 165 away from the rocket is rotatably connected to the anti-rollover device chassis 11. When the aluminum belt 161 no longer tensions the two-stage load relief support mechanism 165, the top surface of the two-stage load relief support mechanism 165 rotates around the rotation axis connected to the anti-rollover device chassis 11, so that the top surface of the two-stage load relief support mechanism 165 is no longer supported on the bottom of the anti-rollover arm 12, the anti-rollover arm 12 is released, and the anti-rollover arm 12 falls over.

[0038] As a specific embodiment of the present invention, when the rocket 3 is ignited, the impact force of the tail flame of the rocket 3 breaks the aluminum strip 161, the two-stage load-reducing support mechanism 165 is unlocked, and the end surface of the two-stage load-reducing support mechanism 165 in contact with the anti-overturning arm 12 falls over, and the two-stage load-reducing support mechanism 165 is separated from the anti-overturning arm 12 and is no longer supported at the bottom of the anti-overturning arm 12, and the anti-overturning arm 12 is released. The anti-overturning arm 12 opens quickly under the action of gravity, and the anti-overturning arm 12 falls over. When the anti-overturning arm 12 opens to a certain angle, it contacts the inclined pressure rod 142 of the shock-absorbing and anti-rebound mechanism 14, and the anti-overturning arm 12 continues to fall under its own weight, and the elastic support rod 141 of the shock-absorbing and anti-rebound mechanism 14 is compressed. In this process, the anti-overturning arm 12 slides downward on the contact surface with the inclined pressure rod 142, the elastic support rod 141 is compressed, and the anti-overturning arm 12 is decelerated. When the elastic support rod 141 is compressed to the limit position, the anti-overturning arm 12 is limited by the inclined pressure rod 142 and cannot continue to rotate.

[0039] As a specific embodiment of the present invention, 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 closing the anti-overturning arm auxiliary closing mechanism 13, the anti-overturning arm 12 is in a tilted state. The erecting cylinder 131 has an ear plate hole, and the anti-overturning arm 12 has an ear plate hole. The ear plate hole of the erecting cylinder 131 is coaxially connected with the ear plate hole of the anti-overturning arm 12. The erecting cylinder 131 is connected to the anti-overturning arm 12 through a pin shaft. After the erecting cylinder 131 is extended until the anti-overturning arm 12 fits with the arrow body, the support and quick opening mechanism closes and supports the anti-overturning arm 12; then the pin shaft connecting the erecting cylinder 131 and the anti-overturning arm 12 is retracted, the erecting cylinder 131 and the anti-overturning arm 12 are unlocked, and the erecting cylinder 131 falls backward under the drive of the auxiliary support cylinder.

[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 supporting cylinder 132;

[0043] The ear plate hole of the erecting oil cylinder 131 is coaxially connected with the ear plate hole of the anti-overturning arm through a latch;

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

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

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

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

[0048] The pins in the ear plate holes of the erecting oil cylinder 131 and the ear plate holes of the anti-overturning arm are pulled out to unlock;

[0049] The erection 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 first anti-overturning device and the second anti-overturning device of the present application can reliably support the rocket body to prevent overturning before the rocket is launched. When the rocket is launched, the rocket body can be quickly opened before leaving the launch pad without hindering the flight of the rocket body.

[0053] (2) The shock-absorbing and anti-rebound mechanism of the present application can play a buffering role when the anti-rollover arm is fully opened, reduce the vibration impact generated when the anti-rollover arm is opened, and prevent the anti-rollover arm from rebounding.

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

[0055] In the description of the present application, the word "for example" is used to mean "used as an example, illustration or explanation". Any embodiment described as "for example" in the present application is not necessarily to be construed as being more preferred or advantageous than other embodiments. The following description is given to enable any technician in the field 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 the present application.

[0056] The above description is only an embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent substitution, improvement, etc. made within the spirit and principle of the present invention should be included in the scope of the claims of the present invention.

Claims

1. A rocket stabilizing device for launching at sea, characterized in that: include: a first anti-overturning device and a second anti-overturning device, wherein 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 supported and connected to two sides of the rocket respectively; The first anti-overturning device and the second anti-overturning device have the same structure; the rocket is vertically arranged on the launch pad; The first anti-overturning device and the second anti-overturning device both 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 bottom frame of the anti-overturning device, and the bracket is fixedly connected to the top end of the anti-overturning arm. The bracket is used to fix and hold the side of the rocket body.

2. The device for stabilizing a rocket launched at sea according to claim 1, characterized in that: The bottom of the anti-rollover arm is rotatably connected to the anti-rollover device chassis at one end close to the rocket, and the other end is supported on a support and quick-detachment mechanism connected to the anti-rollover device chassis.

3. The device for stabilizing a rocket launched at sea according to claim 2, characterized in that: The first anti-overturning device and the second anti-overturning device further include an anti-overturning arm auxiliary closing mechanism and a shock-absorbing and anti-rebound mechanism; The anti-overturning arm auxiliary closing mechanism and the shock-absorbing and anti-rebound mechanism are both connected to the anti-overturning device chassis; The anti-overturning arm auxiliary closing mechanism is supported and connected to the bottom of the anti-overturning arm; the anti-overturning arm auxiliary closing mechanism is used to make the anti-overturning arm stand up from a tilted state to a vertical state, and after the support and quick separation mechanism supports the anti-overturning arm, the anti-overturning arm auxiliary closing mechanism is unlocked and retracted from the anti-overturning arm, releasing the anti-overturning arm; The shock-absorbing and anti-rebound mechanism is used to play a buffering role when the anti-overturning arm is opened to the full position, and prevent the anti-overturning arm from rebounding.

4. The device for stabilizing a rocket launched at sea according to claim 3, characterized in that: The anti-overturning arm auxiliary closing mechanism includes an erecting cylinder, a latch cylinder and an auxiliary supporting cylinder; One end of the erecting oil cylinder is connected to the bottom frame of the anti-overturning device, and the other end is connected to the bottom of the anti-overturning arm through a latch pushed by the latch oil cylinder; The auxiliary supporting oil cylinder is connected to the side of the erecting oil cylinder by tilting support, one end of the auxiliary supporting oil cylinder is connected to the bottom frame of the anti-overturning device, and the other end is connected to the erecting oil cylinder.

5. The device for stabilizing a rocket launched at sea according to claim 3, characterized in that: The shock-absorbing and anti-rebound mechanism comprises: an inclined pressure rod and an elastic support rod; The end of the inclined pressure rod is rotatably connected to the bottom frame of the anti-overturning device, and the elastic support rod is obliquely supported and connected to the side of the inclined pressure rod; When the anti-overturning arm tilts to a certain angle, the side surface of the anti-overturning arm fits with the inclined pressure rod, and the elastic support rod is compressed, which plays a buffering role for the anti-overturning arm; When the anti-rollover arm falls back into place, the anti-rollover arm is limited by the supporting force of the inclined pressure rod.

6. The device for stabilizing a rocket launched at sea according to claim 3, characterized in that: The support and quick release mechanism is connected to the anti-overturning device chassis; The support and quick-detachment mechanism is supported and connected to the bottom of the anti-overturning arm at one end away from the rocket; The support and quick separation mechanism is used to support the anti-overturning arm before the rocket is launched. When the rocket is ignited, the support and quick separation mechanism is passively unlocked, and the anti-overturning arm is opened under the action of gravity.

7. The device for stabilizing a rocket launched at sea according to claim 6, characterized in that: The support and quick separation mechanism includes a two-stage load-reducing support mechanism, a transition belt, an aluminum belt connecting mechanism, an aluminum belt recycling mechanism and an aluminum belt; The two ends of the aluminum strip are connected to the bottom frame of the anti-overturning device through the aluminum strip connecting mechanism, the aluminum strip recycling mechanism, the transition strip, and the two-stage load reduction support mechanism; The aluminum strip connection mechanism is connected to the end of the aluminum strip, one end of the aluminum strip recovery mechanism is connected to the aluminum strip connection mechanism, and the other end is connected to the transition strip, and the end of the transition strip away from the aluminum strip recovery mechanism is connected to the two-stage load reduction support mechanism; The two-stage load-reducing support mechanism is connected to the anti-overturning device chassis and supported at the bottom of the anti-overturning arm, so that the force transmitted from the anti-overturning arm to the aluminum strip is reduced proportionally.

8. The device for stabilizing a rocket launched at sea according to claim 7, characterized in that: The support and quick separation mechanism also includes: an aluminum belt tensioning mechanism; The aluminum belt tensioning mechanism is connected to the side of the two-stage load-reducing support mechanism and is connected to the transition belt. The aluminum belt tensioning mechanism is used to tighten the transition belt and the aluminum belt so that the two-stage load-reducing support mechanism presses against the anti-overturning arm, and the anti-overturning arm firmly holds the arrow body.

9. The device for stabilizing a rocket launched at sea according to claim 8, characterized in that: A tension sensor is connected between the aluminum belt tensioning mechanism and the transition belt, and the tension sensor is used to detect whether the aluminum belt is in a tensioned state, so as to determine whether the anti-overturning arm is closed in place to hold the arrow body.

10. The device for stabilizing a rocket launched at sea according to claim 9, characterized in that: When the rocket is ignited, the impact force of the rocket tail flame breaks the aluminum strip, the two-stage load-reducing support mechanism is unlocked, the anti-overturning arm is released, and the anti-overturning arm overturns.

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