Supporting and rapid separating mechanism of rocket stabilizing device

Abstract

The utility model provides a supporting and quick separating mechanism of a rocket stabilizing device, the supporting and quick separating mechanism is connected to the bottom of the rocket stabilizing device, and the supporting and quick separating mechanism is connected to an anti-overturning device chassis of the rocket stabilizing device and is supported at the bottom of an anti-overturning arm of the rocket stabilizing device; after the rocket is ignited, the supporting and quick separating mechanism is unlocked, and the anti-overturning arm is released; before the rocket is not ignited, the supporting and rapid separating mechanism is connected to the bottom of the anti-overturning arm in a supporting mode. The supporting and rapid separating mechanism comprises a two-stage deloading supporting mechanism and an aluminum strip; the two-stage load shedding supporting mechanism is connected to the anti-overturning device underframe and is connected to the bottom of the anti-overturning arm in a supporting manner; the aluminum strip is arranged at the bottom of the rocket, and the two ends of the aluminum strip are connected with the two-stage load shedding supporting mechanisms correspondingly. According to the supporting and rapid separating mechanism, stable supporting and unlocking releasing of the anti-overturning arm of the rocket stabilizing device are achieved, so that the anti-overturning arm is rapidly opened, and rocket launching is not hindered.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of rocket launching, in particular to a support and quick separation mechanism of a rocket stabilizing device. BACKGROUND

[0002] At present, offshore rocket launching has become an important way, which has higher plan flexibility and safer geographical applicability compared with land launching, and a relatively mature and stable launching platform is built on the sea. However, the offshore launching conditions are affected by the sea conditions and climate. Due to the uncertainty of the sea waves, the roll and pitch of the ship body are transmitted to the launching platform, thereby affecting the stability of the rocket before and after the rocket is erected. After the rocket is erected, the stability of the rocket standing on the launching platform is poor. Due to the large overturning moment of the rocket body caused by the ship sway, the rocket structure is prone to failure, and even the rocket is overturned. The rocket over large inclination not only affects the launch control accuracy, but also may cause the rocket to fall down, resulting in launch failure or even launch accident. How to keep the rocket stable and safe during the standing period before the rocket ignition is crucial.

[0003] The existing patent with the patent number CN117950302A provides a rocket offshore hot launching platform support control system, which can provide effective protection for the rocket offshore hot launching platform and improve the ability of offshore hot launching task, and has high reliability. However, it provides support control for the rocket offshore hot launching platform, cannot provide support and stabilizing effect for the rocket, and cannot prevent the rocket from falling down.

[0004] For the rocket stabilizing device, the existing technology does not provide a support and quick separation mechanism of an anti-overturning arm of the rocket stabilizing device and the anti-overturning arm.

[0005] Therefore, the technical problem to be solved at present is how to provide a support and quick separation mechanism of a rocket stabilizing device, which realizes stable support and unlocking release of the anti-overturning arm of the rocket stabilizing device, so that the anti-overturning arm is quickly opened and does not hinder the rocket launching. CONTENT OF THE INVENTION

[0006] The present application aims to provide a support and quick separation mechanism of a rocket stabilizing device, which realizes stable support and unlocking release of the anti-overturning arm of the rocket stabilizing device, so that the anti-overturning arm is quickly opened and does not hinder the rocket launching.

[0007] To achieve the above object, the application provides a support and quick separation mechanism of a rocket stabilizing device, which is connected to the bottom of the rocket stabilizing device, and the rocket stabilizing device comprises 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 for fixedly embracing the side of the rocket body; the support and quick separation mechanism is connected to the anti-overturning device chassis and supported at the bottom of the anti-overturning arm; when the rocket is ignited, the support and quick separation mechanism is unlocked to release the anti-overturning arm; before the rocket is ignited, the support and quick separation mechanism is supported at the bottom of the anti-overturning arm; the support and quick separation mechanism comprises two-stage load reduction support mechanisms and an aluminum belt, the two-stage load reduction support mechanisms are connected to the anti-overturning device chassis and supported at the bottom of the anti-overturning arm, and the aluminum belt is arranged at the bottom of the rocket, and the two ends of the aluminum belt are respectively connected to a group of the two-stage load reduction support mechanisms.

[0008] The support and quick separation mechanism of the rocket stabilizing device as described above, wherein the support and quick separation mechanism further comprises a transition belt, an aluminum belt connecting mechanism and an aluminum belt recovery mechanism; the two ends of the aluminum belt are connected to the anti-overturning device chassis through the aluminum belt connecting mechanism, the aluminum belt recovery mechanism, the transition belt and the two-stage load reduction support mechanisms; the aluminum belt connecting mechanism is connected to the end of the aluminum belt and connected to the aluminum belt recovery mechanism; one end of the aluminum belt recovery mechanism is connected to the aluminum belt connecting mechanism, and the other end is connected to the transition belt, and the end of the transition belt away from the aluminum belt recovery mechanism is connected to the two-stage load reduction support mechanisms.

[0009] The support and quick separation mechanism of the rocket stabilizing device as described above, wherein the support and quick separation mechanism further comprises an aluminum belt tensioning mechanism; the aluminum belt tensioning mechanism is connected to the side of the two-stage load reduction support mechanisms and connected to the transition belt, and the aluminum belt tensioning mechanism is used for tensioning the transition belt and the aluminum belt.

[0010] The support and quick separation mechanism of the rocket stabilizing device as described above, wherein a tension sensor is connected between the aluminum belt tensioning mechanism and the transition belt, and the tension sensor is used for detecting whether the aluminum belt is in a tensioning-in-place state.

[0011] The support and quick separation mechanism of the rocket stabilizing device as described above, wherein when the rocket is ignited, the impact force of the rocket exhaust will break the aluminum belt, the two-stage load reduction support mechanisms are unlocked to release the anti-overturning arm, and the anti-overturning arm is tilted.

[0012] The support and quick separation mechanism of the rocket stabilizing device as described above, wherein the aluminum band connecting mechanism comprises an upper aluminum band pressing plate, a lower aluminum band pressing plate, a connecting rod, a locking cap and a threaded rod; the upper aluminum band pressing plate and the lower aluminum band pressing plate are fixedly connected to upper and lower surfaces of the end of the aluminum band respectively; the end of the upper aluminum band pressing plate and the end of the lower aluminum band pressing plate are connected to the connecting rod; the locking cap is sleeved on the connecting rod; the locking cap is threadedly connected with the threaded rod; and the threaded rod is fixedly connected with the aluminum band recovery mechanism.

[0013] The support and quick separation mechanism of the rocket stabilizing device as described above, wherein the aluminum band connecting mechanism further comprises a connecting shaft, and the end of the aluminum band is sleeved on the connecting shaft; the ends of the upper aluminum band pressing plate and the lower aluminum band pressing plate are connected to both ends of the connecting shaft; and the connecting rod is connected to the end of the connecting shaft.

[0014] The support and quick separation mechanism of the rocket stabilizing device as described above, wherein the connecting rod comprises two, and the two connecting rods are connected to both ends of the connecting shaft respectively.

[0015] The support and quick separation mechanism of the rocket stabilizing device as described above, wherein the connecting rod is provided with a limiting protrusion away from the end of the aluminum band, and the limiting protrusion limits the locking cap on the connecting rod.

[0016] The support and quick separation mechanism of the rocket stabilizing device as described above, wherein one end of the bottom of the anti-overturning arm close to the rocket is rotationally connected to the anti-overturning device chassis, and the other end abuts against the support and quick separation mechanism.

[0017] The application achieves the following beneficial effects:

[0018] (1) The support and quick separation mechanism can reliably support the anti-overturning arm of the rocket stabilizing device before the rocket is launched, thereby improving the stability of the rocket stabilizing device.

[0019] (2) The support and quick separation mechanism can release the anti-overturning arm before the rocket body is separated from the launch pad during the launch of the rocket, so that the anti-overturning arm is quickly opened and does not hinder the launch or flight of the rocket body. BRIEF DESCRIPTION OF DRAWINGS

[0020] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments or prior art description. Obviously, the drawings in the following description are only some embodiments described in the present application, and other drawings can also be obtained by those skilled in the art according to these drawings.

[0021] Figure 1Figure 1 is a structural schematic diagram of a rocket stabilizing device support and quick release mechanism according to an embodiment of the present application.

[0022] Figure 2 Figure 2 is a structural schematic diagram of a rocket stabilizing device support and quick release mechanism according to an embodiment of the present application. Figure 1 .

[0023] Figure 3 Figure 3 is a structural schematic diagram of a rocket stabilizing device support and quick release mechanism according to an embodiment of the present application. Figure 2 .

[0024] Figure 4 Figure 4 is a structural schematic diagram of an aluminum band connecting mechanism according to an embodiment of the present application. Figure 1 .

[0025] Figure 5 Figure 5 is a structural schematic diagram of an aluminum band connecting mechanism according to an embodiment of the present application. Figure 2 .

[0026] Figure 1 is a structural schematic diagram of a rocket stabilizing device support and quick release mechanism according to an embodiment of the present application. DETAILED DESCRIPTION

[0027] The technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the accompanying drawings. Obviously, the described embodiments are only some of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work fall within the scope of the present application.

[0028] As Figures 1-5As shown, the application provides a support and quick release mechanism of a rocket stabilizing device. The rocket stabilizing device stabilizes the rocket body after the rocket is erected and parked on the launch platform, preventing the rocket 3 from toppling over and improving the stability and safety of the rocket 3. The support and quick release mechanism is connected to the bottom of the rocket stabilizing device. The rocket stabilizing device includes: an anti-overturning device chassis 11, an anti-overturning arm 12, and a bracket 15. The bottom end of the anti-overturning arm is installed 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 tightly connect to the side of the rocket body of the rocket 3.

[0029] As shown in Figure 1 The rocket stabilizing device includes: a first anti-overturning device 1 and a second anti-overturning device 2, which are fixedly connected to the launch platform 4 and are respectively supported and connected to the two sides of the rocket 3. The first anti-overturning device 1 and the second anti-overturning device 2 are the same in 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 each 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 installed 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 tightly connect to 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 near one end of the rocket 3, and the other end is abuttingly connected to the support and quick release mechanism 16, which is connected to the anti-overturning device chassis 11. The first anti-overturning device 1 and the second anti-overturning device 2 are respectively arranged on the two sides of the rocket body and can withstand the horizontal overturning force of the rocket 3 under four-stage sea conditions. 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 before the launch of the rocket 3 to prevent overturning. The support and quick release mechanism 16 is used to release the anti-overturning arm 12, so that the anti-overturning arm 12 can be quickly opened before the rocket body is separated from the launch platform 4 during the launch of the rocket 3, without hindering the launch or flight of the rocket body.

[0030] As shown in Figure 2 The bottom of the anti-overturning arm 12 is rotatably connected to the anti-overturning device chassis 11 near one end of the rocket 3, and the other end is abuttingly connected to the support and quick release mechanism 16, which is connected to the anti-overturning device chassis 11. When the rocket 3 is ignited, the support and quick release mechanism 16 can be passively and quickly unlocked. The support and quick release mechanism 16 does not support the end of the bottom 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.

[0031] As the specific embodiment of the utility model, the anti-overturning device chassis 11 includes a horizontal chassis and a vertical support frame, the vertical support frame is fixedly connected perpendicularly on the horizontal chassis, the bottom of the anti-overturning arm 12 is rotatably connected with the vertical support frame through a rotary shaft, when the anti-overturning arm 12 needs to be supported on both sides of the rocket 3, the end of the bottom of the anti-overturning arm 12 away from the rocket 3 is supported by the support and quick separation mechanism 16, the anti-overturning arm 12 cannot rotate around the rotary shaft rotatably connected with the vertical support frame. When the rocket 3 needs to be launched, the support and quick separation mechanism 16 at the end of the bottom of the anti-overturning arm 12 away from the rocket 3 is unlocked, does not support 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 rotary shaft rotatably connected with the vertical support frame, the anti-overturning arm 12 does not tightly fix the rocket 3, thereby releasing the rocket 3, and the rocket 3 can be launched smoothly.

[0032] As shown in Figure 2 , the support and quick separation mechanism 16 is connected on the anti-overturning device chassis 11; the support and quick separation mechanism 16 is supported and connected on the bottom of the anti-overturning arm 12; the support and quick separation mechanism 16 is used for supporting the anti-overturning arm 12 before the rocket 3 is launched, when the rocket 3 is ignited, the support and quick separation mechanism 16 is unlocked passively, and the anti-overturning arm 12 is opened under the action of gravity.

[0033] As shown in Figure 2 and 3 , the support and quick separation mechanism 16 includes two-stage load reduction support mechanism 165, transition belt 164, aluminum belt connecting mechanism 162, aluminum belt recovery mechanism 163 and aluminum belt 161; the aluminum belt 161 is horizontally arranged below the rocket 3, the aluminum belt 161 is arranged at the bottom of the rocket 3, and the two ends of the aluminum belt 161 are respectively connected with a group of two-stage load reduction support mechanism 165. One side of the aluminum belt 161 is connected with the first anti-overturning device 1, and the other side is connected with the second anti-overturning device 2, the two ends of the aluminum belt 161 are connected on the anti-overturning device chassis 11 through the aluminum belt connecting mechanism 162, the aluminum belt recovery mechanism 163, the transition belt 164 and the two-stage load reduction support mechanism 165; the aluminum belt 161 is connected to the transition belt 164 of the anti-overturning device on both sides of the rocket body through the aluminum belt recovery mechanism 163; the aluminum belt connecting mechanism 162 is connected at the end of the aluminum belt 161, one end of the aluminum belt recovery mechanism 163 is connected with the aluminum belt connecting mechanism 162, and the other end is connected with the transition belt 164, the end of the transition belt 164 away from the aluminum belt recovery mechanism 163 is connected with the two-stage load reduction support mechanism 165; the two-stage load reduction support mechanism 165 is connected on the anti-overturning device chassis 11 and supported and connected on the bottom of the anti-overturning arm 12.

[0034] As shown in Figure 3As shown, the support and quick release mechanism 16 further comprises: 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 reduction support mechanism 165 and connected with the transition belt 164, and the aluminum belt tensioning mechanism 166 is used for tensioning the transition belt 164 and the aluminum belt 161. The aluminum belt tensioning mechanism 166 transmits the tension to the aluminum belt 161 by pulling the transition belt 164, so that the aluminum belt 161 tensions the two-stage load reduction support mechanism 165 of the two-side anti-overturning device, and the two-stage load reduction 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 on the side of 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, and limits the side of the two-stage load reduction support mechanism 165 close to the rocket 3, avoiding the deflection of the two-stage load reduction support mechanism 165 to the side close to the rocket 3.

[0035] As shown in the drawings, Figure 3 The tension sensor 168 is connected between the aluminum belt tensioning mechanism 166 and the transition belt 164, and the tension sensor 168 is used for detecting whether the aluminum belt 161 is in a tensioning-in-place state. The tension sensor 168 adopts an existing tension sensor, for example, the model of the tension sensor 168 is EL20-S458, chlbs-2, FSSM, CPR607-1, SL721, etc.

[0036] As a specific embodiment of the utility model, the top surface of the two-stage load reduction support mechanism 165 is in contact with the anti-overturning arm 12, one end of the top surface of the two-stage load reduction support mechanism 165 away from the rocket is rotationally connected with the anti-overturning device chassis 11, when the aluminum belt 161 no longer tensions the two-stage load reduction support mechanism 165, the top surface of the two-stage load reduction support mechanism 165 rotates around the rotation shaft connected with the anti-overturning device chassis 11, so that the top surface of the two-stage load reduction support mechanism 165 is no longer supported at the bottom of the anti-overturning arm 12, the anti-overturning arm 12 is released, and the anti-overturning arm 12 is tilted.

[0037] As shown in the drawings, Figure 3 The two-stage load reduction support mechanism 165 comprises a first-stage load reduction mechanism 1651 and a second-stage load reduction mechanism 1652, the anti-overturning device chassis 11 is provided with a support frame at the bottom of the anti-overturning arm, and the first-stage load reduction mechanism 1651 is rotationally connected to the support frame.

[0038] As shown in the drawings, Figure 3As shown, the short arm of the first load reduction mechanism 1651 is in contact with the lower bottom surface of the anti-overturning arm 12 for supporting the anti-overturning arm 12; the second load reduction mechanism 1652 is limitingly connected to the side of the long arm of the first load reduction mechanism 1651 for limiting the long arm of the first load reduction mechanism 1651, the bottom end of the second load reduction mechanism 1652 is rotationally connected to the support frame, and the top end is connected to the transition belt 164; before the aluminum belt 161 is disconnected, the transition belt 164 tightens the second load reduction mechanism 1652; the second load reduction mechanism 1652 is limitingly connected to the side of the long arm of the first load reduction mechanism 1651, and the first load reduction mechanism 1651 is supported at the bottom of the anti-overturning arm 12; when the rocket 3 is ignited, the rocket 3 tail flame breaks the aluminum belt 161, and the transition belt 164 no longer tightens the second load reduction mechanism 1652; the second load reduction mechanism 1652 rotates away from the long arm of the first load reduction mechanism 1651 around the rotation shaft at the bottom; the first load reduction mechanism 1651 no longer receives the limitation of the second load reduction mechanism 1652, and rotates around the rotation connection with the support frame; the short arm of the first load reduction mechanism 1651 swings downward; and the first load reduction mechanism 1651 no longer supports at the bottom of the anti-overturning arm 12, thereby releasing the anti-overturning arm 12.

[0039] As a specific embodiment of the utility model, the long arm of the first load reduction mechanism 1651 is in contact with the short arm of the second load reduction mechanism 1652; and the long arm of the second load reduction mechanism 1652 is hingedly connected to the transition belt 164.

[0040] As shown in the drawings, Figure 3 The long arm of the second load reduction mechanism 1652 is provided with an aluminum belt tensioning mechanism 166; the aluminum belt tensioning mechanism 166 transmits the tension to the transition belt 164 through the tensioning of the transition belt 164, so that the aluminum belt 161 tightens the second load reduction mechanism 1652 of the anti-overturning device on both sides, the second load reduction mechanism 1652 reliably supports the anti-overturning arm 12, and the aluminum belt tensioning mechanism 166 is tensioned between the transition belt 164.

[0041] As shown in the drawings, Figure 4 And 5 The aluminum belt connecting mechanism 162 comprises an aluminum belt upper pressing plate 51, an aluminum belt lower pressing plate 52, a connecting rod 53, a locking cap 54, a connecting shaft 55, and a threaded rod 56; the aluminum belt upper pressing plate 51 and the aluminum belt lower pressing plate 52 are fixedly connected to the upper and lower surfaces of the end portions of the aluminum belt 161 respectively; the aluminum belt upper pressing plate 51 and the aluminum belt lower pressing plate 52 are used for tightly fixing the aluminum belt; the two ends of the aluminum belt upper pressing plate 51 and the aluminum belt lower pressing plate 52 are connected with the connecting rod 53; the locking cap 54 is sleeved on the connecting rod 53, the end portion of the connecting rod 53 away from the aluminum belt is provided with a limiting protrusion 57, the limiting protrusion 57 limits the locking cap 54 on the connecting rod 53, prevents the locking cap 54 from being separated from the connecting rod 53, the locking cap 54 can rotate around the connecting rod 53 and move in the axial direction and will not be separated from the connecting rod 53, and the locking cap 54 is screwedly connected with the threaded rod 56.

[0042] As an embodiment of the present application, the inside of the locking cap 54 is provided with an internal thread, and the outer periphery of the threaded rod 56 is provided with an external thread, and the locking cap 54 is threadedly connected with the external thread of the threaded rod 56 through the internal thread.

[0043] As an embodiment of the present application, the threaded rod 56 is fixedly connected at one end of the aluminum strip recycling mechanism 163 away from the transition belt 164.

[0044] Preferably, the end of the aluminum strip is wound on the connecting shaft 55 to form a folded double-layer structure, and the upper aluminum strip pressing plate 51 and the lower aluminum strip pressing plate 52 are fixedly connected to the upper and lower surfaces of the double-layer structure of the aluminum strip. The two sides of the end of the connecting rod 53 connected with the upper aluminum strip pressing plate 51 and the lower aluminum strip pressing plate 52 are respectively connected to the two ends of the connecting shaft 55.

[0045] As an embodiment of the present application, the connecting rod 53 includes two, and the two connecting rods 53 are respectively connected to the two ends of the connecting shaft 55. A locking cap 54 is sleeved on each connecting rod 53, and each locking cap 54 is connected with a threaded rod 56, and the threaded rod 56 is fixedly connected with the aluminum strip recycling mechanism 163.

[0046] Preferably, the connecting rod 53, the locking cap 54 and the threaded rod 56 arranged on one side of the connecting shaft 55 are coaxial.

[0047] As an embodiment of the present application, when the rocket 3 is ignited, the impact force of the rocket 3 tail flame will break the aluminum strip 161, the two-stage load reduction supporting mechanism 165 is unlocked, the end surface of the two-stage load reduction supporting mechanism 165 in contact with the anti-overturning arm 12 is tilted, the two-stage load reduction supporting mechanism 165 is separated from the anti-overturning arm 12, and no longer supports the bottom of the anti-overturning arm 12, releases the anti-overturning arm 12, and the anti-overturning arm 12 is quickly opened under the action of gravity, and the anti-overturning arm 12 is tilted.

[0048] The application has the following beneficial effects:

[0049] (1) The supporting and quick separating mechanism can reliably support the anti-overturning arm of the rocket stabilizing device before the rocket is launched, and improve the stability of the rocket stabilizing device.

[0050] (2) The supporting and quick separating mechanism can release the anti-overturning arm before the rocket body separates from the launch pad during the launch of the rocket, so that the anti-overturning arm is quickly opened and does not hinder the launch or flight of the rocket body.

[0051] In the description of the application, the terms "first", "second", "third", etc. are used only for descriptive purposes and are not to be construed as indicating or implying relative importance or an indicated number of technical features. Thus, features defined with "first", "second" or "third" can explicitly or implicitly include one or more of the features. In the description of the application, the meaning of "a plurality of" is two or more, unless otherwise expressly and specifically limited.

[0052] In the description of the application, the word "for example" is used to mean "serving as an example, instance, or illustration." Any embodiment described as "for example" in this application is not necessarily to be construed as preferred or advantageous over other embodiments. The following description is presented to enable any person skilled in the art to make and use the application. In the following description, for the purposes of explanation, numerous specific details are set forth in order to provide a thorough understanding of the present application. It will be apparent, however, to one skilled in the art that the present application can be practiced without using these specific details. In other instances, well-known structures and processes are not elaborated upon in order to avoid unnecessary detail and so as to not obscure the present application. Thus, the present application is not intended to be limited by the embodiments shown, but is to be accorded the widest scope consistent with the principles and features disclosed herein.

[0053] The above only describes the embodiments of the present application and is not intended to limit the present application. The present application can have various changes and modifications for those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principles of the present application shall be included in the scope of the claims of the present application.

Claims

1. A support and quick release mechanism for a rocket stabilizing device, characterized by, The support and quick separation mechanism is connected to the bottom of the rocket stabilizing device, The rocket stabilizing device comprises 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, and the bracket is fixedly connected to the top end of the anti-overturning arm, and the bracket is used for fixedly holding and connecting to the side of the rocket body; The support and quick separation mechanism is connected to the anti-overturning device chassis and supported at the bottom of the anti-overturning arm; When the rocket is ignited, the support and quick separation mechanism is unlocked to release the anti-overturning arm; before the rocket is ignited, the support and quick separation mechanism is supported and connected to the bottom of the anti-overturning arm; The support and quick separation mechanism comprises two-stage load reduction support mechanisms and an aluminum belt; The two-stage load reduction support mechanisms are connected to the anti-overturning device chassis and supported at the bottom of the anti-overturning arm; The aluminum belt is arranged at the bottom of the rocket, and two ends of the aluminum belt are respectively connected to a group of the two-stage load reduction support mechanisms.

2. The support and quick release mechanism for a rocket harness according to claim 1, wherein, The support and quick separation mechanism further comprises a transition belt, an aluminum belt connecting mechanism and an aluminum belt recovery mechanism; Two ends of the aluminum belt are connected to the anti-overturning device chassis through the aluminum belt connecting mechanism, the aluminum belt recovery mechanism, the transition belt and the two-stage load reduction support mechanisms; The aluminum belt connecting mechanism is connected to the end of the aluminum belt and connected to the aluminum belt recovery mechanism; One end of the aluminum belt recovery mechanism is connected to the aluminum belt connecting mechanism, and the other end is connected to the transition belt, and one end of the transition belt away from the aluminum belt recovery mechanism is connected to the two-stage load reduction support mechanisms.

3. The support and quick release mechanism for a rocket harness according to claim 2, wherein, The support and quick separation mechanism further comprises an aluminum belt tensioning mechanism; The aluminum belt tensioning mechanism is connected to the side of the two-stage load reduction support mechanism and connected to the transition belt, and the aluminum belt tensioning mechanism is used for tensioning the transition belt and the aluminum belt.

4. The support and quick release mechanism for a rocket harness according to claim 3, wherein, A tension sensor is connected between the aluminum belt tensioning mechanism and the transition belt, and the tension sensor is used for detecting whether the aluminum belt is in a tensioning in-place state.

5. The support and quick release mechanism for a rocket harness according to claim 4, wherein, When the rocket is ignited, the impact force of the rocket exhaust will break the aluminum belt, the two-stage load reduction support mechanisms are unlocked to release the anti-overturning arm, and the anti-overturning arm is tilted.

6. The support and quick release mechanism for a rocket harness according to claim 2, wherein, The aluminum belt connecting mechanism comprises an aluminum belt upper pressing plate, an aluminum belt lower pressing plate, a connecting rod, a locking cap and a threaded rod; The aluminum belt upper pressing plate and the aluminum belt lower pressing plate are fixedly connected to the upper and lower surfaces of the end of the aluminum belt, respectively; The end of the aluminum belt upper pressing plate and the aluminum belt lower pressing plate is connected to the connecting rod; The locking cap is sleeved on the connecting rod; The locking cap is threadedly connected to the threaded rod; The threaded rod is fixedly connected to the aluminum belt recovery mechanism.

7. The support and quick release mechanism for a rocket harness according to claim 6, wherein, The aluminum belt connecting mechanism further comprises a connecting shaft, The end of the aluminum belt is arranged around the connecting shaft; The ends of the aluminum belt upper pressing plate and the aluminum belt lower pressing plate are connected to the two ends of the connecting shaft; The connecting rod is connected to the end of the connecting shaft.

8. The support and quick release mechanism for a rocket harness according to claim 7, wherein, The connecting rod comprises two, The two connecting rods are respectively connected to the two ends of the connecting shaft.

9. The support and quick release mechanism for a rocket harness according to claim 8, wherein, The end of the connecting rod away from the aluminum belt is provided with a limiting protrusion, and the limiting protrusion limits the locking cap on the connecting rod.

10. The support and quick release mechanism for a rocket harness according to claim 1, wherein, The bottom of the anti-overturning arm is rotatably connected to the anti-overturning device chassis near one end of the rocket, and the other end abuts against the support and quick separation mechanism.

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