Protection device and protection method suitable for core-level transportation of carrier rocket

Abstract

The invention relates to the field of core-level intelligent transportation of carrier rockets, and provides a protection device and method suitable for core-level transportation of carrier rockets, and a sectional type protection integrated device comprises a plurality of protection integrated units, an energy storage power generation unit, an air supply unit, a buffer unit, a vehicle body and two protection covers; the two protection covers are arranged at the front end and the rear end of the rocket core level correspondingly, the multiple protection integration units are arranged in the circumferential direction of the rocket core level and sequentially arranged in the axial direction of the rocket core level, and the multiple protection integration units are all arranged between the front protection cover and the rear protection cover. According to the protection integrated device, the vibration reduction function can be provided, meanwhile, vibration energy can be converted into electric energy to be stored, the protection integrated unit wrapping the carrier rocket core level can reduce the influence of flying stone impact in the transportation process and has the secondary repairing capacity, and a guarantee is provided for transportation of the carrier rocket core level.

Description

Technical Field

[0001] The present invention relates to the field of intelligent transportation of the core stage of a launch vehicle, and specifically, to a protection device and a protection method suitable for the transportation of the core stage of a launch vehicle. Background Art

[0002] In the existing field of transportation of the core stage of a launch vehicle, due to the limitation of the railway transportation boundary of the core stage of a large-diameter launch vehicle, it cannot be transported by rail in the way of loading it into a thermal insulation carriage according to the traditional diameter. Therefore, it is necessary to wrap the core stage of a large-diameter launch vehicle, and the existing wrapping methods all adopt the form of directly wrapping a rainproof cloth. The wrapping form is relatively simple, and it does not have the function of protecting against impacts such as flying stones during transportation. In this way, there are great safety hazards during the transportation of the core stage of a launch vehicle. Summary of the Invention

[0003] Aiming at the defects in the prior art, the purpose of the present invention is to provide a protection device and a protection method suitable for the transportation of the core stage of a launch vehicle.

[0004] A protection device suitable for the transportation of the core stage of a launch vehicle according to the present invention includes a plurality of protection integration units, an energy storage and power generation unit, a air supply unit, a buffer unit, a vehicle body, and two protective covers; The two protective covers are respectively arranged at the front and rear ends of the rocket core stage. The plurality of protection integration units are arranged along the circumferential direction of the rocket core stage and are arranged in sequence along the axial direction of the rocket core stage. The plurality of protection integration units are all arranged between the front and rear two protective covers; The air supply unit can supply air to the protection integration units and is electrically connected to the energy storage and power generation unit; The energy storage and power generation unit and the air supply unit are both arranged on the vehicle body. The protective cover is arranged on the vehicle body through the buffer unit. The buffer unit has a vibration damping function and can trigger the energy storage and power generation unit to generate electricity and complete energy storage through the buffer unit when the rocket core stage vibrates.

[0005] Preferably, the energy storage and power generation unit includes a first energy storage component, a second energy storage component, a power generation component, and a power distribution mechanism. The protective cover is arranged on the support bracket. The power generation component and the power distribution mechanism are both arranged inside the vehicle body. The power distribution mechanism is electrically connected to a plurality of power generation components respectively; The first energy storage component and the second energy storage component are both arranged outside the vehicle body. A part of the power generation components is electrically connected to the first energy storage component, and another part of the power generation components is electrically connected to the second energy storage component.

[0006] Preferably, the buffer unit includes two front and rear support brackets, two front and rear first main oil-gas spring cylinder brackets, two front and rear first main oil-gas spring cylinders, two front and rear second main oil-gas spring cylinder brackets, two front and rear second main oil-gas spring cylinders, an upper body bracket, and two front and rear drive shafts; The upper body bracket is arranged at the upper part of the vehicle body. The lower end of the drive shaft is arranged at the top of the power distribution mechanism. The upper end of the drive shaft passes through the upper body bracket and is connected to the bottom of the support bracket. The first main oil-gas spring cylinder is arranged between the upper body bracket and the support bracket through the first main oil-gas spring cylinder bracket and is located on one side of the drive shaft. The second main oil-gas spring cylinder is arranged between the upper body bracket and the support bracket through the second main oil-gas spring cylinder bracket and is located on the other side of the drive shaft; The first main oil-gas spring cylinder and the second main oil-gas spring cylinder are used to provide vibration damping for the rocket core stage.

[0007] Preferably, the protection integration unit includes two metal connection segments, a flexible support assembly, an airbag arranged between the two metal connection segments, an airbag pushing assembly, and a positioning assembly arranged inside the metal connection segment. The protection integration unit presses against the outside of the rocket core stage through the flexible support assembly. A first opening is provided on the side of the metal connection segment, and the first openings of the two metal connection segments are arranged opposite to each other. Second openings are provided on both sides of the airbag. Both the first opening and the second opening are hard openings. The airbag can be driven by the airbag pushing assembly to make the first opening and the second opening in a facing arrangement position. At this time, by controlling the air supply assembly, the positioning assembly can position the airbag.

[0008] Preferably, the flexible support assembly includes a plurality of flexible support pads and a plurality of auxiliary oil-gas spring cylinders. One end of the auxiliary oil-gas spring cylinder is connected to the metal connection segment, and the other end of the auxiliary oil-gas spring cylinder is connected to the flexible support pad. The flexible support pad presses against the outside of the rocket core stage.

[0009] Preferably, the airbag pushing assembly includes a first electric push rod bracket, a first electric push rod, a first slide rail, a second electric push rod, a second electric push rod bracket, and a second slide rail. The first slide rail is arranged on the side of one metal connection segment. The first electric push rod is arranged on one metal connection segment through the first electric push rod bracket; The second slide rail is arranged on the side of the other metal connection segment. The second electric push rod is arranged on the other metal connection segment through the second electric push rod bracket, and the first slide rail and the second slide rail are arranged opposite to each other; Driven by the first electric push rod and the second electric push rod, the airbag can slide along the first slide rail and the second slide rail, so that the airbag can slide between the two metal connection segments.

[0010] Preferably, the airbag pushing assembly further includes a backup airbag. When the airbag fails, the backup airbag can be configured at the position of the airbag and used. Then, under the push of the first electric push rod and the second electric push rod, the backup airbag can slide up and down between the first slide rail and the second slide rail. The left and right sides of the backup airbag are also provided with hard openings.

[0011] Preferably, the positioning assembly includes two built-in balloons, two first connecting rods, a first inner support sheet, a second inner support sheet, two second connecting rods, a first gear, a second gear, a first limiting rod and a second limiting rod; Two built-in balloons are respectively arranged in the two metal connecting sections, and the two built-in balloons both have a third opening, and the third opening is rigidly sealed and connected to the first opening, the first inner support sheet and the second inner support sheet are respectively bonded to one end of the two built-in balloons away from the first opening, one end of two first connecting rods is connected to the first inner support sheet, and the other ends of the two first connecting rods are transmission-connected to the first limit rod through a first gear, one end of two second connecting rods is connected to the second inner support sheet, and the other ends of the two second connecting rods are transmission-connected to the second limit rod through a second gear; When the first inner support sheet pushes the two first connecting rods to move in a direction close to the first opening, the two first connecting rods drive the first gear to rotate and then drive the first limiting rod to move in a direction toward the inside of the built-in balloon. At this time, the first limiting rod allows the airbag to slide up and down; when the first inner support sheet pulls the two first connecting rods to move away from the first opening, the two first connecting rods drive the first gear to rotate and then drive the first limiting rod to move in a direction close to the airbag. At this time, the first limiting rod does not allow the airbag to slide up and down; When the second inner support plate pushes the two second connecting rods to move toward the first opening, the two second connecting rods drive the second gear to rotate and then drive the second limit rod to move toward the inside of the built-in balloon. At this time, the second limit rod allows the airbag to slide up and down; when the second inner support plate pulls the two second connecting rods to move away from the first opening, the two second connecting rods drive the second gear to rotate and then drive the second limit rod to move toward the direction of the airbag. At this time, the second limit rod does not allow the airbag to slide up and down; wherein, the first limit rod and the second limit rod need to move synchronously during action to achieve positioning locking or unlocking of the airbag.

[0012] Preferably, the air supply unit includes an air supply assembly, the air supply assembly having a first main air supply hard pipe and a second main air supply hard pipe. One of the metal connection segments is connected to the first main air supply hard pipe through a first sub-air supply hard pipe, and the other metal connection segment is connected to the second main air supply hard pipe through a third sub-air supply hard pipe. One of the built-in balloons is sequentially connected to the first main air supply hard pipe through a first air supply hose and a second sub-air supply hard pipe, and the other built-in balloon is sequentially connected to the second main air supply hard pipe through a second air supply hose and a fourth sub-air supply hard pipe. Wherein, a first solenoid valve is provided on the first sub-air supply hard pipe, a second solenoid valve is provided on the second sub-air supply hard pipe, a third solenoid valve is provided on the third sub-air supply hard pipe, and a fourth solenoid valve is provided on the fourth sub-air supply hard pipe.

[0013] A segmented protection method for the core stage transportation of a launch vehicle according to the present invention includes the following steps: Step 1: Install the protection integration unit on the outer side of the core stage of the launch vehicle. In the initial state, neither the right side of the first limiting rod nor the left side of the second limiting rod exceeds the metal connection segment. The second solenoid valve and the fourth solenoid valve are both in the closed state, and the air release solenoid valve of the air supply assembly is also in the closed state. The first solenoid valve and the third solenoid valve are in the open state. Control the first electric push rod and the second electric push rod to work. The airbag moves upward from the initial position under the push of the first electric push rod and the second electric push rod until the second openings on the left and right sides of the airbag are docked with the first openings on the sides of the metal connection segments on the left and right sides, and the built-in airbags on the left and right sides are communicated with the airbag; Step 2: Control the air supply assembly to start working and start supplying air into the two metal connection segments. The internal pressure of the two left metal connection segments increases, which can cause the first inner support piece to drive the first connecting rod to move to the right and drive the second gear to rotate, and then drive the first limiting rod to move to the left until it stops. The second inner support piece drives the second connecting rod to move to the left and drive the first gear to rotate, and then drive the second limiting rod to move to the right until it stops; Step 3: Close the first solenoid valve and the third solenoid valve, then open the second solenoid valve and the fourth solenoid valve, and open the air supply assembly to start supplying air into the two built-in airbags and the airbag. The internal pressure of the two built-in airbags and the airbag increases, causing the two first connecting rods to move to the left and drive the second gear to rotate, and then drive the first limiting rod to move to the right until it stops. The two second connecting rods move to the right and drive the first gear to rotate, and then drive the second limiting rod to move to the left until it stops. When the internal pressure of the two built-in airbags and the airbag is greater than the internal pressure of the two metal connection segments, close the second solenoid valve and the fourth solenoid valve. At this time, the right side of the first limiting rod and the left side of the second limiting rod both exceed the boundary of the metal connection segment, and the airbag can be limited in the radial direction. Along the circumferential direction of the core stage of the launch vehicle, two adjacent airbags are in soft contact; Step 4: During the transportation of the core stage of the launch vehicle, the oil-gas spring cylinders under the two end support brackets provide vibration damping function throughout the process, and at the same time, they can convert mechanical energy into electrical energy for storage. If the outer side of the metal connection section is hit by flying stones, the two auxiliary oil-gas spring cylinders can provide vibration damping function. If the airbag is damaged due to being hit by flying stones, the first electric push rod and the second electric push rod can push out the spare airbag and continue to perform the operation of inflating the spare airbag, so as to continue to provide protection function for the transportation of the core stage of the launch vehicle.

[0014] Compared with the prior art, the present invention has the following beneficial effects: The present invention provides a brand-new transportation method for the core stage of the launch vehicle. Different from the traditional transportation method using a rainproof cloth for covering, the protection integration device in the present invention can not only provide vibration damping function for the core stage of the launch vehicle during transportation, but also convert the vibration energy of the core stage of the launch vehicle into electrical energy and store it. In addition, the protection integration unit covering the outside of the core stage of the launch vehicle can greatly reduce the impact of flying stones during transportation and has the ability of secondary self-repair, providing all-round guarantee for the safe transportation of the core stage of the launch vehicle. Brief Description of the Drawings

[0015] By reading the detailed description of the non-limiting embodiments with reference to the following drawings, other features, objects and advantages of the present invention will become more obvious: Figure 1 It is a schematic structural diagram of the protection integration unit; Figure 2 It is a schematic structural diagram of the protection structures at both ends of the rocket core stage; Figure 3 It is a schematic diagram of three different positions during the movement of the airbag; Figure 4 It is a schematic structural diagram of the support fixing frame configured at the second opening; Figure 5 It is a schematic structural diagram when the convex platform is matched with the slide rail; Figure 6 It is a schematic structural diagram of the support plate.

[0016] As shown in the figure: Metal connection section 1; First opening 101; Built-in balloon 2; First connecting rod 3; First inner support sheet 4; First air supply hose 5; Air supply component 6; First main air supply hard pipe 7; Air release solenoid valve 8; Flexible support pad 9; Auxiliary oil-gas spring cylinder 10; The first sub-air supply rigid pipe 11; The first solenoid valve 12; The second sub-air supply rigid pipe 13; The second solenoid valve 14; The first electric push rod bracket 15; The first electric push rod 16; The first slide rail 17; The spare airbag 18; The second main air supply rigid pipe 19; The second electric push rod 20; The second electric push rod bracket 21; The third sub-air supply rigid pipe 22; The fourth sub-air supply rigid pipe 23; The fourth solenoid valve 24; The third solenoid valve 25; The second air supply hose 26; The second slide rail 27; The second inner support piece 28; The second connecting rod 29; The first gear 30; The second gear 31; The airbag 32; The second opening 321; The support fixing frame 322; The boss 3221; The support plate 323; The first limiting rod 33; The second limiting rod 34; The first main oil and gas spring cylinder bracket 35; The first main oil and gas spring cylinder 36; The vehicle body upper bracket 37; The first energy storage component 38; The vehicle body 39; The power generation component 40; The power distribution mechanism 41; The second energy storage component 42; The transmission shaft 43; The second main oil and gas spring cylinder 44; The second main oil and gas spring cylinder bracket 45; The support bracket 46; The protective cover 47. Detailed implementation manners

[0017] The present invention will be described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that for those of ordinary skill in the art, without departing from the concept of the present invention, several changes and improvements can still be made. These all belong to the protection scope of the present invention.

[0018] The present invention provides a protection device applicable to the transportation of the core stage of a launch vehicle, including a plurality of protection integration units, a control unit, an energy storage and power generation unit, a air supply unit, a buffer unit, and two front and rear protective covers 47. The air supply unit can supply air to the protection integration units and is electrically connected to the energy storage and power generation unit. Protective covers 47 are arranged at both the front and rear ends of the rocket core stage. A plurality of protection integration units are arranged circumferentially around the rocket core stage and are arranged in sequence along the axial direction of the rocket core stage. A plurality of protection integration units are all arranged between the two front and rear protective covers 47.

[0019] Specifically, the energy storage and power generation unit and the air supply unit are both arranged on the vehicle body 39. The protective cover 47 is arranged on the vehicle body 39 through the buffer unit. The buffer unit has a vibration damping function and can trigger the energy storage and power generation unit to generate electricity and complete energy storage when the rocket core stage vibrates.

[0020] As Figure 2 shown, the buffer unit includes two front and rear support brackets 46, two front and rear first main oil-gas spring cylinder brackets 35, two front and rear first main oil-gas spring cylinders 36, two front and rear second main oil-gas spring cylinder brackets 45, two front and rear second main oil-gas spring cylinders 44, an upper bracket 37 on the vehicle body, and two front and rear drive shafts 43. The energy storage and power generation unit includes a first energy storage component 38, a second energy storage component 42, a power generation component 40, and a power distribution mechanism 41. The protective cover 47 is arranged on the support bracket 46. The power generation component 40 and the power distribution mechanism 41 are both arranged inside the vehicle body 39. The power distribution mechanism 41 is electrically connected to a plurality of power generation components 40 respectively. Multiple groups of power generation components 40 can be set. For example, 4 groups of power generation components 40 can be set. The first energy storage component 38 and the second energy storage component 42 are both arranged outside the vehicle body 39. A part of the power generation components 40 is electrically connected to the first energy storage component 38, and another part of the power generation components 40 is electrically connected to the second energy storage component 42.

[0021] Furthermore, the upper bracket 37 of the vehicle body is arranged on the upper part of the vehicle body 39, the lower end of the transmission shaft 43 is arranged on the top of the power distribution mechanism 41, the upper end of the transmission shaft 43 passes through the upper bracket 37 of the vehicle body and is connected to the bottom of the support bracket 46, the first master oil-gas spring cylinder 36 is arranged between the upper bracket 37 of the vehicle body and the support bracket 46 through the first master oil-gas spring cylinder bracket 35 and is located on one side of the transmission shaft 43, and the second master oil-gas spring cylinder 44 is arranged between the upper bracket 37 of the vehicle body and the support bracket 46 through the second master oil-gas spring cylinder bracket 45 and is located on the other side of the transmission shaft 43. When the transport vehicle is moving, the core stage of the launch vehicle will be in a state of vibration due to the bumpy road surface. The first main oil-gas spring cylinder 36 and the second main oil-gas spring cylinder 44 can provide a vibration reduction function for the core stage of the rocket. At the same time, the up and down vibration of the core stage of the launch vehicle can drive the transmission shaft 43 to vibrate up and down through the support bracket 46. The up and down vibration of the transmission shaft 43 can enable the two power generation components 40 to generate electricity through the power distribution mechanism 41. The electric energy generated by the two power generation components 40 is stored in the first energy storage component 38 and the second energy storage component 42, and can power other electrical equipment in the device.

[0022] Specifically, the control unit preferably adopts a central processing unit, and the air supply unit includes an air supply component 6, and the air supply component 6 is provided with an air release solenoid valve 8. The air supply component 6 supplies air to the protection integrated unit through an air supply pipe.

[0023] like Figure 1 As shown, the protection integrated unit is the main structure of the segmented protection integrated device for transporting the core stage of a carrier rocket. The number of protection integrated units is large and they are closely arranged along the axial and circumferential directions of the core stage. The protection integrated unit includes two metal connecting segments 1, a flexible support assembly, an airbag 32 arranged between the two metal connecting segments 1, an airbag pushing assembly and a positioning assembly arranged inside the metal connecting segment 1. The protection integrated unit presses the outer side of the core stage of the carrier rocket through the flexible support assembly. A first opening 101 is provided on the side of the metal connecting segment 1, and the first openings 101 of the two metal connecting segments 1 are arranged oppositely. Second openings 321 are provided on both sides of the airbag 32. Both the first opening 101 and the second opening 321 are hard openings. Driven by the airbag pushing assembly, the airbag 32 can make the first opening 101 and the second opening 321 in a facing position or make the first opening 101 and the second opening 321 relatively staggered. When the first opening 101 and the second opening 321 are in a facing position, the control unit can control the air supply assembly 6 so that the positioning assembly positions the airbag 32.

[0024] The flexible support assembly includes four flexible support pads 9 and four auxiliary oil-gas spring cylinders 10. One end of the auxiliary oil-gas spring cylinder 10 is connected to the metal connecting section 1, and the other end of the auxiliary oil-gas spring cylinder 10 is connected to the flexible support pad 9. The flexible support pad 9 presses the outer side of the core stage of the launch vehicle. The auxiliary oil-gas spring cylinder 10 is smaller in size than the main oil-gas spring cylinder.

[0025] As shown Figure 1 in the figure, the airbag pushing assembly includes a first electric push rod bracket 15, a first electric push rod 16, a first slide rail 17, a second electric push rod 20, a second electric push rod bracket 21, and a second slide rail 27. The first slide rail 17 is arranged on the side of a metal connection section 1. The first electric push rod 16 is arranged on a metal connection section 1 through the first electric push rod bracket 15. The second slide rail 27 is arranged on the side of another metal connection section 1. The second electric push rod 20 is arranged on another metal connection section 1 through the second electric push rod bracket 21. The first slide rail 17 and the second slide rail 27 are arranged oppositely. Driven by the first electric push rod 16 and the second electric push rod 20, the airbag 32 can be driven to slide along the first slide rail 17 and the second slide rail 27, so that the airbag 32 can slide between the two metal connection sections 1.

[0026] It should be noted that the first electric push rod 16 has a telescopic first ejector rod, and the end of the first ejector rod is fixedly connected to the second opening 321 on one side of the airbag 32. The second electric push rod 20 has a telescopic second ejector rod, and the end of the second ejector rod is fixedly connected to the second opening 321 on the other side of the airbag 32. Since the second opening 321 is a rigid opening, when the electric push rod pushes the second opening 321 to move, the certainty of the movement track of the second opening 321 can be ensured. In order to make the first opening 101 and the second opening 321 accurately correspond, the stop positions of the movement strokes of the first electric push rod 16 and the second electric push rod 20 can be set, so that when the first ejector rod and the second ejector rod on the first electric push rod 16 and the second electric push rod 20 stop moving, the first opening 101 and the second opening 321 are exactly in the facing position. To increase the stability of the connection between the ejector rod and the second opening 321, it is preferably to configure a support fixing frame 322 on the outer wall of the second opening 321, such as an annular support fixing frame. One side of the annular support fixing frame is fixedly connected to the end of the ejector rod, and the other side is detachably fixed on the second opening. When the airbag 32 needs to be disassembled, only the support fixing frame 322 needs to be removed from the second opening.

[0027] In order to reduce interference during the movement of the airbag 32, the end of the first opening 101 in the present invention protrudes outside the metal connection section 1, and the second opening 321 is arranged with a gap from the side wall of the metal connection section 1. As Figure 3 、 Figure 4 shown in the figure, a boss 3221 extends from the side of the support fixing frame 322 facing the metal connection section 1. The boss 3221 on one side forms a first sliding pair with the first slide rail 17 in sliding cooperation, and the boss 3221 on the other side forms a second sliding pair with the second slide rail 27 in sliding cooperation. As Figure 3 、 Figure 4 、 Figure 5As shown, when the first ejector rod and the second ejector rod respectively and synchronously push the support fixing frames 322 on both sides of the airbag 32 to move, the bosses 3221 on the two support fixing frames 322 slide in the first slide rail 17 and the second slide rail 27 respectively, guiding the movement of the airbag 32 until the first opening 101 and the second opening 321 are directly opposite and connected.

[0028] In order to achieve sealing after the connection of the first opening 101 and the second opening 321, the ends of the first opening 101 and the second opening 321 are both flexible sealing structures. During the movement of the airbag 32, the second opening 321 contacts and slides relative to the first opening 101, as Figure 5 shown, until the first opening 101 and the second opening 321 are directly opposite and connected, and the flexible sealing structures on the first opening 101 and the second opening 321 contact and are sealed and connected.

[0029] As Figure 1 shown, the airbag pushing assembly further includes a spare airbag 18. The left and right sides of the spare airbag 18 are also hard openings. Based on the same principle as the airbag 32, under the push of the first electric push rod 16 and the second electric push rod 20, the spare airbag 18 can also slide up and down. If the airbag 32 is damaged by flying stones, it can be replaced with the spare airbag 18. The spare airbag 18 is pushed out by the first electric push rod 16 and the second electric push rod 20, which can continue to provide a protection function for the transportation of the core stage of the launch vehicle.

[0030] As Figure 1As shown, the positioning assembly includes two built-in balloons 2, two first connecting rods 3, a first inner support sheet 4, a second inner support sheet 28, two second connecting rods 29, a first gear 30, a second gear 31, a first limiting rod 33 and a second limiting rod 34. The two built-in balloons 2 are respectively arranged in two metal connecting sections 1. The built-in balloons 2 have a third opening, and the third opening is rigidly sealed and connected to the first opening 101. After the third opening is connected to the first opening 101, a movement space is formed together. The movement space provides a channel for the movement of the limiting rod. The first inner support sheet 4 and the second inner support sheet 28 are respectively arranged at one end of the two built-in balloons 2 away from the first opening 101. One end of the two first connecting rods 3 is connected to the first inner support sheet 4. The two The other end of the first connecting rod 3 extends to the interior of the motion space and is connected to the first limiting rod 33 through the first gear 30, and the other end of the first connecting rod 3 is a rack structure matching the first gear 30 on the side facing the first gear 30; one end of the two second connecting rods 29 is connected to the second inner support plate 28, and the other ends of the two second connecting rods 29 extend to the interior of the motion space and are connected to the second limiting rod 34 through the second gear 31, and the other end of the second connecting rod 29 is a rack structure matching the second gear 31 on the side facing the second gear 31; both sides of the first limiting rod 33 are rack structures and are respectively meshed with the first gear 30, and both sides of the second limiting rod 34 are rack structures and are respectively meshed with the second gear 31.

[0031] Further, when the first inner support sheet 4 pushes the two first connecting rods 3 to move in a direction close to the first opening 101, the two first connecting rods 3 drive the first gear 30 to rotate and thereby drive the first limiting rod 33 to move in a direction toward the inside of the built-in balloon 2, and the first limiting rod 33 moves toward one end of the airbag 32 to the inside of the first opening 101. At this time, the first limiting rod 33 does not interfere with the airbag 32, allowing the airbag 32 to slide up and down; when the first inner support sheet 4 pulls the two first connecting rods 3 to move in a direction away from the first opening 101, the two first connecting rods 3 drive the first gear 30 to rotate, thereby driving the first limiting rod 33 to move in a direction toward the airbag 32. At this time, the end of the first limiting rod 33 extends into the second opening 321, that is, the first limiting rod 33 is inserted into the second opening 321 of the airbag 32 ( Figure 1In the second opening 321 on the left side of the middle airbag 32, the up-and-down sliding of the airbag 32 is not allowed. Similarly, when the second inner support piece 28 pushes the two second connecting rods 29 to move towards the first opening 101, the two second connecting rods 29 drive the second gear 31 to rotate, which in turn drives the second limiting rod 34 to move towards the inside of the built-in balloon 2. At this time, the end of the second limiting rod 34 facing the airbag 32 moves into the first opening 101, allowing the airbag 32 to slide up and down; when the second inner support piece 28 pulls the two second connecting rods 29 to move away from the first opening 101, the two second connecting rods 29 drive the second gear 31 to rotate, and then drive the second limiting rod 34 to move towards the airbag 32. At this time, the end of the second limiting rod 34 facing the airbag 32 is inserted into the second opening 321 ( Figure 1 in the second opening 321 on the right side of the middle airbag 32), interfering with the movement of the airbag 32, and thus not allowing the airbag 32 to slide up and down; among them, the first limiting rod 33 and the second limiting rod 34 need to move synchronously during operation, so as to realize the synchronous positioning and locking or synchronous unlocking of both sides of the airbag 32.

[0032] It should be noted that the first inner support piece 4 and the second inner support piece 28 are preferably adhesively bonded to the inner surfaces of the two built-in balloons 2 respectively. A support plate 323 is arranged inside the second opening 321. As Figure 6 shown, the support piece is a porous structure. On the one hand, the support plate 323 can play a role in supporting the second opening 321. On the other hand, the support piece has a central hole, and the central hole matches both the first limiting rod 33 and the second limiting rod 34. The ends of the first limiting rod 33 and the second limiting rod 34 can just be inserted into the central hole of the support piece to realize the limiting or positioning of the second opening 321. That is to say, when the first limiting rod 33 moves towards the outside of the built-in balloon 2, it is inserted into the second opening 321 on one side of the airbag 32, and when the second limiting rod 34 moves towards the outside of the built-in balloon 2, it is inserted into the second opening 321 on the other side of the airbag 32, so that the airbag 32 is positioned and locked.

[0033] The air supply assembly 6 has a first main air supply hard pipe 7, a second main air supply hard pipe 19. One metal connection section 1 is connected to the first main air supply hard pipe 7 through a first sub-air supply hard pipe 11, and the other metal connection section 1 is connected to the second main air supply hard pipe 19 through a third sub-air supply hard pipe 22. One built-in balloon 2 is sequentially connected to the first main air supply hard pipe 7 through a first air supply hose 5 and a second sub-air supply hard pipe 13, and the other built-in balloon 2 is sequentially connected to the second main air supply hard pipe 19 through a second air supply hose 26 and a fourth sub-air supply hard pipe 23. Among them, a first electromagnetic valve 12 is arranged on the first sub-air supply hard pipe 11, a second electromagnetic valve 14 is arranged on the second sub-air supply hard pipe 13, a third electromagnetic valve 25 is arranged on the third sub-air supply hard pipe 22, and a fourth electromagnetic valve 24 is arranged on the fourth sub-air supply hard pipe 23.

[0034] Specifically, as Figure 1 、 Figure 2 shown, both of the left and right metal connecting segments 1 have a cavity structure inside, and each metal connecting segment 1 is provided with an internal balloon 2. Inside the left internal balloon 2, there are a first connecting rod 3, a first inner support sheet 4, a second gear 31, and a first limiting rod 33. The first inner support sheet 4 is closely attached to the inner side of the left internal balloon 2 and is connected to the two first connecting rods 3. The two first connecting rods 3 can move left and right under the drive of the first inner support sheet 4, and then drive the first limiting rod 33 to move left and right through the second gear 31. Inside the right internal balloon 2, there are a second connecting rod 29, a second inner support sheet 28, a first gear 30, and a second limiting rod 34. The second inner support sheet 28 is closely attached to the inner side of the right internal balloon 2 and is connected to the two second connecting rods 29. The two second connecting rods 29 can move left and right under the drive of the second inner support sheet 28, and then drive the second limiting rod 34 to move left and right through the first gear 30.

[0035] Specifically, as Figure 1 shown, the lower end of the left internal balloon 2 is connected to one end of the first air supply hose 5, and the right side is connected to the fixed rigid pipe of the metal connecting segment 1. The other end of the first air supply hose 5 is connected to one end of the second sub-air supply rigid pipe 13, and the connection point is located on the shell of the left metal connecting segment 1. The other end of the second sub-air supply rigid pipe 13 is connected to the first main air supply rigid pipe 7. One end of the first sub-air supply rigid pipe 11 is directly connected to the left metal connecting segment 1, and the other end of the first sub-air supply rigid pipe 11 is connected to the first main air supply rigid pipe 7. The first main air supply rigid pipe 7 is connected to the air supply component 6. On the right side inside the left metal connecting segment 1, there is a first slide rail 17.

[0036] Specifically, as Figure 1 shown, the right internal balloon 2 is connected to one end of the second air supply hose 26, and the left side is connected to the fixed rigid pipe of the metal connecting segment 1. The other end of the second air supply hose 26 is connected to one end of the fourth sub-air supply rigid pipe 23, and the connection point is located on the shell of the right metal connecting segment 1. The other end of the fourth sub-air supply rigid pipe 23 is connected to the second main air supply rigid pipe 19. One end of the third sub-air supply rigid pipe 22 is directly connected to the right metal connecting segment 1, and the other end of the third sub-air supply rigid pipe 22 is connected to the second main air supply rigid pipe 19. The second main air supply rigid pipe 19 is connected to the air supply component 6. On the left side inside the right metal connecting segment 1, there is a second slide rail 27.

[0037] Specifically, as Figure 1As shown in the figure, for the protection device applicable to the transportation of the core stage of a launch vehicle, the first electric push rod 16 is connected to the left metal connection section 1 through the first electric push rod bracket 15, and the second electric push rod 20 is connected to the right metal connection section 1 through the second electric push rod bracket 21. Two auxiliary oil-gas spring cylinders 10 are arranged at the lower end of each metal connection section 1, and the lower end of the auxiliary oil-gas spring cylinder 10 is connected to the flexible support pad 9, and the flexible support pad 9 can press against the outside of the core stage of the launch vehicle.

[0038] Specifically, as Figure 1 , Figure 2 shown, for the protection device applicable to the transportation of the core stage of a launch vehicle in this embodiment, the protective cover 47 is connected to the support bracket 46, and the support bracket 46 is respectively connected to the first main oil-gas spring cylinder bracket 35 and the second main oil-gas spring cylinder bracket 45. The first main oil-gas spring cylinder bracket 35 and the second main oil-gas spring cylinder bracket 45 are respectively connected to the first main oil-gas spring cylinder 36 and the second main oil-gas spring cylinder 44. Both the first main oil-gas spring cylinder bracket 35 and the second main oil-gas spring cylinder bracket 45 are connected to the vehicle body upper bracket 37, and the vehicle body upper bracket 37 is installed on the vehicle body 39. One end of the transmission shaft 43 is connected to the center of the lower end of the support bracket 46, and the other end is connected to the power distribution mechanism 41. The power distribution mechanism 41 is connected to two power generation components 40. Both the power distribution mechanism 41 and the two power generation components 40 are arranged inside the vehicle body 39. The two power generation components 40 are connected to the air supply component 6, and the electric energy of the two energy storage devices is connected to the air supply component 6, which can drive the air supply component 6 to supply air to the protection integration unit.

[0039] As Figure 1 , Figure 2 shown, the present invention also provides a segmented protection method for the transportation of the core stage of a launch vehicle, including the following steps: Step 1: The protection integration unit is first installed on the outside of the core stage of the launch vehicle. In the initial state, neither the right side of the first limit rod 33 nor the left side of the second limit rod 34 exceeds the metal connection section 1. Both the second solenoid valve 14 and the fourth solenoid valve 24 are in the closed state, and the air release solenoid valve 8 of the air supply component 6 is also in the closed state. The first solenoid valve 12 and the third solenoid valve 25 are in the open state. Then the central processor issues an instruction to make the first electric push rod 16 and the second electric push rod 20 work. The airbag 32 moves upward from the initial position under the push of the first electric push rod 16 and the second electric push rod 20 until the second openings 321 on the left and right sides of the airbag 32 are docked with the first openings 101 on the sides of the left and right metal connection sections 1. In this way, the built-in balloons 2 on the left and right sides are connected to the airbag 32; Step 2: Then the central processing unit issues an instruction, and the air supply component 6 starts to work, starting to supply air into the left metal connection section 1 and the right metal connection section 1. The internal pressure of the left metal connection section 1 and the right metal connection section 1 gradually rises to the preset pressure P1. The central processing unit issues an instruction to turn off the air supply component 6. During the process of the internal pressure of the two metal connection sections 1 gradually rising, due to the initially low pressure of the built-in balloon 2, under the influence of the pressure difference, the first inner support piece 4 gradually moves to the right, and the second inner support piece 28 gradually moves to the left. The two first connecting rods 3 gradually move to the right during this process, and then drive the second gear 31 to rotate, and then drive the first limiting rod 33 to move to the left until it stops. The second inner support piece 28 gradually moves to the left, and the two second connecting rods 29 gradually move to the left during this process, and then drive the first gear 30 to rotate, and then drive the second limiting rod 34 to move to the right until it stops; Step 3: Then the central processing unit issues an instruction to close the first solenoid valve 12 and the third solenoid valve 25, then open the second solenoid valve 14 and the fourth solenoid valve 24, and open the air supply component 6 to start supplying air into the two built-in balloons 2 and the airbag 32. During this process, the internal pressure of the two built-in balloons 2 and the airbag 32 gradually rises. The increase in pressure makes the ends of the first opening 101 and the second opening 321 fit more closely. Due to the influence of the pressure difference change, the two first connecting rods 3 move to the left, driving the second gear 31 to rotate, and then driving the first limiting rod 33 to move to the right until it stops. The two second connecting rods 29 move to the right, driving the first gear 30 to rotate, and the second limiting rod 34 moves to the left until it stops; when the internal pressure of the two built-in balloons 2 and the airbag 32 is greater than the internal pressure of the two metal connection sections 1, close the second solenoid valve 14 and the fourth solenoid valve 24. At this time, the internal pressure of the two built-in balloons 2 and the airbag 32 and the internal pressure of the two metal connection sections 1 are P2. At this time, both the right side of the first limiting rod 33 and the left side of the second limiting rod 34 have exceeded the boundary of the metal connection section 1, and the airbag 32 can be limited in the radial direction. Along the circumferential direction of the core stage of the launch vehicle, two adjacent airbags 32 are in soft contact; Step 4: During the transportation of the core stage of the launch vehicle, the oil-gas spring cylinders under the two end support brackets 46 provide shock absorption functions throughout the process, and at the same time, the mechanical energy can be converted into electrical energy for storage. If the outer side of the metal connection section 1 is hit by flying stones, the two auxiliary oil-gas spring cylinders 10 can provide shock absorption functions, greatly buffering the impact on the core stage of the launch vehicle. If the airbag 32 is damaged by being hit by flying stones, the first electric push rod 16 and the second electric push rod 20 can push out the spare airbag 18, and continue to perform the above operations to inflate the spare airbag 18, which can continue to provide protection functions for the transportation of the core stage of the launch vehicle.

[0040] In the description of the present application, it should be understood that the orientation or positional relationship indicated by the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present application.

[0041] The specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Without conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A protection device applicable to the transportation of the core stage of a launch vehicle, characterized in that, It includes multiple protection integration units, an energy storage and power generation unit, a ventilation unit, a buffer unit, a vehicle body (39), and two protective covers (47). The two protective covers (47) are respectively arranged at the front and rear ends of the rocket core stage. The multiple protection integration units are arranged circumferentially along the rocket core stage and are arranged in sequence along the axial direction of the rocket core stage. The multiple protection integration units are all arranged between the front and rear two protective covers (47). The ventilation unit can supply air to the protection integration unit and is electrically connected to the energy storage and power generation unit. The energy storage and power generation unit and the ventilation unit are both arranged on the vehicle body (39). The protective cover (47) is arranged on the vehicle body (39) through the buffer unit. The buffer unit has a vibration damping function and can trigger the energy storage and power generation unit to generate electricity and complete energy storage through the buffer unit when the rocket core stage vibrates. The protection integration unit includes two metal connection segments (1), a flexible support assembly, an airbag (32) arranged between the two metal connection segments (1), an airbag pushing assembly, and a positioning assembly arranged inside the metal connection segment (1). The protection integration unit presses against the outside of the carrier rocket core stage through the flexible support assembly. A first opening (101) is provided on the side of the metal connection segment (1), and the first openings (101) of the two metal connection segments (1) are arranged opposite to each other. Second openings (321) are provided on both sides of the airbag (32). The first opening (101) and the second opening (321) are both rigid openings. The airbag (32) can be driven by the airbag pushing assembly to make the first opening (101) and the second opening (321) in a facing arrangement position. At this time, the positioning assembly can position the airbag (32) by controlling the ventilation assembly (6).

2. The protective device applicable to the core stage transportation of a launch vehicle according to claim 1, wherein The energy storage and power generation unit includes a first energy storage component (38), a second energy storage component (42), a power generation component (40), and a power distribution mechanism (41). The protective cover (47) is arranged on the support bracket (46) of the buffer unit. The power generation component (40) and the power distribution mechanism (41) are both arranged inside the vehicle body (39). The power distribution mechanism (41) is electrically connected to multiple power generation components (40) respectively. The first energy storage component (38) and the second energy storage component (42) are both arranged outside the vehicle body (39). A part of the power generation components (40) is electrically connected to the first energy storage component (38), and another part of the power generation components (40) is electrically connected to the second energy storage component (42).

3. The protective device applicable to the transportation of the core stage of a launch vehicle according to claim 2, wherein The buffer unit includes two front and rear support brackets (46), two front and rear first main oil-gas spring cylinder brackets (35), two front and rear first main oil-gas spring cylinders (36), two front and rear second main oil-gas spring cylinder brackets (45), two front and rear second main oil-gas spring cylinders (44), a vehicle body upper bracket (37), and two front and rear transmission shafts (43). The upper bracket (37) of the vehicle body is arranged at the upper part of the vehicle body (39). The lower end of the transmission shaft (43) is arranged at the top of the power distribution mechanism (41). The upper end of the transmission shaft (43) passes through the upper bracket (37) of the vehicle body and is connected to the bottom of the support bracket (46). The first main oil-gas spring cylinder (36) is arranged between the upper bracket (37) of the vehicle body and the support bracket (46) through the first main oil-gas spring cylinder bracket (35) and is located on one side of the transmission shaft (43). The second main oil-gas spring cylinder (44) is arranged between the upper bracket (37) of the vehicle body and the support bracket (46) through the second main oil-gas spring cylinder bracket (45) and is located on the other side of the transmission shaft (43); The first main oil-gas spring cylinder (36) and the second main oil-gas spring cylinder (44) are used to provide vibration damping for the rocket core stage.

4. The protective device applicable to the core stage transportation of a launch vehicle according to claim 1, wherein The flexible support assembly includes a plurality of flexible support pads (9) and a plurality of auxiliary oil-gas spring cylinders (10). One end of the auxiliary oil-gas spring cylinder (10) is connected to the metal connection section (1), and the other end of the auxiliary oil-gas spring cylinder (10) is connected to the flexible support pad (9). The flexible support pad (9) presses against the outside of the rocket core stage.

5. The protective device applicable to the core stage transportation of a launch vehicle according to claim 1, characterized in that, The airbag pushing assembly includes a first electric push rod bracket (15), a first electric push rod (16), a first slide rail (17), a second electric push rod (20), a second electric push rod bracket (21), and a second slide rail (27). The first slide rail (17) is arranged on the side of a metal connection section (1). The first electric push rod (16) is arranged on a metal connection section (1) through the first electric push rod bracket (15); The second slide rail (27) is arranged on the side of another metal connection section (1). The second electric push rod (20) is arranged on another metal connection section (1) through the second electric push rod bracket (21), and the first slide rail (17) and the second slide rail (27) are arranged oppositely; Driven by the first electric push rod (16) and the second electric push rod (20), the airbag (32) can slide along the first slide rail (17) and the second slide rail (27), so that the airbag (32) can slide between the two metal connection sections (1).

6. The protective device applicable to the core stage transportation of a launch vehicle according to claim 5, characterized in that, The airbag pushing assembly further includes a spare airbag (18). When the airbag (32) fails, the spare airbag (18) can be arranged at the position of the airbag (32) for use. Then, under the push of the first electric push rod (16) and the second electric push rod (20), the spare airbag (18) can slide up and down between the first slide rail (17) and the second slide rail (27); Hard openings are also provided on both the left and right sides of the spare airbag (18).

7. The protective device applicable to the core stage transportation of a launch vehicle according to claim 1, characterized in that, The positioning assembly includes two built-in balloons (2), two first connecting rods (3), a first inner support sheet (4), a second inner support sheet (28), two second connecting rods (29), a first gear (30), a second gear (31), a first limiting rod (33), and a second limiting rod (34); Two built-in balloons (2) are respectively arranged in the two metal connecting sections (1); the built-in balloons (2) each have a third opening, and the third opening is rigidly sealed and connected to the first opening (101); the first inner support sheet (4) and the second inner support sheet (28) are respectively bonded to one end of the two built-in balloons (2) away from the first opening (101); one end of two first connecting rods (3) are connected to the first inner support sheet (4); the other ends of the two first connecting rods (3) are transmission-connected to the first limit rod (33) via a first gear (30); one end of two second connecting rods (29) are connected to the second inner support sheet (28); the other ends of the two second connecting rods (29) are transmission-connected to the second limit rod (34) via a second gear (31); When the first inner support sheet (4) pushes the two first connecting rods (3) to move in a direction close to the first opening (101), the two first connecting rods (3) drive the first gear (30) to rotate and thereby drive the first limiting rod (33) to move in a direction toward the inside of the built-in balloon (2). At this time, the first limiting rod (33) allows the balloon (32) to slide up and down; when the first inner support sheet (4) pulls the two first connecting rods (3) to move in a direction away from the first opening (101), the two first connecting rods (3) drive the first gear (30) to rotate and thereby drive the first limiting rod (33) to move in a direction toward the balloon (32). At this time, the first limiting rod (33) does not allow the balloon (32) to slide up and down; When the second inner support sheet (28) pushes the two second connecting rods (29) to move in a direction close to the first opening (101), the two second connecting rods (29) drive the second gear (31) to rotate and thereby drive the second limiting rod (34) to move toward the inside of the built-in balloon (2). At this time, the second limiting rod (34) allows the balloon (32) to slide up and down; when the second inner support sheet (28) pulls the two second connecting rods (29) to move in a direction away from the first opening (101), the two second connecting rods (29) drive the second gear (31) to rotate and thereby drive the second limiting rod (34) to move toward the direction of the balloon (32). At this time, the second limiting rod (34) does not allow the balloon (32) to slide up and down; wherein, the first limiting rod (33) and the second limiting rod (34) need to move synchronously when in action to achieve positioning locking or unlocking of the balloon (32).

8. The protective device applicable to the core stage transportation of a launch vehicle according to claim 7, characterized in that, The air supply unit includes an air supply assembly (6). The air supply assembly (6) has a first main air supply hard pipe (7) and a second main air supply hard pipe (19). One of the metal connection segments (1) is connected to the first main air supply hard pipe (7) through a first sub-air supply hard pipe (11), and the other metal connection segment (1) is connected to the second main air supply hard pipe (19) through a third sub-air supply hard pipe (22). One of the built-in balloons (2) is sequentially connected to the first main air supply hard pipe (7) through a first air supply hose (5) and a second sub-air supply hard pipe (13), and the other built-in balloon (2) is sequentially connected to the second main air supply hard pipe (19) through a second air supply hose (26) and a fourth sub-air supply hard pipe (23). Wherein, a first electromagnetic valve (12) is arranged on the first sub-air supply hard pipe (11), a second electromagnetic valve (14) is arranged on the second sub-air supply hard pipe (13), a third electromagnetic valve (25) is arranged on the third sub-air supply hard pipe (22), and a fourth electromagnetic valve (24) is arranged on the fourth sub-air supply hard pipe (23).

9. A segmented protection method for the core stage transportation of a launch vehicle, characterized in that, Using the protection device applicable to the transportation of the core stage of a launch vehicle described in any one of claims 1 to 8, includes the following steps: Step 1: Install the protection integration unit on the outside of the core stage of the launch vehicle. In the initial state, neither the right side of the first limiting rod (33) nor the left side of the second limiting rod (34) exceeds the metal connection segment (1). The second electromagnetic valve (14) and the fourth electromagnetic valve (24) are both in the closed state, and the air release electromagnetic valve (8) of the air supply assembly (6) is also in the closed state. The first electromagnetic valve (12) and the third electromagnetic valve (25) are in the open state. Control the first electric push rod (16) and the second electric push rod (20) to work. The airbag (32) moves upward from the initial position under the push of the first electric push rod (16) and the second electric push rod (20) until the second openings (321) on the left and right sides of the airbag (32) are docked with the first openings (101) on the sides of the metal connection segments (1) on the left and right sides, and the built-in balloons (2) on the left and right sides are communicated with the airbag (32); Step 2: Control the air supply assembly (6) to start working, and start supplying air into the two metal connection segments (1). The pressure in the inner cavities of the two left metal connection segments (1) increases, so that the first inner support piece (4) drives the first connecting rod (3) to move to the right, driving the second gear (31) to rotate, and then driving the first limiting rod (33) to move to the left until it stops. The second inner support piece (28) drives the second connecting rod (29) to move to the left, driving the first gear (30) to rotate, and then driving the second limiting rod (34) to move to the right until it stops; Step 3: Close the first solenoid valve (12) and the third solenoid valve (25), then open the second solenoid valve (14) and the fourth solenoid valve (24), and turn on the air supply assembly (6) to start supplying air into the two built-in balloons (2) and the airbag (32). The increase in the internal pressure of the two built-in balloons (2) and the airbag (32) causes the two first connecting rods (3) to move to the left, driving the second gear (31) to rotate, which in turn drives the first limit rod (33) to move to the right until it stops. The two second connecting rods (29) move to the right, driving the first gear (30) to rotate, which in turn drives the second limit rod (34) to move to the left until it stops. When the internal pressure of the two built-in balloons (2) and the airbag (32) is greater than the internal pressure of the two metal connection sections (1), close the second solenoid valve (14) and the fourth solenoid valve (24). At this time, the right side of the first limit rod (33) and the left side of the second limit rod (34) have both exceeded the boundary of the metal connection section (1), and the airbag (32) can be limited radially. Along the circumferential direction of the core stage of the launch vehicle, two adjacent airbags (32) are in soft contact; Step 4: During the transportation of the core stage of the launch vehicle, the oil-gas spring cylinders under the two end support brackets (46) provide damping functions throughout the process and can convert mechanical energy into electrical energy for storage. If the outer side of the metal connection section (1) is hit by flying stones, the two auxiliary oil-gas spring cylinders (10) can provide damping functions. If the airbag (32) is damaged due to being hit by flying stones, the first electric push rod (16) and the second electric push rod (20) can push out the spare airbag (18), and continue to perform the operation of inflating the spare airbag (18), which can continue to provide protection functions for the transportation of the core stage of the launch vehicle.

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