Lifting device for launch vehicle and lifting method thereof

Abstract

The embodiment of the present application provides a lifting device of a carrier rocket and a lifting method thereof. In the lifting device of the carrier rocket provided in the embodiment of the present application, the carrier rocket is fixed by the arm mechanism during the lifting process of the carrier rocket, and the height difference between the first lifting point structure assembly and the second lifting point structure assembly can be controlled, so that the sling body carrying the carrier rocket can be turned to a vertical state. Compared with the lifting device in the prior art, the lifting device of the carrier rocket provided in the embodiment of the present application can avoid setting a connecting mechanism for cooperating with the sling on the carrier rocket, and can reduce the weight of the carrier rocket itself, thereby improving the carrying capacity of the carrier rocket and reducing the launch cost of the carrier rocket. The tray supports the carrier rocket in an axial direction parallel to the carrier rocket, which can ensure the reliability of the connection between the carrier rocket and the lifting device. And the tray is rotatably connected to the sling body, and when the sling body is evacuated, the sling body can be prevented from colliding with the carrier rocket.

Description

Technical Field

[0001] The present application relates to the technical field of launch preparation for a carrier rocket, and in particular, to a lifting device and a lifting method for a carrier rocket. Background Art

[0002] During the launch preparation process of the carrier rocket, after the carrier rocket is transported from the technical area to the launch area, a hoist is needed to transform the carrier rocket from a horizontal state to a vertical state to facilitate the docking of the carrier rocket with the launch pad.

[0003] In order to realize the lifting and rotation of the carrier rocket, it is necessary to set a connecting mechanism on the body of the carrier rocket to cooperate with the lifting device. However, setting the connecting mechanism will increase the weight of the carrier rocket itself, reduce the carrying capacity of the carrier rocket, and further increase the launch cost of the carrier rocket. Summary of the invention

[0004] In view of the shortcomings of the existing methods, the present application proposes a lifting device and a lifting method for a carrier rocket, so as to solve the technical problem in the prior art that during the lifting and rotation of the carrier rocket, the connecting mechanism set on the rocket body causes the weight of the carrier rocket itself to increase, resulting in a reduction in the carrying capacity of the carrier rocket.

[0005] In a first aspect, an embodiment of the present application provides a lifting device for a launch vehicle, comprising:

[0006] A sling body, the sling body comprising at least one arm mechanism, the arm mechanism being used to fix the carrier rocket during the lifting process of the carrier rocket;

[0007] At least one first suspension point structure component and at least one second suspension point structure component, the first suspension point structure component and the second suspension point structure component are both connected to the sling body;

[0008] The tray is arranged at one end of the sling body and is rotatably connected to the sling body, and the tray is connected to the launch vehicle.

[0009] Optionally, the first suspension point structure assembly is located at an end of the sling body away from the pallet and is rotatably connected to the sling body, and the rotation plane of the first suspension point structure assembly is parallel to the length extension direction of the sling body;

[0010] The second lifting point structure component is located at one end of the lifting device body close to the pallet.

[0011] Optionally, the first suspension point structure assembly includes two first sub-suspension point structures arranged opposite to each other; a first sub-suspension point structure is arranged on both sides of the sling body, and a direction from one first sub-suspension point structure to another first sub-suspension point structure is perpendicular to the length extension direction of the sling body;

[0012] The second lifting point structure assembly includes two second sub-lifting point structures arranged opposite to each other; a second sub-lifting point structure is arranged on both sides of the sling body, and the direction from one second sub-lifting point structure to another second sub-lifting point structure is perpendicular to the length extension direction of the sling body.

[0013] Optionally, the lifting device of the launch vehicle also includes a first sling assembly and a second sling assembly, the first sling assembly is connected to the first sling point structure assembly, and the second sling assembly is connected to the second sling point structure assembly.

[0014] Optionally, the lifting device of the launch vehicle also includes a first locking mechanism, which is fixedly connected to one of the pallet and the hanger body, and during the lifting process of the launch vehicle, locks the other one of the pallet and the hanger body.

[0015] Optionally, the tray is provided with a first positioning piece, and the first positioning piece matches with the second positioning piece of the launch pad. When the carrier rocket is in a vertical state, the first positioning piece is aligned and connected with the second positioning piece.

[0016] Optionally, the arm-holding mechanism includes a first holding ring and a second holding ring that are arranged opposite to each other, the first holding ring is fixedly connected to the sling body, one end of the second holding ring is rotatably connected to one end of the first holding ring, and the other end of the second holding ring is detachably connected to the other end of the first holding ring.

[0017] Optionally, the sling body comprises a bottom plate and at least two side beams, the side beams are connected to the bottom plate, and at least one side beam is disposed on two opposite sides of the bottom plate;

[0018] The tray is rotatably connected to the bottom plate, and the rotation plane of the tray is perpendicular to the bottom plate.

[0019] In a second aspect, an embodiment of the present application provides a lifting method of a lifting device of a launch vehicle based on the first aspect, comprising:

[0020] Connecting a carrier rocket loaded in a sling body of the lifting device to a tray of the lifting device, and locking the carrier rocket in an openable and closable manner by using at least one arm mechanism of the sling body;

[0021] Connecting the lifting device to at least one first lifting point structural component and at least one second lifting point structural component to lift the lifting device body loaded and locked with the launch vehicle; each first lifting point structural component and each second lifting point structural component are connected to the lifting device body;

[0022] By controlling the height difference between the first suspension point structure assembly and the second suspension point structure assembly, the sling body carrying the launch vehicle is turned over to a vertical state.

[0023] Optionally, the sling body carrying the launch vehicle is turned over to a vertical state by controlling the height difference between the first sling point structure assembly and the second sling point structure assembly, including:

[0024] Controlling the height of the second suspension point structure assembly to be gradually lower than the height of the first suspension point structure assembly until the sling body is in a vertical state;

[0025] The first hanging point structure component is located at a side of the second hanging point structure component away from the pallet.

[0026] Optionally, after the height difference between the first suspension point structure assembly and the second suspension point structure assembly is controlled so that the sling body carrying the launch vehicle is turned over to a vertical state, the method further includes:

[0027] Open the arm mechanism that locks the launch vehicle;

[0028] unlocking the first locking mechanism in a locked state;

[0029] Controlling the height of the first suspension point structure assembly to gradually decrease until the sling body is in a horizontal state;

[0030] Disassemble the pallet so that the pallet is separated from the spreader body;

[0031] The first lifting point structure assembly is controlled to drive the lifting device body away from the pallet, so that the lifting device body is away from the launching platform.

[0032] The beneficial technical effects brought about by the technical solution provided by the embodiment of the present application include:

[0033] In the lifting device of the carrier rocket provided in the embodiment of the present application, the arm mechanism fixes the carrier rocket during the lifting process of the carrier rocket, and by controlling the height difference between the first lifting point structure assembly and the second lifting point structure assembly, the sling body carrying the carrier rocket can be turned to a vertical state. Compared with the lifting device in the prior art, the lifting device of the carrier rocket provided in the embodiment of the present application can avoid setting a connecting mechanism for cooperating with the sling on the carrier rocket, and can reduce the weight of the carrier rocket itself, thereby improving the carrying capacity of the carrier rocket and reducing the launch cost of the carrier rocket.

[0034] During the lifting process of the carrier rocket, the tray arranged at one end of the lifting device body is connected to the carrier rocket, thereby supporting the carrier rocket in an axial direction parallel to the carrier rocket, and ensuring the reliability of the connection between the carrier rocket and the lifting device.

[0035] Moreover, since the pallet is rotatably connected to the hoist body, after the carrier rocket is flipped to a vertical state, the arm mechanism can be relatively away from the carrier rocket by controlling the rotation of the hoist body relative to the pallet. Therefore, in the process of evacuating and recovering the hoist body, collision between the hoist body and the carrier rocket can be avoided, thereby reducing the probability of damage to the carrier rocket and improving the lifting efficiency of the carrier rocket.

[0036] Additional aspects and advantages of the present application will be partially given in the following description, which will become apparent from the following description, or will be understood through the practice of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] The above and / or additional aspects and advantages of the present application will become apparent and easily understood from the following description of the embodiments in conjunction with the accompanying drawings, in which:

[0038] Figure 1 A schematic diagram of the structure of a lifting device for a launch vehicle provided in an embodiment of the present application;

[0039] Figure 2 Provided in the embodiments of this application Figure 1 An enlarged schematic diagram of point A of the lifting device of the launch vehicle shown;

[0040] Figure 3 Provided in the embodiments of this application Figure 2 The structural schematic diagram of the rotatable mechanism in the enlarged schematic diagram at A shown;

[0041] Figure 4 A schematic structural diagram of a hoisting device body of a launch vehicle provided in an embodiment of the present application;

[0042] Figure 5 Provided in the embodiments of this application Figure 4 The enlarged schematic diagram of point B of the sling body is shown;

[0043] Figure 6 Provided in the embodiments of this application Figure 4 A schematic structural diagram of the sling body from another perspective;

[0044] Figure 7 Provided in the embodiments of this application Figure 6 The enlarged schematic diagram of the C position of the sling body is shown;

[0045] Figure 8 Provided in the embodiments of this application Figure 6 The enlarged schematic diagram of the D position of the sling body is shown;

[0046] Fig. 9 Provided in the embodiments of this application Figure 6 The enlarged schematic diagram of the E position of the sling body is shown;

[0047] Fig.10 A schematic structural diagram of a first locking mechanism of a lifting device for a launch vehicle provided in an embodiment of the present application;

[0048] Fig.11 A schematic flow chart of a lifting method based on a lifting device of a launch vehicle provided in an embodiment of the present application;

[0049] Fig.12 A schematic diagram of loading a launch vehicle and a sling body in a lifting method provided in an embodiment of the present application;

[0050] Fig.13 A schematic diagram of a lifting method provided in an embodiment of the present application in which a carrier rocket is locked and connected to a lifting device body, and a carrier rocket is connected to a pallet;

[0051] Fig.14 A schematic diagram of a lifting device body of a lifting device loaded with a carrier rocket in a lifting method provided in an embodiment of the present application being in a horizontal state;

[0052] Fig.15 A schematic diagram of a process in which a hoisting device body of a hoisting device loaded with a carrier rocket is flipped from a horizontal state to a vertical state in a hoisting method provided in an embodiment of the present application;

[0053] Fig.16 A schematic diagram of a lifting device body in a vertical state with a lifting device loaded with a carrier rocket in a lifting method provided in an embodiment of the present application;

[0054] Fig.17 A schematic diagram of the separation of a hoisting device body and a launch vehicle in a lifting method provided in an embodiment of the present application.

[0055] Description of reference numerals:

[0056] 10- sling body; 101- bottom plate; 102- side beam; 103- connecting beam;

[0057] 11-arm holding mechanism; 111-first holding ring; 1111-locking seat; 1112-second holding ring ear seat; 112-second holding ring; 1121-first locking screw; 1122-first locking nut; 1123-first holding ring ear seat; 1124-holding ring rotating shaft;

[0058] 20-first hanging point structure assembly; 21-first sub-connection structure; 22-hanging ring shaft; 23-square nut;

[0059] 30-second suspension point structure assembly; 31-second sub-connection structure;

[0060] 40-tray; 41-first positioning member;

[0061] 50-rotatable mechanism; 51-rotating ear seat; 52-rotating shaft; 53-rotating ear piece;

[0062] 60-first sling assembly; 61-first sub-sling; 62-second sub-sling; 63-sling beam;

[0063] 70 - second sling assembly;

[0064] 80-first locking mechanism; 81-first support; 82-second support; 83-locking ring; 84-locking screw; 85-locking nut;

[0065] 200 - Launch vehicle. DETAILED DESCRIPTION

[0066] The present application is described in detail below, and examples of embodiments of the present application are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar components or components with the same or similar functions. In addition, if the detailed description of the known technology is unnecessary for the features of the present application shown, it will be omitted. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present application, and cannot be interpreted as limiting the present application.

[0067] It will be understood by those skilled in the art that, unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as those generally understood by those skilled in the art to which this application belongs. It should also be understood that terms such as those defined in general dictionaries should be understood to have meanings consistent with those in the context of the prior art, and will not be interpreted with idealized or overly formal meanings unless specifically defined as here.

[0068] Those skilled in the art will appreciate that, unless otherwise stated, the singular forms "a", "an", "said" and "the" used herein may also include plural forms. It should be further understood that the term "comprising" used in the specification of the present application refers to the presence of the features, integers, steps, operations, elements and / or components, but does not exclude the presence or addition of one or more other features, integers, steps, operations, elements, components and / or groups thereof. The term "and / or" used herein includes all or any unit and all combinations of one or more associated listed items.

[0069] The invention of this application has been studied and found that during the launch preparation process of a carrier rocket, after the carrier rocket in a horizontal state is transported from the technical area to the launch area, it is necessary to use an erection device or a hoist to transform the carrier rocket from a horizontal state to a vertical state. Due to the high cost and long development cycle of the erection device, it is difficult for commercial aerospace companies with high requirements for economy and development cycle to accept it. Therefore, commercial aerospace companies currently use hoists to flip the carrier rocket from a horizontal state to a vertical state.

[0070] However, in order to achieve the lifting and rotation of the carrier rocket, a connecting mechanism for cooperating with the lifting device needs to be set on the body of the carrier rocket. Setting the connecting mechanism will increase the weight of the carrier rocket itself, reduce the carrying capacity of the carrier rocket, and further increase the launch cost of the carrier rocket.

[0071] Moreover, after the carrier rocket is flipped from a horizontal state to a vertical state, the hoist needs to be evacuated from the launch area. During the evacuation of the hoist, the hoist is prone to collision with the carrier rocket, causing damage to the carrier rocket.

[0072] The lifting device of the launch vehicle and the lifting method thereof provided in the present application are intended to solve the above technical problems of the prior art.

[0073] The technical solution of the present application and how the technical solution of the present application solves the above-mentioned technical problems are described in detail below with specific embodiments.

[0074] The embodiment of the present application provides a lifting device for a launch vehicle, and the structural schematic diagram of the lifting device for a launch vehicle is shown in FIG. Figure 1 As shown, including:

[0075] The sling body 10 includes at least one arm holding mechanism 11, and the arm holding mechanism 11 is used to fix the carrier rocket 200 during the lifting process of the carrier rocket 200;

[0076] At least one first suspension point structure assembly 20 and at least one second suspension point structure assembly 30, the first suspension point structure assembly 20 and the second suspension point structure assembly 30 are both connected to the sling body 10;

[0077] The tray 40 is disposed at one end of the sling body 10 and is rotatably connected to the sling body 10 , and the tray 40 is connected to the launch vehicle 200 .

[0078] In the lifting device of the carrier rocket provided in the embodiment of the present application, the arm mechanism 11 fixes the carrier rocket 200 during the lifting process of the carrier rocket 200, and by controlling the height difference between the first lifting point structure assembly 20 and the second lifting point structure assembly 30, the sling body 10 can carry the carrier rocket 200 and flip to a vertical state. Compared with the lifting device in the prior art, the lifting device of the carrier rocket provided in the embodiment of the present application can avoid setting a connection mechanism for cooperating with the sling on the carrier rocket 200, and can reduce the weight of the carrier rocket 200 itself, thereby improving the carrying capacity of the carrier rocket 200 and reducing the launch cost of the carrier rocket 200.

[0079] During the lifting process of the launch vehicle 200, the tray 40 arranged at one end of the lifting device body 10 is connected to the launch vehicle 200, so as to support the launch vehicle 200 in the axial direction parallel to the launch vehicle 200, thereby ensuring the reliability of the connection between the launch vehicle 200 and the lifting device.

[0080] Moreover, since the tray 40 is rotatably connected to the hoist body 10, after the launch vehicle 200 is flipped to a vertical state, the arm mechanism 11 can be relatively away from the launch vehicle 200 by controlling the rotation of the hoist body 10 relative to the tray 40, so that in the process of evacuating and recovering the hoist body 10, collision between the hoist body 10 and the launch vehicle 200 can be avoided, thereby reducing the probability of damage to the launch vehicle 200 and improving the lifting efficiency of the launch vehicle 200.

[0081] In the present application embodiment, Figure 1 As shown, the hoist body 10 includes four arm mechanisms 11, and the four arm mechanisms 11 are arranged sequentially along the direction extending along the length of the hoist body 10. During the lifting process of the launch vehicle 200, the four arm mechanisms 11 all hold and fix the launch vehicle 200, thereby enhancing the reliability of the connection between the launch vehicle 200 and the lifting device.

[0082] The sling body 10 is also connected to a first sling point structure assembly 20 and a second sling point structure assembly 30. By controlling the height difference between the first sling point structure assembly 20 and the second sling point structure assembly 30, the sling body 10 can be controlled to rotate, so that the sling body 10 carrying the launch vehicle 200 can be turned to a vertical state. This can avoid setting a connection mechanism for cooperating with the sling on the launch vehicle 200, can reduce the weight of the launch vehicle itself, and thus can improve the carrying capacity of the launch vehicle 200.

[0083] Since a tray 40 is provided at one end of the sling body 10, the tray 40 plays a role of supporting the carrier rocket 200 during the lifting process of the carrier rocket 200, thereby further ensuring the reliability of the connection between the carrier rocket 200 and the lifting device. In the embodiment of the present application, the tray 40 is rotatably connected to the sling body 10, so that after the carrier rocket 200 is flipped from a horizontal state to a vertical state, by controlling the rotation of the sling body 10 relative to the tray 40, the sling body 10 and the carrier rocket 200 can be relatively far away, and in particular, the arm mechanism 11 can be relatively far away from the carrier rocket 200, so that in the process of evacuating and recovering the sling body 10, the sling body 10 and the carrier rocket 200 can be prevented from colliding, so that in the lifting process of the carrier rocket 200, the probability of damage to the carrier rocket 200 can be reduced, and the lifting efficiency of the carrier rocket 200 can be improved.

[0084] It should be noted that the number and arrangement of the arm-holding mechanisms 11 are not limited to Figure 1 In the scheme shown, those skilled in the art can set the number and arrangement of the arm-holding mechanisms 11 according to the actual requirements for lifting the launch vehicle 200. Similarly, those skilled in the art can set the number and arrangement of the first suspension point structure components 20 and the second suspension point structure components 30 according to actual needs.

[0085] In the present application embodiment, Figure 2 and Figure 3 As shown, the sling body 10 and the pallet 40 are connected through a rotatable mechanism 50, thereby realizing a rotatable connection between the pallet 40 and the sling body 10. The rotatable mechanism 50 includes a swivel ear seat 51, a swivel shaft 52 and a swivel ear piece 53, one end of the swivel ear seat 51 is connected to the pallet 40, one end of the swivel ear piece 53 is connected to the sling body 10, and the other end of the swivel ear piece 53 is located between the two ear pieces of the swivel ear seat 51 and is connected to the swivel ear seat 51 through the swivel shaft 52, thereby realizing a rotatable connection between the pallet 40 and the sling body 10. After the launch vehicle 200 is flipped from a horizontal state to a vertical state, and after the sling body 10 is controlled to rotate to a specified position relative to the pallet 40, the sling shaft 52 is removed to separate the sling ear 53 and the sling ear seat 51, so that the sling body 10 can be separated from the pallet 40. In the process of evacuating and recovering the sling body 10, the collision between the sling body 10 and the launch vehicle 200 can be further avoided, the probability of damage to the launch vehicle 200 can be further reduced, and the lifting efficiency of the launch vehicle 200 can be further improved.

[0086] It should be noted that those skilled in the art understand that the swivel ear seat 51 can be connected to the sling body 10 , and the swivel ear piece 53 can be connected to the pallet 40 , which can also achieve a rotatable connection between the pallet 40 and the sling body 10 .

[0087] In the embodiment of the present application, the lifting process of the carrier rocket 200 includes flipping the carrier rocket 200 from a horizontal state to a vertical state.

[0088] In one embodiment of the present application, the first suspension point structure assembly 20 is located at one end of the sling body 10 away from the pallet 40 and is rotatably connected to the sling body 10 , and the rotation plane of the first suspension point structure assembly 20 is parallel to the length extension direction of the sling body 10 .

[0089] Alternatively, if Figure 1 As shown, the first suspension point structure assembly 20 is located at one end of the sling body 10 away from the tray 40. Since the tail of the launch vehicle 200 is connected to the tray 40, and the tail of the launch vehicle 200 flipped to a vertical state faces the ground, it is necessary to set the first suspension point structure assembly 20 at one end of the sling body 10 away from the tray 40 to ensure that when the sling body 10 and the first suspension point structure assembly 20 rotate relative to each other, the end of the sling body 10 provided with the tray 40 will tend to move downward by utilizing the deadweight of the sling body 10, so that the sling body 10 drives the launch vehicle 200 to be in a vertical state after only 90° flipping from a horizontal state, thereby reducing the flipping difficulty of the launch vehicle 200, shortening the flipping time of the launch vehicle 200, and improving the lifting efficiency of the launch vehicle 200.

[0090] In the present application embodiment, Figure 1 As shown, the sling body 10 also includes a second suspension point structure assembly 30 located at one end of the sling body 10 near the tray 40, and the second suspension point structure assembly 30 is fixedly connected to the sling body 10. In the process of flipping the launch vehicle 200 from a horizontal state to a vertical state, by controlling the tension applied to the second suspension point structure assembly 30, the rotation speed of the sling body 10 relative to the first suspension point structure assembly 20 can be controlled, thereby ensuring the speed of flipping the launch vehicle 200 from a horizontal state to a vertical state, and also ensuring the stability of the lifting process of the launch vehicle 200, which can reduce the probability of damage to the launch vehicle 200. Those skilled in the art can set the number and arrangement of the second suspension point structure assembly 30 according to the actual requirements for lifting the launch vehicle 200.

[0091] Optionally, the tension applied to the second suspension point structure assembly 30 may be provided by equipment such as a crane or a hoisting vehicle.

[0092] It should be noted that, in the embodiment of the present application, the two ends of the sling body 10 refer to the two ends along the length extension direction of the sling body 10 .

[0093] In one embodiment of the present application, the first hanging point structure assembly 20 includes two relatively arranged first sub-hanging point structures 21; a first sub-hanging point structure 21 is arranged on both sides of the sling body 10, and the direction from one first sub-hanging point structure 21 to another first sub-hanging point structure 21 is perpendicular to the length extension direction of the sling body 10.

[0094] In the present application embodiment, combined Figure 4 and Figure 6 It can be seen that the first hanging point structure assembly 20 is located at one end of the sling body 10 away from the pallet 40, and a first sub-hanging point structure 21 is arranged on each side of the sling body 10. The two first sub-hanging point structures 21 are arranged opposite to each other, so that the direction from one first sub-hanging point structure 21 to another first sub-hanging point structure 21 is perpendicular to the length extension direction of the sling body 10, so that the sling body 10 can rotate with the line connecting the two first sub-hanging point structures 21 as the center axis, thereby ensuring the rotation of the sling body 10 relative to the first hanging point structure assembly 20.

[0095] The second suspension point structure assembly 30 includes two second sub-suspension point structures 31 arranged opposite to each other; a second sub-suspension point structure 31 is arranged on both sides of the sling body 10, and the direction from one second sub-suspension point structure 31 to another second sub-suspension point structure 31 is perpendicular to the length extension direction of the sling body 10.

[0096] In the present application embodiment, combined Figure 4 and Figure 6 It can be seen that the second hanging point structure assembly 30 is located at one end of the sling body 10 close to the pallet 40, and a second sub-hanging point structure 31 is arranged on each side of the sling body 10. The two second sub-hanging point structures 31 are arranged opposite to each other, so that the direction from one second sub-hanging point structure 31 to another second sub-hanging point structure 31 is perpendicular to the length extension direction of the sling body 10.

[0097] It should be noted that in the embodiment of the present application, the two sides of the sling body 10 refer to two side edges perpendicular to the length extension direction of the sling body 10 .

[0098] Alternatively, if Figure 7 As shown, the second sub-hanging point structure 31 is a bow-shaped shackle, and the second sub-hanging point structure 31 is fixedly connected to the sling body 10. Figure 8 As shown, the first sub-hanging point structure 21 is a lifting ring, one end of the first sub-hanging point structure 21 is movably connected to the lifting ring rotating shaft 22, one end of the lifting ring rotating shaft 22 is fixedly connected to the sling body 10, and the other end of the lifting ring rotating shaft 22 is provided with a square nut 23, so that the first sub-hanging point structure 21 is limited to prevent the first sub-hanging point structure 21 from being separated from the lifting ring rotating shaft 22.

[0099] It should be noted that those skilled in the art can select the second sub-hanging point structure 31 , the first sub-hanging point structure 21 and the square nut 23 of different structures according to actual needs.

[0100] In one embodiment of the present application, the lifting device of the launch vehicle also includes a first sling assembly 60 and a second sling assembly 70, the first sling assembly 60 is connected to the first sling point structure assembly 20, and the second sling assembly 70 is connected to the second sling point structure assembly 30.

[0101] In the present application embodiment, Figure 1 As shown, one end of the first sling assembly 60 is connected to the first suspension point structure assembly 20, and one end of the second sling assembly 70 is connected to the second suspension point structure assembly 30. The other end of the first sling assembly 60 can be connected to a crane, and the other end of the second sling assembly 70 can be connected to another crane. By controlling the tension applied by the crane to the first sling assembly 60 and the tension of the second sling assembly 70, the state of the sling body 10 can be controlled, so that the launch vehicle 200 can be controlled to flip from a horizontal state to a vertical state. Optionally, the other end of the first sling assembly 60 and the other end of the second sling assembly 70 can also be connected to a device that can provide tension, such as a crane. By setting the first sling assembly 60 and the second sling assembly 70, the sling body 10 and the launch vehicle 200 can be kept at a safe distance from equipment such as a crane and a crane, and the influence of equipment such as a crane and a crane on the lifting process of the launch vehicle 200 can be avoided.

[0102] Specifically, the first sling assembly 60 includes two first sub-slings 61, a second sub-sling 62 and a suspension beam 63. One end of one first sub-sling 61 is fixedly connected to a first sub-sling point structure 21 of the first suspension point structure assembly 20, one end of another first sub-sling 61 is fixedly connected to another first suspension point structure 21 of the first suspension point structure assembly 20, and the other ends of the two first sub-slings 61 are respectively connected to one end of a suspension beam 63, and the length of the suspension beam 63 is equal to the width of the sling body 10, so that the first sub-sling 61 can avoid interfering with the sling body 10 during the rotation of the sling body 10 relative to the first suspension point structure assembly 20. Both ends of the second sub-sling 62 are connected to the suspension beam 63, and the middle part of the second sub-sling 62 is directly connected to equipment such as a crane and a hoisting vehicle.

[0103] In the embodiment of the present application, one end of the second sling assembly 70 is fixedly connected to a second sub-sling point structure 31 of the second sling point structure assembly 30, and the other end of the second sling assembly 70 is fixedly connected to another second sub-sling point structure 31 of the second sling point structure assembly 30. The middle part of the second sling assembly 70 is directly connected to a crane, a hoisting vehicle, etc. By controlling the tension applied by the crane to the second sling assembly 70, the state of the sling body 10 can be controlled, so that the launch vehicle 200 can be controlled to flip from a horizontal state to a vertical state.

[0104] Optionally, in an embodiment of the present application, when the launch vehicle 200 is in a horizontal state, that is, when the sling body 10 is in a horizontal state, the distance between the second suspension point structure assembly 30 and the ground is greater than the distance between the first suspension point structure assembly 20 and the ground, thereby avoiding interference between the first sling assembly 60 and the second sling assembly 70 during the process of flipping the launch vehicle 200 from a horizontal state to a vertical state.

[0105] In one embodiment of the present application, the lifting device of the launch vehicle also includes a first locking mechanism 80, which is fixedly connected to one of the pallet 40 and the sling body 10, and locks the other one of the pallet 40 and the sling body 10 when the launch vehicle 200 is in the lifting process.

[0106] In the present application embodiment, Figure 2 and Fig.10 As shown, the lifting device of the launch vehicle also includes a first locking mechanism 80. The first locking mechanism 80 includes a first support 81, a second support 82, a locking ring 83, a locking screw 84 and a locking nut 85. The first support 81 is connected to the pallet 40, and the second support 82 is connected to the sling body 10. The first support 81 includes two ears, and the second support 82 includes one ear. When the first locking mechanism 80 is in a locked state, the ear of the second support 82 is inserted between the two ears of the first support 81, and the locking ring 83 surrounds at least part of the ear of the first support 81 and at least part of the ear of the second support 82. The locking screw 84 and the locking nut 85 cooperate to achieve the locking of the locking ring 83, thereby locking the first support 81 and the second support 82, and then achieving the locked connection between the pallet 40 and the sling body 10.

[0107] It is understood by those skilled in the art that the first support 81 can be connected to the sling body 10 , and the second support 82 can be connected to the pallet 40 , so that a locking connection between the pallet 40 and the sling body 10 can also be achieved.

[0108] In one embodiment of the present application, the tray 40 is provided with a first positioning member 41, and the first positioning member 41 matches with the second positioning member of the launch pad. When the carrier rocket is in a vertical state, the first positioning member 41 is aligned and connected with the second positioning member.

[0109] In the present application embodiment, Figure 1 and Figure 2 As shown, the pallet 40 is provided with a first positioning member 41. Optionally, in order to improve the alignment accuracy between the pallet 40 and the launch pad, a plurality of first positioning members 41 are provided on the pallet 20. The first positioning member 41 matches with the second positioning member of the launch pad, so that when the pallet 40 is docked with the launch pad, the first positioning member 41 is aligned and connected with the second positioning member, so that the pallet 40 is docked with the launch pad, and then the carrier rocket 200 is docked with the launch pad.

[0110] In the embodiment of the present application, the indirect docking of the launch vehicle 200 and the launch pad can be achieved by directly docking the tray 40 with the launch pad. Compared with the solution of directly docking the launch vehicle 200 with the launch pad in the prior art, it is possible to avoid collision between the launch vehicle 200 and the launch pad, thereby ensuring the lifting efficiency of the launch vehicle 200.

[0111] At the same time, during the direct docking process between the pallet 40 and the launch pad, the setting of the matching first positioning member 41 and the second positioning member can reduce the requirements for the operator, shorten the direct docking time between the pallet 20 and the launch pad, and further improve the lifting efficiency of the carrier rocket 200.

[0112] In one embodiment of the present application, the arm mechanism 11 includes a first holding ring 111 and a second holding ring 112 which are arranged opposite to each other. The first holding ring 111 is fixedly connected to the sling body 10, one end of the second holding ring 112 is rotatably connected to one end of the first holding ring 111, and the other end of the second holding ring 112 is detachably connected to the other end of the first holding ring 111.

[0113] In the present application embodiment, Figure 4 and Figure 6As shown, the arm-holding mechanism 11 includes a first holding ring 111 and a second holding ring 112 which are arranged opposite to each other. The first holding ring 111 is fixedly connected to the sling body 10 and is used to support the carrier rocket 200 when the loaded carrier rocket 200 is in a horizontal state. One end of the second holding ring 112 is rotatably connected to one end of the first holding ring 111, and the other end of the second holding ring 112 is detachably connected to the other end of the first holding ring 111. When the arm-holding mechanism 11 is in a locked state, the other end of the second holding ring 112 is connected to the other end of the first holding ring 111, so that the first holding ring 111 and the second holding ring 112 are in an embracing state, so that the first holding ring 111 and the second holding ring 112 can fix the carrier rocket 200. When the arm mechanism 11 is in the unlocked state, the other end of the second ring 112 can be separated from the other end of the first ring 111. Since one end of the second ring 112 is rotatably connected to one end of the first ring 111, the first ring 111 and the second ring 112 can be in the open state, so that the arm mechanism 11 releases the launch vehicle 200.

[0114] Alternatively, if Figure 5 As shown, the other end of the second embrace ring 112 is connected to the locking seat 1111 disposed on the other end of the first embrace ring 111 through the first locking screw 1121 and the first locking nut 1122. By disassembling the first locking screw 1121 and the first locking nut 1122, the other end of the second embrace ring 112 can be separated from the other end of the first embrace ring 111. Fig. 9 As shown, one end of the second ring 112 is connected to the first ring ear seat 1123, one end of the first ring 111 is connected to the second ring ear seat 1112, and the first ring ear seat 1123 and the second ring ear seat 1112 are connected through the ring rotating shaft 1124, so that one end of the second ring 112 is rotatably connected to one end of the first ring 111.

[0115] In the embodiment of the present application, a layer of flexible material such as rubber or sponge may be provided on the side where the first holding ring 111 and the second holding ring 112 are in contact with the launch vehicle 200. This can prevent the first holding ring 111 and the second holding ring 112 from wearing the outer shell of the launch vehicle 200, and can also increase the friction between the first holding ring 111 and the second holding ring 112 and the launch vehicle 200, thereby enhancing the connection strength between the arm mechanism 11 and the launch vehicle 200 and ensuring the connection stability between the arm mechanism 11 and the launch vehicle 200.

[0116] In one embodiment of the present application, the sling body 10 includes a bottom plate 101 and at least two side beams 102 . The side beams 102 are connected to the bottom plate 101 . At least one side beam 102 is disposed on two opposite sides of the bottom plate 101 .

[0117] In the present application embodiment, Figure 4 and Figure 6As shown, the sling body 10 includes a bottom plate 101, and a side beam 102 is disposed on two opposite sides of the bottom plate 101, and the side beam 102 and the bottom plate 101 can be connected by a connecting beam 103. In the embodiment of the present application, the side beams 102 are disposed on two opposite sides of the bottom plate 101, which can reduce the weight of the sling body 10 while ensuring the structural strength of the sling body 10, thereby reducing the power requirements of equipment such as cranes and hoisting vehicles.

[0118] In the embodiment of the present application, the tray 40 is rotatably connected to the bottom plate 101, and the rotation plane of the tray 40 is perpendicular to the bottom plate 101. The first suspension point structure assembly 20 and the second suspension point structure assembly 30 are both connected to the side beam 102. Specifically, the side beams 102 on two opposite sides of the bottom plate 101 are each provided with a first sub-suspension point structure 21, so that the direction from one first sub-suspension point structure 21 to another first sub-suspension point structure 21 is perpendicular to the length extension direction of the sling body 10; the side beams 102 on two opposite sides of the bottom plate 101 are each provided with a second sub-suspension point structure 31, so that the direction from one second sub-suspension point structure 31 to another second sub-suspension point structure 31 is perpendicular to the length extension direction of the sling body 10.

[0119] Based on the same inventive concept, an embodiment of the present application provides a lifting method for a lifting device of a launch vehicle based on the above embodiments, including:

[0120] S1101, connecting the carrier rocket loaded in the hoist body of the hoisting device to the tray of the hoisting device, and locking the carrier rocket in an openable and closable manner using at least one arm mechanism of the hoist body.

[0121] Optionally, the arm mechanism 11 of the sling body 10 is in an unlocked state, and the launch vehicle 200 is loaded on the sling body 10 of the lifting device, so as to obtain Fig.12 The loading schematic diagram shown in FIG. 2 shows a loading schematic diagram; the launch vehicle 200 loaded in the sling body 10 of the lifting device is connected to the tray 40 of the lifting device, and the launch vehicle 200 is locked in an openable and closable manner by using at least one arm mechanism 11 of the sling body 10, thereby obtaining a Fig.13 During the lifting process of the launch vehicle 200 , the arm mechanism 11 fixes the launch vehicle 200 in the radial direction and the circumferential direction of the launch vehicle 200 , and the tray 40 supports and fixes the launch vehicle 200 in the circumferential direction parallel to the launch vehicle 200 .

[0122] S1102, connecting the lifting equipment to at least one first lifting point structure assembly and at least one second lifting point structure assembly, lifting the lifting device body loaded with and locking the launch vehicle; each first lifting point structure assembly and each second lifting point structure assembly are connected to the lifting device body.

[0123] Optionally, since each first lifting point structure assembly 20 and each second lifting point structure assembly 30 are connected to the sling body 10, the lifting equipment is connected to at least one first lifting point structure assembly 20 and at least one second lifting point structure assembly 30 to lift, load and lock the sling body 10 with the launch vehicle 200.

[0124] In the embodiments of the present application, the lifting equipment includes cranes, hoisting vehicles and other equipment.

[0125] S1103, by controlling the height difference between the first suspension point structure assembly and the second suspension point structure assembly, the sling body carrying the carrier rocket is flipped to a vertical state.

[0126] Optionally, by applying tension to the first suspension point structure assembly 20 and the second suspension point structure assembly 30 through a lifting device, the height difference between the first suspension point structure assembly 20 and the second suspension point structure assembly 30 is controlled, so that the sling body 10 rotates relative to the first suspension point structure assembly 20, thereby causing the sling body 10 carrying the launch vehicle 200 to flip from a horizontal state to a vertical state.

[0127] In one embodiment of the present application, the above step S1103 includes:

[0128] The height of the second suspension point structure assembly 30 is controlled to be gradually lower than the height of the first suspension point structure assembly 20 until the sling body 10 is in a vertical state; the first suspension point structure assembly 20 is located on a side of the second suspension point structure assembly 30 away from the pallet 40 .

[0129] Alternatively, if Fig.14 As shown, the first sling first sling assembly 20 and the second sling second sling assembly 30 are pulled up by a crane, a hoisting vehicle or other equipment, so that the sling body 10 is in a horizontal state, and the launch vehicle 200 carried by the sling body 10 is in a horizontal state.

[0130] When the sling body 10 is in a horizontal state, the sling body 10 is hoisted to the launch platform, and the distance between the sling body 10 and the launch platform meets the design value. Optionally, the design value between the sling body 10 and the launch platform is greater than the length of the sling body 10 to ensure the rotation of the sling body 10 and avoid interference of the launch platform with the sling body 10.

[0131] like Fig.15 As shown, the lifting equipment applies a pulling force to the first lifting point structure assembly 20 and the second lifting point structure assembly 30, so that the sling body 10 rotates relative to the first lifting point structure assembly 20, that is, the height of the second lifting point structure assembly 30 gradually becomes lower than the height of the first lifting point structure assembly 20, until the sling body 10 is in a vertical state, so that the sling body 10 carrying the launch vehicle 200 is flipped from a horizontal state to a vertical state, as shown in FIG. Fig.16 shown.

[0132] In one embodiment of the present application, after the above step S1103, the method further includes:

[0133] The arm mechanism 11 locking the launch vehicle 200 is opened. Optionally, one end of the second holding ring 112 of the arm mechanism 11 is separated from one end of the first holding ring 111, so that the arm mechanism 11 is in an open state, so that the arm mechanism 11 releases the launch vehicle 200.

[0134] Unlock the first locking mechanism 80 in the locked state. Optionally, the screw 84 and the locking nut 85 of the first locking mechanism 80 cooperate to extend the locking ring 83, thereby separating the first support 81 and the second support 82, and then unlocking the pallet 40 and the sling body 10.

[0135] The height of the first suspension point structure assembly 20 is controlled to gradually decrease until the sling body 10 is in a horizontal state. Optionally, a lifting device is used to apply a pulling force to the first suspension point structure assembly 20, so that the height of the first suspension point structure assembly 20 is gradually reduced until the sling body 10 is in a horizontal state, such as Fig.17 shown.

[0136] The tray 40 is disassembled so that the tray 40 is separated from the sling body 10. Optionally, the rotating shaft 52 of the rotatable mechanism 50 is removed so that the rotating ear piece 53 and the rotating ear seat 51 are separated, so that the sling body 10 is separated from the tray 40, so that in the process of evacuating and recovering the sling body 10, the collision between the sling body 10 and the launch vehicle 200 can be further avoided, the probability of damage to the launch vehicle 200 can be further reduced, and the lifting efficiency of the launch vehicle 200 can be further improved.

[0137] The first lifting point structure assembly 30 is controlled to drive the sling body 10 away from the pallet 40, so that the sling body 10 is away from the launch platform. Optionally, the first lifting point structure assembly 30 is driven to move by a lifting device, so that the first lifting point structure assembly 30 drives the sling body 10 away from the pallet 40, so that the sling body 10 is away from the launch platform.

[0138] By applying the embodiments of the present application, at least the following beneficial effects can be achieved:

[0139] In the lifting device of the carrier rocket provided in the embodiment of the present application, the arm mechanism 11 fixes the carrier rocket 200 during the lifting process of the carrier rocket 200, and by controlling the height difference between the first lifting point structure assembly 20 and the second lifting point structure assembly 30, the sling body 10 can carry the carrier rocket 200 and flip to a vertical state. Compared with the lifting device in the prior art, the lifting device of the carrier rocket provided in the embodiment of the present application can avoid setting a connection mechanism for cooperating with the sling on the carrier rocket 200, and can reduce the weight of the carrier rocket 200 itself, thereby improving the carrying capacity of the carrier rocket 200 and reducing the launch cost of the carrier rocket 200.

[0140] During the lifting process of the launch vehicle 200, the tray 40 arranged at one end of the lifting device body 10 is connected to the launch vehicle 200, so as to support the launch vehicle 200 in the axial direction parallel to the launch vehicle 200, thereby ensuring the reliability of the connection between the launch vehicle 200 and the lifting device.

[0141] Moreover, since the tray 40 is rotatably connected to the hoist body 10, after the launch vehicle 200 is flipped to a vertical state, the arm mechanism 11 can be relatively away from the launch vehicle 200 by controlling the rotation of the hoist body 10 relative to the tray 40, so that in the process of evacuating and recovering the hoist body 10, collision between the hoist body 10 and the launch vehicle 200 can be avoided, thereby reducing the probability of damage to the launch vehicle 200 and improving the lifting efficiency of the launch vehicle 200.

[0142] In the embodiment of the present application, the indirect docking of the launch vehicle 200 and the launch pad can be achieved by directly docking the tray 40 with the launch pad. Compared with the solution of directly docking the launch vehicle 200 with the launch pad in the prior art, it is possible to avoid collision between the launch vehicle 200 and the launch pad, thereby ensuring the lifting efficiency of the launch vehicle 200.

[0143] Those skilled in the art will appreciate that the various operations, methods, steps, measures, and schemes in the processes discussed in this application may be alternated, altered, combined, or deleted. Further, other steps, measures, and schemes in the various operations, methods, and processes discussed in this application may also be alternated, altered, rearranged, decomposed, combined, or deleted. Further, the steps, measures, and schemes in the prior art that are similar to those disclosed in this application may also be alternated, altered, rearranged, decomposed, combined, or deleted.

[0144] In the description of the present application, it should be understood that the terms "center", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply 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 understood as a limitation on the present application.

[0145] The terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of this application, unless otherwise specified, "plurality" means two or more.

[0146] In the description of this application, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0147] It should be understood that, although the steps in the flowchart of the accompanying drawings are displayed in sequence as indicated by the arrows, these steps are not necessarily executed in sequence in the order indicated by the arrows. Unless otherwise specified herein, there is no strict order restriction on the execution of these steps, and they can be executed in other orders. Moreover, at least a part of the steps in the flowchart of the accompanying drawings may include multiple sub-steps or multiple stages, and these sub-steps or stages are not necessarily executed at the same time, but can be executed at different times, and their execution order is not necessarily sequential, but can be executed in turn or alternately with other steps or at least a part of the sub-steps or stages of other steps.

[0148] In the description of this specification, specific features, structures, materials or characteristics may be combined in an appropriate manner in any one or more embodiments or examples.

[0149] The above description is only a partial implementation method of the present application. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principles of the present application. These improvements and modifications should also be regarded as the scope of protection of the present application.

Claims

1. A lifting device for a launch vehicle, characterized in that: include: A sling body, the sling body comprising a bottom plate, at least two side beams and at least one arm mechanism, the arm mechanism being used to fix the carrier rocket during the lifting process of the carrier rocket, the side beams being connected to the bottom plate, and at least one side beam being disposed on two opposite sides of the bottom plate; at least one first suspension point structure component and at least one second suspension point structure component, wherein the first suspension point structure component and the second suspension point structure component are both connected to the sling body; A tray is provided at one end of the sling body, rotatably connected to the sling body, and connected to the carrier rocket. The tray is rotatably connected to the base plate, and the rotation plane of the tray is perpendicular to the base plate. The tray is provided with a first positioning member, and the first positioning member matches the second positioning member of the launch pad. When the carrier rocket is in a vertical state, the first positioning member is aligned with the second positioning member. After the launch vehicle is flipped to a vertical state, the arm mechanism can be moved relatively away from the launch vehicle by controlling the rotation of the sling body relative to the pallet.

2. The lifting device of a launch vehicle according to claim 1, characterized in that: The first suspension point structure component is located at one end of the sling body away from the pallet and is rotatably connected to the sling body, and the rotation plane of the first suspension point structure component is parallel to the length extension direction of the sling body; The second lifting point structure component is located at one end of the lifting device body close to the pallet.

3. The lifting device of a launch vehicle according to claim 2, characterized in that: The first suspension point structure assembly includes two first sub-suspension point structures arranged opposite to each other; one first sub-suspension point structure is arranged on both sides of the sling body, and the direction from one first sub-suspension point structure to the other first sub-suspension point structure is perpendicular to the length extension direction of the sling body; The second hanging point structure assembly includes two second sub-hanging point structures arranged opposite to each other; a second sub-hanging point structure is arranged on both sides of the sling body, and the direction from one second sub-hanging point structure to another second sub-hanging point structure is perpendicular to the length extension direction of the sling body.

4. The lifting device for a launch vehicle according to claim 2, characterized in that: It also includes a first sling assembly and a second sling assembly, wherein the first sling assembly is connected to the first suspension point structure assembly, and the second sling assembly is connected to the second suspension point structure assembly.

5. The lifting device for a launch vehicle according to claim 1, characterized in that: It also includes a first locking mechanism, which is fixedly connected to one of the pallet and the sling body, and locks the pallet and the other of the sling bodies during the lifting process of the launch vehicle.

6. The lifting device for a launch vehicle according to claim 1, characterized in that: The arm-holding mechanism includes a first holding ring and a second holding ring which are arranged opposite to each other. The first holding ring is fixedly connected to the sling body, one end of the second holding ring is rotatably connected to one end of the first holding ring, and the other end of the second holding ring is detachably connected to the other end of the first holding ring.

7. A lifting method based on the lifting device of the launch vehicle according to any one of claims 1 to 6, characterized in that: include: Connecting a carrier rocket loaded in a sling body of a lifting device to a tray of the lifting device, and locking the carrier rocket in an openable and closable manner by using at least one arm holding mechanism of the sling body; Connecting the lifting device to at least one first lifting point structural component and at least one second lifting point structural component to lift the lifting device body loaded with and locked with the launch vehicle; each first lifting point structural component and each second lifting point structural component are connected to the lifting device body; By controlling the height difference between the first suspension point structure assembly and the second suspension point structure assembly, the sling body carrying the carrier rocket is flipped to a vertical state.

8. The lifting method according to claim 7, characterized in that: The method of controlling the height difference between the first suspension point structure assembly and the second suspension point structure assembly so that the sling body carrying the carrier rocket flips to a vertical state comprises: Controlling the height of the second suspension point structure assembly to be gradually lower than the height of the first suspension point structure assembly until the sling body is in a vertical state; The first suspension point structure component is located on a side of the second suspension point structure component away from the pallet.

9. The lifting method according to claim 8, characterized in that: After the height difference between the first suspension point structure assembly and the second suspension point structure assembly is controlled so that the sling body carrying the carrier rocket is turned over to a vertical state, the method further includes: Opening the arm mechanism that locks the launch vehicle; unlocking the first locking mechanism in a locked state; Controlling the height of the first suspension point structure assembly to gradually decrease until the sling body is in a horizontal state; Disassembling the pallet so that the pallet is separated from the spreader body; The first suspension point structure assembly is controlled to drive the suspension device body away from the pallet, so that the suspension device body is away from the launching platform.

Images