Transfer box for carrier rocket power device

Abstract

The invention relates to the technical field of power device transfer, in particular to a carrier rocket power device transfer box which is characterized in that a box body upper cover is in lap joint with a bracket, connecting pieces are fixedly mounted on the box body upper cover and the bracket, the box body upper cover and the bracket are connected through the two sets of connecting pieces, and an arc-shaped bracket is slidably connected to the bracket; the arc-shaped bracket is used for bearing a carrier rocket power device, and the hoop assembly is installed on the arc-shaped bracket and used for sleeving and fixing the carrier rocket power device. According to the technical scheme, multiple sets of damping and buffering mechanisms are arranged, the situation that in the transfer process, due to improper protection of the carrier rocket power device, a shell or a spray pipe or other components are collided is avoided, meanwhile, the sealing performance in the transfer process is guaranteed, and the carrier rocket power device is prevented from being affected with damp in the transfer process.

Description

Technical Field

[0001] The present invention relates to the technical field of power unit transportation, in particular to a carrier rocket power unit transportation box. Background Art

[0002] The production process for the power plant of a conventional launch vehicle generally includes the production of non-pyrotechnic components, combustion chamber charge, and power plant assembly. Each production link cannot be located within a single factory building and requires multiple transfers. For example, after the combustion chamber shell is completed, it must remain stationary for a certain period of time for stress relief. The combustion chamber shell, combustion chamber, and power plant all need to be transferred and positioned before and after combustion chamber charge, and before and after combustion chamber assembly. Using a general-purpose placement and transfer arc rack or bracket requires frequent lifting, increasing safety risks and making it difficult to maintain a specific temperature and humidity.

[0003] Therefore, how to ensure the safety of the launch vehicle power unit during transportation and avoid bumps and moisture has become a technical problem that needs to be urgently solved by technical personnel in this field. Summary of the Invention

[0004] The invention provides a carrier rocket power unit transfer box, which is used to solve the problem of how to prevent the carrier rocket power unit from being bumped and damp during transportation.

[0005] The present invention provides a carrier rocket power unit transfer box, comprising: Box cover; Bracket, the upper cover of the box body is overlapped on the bracket; Connectors: The upper cover of the box and the bracket are both fixedly mounted with connectors, and the upper cover of the box and the bracket are connected by two sets of connectors; An arc-shaped bracket, slidably connected to the bracket, is used to carry the launch vehicle power unit; The clamp assembly is installed on the arc-shaped bracket and is used to fit and fix the launch vehicle power unit.

[0006] In some embodiments, the connector includes: The first U-shaped connecting piece is fixedly mounted on the upper cover of the box; The second U-shaped connecting piece is fixedly mounted on the bracket, and the lower bottom surface of the first U-shaped connecting piece abuts against the upper top surface of the second U-shaped connecting piece and is connected by bolts.

[0007] In some embodiments, the clamp assembly includes: The outer arc-shaped clamp is detachably connected to the arc-shaped bracket; The inner arc-shaped clamp is connected to the inner ring of the outer arc-shaped clamp through a radial shock-absorbing component and is used to support the launch vehicle power unit.

[0008] In some embodiments, the outer arc-shaped clamp comprises: The outer arc-shaped upper clamp is connected to the top of the arc-shaped bracket; The outer ring arc-shaped lower clamp is installed on the arc-shaped part of the arc-shaped bracket.

[0009] In some embodiments, the inner arc clamp comprises: The inner arc-shaped upper clamp is connected to the inner ring of the outer arc-shaped upper clamp through a radial shock-absorbing component; The inner arc-shaped lower clamp is connected to the inner ring of the outer arc-shaped lower clamp through a radial shock-absorbing component.

[0010] In some embodiments, the radial damping assembly includes: A first hydraulic telescopic rod, wherein the inner surface of the outer arc-shaped clamp is provided with a rectangular groove, and one end of the first hydraulic telescopic rod is fixedly mounted inside the rectangular groove; A connecting block, fixedly mounted on the other end of the first hydraulic telescopic rod; a first threaded spring, sleeved on the first hydraulic telescopic rod, with one end abutting against the inner wall of the rectangular groove and the other end abutting against the connecting block; One end of the spring sheet is connected to the connecting block, and the other end is connected to the outer ring surface of the inner ring arc clamp.

[0011] In some embodiments, the outer arc-shaped clamp is further threadedly connected to a radial shock-absorbing locking piece, and one end of the radial shock-absorbing locking piece passes through the outer arc-shaped clamp and abuts against the inner arc-shaped clamp.

[0012] In some embodiments, two groups of arc-shaped brackets are provided, and axial buffers are provided on the arc-shaped brackets, and the axial buffers include: a second hydraulic telescopic rod, one end of which is connected to the side wall of a set of arc-shaped brackets, and the other end of which is connected to the inner wall of the bracket; A second threaded spring is sleeved on the second hydraulic telescopic rod, and one end of the second threaded spring abuts against the side wall of the set of arc-shaped brackets, and the other end abuts against the inner wall of the bracket; The support rod is fixedly connected between the two sets of arc-shaped brackets.

[0013] In some embodiments, a bracket shock absorbing assembly is installed at the bottom of the bracket, and the bracket shock absorbing assembly includes: The longitudinal support beam has a T-slot at the bottom of the bracket, and the longitudinal support beam is plugged into the bottom of the bracket through the T-slot; a third hydraulic telescopic rod, one end of which is rotatably connected to the upper portion of the longitudinal support beam; There are two sets of gaskets, which are respectively sleeved on both ends of the third hydraulic telescopic rod; a third threaded spring, sleeved on the third hydraulic telescopic rod, with both ends of the spring abutting against washers on the third hydraulic telescopic rod; The top end of the column is rotatably connected to the other end of the third hydraulic telescopic rod; A first limiting rod, one end of which is rotatably connected to the bottom of the longitudinal support beam and the other end of which is rotatably connected to the middle of the column; A second limiting rod, one end of which is rotatably connected to the bottom of the longitudinal support beam and the other end of which is rotatably connected to the middle of the column, and the lengths of the first limiting rod and the second limiting rod are both less than the minimum length of the third hydraulic telescopic rod; Base plate, installed at the bottom of the column.

[0014] In some embodiments, a sealing mechanism is provided on the top edge of the bracket.

[0015] The beneficial effects of the present invention are as follows: When a carrier rocket power unit transfer box of the present invention is in use, the carrier rocket power unit is hoisted onto the inner circle arc-shaped lower clamp, and then the outer circle arc-shaped upper clamp is covered thereon, so that the inner surface of the inner circle arc-shaped upper clamp is in contact with the surface of the carrier rocket power unit, and the outer circle arc-shaped upper clamp is connected to the top of the arc-shaped bracket by bolts, and then the box cover is placed on the bracket to complete the seal to prevent the carrier rocket power unit from getting wet, and the assembled transfer box is hoisted onto the carrier for transportation. During the transportation process, the transfer box will be vibrated by external forces. The transfer box in the present invention first uses the bracket shock-absorbing assembly at the bottom of the bracket to dampen the entire transfer box to prevent the transfer box from vibrating too much, causing the carrier rocket power unit to vibrate. The present invention prevents the axial ends of the carrier rocket power unit from colliding with the inner wall of the transfer box by arranging axial buffer parts. The technical solution of the present invention avoids the collision of the shell or nozzle and other components of the carrier rocket power unit due to improper protection during the transfer process by arranging multiple groups of shock absorbing and buffering mechanisms. At the same time, the sealing performance during the transfer process is guaranteed, and the carrier rocket power unit is prevented from getting damp during the transfer process. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 This is a structural schematic diagram of a carrier rocket power unit transfer box from one perspective of the present invention; Figure 2 yes Figure 1 The schematic diagram of the structure of the upper cover of the case in a carrier rocket power unit transfer case is shown; Figure 3 yes Figure 1 A schematic structural diagram of a carrier rocket power unit transfer box from one perspective is shown; Figure 4 yes Figure 1 A schematic structural diagram of a bracket in a carrier rocket power unit transfer box from another perspective is shown; Figure 5 yes Figure 1 A schematic structural diagram of a carrier rocket power unit transfer box from another perspective is shown; Figure 6 yes Figure 1 A schematic diagram of a carrier rocket power unit transfer box carrying a power unit is shown; Figure 7 yes Figure 1 A schematic structural diagram of a clamp assembly in a carrier rocket power unit transfer box is shown; Figure 8 yes Figure 1 The figure shows a schematic structural diagram of a radial shock absorbing assembly in a transfer box of a carrier rocket power unit.

[0017] Figure 9 yes Figure 1 The figure shows a schematic structural diagram of a spring sheet in a transfer box of a carrier rocket power unit.

[0018] Figure 10 yes Figure 1 The figure shows a schematic structural diagram of a bracket shock-absorbing assembly in a transfer box of a carrier rocket power unit.

[0019] Figure 11 yes Figure 1 The figure shows a schematic structural diagram of a felt A in a transfer box of a carrier rocket power unit.

[0020] In the accompanying drawings, 1. Box cover; 2. Bracket; 3. Connector; 31. First U-shaped connector; 32. Second U-shaped connector; 4. Arc-shaped bracket; 5. Outer arc-shaped clamp; 51. Outer arc-shaped upper clamp; 52. Outer arc-shaped lower clamp; 6. Inner arc-shaped clamp; 61. Inner arc-shaped upper clamp; 62. Inner arc-shaped lower clamp; 7. Radial shock-absorbing assembly; 71. First hydraulic telescopic rod; 72. Connecting block; 73. First threaded spring; 74. Spring sheet; 8. Radial shock-absorbing lock Parts; 9. Axial buffer; 91. Second hydraulic telescopic rod; 92. Second threaded spring; 93. Support rod; 10. Bracket shock absorption assembly; 101. Longitudinal support beam; 102. Third hydraulic telescopic rod; 103. Gasket; 104. Third threaded spring; 105. Column; 106. First limiting rod; 107. Second limiting rod; 108. Bottom plate; 11. Sealing mechanism; 111. Silicone sealing strip A; 112. Silicone sealing strip B; 12. Felt A; 13. Felt B. DETAILED DESCRIPTION

[0021] The following will clearly and completely describe the technical solutions of the present invention in conjunction with the embodiments. Obviously, the embodiments described are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0022] As mentioned in the background, transporting launch vehicle propulsion systems often occurs outdoors. Improper protection can lead to collisions with components such as the housing and nozzle, causing damage. Moisture or water exposure during combustion, before or after charge loading, can also render the propulsion system useless or hinder production. Therefore, preventing collisions and moisture from occurring during transport of launch vehicle propulsion systems has become a pressing technical challenge for those skilled in the art.

[0023] To solve the above problems, refer to Figure 1 、 Figure 2 、 Figure 3 、 Figure 4 、 Figure 5 、 Figure 6 、 Figure 7 、 Figure 8 、 Figure 9 、 Figure 10 and Figure 11 The present invention provides a carrier rocket power unit transfer box, including a box cover 1, a bracket 2, a connector 3, an arc-shaped bracket 4 and a clamp assembly. The box cover 1 is overlapped on the bracket 2, and the box cover 1 and the bracket 2 are fixedly installed with connectors 3, and the box cover 1 and the bracket 2 are connected by two groups of connectors 3. The arc-shaped bracket 4 is slidably connected to the bracket 2 for carrying the carrier rocket power unit, and the clamp assembly is installed on the arc-shaped bracket 4 for sleeve-fixing the carrier rocket power unit.

[0024] In one embodiment, the clamp assemblies of the present invention can be provided in multiple groups, and are symmetrical along the horizontal center of gravity of the launch vehicle power unit, ensuring that the force on each group of clamp assemblies is the same, thereby ensuring that the launch vehicle power unit can maintain a horizontal state inside the transfer box. The number of arc-shaped brackets 4 is the same as the number of clamp assemblies, and each group of arc-shaped brackets 4 includes two groups. The two groups of arc-shaped brackets 4 are symmetrical about the longitudinal section of the launch vehicle power unit, so that the clamp assemblies are subjected to balanced force in all directions, will not slide, and are easy to lift.

[0025] Preferably, the connector 3 includes: a first U-shaped connector 31 and a second U-shaped connector 32, the first U-shaped connector 31 is fixedly mounted on the upper cover 1 of the box body, the second U-shaped connector 32 is fixedly mounted on the bracket 2, and the lower bottom surface of the first U-shaped connector 31 abuts against the upper top surface of the second U-shaped connector 32 and is connected by bolts.

[0026] In another embodiment, the first U-shaped connector 31 and the second U-shaped connector 32 can also be set as a plug-in structure, that is, a groove is opened at the abutting end of the first U-shaped connector 31 and the second U-shaped connector 32, and the second U-shaped connector 32 is provided with a fixing block corresponding to the groove at the abutting end. When the box cover 1 is installed, the fixing block is removed into the groove, and then the first U-shaped connector 31 and the second U-shaped connector 32 are fastened by bolts passing through the groove and the fixing block. This design can effectively protect the bolts. When the transfer box is subjected to horizontal force, it slides and causes the bolts to deform.

[0027] Furthermore, in another preferred embodiment, a plurality of grooves evenly arranged horizontally can be provided at the abutting ends of the first U-shaped connector 31 and the second U-shaped connector 32, and the second U-shaped connector 32 is provided with a plurality of fixed blocks corresponding to the grooves at the abutting end, so that when the transfer box is subjected to horizontal force, the force-bearing area of ​​the fixed blocks and the grooves is increased, and stress can be released quickly.

[0028] Preferably, the clamp assembly includes: an outer ring arc clamp 5 and an inner ring arc clamp 6, the outer ring arc clamp 5 is detachably connected to the arc bracket 4, and the inner ring arc clamp 6 is connected to the inner ring of the outer ring arc clamp 5 through a radial shock absorbing assembly 7, and is used to support the launch vehicle power unit.

[0029] Preferably, the outer arc-shaped clamp 5 includes: an outer arc-shaped upper clamp 51 and an outer arc-shaped lower clamp 52 , the outer arc-shaped upper clamp 51 is connected to the top of the arc-shaped bracket 4 , and the outer arc-shaped lower clamp 52 is installed on the arc-shaped part of the arc-shaped bracket 4 .

[0030] Specifically, support plates are installed at both ends of the outer ring arc-shaped upper clamp 51, and the support plates are fixed to the top of the arc-shaped bracket 4 by bolts. The nuts used can be butterfly nuts or fastening nuts. In order to improve the fixing effect and avoid loosening, double nuts and gaskets can also be used for tightening.

[0031] In another embodiment, a groove can be further provided on the outer surface of the arc-shaped bracket 4, and an L-shaped fastener can be provided, one end of which is locked on the outer surface of the arc-shaped bracket 4 and the other end is locked on the support plate, thereby fixing the outer arc-shaped upper clamp 51.

[0032] In another preferred embodiment, two groups of outer arc-shaped lower clamps 52 are provided and are respectively installed on two groups of arc-shaped brackets 4, that is, the launch vehicle power unit is supported from the side by two groups of outer arc-shaped lower clamps 52, which effectively optimizes the weight of the outer arc-shaped lower clamps 52 and achieves a lightweight effect.

[0033] Preferably, the inner ring arc clamp 6 includes: an inner ring arc upper clamp 61 and an inner ring arc lower clamp 62. The inner ring arc upper clamp 61 is connected to the inner ring of the outer ring arc upper clamp 51 through a radial shock-absorbing component 7, and the inner ring arc lower clamp 62 is connected to the inner ring of the outer ring arc lower clamp 52 through a radial shock-absorbing component 7.

[0034] Specifically, the inner arc-shaped lower clamp 62 can also be divided into two groups, and correspond one-to-one with the two groups of outer arc-shaped lower clamps 52. While supporting and shock-absorbing the launch vehicle power device, it can also achieve a lightweight effect.

[0035] Preferably, the radial shock absorbing assembly 7 includes: a first hydraulic telescopic rod 71, a connecting block 72, a first threaded spring 73 and a spring sheet 74. A rectangular groove is provided on the inner ring surface of the outer ring arc clamp 5. One end of the first hydraulic telescopic rod 71 is fixedly installed inside the rectangular groove. The connecting block 72 is fixedly installed on the other end of the first hydraulic telescopic rod 71. The first threaded spring 73 is sleeved on the first hydraulic telescopic rod 71, and one end abuts against the inner wall of the rectangular groove and the other end abuts against the connecting block 72. One end of the spring sheet 74 is connected to the connecting block 72, and the other end is connected to the outer ring surface of the inner ring arc clamp 6.

[0036] Specifically, the spring leaves 74 are arranged in pairs, and the curvature of the paired spring leaves 74 is the same as that of the inner arc-shaped upper clamp 61. The protrusions of the two groups of spring leaves 74 arranged in pairs are opposite to each other. When the carrier rocket power unit is overweight or the vibration inertia is too large, the protrusions of the two groups of spring leaves 74 abut against each other to prevent the spring leaves 74 from being damaged by excessive force. At the same time, by arranging the first hydraulic telescopic rod 71, the connecting block 72 and the first threaded spring 73, the absorption or release stroke of the elastic potential energy can be increased, thereby effectively improving the shock absorption effect of the spring leaves 74.

[0037] In another embodiment, the spring sheet 74 of the present invention can also be replaced with a bionic spider web shock-absorbing structure. By installing the bionic spider web shock-absorbing structure between the inner arc clamp 6 and the outer arc clamp 5, the device of the present invention can buffer vibrations in any direction, and the density of the bionic spider web shock-absorbing structure can be specifically set according to the weight of the target power device.

[0038] Preferably, the outer arc-shaped clamp 5 is further threadedly connected to a radial shock-absorbing locking piece 8 , and one end of the radial shock-absorbing locking piece 8 passes through the outer arc-shaped clamp 5 and abuts against the inner arc-shaped clamp 6 .

[0039] Specifically, in order to facilitate the installation of the radial shock-absorbing locking member 8, the width of the outer ring arc clamp 5 and the inner ring arc clamp 6 in the technical solution of the present invention should be greater than the width of the arc bracket 4. When the carrier rocket power unit needs to be disassembled, the radial shock-absorbing locking member 8 is used to lock the position of the current inner ring arc clamp 6 to prevent the carrier rocket power unit from shaking up and down under the elastic action of the radial shock-absorbing assembly 7 during the lifting process, causing bumps and damage to the outer shell of the carrier rocket engine.

[0040] Preferably, two groups of arc-shaped brackets 4 are provided, and an axial buffer 9 is provided on the arc-shaped bracket 4. The axial buffer 9 includes: a second hydraulic telescopic rod 91, a second threaded spring 92 and a support rod 93. One end of the second hydraulic telescopic rod 91 is connected to the side wall of a group of arc-shaped brackets 4, and the other end is connected to the inner wall of the bracket 2. The second threaded spring 92 is sleeved on the second hydraulic telescopic rod 91, and one end of the second threaded spring 92 abuts against the side wall of a group of arc-shaped brackets 4, and the other end abuts against the inner wall of the bracket 2. The support rod 93 is fixedly connected between the two groups of arc-shaped brackets 4.

[0041] Specifically, the provision of the axial buffer 9 can effectively buffer the axial force, thereby preventing the launch vehicle power unit from rubbing against the inner surface of the inner arc-shaped clamp 6 when subjected to the axial force, thereby preventing the outer shell surface from being damaged.

[0042] In another embodiment, the sliding connection between the arc-shaped bracket 4 and the bracket 2 can be in the form of a slider and a slide groove, and two groups of axial buffers 9 are provided, and are symmetrical with respect to the longitudinal section of the launch vehicle power unit, ensuring that they can move in a straight line during buffering without offset.

[0043] Preferably, a bracket shock-absorbing assembly 10 is installed at the bottom of the bracket 2, and the bracket shock-absorbing assembly 10 includes: a longitudinal support beam 101, a third hydraulic telescopic rod 102, a gasket 103, a third threaded spring 104, a column 105, a first limit rod 106, a second limit rod 107 and a bottom plate 108. A T-slot is provided at the bottom of the bracket 2, and the longitudinal support beam 101 is plugged into the bottom of the bracket 2 through the T-slot. One end of the third hydraulic telescopic rod 102 is rotatably connected to the upper part of the longitudinal support beam 101. There are two groups of gaskets 103, which are respectively sleeved on both ends of the third hydraulic telescopic rod 102. The third threaded spring 104 is sleeved on the third hydraulic On the telescopic rod 102, and both ends are respectively abutted against the gasket 103 located on the third hydraulic telescopic rod 102, the top of the column 105 is rotatably connected to the other end of the third hydraulic telescopic rod 102, the first limiting rod 106, one end is rotatably connected to the bottom of the longitudinal support beam 101, and the other end is rotatably connected to the middle of the column 105, the second limiting rod 107, one end is rotatably connected to the bottom of the longitudinal support beam 101, and the other end is rotatably connected to the middle of the column 105, and the lengths of the first limiting rod 106 and the second limiting rod 107 are both less than the minimum length of the third hydraulic telescopic rod 102, and the base plate 108 is installed at the bottom of the column 105.

[0044] In another embodiment, in order to adapt to the weight of different launch vehicle power units, the operator can set different numbers and sizes of limit rods according to the power units of different weights to ensure the rigidity of the support. At the same time, the base plate 108 in the present invention can also be replaced with more mobile tires to facilitate short-distance transportation.

[0045] Preferably, a sealing mechanism 11 is provided on the top edge of the bracket 2 .

[0046] Specifically, the sealing mechanism 11 includes a silicone sealing strip A111 and a silicone sealing strip B112 arranged on the top edge of the bracket 2, wherein the upper edge of the bracket 2 in the present invention is not flush, but the end where the long side is located is high, and the end where the short side is located is low, and the upper cover 1 of the box body is correspondingly set, with the end where the long side is located being low and the end where the short side is located being high, wherein the silicone sealing strip A111 is set on the upper edge of the short side, and the silicone sealing strip B112 is set on the upper edge of the long side, and the side wall of the bracket 2 between the short side and the long side is sealed by coating silicone rubber putty.

[0047] In another embodiment, a layer of felt A12 is attached to the surface of the arc portion of the arc-shaped bracket 4, and a layer of felt B13 is attached to the inner ring surface of the inner ring arc-shaped clamp 6, thereby achieving the effect of reducing friction and avoiding damage to the outer shell surface of the carrier rocket power unit.

[0048] When the technical solution of the present invention is actually applied, the carrier rocket power unit is first hoisted onto the inner circle arc-shaped lower clamp 62, and then the outer circle arc-shaped upper clamp 51 is covered thereon, and the outer circle arc-shaped upper clamp 51 is fixed to the arc-shaped bracket 4 through the support plate, so that the inner surface of the inner circle arc-shaped upper clamp 61 is in contact with the surface of the carrier rocket power unit, and then the box cover 1 is placed on the bracket 2, and sealed with silicone sealing strip A111, silicone sealing strip B112 and silicone rubber putty to prevent the carrier rocket power unit from getting damp, and the assembled transfer box is hoisted onto the carrier for transfer. During the transfer process, the transfer box will be vibrated by external forces. The transfer box in the present invention first uses the bracket shock-absorbing assembly 10 at the bottom of the bracket 2 to dampen the entire transfer box to prevent the transfer box from vibrating too much. , causing the carrier rocket power unit to collide with the components inside the transfer box. Inside the transfer box, a radial shock-absorbing assembly 7 is provided to prevent the carrier rocket power unit from being squeezed by the clamp assembly during radial vibration, causing the surface of the carrier rocket power unit to be deformed. At the same time, the vehicle carrying the transfer box will generate axial inertia when starting, stopping, accelerating or decelerating. The present invention avoids the axial ends of the carrier rocket power unit from colliding with the inner wall of the transfer box by providing an axial buffer 9. The technical solution of the present invention avoids the collision of components such as the shell or nozzle of the carrier rocket power unit due to improper protection during transportation by providing multiple groups of shock-absorbing and buffering mechanisms. At the same time, it also ensures the sealing performance during transportation and prevents the carrier rocket power unit from getting damp during transportation.

[0049] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like to indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention 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 understood as limiting the present invention.

[0050] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of the technical features being referred to. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "plurality" means at least two, such as two, three, etc., unless otherwise specifically defined.

[0051] In the present invention, unless otherwise specified or limited, the terms "installed," "connected," "connect," "fixed," etc. should be understood in a broad sense. For example, they can refer to fixed connection, detachable connection, or integration; mechanical connection, electrical connection, or communication; direct connection or indirect connection through an intermediate medium; internal communication between two elements or interaction between two elements, unless otherwise specified. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0052] In the present invention, the terms "one embodiment", "some embodiments", "examples", "specific examples" or "some examples" mean that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic expressions of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art can combine and combine different embodiments or examples described in this specification and the features of different embodiments or examples without contradiction.

[0053] Although the embodiments of the present invention have been shown and described above, it will be understood that the above embodiments are exemplary and are not to be construed as limitations on the present invention. A person skilled in the art may change, modify, replace and deform the above embodiments within the scope of the present invention.

Claims

1. A carrier rocket power unit transfer box, characterized in that: include: Box cover; a bracket, on which the upper cover of the box body is overlapped; Connecting pieces, the box cover and the bracket are both fixedly mounted with the connecting pieces, and the box cover and the bracket are connected by two sets of the connecting pieces; an arc-shaped bracket, slidably connected to the bracket, for carrying a launch vehicle power unit; The clamp assembly is installed on the arc-shaped bracket and is used for sleeve-mounting and fixing the launch vehicle power unit.

2. The carrier rocket power unit transfer box according to claim 1, characterized in that: The connecting piece includes: A first U-shaped connecting piece is fixedly mounted on the upper cover of the box body; The second U-shaped connecting member is fixedly mounted on the bracket, and the lower bottom surface of the first U-shaped connecting member abuts against the upper top surface of the second U-shaped connecting member and is connected by bolts.

3. The carrier rocket power unit transfer box according to claim 1, characterized in that: The clamp assembly comprises: An outer arc-shaped clamp is detachably connected to the arc-shaped bracket; The inner arc-shaped clamp is connected to the inner ring of the outer arc-shaped clamp through a radial shock-absorbing component and is used to support the launch vehicle power unit.

4. The carrier rocket power unit transfer box according to claim 3, characterized in that: The outer arc-shaped clamp comprises: An outer arc-shaped upper clamp is connected to the top of the arc-shaped bracket; The outer arc-shaped lower clamp is installed on the arc-shaped portion of the arc-shaped bracket.

5. The carrier rocket power unit transfer box according to claim 4, characterized in that: The inner arc clamp comprises: An inner arc-shaped upper clamp is connected to the inner ring of the outer arc-shaped upper clamp via a radial damping assembly; The inner arc-shaped lower clamp is connected to the inner ring of the outer arc-shaped lower clamp through a radial shock-absorbing component.

6. The carrier rocket power unit transfer box according to claim 3, characterized in that: The radial damping assembly comprises: A first hydraulic telescopic rod, wherein the inner surface of the outer arc-shaped clamp is provided with a rectangular groove, and one end of the first hydraulic telescopic rod is fixedly mounted inside the rectangular groove; A connecting block fixedly mounted on the other end of the first hydraulic telescopic rod; a first threaded spring, sleeved on the first hydraulic telescopic rod, with one end abutting against the inner wall of the rectangular groove and the other end abutting against the connecting block; One end of the spring sheet is connected to the connecting block, and the other end is connected to the outer ring surface of the inner ring arc clamp.

7. The carrier rocket power unit transfer box according to claim 3, characterized in that: The outer arc-shaped clamp is also threadedly connected to a radial shock-absorbing locking piece, and one end of the radial shock-absorbing locking piece passes through the outer arc-shaped clamp and abuts against the inner arc-shaped clamp.

8. The carrier rocket power unit transfer box according to claim 1, characterized in that: The arc-shaped brackets are provided in two groups, and an axial buffer is provided on the arc-shaped brackets, and the axial buffer comprises: a second hydraulic telescopic rod, one end of which is connected to a side wall of a group of said arc-shaped brackets, and the other end of which is connected to an inner wall of said bracket; a second threaded spring, sleeved on the second hydraulic telescopic rod, with one end of the second threaded spring abutting against a side wall of one set of the arc-shaped brackets, and the other end abutting against an inner wall of the bracket; The support rod is fixedly connected between the two groups of arc-shaped brackets.

9. The carrier rocket power unit transfer box according to claim 1, characterized in that: A bracket shock-absorbing assembly is installed at the bottom of the bracket, and the bracket shock-absorbing assembly includes: A longitudinal support beam, wherein a T-slot is provided at the bottom of the bracket, and the longitudinal support beam is plugged into the bottom of the bracket through the T-slot; a third hydraulic telescopic rod, one end of which is rotatably connected to the upper portion of the longitudinal support beam; Two sets of gaskets are provided and are respectively sleeved on both ends of the third hydraulic telescopic rod; a third threaded spring, sleeved on the third hydraulic telescopic rod, with both ends respectively abutting against the gasket on the third hydraulic telescopic rod; A column, the top end of which is rotatably connected to the other end of the third hydraulic telescopic rod; a first limiting rod, one end of which is rotatably connected to the bottom of the longitudinal support beam, and the other end of which is rotatably connected to the middle of the column; a second limiting rod, one end of which is rotatably connected to the bottom of the longitudinal support beam, and the other end of which is rotatably connected to the middle of the column, and the lengths of the first limiting rod and the second limiting rod are both less than the minimum length of the third hydraulic telescopic rod; A base plate is installed at the bottom of the column.

10. The carrier rocket power unit transfer box according to claim 1, characterized in that: A sealing mechanism is provided on the top edge of the bracket.

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