Supporting device

Abstract

The invention provides a supporting device. The supporting device is used for a carrier rocket sub-stage power system test run and comprises a supporting frame, a first supporting frame and a second supporting frame, the multiple stand columns are detachably connected to the lower portion of the first platform assembly. The first platform assembly comprises a first platform and a bearing frame; a first through groove is formed in the center of the first platform, and the bearing frame is detachably connected with the inner circumferential wall of the first through groove; the lower surface of the transfer frame is detachably connected with the bearing frame, and the upper surface of the transfer frame is configured to be detachably connected with the bottom end of the carrier rocket sub-stage power system; one end of the mooring tool is detachably connected with the first platform, and the other end of the mooring tool is constructed to be detachably connected with the top end of the carrier rocket sub-stage power system; therefore, the supporting device can be quickly disassembled and assembled and is convenient to transport. Moreover, the mooring tool provides a downward pulling force, so that the phenomenon that the carrier rocket sub-stage is out of control and flies off due to accidents in the test run process of the carrier rocket sub-stage power system can be avoided.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of test technology of launch vehicle, in particular, the present application relates to a supporting device. BACKGROUND

[0002] The test of the sub-stage power system of the launch vehicle is an important part of the development of the new rocket, which aims to simulate the working process of the launch vehicle in the flight state, to verify the coordination and stability of the rocket on-board systems such as the sub-stage power system and the propulsion system, and to provide a basis for predicting and solving problems that may occur in flight. The supporting device is a load-bearing carrier for the test of the sub-stage power system of the launch vehicle, which needs to bear various loads such as rocket thrust, wind force, impact and the like during the test.

[0003] The existing supporting device for the test of the sub-stage power system of the launch vehicle is usually an integral metal structure welded on site or a reinforced concrete structure cast on site, which results in that the existing supporting device is large in size and heavy in weight, cannot be disassembled and cannot be reused. In addition, in the existing test process of the sub-stage power system of the launch vehicle, only the bottom end of the sub-stage power system of the launch vehicle is detachably connected with the supporting device, which has the risk of causing the sub-stage of the launch vehicle to lose control and fly away due to unexpected situations. SUMMARY

[0004] The present application proposes a supporting device to solve the technical problems that the existing supporting device cannot be disassembled and cannot be reused, and there is a risk of the sub-stage power system of the launch vehicle losing control and flying away due to unexpected situations during the test.

[0005] The present application provides a supporting device for the test of the sub-stage power system of the launch vehicle, comprising: A supporting frame comprising a first platform assembly and a plurality of columns which are detachably connected; the plurality of columns are vertically connected below the first platform assembly; the first platform assembly comprises a first platform and a bearing frame; the first platform has a first through slot in the center, and the bearing frame is annular and detachably connected to the inner peripheral wall of the first through slot; An adapter frame, the lower surface of the adapter frame is detachably connected with the bearing frame, and the upper surface of the adapter frame is configured to be detachably connected with the bottom end of the sub-stage power system of the launch vehicle; A tethering tool, one end of which is detachably connected with the first platform, and the other end is configured to be detachably connected with the top end of the sub-stage power system of the launch vehicle.

[0006] Optionally, the first platform comprises: At least two first sub-platforms, all the first sub-platforms are sequentially connected end to end in a clockwise direction to form a component with the first through slot in the center; A first fixed plate is arranged on the upper surface of the connection between two adjacent first sub-platforms and detachably connected with the two adjacent first sub-platforms.

[0007] Optionally, the carrier frame comprises at least two sub-carrier frames; all the sub-carrier frames are sequentially connected in a head-to-tail manner along the circumference to form a circular carrier frame. The circular carrier frame is clamped in the first through slot and at least partially protrudes from the upper surface of the first platform. The number of the sub-carrier frames is equal to the number of the first sub-platforms.

[0008] Optionally, the tethered tooling comprises: A top cover assembly is configured to cover the top end of the sub-stage power system of the launch vehicle; A flexible member is detachably connected at one end to the top cover assembly and at the other end to the first platform; An adjusting member is arranged on the flexible member and used to adjust the length of the flexible member.

[0009] Optionally, the top cover assembly comprises: A top cover is configured to cover the top end of the sub-stage power system of the launch vehicle; A support member is fixedly connected to the top end of the top cover and radially arranged with the end protruding from the edge of the top cover; One end of the flexible member is detachably connected to the support member.

[0010] Optionally, the support device further comprises a second platform assembly; the second platform assembly comprises: At least two second sub-platforms are sequentially connected in a head-to-tail manner along the clockwise direction to form a member with a second through slot in the center; A second fixed plate is arranged on the upper surface of the connection between two adjacent second sub-platforms and detachably connected with the two adjacent second sub-platforms.

[0011] Optionally, the support frame further comprises: A horizontal beam is horizontally arranged between two adjacent columns and detachably connected at both ends to the two adjacent columns; A first reinforcing beam is radially arranged between two adjacent columns and detachably connected to the two adjacent columns; A second reinforcing beam is arranged between two adjacent columns and detachably connected to the two adjacent columns; at least two second reinforcing beams are symmetrically arranged.

[0012] Optionally, the support frame further comprises: a first support column, a second support column and a third support column which are arranged obliquely towards the first through slot. One end of the first support column, one end of the second support column and one end of the third support column are detachably connected with the column; the other end of the first support column and the other end of the second support column are detachably connected with the first platform; the other end of the third support column is detachably connected with the bottom surface of the carrier.

[0013] Optionally, the support device further comprises a support table; the support table is fixed to the side of the third support column away from the column, and the second platform assembly is detachably connected with the support table.

[0014] Optionally, the support device further comprises a first operation platform assembly and a second operation platform assembly. The bottom of the first operation platform assembly is detachably connected to the upper surface of the first platform, the bottom of the second operation platform assembly is fixed to the first operation platform assembly, and the top surface of the second operation platform assembly is not lower than the top end of the sub-level power system of the launch vehicle.

[0015] The technical scheme provided by the embodiments of the present application has the following beneficial technical effects: The support device of the embodiments of the present application is detachably connected with the first platform assembly below the plurality of columns, the first platform assembly comprises a first platform and a carrier, the carrier is detachably connected with the inner circumferential wall of the first through slot in the center of the first platform, the lower surface of the adapter is detachably connected with the upper surface of the carrier, the upper surface of the adapter is detachably connected with the bottom end of the sub-level power system of the launch vehicle, one end of the tethered tooling is detachably connected with the first platform, and the other end of the tethered tooling is detachably connected with the top end of the sub-level power system of the launch vehicle. Since the components of the support device are detachably connected with each other, the support device can be quickly disassembled and assembled, so that the support structure can be repeatedly used and transported.

[0016] In addition, one end of the tethered tooling is detachably connected with the first platform, and the other end of the tethered tooling is detachably connected with the top end of the sub-level power system of the launch vehicle. During the test run of the sub-level power system of the launch vehicle, the tethered tooling provides a downward pulling force, the direction of the pulling force provided by the tethered tooling is opposite to the direction of the impact force formed after the sub-level of the launch vehicle is ignited, and the pulling force provided by the tethered tooling is greater than the impact force formed after the sub-level of the launch vehicle is ignited, so that the accidental failure of the connection between the bottom end of the sub-level power system of the launch vehicle and the adapter can be avoided, and the sub-level of the launch vehicle can be prevented from losing control and flying away, thereby improving the safety of the test run of the sub-level power system of the launch vehicle.

[0017] 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 by those skilled in the art through the practice of the present application. BRIEF DESCRIPTION OF DRAWINGS

[0018] The above and / or additional aspects and advantages of the present application will become apparent and more readily appreciated from the following description of the embodiments, taken in conjunction with the accompanying drawings in which: Figure 1 A structural schematic diagram of a support device according to an embodiment of the present application from one perspective; Figure 2 A structural schematic diagram of a support device according to an embodiment of the present application from another perspective; Figure 3 A structural schematic diagram of a support device according to an embodiment of the present application from one perspective; Figure 4 A structural schematic diagram of a support device according to an embodiment of the present application from another perspective; Figure 5 A structural schematic diagram of a support device according to an embodiment of the present application from one perspective; Figure 6 A structural schematic diagram of a support device according to an embodiment of the present application from another perspective; Figure 7 A structural schematic diagram of a support device according to an embodiment of the present application from one perspective; Figure 8 A structural schematic diagram of a support device according to an embodiment of the present application from another perspective; Figure 9 A structural schematic diagram of a support device according to an embodiment of the present application from one perspective; Figure 10 A structural schematic diagram of a support device according to an embodiment of the present application from another perspective. Reference Signs: 1 - support device; 11 - support frame; 111 - first platform assembly; 1111 - first platform; 11111 - first through slot; 11112 - first sub-platform; 11113 - first fixed plate; 11114 - fixed slot; 11115 - first ladder; 1112 - carrier frame; 11121 - sub-carrier frame; 112 - column; 113 - cross beam; 114 - first reinforcing beam; 115 - second reinforcing beam; 116 - first support column; 117 - second support column; 118 - third support column; 119 - support table; 12 - adapter frame; 121 - sub-adapter frame; 122 - docking plate; 123 - reinforcing rib; 13-tethered tool; 131-top cover assembly; 1311-top cover; 1312-support; 1313-lifting lug; 132-flexible member; 133-adjusting member; 134-connecting member; 14-second platform assembly; 141-second sub-platform; 142-second through slot; 143-second fixed plate; 144-third operation platform; 15-first operation platform assembly; 151-first operation platform; 152-second ladder; 153-base; 16-second operation platform assembly; 161-second operation platform; 162-third ladder; 2-substage power system of launch vehicle. DETAILED DESCRIPTION

[0019] The embodiments of the present application will be described below in conjunction with the accompanying drawings. It should be understood that the embodiments described below in conjunction with the accompanying drawings are exemplary descriptions of the technical solutions of the embodiments of the present application, and do not constitute a limitation on the technical solutions of the embodiments of the present application.

[0020] Those skilled in the art can understand that, unless specifically stated otherwise, "said" and "the" used herein can also include plural forms. It should be further understood that the wording "comprising" used in the specification of the present application means that the features, integers, steps, operations, elements and / or components exist, but does not exclude other features, information, data, steps, operations, elements, components and / or combinations thereof supported by the present technical field. The term "and / or" used herein means at least one of the items defined by the term, for example, "A and / or B" can be implemented as "A", or as "B", or as "A and B".

[0021] In order to make the purpose, technical solutions and advantages of the present application clearer, the embodiments of the present application will be described in further detail below in conjunction with the accompanying drawings.

[0022] The substage power system test of the launch vehicle is an important part of the development process of the new rocket, and the purpose is to simulate the working process of the launch vehicle in the flight state, to verify the coordination and stability of the launch vehicle substage power system and the propelling system and other on-board systems, to provide a basis for predicting and solving problems that may occur in flight. The supporting device is the load-bearing carrier of the substage power system test of the launch vehicle, and needs to bear various loads such as rocket thrust, wind force, impact and the like during the test.

[0023] Existing support structures for test launch vehicle stage propulsion systems are typically integral metal structures welded on-site or reinforced concrete structures cast in-site. This results in large, heavy, and non-removable support structures that cannot be reused. Furthermore, during test launches, only the bottom of the stage propulsion system is detachably connected to the support structure, posing a risk of the stage detaching uncontrollably in case of unforeseen circumstances.

[0024] The technical solution of this application and how it solves the above-mentioned technical problems are described in detail below with specific embodiments. It should be noted that the following embodiments can be referenced, borrowed, or combined with each other, and the same terms, similar features, and similar implementation steps in different embodiments will not be described again.

[0025] This application provides a support device 1 for testing the propulsion system 2 of a launch vehicle sub-stage, such as... Figures 1-10 As shown, the support device 1 includes: a support frame 11, a transition frame 12, and a tethering fixture 13.

[0026] The support frame 11 includes a first platform assembly 111 that is detachably connected and multiple columns 112; the multiple columns 112 are vertically connected to the lower part of the first platform assembly 111; the first platform assembly 111 includes a first platform 1111 and a support frame 1112; the first platform 1111 has a first through groove 11111 at its center, and the support frame 1112 is annular and detachably connected to the inner peripheral wall of the first through groove 11111.

[0027] The adapter 12 has its lower surface detachably connected to the support frame 1112, and its upper surface is configured to be detachably connected to the bottom of the launch vehicle stage propulsion system 2.

[0028] The tethering fixture 13 is detachably connected at one end to the first platform 1111, and at the other end is configured to be detachably connected to the top of the launch vehicle sub-stage propulsion system 2.

[0029] The support device 1 of the embodiment of the present application, a plurality of columns 112 are detachably connected below the first platform assembly 111, the first platform assembly 111 comprises a first platform 1111 and a bearing frame 1112, the bearing frame 1112 is detachably connected with the inner peripheral wall of the first through slot 11111 in the center of the first platform 1111, the lower surface of the adapter frame 12 is detachably connected with the upper surface of the bearing frame 1112, the upper surface of the adapter frame 12 is detachably connected with the bottom end of the sub-level power system 2 of the carrier rocket, one end of the tethered tooling 13 is detachably connected with the first platform 1111, the other end of the tethered tooling 13 is detachably connected with the top end of the sub-level power system 2 of the carrier rocket, since the support device 1 is detachably connected between each component, the support device 1 can be quickly disassembled and installed, the operation is simple, the support structure can be repeatedly used, the cost is saved, and transportation is facilitated.

[0030] In addition, one end of the tethered tooling 13 is detachably connected with the first platform 1111, and the other end of the tethered tooling 13 is detachably connected with the top end of the sub-level power system 2 of the carrier rocket, during the test run of the sub-level power system 2 of the carrier rocket, the tethered tooling 13 provides a downward pulling force, the direction of the pulling force provided by the tethered tooling 13 is opposite to the direction of the impact force formed after the sub-level of the carrier rocket is ignited, and the pulling force provided by the tethered tooling 13 is greater than the impact force formed after the sub-level of the carrier rocket is ignited, so that the bottom end of the sub-level power system 2 of the carrier rocket and the adapter frame 12 are prevented from being accidentally failed, the sub-level of the carrier rocket is prevented from being out of control and flying away, and the safety of the test run of the sub-level power system 2 of the carrier rocket is improved.

[0031] Optionally, in one embodiment of the present application, as shown in Figures 2-3 、 Figure 5 and Figure 8 , the first platform 1111 comprises at least two first sub-platforms 11112 and a first fixed plate 11113.

[0032] The at least two first sub-platforms 11112 are sequentially connected in a clockwise direction to form a component with the first through slot 11111 in the center.

[0033] The first fixed plate 11113 is arranged on the upper surface of the connection between the adjacent two first sub-platforms 11112 and is detachably connected with the adjacent two first sub-platforms 11112.

[0034] In the embodiment of the present application, the plurality of first sub-platforms 11112 are sequentially connected in a clockwise or counterclockwise direction to form a component with a first through slot 11111 at the center, a plurality of first fixing plates 11113 are arranged at intervals on the upper surfaces of the connecting portions between adjacent two first sub-platforms 11112, the plurality of first fixing plates 11113 are detachably connected with the adjacent two first sub-platforms 11112, and the connection mode of the plurality of first fixing plates 11113 and the first sub-platforms 11112 includes bolts, studs and the like; a plurality of flanges are welded at the edges of the lower surfaces of the first sub-platforms 11112, wherein the flanges located at the ends of the adjacent two first sub-platforms 11112 are used for detachable connection with the flanges on the top surface of the stand column 112, and the flanges located at the outer edges of the first sub-platforms 11112 are respectively used for detachable connection with the flanges welded on the top surfaces of the first support column 116 and the second support column 117, so that when the sub-stage power system 2 of the launch vehicle needs to be tested, the first sub-platforms 11112, the first fixing plates 11113, the first support column 116, the second support column 117 and the stand column 112 can be quickly assembled together by bolts, studs and the like, and the operation is simple; after the test is completed, the first sub-platforms 11112, the first fixing plates 11113, the first support column 116, the second support column 117 and the stand column 112 can be disassembled, which is convenient for transportation.

[0035] In the embodiment of the present application, a fence is arranged at the outer edges of the first sub-platforms 11112 to prevent the operator from falling from the first platform 1111. The flange portions of the lower surfaces of the first sub-platforms 11112 are arranged to protrude beyond the outer edges of the first sub-platforms 11112, and a reinforcing rib is arranged between the side edges of the first sub-platforms 11112 and the flanges, so as to increase the strength of the flanges and improve the strength of the connection portions.

[0036] In this embodiment, the first platform 1111 further includes a fixing groove 11114 and a first ladder 11115. Multiple fixing grooves 11114 are arranged circumferentially around the first groove 11111. The fixing grooves 11114 are used to connect with the connector 134 of the tethering fixture 13. A support seat can be provided in the fixing groove 11114, and the support seat is detachably connected to the connector 134, or the connector 134 can be fixed in the fixing groove 11114. The first ladder 11115 extends vertically downwards. After the support device 1 is assembled, the first ladder 11115 extends downwards to the upper surface of the third operating platform 144 of the second platform assembly 14, thereby allowing access to the first platform 1111 or the third operating platform 144 for related operational tasks. The fixing slot 11114 can be set in multiple ways. For example, multiple fixing slots 11114 can be arranged in multiple circumferential intervals from the inside to the outside along the circumference of the first slot 11111. In this way, when different launch vehicle stage propulsion system tests are carried out, the position of the fixing slot 11114 can be adaptively adjusted to provide appropriate tension to meet the needs of different types of rocket stage tests.

[0037] In this embodiment, the first platform 1111 provides an installation plane for the interface operation platform in the vertical direction of the launch vehicle substage.

[0038] Optionally, in one embodiment of this application, such as Figures 2-5 As shown, the support frame 1112 includes at least two sub-support frames 11121; all the sub-support frames 11121 are connected end to end in the circumferential direction to form a ring-shaped support frame 1112.

[0039] The annular support frame 1112 is engaged in the first through slot 11111 and extends at least partially beyond the upper surface of the first platform 1111.

[0040] The number of sub-support frames 11121 is equal to the number of first sub-platforms 11112.

[0041] In this embodiment, the sub-support frame 11121 is engaged on the inner edge of the first sub-platform 11112. The number of sub-support frames 11121 is the same as the number of first sub-platforms 11112, so that when the first sub-platforms 11112 are detachably connected together, the sub-support frames 11121 are also connected together. The upper surface of the support frame 1112 is provided with multiple through holes for detachable connection with the lower surface of the adapter frame 12; the lower surface of the support frame 1112 is provided with multiple through holes for detachable connection with the third support column 118 of the support frame 11.

[0042] Optionally, in one embodiment of this application, such as Figure 7As shown, the adapter frame 12 comprises sub-adapter frames 121, abutting plates 122 and reinforcing ribs 123. All the sub-adapter frames 121 are sequentially connected in a circumferential direction to form a circular truncated cone-shaped adapter frame 12. The end of the sub-adapter frame 121 is provided with an abutting plate 122, and two adjacent sub-adapter frames 121 are detachably connected through the abutting plates at the ends. Along the circumferential direction of the adapter frame 12, the reinforcing ribs 123 are arranged at intervals on the side walls of the sub-adapter frames 121, thereby increasing the strength of the adapter frame 12. The upper edge surface of the adapter frame 12 is provided with a plurality of through holes, and the bottom end of the sub-stage power system 2 of the launch vehicle is connected to the upper surface of the adapter frame 12 through bolts. According to the model of the sub-stage of the launch vehicle, the corresponding adapter frame 12 is selected, so that the support device 1 can meet the needs of the test run of the rocket sub-stage of different models.

[0043] Optionally, in an embodiment of the present application, as shown in Figures 1-2 、 Figure 5 and Figure 8 , the mooring tool 13 comprises a top cover assembly 131, a flexible member 132 and an adjusting member 133.

[0044] The top cover assembly 131 is configured to cover the top end of the sub-stage power system 2 of the launch vehicle.

[0045] The flexible member 132 is detachably connected at one end to the top cover assembly 131 and at the other end to the first platform 1111.

[0046] The adjusting member 133 is arranged on the flexible member 132 and used for adjusting the length of the flexible member 132.

[0047] In the embodiment of the present application, the lower surface of the top cover assembly 131 is detachably connected with the top end of the sub-level power system of the carrier rocket, one end of the flexible member 132 is connected with the top cover assembly 131 through a pin shaft, so that the flexible member 132 can rotate a certain angle relative to the top cover assembly 131, which facilitates the other end of the flexible member 132 to be fixed at the fixed groove 11114 of the first platform 1111, and the adjusting member 133 located on the flexible member 132 can adjust the length of the flexible member 132, so that the flexible member 132 is in a tension state, so that the flexible member 132 has a certain tension. The tethering tool 13 further comprises a connecting member 134 fixed to one end of the flexible member 132 away from the top cover assembly 131, and the connecting member 134 is used to be detachably connected with the first platform 1111. Thus, during the test run of the sub-level power system 2 of the carrier rocket, the tethering tool 13 provides a downward tension, the direction of the tension provided by the tethering tool 13 is opposite to the direction of the impact force formed after the sub-level of the carrier rocket is ignited, and the tension provided by the tethering tool 13 is greater than the impact force formed after the sub-level of the carrier rocket is ignited, so that the tethering tool 13 can fix the sub-level power system 2 of the carrier rocket on the support device 1, so that the sub-level of the carrier rocket is in a static state, thereby avoiding that the bottom end of the sub-level power system 2 of the carrier rocket is connected with the adapter 12 to be accidentally failed, the sub-level of the carrier rocket is out of control and flies away, thereby improving the safety of the test run of the sub-level power system 2 of the carrier rocket.

[0048] Optionally, in one embodiment of the present application, as shown in Figures 1-2 and Figure 8 , the top cover assembly 131 comprises a top cover 1311 and a support member 1312.

[0049] The top cover 1311 is configured to cover the top end of the sub-level power system 2 of the carrier rocket.

[0050] The support member 1312 is fixedly connected to the top end of the top cover 1311, is in a radial shape, and the terminal end extends out of the edge of the top cover 1311.

[0051] One end of the flexible member 132 is detachably connected with the support member 1312.

[0052] In the embodiment of the present application, when the sub-level power system 2 of the carrier rocket is tested, the top cover 1311 can cover the top end of the entire sub-level power system 2 of the carrier rocket, the support member 1312 is fixedly pressed on the top end of the top cover 1311, and the entire sub-level of the carrier rocket can be protected, so as to avoid that the sub-level of the carrier rocket breaks through the top cover 1311 due to excessive impact force during the test run, ensure the smooth progress of the test run task, and improve the success rate of the test run task.

[0053] In the embodiment of the present application, one end of the flexible piece 132 is detachably connected with one end of the supporting piece 1312 through a pin shaft, which is simple in structure and convenient for dismounting and mounting. The top cover assembly 131 further comprises two lugs 1313 symmetrically fixed to the upper surface of the top cover 1311.

[0054] Optionally, in one embodiment of the present application, as shown in Figures 1-4 and Figure 9 , the supporting device 1 further comprises a second platform assembly 14; the second platform assembly 14 comprises at least two second sub-platforms 141 and a second fixed plate 143.

[0055] The at least two second sub-platforms 141 are sequentially connected in a clockwise direction to form a component with a second through slot 142 in the center.

[0056] The second fixed plate 143 is arranged on the upper surface at the connection between the adjacent two second sub-platforms 141 and is detachably connected with the adjacent two second sub-platforms 141.

[0057] In the embodiment of the present application, in the embodiment of the present application, the plurality of second sub-platforms 141 are sequentially connected in a clockwise or counterclockwise direction to form a component with a second through slot 142 in the center, a plurality of second fixed plates 143 are arranged on the upper surface at the connection between the adjacent two second sub-platforms 141, and the plurality of second fixed plates 143 are detachably connected with the adjacent two second sub-platforms 141; the second platform assembly 14 further comprises a third operation platform 144, the third operation platform 144 is located at the edge of one of the second sub-platforms 141 and is detachably connected with the second sub-platform 141, and a plurality of second fixed plates 143 are arranged on the upper surface at the connection between the third operation platform 144 and the adjacent second sub-platform 141, so that the second platform assembly 14 is convenient for dismounting and mounting; since the second platform assembly 14 can be disassembled, the volume of each part after disassembly is small, which is convenient for transportation.

[0058] In the embodiment of the present application, the bottom surface of each second sub-platform 141 is welded with a flange, which facilitates the detachable connection between the second platform assembly and the supporting table 119 of the supporting frame 11. In addition, a fence is arranged on the outer edge of each second sub-platform 141 and the outer edge of the third operation platform 144.

[0059] Optionally, in one embodiment of the present application, as shown in Figures 3-4 and Figure 6 , the supporting frame 11 further comprises a cross beam 113, a first reinforcing beam 114 and a second reinforcing beam 115.

[0060] The cross beam 113 is horizontally arranged between the adjacent two columns 112 and is detachably connected with the adjacent two columns 112 at both ends.

[0061] The first reinforcing beam 114 is radially arranged between two adjacent columns 112 and detachably connected with the two adjacent columns 112.

[0062] The second reinforcing beam 115 is arranged between two adjacent columns 112 and detachably connected with the two adjacent columns 112; and at least two second reinforcing beams 115 are symmetrically arranged.

[0063] In the embodiment, the bottom of the column 112 is welded with a flange, and the column 112 can be fixed to the bottom surface or other devices through the bottom flange; one horizontal beam 113 is arranged between any two adjacent columns 112 to connect all the columns 112; the second reinforcing beam 114 in a cross shape is detachably connected with two adjacent columns 112; and the second reinforcing beam 115 is arranged between two adjacent columns 112 in an inclined manner, thereby increasing the strength of the support frame 11 and preventing the support frame 11 from being skewed, tilted or deformed; the connection between the horizontal beam 113, the first reinforcing beam 114 and the second reinforcing beam 115 and the column 112 is welded with a flange, and the flanges of the horizontal beam 113, the first reinforcing beam 114 and the second reinforcing beam 115 are detachably connected with the flange of the column 112, which is simple in structure, easy to install and detach, and can be repeatedly used.

[0064] Optionally, in one embodiment of the present application, as shown in Figures 3-4 and Figure 6 The support frame 11 further comprises a first support column 116, a second support column 117 and a third support column 118 arranged in an inclined manner towards the first through groove 11111.

[0065] One end of the first support column 116, one end of the second support column 117 and one end of the third support column 118 are detachably connected with the column 112; the other end of the first support column 116 and the other end of the second support column 117 are detachably connected with the first platform 1111; and the other end of the third support column 118 is detachably connected with the bottom surface of the bearing frame 1112.

[0066] In the embodiment of the present application, the first support column 116, the second support column 117 and the third support column 118 have different inclination angles, the top surface of each of the first support column 116, the second support column 117 and the third support column 118 is welded with a flange, the first support column 116 and the second support column 117 are detachably connected with the bottom surface of the first platform 1111 through the flange, and the third support column 118 is detachably connected with the bottom surface of the bearing frame 1112 through the flange; the connection between each of the first support column 116, the second support column 117 and the third support column 118 and the stand column 112 is welded with a flange, and the flange of the first support column 116, the flange of the second support column 117 and the flange of the third support column 118 are connected with the flange of the stand column 112 through bolts, so that the structure is simple, the installation and dismounting are facilitated, and the structure can be repeatedly used.

[0067] Optionally, in an embodiment of the present application, as shown in Figures 3-4 and Figure 6 , the support device 1 further comprises a support table 119; the support table 119 is fixed to the side of the third support column 118 away from the stand column 112, and the second platform assembly 14 is detachably connected with the support table 119.

[0068] In the embodiment of the present application, the second platform assembly 14 is an operation platform for the engine interface of the launch vehicle, the support table 119 is welded to the side of the third support column 118 away from the stand column 112, and the support table 119 is detachably connected with the flange on the bottom surface of the second operation platform 14.

[0069] Optionally, in an embodiment of the present application, as shown in Figures 1-2 and Figure 10 , the support device 1 further comprises a first operation platform assembly 15 and a second operation platform assembly 16.

[0070] The bottom of the first operation platform assembly 15 is detachably connected with the upper surface of the first platform 1111, the bottom of the second operation platform assembly 16 is fixed to the first operation platform assembly 15, and the top surface of the second operation platform assembly 16 is not lower than the top end of the launch vehicle sub-stage power system 2.

[0071] In the embodiment of the present application, the first operation platform assembly 15 comprises a first operation platform 151, a second ladder 152 and a base 153; the second operation platform assembly 16 comprises a second operation platform 161 and a third ladder 162. The base 153 is fixed to the upper surface of the first platform 1111, so that the operator can reach the first operation platform 151 from the first platform 1111 via the second ladder 152 and reach the second operation platform 161 via the third ladder 162 to perform the operation task. The top surface of the second operation platform assembly 16, i.e. the upper surface of the second operation platform 161, is not lower than the top end of the sub-stage power system 2 of the launch vehicle, so as to facilitate the operator to perform the operation on the top end of the sub-stage power system 2 of the launch vehicle. Moreover, the heights of the first operation platform 151 and the second operation platform 161 are different, so as to facilitate the operation on different functional interfaces on the rocket body of the launch vehicle. The first operation platform 151 can perform the liquid oxygen leak port operation, and the second operation platform 161 can perform the gas cylinder inflation port operation.

[0072] By applying the embodiment of the present application, the following beneficial effects can be achieved at least: 1. The support device 1 of the embodiment of the present application, a plurality of columns 112 are detachably connected below the first platform assembly 111, the first platform assembly 111 comprises a first platform 1111 and a bearing frame 1112, the bearing frame 1112 is detachably connected with the inner peripheral wall of the first through slot 11111 in the center of the first platform 1111, the lower surface of the adapter frame 12 is detachably connected with the upper surface of the bearing frame 1112, the upper surface of the adapter frame 12 is detachably connected with the bottom end of the sub-stage power system 2 of the launch vehicle, one end of the tethered tooling 13 is detachably connected with the first platform 1111, and the other end of the tethered tooling 13 is detachably connected with the top end of the sub-stage power system 2 of the launch vehicle. Since the components of the support device 1 are detachably connected, the support device 1 can be quickly disassembled and installed, so that the support structure can be repeatedly used and is convenient for transportation.

[0073] In addition, one end of the tethered tooling 13 is detachably connected with the first platform 1111, and the other end of the tethered tooling 13 is detachably connected with the top end of the sub-stage power system 2 of the launch vehicle. During the test run of the sub-stage power system 2 of the launch vehicle, the tethered tooling 13 provides a downward pulling force, the direction of the pulling force provided by the tethered tooling 13 is opposite to the direction of the impact force formed after the sub-stage of the launch vehicle is ignited, and the pulling force provided by the tethered tooling 13 is greater than the impact force formed after the sub-stage of the launch vehicle is ignited, so as to avoid the accidental failure of the connection between the bottom end of the sub-stage power system 2 of the launch vehicle and the adapter frame 12 and the out-of-control flight of the sub-stage of the launch vehicle, thereby improving the safety of the test run of the sub-stage power system 2 of the launch vehicle.

[0074] Those skilled in the art can understand that the steps, measures, and schemes in various operations, methods, and processes discussed in the present application can be alternated, changed, combined, or deleted. Further, other steps, measures, and schemes in various operations, methods, and processes discussed in the present application can also be alternated, changed, rearranged, decomposed, combined, or deleted. Further, steps, measures, and schemes in various operations, methods, and processes in the related art can also be alternated, changed, rearranged, decomposed, combined, or deleted.

[0075] In the description of the present application, the directions or positional relationships indicated by the words "center", "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. are the exemplary directions or positional relationships based on the examples shown in the drawings, and are for the convenience of description or simplification of the description of the embodiments of the present application, and do not indicate or imply that the devices or components indicated thereby must have a particular orientation or be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation of the present application.

[0076] The terms "first", "second", etc. are only for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the technical features indicated thereby. Therefore, the features defined with "first", "second", etc. can explicitly or implicitly include one or more of the features. In the description of the present application, the meaning of "a plurality of" is two or more, unless otherwise specified.

[0077] In the description of the present application, it should be noted that, unless otherwise explicitly specified and limited, the terms "mounting", "connection", and "connection" should be understood in a broad sense, for example, can be fixed connection, can also be detachable connection, or integral connection; can be directly connected, or indirectly connected through an intermediate medium; can be the communication inside two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0078] In the description of the present application, specific features, structures, materials, or characteristics can be combined in any one or more embodiments or examples in a suitable manner.

[0079] The above is only part of the embodiments of the present application, and it should be noted that, for those skilled in the art, other similar implementation means based on the technical idea of the present application can be used without departing from the technical concept of the present application, which also belongs to the protection scope of the embodiments of the present application.

Claims

1. A support device for carrying out a test run of a power system of a substage of a rocket, characterized in that, The support frame comprises a first platform assembly and a plurality of columns which are detachably connected; The plurality of columns are vertically connected to the lower side of the first platform assembly; the first platform assembly comprises a first platform and a bearing frame; the first platform has a first through slot in the center; the bearing frame is annular and detachably connected to the inner circumferential wall of the first through slot; An adapter frame is detachably connected to the lower surface of the bearing frame, and the upper surface of the adapter frame is configured to be detachably connected to the bottom end of the sub-stage power system of the launch vehicle; A tethering tool is detachably connected to one end of the first platform and configured to be detachably connected to the top end of the sub-stage power system of the launch vehicle. The first platform comprises:

2. The support apparatus of claim 1, wherein At least two first sub-platforms, all of which are connected end to end in sequence in a clockwise direction to form a component with the first through slot in the center; A first fixing plate is arranged on the upper surface of the connection between adjacent two first sub-platforms and detachably connected to both of them. The bearing frame comprises at least two sub-bearing frames; all of the sub-bearing frames are connected end to end in sequence in a circumferential direction to form a circular bearing frame; 3. The support device of claim 2, wherein, The circular bearing frame is clamped in the first through slot and at least partially protrudes above the first platform; The number of the sub-bearing frames is equal to the number of the first sub-platforms. The tethering tool comprises:

4. The support device of claim 1, wherein A top cover assembly configured to cover the top end of the sub-stage power system of the launch vehicle; A flexible member detachably connected to one end of the top cover assembly and the other end of the first platform; An adjusting member arranged on the flexible member for adjusting the length of the flexible member. The top cover assembly comprises:

5. The support apparatus of claim 4, wherein A top cover configured to cover the top end of the sub-stage power system of the launch vehicle; A support member fixedly connected to the top end of the top cover and radially arranged with the end protruding beyond the edge of the top cover; One end of the flexible member is detachably connected to the support member. The support frame further comprises:

6. The support device of claim 1, wherein, A horizontal beam arranged between adjacent two columns and detachably connected to both of them at both ends; A first reinforcing beam radially arranged between two adjacent columns and detachably connected to both of them; A second reinforcing beam arranged between adjacent two columns and detachably connected to both of them; at least two second reinforcing beams are symmetrically arranged.

7. The support device of claim 1, wherein, The support frame further comprises: First, second and third support columns which are arranged obliquely towards the first through slot; ​ ​ 8. The support apparatus of claim 6, wherein ​ ​ One end of the first support column, one end of the second support column and one end of the third support column are detachably connected with the column; the other end of the first support column and the other end of the second support column are detachably connected with the first platform; the other end of the third support column is detachably connected with the bottom surface of the carrier frame.

9. The support apparatus of claim 8, wherein, The support frame further comprises a support table; the support table is fixed to the side of the third support column away from the column, and the second platform assembly is detachably connected with the support table.

10. The support device of claim 1, wherein, Further comprising: a first operation platform assembly and a second operation platform assembly; the bottom of the first operation platform assembly is detachably connected with the upper surface of the first platform, the bottom of the second operation platform assembly is fixed on the first operation platform assembly, and the top surface of the second operation platform assembly is not lower than the top end of the sub-stage power system of the launch vehicle.

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