CN219714748U - Support structure for carrier rocket power system test vehicle - Google Patents

Abstract

The embodiment of the utility model provides a support structure for a carrier rocket power system test vehicle, which comprises a support frame and a thrust frame; the support frame comprises a top frame and four upright posts; the top frame is horizontally arranged and is provided with a square hollow structure; the thrust frame comprises a main bearing ring, an adapter frame and a plurality of connecting supporting legs arranged at the front end and the rear end of the main bearing ring; the inner side ends of the connecting support legs are fixedly connected with the main bearing ring, and the outer side ends of the connecting support legs are detachably connected with the top frame; the middle part of the main bearing ring is provided with a circular opening; the switching frame is of a circular ring structure; the transfer frame is connected with the main bearing ring through a circular opening; the upper surface of the adapter frame is connected with a carrier rocket power system. According to the technical scheme, the supporting structure is designed into a split structure, so that the transportation is convenient, and the problem that the supporting structure for the existing carrier rocket power system test vehicle is difficult to transport is solved.

Description

Support structure for carrier rocket power system test vehicle

Technical Field

The utility model relates to the technical field of rocket engine testing, in particular to a support structure for a carrier rocket power system test vehicle.

Background

The test run of the rocket power system is an important component of the development work of a novel rocket, and aims to simulate the working flow of the rocket in a flying state, test the reliability and coordination of systems on the rocket such as an engine, a propulsion system and the like, and provide a basis for predicting and solving the problems possibly generated in flying. The supporting structure is a load carrier for rocket power system test, and needs to bear various loads such as rocket thrust, wind power, impact and the like in the test process.

The inventor finds that at least the following problems exist in the prior art:

at present, the existing support structures for the carrier rocket power system test vehicle are all integrated processing structures, and belong to oversized parts, the size and the weight are very large, and the carrier rocket power system test vehicle is difficult to transport in use and the like, and is difficult to transfer between different test sites. Therefore, how to realize a support structure for a carrier rocket power system test vehicle which is easy to transfer and transport is a problem to be solved.

Disclosure of Invention

The embodiment of the utility model provides a support structure for a carrier rocket power system test car, which is used for solving the problem that the existing support structure for the carrier rocket power system test car is difficult to transfer and transport.

In order to achieve the above purpose, the embodiment of the utility model provides a support structure for a carrier rocket power system test vehicle, which comprises a support frame and a thrust frame; the support frame comprises a top frame and a plurality of upright posts vertically connected below the top frame; the top frame is horizontally arranged, and the middle part of the top frame is provided with a hollow structure; the thrust frame comprises a main bearing ring, an adapter frame and a plurality of connecting supporting legs, wherein the main bearing ring, the adapter frame and the connecting supporting legs are horizontally arranged; the inner side ends of the connecting support legs are fixedly connected with the main bearing ring, and the outer side ends of the connecting support legs are detachably connected with the top frame; the upper surface of the main bearing ring is lower than the lower surface of the top frame, and the lower surface of the main bearing ring is higher than the bottom end surface of the upright post; the middle part of the main bearing ring is provided with a circular opening; the switching frame is of a circular ring structure; the transfer frame is connected with the main bearing ring through a circular opening; the upper surface of the adapter frame is connected with a carrier rocket power system.

Further, the main bearing ring comprises a left half ring and a right half ring which are oppositely arranged; the right end face of the left semi-ring is attached to the left end face of the right semi-ring, and the left semi-ring and the right semi-ring are mirror images along the attaching face; the left half ring and the right half ring are detachably connected.

Further, the support structure for the carrier rocket power system test vehicle further comprises a plurality of inclined supports distributed left and right; the outer side end of the inclined support is detachably connected with the top frame; the inner side end of the inclined support positioned on the right side is detachably connected with the right semi-ring, and the inner side end of the inclined support positioned on the left side is detachably connected with the left semi-ring; the outer side end of the inclined support is higher than the inner side end of the inclined support.

Further, the outer side ends of the connecting support legs are connected with the top frame in a threaded mode; the left half ring and the right half ring are connected in a threaded manner; the outer side end of the inclined support is connected with the top frame in a threaded manner; the inner side end of the inclined support positioned at the left side is connected with the left semi-ring in a threaded manner; the inner side end of the inclined support positioned on the right side is connected with the right semi-ring in a threaded mode.

Further, the top frame comprises two main beams which are arranged in parallel and two auxiliary beams which are arranged between the two main beams; each auxiliary beam is vertically arranged with the main beam, and two ends of each auxiliary beam are fixedly connected with the inner side surface of the main beam respectively; the outer side ends of the connecting support legs are connected with the main beam.

Furthermore, the connecting support leg is of a step-shaped structure with a high outer side end and a low inner side end; the connecting support leg comprises an upper support leg plate, a lower support leg plate and a support leg vertical plate, wherein the upper support leg plate and the lower support leg plate are arranged in parallel, and the support leg vertical plate is fixedly connected between the upper support leg plate and the lower support leg plate.

Further, a reinforcement is fixedly arranged between the connecting support leg and the main bearing ring; the reinforcement includes triangular reinforcing ribs and rectangular reinforcing tubes.

Further, the top frame is a box-type beam structure consisting of an upper beam plate, a lower beam plate and a vertical beam plate; the upper beam plate and the lower beam plate are arranged at intervals in a horizontal mode; the upper end of the vertical beam plate is fixedly connected with the lower side surface of the upper beam plate, and the lower end of the vertical beam plate is fixedly connected with the upper side surface of the lower beam plate.

Further, the adapter frame is connected with the main bearing ring through a long bolt; the threaded end of each long bolt is provided with a nut; the outer side of the long bolt is also sleeved with a porous gasket; every three adjacent long bolts share a porous gasket.

Further, a positioning pin is arranged between the left half ring and the right half ring; and the left half ring and the right half ring are provided with positioning pin holes matched with the positioning pins.

The technical scheme has the following beneficial effects:

according to the technical scheme, the support structure for the carrier rocket power system test vehicle is designed to be a split type structure, so that the main bearing ring is detachably connected with the support frame through the connecting support legs, the inclined support and the like, the main bearing ring can be split into a left part and a right part, when the field transfer is required, the whole support structure can be split into a plurality of small parts and transferred in batches, the transportation difficulty and the requirement on a transfer vehicle are reduced, and the support structure can be put into use again after being assembled to a target field, so that the problem that the existing similar products are difficult to transfer is solved.

In addition, the utility model has the following characteristics:

through the optimally designed connecting structure, the strength of the support structure for the carrier rocket power system test vehicle is greatly improved, and more test requirements are met. After the technical scheme is adopted, the ultimate bearing capacity of the support structure for the rocket power system test car can reach 600t, the bearing capacity of similar products is selected, the rocket power system test car with the diameter of 3800mm or less can be compatible with the test car requirement, and the application range is wider.

Drawings

In order to more clearly illustrate the embodiments of the present utility model or the technical solutions in the prior art, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present utility model, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.

FIG. 1 is a schematic view of a support structure for a test vehicle of a launch vehicle power system according to an embodiment of the present utility model;

FIG. 2 is a schematic top view of a thrust frame in accordance with an embodiment of the present utility model;

FIG. 3 is a schematic view of a supporting frame according to an embodiment of the present utility model;

FIG. 4 is a schematic view of a connecting leg structure according to an embodiment of the present utility model;

FIG. 5 is a schematic view showing the construction of a top frame in an embodiment of the present utility model;

FIG. 6 is a schematic view of the bottom structure of a thrust frame in an embodiment of the utility model;

FIG. 7 is a schematic view of the left half ring and right half ring connection in an embodiment of the present utility model;

reference numerals: 1. a top frame; 2. a column; 3. a main load-bearing ring; 4. a transfer frame; 5. connecting the supporting legs; 6. a diagonal support; 7. a porous gasket; 11. a main beam; 12. an auxiliary beam; 31. a left half ring; 32. a right half ring; 33. a fixed ear; 34. a positioning device; 36. a main bearing ring reinforcing rib; 51. an upper leg plate; 52. a lower leg plate; 53. a landing leg vertical plate; 54. reinforcing ribs; 55. reinforcing the pipe; 111. an upper beam plate; 112. a lower beam plate; 113. and (5) erecting a beam plate.

Detailed Description

The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.

As shown in fig. 1, an embodiment of the present utility model provides a support structure for a test vehicle of a carrier rocket power system, including a support frame and a thrust frame; the support frame comprises a square top frame 1 and four upright posts 2 vertically connected below the top frame 1; the top frame 1 is horizontally arranged, and the middle part of the top frame 1 is provided with a square hollow structure; the thrust frame comprises a main bearing ring 3, an adapter frame 4 and a plurality of connecting supporting legs 5 which are horizontally arranged and are arranged at the front end and the rear end of the main bearing ring 3; the inner side ends of the connecting support legs 5 are fixedly connected with the main bearing ring 3, and the outer side ends of the connecting support legs 5 are detachably connected with the top frame 1; the upper surface of the main bearing ring 3 is lower than the lower surface of the top frame 1, and the lower surface of the main bearing ring 3 is higher than the bottom end surface of the upright post 2; the middle part of the main bearing ring 3 is provided with a circular opening; the adapter rack 4 is of a circular ring structure; the adapter bracket 4 is connected with the main bearing ring 3 through a circular opening; the upper surface of the adapter frame 4 is connected with a carrier rocket power system.

In order to solve the foregoing problems, in the present utility model, the support structure is divided into two parts, namely a support frame and a thrust frame. The adapter rack 4 in the thrust rack is a part connected with the rocket body and is a part directly bearing load, plays a role of adapting the rocket power system and the main bearing ring 3, and can be replaced according to rocket sizes of different specifications. The adapter bracket 4 is formed by welding upper and lower end face circular ring sheet metal parts with circular vertical plates and triangular ribs, and is required to be integrally processed and is indistinct. The main bearing ring 3 is used for fixing the adapter bracket 4, the main bearing ring 3 is detachably connected with the supporting frame through the connecting supporting legs 5, and meanwhile, the adapter bracket 4 also plays a role in reinforcing the main bearing ring 3. Before transferring and transporting, the whole thrust frame part can be separated from the supporting frame by detaching the connecting supporting leg 5 from the supporting frame, so that the supporting frame and the thrust frame can be transported respectively, and the transportation difficulty and the bearing requirement on a transportation tool are reduced. The support frame is the civil engineering part, contains the roof-rack 1 at four stands 2 and top, wherein, before using, need with the foundation buries the latter half of stand 2 in order to obtain reliable fixed deeply underground.

The installation form of thrust frame and support frame is: the upper surface of the connecting support leg 5 of the thrust frame is in butt joint with the lower surface of the top frame 1, and because the thrust is upward after the rocket power system is ignited, when the force is transmitted to the connecting support leg 5, the whole structure of the connecting support leg 5 can be ensured to bear the thrust, and then the thrust is transmitted to the top frame 1. If the lower end face of the connecting support leg 5 is in butt joint with the upper end face of the top frame 1, after upward thrust is transmitted to the positions of the connecting support leg 5 and the top frame 1, the corresponding thrust is mainly born by the connecting bolts, and the connecting form is not preferable. In addition, the connecting bolt of the connecting support leg 5 and the top frame 1 is required to be customized to process a long bolt, so that the long bolt can penetrate through the top frame 1 and the connecting support leg 5, then penetrates out of the lower end face of the connecting support leg 5, and then the double nuts are screwed.

Further, the main bearing ring 3 comprises a left half ring 31 and a right half ring 32 which are oppositely arranged; the right end face of the left half ring 31 is attached to the left end face of the right half ring 32, and the left half ring 31 and the right half ring 32 are mirror images along the attaching face; the left half ring 31 is detachably connected to the right half ring 32.

In order to further reduce the weight of the parts and facilitate transportation, the main bearing ring 3 can also be designed into a split structure. As shown in fig. 2 and 7, the main bearing ring 3 is formed by splicing a left half ring 31 and a right half ring 32, and the front end and the rear end of the left half ring 31 and the right half ring 32 are respectively provided with symmetrically arranged fixing lugs 33, after the left half ring 31 and the right half ring 32 are spliced, the fixing lugs 33 on the left side and the right side are connected together through connecting bolts, so that the left half ring 31 and the right half ring 32 are fixed. Meanwhile, for stability, four main bearing ring reinforcing ribs 36 are respectively arranged on the upper side and the lower side surfaces of the left half ring 31 and the right half ring 32, and the main bearing ring reinforcing ribs 36 are respectively connected with the left half ring 31 and the right half ring 32 in a threaded connection mode. The left half ring 31 and the right half ring 32 are respectively formed by welding an upper sheet metal part, a lower sheet metal part, a plurality of vertical plates and reinforcing ribs.

Further, the support structure for the carrier rocket power system test vehicle further comprises a plurality of inclined supports 6 distributed left and right; the outer side end of the inclined support 6 is detachably connected with the top frame 1; the inner side end of the inclined support 6 positioned on the right side is detachably connected with the right semi-ring 32, and the inner side end of the inclined support 6 positioned on the left side is detachably connected with the left semi-ring 31; the outer end of the diagonal brace 6 is higher than the inner end of the diagonal brace 6.

After the thrust frame and the support frame are assembled, the inclined support 6 can be further installed so as to strengthen the structural integrity of the thrust frame. Wherein the inclined support 6 is in bolt connection with the thrust frame and the supporting frame (the outer side end of the inclined support 6 is connected to the inner side surface of the auxiliary beam 12).

Further, the outer ends of the connecting support legs 5 are connected with the top frame 1 in a threaded manner; the left half ring 31 and the right half ring 32 are connected in a threaded manner; the outer side end of the inclined support 6 is connected with the top frame 1 in a threaded manner; the inner side end of the inclined support 6 positioned at the left side is connected with the left semi-ring 31 in a threaded manner; the inner end of the diagonal brace 6 on the right side is connected with the right half ring 32 in a threaded manner.

In order to facilitate processing and use, the detachable connection mode in the utility model adopts a threaded connection mode. For example, as shown in fig. 1, the assembling mode of the thrust frame and the support frame is that the upper outer side end (the higher end) of the connecting support leg 5 in the thrust frame is in butt joint with the lower end surface of the top frame 1 (the main beam 11), long bolts penetrate through the main beam 11 and the connecting support leg 5, the tail ends of the bolts penetrate out of the lower end surface of the connecting support leg 5, finally, nuts are used for tightening, and if necessary, hydraulic wrenches are used for fastening and anti-loosening. The bolt materials used in the technical scheme are all 30CrMnSi, and the strength grade is 12.9.

Further, the top frame 1 includes two main beams 11 arranged in parallel, and two auxiliary beams 12 disposed between the two main beams 11; each auxiliary beam 12 is vertically arranged with the main beam 11, and two ends of each auxiliary beam 12 are respectively fixedly connected with the inner side surface of the main beam 11; the outer ends of the connecting legs 5 are connected with the main beams 11.

As shown in fig. 3, since the main load ring 3 is directly connected to the main girder 11, the main girder 11 bears a main load, and thus the cross-sectional size of the main girder 11 should be greater than that of the sub-girder 12.

Furthermore, the connecting support leg 5 is of a step-shaped structure with a high outer side end and a low inner side end; the connecting leg 5 includes an upper side leg plate 51 and a lower side leg plate 52 arranged in parallel, and a leg standing plate 53 fixedly connected between the upper side leg plate 51 and the lower side leg plate 52.

The main function of the connection support leg 5 is to convert the bending stress born by the thrust frame into tensile stress, because the structural form of the support structure for the test vehicle of the carrier rocket power system is a typical simply supported beam form, the structure of the connection support leg 5 is designed into the form shown in fig. 4 according to stress analysis, the connection support leg is formed by welding an upper support leg plate 51 and a lower support leg plate 52 together with a support leg vertical plate 53, and finally, a triangular rib is welded at the lower part of the connection support leg 5 for strengthening treatment.

Further, a reinforcement is fixedly arranged between the connecting support leg 5 and the main bearing ring 3; the reinforcement includes triangular ribs 54 and rectangular tubes 55.

As shown in fig. 2, four connecting legs 5 are fixedly connected with the main bearing ring 3 in a welding mode, and after welding, reinforcing pipes 55 and reinforcing ribs 54 are selected to reinforce the welding position. After the rectangular reinforcing pipe 55 is required to be placed vertically to the welding seam, one end of the rectangular reinforcing pipe is welded on the surface of the connecting supporting leg 5, and the other end of the rectangular reinforcing pipe is welded on the surface of the main bearing ring 3. Four rectangular reinforcing pipes 55 are arranged on the upper and lower end surfaces of the thrust frame.

Further, the top frame 1 is a box-type beam structure composed of an upper beam plate 111, a lower beam plate 112 and a vertical beam plate 113; the upper beam plate 111 and the lower beam plate 112 are arranged at intervals in a horizontal manner; the upper end of the vertical beam plate 113 is fixedly connected with the lower side surface of the upper beam plate 111, and the lower end of the vertical beam plate 113 is fixedly connected with the upper side surface of the lower beam plate 112.

As shown in fig. 5, the main beam 11 and the auxiliary beam 12 each adopt a box beam structure formed by an upper beam plate 111, a lower beam plate 112 and a vertical beam plate 113, so that the strength can be improved to the greatest extent while the weight is reduced. The main beam 11 and the auxiliary beam 12 are connected with the upright post 2 by adopting a mode of firstly bolting and then welding. The upright post 2 adopts a reverse-U-shaped cross-section structural form with a large amount of hollow space, and the hollow part is formed by pouring steel bars, bolts and concrete. Meanwhile, the outer surface of the overground part of the upright post 2 is required to be coated with refractory cement or aerogel for isolation and protection treatment.

Further, the adapter bracket 4 is connected with the main bearing ring 3 through long bolts; the threaded end of each long bolt is provided with a nut; the outer side of the long bolt is also sleeved with a porous gasket 7; every three adjacent long bolts share a porous pad 7.

As shown in fig. 6, the adapter bracket 4 is assembled with the main bearing ring 3 by long bolts which pass through the lower end face of the adapter bracket 4 and the entire main bearing ring 3, then pass out from the lower end face of the main bearing ring 3, and are assembled with porous gaskets 7, and each three or more bolts are a group of common porous gaskets 7. The purpose of adopting the design of porous gasket 7 is in order to change the point atress into the face atress back and act on main load ring 3 to this improves bolted connection tightness, afterwards, adopt double nut to screw up can, adopts hydraulic wrench to screw up locking treatment if necessary.

Further, a positioning pin is further disposed between the left half ring 31 and the right half ring 32; the left half ring 31 and the right half ring 32 are provided with positioning pin holes matched with the positioning pins.

Before the left half ring 31 and the right half ring 32 are connected, in order to achieve accurate positioning, a positioning device 34 may be respectively provided for the left half ring 31 and the right half ring 32, each positioning device 34 is provided with a positioning pin hole, and the positioning pin holes on the left half ring 31 and the right half ring 32 are relatively arranged. Before connection, the positioning devices 34 on the left half ring 31 and the right half ring 32 are connected together through the connection of the positioning pins and the positioning pin holes, then the main bearing ring reinforcing ribs 36 are installed, and finally the fixing lugs 33 on the left side and the right side are connected together through the connecting bolts, so that the fixed connection of the left half ring 31 and the right half ring 32 is completed.

In addition, in the manufacturing process, it should be noted that after the welding of the connecting support legs 5 and the main bearing ring 3 is completed, the upper surfaces of the four connecting support legs 5 are integrally processed by taking the upper surface of the main bearing ring 3 as a reference, so as to ensure certain flatness and parallelism requirements, and further meet the perpendicularity requirements of the rocket power system and the thrust frame after the butt joint.

In the foregoing detailed description, various features are grouped together in a single embodiment for the purpose of streamlining the disclosure. This method of disclosure is not to be interpreted as reflecting an intention that the claimed embodiments of the subject matter require more features than are expressly recited in each claim. Rather, as the following claims reflect, utility model lies in less than all features of a single disclosed embodiment. Thus the following claims are hereby expressly incorporated into this detailed description, with each claim standing on its own as a separate preferred embodiment of this utility model.

The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present utility model. As will be apparent to those skilled in the art; various modifications to these embodiments will be readily apparent, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the disclosure. Thus, the present disclosure is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

The foregoing description of the embodiments has been provided for the purpose of illustrating the general principles of the utility model, and is not meant to limit the scope of the utility model, but to limit the utility model to the particular embodiments, and any modifications, equivalents, improvements, etc. that fall within the spirit and principles of the utility model are intended to be included within the scope of the utility model.

Claims (10)

1. The support structure for the test vehicle of the carrier rocket power system is characterized by comprising a support frame and a thrust frame;

the supporting frame comprises a top frame (1) and a plurality of upright posts (2) vertically connected below the top frame (1), wherein the top frame (1) is horizontally arranged, and the middle part of the top frame (1) is provided with a hollow structure;

the thrust frame comprises a main bearing ring (3), an adapter frame (4) and a plurality of connecting support legs (5) which are horizontally arranged and are arranged at the front end and the rear end of the main bearing ring (3);

the inner side end of the connecting support leg (5) is fixedly connected with the main bearing ring (3), and the outer side end of the connecting support leg (5) is detachably connected with the top frame (1);

the upper surface of the main bearing ring (3) is lower than the lower surface of the top frame (1), the lower surface of the main bearing ring (3) is higher than the bottom end surface of the upright post (2), and a circular opening is formed in the middle of the main bearing ring (3);

the transfer frame (4) is of a circular ring structure, the transfer frame (4) is connected with the main bearing ring (3) through the circular opening, and the upper surface of the transfer frame (4) is connected with a carrier rocket power system.

2. Support structure for a test vehicle of a launch vehicle power system according to claim 1, wherein said main load-carrying ring (3) comprises a left half-ring (31) and a right half-ring (32) arranged opposite each other; the right end face of the left half ring (31) is attached to the left end face of the right half ring (32), and the left half ring (31) and the right half ring (32) are mirror images along the attaching face; the left half ring (31) and the right half ring (32) are detachably connected.

3. A support structure for a launch vehicle power system test vehicle according to claim 2, further comprising a plurality of diagonal braces (6) distributed left and right; the outer side end of the inclined support (6) is detachably connected with the top frame (1); the inner side end of the inclined support (6) positioned on the right side is detachably connected with the right semi-ring (32), and the inner side end of the inclined support (6) positioned on the left side is detachably connected with the left semi-ring (31); the outer side end of the inclined support (6) is higher than the inner side end of the inclined support (6).

4. A support structure for a test vehicle of a launch vehicle power system according to claim 3, characterized in that the outer ends of the connecting legs (5) are screwed to the roof frame (1); the left half ring (31) and the right half ring (32) are connected in a threaded mode; the outer side end of the inclined support (6) is connected with the top frame (1) in a threaded mode; the inner side end of the inclined support (6) positioned at the left side is connected with the left semi-ring (31) in a threaded manner; the inner side end of the inclined support (6) positioned on the right side is connected with the right semi-ring (32) in a threaded mode.

5. A support structure for a test vehicle of a launch vehicle power system according to claim 1, wherein said roof frame (1) comprises two main beams (11) arranged in parallel, and two auxiliary beams (12) arranged between two of said main beams (11); each auxiliary beam (12) is vertically arranged with the main beam (11), and two ends of each auxiliary beam (12) are fixedly connected with the inner side surface of the main beam (11) respectively; the outer side ends of the connecting support legs (5) are connected with the main beam (11).

6. Support structure for a test vehicle of a launch vehicle power system according to claim 1, characterized in that said connecting legs (5) are of stepped structure with high outside and low inside; the connecting support leg (5) comprises an upper support leg plate (51) and a lower support leg plate (52) which are arranged in parallel, and a support leg vertical plate (53) fixedly connected between the upper support leg plate (51) and the lower support leg plate (52).

7. Support structure for a test vehicle of a launch vehicle power system according to claim 6, characterized in that a reinforcement is also fixedly arranged between the connecting leg (5) and the main bearing ring (3); the reinforcement includes triangular ribs (54) and rectangular reinforcing tubes (55).

8. The support structure for a test vehicle of a carrier rocket power system according to claim 1, wherein the top frame (1) is a box-type beam structure consisting of an upper beam plate (111), a lower beam plate (112) and a vertical beam plate (113); the upper beam plate (111) and the lower beam plate (112) are arranged at intervals in a horizontal manner; the upper end of the vertical beam plate (113) is fixedly connected with the lower side face of the upper beam plate (111), and the lower end of the vertical beam plate (113) is fixedly connected with the upper side face of the lower beam plate (112).

9. Support structure for a test vehicle of a launch vehicle power system according to claim 1, wherein said adapter bracket (4) is connected to said main load ring (3) by means of long bolts; a nut is arranged at the threaded end of each long bolt; a porous gasket (7) is sleeved outside the long bolt; each three adjacent long bolts share one porous pad (7).

10. Support structure for a test vehicle of a launch vehicle power system according to claim 2, characterized in that between said left half-ring (31) and said right half-ring (32) there are also provided positioning pins; and the left half ring (31) and the right half ring (32) are provided with positioning pin holes matched with the positioning pins.