A rocket engine rack test device

Abstract

The application belongs to the field of structural test loading design, and particularly relates to a rocket engine frame test device. The device comprises a loading platform (1), a stand column (2), an actuating cylinder (3) and a supporting platform (6). The stand column (2) is arranged between the loading platform (1) and the supporting platform (6) to form a loading space between the loading platform (1) and the supporting platform (6). The actuating cylinder (3) has a plurality of fixed ends connected to the loading platform (1). The telescopic end of the actuating cylinder (3) is located in the loading space and is hinged at a top loading point (501) of a test piece (5). A bottom supporting point (503) of the test piece (5) is fixed to the supporting platform (6). The application has simple, clear and explicit load transmission, can guarantee the accuracy of loading, has simple structure, is easy to realize and can be widely used in structural tests.

Description

TECHNICAL FIELD

[0001] The application belongs to the field of structural test loading design, and particularly relates to a rocket engine frame test device. BACKGROUND

[0002] The engine frame of a rocket is usually a truss structure, is used for connecting an engine and a rocket body, is a key component of the rocket, and is a main load-bearing structure. The engine frame bears a large load, and the total load of part of the engine frame exceeds 500 tons. In order to ensure sufficient rigidity and strength of the structure, rigidity test and strength verification test need to be performed during development.

[0003] The engine frame of a large-thrust rocket is large in size, and an ordinary pressure testing machine cannot provide sufficient space for the test piece. In addition, the engine frame has several loading points, and each point is loaded obliquely (the load direction forms an angle with the axis of the engine). Therefore, the test cannot be performed on the pressure testing machine. Since the test piece bears a large load, the constraint force of the test piece is also large. However, the ground rail of an ordinary test site can usually only provide a constraint force of about 20 tons / m 2 . Therefore, it is very difficult to directly constrain the test piece to the ground rail. SUMMARY

[0004] In order to solve the above technical problems, in view of the large size of the engine frame, and the test requirements such as large test load and multi-point loading, the application provides a test device capable of rigidity measurement and strength verification.

[0005] The rocket engine frame test device provided by the application is used for loading a test piece simulating an engine frame. The test piece is enclosed into a frame structure by connecting rods. The intersection of the top end connecting rods of the test piece forms a loading point, and the intersection of the bottom end connecting rods of the test piece forms a support point. The test device comprises a loading platform, a column, an actuating cylinder, and a support platform. The column is arranged between the loading platform and the support platform, and is used for forming a loading space between the loading platform and the support platform. The actuating cylinder has a plurality of fixed ends connected to the loading platform. The extension end of the actuating cylinder is located in the loading space and is hinged at the top end loading point of the test piece. The bottom end support point of the test piece is fixed to the support platform.

[0006] Preferably, the column and the loading platform are connected by bolts, and the column and the support platform are connected by bolts.

[0007] Preferably, the loading platform is composed of a plurality of horizontal and vertical frame beams, the support platform is composed of a plurality of horizontal and vertical frame beams, and the frame beams are reinforced by a plurality of reinforcing plates.

[0008] Preferably, the fixed end of the actuating cylinder is provided with a first double lug, which is adapted to be hingedly connected with a first single lug, and the first single lug is fixed on the lower end face of the loading platform by means of a bolt.

[0009] Preferably, the telescopic end of the actuating cylinder is provided with a second double lug, which is adapted to be hingedly connected with a second single lug, and the second single lug is fixed at the top loading point of the test piece.

[0010] Preferably, a connecting hole is arranged at the support point of the bottom end of the test piece, and a bolt mounting hole corresponding to the connecting hole is arranged on the end face of the support platform, and the support point of the bottom end of the test piece is crimped on the end face of the support platform and fastened by means of a bolt.

[0011] Preferably, a gasket is arranged between the support point of the bottom end of the test piece and the end face of the support platform.

[0012] Preferably, the connecting rod of the test piece is in a circular, I-shaped or channel-shaped structure.

[0013] The present application realizes the stiffness test and strength verification of the rocket engine frame, overcomes the problem of large size of the test piece, and solves the problems of large load and multi-point oblique loading in the test. The device has the advantages of simple, clear and clear load transmission, can ensure the accuracy of loading, the test device structure is simple, easy to realize, and can be widely used in structural tests. BRIEF DESCRIPTION OF DRAWINGS

[0014] Figure 1 is a test device structure schematic diagram of a preferred embodiment of the test device of the present application.

[0015] Figure 2 is a test piece structure schematic diagram.

[0016] Among them, 1 is a loading platform, 2 is a stand, 3 is an actuating cylinder, 4 is a second single lug, 5 is a test piece, 501 is a loading point, 502 is a connecting rod, 503 is a support point, 6 is a support platform, 7 is a first single lug, and 8 is a gasket. DETAILED DESCRIPTION

[0017] For the purpose of making the objectives, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. Identical or similar reference numerals are used to represent identical or similar elements or elements having identical or similar functions throughout the drawings. The described embodiments are part of the embodiments of the present application, rather than all the embodiments of the present application. The embodiments described below with reference to the drawings are exemplary and are intended to explain the present application, and cannot be understood as a limitation of the present application. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative work fall within the scope of protection of the present application. The embodiments of the present application will be described in detail below with reference to the drawings.

[0018] The present application provides a rocket engine mount test device for loading a test piece 5 simulating an engine mount, referring to Figure 2 , the test piece 5 is enclosed into a frame structure by connecting rods 502, the intersection of the top end connecting rods 502 of the test piece 5 forms a loading point 501, and the intersection of the bottom end connecting rods 502 of the test piece forms a support point 503, referring to Figure 1 , the test device comprises a loading platform 1, a column 2, an actuator cylinder 3, and a support platform 6, the column 2 is arranged between the loading platform 1 and the support platform 6 to form a loading space between the loading platform 1 and the support platform 6, the actuator cylinder 3 has a plurality of fixed ends connected to the loading platform 1, and the telescopic end of the actuator cylinder 3 is located in the loading space and is hinged at the top end loading point 501 of the test piece 5, and the bottom end support point 503 of the test piece 5 is fixed on the support platform 6.

[0019] In some alternative embodiments, the column 2 and the loading platform 1 are connected by bolts, and the column 2 and the support platform 6 are connected by bolts. The loading platform 1 mainly bears bending load in the test, and in order to ensure the safe and smooth progress of the test, the loading platform 1 needs to have sufficient strength and bending stiffness, and for the same reason, the support platform 6 mainly provides support for the test piece 5, and the support platform 6 mainly bears bending load in the test, and in order to ensure the safety of the test, the support platform 6 needs to have sufficient strength and bending stiffness. Therefore, in this embodiment, the column 2 is connected to the support platform 6 and the loading platform 1 by bolts, and in the alternative embodiment, the column 2 can be welded to one of the support platform 6 and the loading platform 1, and detachably connected (bolted) to the other.

[0020] In some alternative embodiments, the loading platform 1 is formed by a plurality of transverse and longitudinal frame beams, the support platform 6 is formed by a plurality of transverse and longitudinal frame beams, and the frame beams are reinforced by a plurality of reinforcing plates. This embodiment reduces the weight of the loading platform 1 and the support platform 6 by frame beams, and at the same time, the strength of the loading platform 1 and the support platform 6 is reinforced by the reinforcing plates, so that the loading platform 1 and the support platform 6 have sufficient strength and bending stiffness. In alternative embodiments, the column 2 mainly bears axial force, is also a frame beam structure, and is reinforced by a triangular plate at the connection with the loading platform 1 and the support platform 6.

[0021] In some alternative embodiments, the fixed end of the actuator cylinder 3 is provided with a first double lug, which is adapted to be hingedly connected with a first single lug 7, and the first single lug 7 is fixed on the lower end face of the loading platform 1 by a bolt. In some alternative embodiments, the telescopic end of the actuator cylinder 3 is provided with a second double lug, which is adapted to be hingedly connected with a second single lug 4, and the second single lug 4 is fixed at the top loading point 501 of the test piece 5 by a bolt.

[0022] In the above embodiments, the single-double lug structure enables the loading of the actuator cylinder 3 to be free from constraints in other directions, and the position of the actuator cylinder in the loading platform 1 is determined by the loading angle, the length of the actuator cylinder, and the pre-elongation of the actuator cylinder. The actuator cylinder 3 is the main equipment for applying load to the test piece, and there are a total of four in the figure, and the number can be adjusted according to the test requirements. In order to ensure the safety of the test, the connecting bolt between the second single lug 4 and the test piece 5 needs to be determined according to the size of the load.

[0023] In some alternative embodiments, the bottom end of the test piece 5 is provided with a connecting hole at the support point 503, the end face of the support platform 6 is provided with a bolt mounting hole corresponding to the connecting hole, and the bottom end of the test piece 5 is crimped on the end face of the support platform 6 and connected by a bolt.

[0024] In some alternative embodiments, in order to avoid interference between the truss of the test piece 5 and the support platform, a gasket 8 is arranged between the support point 503 of the bottom end of the test piece 5 and the end face of the support platform 6.

[0025] In some alternative embodiments, the connecting rod 502 of the test piece 5 is a part of the test piece, mainly bears axial force, and has a circular, I-shaped or channel-shaped structure.

[0026] The test piece, the support platform, the actuator cylinder, the loading platform and the column of the present application form a self-balancing system, and no constraint needs to be applied to the system. Compression or stretching load is applied to the test piece 5 by controlling the elongation or contraction of the actuator cylinder 3.

[0027] The above merely provides the specific implementation of the present application, but the protection scope of the present application is not limited to this. Any person skilled in the art can easily think of the changes or replacements within the technical range disclosed by the present application, which should be covered in the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. A rocket engine mount testing device for loading a test piece (5) simulating an engine mount, wherein the test piece (5) is a frame structure formed by connecting rods (502), a loading point (501) is formed at the intersection of the top connecting rods (502) of the test piece (5), and a support point (503) is formed at the intersection of the bottom connecting rods (502) of the test piece, characterized in that, The test apparatus includes a loading platform (1), a column (2), an actuator (3), and a support platform (6). The column (2) is positioned between the loading platform (1) and the support platform (6) to form a loading space between the loading platform (1) and the support platform (6). There are multiple actuators (3). The fixed end of each actuator (3) is connected to the loading platform (1). The telescopic end of the actuator (3) is located in the loading space and is hinged to the top loading point (501) of the test piece (5). The bottom support point (503) of the test piece (5) is fixed to the support platform (6).

2. The rocket engine mount test apparatus as described in claim 1, characterized in that, The column (2) is connected to the loading platform (1) by bolts, and the column (2) is connected to the support platform (6) by bolts.

3. The rocket engine mount test apparatus as described in claim 1, characterized in that, The loading platform (1) is composed of multiple horizontal and vertical frame beams, and the support platform (6) is composed of multiple horizontal and vertical frame beams, which are reinforced by multiple reinforcing plates.

4. The rocket engine mount test apparatus as described in claim 1, characterized in that, The fixed end of the actuator (3) has a first double lug and a first single lug (7) is adapted to be hinged. The first single lug (7) is fixed to the lower end face of the loading platform (1) by bolts.

5. The rocket engine mount test apparatus as described in claim 1, characterized in that, The telescopic end of the actuating cylinder (3) has a second double lug and a second single lug (4) which is adapted to be hinged. The second single lug (4) is fixed to the top loading point (501) of the test piece (5) by bolts.

6. The rocket engine mount test apparatus as described in claim 1, characterized in that, A connection hole is provided at the support point (503) at the bottom end of the test piece (5), and a bolt mounting hole corresponding to the connection hole is provided on the end face of the support platform (6). The support point (503) at the bottom end of the test piece (5) is pressed against the end face of the support platform (6) and fastened with bolts.

7. The rocket engine mount test apparatus as described in claim 6, characterized in that, A gasket (8) is provided between the support point (503) at the bottom of the test piece (5) and the end face of the support platform (6).

8. The rocket engine mount test apparatus as described in claim 1, characterized in that, The connecting rod (502) of the test piece (5) has a circular, I-shaped or groove-shaped cross section.

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