Spaceflight fuel tank tower falling test device

Abstract

The invention discloses a spaceflight fuel tank tower falling test device which comprises a tool frame and an electric vehicle, three guide steel wire ropes are connected between the top end and the bottom end of the interior of the tool frame, a sliding frame is slidably connected to the three guide steel wire ropes, and a simulation tank is installed on the sliding frame. The bottom of the sliding frame is connected with the bottom of the tool frame through an overload acceleration assembly, a lifting ring is connected to the top of the sliding frame, a release hook is connected to the lifting ring, a lifting steel wire rope is connected to the top of the release hook, and the other end of the lifting steel wire rope penetrates through a through hole formed in the top of the tool frame, is guided by a fixed pulley and then is connected with an electric vehicle. According to the invention, the actual environment simulation of the overload acceleration falling state of the simulation storage tank is initiated for the first time, the overload acceleration in the test process is provided by the spring rope connected to the bottom of the simulation storage tank, the release hook is released at the beginning of the test, and the simulation storage tank falls in an accelerated manner under the action of gravity and tension of the spring rope to generate the overload acceleration; and thus, corresponding data is obtained.

Description

Technical Field

[0001] The present invention relates to the technical field of launch vehicles, and particularly relates to a falling tower test device for a space fuel tank. Background Art

[0002] At present, the civilian space field is gradually starting and forming a certain scale. Launch vehicles also happen to have an unprecedented leapfrog development opportunity, which has a wide and in-depth promoting significance for their experimental research. Nowadays, the aviation field is also achieving an unprecedented leapfrog development. Therefore, the development and research progress in the aerospace field are of great significance. Among them, the fuel tank is an important part of the launch vehicle, and the fuel tank needs to undergo a large number of tests before being installed on the rocket to ensure its integrity. In a large number of tests, it is necessary to test the overloaded falling state of the fuel tank, but there is no corresponding equipment for environmental simulation at the present stage, and it is difficult to obtain relevant data, which causes great difficulties to space tests. Summary of the Invention

[0003] The purpose of the present invention is to provide a falling tower test device for a space fuel tank to solve the above problems.

[0004] To solve the above technical problems, the present invention adopts the following technical solutions:

[0005] A falling tower test device for a space fuel tank of the present invention includes a tooling rack and an electric vehicle. Three guiding steel wires are connected between the top end and the bottom end inside the tooling rack. A sliding frame is slidably connected to the three guiding steel wires. A simulated fuel tank is installed on the sliding frame. The bottom of the sliding frame is connected to the bottom of the tooling rack through an overload acceleration component. A lifting ring is connected to the top of the sliding frame. A release hook is connected to the lifting ring. The top of the release hook is connected to a lifting steel wire. The other end of the lifting steel wire passes through a through hole opened at the top of the tooling rack, is guided by a fixed pulley, and is then connected to the electric vehicle.

[0006] Further, a plurality of auxiliary brackets are connected to the side of the lower half of the tooling rack.

[0007] Further, the included angle between two adjacent guiding steel wires is 120°.

[0008] Further, the sliding frame includes two symmetrically arranged circular plates up and down. Three connecting plates are connected to the outer peripheral wall of the circular plate. The included angle between two adjacent connecting plates is 120°. The corresponding connecting plates up and down are connected by a vertical plate. The upper and lower ends of the side of the vertical plate away from the connecting plate are respectively slidably connected to the guiding steel wires. The top end and the bottom end of the simulated fuel tank are respectively connected to the two circular plates up and down. The overload acceleration component is connected to the lower circular plate.

[0009] Further, sliding fasteners are respectively connected to the upper and lower ends of the side of the vertical plate away from the connecting plate, and the guiding steel wire rope is placed between the sliding fasteners and the vertical plate.

[0010] Further, the sliding fasteners are connected to the vertical plate by bolts.

[0011] Further, the circular plate and the connecting plate on the same horizontal plane are of an integrally formed structure.

[0012] Further, the overload acceleration assembly includes a spring rope, one end of the spring rope is connected to the bottom of the tooling rack, and the other end is connected to the bottom surface of the circular plate below.

[0013] Further, the width of one end of the connecting plate close to the circular plate is greater than the width of the other end.

[0014] Further, shock-absorbing sponge is provided at the bottom of the tooling rack.

[0015] Compared with the prior art, the beneficial technical effects of the present invention are as follows:

[0016] The present invention firstly creates an actual simulation of the environment of the falling state of the simulated storage tank with overload acceleration. The overload acceleration during the test is provided by the spring rope connected to the bottom of the simulated storage tank. Before the test, an electric vehicle, a steel wire rope and a fixed pulley are used to lift the simulated storage tank, and at the same time, the spring rope is tightened. When the release hook is released at the start of the test, the simulated storage tank accelerates downward under the action of gravity and the tension of the spring rope, generating overload acceleration, so as to obtain corresponding data, which provides great help for the space industry. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The present invention will be further described below in conjunction with the drawings.

[0018] Figure 1 is a schematic structural diagram of the falling tower test device for the space fuel storage tank of the present invention;

[0019] Figure 2 is Figure 1 the enlarged view at A in

[0020] Figure 3 is the front view of the falling tower test device for the space fuel storage tank of the present invention;

[0021] Figure 4 is a schematic structural diagram of the sliding frame;

[0022] Figure 5 is the top view of the sliding frame;

[0023] Figure 6 is a schematic structural diagram of the sliding fastener;

[0024] Description of reference numerals: 1, tooling rack; 2, electric vehicle; 3, guiding steel wire rope; 4, sliding carriage; 41, circular plate; 42, connecting plate; 43, vertical plate; 5, simulated storage tank; 6, release hook; 7, lifting steel wire rope; 8, fixed pulley; 9, auxiliary support; 10, sliding clamping member; 11, spring rope; 12, shock-absorbing sponge. Detailed implementation mode

[0025] As Figures 1-6 shown, a drop tower test device for a space fuel storage tank includes a tooling rack 1 and an electric vehicle 2. A plurality of auxiliary supports 9 are connected to the side edges of the lower half of the tooling rack 1, and the stability of the tooling rack 1 is improved through the auxiliary supports 9.

[0026] Three guiding steel wire ropes 3 are connected between the top end and the bottom end inside the tooling rack 1, and the included angle between two adjacent guiding steel wire ropes 3 is 120°.

[0027] A sliding carriage 4 is slidably connected to the three guiding steel wire ropes 3. A simulated storage tank 5 is installed on the sliding carriage 4, and the bottom of the sliding carriage 4 is connected to the bottom of the tooling rack 1 through an overload acceleration component.

[0028] As Figures 4-6 shown, the sliding carriage 4 includes two symmetrically arranged circular plates 41 up and down. Three connecting plates 42 are connected to the outer peripheral wall of the circular plate 41, and the included angle between two adjacent connecting plates 42 is 120°. The circular plate 41 and the connecting plate 42 on the same horizontal plane are integrally formed structures, and the width of one end of the connecting plate 42 close to the circular plate 41 is greater than that of the other end. The connecting plates 42 corresponding up and down are connected through a vertical plate 43. The upper and lower ends of the side of the vertical plate 43 away from the connecting plate 42 are respectively slidably connected to the guiding steel wire ropes 3. The top end and the bottom end of the simulated storage tank 5 are respectively connected to the two circular plates 41 up and down, and the overload acceleration component is connected to the lower circular plate 41.

[0029] Sliding clamping members 10 are respectively connected to the upper and lower ends of the side of the vertical plate 43 away from the connecting plate 42. The guiding steel wire rope 3 is placed between the sliding clamping member 10 and the vertical plate 43, and the sliding clamping member 10 is connected to the vertical plate 43 through bolts.

[0030] The overload acceleration component includes a spring rope 11. One end of the spring rope 11 is connected to the bottom of the tooling rack 1, and the other end is connected to the bottom surface of the lower circular plate 41. A downward force is applied to the sliding carriage 4 through the stretched spring rope 11 to make it accelerate and fall, providing an overload acceleration.

[0031] A lifting ring is connected to the top of the carriage 4, and a release hook 6 is connected to the lifting ring. The release hook 6 is a prior art, and its specific structure will not be described in detail here. The top of the release hook 6 is connected to a lifting steel wire rope 7. The other end of the lifting steel wire rope 7 passes through a through hole opened at the top of the tooling rack 1, is guided by a fixed pulley 8, and then is connected to the electric vehicle 2.

[0032] A shock-absorbing sponge 12 is provided at the bottom of the tooling rack 1 to buffer and protect the simulation storage tank 5 through the shock-absorbing sponge 12.

[0033] The operation process of the present invention is as follows:

[0034] During use, the release hook 6 hooks the lifting ring on the top of the carriage 4, and then the electric vehicle 2 is used to pull the lifting steel wire rope 7, so that the carriage 4 drives the simulation storage tank to rise to the top of the tooling rack 1. At the same time, the spring rope 11 is stretched. Then the release hook 6 releases the lifting ring, so that the carriage 4 drives the simulation storage tank to fall. The simulation storage tank accelerates and falls under the action of gravity and the spring rope 11, generating an overload acceleration, and the data is recorded.

[0035] The embodiments described above are only used to describe the preferred mode of the present invention, and do not limit the scope of the present invention. Without departing from the design spirit of the present invention, various deformations and improvements made by those of ordinary skill in the art to the technical solution of the present invention should fall within the protection scope determined by the claims of the present invention.

Claims

1. A falling tower test device for a space fuel tank, characterized in that: It includes a tooling rack (1) and an electric vehicle (2). Between the inner top end and the bottom end of the tooling rack (1), three guiding steel wires (3) are connected. A sliding rack (4) is slidably connected to the three guiding steel wires (3). A simulated storage tank (5) is installed on the sliding rack (4). The bottom of the sliding rack (4) is connected to the bottom of the tooling rack (1) through an overload acceleration component. A lifting ring is connected to the top of the sliding rack (4), and a release hook (6) is connected to the lifting ring. The top of the release hook (6) is connected to a lifting steel wire (7). The other end of the lifting steel wire (7) passes through a through hole opened at the top of the tooling rack (1), is guided by a fixed pulley (8), and is connected to the electric vehicle (2).

2. The space fuel tank drop tower test device according to claim 1, characterized in that: A plurality of auxiliary brackets (9) are connected to the side of the lower half of the tooling rack (1).

3. The space fuel tank drop tower test device according to claim 1, characterized in that: The included angle between two adjacent guiding steel wires (3) is 120°.

4. The space fuel tank drop tower test device according to claim 1, characterized in that: The sliding rack (4) includes two symmetrically arranged circular plates (41) up and down. Three connecting plates (42) are connected to the outer peripheral wall of the circular plate (41). The included angle between two adjacent connecting plates (42) is 120°. The upper and lower corresponding connecting plates (42) are connected by a vertical plate (43). The upper and lower ends of the side of the vertical plate (43) away from the connecting plate (42) are respectively slidably connected to the guiding steel wire (3). The top end and the bottom end of the simulated storage tank (5) are respectively connected to the upper and lower circular plates (41). The overload acceleration component is connected to the lower circular plate (41).

5. The drop tower test device for the aerospace fuel storage tank according to claim 4, characterized in that: Sliding clamping parts (10) are respectively connected to the upper and lower ends of the side of the vertical plate (43) away from the connecting plate (42). The guiding steel wire (3) is placed between the sliding clamping part (10) and the vertical plate (43).

6. The drop tower test device for aerospace fuel storage tanks according to claim 5, characterized in that: The sliding clamping part (10) is connected to the vertical plate (43) by bolts.

7. The drop tower test device for aerospace fuel storage tanks according to claim 6, characterized in that: The circular plate (41) and the connecting plate (42) on the same horizontal plane are of an integrally formed structure.

8. The space fuel tank drop tower test device according to claim 7, characterized in that: The overload acceleration component includes a spring rope (11). One end of the spring rope (11) is connected to the bottom of the tooling rack (1), and the other end is connected to the bottom surface of the lower circular plate (41).

9. The drop tower test device for aerospace fuel storage tanks according to claim 8, characterized in that: The width of one end of the connecting plate (42) close to the circular plate (41) is greater than that of the other end.

10. The space fuel tank drop tower test device according to claim 1, characterized in that: A shock-absorbing sponge (12) is provided at the bottom of the tooling rack (1).

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