Reusable lower stage simulation counterweight device for rocket interstage separation ground test

Abstract

A reusable lower stage simulation counterweight device for a rocket interstage separation ground test belongs to the technical field of carrier rockets, compresses the preparation period of repeated simulation of an interstage separation test of a rocket shell and saves the test cost, and specifically comprises a front end socket simulation piece, the shell, an upper roller, a lower roller, a speed brake, a water tank, a guide rail and a track, the front end socket simulation piece is consistent with a real rocket lower stage engine front end socket in aerodynamic shape, and the diameter, the weight and the mass center characteristics of a shell are consistent with the real lower stage of an actually verified rocket. The front end socket simulation piece is connected with the front end of the shell; adapter blocks are welded on the left and right sides of the shell; the upper roller, the lower roller and the speed brake are respectively connected with the adapter blocks; the upper roller and the lower roller are slidably engaged with the track; the water tank and the guide rail are connected to the track, and the track can adjust the levelness and the alignment degree with a test wind tunnel by installing a gasket at the bottom of the track. In the test process, the shell slides along the track; after entering the water tank under the constraint effect of the guide rail, the speed reducing plate is used for reducing speed.

Description

Technical Field

[0001] The invention relates to a reusable lower stage simulation counterweight device for rocket stage separation ground test and a test method, belonging to the technical field of launch vehicles. Background Art

[0002] In order to reduce the ineffective mass of the structure and improve the carrying efficiency, launch vehicles generally adopt a multi-stage engine series design. During flight, the lower stage engine ignites first, and after the fuel is consumed, the interstage separation is carried out, the lower stage is thrown away, and the upper stage engine is started at the same time for the subsequent flight of the rocket. Interstage separation has the characteristics of large instantaneous load, complex internal flow field, and strong mechanical and thermal coupling, and is one of the key links in the overall design of the rocket.

[0003] In the existing technology, the cost of conducting inter-stage separation tests is high and the test cycle is long, which does not match the actual needs. Summary of the invention

[0004] The technical problem to be solved by the present invention is to provide a reusable lower-stage simulation counterweight device for ground tests of rocket stage separation, so that when a ground test of rocket stage separation is carried out using a test wind tunnel (such as a shock wave wind tunnel or a blast wave tunnel), the test pieces can be reliably reused, while the repeated test preparation cycle is compressed and the test cost is saved.

[0005] The purpose of the present invention is achieved through the following technical solutions: A reusable lower stage simulation counterweight device for rocket stage separation ground test, including a front head simulation part, a shell, an upper roller, a lower roller, a deceleration plate, a water tank, a guide rail, and a track; The front head simulation part is consistent with the aerodynamic shape of the front head of the real lower stage engine of the rocket, and the diameter, weight and center of mass characteristics of the shell are consistent with the actual verified real lower stage of the rocket; the front head simulation part is connected to the front end of the shell; Adapter blocks are welded on the left and right sides of the shell, and the upper roller, lower roller and deceleration plate are respectively connected to the adapter blocks; the upper roller, lower roller and track can be slidably engaged; The flume and rails are connected to a track, which can be adjusted for levelness and alignment with the test wind tunnel by installing shims on its bottom; During the test, the shell slides along the track; when the speed brake enters the water tank under the constraint of the guide rail, it is used to slow down.

[0006] In one embodiment of the present invention, the front head simulation component is connected to the front end of the shell by using a plurality of axial bolts so as to adapt to the front head simulation components with different aerodynamic shapes.

[0007] In one embodiment of the present invention, the water tank and the guide rail are formed by welding steel plates.

[0008] In one embodiment of the present invention, the rail itself is formed by integral welding.

[0009] In one embodiment of the present invention, the water tank and the guide rail are connected to the track by welding.

[0010] In one embodiment of the present invention, the upper roller, the lower roller and the speed reducer are respectively connected to the adapter block by bolts.

[0011] A method for simulating interstage separation based on the above-mentioned rocket interstage separation ground test, which can reuse the lower stage simulation counterweight device, comprises: Before the test, the front head simulation parts, shell, upper roller, lower roller and speed reducer are assembled to form the lower stage assembly; Lift the assembly onto the track to ensure that the upper roller, lower roller and track are properly engaged; adjust the levelness of the assembly by installing gaskets at the bottom of the track and align its central axis with the central axis of the test wind tunnel; then adjust the front and rear position of the assembly on the track to make it in the position to be connected; Lift the interstage to be tested, connect the front part of the interstage to the test wind tunnel, push the assembly forward along the track, and use bolts to connect the front head simulation part on the assembly to the rear part of the interstage to be tested; Adjust the speed brake to the correct position to ensure that when the assembly moves backward, the speed brake will rotate into the water tank under the constraint of the guide rail; inject a certain amount of water into the water tank, and at the same time prepare the interstage separation test in the test wind tunnel; The test wind tunnel is started, the test interstage is separated, and the assembly moves backward along the track under the action of aerodynamic load; the speed brake is constrained by the guide rail, rotates a certain angle and enters the water tank; the speed brake generates resistance when encountering water, causing the assembly to slow down until it stops completely.

[0012] In one embodiment of the present invention, after the assembly comes to a complete stop, the speed brake is flipped upwards to check the assembly. If there is no abnormality, the assembly is pushed forward along the track to the position to be connected in preparation for the next test.

[0013] Compared with the prior art, the present invention has the following beneficial effects: (1) The present invention adopts a scheme of using a sliding track to push the lower stage simulated counterweight assembly to move after the test is started, so that under the equivalent test simulation condition, the lower stage simulated counterweight assembly will not fall to the ground due to gravity after separation, and at the same time, its movement speed characteristics can be analyzed.

[0014] (2) The present invention uses the resistance generated by the movement of the deceleration plate in the water tank to gradually decelerate the lower stage assembly after the test, thereby reducing the impact of the lower stage assembly during deceleration, avoiding structural deformation during impact, and avoiding the problem of the lower stage assembly needing to be repaired due to structural deformation during repeated tests.

[0015] (3) The upper stage simulation part of the present invention is connected to the shell by bolts, and can be adapted to different upper stage simulation parts to simulate the aerodynamic shape of the lower stage front head during the separation between different launch vehicle stages, thereby increasing the test realism. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 A schematic diagram of the shell.

[0017] Figure 2 Schematic diagram of the following level assembly.

[0018] Figure 3 This is a schematic diagram of the speed brake.

[0019] Figure 4 Schematic diagram of interstage separation test.

[0020] Figure 5 This is a schematic diagram of the lower-stage assembly and track installation.

[0021] Figure 6 This is a partial schematic diagram of the guide rail.

[0022] Figure numerals: front head simulation part-1, shell-2, upper roller-3, lower roller-4, speed reducer-5, water tank-6, guide rail-7, track-8. DETAILED DESCRIPTION

[0023] In order to make the objectives, technical solutions and advantages of the present invention more clear, the embodiments of the present invention will be further described in detail below with reference to the accompanying drawings.

[0024] In order to fully verify the interstage separation technical solution, the present invention provides a rocket interstage separation ground test reusable lower stage simulation counterweight device and test method. During the test, the rocket interstage shell is installed at the nozzle outlet of the test wind tunnel (see Figure 4 ), using the test wind tunnel to simulate the flow field in the interstage section when the upper stage engine is ignited. In order to complete the test, it is necessary to develop a simulated counterweight device for the lower stage of the rocket, which can simulate the shape, weight and center of mass of the actual lower stage. During the test, the test wind tunnel is started to simulate the ignition jet of the upper stage engine. Subsequently, the interstage section is cut, the connection between the upper and lower stages is released, and the simulated counterweight device of the lower stage moves axially backward under the action of the jet, simulating the separation characteristics of the lower stage during actual flight.

[0025] A lower stage simulation counterweight device that can be reused for a ground test of rocket stage separation comprises a front head simulation component 1, a shell 2, an upper roller 3, a lower roller 4, a deceleration plate 5, a water tank 6, a guide rail 7, and a track 8.

[0026] The front head simulation part 1 is consistent with the aerodynamic shape of the front head of the real lower stage engine, so as to simulate as much as possible the flow field in the interstage section after the jet of the upper stage engine hits the front head of the lower stage during the real interstage separation.

[0027] Shell 2 is the main structure of the lower stage simulation counterweight device. Its diameter, weight and center of mass characteristics are consistent with the actual lower stage of the rocket verified in practice. Figure 1 The front head simulation part 1 is connected to the front end of the shell 2 by multiple axial bolts to adapt to the front head simulation part 1 with different aerodynamic shapes; adapter blocks (such as Figure 2 ), the upper roller 3, the lower roller 4 and the deceleration plate 5 are respectively connected to the adapter block by bolts, and the deceleration plate 5 is as shown in Figure 3 shown.

[0028] The water tank 6 and the guide rail 7 are welded by steel plates and connected to the track 8 by welding. Figure 6 As shown, the rail 8 itself is formed by integral welding, and the horizontality and the alignment with the test wind tunnel can be adjusted by installing spacers at the bottom.

[0029] The working principle of the present invention is as follows: 1. Before the test, the front head simulation part 1, the shell 2, the upper roller 3, the lower roller 4, and the deceleration plate 5 are assembled on the ground to form a lower stage assembly, such as Figure 2 2. Lift the assembly in step 1 onto the track 8, as shown in FIG. Figure 5 As shown, ensure that the upper roller 3 and the lower roller 4 are correctly engaged with the track 8; 3. By installing a gasket at the bottom of the track 8, reasonably adjust the horizontality of the assembly and align its central axis with the central axis of the test wind tunnel, then adjust the front and rear positions of the assembly on the track 8 to make it in the position to be connected; 4. Hoist the interstage section to be tested, connect the front part of the interstage section to the test wind tunnel, push the assembly forward along the track 8, and use bolts to connect the front head simulation part 1 on the assembly to the rear of the interstage section to be tested; 5. Adjust the speed brake 5 to the correct position to ensure that the speed brake 5 will be on the guide when the assembly moves backward. 6. A certain amount of water is injected into the water tank 6, and the test wind tunnel is prepared for the interstage separation test; 7. The test wind tunnel is started, the interstage section under test is separated, and the assembly moves backward along the track 8 under the action of the aerodynamic load; 8. The deceleration plate 5 is constrained by the guide rail 7 and rotates a certain angle to enter the water tank 6; 9. The deceleration plate 5 generates resistance when encountering water, which slows down the assembly until it stops completely; 10. Turn the deceleration plate 5 upwards and check the condition of the assembly. If there is no abnormality, push the assembly forward along the track 8 to the position to be connected, and prepare for the next test.

[0030] The contents not described in detail in the specification of the present invention belong to the common knowledge of those skilled in the art.

[0031] Although the present invention has been disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

Claims

1. A reusable lower stage simulation counterweight device for rocket stage separation ground test, characterized in that: It comprises a front head simulation component (1), a shell (2), an upper roller (3), a lower roller (4), a speed reducer (5), a water tank (6), a guide rail (7), and a track (8); The front head simulation component (1) is consistent with the aerodynamic shape of the front head of the real rocket lower stage engine, and the diameter, weight and center of mass characteristics of the shell (2) are consistent with the actual verified real rocket lower stage; the front head simulation component (1) is connected to the front end of the shell (2); Adapter blocks are welded on the left and right sides of the housing (2); the upper roller (3), the lower roller (4) and the deceleration plate (5) are respectively connected to the adapter blocks; the upper roller (3), the lower roller (4) and the track (8) are slidably engaged; The water tank (6) and the guide rail (7) are connected to the track (8), and the track (8) can be adjusted in level and alignment with the test wind tunnel by installing a spacer on the bottom of the track (8); During the test, the housing (2) slides along the track (8); when the deceleration plate (5) enters the water tank (6) under the restraining action of the guide rail (7), it is used to decelerate.

2. The rocket inter-stage separation ground test reusable lower stage simulation counterweight device according to claim 1, characterized in that: The front head simulation component (1) is connected to the front end of the shell (2) by using a plurality of axial bolts so as to adapt to front head simulation components (1) with different aerodynamic shapes.

3. The rocket inter-stage separation ground test reusable lower stage simulation counterweight device according to claim 1, characterized in that: The water tank (6) and the guide rail (7) are formed by welding steel plates.

4. The rocket inter-stage separation ground test reusable lower stage simulation counterweight device according to claim 1, characterized in that: The rail (8) itself is formed by integral welding.

5. The rocket inter-stage separation ground test reusable lower stage simulation counterweight device according to claim 1, characterized in that: The water tank (6) and the guide rail (7) are connected to the track (8) by welding.

6. The rocket inter-stage separation ground test reusable lower stage simulation counterweight device according to claim 1, characterized in that: The upper roller (3), the lower roller (4) and the speed reducer (5) are respectively connected to the adapter block via bolts.

7. A method for simulating interstage separation based on the rocket interstage separation ground test method of claim 1, which can reuse the lower stage simulation counterweight device, characterized in that: include: Before the test, the front head simulation component (1), the shell (2), the upper roller (3), the lower roller (4), and the speed reducer (5) are assembled to form a lower stage assembly; The assembly is hoisted onto the track (8) to ensure that the upper roller (3), the lower roller (4) and the track (8) are properly engaged; a gasket is installed at the bottom of the track (8) to adjust the horizontality of the assembly and align its central axis with the central axis of the test wind tunnel; and then the front and rear positions of the assembly on the track (8) are adjusted to be in a position to be connected; Lift the interstage section to be tested, connect the front part of the interstage section to the test wind tunnel, push the assembly forward along the track (8), and use bolts to connect the front head simulation component (1) on the assembly to the rear part of the interstage section to be tested; Adjust the speed brake (5) to the correct position to ensure that when the assembly moves backward, the speed brake (5) will rotate into the water tank (6) under the restraining action of the guide rail (7); inject a certain amount of water into the water tank (6) to prepare for the interstage separation test; The test wind tunnel is started, the interstage to be tested is separated, and the assembly moves backward along the track (8) under the action of aerodynamic load; the deceleration plate (5) rotates a certain angle under the restraining action of the guide rail (7) and enters the water tank (6); the deceleration plate (5) generates resistance when encountering water, causing the assembly to slow down until it stops completely.

8. The inter-stage separation simulation test method according to claim 7, characterized in that: After the assembly comes to a complete stop, the deceleration plate (5) is turned upwards to check the assembly. If there is no abnormality, the assembly is pushed forward along the track (8) to the position to be connected, ready for the next test.

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