A rocket engine test vibration reduction device

Abstract

The present invention relates to the field of liquid rocket engine testing technology, and in particular to a rocket engine test vibration reduction device. The rocket engine test vibration reduction device of the present invention comprises a base and two sets of vibration reduction rod assemblies, one end of the two sets of vibration reduction rod assemblies being movably connected to the two ends of the upper portion of the base, and the other ends of the two sets of vibration reduction rod assemblies extending obliquely upward and being used for movably connecting to the support lugs on the engine. Advantages: simple and reasonable structural design, stable and reliable, small space occupation, high disassembly and assembly efficiency, can effectively reduce vibration during the test process, and ensure that the engine is always in a safe and reliable state during the test process.

Description

Technical Field

[0001] The present invention relates to the technical field of liquid rocket engine testing, and in particular to a rocket engine test vibration reduction device. Background Art

[0002] During the startup and shutdown process of the liquid rocket engine (referred to as the engine) test (referred to as the test run), the gas flow in the nozzle is an uneven non-steady-state process, and the nozzle will be subjected to significant lateral loads. According to the parameters of a certain type of engine, the vibration amplitude of the nozzle outlet during the startup and shutdown process of the 70-ton ground version is currently more than 1000G. The nozzle outlet area of ​​the 70-ton vacuum version engine is larger than that of the ground version, and the vibration environment caused by lateral loads, gas flow during steady-state working process, etc. will be more severe. Since the vacuum version has a large area and is weaker than the overall rigidity of the nozzle, in order to ensure the structural reliability during the ground test run, the engine nozzle needs to be protected by a vibration reduction device.

[0003] At present, the test device does not have a shock-absorbing and protective structure design for the engine nozzle. Generally, a rigid pull rod is connected between the two sides of the nozzle and the crossbeam below. Based on the structural form, rated thrust and other parameters of a certain type of vacuum version liquid rocket engine, the vibration amplitude generated during the test is greater than 1000G; under the action of axial thrust, the entire thrust chamber (including the nozzle) tends to rotate upward around the swing center, which is converted into an angle of about 0.5°. Factors such as the displacement variable of the structural parts will affect the safety of the engine during the test. When the engine is working, the engine nozzle has a large displacement relative to the ground. Therefore, the rigidity of the engine nozzle fixing tooling should not be too large, otherwise the nozzle will be subjected to a large pulling force from the fixing tooling, which will cause damage to the nozzle.

[0004] Based on this, it is necessary to develop a rocket engine test vibration reduction device to overcome the above technical problems. Summary of the Invention

[0005] The technical problem to be solved by the present invention is to provide a rocket engine test vibration reduction device, which effectively overcomes the defects of the prior art.

[0006] The technical solution of the present invention to solve the above technical problems is as follows:

[0007] A rocket engine test vibration reduction device includes a base and two groups of vibration reduction rod assemblies, one end of the two groups of vibration reduction rod assemblies are respectively movably connected to the two ends of the upper part of the base, and the other ends of the two groups of vibration reduction rod assemblies extend obliquely upward and are used for movably connecting with the support ears on the engine.

[0008] On the basis of the above technical solution, the present invention can also be improved as follows.

[0009] Furthermore, the base includes a straight crossbeam, which is arranged horizontally.

[0010] Furthermore, the crossbeam is an I-shaped steel, and a plurality of reinforcing ribs are fixed at intervals along the length direction between the upper and lower webs of the crossbeam.

[0011] Furthermore, the above-mentioned reinforcement ribs are vertically arranged channel steels.

[0012] Furthermore, the above-mentioned vibration damping rod assembly includes a guide rod, a pull rod, a support plate, a connecting plate, a first elastic member and a second elastic member. A cavity is coaxially provided inside one end of the above-mentioned pull rod, one end of the above-mentioned guide rod is inserted into the above-mentioned cavity, one end of the above-mentioned pull rod vertically passes through the above-mentioned connecting plate and is fixed to each other, the above-mentioned guide rod vertically passes through the above-mentioned support plate and is slidably connected to each other, the above-mentioned support plate and the connecting plate are connected by a connecting assembly, the two ends of the above-mentioned guide rod are respectively provided with a first limiting structure and a second limiting structure, the above-mentioned support plate is located between the above-mentioned first limiting structure and the second limiting structure, the above-mentioned first elastic member is connected between the above-mentioned support plate and the above-mentioned first limiting structure, the above-mentioned second elastic member is connected between the above-mentioned support plate and the second limiting structure, the other end of the above-mentioned guide rod is movably connected to the corresponding end of the upper part of the above-mentioned base, and the other end of the above-mentioned pull rod is used for movably connecting to the support ear on the engine.

[0013] Furthermore, the first limiting structure is a limiting ring vertically fixed to the other end of the guide rod, and the second limiting structure is a movable ring slidably sleeved on one end of the guide rod. One end of the guide rod is provided with a thread on the outside and a locking nut is screwed on it.

[0014] Furthermore, the first elastic member and the second elastic member are both disc springs sleeved outside the guide rod.

[0015] Furthermore, the above-mentioned connecting components are provided in multiple groups and are arranged at intervals around the above-mentioned guide rod. The above-mentioned connecting components include connecting bolts, the screws of the above-mentioned connecting bolts sequentially pass through the matching through holes on the above-mentioned connecting plate and the support plate, and the above-mentioned connecting bolts are screwed with locking nuts that abut against both sides of the above-mentioned support plate.

[0016] Furthermore, one end portion of the above-mentioned vibration damping rod assembly is provided with a first screw hole, and is coaxially threadedly connected to a first adjusting screw. The end of the above-mentioned first adjusting screw away from the above-mentioned vibration damping rod assembly is provided with a first ear plate, and the two ends of the upper part of the above-mentioned base are respectively provided with hinged ear seats adapted to the above-mentioned first ear plate. The above-mentioned first ear plate and the above-mentioned hinged ear seat are connected by a first pin shaft passing through the two, and a first fastening nut is screwed on the above-mentioned first adjusting screw.

[0017] Furthermore, a second screw hole is provided at one end portion of the above-mentioned vibration damping rod assembly, and a second adjusting screw is coaxially threadedly connected thereto. A second ear plate is provided at the end of the above-mentioned second adjusting screw away from the above-mentioned vibration damping rod assembly. The second ear plate and the above-mentioned support ear are connected by a second pin shaft passing through the two, and a second fastening nut is screwed on the above-mentioned second adjusting screw.

[0018] The beneficial effects of the present invention are: simple and reasonable structural design, stable and reliable, small space occupation, high disassembly and assembly efficiency, and the ability to effectively reduce vibration during the test run, ensuring that the engine is always in a safe and reliable state during the test run. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 This is a schematic structural diagram of the rocket engine test vibration reduction device of the present invention;

[0020] Figure 2 Schematic diagram of the structure of the vibration reduction rod assembly in the rocket engine test vibration reduction device of the present invention;

[0021] Figure 3 It is a partial cross-sectional view of the vibration reduction rod assembly in the rocket engine test vibration reduction device of the present invention;

[0022] Figure 4 The figure is a schematic structural diagram of the hinged ear seat in the rocket engine test vibration reduction device of the present invention.

[0023] In the accompanying drawings, the components represented by the reference numerals are as follows:

[0024] 1. Base; 2. Vibration damping rod assembly; 3. First adjusting screw; 4. Second adjusting screw; 11. Reinforcing rib; 12. Articulated ear seat; 21. Guide rod; 22. Pull rod; 23. Support plate; 24. Connecting plate; 25. First elastic member; 26. Second elastic member; 27. Connecting assembly; 211. First limiting structure; 212. Second limiting structure; 213. Locking nut; 271. Connecting bolt. DETAILED DESCRIPTION

[0025] The principles and features of the present invention are described below with reference to the accompanying drawings. The examples given are only used to explain the present invention and are not used to limit the scope of the present invention.

[0026] Example: Figures 1 to 4 As shown, the rocket engine test vibration reduction device of this embodiment includes a base 1 and two groups of vibration reduction rod assemblies 2, one end of the two groups of vibration reduction rod assemblies 2 are respectively movably connected to the two ends of the upper part of the above-mentioned base 1, and the other ends of the two groups of vibration reduction rod assemblies 2 are respectively extended obliquely upward and used for movably connecting with the support ears on the engine.

[0027] The rocket engine test vibration reduction device of this embodiment uses two sets of vibration reduction rod assemblies 2 to pull the engine in two directions. When the engine is working, under the action of thrust, when the engine nozzle tilts upward, the two sets of vibration reduction rod assemblies 2 will release the engine nozzle to a certain extent. When the engine nozzle is impacted, it can play a certain damping and buffering role. The vibration reduction rod assembly 2 has a good shock absorption effect, and a certain degree of protection for the engine can be achieved by utilizing this shock absorption effect.

[0028] As a preferred embodiment, the base 1 includes a straight crossbeam, and the crossbeam is horizontally arranged.

[0029] In the above embodiment, the base 1 adopts a crossbeam, which has a simple structure and is easy to install.

[0030] As a preferred embodiment, the crossbeam is an I-shaped steel, and a plurality of reinforcing ribs 11 are fixed at intervals along the length direction between the upper and lower webs of the crossbeam.

[0031] In the above embodiment, the crossbeam is made of existing I-shaped steel material, which is a standard profile and easy to purchase and process. The webs are reinforced by reinforcing ribs 11, so that the structural strength of the entire base 1 is higher and not easy to deform.

[0032] In this embodiment, mounting holes are respectively opened at both ends of the lower web of the crossbeam, and bolts are inserted through the mounting holes to fix and assemble with other carriers, which makes assembly relatively simple.

[0033] In this embodiment, the reinforcing ribs 11 are vertically arranged channel steels. H-shaped steel and channel steels are standard profiles, easy to purchase and process, and have simple shapes, are easy to install, and have good stability.

[0034] As a preferred embodiment, the vibration damping rod assembly 2 includes a guide rod 21, a pull rod 22, a support plate 23, a connecting plate 24, a first elastic member 25 and a second elastic member 26. A cavity is coaxially provided inside one end of the pull rod 22, one end of the guide rod 21 is inserted into the cavity, one end of the pull rod 22 vertically passes through the connecting plate 24, and is connected and fixed to each other, the guide rod 21 vertically passes through the support plate 23, and is slidably connected to each other, the support plate 23 and the connecting plate 24 are connected by a connecting assembly 27, and the guide rod 21 vertically passes through the support plate 23 and is slidably connected to each other, and the support plate 23 and the connecting plate 24 are connected by a connecting assembly 27. A first limiting structure 211 and a second limiting structure 212 are respectively provided at both ends of the guide rod 21. The above-mentioned support plate 23 is located between the above-mentioned first limiting structure 211 and the second limiting structure 212. The above-mentioned first elastic member 25 is connected between the above-mentioned support plate 23 and the above-mentioned first limiting structure 211, and the above-mentioned second elastic member 26 is connected between the above-mentioned support plate 23 and the second limiting structure 212. The other end of the above-mentioned guide rod 21 is movably connected to the corresponding end of the upper part of the above-mentioned base 1, and the other end of the above-mentioned pull rod 22 is used to be movably connected to the support ear on the engine.

[0035] In the above embodiment, a piston-type structure is formed between the guide rod 21 and the pull rod 22 (one end of the guide rod 21 is inserted into the cavity at one end of the pull rod 22, and the two are coaxially distributed). During the engine test, the vibration and displacement of the engine body are transmitted to the vibration reduction device, causing relative movement between the guide rod 21 and the pull rod 22. The first elastic member 25 and the second elastic member 26 are continuously compressed and released through the connecting plate 24, the connecting assembly 27 and the support plate 23. During the compression and elongation of the first elastic member 25 and the second elastic member 26, the vibration energy is effectively released, thereby achieving the purpose of protecting the engine. The entire structure adopts a long straight connecting rod docking structure, which is simple in structure, small in size, and easy to disassemble and assemble. It also effectively suppresses the vibration frequency of the entire engine and the impact of the nozzle. Overall, the connecting rod docking is simple in structure, small in size, and easy to disassemble and assemble.

[0036] More specifically, when the engine nozzle tilts upward under thrust, it compresses the first elastic member 25 and the second elastic member 26, releasing the nozzle to a certain degree of displacement. The first and second elastic members 25 and 26 have a certain degree of rigidity, providing a certain degree of damping and buffering when the engine nozzle is impacted.

[0037] As a preferred embodiment, the first limiting structure 211 is a limiting ring vertically fixed to the other end of the guide rod 21, and the second limiting structure 212 is a movable ring slidably sleeved on one end of the guide rod 21. One end of the guide rod 21 is provided with a thread on the outside and a locking nut 213 is screwed on.

[0038] In the above embodiment, the elastic compression strength of the first elastic member 25 and the second elastic member 26 can be adjusted by pre-tightening the locking nut 213, thereby better coordinating the engine test and reducing the vibration amplitude.

[0039] In this embodiment, both the first elastic member 25 and the second elastic member 26 are disc springs sleeved around the guide rod 21, providing a more stable installation and more consistent elastic performance. Furthermore, the disc spring combination facilitates adjustment of compression force, enabling better coordination with engine testing and reducing vibration amplitude and impact.

[0040] It should be noted that in this embodiment, the number of disc springs is determined based on the displacement of the engine nozzle and the tension of the damper rod assembly 2. Specifically, taking the example of a nozzle displacement of approximately 8 mm along the long axis of the damper rod assembly 2 in the free state, if a rigid tie rod is used, the axial force of the tie rod is approximately 30,980 N. In this embodiment, after adding the damper rod assembly 2, the axial force of the tie rod is linearly related to the nozzle displacement. Assuming the final axial force of the tie rod is 10,000 N, the axial displacement of the tie rod is 8-10,000 × 8 / 30,985 = 5.4 mm. Therefore, the disc spring stiffness is 10,000 / 5.4 = 1846 N / mm. Assuming a disc spring stiffness of 2,000 N / mm, the corresponding disc spring specifications are determined by consulting the tool manual, and the number of disc springs is determined by using a dorsal-ventral stacking method.

[0041] As a preferred embodiment, the above-mentioned connecting components 27 are provided in multiple groups and are arranged at intervals around the above-mentioned guide rod 21. The above-mentioned connecting components 27 include connecting bolts 271. The screws of the above-mentioned connecting bolts 271 sequentially pass through the matching through holes on the above-mentioned connecting plate 24 and the support plate 23. The above-mentioned connecting bolts 271 are screwed with locking nuts that are against both sides of the above-mentioned support plate 23.

[0042] In the above embodiment, the provision of multiple groups of connecting components 27 makes the connection between the connecting plate 24 and the support plate 23 relatively stable. At the same time, the transmission of the force of the first elastic member 25 and the second elastic member 26 is also relatively stable, so that the entire vibration damping rod assembly 2 can have relatively stable shock absorbing performance.

[0043] As a preferred embodiment, one end of the damping rod assembly 2 is provided with a first screw hole, and is coaxially threadedly connected to a first adjusting screw 3, and the end of the first adjusting screw 3 away from the damping rod assembly 2 is provided with a first ear plate (indicated by a in the figure), and both ends of the upper part of the base 1 are respectively provided with hinged ear seats 12 (such as Figure 4 As shown, this product belongs to the prior art), the first ear plate and the hinged ear seat 12 are connected via a first pin that passes through the two, and a first fastening nut is screwed onto the first adjusting screw 3.

[0044] In the above embodiment, bolts are respectively installed at both ends of the upper part of the base 1 to assemble the articulated ear seat 12, and the first adjusting screw 3 is installed at one end of the vibration damping rod assembly 2 in a threaded connection manner. The first adjusting screw 3 can be stably articulated with the articulated ear seat 12 through the first ear plate and the first pin shaft. At the same time, the first adjusting screw 3 can fine-tune the length to a certain extent, which can be more convenient during the installation process.

[0045] In this embodiment, mounting holes are provided at both ends of the upward side of the base 1 (i.e., both ends of the upper web) for hinged ear seats 12, and several mounting holes are provided at the downward side (i.e., the lower web) for its own fixation.

[0046] As a preferred embodiment, one end portion of the above-mentioned vibration damping rod assembly 2 is provided with a second screw hole, and is coaxially threadedly connected to a second adjusting screw 4. The second adjusting screw 4 is provided with a second ear plate (indicated by b in the figure) at the end away from the above-mentioned vibration damping rod assembly 2. The second ear plate and the above-mentioned support ear are connected by a second pin shaft passing through the two, and a second fastening nut is screwed on the above-mentioned second adjusting screw 4.

[0047] In the above embodiment, the other end of the vibration damping rod assembly 2 is installed with a second adjusting screw 4 in a threaded connection manner. The second adjusting screw 4 can be stably hinged with the support ear through the second ear plate and the second pin shaft. At the same time, the second adjusting screw 4 can fine-tune the length to a certain extent, which can be more convenient during the installation process, and the tension state after installation is also more appropriate.

[0048] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like to indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0049] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of the technical features being referred to. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "plurality" means at least two, such as two, three, etc., unless otherwise specifically defined.

[0050] In the present invention, unless otherwise specified or limited, the terms "installed," "connected," "connect," "fixed," etc. should be understood in a broad sense. For example, they can refer to fixed connection, detachable connection, or integration; mechanical connection, electrical connection; direct connection, or indirect connection through an intermediate medium; internal communication between two components, or interaction between two components, unless otherwise specified. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on specific circumstances.

[0051] In the present invention, unless otherwise expressly specified or limited, when a first feature is "above" or "below" a second feature, it may mean that the first and second features are in direct contact, or that the first and second features are in indirect contact through an intermediary. Furthermore, when a first feature is "above," "above," or "above" a second feature, it may mean that the first feature is directly above or diagonally above the second feature, or simply means that the first feature is at a higher level than the second feature. When a first feature is "below," "below," or "below" a second feature, it may mean that the first feature is directly below or diagonally below the second feature, or simply means that the first feature is at a lower level than the second feature.

[0052] In the description of this specification, the reference terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" mean that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art can combine and combine different embodiments or examples described in this specification and features of different embodiments or examples without contradiction.

[0053] Although the embodiments of the present invention have been shown and described above, it will be understood that the above embodiments are illustrative and are not to be construed as limitations on the present invention. A person skilled in the art may change, modify, replace and modify the above embodiments within the scope of the present invention.

Claims

1. A rocket engine test vibration reduction device, characterized by: The invention comprises a base (1) and two groups of vibration damping rod assemblies (2), one end of the two groups of vibration damping rod assemblies (2) are respectively movably connected to the two ends of the upper part of the base (1), and the other ends of the two groups of vibration damping rod assemblies (2) are respectively extended obliquely upward and used for movably connecting with the ear seats on both sides of the engine nozzle; the vibration damping rod assembly (2) comprises a guide rod (21), a pull rod (22), a support plate (23), a connecting plate (24), a first elastic member (25) and a second elastic member (26), one end of the pull rod (22) is coaxially provided with a cavity inside, and one end of the guide rod (21) is inserted into the cavity. One end of the pull rod (22) vertically passes through the connecting plate (24) and is connected and fixed to each other. The guide rod (21) vertically passes through the support plate (23) and is slidably connected to each other. The support plate (23) and the connecting plate (24) are connected via a connecting assembly (27). The two ends of the guide rod (21) are respectively provided with a first limiting structure (211) and a second limiting structure (212). The support plate (23) is located between the first limiting structure (211) and the second limiting structure (212). The support plate (23) and the first limiting structure (211) are connected. The first elastic member (25) is connected, the second elastic member (26) is connected between the support plate (23) and the second limiting structure (212), the other end of the guide rod (21) is movably connected to the corresponding end of the upper part of the base (1), and the other end of the pull rod (22) is used to be movably connected to the support ear on the engine; the first limiting structure (211) is a limiting ring vertically fixed to the other end of the guide rod (21), and the second limiting structure (212) is a movable ring slidably sleeved on one end of the guide rod (21), and one end of the guide rod (21) is provided with a thread on the outside. A locking nut (213) is screwed on, and the elastic compression force of the first elastic member (25) and the second elastic member (26) can be adjusted by screwing the locking nut (213) to pre-tighten, thereby reducing the vibration amplitude; the connecting assembly (27) is provided with multiple groups, and is spaced around the guide rod (21), and the connecting assembly (27) includes a connecting bolt (271), the screw of the connecting bolt (271) sequentially passes through the matching through holes on the connecting plate (24) and the support plate (23), and the connecting bolt (271) is screwed with a locking nut that abuts against both sides of the support plate (23).

2. A rocket engine test vibration reduction device according to claim 1, characterized in that: The base (1) comprises a straight crossbeam, and the crossbeam is arranged horizontally.

3. The rocket engine test vibration reduction device according to claim 2, characterized in that: The crossbeam is an I-shaped steel, and a plurality of reinforcing ribs (11) are fixed at intervals along the length direction between the upper and lower webs of the crossbeam.

4. The rocket engine test vibration reduction device according to claim 3, characterized in that: The reinforcing ribs (11) are vertically arranged channel steels and are welded and fixed to the upper and lower webs.

5. The rocket engine test vibration reduction device according to claim 1, characterized in that: The first elastic member (25) and the second elastic member (26) are both disc springs sleeved outside the guide rod (21).

6. A rocket engine test vibration reduction device according to any one of claims 1 to 5, characterized in that: One end of the vibration damping rod assembly (2) is provided with a first screw hole and is coaxially threadedly connected to a first adjusting screw (3); an end of the first adjusting screw (3) away from the vibration damping rod assembly (2) is provided with a first ear plate; both ends of the upper portion of the base (1) are respectively provided with hinged ear seats (12) adapted to the first ear plate; the first ear plate and the hinged ear seat (12) are connected by a first pin shaft passing through the two; and a first fastening nut is screwed on the first adjusting screw (3).

7. A rocket engine test vibration reduction device according to any one of claims 1 to 5, characterized in that: One end of the vibration damping rod assembly (2) is provided with a second screw hole, and is coaxially threadedly connected to a second adjusting screw (4); an end of the second adjusting screw (4) away from the vibration damping rod assembly (2) is provided with a second ear plate, and the second ear plate is connected to the support ear via a second pin shaft passing through the two, and a second fastening nut is screwed on the second adjusting screw (4).

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