Rocket engine test run damping device

Abstract

The invention relates to the technical field of liquid rocket engine testing, in particular to a rocket engine test run damping device. The rocket engine test run damping device comprises a base and two sets of damping rod assemblies, one ends of the two sets of damping rod assemblies are movably connected with the two ends of the upper portion of the base respectively, and the other ends of the two sets of damping rod assemblies extend upwards in an inclined mode respectively and are used for being movably connected with supporting lugs on an engine. The device has the advantages of being simple, reasonable, stable and reliable in structural design, small in occupied space, high in disassembly and assembly efficiency and capable of effectively reducing vibration in the test run process and guaranteeing that an engine is in a safe and reliable state all the time in the test run process.

Description

Technical Field

[0001] The 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 start-up and shutdown process of the liquid rocket engine (engine for short) test (test run for short), there is an uneven non-steady-state process in the flow of gas in the nozzle, 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 start-up and shutdown process of the 70-ton ground version is currently over 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 and gas flow during steady-state working 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 protection structure design for the engine nozzle. Generally, a rigid pull rod is connected between the two sides of the nozzle and the beam below. Based on the structural form, rated thrust and other parameters of a certain type of vacuum version of 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 comprises 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] Based on the above technical solution, the present invention can also be improved as follows.

[0009] Furthermore, the base comprises a straight crossbeam, and the crossbeam is arranged horizontally.

[0010] Furthermore, the cross beam 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 cross beam.

[0011] Furthermore, the above-mentioned reinforcing 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 penetrates the above-mentioned connecting plate, and is connected and fixed to each other, the above-mentioned guide rod vertically penetrates 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 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 mounted on one end of the guide rod. One end of the guide rod is provided with a thread on the outside and is screwed with a locking nut.

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

[0017] Furthermore, a second screw hole is provided at one end 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 one end of the above-mentioned second adjusting screw away from the above-mentioned vibration damping rod assembly. The second ear plate is connected to the above-mentioned support ear by a second pin shaft passing through the two. 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 It is a structural schematic diagram of the rocket engine test vibration reduction device of the present invention;

[0020] Figure 2 It is a structural schematic diagram 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 It 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 listed as follows:

[0024] 1. Base; 2. Vibration damping rod assembly; 3. First adjusting screw; 4. Second adjusting screw; 11. Reinforcing ribs; 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 in conjunction with 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 ends 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 utilizes 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 degree of displacement. When the engine nozzle receives impact, it can play a certain damping and buffering role. The vibration reduction rod assembly 2 has a good shock absorbing effect, and a certain degree of protection for the engine can be achieved by utilizing this shock absorbing effect.

[0028] As a preferred embodiment, the base 1 comprises 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 cross beam 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 cross beam.

[0031] In the above embodiment, the cross beam is made of existing I-beam steel material, which is a standard profile and is 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 cross beam, and bolts are inserted through the mounting holes to fix and assemble with other carriers, so the assembly is relatively simple.

[0033] In this embodiment, the reinforcing ribs 11 are vertically arranged channel steels. H-shaped steels and channel steels are standard profiles, easy to purchase and process, simple in shape, easy to install, and relatively stable.

[0034] As a preferred embodiment, the 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. 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 penetrates the connecting plate 24 and is connected and fixed to each other. The guide rod 21 vertically penetrates 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. A first limiting structure 211 and a second limiting structure 212 are respectively provided at both ends of the guide rod 21, the support plate 23 is located between the first limiting structure 211 and the second limiting structure 212, the first elastic member 25 is connected between the support plate 23 and the first limiting structure 211, 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 for movably connecting to the support ear on the engine.

[0035] In the above embodiment, there is a piston structure 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, and the vibration energy is effectively released during the compression and elongation of the first elastic member 25 and the second elastic member 26, thereby 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, and the vibration frequency of the entire engine and the impact of the nozzle are effectively suppressed. On the whole, the connecting rod docking is adopted, which is simple in structure, small in size, and easy to disassemble and assemble.

[0036] More specifically, under the action of thrust, when the engine nozzle tilts upward, the first elastic member 25 and the second elastic member 26 will be compressed, and the engine nozzle will be displaced and released to a certain extent. The first elastic member 25 and the second elastic member 26 have a certain rigidity, and can play a certain damping and buffering role 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 mounted 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, so as to better cooperate with the engine test and reduce the vibration amplitude.

[0039] In this embodiment, the first elastic member 25 and the second elastic member 26 are both disc springs sleeved outside the guide rod 21, which are more stable to install and exert elastic performance. In addition, the disc spring combination is easy to adjust the compression force, which can better cooperate with the engine test and reduce the vibration amplitude and impact.

[0040] It should be noted that: in this embodiment, the number of disc springs is determined according to the displacement of the engine nozzle and the tension of the damping rod assembly 2. Specifically, taking the displacement of the nozzle along the long axis direction of the damping rod assembly 2 in the free state of about 8mm as an example, if a rigid pull rod is used, the axial force of the pull rod is about 30980N. In this embodiment, after adding the damping rod assembly 2, the axial force of the pull rod is linearly related to the nozzle displacement, and assuming that the final axial force of the pull rod is 10000N, the axial displacement of the pull rod is 8-10000×8 / 30985=5.4mm, so the stiffness of the disc spring is 10000 / 5.4=1846N / mm, and the stiffness of the disc spring is 2000N / mm, and then the tool manual is consulted to determine the corresponding specifications of the disc spring, and the number of disc springs is determined by the dorsal and ventral superposition combination method.

[0041] As a preferred embodiment, the above-mentioned connecting assembly 27 is provided with multiple groups and is arranged at intervals around the above-mentioned guide rod 21. The above-mentioned connecting assembly 27 includes a connecting bolt 271, and the screw rod of the above-mentioned connecting bolt 271 sequentially passes through the matching through holes on the above-mentioned connecting plate 24 and the support plate 23. The above-mentioned connecting bolt 271 is screwed with a locking nut that abuts 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 supporting 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 a 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 with 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, the product belongs to the prior art), the first ear plate and the hinged ear seat 12 are connected via a first pin that runs through the two, and the first adjusting screw 3 is screwed with a first fastening nut.

[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 belly plate) for hinged ear seats 12, and a plurality of mounting holes are provided at the downward side (i.e., the lower belly plate) for its own fixation.

[0046] As a preferred embodiment, a second screw hole is provided at one end of the above-mentioned vibration damping rod assembly 2, and a second adjusting screw 4 is coaxially threadedly connected thereto. A second ear plate (indicated by b in the figure) is provided at one end of the above-mentioned vibration damping rod assembly 2, and the second ear plate is connected to the above-mentioned support ear 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 is to 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”, etc., indicating orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element 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] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In the description of the present invention, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0050] In the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0051] In the present invention, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may mean that the first and second features are in direct contact, or the first and second features are in indirect contact through an intermediate medium. Moreover, a first feature being "above", "above" or "above" a second feature may mean that the first feature is directly above or obliquely above the second feature, or simply means that the first feature is higher in level than the second feature. A first feature being "below", "below" or "below" a second feature may mean that the first feature is directly below or obliquely below the second feature, or simply means that the first feature is lower in level than the second feature.

[0052] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" etc. means 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 may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, without contradiction.

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

Claims

1. A rocket engine test vibration reduction device, Features: It 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) extend obliquely upward and are used for movably connecting to the ear seats on both sides of the engine nozzle.

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

3. A rocket engine test vibration reduction device according to claim 2, Features: The cross beam 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 cross beam.

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

5. A rocket engine test vibration reduction device according to claim 1, Features: 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); 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 penetrates the connecting plate (24) and is connected and fixed to each other; the guide rod (21) vertically penetrates 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 guide rod (21) ) are respectively provided with a first limiting structure (211) and a second limiting structure (212) at both ends of the base (1), the support plate (23) is located between the first limiting structure (211) and the second limiting structure (212), the first elastic member (25) is connected between the support plate (23) and the first limiting structure (211), 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 for movably connecting to the support ear on the engine.

6. A rocket engine test vibration reduction device according to claim 5, Features: 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 is screwed with a locking nut (213).

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

8. A rocket engine test vibration reduction device according to claim 5, Features: The connection assembly (27) is provided with a plurality of groups and is arranged at intervals around the guide rod (21). The connection assembly (27) includes a connection bolt (271). The screw rod of the connection bolt (271) sequentially passes through the matching through holes on the connection plate (24) and the support plate (23). The connection bolt (271) is screwed with a locking nut that abuts against two sides of the support plate (23).

9. A rocket engine test vibration reduction device according to any one of claims 1 to 8, Features: A first screw hole is provided at one end of the vibration damping rod assembly (2), and a first adjusting screw (3) is coaxially threadedly connected thereto; a first ear plate is provided at one end of the first adjusting screw (3) away from the vibration damping rod assembly (2); hinged ear seats (12) adapted to the first ear plate are provided at both ends of the upper part of the base (1); the first ear plate and the hinged ear seat (12) are connected to each other via a first pin shaft penetrating the two; and a first fastening nut is screwed onto the first adjusting screw (3).

10. A rocket engine test vibration reduction device according to any one of claims 1 to 8, Features: A second screw hole is provided at one end of the vibration damping rod assembly (2) and is coaxially threadedly connected to a second adjusting screw (4); a second ear plate is provided at one end of the second adjusting screw (4) away from the vibration damping rod assembly (2); the second ear plate is connected to the support ear via a second pin shaft penetrating the two; a second fastening nut is screwed onto the second adjusting screw (4).

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