Liquid rocket engine thrust measuring device

Abstract

The invention discloses a liquid rocket engine thrust measuring device, and relates to the technical field of engine thrust measurement, the liquid rocket engine thrust measuring device is used for measuring the thrust of an engine, the liquid rocket engine thrust measuring device comprises a force bearing wall, a portal frame, a movable frame, a force measuring assembly, a conveying pipeline and a supporting assembly, and the portal frame and the force bearing wall are arranged at an interval in the first direction; the movable frame is slidably arranged on the inner periphery of the portal frame and has the freedom degree of sliding in the first direction. The force measuring assembly is arranged between the force bearing wall and the movable frame and extends in the first direction, one end of the force measuring assembly is fixed to the force bearing wall, and the other end abuts against the movable frame; one end of the conveying pipeline communicates with the end, close to the bearing wall, of the engine, and the other end communicates with an external pipeline; the supporting assembly is arranged on the side, away from the bearing wall, of the portal frame. The end, away from the bearing wall, of the engine abuts against the top end of the supporting assembly. According to the liquid rocket engine thrust measuring device provided by the invention, the construction cost is greatly reduced, the installation and maintenance are convenient, and the device is suitable for frequently iterative test run occasions.

Description

Technical Field

[0001] This application relates to the field of engine thrust measurement technology, and in particular to a liquid rocket engine thrust measurement device. Background Technology

[0002] Thrust is a key performance indicator of rocket engines, directly affecting the orbital accuracy and reliability of launch vehicles. Thrust measurement devices are commonly used to measure the thrust of engines.

[0003] Thrust measurement devices are classified into two types according to their main load-bearing form: vertical and horizontal. Because the engine operating conditions are consistent with the flight conditions during measurement using a vertical measuring device, the error caused by engine gravity is small and the measurement accuracy is high. Therefore, vertical measuring devices are mostly used for engine thrust measurement.

[0004] Traditional horizontal measuring devices are only suitable for thrust measurement of small thrust engines. For large thrust engines of hundreds of tons, only vertical measuring devices can be used for measurement. However, when the above-mentioned vertical measuring devices are used for thrust measurement, the test stand located at the bottom needs to deal with the impact of the high-temperature gas being injected downwards, which makes the construction cost of the test stand support structure very high. At the same time, the overall structure of the vertical measuring device is difficult to install and maintain, and it is not suitable for test occasions with frequent iterations. Summary of the Invention

[0005] The main purpose of this application is to provide a liquid rocket engine thrust measurement device, which aims to solve the problem that traditional horizontal thrust measurement devices are not convenient for measuring the thrust of large thrust engines of hundreds of tons.

[0006] To achieve the above objectives, this application provides a liquid rocket engine thrust measurement device for measuring engine thrust. The liquid rocket engine thrust measurement device includes a load-bearing wall, a gantry, a moving frame, a force measuring component, a delivery pipeline, and a support component. The gantry and the load-bearing wall are spaced apart in a first direction, which is horizontal. The moving frame is slidably disposed on the inner circumference of the gantry and has the freedom to slide along the first direction. The engine is disposed on the side of the moving frame away from the load-bearing wall and its axial direction is the same as the first direction. The force measuring component is disposed between the load-bearing wall and the moving frame and extends along the first direction. One end of the force measuring component is fixed to the load-bearing wall, and the other end abuts against the moving frame. One end of the delivery pipeline is connected to the end of the engine near the load-bearing wall, and the other end is connected to an external pipeline. The support component is disposed on the side of the gantry away from the load-bearing wall, and the end of the engine away from the load-bearing wall abuts against the top of the support component.

[0007] Optionally, the liquid rocket engine thrust measuring device further includes a slide rail, which is fixed to the bottom of the gantry and extends along the first direction; wherein the moving frame slides in conjunction with the slide rail.

[0008] Optionally, the slide rails are two in number and spaced apart in a second direction, which is horizontal and perpendicular to the first direction.

[0009] Optionally, the force measuring component includes a mounting base, a first pressure sensor, and a force transmission rod. The mounting base is fixed to the load-bearing wall. The first pressure sensor is located at the end of the mounting base away from the load-bearing wall. The force transmission rod is located at the end of the first pressure sensor away from the mounting base. The force transmission rod abuts against the moving frame.

[0010] Optionally, the liquid rocket engine thrust measuring device further includes a first contact plate and a second contact plate. The first contact plate is fixed to the side of the moving frame facing the force transmission rod. The second contact plate is fixed to the end of the force transmission rod away from the load-bearing wall and abuts against the first contact plate in the first direction. Either the first contact plate or the second contact plate is provided with a mounting groove, and the other of the first contact plate and the second contact plate is provided with a protrusion that passes through the mounting groove in the first direction.

[0011] Optionally, the liquid rocket engine thrust measurement device further includes an in-situ calibration component; the in-situ calibration component includes a mounting plate, a hydraulic cylinder, a second pressure sensor, a pull rod, and a nut; the mounting plate is fixed to the outer periphery of the moving frame and has a through hole extending along the first direction; the hydraulic cylinder is fixed to the load-bearing wall and its axial direction is the same as the first direction; the second pressure sensor is disposed at the end of the hydraulic cylinder away from the load-bearing wall; the pull rod is fixed to the side of the second pressure sensor opposite to the hydraulic cylinder and extends along the first direction, wherein the pull rod passes through the through hole; the nut is threadedly connected to the end of the pull rod away from the load-bearing wall and abuts against the mounting plate.

[0012] Optionally, the inner circumference of the gantry frame is provided with multiple sets of roller assemblies, and each roller assembly abuts against the moving frame.

[0013] Optionally, the moving frame has a cuboid frame structure; the moving frame includes eight positioning blocks and multiple connecting rods, the eight positioning blocks are respectively disposed at the eight apex corners of the moving frame; the multiple connecting rods connect adjacent positioning blocks; wherein, the inner periphery of the gantry has three mounting surfaces disposed opposite to the outer side of the moving frame, each mounting surface is opposite to four positioning blocks on the outer side of the moving frame, and four roller assemblies are mounted on each mounting surface to abut against the corresponding positioning block.

[0014] Optionally, the roller assembly includes a positioning plate, a first connecting plate, a sliding rod, a threaded rod, and a roller. The positioning plate is fixed to the gantry frame. The first connecting plate is disposed on the side of the positioning plate opposite to the gantry frame. The sliding rod is fixed to the side of the first connecting plate facing the positioning plate and slides with the positioning plate. The threaded rod is rotatably connected to the side of the first connecting plate facing the positioning plate and threadedly connected to the positioning plate. The roller is disposed on the side of the first connecting plate opposite to the positioning plate.

[0015] Optionally, the roller assembly further includes a second connecting plate and a disc spring. The second connecting plate is disposed on the side of the first connecting plate opposite to the positioning plate, and there is a gap between the second connecting plate and the first connecting plate. The disc spring is disposed within the gap and abuts against the first connecting plate and the second connecting plate. The roller is disposed on the side of the second connecting plate opposite to the first connecting plate.

[0016] This application discloses a liquid rocket engine thrust measurement device. When measuring the thrust of a high-thrust engine, the engine starts working, pushing the moving frame towards the load-bearing wall. The moving frame slides relative to the gantry along a first direction, thereby compressing the force measuring component. The force measuring component measures the pressure value, and the thrust value of the engine can be determined based on this pressure value. One end of the engine is connected to the moving frame, and the other end is supported by a support component. This two-end support of the engine can effectively prevent the engine from tilting due to its own weight, thereby ensuring the accuracy of the measurement results. This allows the high-thrust engine to be kept horizontal for thrust measurement. Furthermore, the modular design of the measurement device makes the overall structure of the measurement device simple, easy to install and maintain, and suitable for frequent test runs. At the same time, no components need to withstand the high-temperature exhaust gas emitted by the engine, significantly reducing construction costs. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the overall structure of a liquid rocket engine thrust measurement device proposed in an embodiment of this application; Figure 2 for Figure 1 A structural schematic diagram from another perspective of the embodiment; Figure 3 This is a schematic diagram of the gantry structure in an embodiment of this application; Figure 4 This is a schematic diagram of the moving frame structure in an embodiment of this application; Figure 5 This is a schematic diagram of the force measuring component in an embodiment of this application; Figure 6 This is a schematic diagram of the structure of the in-situ calibration component in an embodiment of this application; Figure 7 This is a schematic diagram of the roller assembly in an embodiment of this application; In the diagram: 1. Engine; 2. Load-bearing wall; 3. Gantry frame; 31. Slide rail; 4. Moving frame; 41. Positioning block; 42. Connecting rod; 5. Force measuring component; 51. Mounting base; 52. First pressure sensor; 53. Force transmission rod; 6. Conveying pipeline; 61. First contact plate; 62. Second contact plate; 7. Support component; 71. Mounting plate; 711. Through hole; 72. Hydraulic cylinder; 73. Second pressure sensor; 74. Tie rod; 75. Nut; 81. Positioning plate; 82. First connecting plate; 83. Sliding rod; 84. Threaded rod; 85. Roller; 86. Second connecting plate.

[0018] The realization of the purpose, functional features and advantages of this application will be further explained in conjunction with the embodiments and with reference to the accompanying drawings. Detailed Implementation

[0019] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0020] It should be noted that all directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present invention are only used to explain the relative positional relationship and movement of each component in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indication will also change accordingly.

[0021] In this invention, unless otherwise explicitly specified and limited, the terms "connection," "fixed," etc., should be interpreted broadly. For example, "fixed" can mean a fixed connection, a detachable connection, or an integral part; it can mean a mechanical connection or an electrical connection; it can mean a direct connection or an indirect connection through an intermediate medium; it can mean the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0022] Furthermore, if the embodiments of this invention involve descriptions such as "first" or "second," these descriptions are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include at least one of those features. Additionally, the meaning of "and / or" throughout the text includes three parallel solutions. For example, "A and / or B" includes solution A, solution B, or a solution that simultaneously satisfies A and B. Furthermore, the technical solutions of the various embodiments can be combined with each other, but this must be based on the ability of those skilled in the art to implement them. When the combination of technical solutions is contradictory or impossible to implement, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection claimed by this invention.

[0023] refer to Figures 1-7 This application provides a liquid rocket engine thrust measuring device for measuring the thrust of engine 1. The liquid rocket engine thrust measuring device may include a load-bearing wall 2, a gantry 3, a moving frame 4, a force measuring component 5, a delivery pipeline 6, and a support component 7. The gantry 3 and the load-bearing wall 2 are spaced apart in a first direction, which is horizontal. The moving frame 4 is slidably disposed on the inner circumference of the gantry 3 and has the freedom to slide along the first direction. The engine 1 is disposed on the side of the moving frame 4 away from the load-bearing wall 2 and its axial direction is the same as the first direction. The force measuring component 5 is disposed between the load-bearing wall 2 and the moving frame 4 and extends along the first direction. One end of the force measuring component 5 is fixed to the load-bearing wall 2, and the other end abuts against the moving frame 4. One end of the delivery pipeline 6 is connected to the end of the engine 1 near the load-bearing wall 2, and the other end is connected to an external pipeline. The support component 7 is disposed on the side of the gantry 3 away from the load-bearing wall 2, and the end of the engine 1 away from the load-bearing wall 2 abuts against the top of the support component 7.

[0024] This application proposes a liquid rocket engine thrust measurement device. When measuring the thrust of a high-thrust engine, the engine 1 starts working, pushing the moving frame 4 towards the load-bearing wall 2. The moving frame 4 slides relative to the gantry 3 along a first direction, thereby squeezing the force measuring component 5. The force measuring component 5 measures the pressure value, and the thrust value of the engine can be determined based on this pressure value. One end of the engine 1 is connected to the moving frame 4, and the other end is supported by the support component 7. This two-end support of the engine 1 can effectively prevent the engine 1 from tilting due to its own weight, thereby ensuring the accuracy of the measurement results. This keeps the high-thrust engine 1 horizontal for thrust measurement. Moreover, the modular design of the measurement device makes the overall structure of the measurement device simple, easy to install and maintain, and suitable for frequent test runs. At the same time, no components need to withstand the high-temperature exhaust gas emitted by the engine, significantly reducing construction costs.

[0025] Specifically, in actual use, both the load-bearing wall 2 and the gantry frame 3 can be installed on the cement ground through a steel frame to ensure the stability of the load-bearing wall 2 and the gantry frame 3.

[0026] Among them, such as Figure 1 As shown, the first direction is the X direction and the second direction is the Y direction. The support component 7 may include a hydraulic cylinder and an arc-shaped plate. The hydraulic cylinder is fixed to the ground and has the freedom to extend and retract along the direction of gravity. The arc-shaped plate is fixed to the top of the hydraulic cylinder. In this way, the height of the arc-shaped plate can be adjusted by extending and retracting the hydraulic cylinder, so that the arc-shaped plate can lift the end of the high-thrust engine away from the moving frame 4 from bottom to top, ensuring that the axis of the engine 1 is the same as the first direction.

[0027] Furthermore, the curved plate fits into the side wall of engine 1, thus providing better support for engine 1 and also limiting the engine to prevent it from swaying in the horizontal direction.

[0028] It should be noted that the delivery pipeline 6 is used to deliver propellant to the engine 1, and both the gantry 3 and the moving frame 4 are frame structures, such as... Figure 1 and Figure 2 As shown, the conveying pipe 6 can bypass the gantry 3 and the moving frame 4, so that the first end of the conveying pipe 6 is connected to the end of the engine 1 near the load-bearing wall 2; the second end of the conveying pipe 6 is connected to an external pipe, such as... Figure 1 As shown, the second end of the conveying pipe 6 can be fixed to the side of the load-bearing wall 2 parallel to the first direction, so that the second end of the conveying pipe 6 is as far away as possible from the components of the measuring device, so that the conveying pipe 6 can be connected to the external pipe.

[0029] The gantry 3 and the moving frame 4 will experience a certain amount of relative sliding. Therefore, a corrugated pipe section can be installed in the middle of the conveying pipeline 6. Both ends of the corrugated pipe section are connected to rigid pipe sections. One rigid pipe section is fixed to the moving frame 4 and connected to the engine 1, while the other rigid pipe section is fixed to the gantry 3 and the load-bearing wall 2. Figure 1 As shown, Figure 1 The corrugated section on the middle conveying pipeline 6 is the corrugated pipe section.

[0030] like Figure 1 As shown, in an exemplary embodiment, the liquid rocket engine thrust measuring device may further include a slide rail 31, which is fixed to the bottom of the gantry 3 and extends along a first direction; wherein the moving frame 4 is slidably engaged with the slide rail 31. In an exemplary embodiment, there are two slide rails 31, spaced apart in a second direction, which is horizontal and perpendicular to the first direction.

[0031] Specifically, the movable frame 4, through its cooperation with the slide rail 31, can have the freedom to slide in the first direction. The two slide rails 31 are spaced apart in the second direction to further improve the smoothness of the sliding of the movable frame 4.

[0032] refer to Figure 5 In an exemplary embodiment, the force measuring component 5 may include a mounting base 51, a first pressure sensor 52, and a force transmission rod 53. The mounting base 51 is fixed to the load-bearing wall 2. The first pressure sensor 52 is disposed at the end of the mounting base 51 away from the load-bearing wall 2. The force transmission rod 53 is disposed at the end of the first pressure sensor 52 away from the mounting base 51. The force transmission rod 53 abuts against the moving frame 4.

[0033] Specifically, when engine 1 is working, engine 1 will push moving frame 4 to approach load-bearing wall 2 in the first direction. Moving frame 4 and force transmission rod 53 will come into contact in the first direction. In this way, moving frame 4 will squeeze force transmission rod 53, and force transmission rod 53 will further squeeze first pressure sensor 52. First pressure sensor 52 can then display the measured value, which is the thrust value of engine 1.

[0034] The first pressure sensor 52 is a bidirectional tension and compression column sensor with an accuracy of ±0.1%. The two ends of the first pressure sensor 52 have a forward and reverse thread design and are threaded to the mounting base 51 and the force transmission rod 53 respectively. In this way, the length of the force measuring component 5 in the first direction can be adjusted by rotating the first pressure sensor 52, thereby adjusting the distance between the moving frame 4 and the load-bearing wall 2.

[0035] refer to Figure 1 , Figure 4 and Figure 5 In an exemplary embodiment, the liquid rocket engine thrust measuring device may further include a first contact plate 61 and a second contact plate 62. The first contact plate 61 is fixed to the side of the moving frame 4 facing the force transmission rod 53; the second contact plate 62 is fixed to the end of the force transmission rod 53 away from the load-bearing wall 2 and abuts against the first contact plate 61 in a first direction; wherein, either the first contact plate 61 or the second contact plate 62 is provided with a mounting groove, and the other of the first contact plate 61 and the second contact plate 62 is provided with a protrusion that passes through the mounting groove in the first direction.

[0036] Specifically, taking the example of a protrusion on the first contact plate 61 and a mounting groove on the second contact plate 62, when the protrusion is inserted into the mounting groove, the first contact plate 61 and the second contact plate 62 abut against each other, and the protrusion fits against the side wall of the mounting groove. At this time, the first contact plate 61 and the second contact plate 62 only have the degree of freedom to move relative to each other in the first direction. Thus, when the moving frame 4 transmits the thrust to the force transmission rod 53 through the second contact plate 62 and the first contact plate 61, the direction of force transmission is always the same as the first direction and will not deviate, that is, the force transmission rod 53 will not deviate.

[0037] Meanwhile, when installing components such as the force transmission rod 53 and the moving frame 4, it is only necessary to insert the protrusion on the first contact plate 61 into the mounting groove on the second contact plate 62 to determine the relative position of the force transmission rod 53 and the moving frame 4, making the installation more convenient and precise.

[0038] refer to Figure 1 , Figure 2 and Figure 6 In an exemplary embodiment, the liquid rocket engine thrust measurement device may further include an in-situ calibration assembly; the in-situ calibration assembly may include a mounting plate 71, a hydraulic cylinder 72, a second pressure sensor 73, a pull rod 74, and a nut 75. The mounting plate 71 is fixed to the outer periphery of the moving frame 4 and is provided with a through hole 711 extending in a first direction; the hydraulic cylinder 72 is fixed to the load-bearing wall 2 and its axial direction is the same as the first direction; the second pressure sensor 73 is disposed at the end of the hydraulic cylinder 72 away from the load-bearing wall 2; the pull rod 74 is fixed to the side of the second pressure sensor 73 away from the hydraulic cylinder 72 and extends in the first direction, wherein the pull rod 74 passes through the through hole 711; the nut 75 is threadedly connected to the end of the pull rod 74 away from the load-bearing wall 2 and abuts against the mounting plate 71.

[0039] Specifically, since the nut 75 abuts against the side of the mounting plate 71 away from the load-bearing wall 2, and the nut 75 is fixed relative to the load-bearing wall 2 by the tie rod 74, the second pressure sensor 73, and the hydraulic cylinder 72, the mounting plate 71 cannot move away from the load-bearing wall 2 in the first direction, that is, the moving frame 4 cannot move away from the load-bearing wall 2 in the first direction, but the moving frame 4 can move closer to the load-bearing wall 2 in the first direction.

[0040] The second pressure sensor 73 is a bidirectional tension-compression spoke-type sensor with an accuracy of ±0.03%. The range of the second pressure sensor 73 is greater than that of the first pressure sensor 52. For example, the range of the second pressure sensor 73 can be a times the range of the first pressure sensor 52, where a can be 1.1, 1.2, 1.3, etc.

[0041] Taking a 100-ton high-thrust engine as an example, before measuring the engine thrust, that is, after all components are connected but the engine is not yet running, it is necessary to perform calibration through the in-situ calibration component. At this time, the second pressure sensor 73 and the first pressure sensor 52 are zeroed. The hydraulic cylinder 72 can gradually pull the moving frame 4, for example, so that the reading of the second pressure sensor 73 can gradually increase to 100 tons. When the reading of the second pressure sensor 73 is 20 tons, 40 tons, 60 tons, 80 tons and 100 tons respectively, the reading of the first pressure sensor 52 is recorded. In this way, the force value reading change curve of the second pressure sensor 73 when pressurized and the force value reading change curve of the first pressure sensor 52 can be obtained.

[0042] Theoretically, the two force value change curves should coincide. However, in reality, due to the deformation of the moving frame 4 and the gantry 3, and the friction between the roller 85 and the moving frame 4, there will be a deviation between the two force value change curves, i.e., an error. Similarly, the two force value change curves during depressurization can be obtained by gradually releasing the moving frame using the hydraulic cylinder 72. Only when the errors of the two force value change curves during pressurization and the two force value change curves during depressurization are both within the specified error range can subsequent thrust measurement of engine 1 be carried out to ensure the accuracy of engine 1 thrust measurement. When using cryogenic propellant in the test, the pipeline can be pressurized and the test can be repeated to correct the force value transmission coefficient.

[0043] Furthermore, before the engine 1 is tested, a certain preload can be applied to the moving frame 4 by retracting the hydraulic cylinder 72 to drive the tie rod 74. The reading of the second pressure sensor 73 indicates the magnitude of the preload.

[0044] When engine 1 is ignited for testing, the force value measured by the first pressure sensor 52 is the sum of the thrust and preload of engine 1. Combined with the force value transmission coefficient mentioned above, the force value is converted. The calculated force value minus the preload is the thrust of engine 1.

[0045] It should be understood that when the engine 1 increases its working horsepower, the instantaneous impact force of the moving frame 4 is relatively large. There is a gap between the moving frame 4 and the force measuring component 5, which can easily lead to damage to the force measuring component 5. Moreover, it is impossible to avoid assembly gaps at various points during the assembly process. Therefore, by applying a preload to the measuring device through the in-situ calibration component, various gaps on the thrust transmission path of the engine 1 can be eliminated, nonlinear errors can be eliminated, the continuous and stable thrust transmission can be ensured, the measurement accuracy can be improved, the impact of the engine 1 on the moving frame 4 at the moment of startup can be reduced, and the aforementioned sensors can be protected.

[0046] It should be noted that the hydraulic cylinder 72 is a complete set of automatic pressure regulating hydraulic pump station. There are many such structures, so they will not be described in detail here. When the thrust is measured, the moving frame 4 will move a certain distance along the first direction to approach the load-bearing wall 2. During the process of the moving frame 4 approaching the load-bearing wall 2, the hydraulic cylinder 72 will retract synchronously to ensure that the preload value measured by the second pressure sensor 73 is maintained within the corresponding range.

[0047] For example, for an engine 1 with a thrust of 100 tons, the preload range of the second pressure sensor 73 can be 4% to 6% of the thrust value, that is, the preload range of the second pressure sensor 73 can be 4 to 6 tons, specifically 4 tons, 5 tons, 6 tons, etc.

[0048] Furthermore, such as Figure 2 As shown, there can be two sets of force measuring components 5, which are symmetrically arranged in the direction of gravity. The same applies to the in-situ calibration components. In this way, the overall components of the measuring device are symmetrically distributed, making it more aesthetically pleasing and ensuring uniform force distribution.

[0049] Among them, the gantry 3 and the moving frame 4 adopt an integral welded frame structure, which has greater rigidity, relatively lighter weight, and high load-bearing capacity.

[0050] It should be noted that, as Figure 1 As shown, the engine 1 is placed as far away from the moving frame as possible, so that the automatic pressure regulating hydraulic pump station corresponding to the hydraulic cylinder 72 is far from the heat emitted by the engine 1, and the impact of heat radiation on the hydraulic system is greatly reduced.

[0051] refer to Figure 1 , Figure 3 and Figure 4 In an exemplary embodiment, the inner periphery of the gantry 3 is provided with multiple sets of roller assemblies, each roller assembly abutting against the movable frame 4. In an exemplary embodiment, the movable frame 4 has a cuboid frame structure; the movable frame 4 may include eight positioning blocks 41 and multiple connecting rods 42, the eight positioning blocks 41 are respectively disposed at the eight apex corners of the movable frame 4; the multiple connecting rods 42 connect adjacent positioning blocks 41; wherein, the inner periphery of the gantry 3 has three mounting surfaces disposed opposite to the outer side of the movable frame 4, each mounting surface is opposite to four positioning blocks 41 on the outer side of the movable frame 4, and four roller assemblies are mounted on each mounting surface to abut against the corresponding positioning block 41.

[0052] Specifically, for ease of explanation, the side of the moving frame 4 closest to the engine 1 is referred to as the front side, and the side of the moving frame 4 furthest from the engine 1 is referred to as the rear side. The moving frame 4 is a frame structure composed of eight positioning blocks 41 and multiple connecting rods 42. The roller assembly abuts against the positioning blocks 41 to provide a limit for the moving frame 4.

[0053] Among them, the positioning block 41 at the bottom of the moving frame 4 cooperates with the slide rail 31 to realize the sliding of the moving frame 4 along the first direction. Specifically, as follows: Figure 4 As shown, the bottom of the moving frame 4 has an inverted V-shaped groove below the positioning block 41. This allows the moving frame 4 to be further limited to the left and right by cooperating with the slide rail 31 through the V-shaped groove.

[0054] Combination Figure 1 and Figure 3 The top, left, and right sides of the moving frame 4 are opposite to the inner circumference of the gantry 3, meaning the inner circumference of the gantry 3 has three mounting surfaces opposite to the outer side of the moving frame 4. The top, left, and right sides of the moving frame 4 each have four positioning blocks 41, meaning each mounting surface is opposite to four positioning blocks 41. Four sets of roller assemblies can be installed on each mounting surface to abut against the positioning blocks 41, thereby limiting the movement of the moving frame 4. A total of 12 sets of roller assemblies are installed. In this way, the top, bottom, left, and right sides of the moving frame 4 are all limited, which greatly improves the stability of the moving frame 4 during the sliding process and further improves the accuracy of the thrust measurement results.

[0055] refer to Figure 3 and Figure 7In an exemplary embodiment, the roller assembly may include a positioning plate 81, a first connecting plate 82, a sliding rod 83, a threaded rod 84, and a roller 85. The positioning plate 81 is fixed to the gantry 3. The first connecting plate 82 is disposed on the side of the positioning plate 81 away from the gantry 3. The sliding rod 83 is fixed to the side of the first connecting plate 82 facing the positioning plate 81 and slides with the positioning plate 81. The threaded rod 84 is rotatably connected to the side of the first connecting plate 82 facing the positioning plate 81 and threadedly connected to the positioning plate 81. The roller 85 is disposed on the side of the first connecting plate 82 away from the positioning plate 81.

[0056] Specifically, the sliding rod 83 slides with the positioning plate 81, so the first connecting plate 82 can slide along the axial direction of the sliding rod 83. At this time, rotating the threaded rod 84 can drive the first connecting plate 82 to move. The first connecting plate 82 further drives the roller 85 to move, which can adjust the distance between the roller 85 and the positioning block 41 in the moving frame 4, so that the roller 85 abuts against and squeezes the positioning block 41, thereby limiting the positioning block 41.

[0057] It should be understood that the roller 85 inside the roller assembly abuts against the positioning block 41. When the moving frame 4 moves, the roller 85 rotates relative to the positioning block 41, that is, there is rolling friction between the roller 85 and the positioning block 41. This has minimal impact on the measurement of the thrust of the engine 1, and at the same time, it can limit the movement of the moving frame 4.

[0058] refer to Figure 7 In an exemplary embodiment, the roller assembly may further include a second connecting plate 86 and a disc spring. The second connecting plate 86 is disposed on the side of the first connecting plate 82 opposite to the positioning plate 81, and there is a gap between the second connecting plate 86 and the first connecting plate 82. The disc spring is disposed within the gap and abuts against the first connecting plate 82 and the second connecting plate 86. The roller 85 is disposed on the side of the second connecting plate 86 opposite to the first connecting plate 82.

[0059] Specifically, when the roller 85 is subjected to vibration from the moving frame 4, the roller 85 will transmit the force to push the second connecting plate 86. The second connecting plate 86 will deform slightly, thereby squeezing the disc spring. Afterwards, the disc spring will return to its original shape. In this way, the disc spring can absorb the vibration force received by the roller 85, ensuring that the roller assembly can normally limit the moving frame, and at the same time improve the service life of the roller assembly.

[0060] Furthermore, the first connecting plate 82 and the second connecting plate 86 can be connected by bolts, and the disc spring can be limited by fitting it onto the bolts.

[0061] Of course, the gap between the first connecting plate 82 and the second connecting plate 86 can generate a certain preload on the disc spring.

[0062] The above are merely preferred embodiments of this application and do not limit the patent scope of this application. Any equivalent structural or procedural transformations made using the content of this application's specification and drawings, or direct or indirect applications in other related technical fields, are similarly included within the patent protection scope of this application.

Claims

1. A liquid rocket engine thrust measuring device, characterized in that, The liquid rocket engine thrust measuring device is used to measure the thrust of engine (1), and includes: Load-bearing wall (2); The gantry frame (3) is spaced apart from the load-bearing wall (2) in a first direction, which is a horizontal direction; The moving frame (4) is slidably disposed on the inner periphery of the gantry frame (3) and has the degree of freedom to slide along the first direction, wherein the engine (1) is disposed on the side of the moving frame (4) away from the load-bearing wall (2) and its axial direction is the same as the first direction; A force measuring component (5) is disposed between the load-bearing wall (2) and the movable frame (4) and extends along the first direction. One end of the force measuring component (5) is fixed to the load-bearing wall (2) and the other end abuts against the movable frame (4). The delivery pipeline (6) is connected at one end to the end of the engine (1) near the load-bearing wall (2) and at the other end to an external pipeline; The support assembly (7) is located on the side of the gantry (3) away from the load-bearing wall (2), and the end of the engine (1) away from the load-bearing wall (2) abuts against the top of the support assembly (7).

2. The liquid rocket engine thrust measurement device as described in claim 1, characterized in that, The liquid rocket engine thrust measurement device also includes: The slide rail (31) is fixed to the bottom of the gantry (3) and extends along the first direction; The moving frame (4) is slidably engaged with the slide rail (31).

3. The liquid rocket engine thrust measuring device as described in claim 2, characterized in that, The slide rail (31) has two rails and is spaced apart in a second direction, which is horizontal and perpendicular to the first direction.

4. The liquid rocket engine thrust measuring device as described in claim 1, characterized in that, The force measuring component (5) includes: Mounting base (51) is fixed to the load-bearing wall (2); The first pressure sensor (52) is disposed at the end of the mounting base (51) away from the load-bearing wall (2); A force transmission rod (53) is disposed at the end of the first pressure sensor (52) away from the mounting base (51); The force transmission rod (53) abuts against the moving frame (4).

5. The liquid rocket engine thrust measuring device as described in claim 4, characterized in that, The liquid rocket engine thrust measurement device also includes: The first contact plate (61) is fixed to the side of the moving frame (4) facing the force transmission rod (53); The second contact plate (62) is fixed to one end of the force transmission rod (53) away from the load-bearing wall (2) and abuts against the first contact plate (61) in the first direction; The first contact plate (61) and the second contact plate (62) are provided with a mounting groove, and the other of the first contact plate (61) and the second contact plate (62) is provided with a protrusion that passes through the mounting groove along the first direction.

6. The liquid rocket engine thrust measuring device as described in claim 1, characterized in that, The liquid rocket engine thrust measurement device also includes an in-situ calibration component; The in-situ calibration component includes: Mounting plate (71) is fixed to the outer periphery of the moving frame (4) and is provided with through hole (711) extending along the first direction. A hydraulic cylinder (72) is fixed to the load-bearing wall (2) and its axial direction is the same as the first direction; The second pressure sensor (73) is located at the end of the hydraulic cylinder (72) away from the load-bearing wall (2); A pull rod (74) is fixed to the side of the second pressure sensor (73) away from the hydraulic cylinder (72) and extends along the first direction, wherein the pull rod (74) passes through the through hole (711). The nut (75) is threaded onto the end of the tie rod (74) away from the load-bearing wall (2) and abuts against the mounting plate (71).

7. The liquid rocket engine thrust measuring device as described in claim 1, characterized in that, The inner circumference of the gantry (3) is provided with multiple sets of roller assemblies, and each roller assembly abuts against the moving frame (4).

8. The liquid rocket engine thrust measuring device as described in claim 7, characterized in that, The movable frame (4) has a rectangular frame structure; The movable frame (4) includes: Eight positioning blocks (41) are respectively set at the eight apex corners of the moving frame (4); Multiple connecting rods (42) connect adjacent positioning blocks (41); The inner periphery of the gantry (3) has three mounting surfaces that are opposite to the outer side of the moving frame (4). Each mounting surface is opposite to the four positioning blocks (41) on the outer side of the moving frame (4). Each mounting surface is equipped with four roller assemblies that abut against the corresponding positioning blocks (41).

9. The liquid rocket engine thrust measuring device as described in claim 7, characterized in that, The roller assembly includes: The positioning plate (81) is fixed to the gantry frame (3); The first connecting plate (82) is disposed on the side of the positioning plate (81) away from the gantry frame (3); The sliding rod (83) is fixed to the side of the first connecting plate (82) facing the positioning plate (81) and slides in cooperation with the positioning plate (81); A threaded rod (84) is rotatably connected to the side of the first connecting plate (82) facing the positioning plate (81) and is threadedly connected to the positioning plate (81); A roller (85) is disposed on the side of the first connecting plate (82) opposite to the positioning plate (81).

10. The liquid rocket engine thrust measuring device as described in claim 9, characterized in that, The roller assembly also includes: The second connecting plate (86) is disposed on the side of the first connecting plate (82) away from the positioning plate (81), and there is a gap between the second connecting plate (86) and the first connecting plate (82); A disc spring is disposed within the gap and abuts against the first connecting plate (82) and the second connecting plate (86). The roller (85) is located on the side of the second connecting plate (86) opposite to the first connecting plate (82).

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