Vertical six-component test device and test method for large solid rocket engine

Abstract

In order to solve the problem that the existing multi-component test device and method cannot meet the measurement requirement of a large solid rocket engine, the invention provides a vertical six-component test device and test method of the large solid rocket engine. The device comprises a main thrust measuring device and a lateral force measuring device. According to the main thrust measuring device, the main thrust of the engine is shared by the three bearing piers, so that the value of force shared by each bearing pier is reduced, the main thrust of the engine can be measured under the condition that the size is small, and the main thrust measuring device is convenient to install and adjust. The lateral force measuring device comprises six lateral force measuring assemblies and one engine connecting base, wherein the six lateral force measuring assemblies are only in contact and are not connected. When the device is used, the axial direction of the engine can be freely extended, so that the axial deformation of the engine does not bring errors to thrust vector measurement. Although the small expansion amount of the engine rear skirt is transmitted to the engine connecting base to enable the lateral force measuring assembly to have additional output, the additional output can be reduced and avoided by enhancing the rigidity of the engine connecting base.

Description

Technical Field

[0001] The invention relates to an upright six-component force testing device and a testing method for a large solid rocket engine. Background Art

[0002] In the ground test of a large solid rocket engine, there is a need for upright six-component force measurement. However, the current multi-component force test device and method are only suitable for small engines and cannot meet the measurement needs of this large solid rocket engine. Therefore, it is necessary to propose a new test device and test method for the six-component force measurement needs of large solid rocket engines. Summary of the Invention

[0003] In order to solve the technical problem that the current multi-component force test device and method cannot meet the measurement requirements of large solid rocket engines, the present invention proposes an upright six-component force test device and test method for large solid rocket engines.

[0004] The technical solution of the present invention is:

[0005] The upright six-component force test device for large solid rocket engines is special in that it includes a main thrust measurement device, a lateral force measurement device, and a column frame;

[0006] The main thrust measuring device adopts a distributed structure, including a thrust frame, a force transmission beam, a main thrust force measuring assembly and a first force bearing pier arranged in sequence from bottom to top, as well as a pre-tightening and leveling assembly and a second force bearing pier arranged below the force transmission beam and located on the periphery of the thrust frame; the lower end of the thrust frame is used to connect to the front skirt of the engine to be tested, and transmit the main thrust generated by the engine to be tested to the force transmission beam; there are three main thrust measuring assemblies and they are evenly distributed along the circumference, the force transmission beam is used to transmit the main thrust to the three main thrust force measuring assemblies, and the three main thrust force measuring assemblies jointly measure the main thrust of the engine to be tested during operation; there are three first force bearing piers, which are respectively connected to the three main thrust force measuring assemblies, and the three first force bearing piers jointly bear the main thrust of the engine to be tested; there are three pre-tightening and leveling assemblies, which correspond to the positions of the three main thrust force measuring assemblies one by one, and are used to load pre-tightening force on the engine to be tested before testing; there are three second force bearing piers, which are respectively arranged below the three pre-tightening and leveling assemblies and connected thereto, and the three second force bearing piers jointly bear the dead weight of the engine to be tested;

[0007] The lateral force measuring device includes an engine connection base and a lateral load-bearing pier arranged in an upper and lower manner, and a lateral force measuring assembly arranged on the outer side of the lower part of the engine connection base; the upper end of the engine connection base is used to connect to the rear skirt of the engine to be tested, and the lower end bottom plate is suspended, and the lower end bottom plate is provided with a central hole for the high-temperature and high-pressure combustion gas ejected by the engine to be tested to pass through during operation; there are three groups of lateral force measuring assemblies, two in each group, and the two lateral force measuring assemblies in the same group are respectively located on both sides of the lower end bottom plate of the engine connection base and are arranged in a collinear manner; the lateral force measuring assembly is only in contact with the lower end bottom plate of the engine connection base, but not connected; there are six lateral load-bearing piers, which are respectively arranged in one-to-one correspondence with the lateral force measuring assemblies, and are used to install the six lateral force measuring assemblies on the column frame, and at the same time are used to withstand the lateral force generated when the engine to be tested is working;

[0008] The column frame includes a base frame and three columns vertically arranged on the base frame. The first and second load-bearing piers in the main thrust measuring device are installed on the columns, and the lateral load-bearing piers in the lateral force measuring device are installed on the base frame.

[0009] Furthermore, the first load-bearing pier and the second load-bearing pier have the same structure, and their mating surfaces with the column adopt a serrated structure.

[0010] Furthermore, the three columns are connected by a plurality of 240° ring-gap reinforcement structures arranged in parallel up and down to increase the overall strength and rigidity.

[0011] Furthermore, the force transmission beam includes a main circular ring and three force transmission arms evenly distributed on the outer wall of the main circular ring and extending radially outward; the upper and lower end faces of the main circular ring are provided with at least one circle of threaded holes for connecting with thrust frames of different specifications; the three force transmission arms are respectively used to connect with the three main thrust force measuring assemblies above it and the pre-tightening and leveling assemblies below it.

[0012] Furthermore, the force transmission beam is a hollow structure.

[0013] Furthermore, the preload and leveling assembly includes a second force sensor, an adapter ring and a second flange; the two adapter rings are fixedly connected to the two ends of the second force sensor, and the second flange is connected to the two adapter rings and threadedly engaged with them. By changing the threaded engagement length of the second flange and the adapter ring, the total length of the preload and leveling assembly can be adjusted to realize the preload and leveling function.

[0014] Furthermore, the lateral force measurement assembly includes a roller, a third force sensor, a flexible member and a third flange plate connected in sequence; the roller is connected to the third force sensor through a roller frame, and the roller is only in contact with the lower end bottom plate of the engine connection base but not connected; the flexible member is used to improve the stress state of the third force sensor so that it is only subjected to pressure along the axial direction of the sensor; the third flange plate is used to realize the connection between the lateral force measurement assembly and the lateral load-bearing pier.

[0015] Furthermore, a first serrated structure and a threaded hole are provided on the side wall of the column for installing the load-bearing pier; the main bodies of the first load-bearing pier and the second load-bearing pier are both rectangular structures, and among the four side walls of the rectangular structure, the side walls for cooperating with the column are provided with a second serrated structure matching the first serrated structure on the column, and mounting plates are provided on both sides of the first serrated structure, and a plurality of strip holes are opened on the mounting plates. By installing bolts in the strip holes and the threaded holes, the first load-bearing pier and the second load-bearing pier are respectively installed on the column.

[0016] The present invention also provides a method for conducting a six-component force measurement test of a large solid rocket launch using the upright six-component force test device for a large solid rocket engine. The method is characterized in that it comprises the following steps:

[0017] Step 1: Connect the front skirt of the engine to the thrust frame, and the rear group to the engine connection base. Then use the pre-tightening and leveling assembly and the second load-bearing pier to adjust the engine to a vertical state, and use the pre-tightening and leveling assembly to apply pre-tightening force.

[0018] Step 2: Operate the engine, measure the main thrust of the engine using three main thrust force measuring assemblies, and measure the lateral force generated by the engine using three operating lateral force force measuring assemblies;

[0019] Step 3: Establish the following mechanical model:

[0020]

[0021] Among them, F1, F2, and F3 are the force values ​​of the sensors of the three main thrust force-measuring assemblies respectively; a is the distance from the sensor in a single main thrust force-measuring assembly to the engine axis; F4, F5, and F6 are the force values ​​of the sensors of the three lateral force-measuring assemblies working in the test; b is the distance from the straight line containing the force measurement directions of the sensors of two side-by-side sets of the three lateral force-measuring assemblies working in the test to the engine axis; and c is the distance between the two force-measuring planes.

[0022] Step 4: Substitute the measured values ​​from step 2 into the mechanical model established in step 3 to solve the thrust vector of the engine.

[0023] The advantages of the present invention are:

[0024] The upright six-component force testing device of the present invention comprises a main thrust measuring device and a lateral force measuring device.

[0025] The main thrust measurement device adopts a distributed structure, sharing the main thrust of the engine through three load-bearing piers, so that the force shared by each load-bearing pier becomes smaller. This can realize the main thrust measurement of the engine in a smaller size and is easy to install and adjust.

[0026] The lateral force measurement device consists of a lateral force measurement assembly and an engine connection base. The engine connection base is not fixed to the lateral force measurement assembly, but only contacts the rollers, which can only withstand pressure. As a result, only three of the six lateral force sensors are working under pressure. The rollers are followed by load cells and flexures, which improve the load cell's load state, so that the sensor is only subjected to axial forces.

[0027] When the present invention is used for measurement, the axial direction can freely stretch during the operation of the engine, and the axial deformation during the operation of the engine will not cause errors in the thrust vector measurement.

[0028] The radial expansion during engine operation is mainly in the engine barrel section. The front and rear skirts of the engine generally expand less. The direction of the tiny expansion of the front skirt of the engine is perpendicular to the main thrust force measurement direction. According to past experience, the measurement error of the main thrust caused by this tiny expansion of the front skirt of the engine is very small and can be ignored; the direction of the tiny expansion of the rear skirt of the engine is consistent with the direction of the lateral force measurement assembly. The deformation of the rear skirt of the engine will be transmitted to the engine connection base, which will bring pressure to the roller and may cause additional output of the lateral force measurement assembly. However, this additional output can be reduced and avoided by strengthening the stiffness of the engine connection base, so that it is within a controllable range.

[0029] It has been verified in practice that the present invention is feasible for use in six-component force tests of large solid rocket engines. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 It is a structural schematic diagram of the upright six-component force testing device of the present invention.

[0031] Figure 2 It is a structural schematic diagram of the three-dimensional frame in the upright six-component force testing device of the present invention.

[0032] Figure 3 It is a partial enlarged view of the upper part of the stereoscopic frame.

[0033] Figure 4 This is a partial enlarged view of the serrated structure on the three-dimensional frame.

[0034] Figure 5 It is a structural schematic diagram of the load-bearing pier in the upright six-component force testing device of the present invention.

[0035] Figure 6 It is a structural schematic diagram of the load-bearing pier in the upright six-component force testing device of the present invention (from another perspective).

[0036] Figure 7 It is a structural schematic diagram of the lateral load-bearing pier in the upright six-component force testing device of the present invention.

[0037] Figure 8 It is a structural schematic diagram of the main thrust force measuring assembly in the upright six-component force testing device of the present invention.

[0038] Figure 9 It is a structural schematic diagram of the lateral force measuring device in the upright six-component force testing device of the present invention.

[0039] Figure 10 It is the main view of the lateral force measuring component in the lateral force measuring device.

[0040] Figure 11 It is a three-dimensional diagram of the lateral force measuring component in the lateral force measuring device.

[0041] Figure 12 It is a structural schematic diagram of the force transmission beam in the upright six-component force testing device of the present invention.

[0042] Figure 13 It is a perspective view of the force transmission beam in the upright six-component force testing device of the present invention.

[0043] Figure 14 It is a structural schematic diagram of the pre-tightening and leveling component in the present invention.

[0044] Figure 15 It is a structural schematic diagram of the thrust frame in the upright six-component force testing device of the present invention.

[0045] Figure 16 It is a structural schematic diagram of the thrust frame in the upright six-component force testing device of the present invention (from another perspective).

[0046] Figure 17 It is a structural schematic diagram of the engine connection base in the upright six-component force testing device of the present invention.

[0047] Figure 18 It is a schematic diagram of the mechanical model of the present invention.

[0048] Reference numerals:

[0049] 1-column frame; 101-column; 102-base frame; 103-first threaded hole; 104-first serrated structure; 105-240° ring-gap reinforcement structure; 106-first center hole;

[0050] 2-first bearing pier; 201-strip hole; 202-round hole; 203-second threaded hole; 204-second serrated structure; 205-mounting plate;

[0051] 3-main thrust force measuring assembly; 301-first force sensor; 302-first flange; 303-first boss; 304-first through hole; 305-neck of flange;

[0052] 4-force transmission beam; 401-main body ring; 402-force transmission arm; 403-third threaded hole; 404-second center hole; 405-first positioning hole; 406-fourth threaded hole;

[0053] 5-preload leveling assembly; 501-second force sensor; 502-adapter ring; 503-second flange; 504-second boss; 505-second through hole; 506-stud;

[0054] 6-thrust frame; 601-upper ring; 602-lower ring; 603-connecting column; 604-third through hole; 605-third boss; 606-fourth through hole; 607-first ring stop;

[0055] 7-Engine;

[0056] 8- the second bearing pier;

[0057] 9 - engine connection base; 901 - circular upper ring; 902 - bottom plate; 903 - connecting rod; 904 - fourth through hole; 905 - second circular ring stop;

[0058] 10 - lateral force measurement assembly; 1001 - roller; 1002 - third force sensor; 1003 - flexible member; 1004 - third flange; 1005 - fourth boss; 1006 - fifth through hole; 1007 - extension of roller frame; 1008 - roller frame;

[0059] 11- lateral load-bearing pier; 1101- fifth threaded hole; 1102- second positioning hole. DETAILED DESCRIPTION

[0060] There are two difficult problems that need to be solved in the upright six-component force measurement of large solid rocket engines: first, the main thrust of large solid rocket engines is relatively large, and the load-bearing pier must not only meet the strength requirements and be able to realize the main thrust measurement of the engine, but also be easy to install and adjust; second, large solid rocket engines will produce radial expansion and axial elongation during operation. This deformation will cause errors in thrust measurement. How to reduce and avoid this error in the six-component force measurement of large solid rocket engines is a technical difficulty.

[0061] In order to overcome the above technical difficulties, the present invention designs a main thrust measurement device with a distributed structure, which shares the main thrust of the engine through three load-bearing piers, so that the force shared by each load-bearing pier becomes smaller. In this way, the main thrust of the engine can be measured in a smaller size and is easy to install and adjust.

[0062] The lateral force measuring device designed in the present invention includes a lateral force measuring assembly and an engine connecting base, and the engine connecting base is not fixedly connected to the lateral force measuring assembly, but is only in contact with the roller and can only withstand pressure; in addition, the lateral force measuring assembly includes a flexible part, which can improve the force state of the force sensor in the lateral force measuring assembly so that the force sensor is only subjected to axial force.

[0063] After the engine to be measured is installed on the present invention, the axial direction can be freely extended during the operation of the engine without causing measurement errors; the radial expansion during the operation of the engine is mainly in the engine barrel section, and the front and rear skirts of the engine generally expand less. The direction of the tiny expansion of the front skirt of the engine is perpendicular to the main thrust measurement direction. According to past experience, the measurement error of the main thrust caused by this tiny expansion of the front skirt of the engine is very small and can be ignored; the direction of the tiny expansion of the rear skirt of the engine is consistent with the direction of the lateral force measurement component. The deformation of the rear skirt of the engine will be transmitted to the engine connection base, which brings pressure to the roller and may cause additional output of the lateral force measurement component. However, this additional output can be reduced and avoided by strengthening the rigidity of the engine connection base, so that it is within a controllable range.

[0064] The present invention will be further described below with reference to the accompanying drawings.

[0065] Reference Figure 1 The upright six-component force test device for a large solid rocket engine provided by the present invention includes a column frame 1, a main thrust measuring device and a lateral force measuring device installed on the column frame 1.

[0066] like Figure 2-4As shown, the column frame 1 includes a base frame 102 and three columns 101 vertically arranged on the base frame 102, as well as multiple 240° ring-gap reinforcement structures 105. The base frame 102 is pre-buried in the foundation and fixedly connected to the columns 101. A first center hole 106 is opened in the center of the base frame 102, and the first center hole 106 serves as a diversion channel. The three columns 101 are evenly distributed along the same circumference. The multiple 240° ring-gap reinforcement structures 105 are arranged parallel to each other and are simultaneously connected to the three columns 101 to increase the strength and rigidity of the overall structure. After assembly, the three columns 101 and the 240° ring-gap reinforcement structures 105 can reserve an engine hoisting inlet and outlet channel. The three columns 101 have the same structure. Two rows of first threaded holes 103 are provided on the inner side wall of the column 101, and a first serration structure 104 is provided between the two rows of threaded holes 103; the first threaded holes 103 are used to connect to the main thrust measuring device, and the first serration structure 104 is used to withstand the main thrust transmitted by the main thrust measuring device.

[0067] The main thrust measuring device includes a first load-bearing pier 2, a main thrust force measuring assembly 3, a force transmission beam 4, a pre-tensioning and leveling assembly 5 and a second load-bearing pier 8, which are arranged in sequence from top to bottom, and a thrust frame 6 arranged below the force transmission beam 4 and located on the inner side of the pre-tensioning and leveling assembly 5.

[0068] like Figure 1 、 5 -6, there are three first load-bearing piers 2 with the same structure, which are respectively installed on the three columns 101 of the column frame 1 and can move up and down along the columns 101. The three first load-bearing piers 2 share the main thrust of the engine to be tested. The main body of the first load-bearing pier 2 is a rectangular structure. Among the four side walls of the rectangular structure, the side wall used to cooperate with the column 101 is provided with a second serrated structure 204 that matches the first serrated structure 104 on the column 101, and mounting plates 205 are provided on both sides of the second serrated structure 204. Both mounting plates 205 are provided with multiple strip holes 201. The first load-bearing pier 2 can be installed on the column 101 by matching the strip holes 201 with the first threaded holes 103 on the column 101 and inserting screws / bolts. The top and bottom surfaces of the rectangular parallelepiped structure are each provided with a circular hole 202 and multiple second threaded holes 203. The circular hole 202 is used for positioning with the main thrust force-measuring assembly 3, and the second threaded holes 203 are used for connection to the main thrust force-measuring assembly 3. The circular hole 202 and second threaded holes 203 are provided on both the top and bottom surfaces of the rectangular parallelepiped structure to facilitate installation. In other embodiments, the circular hole 202 and second threaded holes 203 may be provided only on the bottom surface.

[0069] like Figure 1 、 8As shown, the main thrust force-measuring assembly 3 is used to measure the main thrust of the engine. There are three main thrust force-measuring assemblies 3 with identical structures. They are installed below the three first bearing piers 2 and fixedly connected thereto. They are also installed above the force transmission beam 4 and fixedly connected thereto. A single main thrust force-measuring assembly 3 includes a first force sensor 301 and two first flanges 302, respectively, disposed at either end of the first force sensor 301. A first boss 303 is provided at the center of the outer end surface of the first flange 302, and a plurality of evenly distributed first through-holes 304 are provided on the outer side of the first boss 303. The first through-holes 304 on one end of the first flange 302 are used to connect the main thrust force-measuring assembly 3 to the first bearing pier 2, and the first boss 303 is used to achieve positioning during connection. The first through-holes 304 on the second flange 302 at the other end are used to connect the main thrust force-measuring assembly 3 to the force transmission beam 4, and the first boss 303 is used to achieve positioning during connection.

[0070] like Figure 1 、 12 As shown in Figure 13, the force transmission beam 4 is installed below the three main thrust force measuring assemblies 3 and is fixedly connected thereto, and is used to transmit the thrust of the engine to the main thrust force measuring assemblies 3. The force transmission beam 4 is a symmetrical structure, including a main body ring 401 and three force transmission arms 402 evenly distributed on the outer wall of the main body ring 401 and extending radially outward. To facilitate installation, at least one circle of third threaded holes 403 are provided on the upper and lower end faces of the main body ring 401. The third threaded holes 403 are used to connect to the thrust frame 6; the advantage of providing multiple circles of third threaded holes 403 on the main body ring 402 is that it is convenient to adapt to different thrust frames and engines; the second center hole 404 of the main body ring 401 is used for positioning when the force transmission beam 4 is connected to the thrust frame 6. In other embodiments, the third threaded holes 403 can also be provided only on the lower end face of the main body ring 401. The two end faces of the force transmission arm 402 are provided with a first positioning hole 405 and a plurality of fourth threaded holes 406; the fourth threaded hole 406 located on the upper end face of the force transmission arm 402 is used to realize the fixed connection between the force transmission beam 4 and the main thrust force measuring assembly 3 located above it, and the first positioning hole 405 is used for positioning during connection; the fourth threaded hole 406 located on the lower end face of the force transmission arm 402 is used to realize the fixed connection between the force transmission beam 4 and the pre-tightening and leveling assembly 5 located below it, and the first positioning hole 405 is used for positioning during connection. In order to ensure rigidity while reducing weight, the force transmission beam 4 is a hollow structure, such as Figure 13 shown.

[0071] like Figure 1 、 14As shown, there are three preload and leveling assemblies 5 with the same structure, which are respectively installed under the three force transmission arms 402 of the force transmission beam 4. The preload and leveling assembly 5 includes a second force sensor 501, two adapter rings 502 and two second flanges 503. The two adapter rings 502 are respectively fixedly connected to the two ends of the second force sensor 501, and the two second flanges 503 are respectively connected to the two adapter rings 502. The interior of the adapter ring 502 has an internal thread, which can transmit the engine gravity and preload force. The engine gravity and preload force are transmitted to the adapter ring 502 through the second flange 503, and then transmitted to the second force sensor 501. A circle of second through holes 505 is provided on the end face of the second flange 503, and a second boss 504 is provided at the center of the circle of second through holes 505. The second through holes 505 on the second flange 504 at one end are used to connect the preload and leveling assembly 5 to the second load-bearing pier 8, and the second boss 504 is used for positioning during the connection. The second through holes 505 on the second flange 504 at the other end are used to connect the preload and leveling assembly 5 to the force transmission beam 4, and the second boss 504 is used for positioning during the connection. The end face of the second flange 503 not provided with the second boss 504 is provided with a stud 506. The external thread of the stud 506 mates with the internal thread of the adapter ring 502. By changing the screwing length, the total length of the preload and leveling assembly 5 can be adjusted to achieve the preload and leveling function.

[0072] There are three second bearing blocks 8, each with the same structure. They are mounted below the three preload and leveling assemblies 5 and are fixedly connected to the second flanges 503 of the preload and leveling assemblies 5. The structure of the second bearing blocks 8 is identical to that of the first bearing blocks 2. The connection between the second bearing blocks 8 and the columns 101 of the column frame 1 is the same as that between the first bearing blocks 2 and the columns 101 of the column frame 1. The second bearing blocks 8 can also move up and down along the columns 101 of the column frame 1. The three second bearing blocks 8 jointly bear the deadweight of the engine under test.

[0073] like Figure 1 、 15As shown in Figure 16, the thrust frame 6 is installed at the lower end of the force transmission beam 4 and is located on the inner side of the three pre-tightening and leveling components 5, and is used to transmit the thrust of the engine to the force transmission beam 4. The thrust frame 6 includes an upper ring 601 and a lower ring 602, which are connected by a plurality of evenly distributed connecting columns 603. A circle of third through holes 604 is provided on the end face of the upper ring 601. The third through holes 604 are used to match the third threaded holes 403 on the force transmission beam 4 to achieve the connection between the thrust frame 6 and the force transmission beam 4; a third boss 605 is provided at the center hole of the upper ring 601. The third boss 605 is used to position the thrust frame 6 when it is connected to the force transmission beam 4. A circle of fourth through holes 606 are provided on the end face of the lower circular ring 602, and the fourth through holes 606 are used to connect the thrust frame 6 with the engine; the lower end face of the lower circular ring 602 is also provided with a first circular stop 607, and the first circular stop 607 is used for positioning when the thrust frame 6 is connected to the engine.

[0074] The lateral force measuring device includes an engine connection base 9 and a lateral load-bearing pier 11 arranged above and below, and a lateral force measuring assembly 10 arranged on the outer side of the lower end of the engine connection base 9.

[0075] like Figure 1 、 17 As shown, the engine connection base 9 is located above the base frame 102 of the three-dimensional frame 1 and below the engine to be measured, and is connected to the engine to be measured; the lower part of the engine connection base 9 is suspended. The engine connection base 9 includes a circular upper ring 901 and a bottom plate 902, and the circular upper ring 901 and the bottom plate 902 are connected by a plurality of connecting rods 903. A circle of evenly distributed fourth through holes 904 is provided on the end face of the circular upper ring 901, and the fourth through holes 904 are used to achieve the connection between the engine connection base 9 and the engine; the upper end face edge of the circular upper ring 901 is provided with a second circular stop 905, and the second circular stop 905 is used for positioning when the engine connection base 9 is connected to the engine. The bottom plate 902 is a rectangular flat plate with a central circular hole and a circular hole in the middle, and the inner diameter of the central circular hole is larger than the outer diameter of the circular upper ring 901; the high-temperature and high-pressure gas ejected from the engine during operation passes through the central circular hole of the bottom plate 902.

[0076] like Figure 1 、 7 As shown, the lateral support blocks 11 are used to withstand the lateral forces generated by the engine during operation. There are six lateral support blocks 11, all of identical construction. The base of each block 11 is welded to the upper surface of the base frame 102 of the column frame 1, while its upper portion is located outside the base plate 902 of the engine connection base 9. The lateral support blocks 11 are rectangular parallelepiped structures, with one of their four side walls provided with a fifth threaded hole 1101 for connection to the lateral force measurement assembly 10, as well as a second positioning hole 1102 for positioning during connection.

[0077] like Figure 1 、 9 As shown in Figure 11, the lateral force measurement assembly 10 is used to measure the lateral force generated during engine operation. There are six lateral force measurement assemblies 10, each with the same structure. One lateral force measurement assembly 10 is located on the outside of one pair of side surfaces of the base plate 902 of the engine connection base 9, and these two lateral force measurement assemblies 10 are arranged collinearly. Two lateral force measurement assemblies 10 are located on the outside of the other pair of side surfaces of the base plate 902 of the engine connection base 9, and the lateral force measurement assemblies 10 located on the outside of different side surfaces are grouped in pairs. The two lateral force measurement assemblies 10 in the same group are arranged collinearly. The lateral force measurement assembly 10 includes a roller 1001, a third force sensor 1002, a flexible member 1003, and a third flange 1004, which are connected in sequence. Roller 1001 is mounted on roller frame 1008, and the extension 1007 of roller frame 1008 is mounted on third load cell 1002. Roller 1001 is in contact with engine connection base 9, but not connected. During engine testing, roller 1001 and third load cell 1002 only bear pressure. Flexible member 1003, an existing component, is used to improve the stress state of third load cell 1002, so that it only bears pressure along the sensor's axial direction. The end face of third flange 1004 is provided with a circle of fifth through-holes 1006 and fourth bosses 1005. Fifth through-holes 1006 are used to connect lateral force measurement assembly 10 to lateral bearing pier 11, while fourth bosses 1005 are used for positioning during connection.

[0078] Reference Figure 1 The working principle and use method of the upright six-component force testing device of the present invention are as follows:

[0079] Before the test, the front skirt of the engine 7 is first connected to the thrust frame 6, and the rear skirt of the engine 7 is connected to the engine connection base 9. Then, the engine 7 is adjusted to a vertical state using the pre-tightening and leveling assembly 5 and the second load-bearing pier 8. The second load-bearing pier 8 bears the weight of the engine. Before the test, the engine can be loaded with pre-tightening force by adjusting the threaded engagement length between the second flange 503 of the pre-tightening and leveling assembly 5 and the adapter ring 502.

[0080] During the test, engine 7 is operating, and the main thrust generated by engine 7 is transmitted through thrust frame 6 to force transmission beam 4. It is then transmitted through force transmission beam 4 to main thrust force-measuring assembly 3 and preload-leveling assembly 5. This is then transmitted through main thrust force-measuring assembly 3 and preload-leveling assembly 5 to first and second bearing piers 2 and 8, driving them along column 101. The main thrust is then transmitted to column 101 via the second serration structure on the bearing piers, and then borne by first serration structure 104 on column 101. During this period, the three main thrust force-measuring assemblies 3 jointly measure the main thrust during engine operation.

[0081] When the engine 7 is operating, the base plate 902 of the engine connection base 9 contacts the roller 1001 of the lateral force-measuring assembly 10, transmitting a lateral force to the roller 1001 of the lateral force-measuring assembly 10. The roller 1001 then transmits the lateral force to the third force sensor 1002 in the lateral force-measuring assembly 10, which then measures the lateral force generated during engine operation. A single lateral force-measuring assembly 10 can only withstand pressure. In the present invention, two lateral force-measuring assemblies located on either side of the base plate 902 and on the same straight line are considered a group and used in conjunction. Only one of these two lateral force-measuring assemblies is subjected to pressure, meaning only one is active. Thus, when measuring the engine, three lateral force-measuring assemblies and three main thrust force-measuring assemblies are always operating, measuring a total of six force components to form the combined engine thrust vector.

[0082] The lateral load-bearing pier is fixedly connected to the lateral force measuring assembly to withstand the lateral force generated during engine operation.

[0083] According to the measurement principle of the upright six-component force test device of the present invention, the mechanical model is established as follows:

[0084]

[0085] Among them, F1, F2, and F3 are the force measurement values ​​of the sensors of the three main thrust force measuring assemblies 3 respectively; a is the distance from the sensor in a single main thrust force measuring assembly 3 to the axis of the engine 7; F4, F5, and F6 are the force measurement values ​​of the sensors of the three lateral force measuring assemblies 10 working in the test, b is the distance from the straight line where the force measurement directions of the sensors of two sets of side-by-side lateral force measuring assemblies in the three sets of lateral force measuring assemblies 10 working in the test are located to the axis of the engine 7, and c is the distance between the two force measuring planes.

[0086] Coordinate system such as Figure 18 As shown, with the center of the engine front skirt end surface as the coordinate origin, the force value along the positive direction of the coordinate axis is positive, and the thrust vector of the engine 7 can be solved through the above mechanical model and the sensor force value.

Claims

1. An upright six-component force test device for large solid rocket motors, characterized by: It includes main thrust measuring device, lateral force measuring device and column frame; The main thrust measuring device adopts a distributed structure, including a thrust frame, a force transmission beam, a main thrust force measuring assembly and a first force bearing pier arranged in sequence from bottom to top, as well as a pre-tightening and leveling assembly and a second force bearing pier arranged below the force transmission beam and located on the periphery of the thrust frame; the lower end of the thrust frame is used to connect to the front skirt of the engine to be tested, and transmit the main thrust generated by the engine to be tested to the force transmission beam; there are three main thrust measuring assemblies and they are evenly distributed along the circumference, the force transmission beam is used to transmit the main thrust to the three main thrust force measuring assemblies, and the three main thrust force measuring assemblies jointly measure the main thrust of the engine to be tested during operation; there are three first force bearing piers, which are respectively connected to the three main thrust force measuring assemblies, and the three first force bearing piers jointly bear the main thrust of the engine to be tested; there are three pre-tightening and leveling assemblies, which correspond to the positions of the three main thrust force measuring assemblies one by one, and are used to load pre-tightening force on the engine to be tested before testing; there are three second force bearing piers, which are respectively arranged below the three pre-tightening and leveling assemblies and connected thereto, and the three second force bearing piers jointly bear the dead weight of the engine to be tested; The lateral force measuring device includes an engine connection base and a lateral load-bearing pier arranged in an upper and lower manner, and a lateral force measuring assembly arranged on the outer side of the lower part of the engine connection base; the upper end of the engine connection base is used to connect to the rear skirt of the engine to be tested, and the lower end bottom plate is suspended, and the lower end bottom plate is provided with a central hole for the high-temperature and high-pressure combustion gas ejected by the engine to be tested to pass through during operation; there are three groups of lateral force measuring assemblies, two in each group, and the two lateral force measuring assemblies in the same group are respectively located on both sides of the lower end bottom plate of the engine connection base and are arranged in a collinear manner; the lateral force measuring assembly is only in contact with the lower end bottom plate of the engine connection base, but not connected; there are six lateral load-bearing piers, which are respectively arranged in one-to-one correspondence with the lateral force measuring assemblies, and are used to install the six lateral force measuring assemblies on the column frame, and at the same time are used to withstand the lateral force generated when the engine to be tested is working; The column frame includes a base frame and three columns vertically arranged on the base frame. The first and second load-bearing piers in the main thrust measuring device are installed on the columns, and the lateral load-bearing piers in the lateral force measuring device are installed on the base frame.

2. The upright six-component force test device for a large solid rocket motor according to claim 1, characterized in that: The first load-bearing pier and the second load-bearing pier have the same structure, and the matching surfaces thereof with the column adopt a serrated structure.

3. The upright six-component force test device for a large solid rocket motor according to claim 2, characterized in that: The three columns are connected by a plurality of 240° ring-gap reinforcement structures arranged in parallel up and down to increase the overall strength and rigidity.

4. The upright six-component force test device for a large solid rocket motor according to any one of claims 1 to 3, characterized in that: The force transmission beam includes a main circular ring and three force transmission arms evenly distributed on the outer wall of the main circular ring and extending radially outward; the upper and lower end faces of the main circular ring are provided with at least one circle of threaded holes for connecting with thrust frames of different specifications; the three force transmission arms are respectively used to connect with the three main thrust force measuring assemblies above it and the pre-tightening and leveling assemblies below it.

5. The upright six-component force test device for a large solid rocket motor according to claim 4, characterized in that: The force transmission beam is a hollow structure.

6. The upright six-component force testing device for a large solid rocket motor according to claim 4, characterized in that: The preload and leveling assembly includes a second force sensor, an adapter ring and a second flange; the two adapter rings are fixedly connected to the two ends of the second force sensor, and the second flange is connected to the two adapter rings and threadedly engaged with them. By changing the threaded engagement length of the second flange and the adapter ring, the total length of the preload and leveling assembly can be adjusted to realize the preload and leveling function.

7. The upright six-component force testing device for a large solid rocket motor according to claim 6, characterized in that: The lateral force measurement assembly includes a roller, a third force sensor, a flexible member and a third flange plate connected in sequence; the roller is connected to the third force sensor through a roller frame, and the roller is only in contact with the lower end bottom plate of the engine connection base but not connected; the flexible member is used to improve the stress state of the third force sensor so that it is only subjected to pressure along the axial direction of the sensor; the third flange plate is used to realize the connection between the lateral force measurement assembly and the lateral load-bearing pier.

8. The upright six-component force testing device for a large solid rocket motor according to claim 7, characterized in that: A first serrated structure and a threaded hole are provided on the side wall of the column for installing the load-bearing pier; the main bodies of the first load-bearing pier and the second load-bearing pier are both rectangular structures, and among the four side walls of the rectangular structure, the side walls for cooperating with the column are provided with a second serrated structure matching the first serrated structure on the column, and mounting plates are provided on both sides of the first serrated structure, and a plurality of strip holes are opened on the mounting plates. By installing bolts in the strip holes and the threaded holes, the first load-bearing pier and the second load-bearing pier are respectively installed on the column.

9. A method for conducting a six-component force measurement test of a large solid rocket launch using the upright six-component force test device for a large solid rocket engine according to any one of claims 1 to 8, characterized in that: The following steps are involved: Step 1: Connect the front skirt of the engine to the thrust frame, and the rear group to the engine connection base. Then use the pre-tightening and leveling assembly and the second load-bearing pier to adjust the engine to a vertical state, and use the pre-tightening and leveling assembly to apply pre-tightening force. Step 2: Operate the engine, measure the main thrust of the engine using three main thrust force measuring assemblies, and measure the lateral force generated by the engine using three operating lateral force force measuring assemblies; Step 3: Establish the following mechanical model: Among them, F1, F2, and F3 are the force values ​​of the sensors of the three main thrust force-measuring assemblies respectively; a is the distance from the sensor in a single main thrust force-measuring assembly to the engine axis; F4, F5, and F6 are the force values ​​of the sensors of the three lateral force-measuring assemblies working in the test; b is the distance from the straight line containing the force measurement directions of the sensors of two side-by-side sets of the three lateral force-measuring assemblies working in the test to the engine axis; and c is the distance between the two force-measuring planes. Step 4: Substitute the measured values ​​from step 2 into the mechanical model established in step 3 to solve the thrust vector of the engine.

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