Universal solid rocket engine test bed

Abstract

The invention provides a universal solid rocket engine test bed which comprises a force bearing pier, a sensor, a clamping assembly used for clamping an engine and a tensioning integral structure assembly used for enabling the clamping assembly clamping the engine to be in a suspension state without constraint force on the axis of the clamping assembly. The clamping assembly is fixedly installed on the tensioning overall structure assembly, the sensor is fixedly installed on the force bearing pier, and the clamping assembly comprises a plurality of clamping jaws distributed in the circumferential direction of an engine at intervals and a clamping power structure driving the clamping jaws to move in the radial direction of the engine. According to the invention, the tensioning integral structure assembly is designed, so that the whole clamping assembly for clamping the engine is in a suspension state without constraint force in the axis direction of the engine, the resistance of the test bench to the engine when the engine works is greatly reduced, and the test precision is greatly improved; and meanwhile, a clamping power structure is designed to adjust movement of the clamping jaws to clamp engines of different specifications, and the universality and adaptability of products are improved.

Description

Technical Field

[0001] This invention belongs to the field of solid rocket engine technology, specifically relating to a universal solid rocket engine test stand. Background Technology

[0002] There are two types of existing solid rocket motor test stands: one is the center-frame type, and the other is the mobile trolley type. The center-frame type test stand mounts the engine in two center frames, each equipped with three rollers. The engine head connects to the thrust sensor. The rollers restrict the engine's radial displacement, and as the engine rolls, the thrust is transmitted axially to the sensor during operation, thus achieving the testing purpose. The mobile trolley type test stand mounts the engine on a trolley equipped with a clamp of the same diameter as the engine as a mounting interface. The trolley moves freely in the forward and backward directions, and the engine head connects to the sensor to achieve the testing purpose.

[0003] However, existing solid rocket motor test stands have the following problems: a) The friction between the engine and the test stand, and the friction between the carriage and the guide rail, will introduce resistance to the test. The greater the mass of the test stand and the engine, the greater the resistance, which greatly reduces the accuracy of the test; b) The installation accuracy of the engine on the test stand is not high, which reduces the accuracy of the test; c) The installation efficiency is low, the process is cumbersome, and the operation time is long, making it difficult to apply in some temperature tests (where there are time requirements from the engine being taken out of the insulation box to the end of the test, especially for small engines where the test time is short); d) The installation interface is not universal. Summary of the Invention

[0004] The purpose of this invention is to provide a universal solid rocket engine test stand, which can at least solve some of the defects existing in the prior art.

[0005] To achieve the above objectives, the present invention adopts the following technical solution:

[0006] A universal solid rocket motor test stand includes a support block, a sensor, a clamping assembly for holding the engine, and a tensioned integral structure assembly for placing the clamping assembly holding the engine in a suspended state without constraint on its axis. The tensioned integral structure assembly is located on one side of the support block, the clamping assembly is fixedly installed on the tensioned integral structure assembly, and the sensor is fixedly installed on the support block near the clamping assembly. The clamping assembly includes a plurality of claws spaced apart along the circumference of the engine and a clamping power structure for driving the claws to move radially along the engine.

[0007] Furthermore, the tensioned integral structure component includes an upper frame and a lower frame, the upper frame is suspended above the lower frame, and the upper frame and the lower frame are flexibly connected in the vertical direction, and the clamping component is fixedly installed on the upper frame.

[0008] Furthermore, the upper frame includes a first U-shaped frame and a first L-shaped frame that are perpendicular to each other, and the lower frame includes a second U-shaped frame and a second L-shaped frame that are perpendicular to each other. The first U-shaped frame is located above the second U-shaped frame and is arranged parallel to the engine axis. The first L-shaped frame and the second L-shaped frame are both located between the first U-shaped frame and the second U-shaped frame. The horizontal sections of the first L-shaped frame and the second L-shaped frame at least partially overlap and are both parallel to the engine axis. The first U-shaped frame and the second U-shaped frame, as well as the first L-shaped frame and the second L-shaped frame, are connected in the vertical direction by steel wire ropes.

[0009] Furthermore, the openings of the first U-shaped frame and the second U-shaped frame face opposite directions, and the horizontal segment of the first L-shaped frame is located below the horizontal segment of the second L-shaped frame.

[0010] Furthermore, there are two clamping components, which are coaxially spaced along the axis of the engine, and both clamping components are fixedly installed on the tensioning integral structure component.

[0011] Furthermore, the clamping power structure includes a concentrically arranged disc, a cam disc, and a positioning disc. The positioning disc is fixedly connected to the disc, and the cam disc is rotatably connected between the positioning disc and the disc. The disc, cam disc, and positioning disc have a through hole at their center for the engine to pass through. The positioning disc has several positioning grooves extending radially therefrom. The cam disc has several curved grooves distributed in a spiral radial pattern. Each of the jaws is arranged in a corresponding positioning groove, and the end of each jaw near the cam disc is slidably connected to the corresponding curved groove.

[0012] Furthermore, the edge of the disc is provided with a limiting groove to limit the rotation of the cam disc.

[0013] Furthermore, the claw has a cylindrical section for sliding connection with the curved groove, a positioning block for engaging with the positioning groove, and a clamping block for abutting and holding the engine; the cylindrical section and the clamping block are respectively fixedly connected to both sides of the positioning block.

[0014] Furthermore, the sensor is arranged coaxially with the clamping assembly.

[0015] Furthermore, the aforementioned general-purpose solid rocket engine test stand also includes protective frames disposed on both sides of the clamping assembly along its axial direction.

[0016] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0017] The universal solid rocket engine test stand provided by this invention designs a tensioned integral structure component, which makes the entire clamping component holding the engine free from constraint in the direction of the engine axis and in a suspended state. This greatly reduces the resistance of the test stand to the engine when the engine is working, thereby significantly improving the test accuracy. At the same time, by designing the clamping power structure to adjust the movement of the jaws, it can clamp engines of different specifications, improving the versatility and adaptability of the product.

[0018] The present invention will now be described in further detail with reference to the accompanying drawings. Attached Figure Description

[0019] Figure 1 This is a schematic diagram of the structure of the general-purpose solid rocket engine test stand in an embodiment of the present invention;

[0020] Figure 2 This is a schematic diagram of the tensioned integral structure component in an embodiment of the present invention;

[0021] Figure 3 This is a schematic diagram of the clamping component in an embodiment of the present invention;

[0022] Figure 4 This is a schematic diagram of the cam disk structure of the clamping assembly in an embodiment of the present invention;

[0023] Figure 5 This is a schematic diagram of the positioning disk structure of the clamping component in an embodiment of the present invention;

[0024] Figure 6 This is a schematic diagram of the claw structure in an embodiment of the present invention.

[0025] Explanation of reference numerals in the attached drawings: 1. Load-bearing pier; 2. Sensor; 3. Clamping assembly; 4. Engine; 5. Tensioning integral structure assembly; 6. Protective frame; 7. Upper frame; 8. First U-shaped frame; 9. First L-shaped frame; 10. Lower frame; 11. Second U-shaped frame; 12. Second L-shaped frame; 13. Steel wire rope; 14. Disc; 15. Limiting slot; 16. Cam disc; 17. Positioning disc; 18. Claw; 19. Curved groove; 20. Positioning groove; 21. Cylindrical section; 22. Positioning block; 23. Clamping block. Detailed Implementation

[0026] 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 some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0027] In the description of this invention, it should be understood that the terms "center", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0028] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation", "connection", and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, an abutting connection, or an integral connection. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0029] The terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature; in the description of this invention, unless otherwise stated, "a plurality of" or "several" means two or more.

[0030] like Figure 1 As shown, this embodiment provides a universal solid rocket motor test stand, including a support block 1, a sensor 2, a clamping assembly 3 for clamping the engine 4, and a tensioned integral structure assembly 5 for placing the clamping assembly 3 holding the engine 4 in a suspended state without constraint in its axial direction. The tensioned integral structure assembly 5 is located on one side of the support block 1, the clamping assembly 3 is fixedly installed on the tensioned integral structure assembly 5, and the sensor 2 is fixedly installed on the support block 1 on the side close to the clamping assembly 3. The clamping assembly 3 includes a plurality of claws 18 spaced apart along the circumference of the engine 4 and a clamping power structure that drives the claws 18 to move radially along the engine 4.

[0031] In this embodiment, a tensioned integral structure component 5 is used, so that the clamping component 3 holding the engine 4 is fixed as a whole above the tensioned integral structure component 5. The tensioned integral structure component 5 makes the engine 4 free from constraints in its axial direction, and puts it in a "zero gravity" suspended working environment. This suspended working environment will not generate friction during the test, thereby greatly reducing the resistance of the test bench to the engine during engine testing, and thus greatly improving the test accuracy. In addition, the jaws used to clamp the engine 4 adopt a movable structure design. The movement of the jaws 18 is adjusted by the clamping power structure. While driving the jaws 18 to release or clamp the engine 4, the movement of the jaws 18 can also be adjusted to clamp engines 4 of different specifications, improving the versatility and adaptability of the product.

[0032] In the optimized implementation, the sensor 2 and the clamping assembly 3 are designed to be arranged coaxially. In this way, the engine 4 can be connected to the sensor 2 as soon as it is installed on the clamping assembly 3. The test bench does not need to be adjusted, and high installation accuracy can be achieved, which improves the accuracy of engine test.

[0033] As one specific implementation method, such as Figure 2 As shown, the tensioned integral structure component 5 includes an upper frame 7 and a lower frame 10. The upper frame 7 is suspended above the lower frame 10, and the upper frame 7 and the lower frame 10 are flexibly connected in the vertical direction. The clamping component 3 is fixedly installed on the upper frame 7. In this embodiment, through the structure of the upper frame 7 and the lower frame 10 and the flexible connection between the upper frame 7 and the lower frame 10, they pull each other, so that the upper frame 7 and the lower frame 10, on which the engine is placed, form a self-tensioning mechanical balance body when working, so that there is no constraint force on the axial direction of the engine during testing.

[0034] In some embodiments, the upper frame 7 includes a first U-shaped frame 8 and a first L-shaped frame 9 that are perpendicular to each other, and the lower frame 10 includes a second U-shaped frame 11 and a second L-shaped frame 12 that are perpendicular to each other. The first U-shaped frame 8 is located above the second U-shaped frame 11 and is arranged parallel to the axis of the engine 4. The first L-shaped frame 9 and the second L-shaped frame 12 are both located between the first U-shaped frame 8 and the second U-shaped frame 11. The horizontal sections of the first L-shaped frame 9 and the second L-shaped frame 12 at least partially overlap and are both parallel to the axis of the engine 4. The frames 11 are connected vertically by steel wire ropes 13, as are the first L-shaped frame 9 and the second L-shaped frame 12. The upper frame 7 and the lower frame 10 are flexibly connected by steel wire ropes 13. The steel wire ropes 13 can withstand tension but not bending moment, so there is no constraint along the axis of the engine 4. At the same time, the upper frame 7 and the lower frame 10 are pulled together by the steel wire ropes 13, forming a self-tensioning mechanical balance body. This creates a "zero gravity" suspension environment. This suspension environment will not generate friction during the test, which greatly reduces the resistance during the test and can greatly improve the test accuracy.

[0035] Preferably, the openings of the first U-shaped frame 8 and the second U-shaped frame 11 face opposite directions, and the horizontal segment of the first L-shaped frame 9 is located below the horizontal segment of the second L-shaped frame 12. This structural design can better ensure the balance of the suspended connection between the upper frame 7 and the lower frame 10.

[0036] To ensure the stability of the engine clamping, two clamping components 3 are optimized and arranged coaxially at intervals along the axis of the engine 4. Both clamping components 3 are fixedly installed on the tensioning integral structure component 5. Specifically, the two clamping components 3 are fixedly installed at both ends of the first U-shaped frame 8 of the upper frame 7 along the axis of the engine 4 by bolts, ensuring the balance of the self-tensioning mechanical balance body formed by the upper frame 7, the lower frame 10, and the wire rope 13.

[0037] Regarding the specific structure of the clamping component 3, in some embodiments, such as Figures 3 to 6As shown, the clamping power structure includes a concentrically arranged disc 14, a cam disc 16, and a positioning disc 17. The positioning disc 17 is fixedly connected to the disc 14, and the cam disc 16 is rotatably connected between the positioning disc 17 and the disc 14. The disc 14, the cam disc 16, and the positioning disc 17 have through holes at their centers for the engine 4 to pass through. The positioning disc 17 has several positioning grooves 20 extending radially therefrom. Preferably, the positioning grooves 20 are arranged at equal intervals along the circumference of the positioning disc 17. The cam disc 16 has several curved grooves 19 arranged in a spiral radial pattern. Preferably, the curved grooves 19 are also arranged at equal intervals along the circumference of the cam disc 16, and the curved grooves 19 correspond one-to-one with the positioning grooves 20. Each of the claws 18 is arranged one-to-one in the positioning groove 20, and the end of each claw 18 near the cam disc 16 is slidably connected to the corresponding curved groove 19. During the installation of engine 4, it is only necessary to make engine 4 pass through the through holes of disc 14, cam disc 16 and positioning disc 17. By rotating cam disc 16, each pawl 18 is driven to move synchronously along the radial direction of positioning disc 17, so as to clamp engines 4 of different diameters, thereby improving the versatility and adaptability of the product. At the same time, the curved grooves 19 on cam disc 16 are designed to be distributed in a spiral radial pattern, so that the pressure angle of the curved grooves 19 can be used to achieve the locking effect of pawl 18, thereby realizing the rapid installation of engine 4, shortening the installation time and improving the installation efficiency.

[0038] Specifically, such as Figure 6 As shown, the chuck 18 includes a cylindrical section 21, a positioning block 22, and a clamping block 23. The cylindrical section 21 and the clamping block 23 are respectively fixedly connected to both sides of the positioning block 22. The cylindrical section 21 is used to slide with the curved groove 19, the positioning block 22 is used to cooperate with the positioning groove 20, and the clamping block 23 is used to abut and clamp the engine 4. By rotating the cam disk 16, the rotation of the curved groove 19 on the cam disk 16 drives the cylindrical section 21 of the chuck 18 to move, thereby driving the positioning block 22 and the clamping block 23 to move. The movement of clamping block 23, and the limiting effect of positioning groove 20 on positioning block 22 of positioning disk 17, causes positioning block 22 to move radially within positioning groove 20 of positioning disk 17; since each pawl 18 is connected to the same cam disk 16, all pawls 18 move synchronously. During the installation of engine 4, only the handle of cam disk 16 needs to be turned to make the pawls 18 adapt to the diameter of engine 4 for clamping. No other adjustment means are required to achieve high precision, thereby improving the accuracy of engine test.

[0039] Optimized implementation methods, such as Figure 3As shown, the edge of the disc 14 is provided with a limiting groove 15 to limit the rotation of the cam disc 16. Specifically, the handle of the cam disc 16 moves within the range of the limiting groove 15 to drive the rotation of the cam disc 16. Correspondingly, the size of the limiting groove 15, the length of the curved groove 19, and the length of the positioning groove 20 are adapted to each other.

[0040] Preferably, to ensure product safety, such as Figure 1 As shown, the universal solid rocket engine test stand of this embodiment is also designed with a protective frame 6. The protective frame 6 is set on both sides of the clamping assembly 3 along the axial direction. A certain gap is left between the protective frame 6 and the clamping assembly 3, so that it will not affect the movement of the engine during the test.

[0041] The above examples are merely illustrative of the present invention and do not constitute a limitation on the scope of protection of the present invention. All designs that are the same as or similar to the present invention are within the scope of protection of the present invention.

Claims

1. A universal solid rocket engine test stand, characterized by: The application relates to a tension integral structure assembly for supporting a force-bearing pier, a sensor, a clamping assembly for clamping an engine and a tension integral structure assembly for suspending the clamping assembly with the engine in a state of being unrestrained in the axial direction of the engine, wherein the tension integral structure assembly is located on one side of the force-bearing pier, the clamping assembly is fixedly installed on the tension integral structure assembly, the sensor is fixedly installed on the force-bearing pier on the side close to the clamping assembly, and the clamping assembly comprises a plurality of clamping claws distributed along the circumference of the engine and a clamping power structure for driving the clamping claws to move along the radial direction of the engine.

2. The universal solid rocket engine test stand of claim 1, wherein: The tension integral structure assembly comprises an upper frame and a lower frame, the upper frame is suspended above the lower frame, and the upper frame and the lower frame are flexibly connected in the vertical direction, and the clamping assembly is fixedly installed on the upper frame.

3. The universal solid rocket engine test stand of claim 2, wherein: The upper frame comprises a first U-shaped frame and a first L-shaped frame which are perpendicular to each other, the lower frame comprises a second U-shaped frame and a second L-shaped frame which are perpendicular to each other, the first U-shaped frame is located above the second U-shaped frame and is arranged in parallel to the axis of the engine, the first L-shaped frame and the second L-shaped frame are located between the first U-shaped frame and the second U-shaped frame, the horizontal sections of the first L-shaped frame and the second L-shaped frame at least partially overlap and are parallel to the axis of the engine, and the first U-shaped frame and the second U-shaped frame and the first L-shaped frame and the second L-shaped frame are connected by steel wires in the vertical direction.

4. The universal solid rocket engine test stand of claim 3, wherein: The openings of the first U-shaped frame and the second U-shaped frame face opposite directions, and the horizontal section of the first L-shaped frame is located below the horizontal section of the second L-shaped frame.

5. The universal solid rocket engine test stand of claim 1, wherein: The clamping assembly has two clamping assemblies which are coaxially and spacedly arranged along the axial direction of the engine, and the two clamping assemblies are fixedly installed on the tension integral structure assembly.

6. The universal solid rocket engine test stand of claim 1 or 5, wherein: The clamping power structure comprises a disc, a cam disc and a positioning disc which are concentrically arranged, the positioning disc is fixedly connected with the disc, the cam disc is rotationally connected between the positioning disc and the disc, the centers of the disc, the cam disc and the positioning disc are provided with through holes for the engine to pass through, the positioning disc is provided with a plurality of positioning grooves which extend along the radial direction of the positioning disc, the cam disc is provided with a plurality of curved grooves which are distributed in a spiral radial manner, each clamping claw is arranged in one-to-one correspondence in the positioning groove, and one end of each clamping claw close to the cam disc is slidably connected in the corresponding curved groove.

7. The universal solid rocket engine test stand of claim 6, wherein: The edge of the disc is provided with a limiting clamping groove for limiting the rotation of the cam disc.

8. The universal solid rocket engine test stand of claim 6, wherein: The clamping claw has a cylindrical section for slidably connecting with the curved groove, a positioning block for matching with the positioning groove and a clamping block for abutting and clamping the engine, and the cylindrical section and the clamping block are fixedly connected to the two sides of the positioning block respectively.

9. The universal solid rocket engine test stand of claim 1 or 5, wherein: The sensor is coaxially arranged with the clamping assembly.

10. The universal solid rocket engine test stand of claim 1, wherein: The application further comprises protective frames arranged on both sides of the clamping assembly in the axial direction.

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