Rocket engine thrust test system and system use method thereof

Abstract

The application discloses a rocket engine thrust test system, which comprises a thrust test platform, a rocket body frame and a test element. The rocket body frame is installed in a linear moving mode along the length direction of the thrust test platform. The two ends of the length direction of the rocket body frame are respectively provided with a bracket device. The rocket engine rocket body is horizontally installed on the rocket body frame and is clamped and fixed through the two bracket devices. The test element comprises a bearing wall, a thrust sensor and a thrust transition frame. The thrust sensor is fixedly installed on the outer wall of the bearing wall. The thrust transition frame is fixedly connected to the head of the rocket engine rocket body. The thrust sensor is in close contact with the thrust transition frame. The bracket device, the radial limiting device and the central positioning frame are used for realizing the positioning and movement limitation of the rocket body, so that the interference term is eliminated, the rocket engine can generate thrust in the set direction, the accurate thrust data can be ensured, and the thrust test demand of the rocket engine can be well met.

Description

Technical Field

[0001] This invention relates to the field of rocket engine performance testing technology, and more specifically, to a rocket engine thrust testing system and its usage method. Background Technology

[0002] Rocket engines are a crucial component of launch vehicles, and thrust is one of the most important performance indicators. Once designed, any rocket engine must first meet thrust design standards. Given the massive size of rocket engines, thrust testing requires not only stable mounting but also minimizing interference to obtain accurate thrust data. Therefore, companies need to develop specialized equipment for rocket engine thrust prediction testing to meet customer needs, leading to this project. Summary of the Invention

[0003] The purpose of this invention is to address the needs of the prior art by providing a rocket engine thrust testing system and its usage method. This invention features a rationally designed layout, using a rocket body frame to support the horizontally positioned rocket engine body. A support device, radial limiting device, and central positioning frame are used to position and restrict the movement of the rocket body, thereby eliminating interference and ensuring that the rocket engine generates thrust in the set direction, thus ensuring accurate thrust data. This invention effectively meets the thrust testing requirements of rocket engines.

[0004] To achieve the above objectives, the present invention adopts the following technical solution:

[0005] A rocket engine thrust testing system includes a thrust testing platform, a rocket body frame, and testing elements. The rocket body frame is movably mounted on the platform surface and moves linearly along the length of the platform. Support devices are installed at both ends of the rocket body frame along its length. The rocket engine body is horizontally mounted on the rocket body frame and clamped and fixed by the two support devices. The testing elements include a load-bearing wall, a thrust sensor, and a thrust transition frame. The load-bearing wall is installed facing the head of the rocket engine body. The thrust sensor is fixedly installed on the outer wall of the load-bearing wall. The thrust transition frame is fixedly connected to the head of the rocket engine body, and the thrust sensor is in close contact with the thrust transition frame.

[0006] Furthermore, the two support devices are arranged in parallel. Each support device includes a support body and a gantry frame. The support body is bolted to the rocket body frame. The top of the support body is recessed to form an arc-shaped groove that matches the diameter of the rocket engine body. The rocket engine body is horizontally installed in the arc-shaped groove. The gantry frame straddles the outside of the rocket engine body. A radial clamping device is installed on the top of the gantry frame. The radial clamping device includes a first telescopic element that can be adjusted vertically. The first telescopic element is connected to an arc-shaped pressure seat, which is downwardly fitted and pressed against the outer wall of the rocket engine body.

[0007] Furthermore, the rocket frame includes a frame body, on which a positioning strip seat is fixedly installed on the top surface. The support body has a positioning slot, the size of which is adapted to the cross-sectional size of the positioning strip seat. The support body is positioned and installed by inserting the positioning strip seat into the positioning slot.

[0008] Furthermore, the test element also includes a preload device, which includes two preload rod mechanisms. The two preload rod mechanisms are installed on both sides of the thrust sensor. The preload rod mechanisms are connected to the thrust transition frame. The preload rod mechanisms pull the thrust transition frame toward the thrust sensor. The thrust sensor and the thrust transition frame are kept in close contact by the preload device.

[0009] Furthermore, the pre-tightening rod mechanism includes a fixed base, a hinge, and a screw connecting shaft. The fixed base is bolted to the outer wall of the load-bearing wall. One end of the hinge is connected to the fixed base, and the other end of the hinge is connected to the screw connecting shaft. The screw connecting shaft has a threaded section. A linkage plate is fixedly connected to the outside of the thrust transition frame. The screw connecting shaft can be movably inserted into the linkage plate through the threaded section. A pre-tightening nut is installed on the threaded section of the screw connecting shaft. By pressing the linkage plate with the pre-tightening nut, the thrust transition frame will be pulled towards the direction of the thrust sensor.

[0010] Furthermore, the tail of the rocket engine extends beyond the rocket body frame. A central positioning frame is installed on the thrust test platform. The tail of the rocket engine is inserted through the central positioning frame. The central positioning frame includes an upper support frame, a lower support frame, and a clamp. The upper and lower support frames are stacked and assembled to form a positioning cavity. The clamp is clamped to the outer wall of the tail of the rocket engine and is fitted into the positioning cavity. The central positioning frame is equipped with four radial limiting devices. The four radial limiting devices are evenly distributed around the circumference of the positioning cavity. Each radial limiting device includes a second telescopic element. The second telescopic element is connected to a radial limiting roller. The radial limiting roller contacts the outer wall of the clamp to form a radial limit on the tail of the rocket engine.

[0011] Furthermore, the thrust test platform is equipped with four side limiting devices, which are arranged around the rocket body frame. Four limiting beams are connected to the two long sides of the frame body, and the four side limiting devices are connected to the four limiting beams in a one-to-one correspondence.

[0012] Furthermore, the side limiting device includes a frame body with an open area formed on one side. The limiting beam is inserted into the open area. A first limiting device is installed on the top of the frame body, and a second limiting device is installed on the side of the frame body. The first and second limiting devices have the same structure. Both the first and second limiting devices include a third telescopic element. The third telescopic element is connected to a lateral limiting roller. The lateral limiting rollers are all installed facing the open area. The lateral limiting roller of the first limiting device contacts the upper end face of the limiting beam, and the lateral limiting roller of the second limiting device contacts the outer side face of the limiting beam.

[0013] Furthermore, a fire extinguishing device is installed on the side of the thrust test platform. The fire extinguishing device includes a fire extinguisher, a water tank, and a pipeline assembly. The fire extinguisher includes a base, a shaft, and a cantilever beam. The shaft is vertical and movably connected to the base. The cantilever beam is horizontally connected to the shaft. One end of the pipeline assembly is connected to the water tank, and the other end is laid on the cantilever beam. The liquid outlet end of the pipeline assembly can be inserted into the tail nozzle of the rocket engine body by the planar rotation of the cantilever beam. A mobile workshop is also installed on the installation site of the thrust test platform. The mobile workshop can move linearly and can cover the outside of the thrust test platform and the test element.

[0014] A method for using a rocket engine thrust testing system, applicable to a rocket engine thrust testing system, includes the following steps:

[0015] (a) The mobile workshop was moved and evacuated, exposing the thrust test platform and test components;

[0016] (b) The rocket engine is installed horizontally on the rocket body frame, and the rocket body is clamped and fixed by assembling two support devices;

[0017] (c) Install a thrust transition frame at the head of the rocket engine body, push the rocket body frame towards the load-bearing wall until the thrust transition frame contacts the thrust sensor, operate the pre-tightening device to form a contact pre-tightening force, so that the transition frame and the thrust sensor are in close contact.

[0018] (d) Install side limiting devices to restrict the left and right swing and upward jumping of the rocket body frame through four side limiting devices;

[0019] (e) Install a center positioning frame, which is fitted onto the outside of the tail section of the rocket engine to limit the movement of the tail section of the rocket engine.

[0020] (f) The engine is ignited to conduct a thrust test. After the thrust test is completed, the fire extinguishing device is activated. The fire extinguisher of the fire extinguishing device injects fire extinguishing liquid from the nozzle at the tail of the rocket engine body to extinguish the engine fire. After the fire extinguishing is completed, the fire extinguisher is reset.

[0021] (g) After the rocket engine has cooled down, it will be dismantled. After the rocket engine is dismantled, the mobile workshop will be moved and reset, and the thrust test platform and test components will be re-covered and protected.

[0022] The beneficial effects of this invention are:

[0023] 1. The present invention has a reasonable design layout. The rocket engine body is supported by the rocket body frame, and the positioning and movement restriction of the rocket body are achieved by the support device, radial limit device and central positioning frame, thereby eliminating interference and ensuring that the rocket engine generates thrust in the set direction, and ensuring that accurate thrust data is obtained. The present invention can well meet the thrust testing requirements of rocket engines.

[0024] 2. The present invention has specially designed a pre-tensioning device to protect the thrust sensor. Before the rocket engine is ignited, the pre-tensioning device makes the thrust sensor and the thrust transition frame in close contact. This design can significantly reduce the probability of damage to the thrust sensor.

[0025] 3. This invention is designed with a fire extinguishing device. After the thrust test is completed, the fire extinguishing device can respond quickly and extinguish the fire by accurately injecting fire extinguishing fluid into the tail of the rocket engine. This design can ensure the safe conduct of the rocket engine thrust test experiment. Attached Figure Description

[0026] Figure 1 This is a top view of the structure of a rocket engine thrust testing system in this embodiment;

[0027] Figure 2 This is a schematic diagram of the structure in this embodiment;

[0028] Figure 3 This is a three-dimensional structural diagram of the rocket body frame in this embodiment;

[0029] Figure 4 This is a front view of the mounting bracket device in this embodiment;

[0030] Figure 5 This is a schematic diagram of the support device with a replaceable bracket installed in this embodiment;

[0031] Figure 6This is a three-dimensional structural diagram of the gantry in this embodiment;

[0032] Figure 7 This is a three-dimensional structural diagram of the central positioning frame in this embodiment;

[0033] Figure 8 This is a front view of the central positioning frame in this embodiment;

[0034] Figure 9 This is a three-dimensional structural diagram of the side limiting device in this embodiment;

[0035] Figure 10 This is a front view of the side limiting device in this embodiment;

[0036] Figure 11 This is a three-dimensional external structural diagram of the third telescopic element in this embodiment;

[0037] Figure 12 This is a cross-sectional view of the third telescopic element in this embodiment;

[0038] Figure 13 This is a top view of the connection structure between the preload device and the thrust transition frame in this embodiment;

[0039] Figure 14 This is a three-dimensional external structural diagram of the preload device in this embodiment;

[0040] Figure 15 This is a three-dimensional external structural diagram of the fire extinguisher in this embodiment.

[0041] Reference numerals: 1. Thrust testing platform; 2. Rocket frame; 21. Frame body; 21. Limiting beam; 211. Process groove; 212. Hook lug; 213. Positioning strip seat; 214. Support device; 3. Support body; 31. Arc-shaped groove; 311. Support pad layer; 312. Positioning slot; 313. Support notch; 314. Gantry frame; 32. Replaceable support; 33. Radial clamping device; 34. First telescopic element; 341. Arc-shaped pressure seat; 342. Felt layer; 343. Testing element; 4. Load-bearing wall; 41. Thrust sensor; 42. Thrust transition frame; 43. Linkage plate; 431. Pre-tightening device; 44. Pre-tightening rod mechanism; 441. Fixed seat; 4411. Hinge; 4412. Screw connecting shaft; 4413. Pre-tightening nut; 4414. Center positioning frame; 5. Upper support frame; 51. Lower support frame; 52. Hand operating hole; 521. 53. Positioning cavity 54. Clamp 55. Upper semicircle 541. Lower semicircle 542. Reinforcing rib 543. Notch area 544. Radial limiting device 55. Second telescopic element 551. Radial limiting roller 552. Power handwheel 553. Side limiting device 6. Frame body 61. Opening area 611. First limiter 62. Third telescopic element 621. Cylinder 6211. Adjusting screw 6212. Telescopic column 6213. Nail head groove 62131. Guide screw 6214. Wheel fork seat 6215. Side limiting roller 622. Second limiter 63. Fire extinguishing device 7. Fire extinguisher 71. Base 711. Shaft 712. Cantilever beam 713. Water tank 72. Pipe assembly 73. First infusion tube 731. Second infusion tube 732. Infusion hose 733. Mobile workshop 8. Detailed Implementation

[0042] 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.

[0043] like Figures 1-15The system illustrates a rocket engine thrust testing system for testing rocket engine thrust. It includes a thrust testing platform 1, a rocket body frame 2, and testing elements 4. The thrust testing platform 1 is fixedly installed on the ground. The rocket body frame 2 is movably installed on the platform surface of the thrust testing platform 1. The thrust testing platform 1 is cuboid in shape. Two parallel tracks are laid on the platform surface along the length of the thrust testing platform 1. The rocket body frame 2 includes a frame body 21 with several wheel sets 22 mounted on its bottom surface. The wheel sets 22 are fitted onto the two tracks to allow the rocket body frame 2 to move linearly along the length of the thrust testing platform 1. Support devices 3 are installed at both ends of the rocket body frame 2 along its length. The rocket engine body is horizontally mounted on the rocket body frame 2 and held and fixed by the two support devices 3. With the support devices 3 in place, the rocket engine body and the rocket body frame 2 form an integrated unit, enabling them to move together. Test element 4 includes a load-bearing wall 41, a thrust sensor 42, and a thrust transition frame 43. The load-bearing wall 41 is also fixed to the ground and needs to be designed to withstand the maximum thrust of the rocket engine. The load-bearing wall 41 is installed directly opposite the rocket engine's nose section. After the rocket engine ignites, the rocket engine and the rocket body frame 2 drive towards the load-bearing wall 41. After being blocked by the load-bearing wall 41, the thrust is generated in the direction of the load-bearing wall 41. The thrust sensor 42 is fixedly installed on the outer wall of the load-bearing wall 41 (facing the direction of thrust generation). The thrust transition frame 43 is fixedly connected to the rocket engine's nose section. The thrust sensor 42 and the thrust transition frame 43 are in close contact. The thrust transition frame 43 is equivalent to an extension of the rocket engine's nose section. After the rocket engine ignites, the thrust transition frame 43 squeezes the thrust sensor 42 under the action of thrust. The thrust sensor 42 measures the thrust data. The thrust sensor 42 is also connected to a central computer (not shown in the figure) and transmits the measured thrust data to the central computer in real time for analysis.

[0044] like Figure 3As shown, two support devices 3 are arranged in parallel, with bolt holes along the length of the frame body 21. The two support devices 3 are connected to the bolt hole group as needed (the spacing between the two support devices 3 is configured according to the different lengths of the rocket engine body). The support device 3 includes a support body 31 and a gantry 32. The bottom surface of the support body 31 is bolted to the frame body 21. The support body 31 serves to support the rocket body. Therefore, an arc-shaped groove 311 matching the diameter of the rocket engine body is formed in the top of the support body 31. The rocket engine body is horizontally inserted into the arc-shaped groove 311. A padding layer 312 (attached with high-strength adhesive) is added to the arc-shaped groove 311. The padding layer 312 is made of felt material and contacts the rocket engine body to ensure that the rocket body is not damaged during the clamping process. The gantry 32 straddles the rocket engine body. On the outside, the two bottom feet of the gantry frame 32 are respectively connected to the two ends of the support body 31 along the length direction by flange bolts. A radial clamping device 34 is installed on the top of the gantry frame 32. The radial clamping device 34 includes a first telescopic element 341 that can be adjusted vertically (the specific structure of the first telescopic element 341 will be introduced later). The first telescopic element 341 is connected to an arc-shaped pressure seat 342. The first telescopic element 341 can drive the arc-shaped pressure seat 342 to move vertically up and down. After the arc-shaped pressure seat 342 moves downward, it can fit and press against the outer wall of the rocket engine body. In this way, the horizontally lying rocket engine body can be clamped and fixed in the support device 3. A felt layer 343 (high-strength adhesive bonding) is pasted and connected to the arc-shaped surface of the arc-shaped pressure seat 342. The arc-shaped pressure seat 342 contacts the rocket engine body with the felt layer 343. This is also to ensure that the rocket body is not damaged during the clamping process.

[0045] like Figure 3 As shown, a positioning strip seat 214 is fixedly installed on the top surface of the frame body 21, such as... Figure 4 As shown, the support body 31 has a positioning slot 313. The size of the positioning slot 313 is adapted to the cross-sectional size of the positioning strip seat 214. During installation, the support body 31 is positioned and installed by inserting the positioning strip seat 214 into the positioning slot 313. The above design is to facilitate the precise installation of the support body 31. Through the cooperation of the positioning strip seat 214 and the positioning slot 313, the support body 31 can be easily aligned with the bolt mounting holes after installation, which reduces the installation difficulty and enables rapid assembly.

[0046] like Figure 3 As shown, the frame body 21 has several process grooves 212. This is to reduce the weight of the frame body 21, which not only reduces the cost of production materials but also reduces the moving friction of the rocket frame 2, thus reducing the interference of the moving friction of the rocket frame 2 on the thrust data. Figure 3As shown, hook lugs 213 are connected and installed on both short side end faces along the length of the frame body 21. The rocket engine and rocket body frame 2 are very heavy and need to be pulled by a cable traction mechanism (the cable traction mechanism is a commercially available device and is not shown in the figure). The hook lugs 213 are used to thread the cable to facilitate the cable traction mechanism to pull the rocket engine and rocket body frame 2.

[0047] The rocket engines that actually need to be tested have varying diameters. To accommodate rocket engine bodies of different diameters, such as... Figure 5 As shown, the present invention replaces the support notch 314 in the center of the support body 31, and inserts a replacement support 33 into the support notch 314. The replacement support 33 is installed by fixing with bottom flange bolts and limiting with side bolts. The replacement support 33 has arc-shaped grooves 311 with different diameters to meet the support of rocket engine bodies of different diameters. The radius of the arc-shaped grooves 311 currently designed is 300-1200mm, which can basically cover the support requirements of conventional rocket engine bodies.

[0048] In the preparatory stage of thrust testing, the thrust transition frame 43 needs to be pushed to contact the thrust sensor 42. However, even when the contact between the thrust transition frame 43 and the thrust sensor 42 is visually observed, a small gap still exists between them. This is extremely dangerous during thrust testing. The rocket engine generates a large thrust instantaneously upon ignition. If a small gap (even just a few micrometers) exists between the thrust transition frame 43 and the thrust sensor 42, the thrust transition frame 43 will impact the thrust sensor 42 with a large impact force, causing instantaneous damage to the thrust sensor 42 and rendering the thrust test invalid. Since the rocket engine has already ignited, this will result in significant cost losses. To eliminate the above problems, the test element 4 of this invention is also designed to include a pre-tensioning device 44, such as... Figure 13 and Figure 14As shown, the preload device 44 includes two preload rod mechanisms 441, which are installed on both sides of the thrust sensor 42. The preload rod mechanisms 441 are connected to the thrust transition frame 43. The preload rod mechanisms 441 can pull the thrust transition frame 43 towards the thrust sensor 42, thereby generating a preload force to keep the thrust sensor 42 and the thrust transition frame 43 in close contact. The preload rod mechanism 441 includes a fixed seat 4411, a hinge 4412, and a screw connecting shaft 4413. The fixed seat 4411 is bolted to the outer wall of the load-bearing wall 41, and one end of the hinge 4412 is connected to the fixed seat 4411. The fixed seat 4411 and the other end of the hinge 4412 are connected to the screw connecting shaft 4413. With the hinge 4412 connected, the screw connecting shaft 4413 can move up and down and left and right. The screw connecting shaft 4413 is provided with a threaded section. The thrust transition frame 43 is externally fixedly connected to the linkage plate 431. In use, the screw connecting shaft 4413 is manually operated so that its threaded section moves and inserts into the linkage plate 431 (the linkage plate 431 has an insertion notch). The threaded section of the screw connecting shaft 4413 is equipped with a preload nut 4414. The preload nut 4414 is screwed in from the side near the rocket engine head. After 414 is turned toward the thrust sensor 42, the preload nut 4414 presses against and tightens onto the linkage plate 431. Continuing to turn the preload nut 4414 will pull the thrust transition frame 43 toward the thrust sensor 42 via the linkage plate 431. Preload force is generated once the thrust sensor 42 and the thrust transition frame 43 are fully in contact. The preload nuts 4414 on the two preload rod mechanisms 441 need to be turned synchronously to ensure a basic balance of preload forces on both sides (the preload forces on both sides only need to be basically balanced; slight errors are not a problem. To ensure minimal error, a digital torque wrench should be used when turning the preload nut 4414). The preload is generally set between 100-300KG. Since the preload nut 4414 is located near the head of the rocket engine, when the rocket engine ignites, the rocket engine generates a thrust in the direction of the thrust sensor 42, which causes the thrust transition frame 43 to squeeze the thrust sensor 42. The thrust transition frame 43 will definitely have a certain displacement in the direction of the thrust sensor 42 (the thrust sensor 42 undergoes slight deformation and compression). At this time, the linkage plate 431 can instantly disengage from the preload nut 4414, and the preload disappears instantly. The thrust sensor 42 then measures the thrust data. The preload does not interfere with the acquisition of the thrust data.

[0049] In rocket engine thrust testing experiments, it is crucial to eliminate interference factors as much as possible to obtain a relatively accurate thrust figure. After rocket engine ignition, significant radial runout occurs at the tail position, which is not only a major interference factor but also affects the safety radius of the experiment. Therefore, this invention features a special design for the tail position, such as... Figure 2As shown, in this invention, the tail of the rocket engine extends beyond the rocket body frame 2, and a central positioning frame 5 is installed on the thrust testing platform 1. The tail of the rocket engine is inserted through the central positioning frame 5, as shown. Figure 7 and Figure 8 As shown, the central positioning frame 5 includes an upper support frame 51, a lower support frame 52, and a clamp 54. The upper support frame 51 and the lower support frame 52 are stacked and assembled, forming a through positioning cavity 53 inside the central positioning frame 5. The clamp 54 includes an upper semicircle 541 and a lower semicircle 542. After being bolted together, the upper semicircle 541 and the lower semicircle 542 can clamp onto the outer wall of the rocket engine tail section. The tail section of the rocket engine body is partially fitted into the positioning cavity 53 by the clamp 54. The central positioning frame 5 is then installed... The system is equipped with four radial limiting devices 55, which are evenly distributed around the circumference of the positioning cavity 53. Each radial limiting device 55 includes a second telescopic element 551 (the specific structure of the second telescopic element 551 will be described later). The second telescopic element 551 is connected to and installed with a radial limiting roller 552. The radial limiting roller 552 contacts the outer wall of the clamp 54 to form a radial limit on the tail of the rocket engine body, thereby controlling the radial runout of the tail of the rocket engine body. This reduces the thrust error caused by the radial runout of the tail and ensures the smooth progress of the experimental installation. Figure 8 As shown, the lower support frame 52 has two manual operation holes 521 to facilitate the installation and operation of the two radial limiting devices 55. The clamp 54 has vertical reinforcing ribs 543 connected to the upper semicircle 541 and the lower semicircle 542. The reinforcing ribs 543 can improve the strength of the clamp 54. The reinforcing ribs 543 have four notch areas 544, and the four notch areas 544 correspond to the installation positions of the four radial limiting devices 55 respectively.

[0050] Besides the vibration interference at the tail of the rocket engine, the lateral movement and upward vibration of the rocket body after ignition are also significant interference factors, which can easily affect thrust test data and cause experimental safety risks. Therefore, this invention installs four side limiting devices 6 on the thrust test platform 1 to solve the above problems. The four side limiting devices 6 are arranged around the rocket body frame 2. This invention connects four limiting beams 211 to the two long sides of the frame body 21, arranged in pairs, with the two sets of limiting beams 211 symmetrically arranged. The four side limiting devices 6 are connected one-to-one with the four limiting beams 211 to form lateral limiting around the rocket body frame 2. Figure 9 and Figure 10As shown, the side limiting device 6 includes a frame 61, which is C-shaped. An open area 611 is formed on one side of the frame 61. When the side limiting device 6 is installed, the end of the limiting beam 211 is inserted into the open area 611. A first limiter 62 is installed on the top of the frame 61, and a second limiter 63 is installed on the side of the frame 61. The first limiter 62 and the second limiter 63 have the same structure. Both the first limiter 62 and the second limiter 63 include a third telescopic element 621. Lateral limiting rollers 622 are connected and installed on 621. All lateral limiting rollers 622 are installed facing the open area 611. The lateral limiting rollers 622 of the first limiter 62 contact the upper end face of the end of the limiting beam 211 (the contact surface is thickened and reinforced), thus limiting the upward movement of the rocket body frame 2 (limiting the rocket body frame 2 is equivalent to limiting the rocket engine body). The lateral limiting rollers 622 of the second limiter 63 contact the outer surface of the limiting beam 211, thus limiting the left and right swing of the rocket body frame 2. Figure 11 and Figure 12As shown, in this invention, the third telescopic element 621 includes a cylindrical body 6211, an adjusting screw 6212, and a telescopic column 6213. The cylindrical body 6211 is fixedly installed. The adjusting screw 6212 is partially inserted into the cylindrical body 6211 and rotatably connected to it. The telescopic column 6213 is also partially inserted into the cylindrical body 6211. The inserted part of the telescopic column 6213 is threadedly connected to the adjusting screw 6212. A nail head groove 62131 is provided on the outer wall of the telescopic column 6213. A guide screw 6214 is threaded onto the outer side of the cylindrical body 6211. The end of guide screw 6214 extends through the cylinder 6211 and into the nail head groove 62131. The end of guide screw 6214 can move within the nail head groove 62131. The cooperation between guide screw 6214 and nail head groove 62131 prevents telescopic column 6213 from rotating. When adjusting screw 6212 rotates, linear drive, i.e., telescopic movement, can be achieved for telescopic column 6213. A wheel fork seat 6215 is connected to the outer end of telescopic column 6213 on the cylinder 6211. Lateral limiting roller 622 is rotatably mounted on wheel fork seat 6215. The screw 6212 is connected to an auxiliary handwheel 553 at the outer end of the cylinder 6211. The auxiliary handwheel 553 allows for easy rotation and adjustment of the screw 6212. In this invention, the first telescopic element 341 on the gantry 32 and the second telescopic element 551 on the center positioning frame 5 have the same structure as the third telescopic element 621 on the side limiting device 6. The first telescopic element 341 on the gantry 32 also has a telescopic column 6213, the end of which is connected to an arc-shaped pressure seat 342. The second telescopic element 551 on the center positioning frame 5... 1. It also has a telescopic column 6213, the end of which is connected to a radial limiting roller 552. Whether it is the radial limiting roller 552 or the lateral limiting roller 622, its rotation direction matches the direction generated by the thrust. That is to say, the radial limiting roller 552 or the lateral limiting roller 622 does not restrict the axial movement (that is, the movement in the thrust direction) of the rocket engine and the rocket body frame 2, and does not affect the acquisition of thrust data. The radial limiting roller 552 or the lateral limiting roller 622 will have a small amount of frictional resistance, but it has little impact on the thrust data.

[0051] After completing the thrust test using this invention, it is essential to extinguish the fire in the rocket engine. Therefore, as Figure 1 As shown, the present invention has a fire extinguishing device 7 installed on the side of the thrust test platform 1. The fire extinguishing device 7 is used to complete the fire extinguishing operation. The fire extinguishing device 7 includes a fire extinguisher 71, a water tank 72, and a pipe assembly 73. The water tank 72 stores the fire extinguishing liquid required for fire extinguishing, such as... Figure 15As shown, the fire extinguisher 71 includes a base 711, a shaft 712, and a cantilever beam 713. The shaft 712 is vertically connected to the base 711 and needs to have lifting and planar rotation functions. The installation structure of the shaft 712 is similar to the spindle of a cantilever drilling machine, which is an existing technical solution and will not be described in detail here. The cantilever beam 713 is horizontally fixedly connected to the shaft 712 and can be lifted or rotated in a planar manner with the shaft 712. One end of the pipe assembly 73 is connected to the water tank 72, and the other end is laid on the cantilever beam 713. The planar rotation of the cantilever beam 713 allows the liquid outlet end of the pipe assembly 73 to be inserted into the tail nozzle of the rocket engine body, spraying fire extinguishing fluid into the tail nozzle of the rocket engine to achieve rapid fire extinguishing and cooling. In order to be suitable for testing rocket engines of different lengths, the present invention also provides a track for the fire extinguisher 71. The fire extinguisher 71 can travel along the track. The height adjustment function of the cantilever beam 713 is designed to accommodate rocket engine bodies of different diameters, ensuring accurate spraying of fire extinguishing fluid. In this invention, the pipeline assembly 73 is designed to include a first fluid delivery rigid pipe 731, a second fluid delivery rigid pipe 732, and a fluid delivery hose 733. The first fluid delivery rigid pipe 731 is connected to the water tank 72, and the second fluid delivery rigid pipe 732 is laid and installed on the cantilever beam 713. The first fluid delivery rigid pipe 731 and the second fluid delivery rigid pipe 732 are connected by the fluid delivery hose 733. The hose design is to accommodate the mobility of the fire extinguisher 71. Rocket engine testing experiments are conducted in uninhabited areas such as the Gobi Desert and other barren lands. These areas often experience severe weather conditions such as significant temperature differences between day and night and strong winds and sandstorms. These environments have a significant impact on the service life and accuracy of experimental instruments. Therefore, such as Figure 1 As shown, the present invention also installs a mobile workshop 8 on the installation site of the thrust test platform 1. The mobile workshop 8 is counterweighted and runs along a track. The mobile workshop 8 can move in a straight line along the track. The running direction of the mobile workshop 8 is the length direction of the thrust test platform 1. The mobile workshop 8 needs to be able to cover the outside of the thrust test platform 1 and the test element 4. The mobile workshop 8 is equipped with an air conditioner and a drive mechanism. The mobile workshop 8 can provide a constant temperature and wind-free storage environment for the instruments and equipment. Sometimes, rocket engines are installed in advance, and it is even more necessary to protect and store them through the mobile workshop 8.

[0052] A method for using a rocket engine thrust testing system, applicable to a rocket engine thrust testing system, includes the following steps:

[0053] (a) Move the mobile workshop 8 away to expose the thrust test platform 1 and test element 4;

[0054] (b) The rocket engine is installed horizontally on the rocket body frame 2, and the rocket body is clamped and fixed by assembling two support devices 3;

[0055] (c) Install the thrust transition frame 43 at the head of the rocket engine body, push the rocket body frame 2 towards the load-bearing wall 41 until the thrust transition frame 43 contacts the thrust sensor 42, operate the preload device 44, and form a contact preload by tightening the preload nuts 4414 on the two preload rod mechanisms 441, so that the transition frame 43 and the thrust sensor 42 are in close contact. The preload is generally set in the range of 100-300KG.

[0056] (d) After the rocket engine pre-tightening connection is completed, the side limiting device 6 is installed. The four side limiting devices 6 are installed corresponding to the four limiting beams 211 respectively. The lateral limiting rollers 622 on the side limiting device 6 contact the ends of the limiting beams 211. The left and right swing and upward jump of the rocket body frame 2 are restricted by the four side limiting devices 6.

[0057] (e) After the side limit is installed, the center positioning frame 5 is installed. First, the clamp 54 is installed on the tail of the rocket engine body, and then the center positioning frame 5 is fitted onto the clamp 54. The radial limit device 55 is adjusted so that the radial limit roller 552 contacts the outer wall of the clamp 54. The tail of the rocket engine body is limited by the four radial limit devices 55 installed in a circumferential manner.

[0058] (f) After the central positioning frame 5 is installed, the rocket engine can be ignited to conduct a thrust test. After the thrust test is completed, the fire extinguishing device 7 is activated. The cantilever beam 713 on the fire extinguisher 71 rotates to drive the second liquid delivery pipe 732 toward the tail nozzle of the rocket engine. The outlet of the second liquid delivery pipe 732 is inserted into the tail nozzle of the rocket engine to inject fire extinguishing fluid to extinguish the engine fire. After the fire is extinguished, the fire extinguisher 71 moves in the opposite direction to reset.

[0059] (g) After the rocket engine cools down, it is dismantled. After the rocket engine is dismantled, the mobile workshop 8 is moved and reset, and the thrust test platform 1 and test element 4 are re-covered and protected.

[0060] The above description is merely a preferred embodiment of the present invention. The scope of protection of the present invention is not limited to the above embodiments. All technical solutions falling within the scope of the present invention's concept are within the scope of protection of the present invention. It should be noted that for those skilled in the art, any improvements and modifications made without departing from the principles of the present invention should also be considered within the scope of protection of the present invention.

Claims

1. A rocket engine thrust testing system, characterized in that, The test includes a thrust test platform (1), a rocket body frame (2), and a test element (4). The rocket body frame (2) is movably mounted on the platform of the thrust test platform (1). The rocket body frame (2) moves linearly along the length of the thrust test platform (1). Support devices (3) are installed at both ends of the rocket body frame (2) along the length of the rocket body frame (2). The rocket engine body is horizontally mounted on the rocket body frame (2) and clamped and fixed by the two support devices (3). The test element (4) includes a load-bearing wall (41), a thrust sensor (42), and a thrust transition frame (43). The load-bearing wall (41) is installed facing the head of the rocket engine body. The thrust sensor (42) is fixedly installed on the outer wall of the load-bearing wall (41). The thrust transition frame (43) is fixedly connected to the head of the rocket engine body. The thrust sensor (42) and the thrust transition frame (43) are in close contact.

2. The rocket engine thrust testing system according to claim 1, characterized in that, Two support devices (3) are arranged in parallel. Each support device (3) includes a support body (31) and a gantry frame (32). The support body (31) is bolted to the rocket body frame (2). The top of the support body (31) is recessed to form an arc-shaped groove (311) that matches the diameter of the rocket engine body. The rocket engine body is horizontally installed in the arc-shaped groove (311). The gantry frame (32) is straddled on the outside of the rocket engine body. A radial pressing device (34) is installed on the top of the gantry frame (32). The radial pressing device (34) includes a first telescopic element (341) that can be extended and retracted in the vertical direction. The first telescopic element (341) is connected to an arc-shaped pressure seat (342). The arc-shaped pressure seat (342) is adapted to press against the outer wall of the rocket engine body.

3. The rocket engine thrust testing system according to claim 2, characterized in that, The rocket frame (2) includes a frame body (21), on which a positioning strip seat (214) is fixedly installed. The support body (31) has a positioning slot (313), the size of which is adapted to the cross-sectional size of the positioning strip seat (214). The support body (31) is positioned and installed by inserting the positioning strip seat (214) into the positioning slot (313).

4. The rocket engine thrust testing system according to claim 1, characterized in that, The test element (4) also includes a pre-tensioning device (44), which includes two pre-tensioning rod mechanisms (441). The two pre-tensioning rod mechanisms (441) are installed on both sides of the thrust sensor (42). The pre-tensioning rod mechanism (441) is connected to the thrust transition frame (43). The pre-tensioning rod mechanism (441) pulls the thrust transition frame (43) toward the thrust sensor (42). The thrust sensor (42) and the thrust transition frame (43) are kept in close contact by the pre-tensioning device (44).

5. The rocket engine thrust testing system according to claim 4, characterized in that, The pre-tightening rod mechanism (441) includes a fixed seat (4411), a hinge (4412), and a screw connecting shaft (4413). The fixed seat (4411) is bolted to the outer wall of the load-bearing wall (41). One end of the hinge (4412) is connected to the fixed seat (4411), and the other end of the hinge (4412) is connected to the screw connecting shaft (4413). The screw connecting shaft (4413) is provided with a threaded section. The thrust transition frame (43) is externally fixedly connected to a linkage plate (431). The threaded section of the screw connecting shaft (4413) can be movably inserted into the linkage plate (431). The threaded section of the screw connecting shaft (4413) is equipped with a pre-tightening nut (4414). The pre-tightening nut (4414) presses and tightens the linkage plate (431), which will pull the thrust transition frame (43) to move in the direction of the thrust sensor (42).

6. The rocket engine thrust testing system according to claim 1, characterized in that, The tail of the rocket engine extends beyond the rocket body frame (2). A center positioning frame (5) is installed on the platform of the thrust test platform (1). The tail of the rocket engine is inserted through the center positioning frame (5). The center positioning frame (5) includes an upper support frame (51), a lower support frame (52), and a clamp (54). The upper support frame (51) and the lower support frame (52) are stacked and assembled. A positioning cavity (53) is formed by the assembly of the upper support frame (51) and the lower support frame (52). The clamp (54) clamps the rocket engine. The outer wall of the rocket engine tail section is fitted with the clamp (54) into the positioning cavity (53). The central positioning frame (5) is equipped with four radial limiting devices (55). The four radial limiting devices (55) are evenly distributed around the positioning cavity (53). The radial limiting device (55) includes a second telescopic element (551). The second telescopic element (551) is connected to a radial limiting roller (552). The radial limiting roller (552) forms a radial limit on the tail section of the rocket engine body by contacting the outer wall of the clamp (54).

7. The rocket engine thrust testing system according to claim 2, characterized in that, The thrust test platform (1) is equipped with four side limiting devices (6). The four side limiting devices (6) are arranged around the rocket body frame (2). Four limiting beams (211) are connected to the two long sides of the frame body (21). The four side limiting devices (6) and the four limiting beams (211) are connected one-to-one.

8. The rocket engine thrust testing system according to claim 7, characterized in that, The side limiting device (6) includes a frame body (61), an open area (611) is formed on one side of the frame body (61), the limiting beam (211) is inserted into the open area (611), a first limiter (62) is installed on the top of the frame body (61), and a second limiter (63) is installed on the side of the frame body (61). The first limiter (62) and the second limiter (63) have the same structure. Each of the devices (63) includes a third telescopic element (621), which is connected to a lateral limiting roller (622). The lateral limiting rollers (622) are all installed facing the open area (611). The lateral limiting roller (622) of the first limiter (62) contacts the upper end face of the limiting beam (211), and the lateral limiting roller (622) of the second limiter (63) contacts the outer side of the limiting beam (211).

9. The rocket engine thrust testing system according to claim 1, characterized in that, The thrust test platform (1) is equipped with a fire extinguishing device (7) on its side. The fire extinguishing device (7) includes a fire extinguisher (71), a water tank (72), and a pipe assembly (73). The fire extinguisher (71) includes a base (711), a shaft (712), and a cantilever beam (713). The shaft (712) is vertical and movably connected to the base (711). The cantilever beam (713) is horizontally connected to the shaft (712). One end of the pipe assembly (73) is connected to the water tank (72), and the other end is laid on the cantilever beam (713). The liquid outlet end of the pipe assembly (73) can be inserted into the tail nozzle of the rocket engine body by the planar rotation of the cantilever beam (713). A mobile workshop (8) is also installed on the installation site of the thrust test platform (1). The mobile workshop (8) moves in a straight line and can be covered on the outside of the thrust test platform (1) and the test element (4).

10. A method of using a rocket engine thrust testing system, applied to a rocket engine thrust testing system as described in any one of claims 1-9, characterized in that, Includes the following steps: (a) Move the mobile workshop (8) away to expose the thrust test platform (1) and test components (4). (b) The rocket engine is installed horizontally on the rocket body frame (2), and the rocket body is clamped and fixed by assembling two support devices (3); (c) Install a thrust transition frame (43) on the head of the rocket engine body, push the rocket body frame (2) towards the load-bearing wall (41) until the thrust transition frame (43) contacts the thrust sensor (42), operate the pre-tightening device (44) to form a contact pre-tightening force, so that the transition frame (43) and the thrust sensor (42) remain in close contact. (d) Install side limiting devices (6) to limit the left and right swing and upward jumping of the rocket body frame (2) by using four side limiting devices (6); (e) Install the center positioning frame (5). The center positioning frame (5) is fitted onto the outer side of the tail of the rocket engine. The center positioning frame (5) restricts the jumping of the tail of the rocket engine. (f) The engine is ignited to conduct a thrust test. After the thrust test is completed, the fire extinguishing device (7) is activated. The fire extinguisher (71) of the fire extinguishing device (7) injects fire extinguishing liquid from the nozzle at the tail of the rocket engine body to extinguish the engine fire. After the fire extinguishing, the fire extinguisher (71) is reset. (g) After the rocket engine cools down, it is dismantled. After the rocket engine is dismantled, the mobile workshop (8) is moved and reset, and the thrust test platform (1) and test elements (4) are re-covered.

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