Space engine thrust field testing device with stable structure

Abstract

The present application relates to the technical field of aerospace engine thrust testing, and particularly relates to a kind of aerospace engine thrust field testing device with stable structure, comprising test stand mounting seat, lower balance disc, upper balance disc, balance assembly, cross beam loading tool, mounting assembly, gantry base, loading hydraulic lever and standard load cell;The bottom surface of test stand mounting seat is provided with lower balance disc, and the lower balance disc is provided with upper balance disc below, the side of upper balance disc is provided with balance assembly, the bottom surface of upper balance disc is provided with cross beam loading tool, the gantry base is provided below cross beam loading tool, the side of gantry base is provided with loading hydraulic lever, and the other end of loading hydraulic lever is provided with standard load cell;The present application enhances the overall stability of field testing device by two-stage protection, effectively prevents the overall collapse of device when unexpected situation occurs, ensures the safety of field use, so as to more accurately measure the thrust of aerospace engine.

Description

Technical Field

[0001] The present invention relates to the technical field of aerospace engine thrust testing, and in particular to an aerospace engine thrust field testing device with a stable structure. Background Art

[0002] During the space mission, engine thrust is an extremely critical parameter, which is directly related to whether the rocket can overcome the earth's gravity and successfully enter the predetermined orbit. Therefore, it is necessary to use on-site test equipment to accurately measure the thrust values ​​of the engine under different working conditions (such as startup, acceleration, stable operation, shutdown, etc.) to provide an accurate data basis for the rocket's orbit calculation, fuel consumption estimation, etc. According to the on-site test requirements, a field test device needs to be built, and the on-site loading range is 70% of the full scale, which is 70t.

[0003] Most of the current aerospace engine thrust field test equipment installation structures are relatively simple, and the measuring balances are mostly fixed directly to the equipment, lacking effective buffering or protection mechanisms. If the thrust applied to the sensor during the test is abnormal, this sudden and abnormal force transmission is very likely to exceed the limit that the device structure can withstand, and directly cause the entire device to collapse and be damaged. There are certain safety hazards during the field test process, affecting the safety and stability of the field test operations.

[0004] Therefore, in view of the fact that the structural stability of existing aerospace engine thrust field test devices is often poor and there are certain safety hazards, an aerospace engine thrust field test device with a stable structure can be designed. Through the secondary protection method, the device can be prevented from being damaged when the thrust is overloaded, and the overall stability of the test device can be effectively enhanced. The overall collapse of the device in the event of an accident can be prevented, and the safety of on-site use can be guaranteed, thereby effectively improving the accuracy of the thrust test. Summary of the Invention

[0005] In order to overcome the problems of most aerospace engine thrust field test devices, the measuring balance is mostly fixed directly to the device. If the sensor is overloaded, damaged or separated during the test, it may directly cause the entire device to collapse and be damaged, posing certain safety hazards and affecting the safety and stability of field test operations.

[0006] The technical solution of the present invention is: a field test device for aerospace engine thrust with a stable structure, comprising a test bench mounting seat, a lower balance disc, an upper balance disc, a balance assembly, a cross beam loading fixture, a first mounting assembly, a gantry base, a second mounting assembly, a loading hydraulic lever, a third mounting assembly, a first test assembly, a standard force sensor, and a second test assembly; the bottom surface of the test bench mounting seat is provided with a lower balance disc, the test bench mounting seat is provided at a 45° angle to the upper surface of the lower balance disc, an upper balance disc is provided below the lower balance disc, and the lower balance disc and the upper balance disc are connected. The positions are concentrically corresponding, a balance assembly is provided on one side of the upper balance disc, a cross beam loading tooling is provided on the bottom surface of the upper balance disc, a first installation assembly is provided on one side of the cross beam loading tooling, a gantry base is provided below the cross beam loading tooling, a second installation assembly is provided on one side of the gantry base, a loading hydraulic lever is provided on one side of the gantry base, a third installation assembly is provided on the bottom end of the loading hydraulic lever, a first test assembly is provided on one side of the loading hydraulic lever, a standard force sensor is provided on the other end of the loading hydraulic lever, and a second test assembly is provided on one end of the standard force sensor.

[0007] Preferably, a test bench mounting seat is fixed by setting a lower balance disc, the lower balance disc and the upper balance disc are connected and fixed by a balance assembly, a cross-beam loading fixture is installed and fixed by a first mounting assembly, the cross-beam loading fixture is fixed to the bottom surface of the upper balance disc, a standard force sensor is connected and fixed by a cross-beam loading fixture, and the applied force value is evenly distributed to the lower balance disc by the cross-beam loading fixture, so that the thrust applied to the lower balance disc is uniform, ensuring that the test results of the device are accurate, a second mounting assembly is used to fix the connection to the gantry base, the lower balance disc is further supported and fixed by the gantry base, a third mounting assembly is used to fix the position of the loading hydraulic lever, the loading hydraulic lever is fixed to one side of the gantry base, and a first The test component controls the loading hydraulic lever to apply pressure, and uses the loading hydraulic lever to accurately apply vertical pressure or lateral force to the standard force sensor, thereby simulating the thrust of the engine, and testing the engine thrust through the standard force sensor. Among them, the standard force sensor has a range of 1MN and an accuracy level of 0.03. The standard force sensor is connected and fixed to the cross-beam loading fixture through the second test component. When the standard force sensor is overloaded, damaged or separated, the lower balance disc and the upper balance disc become one to prevent accidents, thereby enhancing the overall stability of the test device, preventing the overall collapse of the device in the event of an accident, ensuring the safety of on-site use, and improving the accuracy of the thrust test.

[0008] Preferably, the balance assembly includes an elastic connecting block, a T-shaped through hole and a threaded hole; an elastic connecting block is provided on one side of the lower balance disc, and there are multiple groups of elastic connecting blocks. The elastic connecting block is provided between the lower balance disc and the upper balance disc, and the other side of the elastic connecting block is fixedly connected to the upper balance disc. A T-shaped through hole is provided on one side of the lower balance disc, and there are multiple groups of T-shaped through holes. A threaded hole is provided on one side of the upper balance disc, and there are multiple groups of threaded holes. The threaded holes correspond to the positions of the T-shaped through holes.

[0009] Preferably, the balance assembly also includes a limiting bolt and a fastening nut; a limiting bolt is arranged on the inner side of the T-shaped through hole, one end of the limiting bolt is threadedly connected to the threaded hole, and a fastening nut is arranged on the other end of the limiting bolt, wherein a gap is left between the fastening nut and the T-shaped through hole.

[0010] Preferably, the first mounting assembly includes a first mounting hole and a second mounting hole; a first mounting hole is opened on one side of the cross-beam loading tooling, and the first mounting hole is opened in multiple groups; a second mounting hole is opened on one side of the cross-beam loading tooling, and the second mounting hole is opened in multiple groups; the second mounting holes are opened at the four corners of the cross-beam loading tooling, and the second mounting holes are opened on one side of the upper balance disc; the second mounting hole of the upper balance disc corresponds to the position of the second mounting hole of the cross-beam loading tooling.

[0011] Preferably, the first mounting assembly further includes a first fixing bolt; a first fixing bolt is provided on the inner side of the second mounting hole, a plurality of first fixing bolts are provided, and the first fixing bolts are threadedly connected to the second mounting hole.

[0012] Preferably, the second mounting assembly includes a gantry support, a first mounting plate and a second mounting plate; a gantry support is provided on the upper surface of the gantry base, and the gantry support is provided in multiple groups, and the gantry support is provided at the four corners of the gantry base, and a first mounting plate is provided at one end of the gantry support, and the first mounting plate is provided at one end of the gantry base support, and a second mounting plate is provided on the outer side of the lower balance disc, and the second mounting plate is provided in multiple groups, and the positions of the first mounting plate and the second mounting plate correspond to each other.

[0013] Preferably, the second mounting assembly also includes a third mounting hole and a third fixing bolt; a third mounting hole is opened on one side of the first mounting plate, and multiple groups of third mounting holes are opened. The third mounting hole is opened on one side of the second mounting plate, and a third fixing bolt is provided on the inner side of the third mounting hole, and the third fixing bolt is threadedly connected to the third mounting hole.

[0014] Preferably, the third mounting assembly includes a connecting flange, a fourth mounting hole and a fourth fixing bolt; a connecting flange is provided at the bottom end of the loading hydraulic lever, the connecting flange is provided on one side of the gantry base, a fourth mounting hole is provided on one side of the connecting flange, multiple groups of fourth mounting holes are provided, the fourth mounting holes are provided on one side of the gantry base, the fourth mounting holes on one side of the gantry base correspond to the positions of the fourth mounting holes on one side of the connecting flange, a fourth fixing bolt is provided on the inner side of the fourth mounting hole, multiple groups of fourth fixing bolts are provided, and the fourth fixing bolt is threadedly connected to the fourth mounting hole.

[0015] Preferably, the first test component includes a cylinder protective shell, a cylinder piston, a cylinder oil inlet and a cylinder oil outlet; a cylinder protective shell is provided on the outside of the loading hydraulic lever, a cylinder piston is provided on the inside of the loading hydraulic lever, the cylinder piston and the loading hydraulic lever are slidingly connected to each other, a cylinder oil inlet is provided on one side of the loading hydraulic lever, and a cylinder oil outlet is provided on one side of the loading hydraulic lever.

[0016] Preferably, the second test assembly includes a sphere fixing seat, a sphere limit seat and a connecting sphere; a sphere fixing seat is provided at one end of the standard force sensor, a sphere limit seat is provided at the bottom surface of the cross beam loading tooling, a connecting sphere is provided on one side of the sphere fixing seat, the connecting sphere is provided on the inner side of the sphere limit seat, and the connecting sphere and the sphere limit seat are rotatably connected to each other.

[0017] Beneficial effects of the present invention:

[0018] 1. When installing the device, the test bench mounting base is fixed through the lower balance disc, the cross-beam loading fixture is fixed to the bottom surface of the upper balance disc, and the standard force sensor is connected and fixed using the cross-beam loading fixture. The applied force is evenly distributed to the lower balance disc through the cross-beam loading fixture. At the same time, the lower balance disc is further supported and fixed by the gantry base. This solves the problem that most aerospace engine thrust field test devices often have poor structural stability and certain safety hazards, and effectively enhances the overall stability of the test device;

[0019] 2. During the test, fix the loading hydraulic lever to one side of the gantry base, and use the loading hydraulic lever to accurately apply vertical pressure or lateral force, thereby applying corresponding thrust to the cross beam loading tooling, and test the engine thrust through the standard force sensor. When the standard force sensor is overloaded, damaged, or separated, the lower balance disc will be displaced and become one with the upper balance disc. The two are subjected to force together, which can effectively prevent accidents caused by overload, avoid the overall collapse of the device, and ensure the safety of on-site testing. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 Shown is a schematic diagram of the three-dimensional structure of an aerospace engine thrust field test device with a stable structure according to the present invention;

[0021] Figure 2 Shown is a schematic diagram of the cross-sectional three-dimensional structure of a balance assembly of an aerospace engine thrust field test device with a stable structure according to the present invention;

[0022] Figure 3 Shown is a schematic diagram of the three-dimensional structure of a balance assembly of an aerospace engine thrust field test device with a stable structure according to the present invention;

[0023] Figure 4 Shown is a schematic diagram of the three-dimensional structure of a gantry base of an aerospace engine thrust field test device with a stable structure according to the present invention;

[0024] Figure 5 Shown is a schematic diagram of the three-dimensional structure of a test assembly of an aerospace engine thrust field test device with a stable structure according to the present invention;

[0025] Figure 6 Shown is a schematic diagram of the cross-sectional three-dimensional structure of a loading hydraulic lever of an aerospace engine thrust field test device with a stable structure according to the present invention.

[0026] Explanation of reference numerals: 1. test bench mounting base; 2. lower balance disc; 3. upper balance disc; 401. elastic connecting block; 402. T-shaped through hole; 403. threaded hole; 404. limit bolt; 405. fastening nut; 5. cross beam loading fixture; 501. first mounting hole; 502. second mounting hole; 503. first fixing bolt; 6. gantry base; 601. gantry support; 602. first mounting plate; 6 03. Second mounting plate; 604. Third mounting hole; 605. Third fixing bolt; 7. Loading hydraulic lever; 701. Connecting flange; 702. Fourth mounting hole; 703. Fourth fixing bolt; 704. Cylinder protective housing; 705. Cylinder piston; 706. Cylinder oil inlet; 707. Cylinder oil outlet; 8. Standard force sensor; 801. Ball fixing seat; 802. Ball limit seat; 803. Connecting ball. DETAILED DESCRIPTION

[0027] The present invention will be further described below with reference to the accompanying drawings and examples.

[0028] See also Figures 1-6The present invention provides an embodiment: a field test device for aerospace engine thrust with a stable structure, comprising a test bench mounting seat 1, a lower balance disc 2, an upper balance disc 3, a balance assembly, a cross beam loading tool 5, a first mounting assembly, a gantry base 6, a second mounting assembly, a loading hydraulic lever 7, a third mounting assembly, a first test assembly, a standard force sensor 8, and a second test assembly; the bottom surface of the test bench mounting seat 1 is provided with a lower balance disc 2, the test bench mounting seat 1 is provided at a 45° angle to the upper surface of the lower balance disc 2, the lower surface of the lower balance disc 2 is provided with an upper balance disc 3, the lower balance disc 2 and the upper balance disc are in contact with each other. The positions of the disks 3 correspond concentrically, a balance assembly is provided on one side of the upper balance disk 3, a cross beam loading tooling 5 is provided on the bottom surface of the upper balance disk 3, a first mounting assembly is provided on one side of the cross beam loading tooling 5, a gantry base 6 is provided below the cross beam loading tooling 5, a second mounting assembly is provided on one side of the gantry base 6, a loading hydraulic lever 7 is provided on one side of the gantry base 6, a third mounting assembly is provided on the bottom end of the loading hydraulic lever 7, a first test assembly is provided on one side of the loading hydraulic lever 7, a standard force sensor 8 is provided on the other end of the loading hydraulic lever 7, and a second test assembly is provided on one end of the standard force sensor 8.

[0029] See also Figure 2-Figure 4403, a plurality of threaded holes 403 are provided on one side of the upper balance disc 3, and the threaded holes 403 are provided on the other side of the upper balance disc 3. The nut 405 has a gap between it and the T-shaped through hole 402, and the lower balance disc 2 and the upper balance disc 3 are connected and fixed by the elastic connecting block 401, so as to ensure that the relative position of the lower balance disc 2 and the upper balance disc 3 is stable. When the device is working normally, the T-shaped through hole 402 is used to prevent the limit bolt 404 from directly contacting the lower balance disc 2, so that the limit bolt 404 matches the influence of the lateral force. The limit bolt 404 is threadedly connected through the threaded hole 403, so that the limit bolt 404 is threadedly connected to the upper balance disc 3, and the fastening nut 405 is used to prevent the limit bolt 404 from loosening. When the device is overloaded, the lower balance disc 2 falls on the limit bolt 404, so that the lower balance disc 2 and the upper balance disc 3 are integrated. When the standard force sensor 8 is overloaded, the lower balance disc 2 and the upper balance disc 3 are subjected to force together, thereby effectively ensuring the safe conduct of the test operation.

[0030] The second mounting assembly includes a gantry support 601, a first mounting plate 602 and a second mounting plate 603; a gantry support 601 is provided on the upper surface of the gantry base 6, and the gantry support 601 is provided with multiple groups, and the gantry support 601 is provided at the four corners of the gantry base 6, and a first mounting plate 602 is provided at one end of the gantry support 601, and the first mounting plate 602 is provided at one end of the gantry base 6 support, and a second mounting plate 603 is provided on the outer side of the lower balance disc 2, and the second mounting plate 603 is provided with multiple groups, and the first mounting plate 602 and the second mounting plate 603 correspond in position, and the first mounting plate 602 is supported and fixed by the gantry support 601, and the first mounting plate 602 is used to clarify the installation position of the second mounting plate 603, and the second mounting plate 603 is used to clarify the installation position of the second mounting plate The second mounting plate 603 is connected and fixed to the lower balance disc 2; the second mounting assembly also includes a third mounting hole 604 and a third fixing bolt 605; a third mounting hole 604 is opened on one side of the first mounting plate 602, and the third mounting hole 604 is opened in multiple groups. The third mounting hole 604 is opened on one side of the second mounting plate 603, and a third fixing bolt 605 is set on the inner side of the third mounting hole 604. The third fixing bolt 605 and the third mounting hole 604 are threadedly connected to each other, and the installation position of the third fixing bolt 605 is clearly defined through the third mounting hole 604. The third fixing bolt 605 is installed in the third mounting hole 604, thereby connecting and fixing the first mounting plate 602 and the second mounting plate 603, so that the gantry base 6 stably supports and fixes the lower balance disc 2.

[0031] See also Figure 5-Figure 6In this embodiment, the first mounting assembly includes a first mounting hole 501, a second mounting hole 502 and a first fixing bolt 503; a first mounting hole 501 is opened on one side of the cross beam loading fixture 5, and the first mounting hole 501 is opened in multiple groups; a second mounting hole 502 is opened on one side of the cross beam loading fixture 5, and the second mounting hole 502 is opened in multiple groups; the second mounting holes 502 are opened at the four corners of the cross beam loading fixture 5, and the second mounting holes 502 are opened on one side of the upper balance disc 3, and the second mounting holes 502 of the upper balance disc 3 are connected to the cross beam loading fixture 5. The second mounting hole 502 of the beam loading fixture 5 corresponds to the position of the second mounting hole 502. A first fixing bolt 503 is provided on the inner side of the second mounting hole 502. There are multiple groups of first fixing bolts 503. The first fixing bolts 503 are threadedly connected with the second mounting hole 502. The installation position of the test bench mounting seat 1 is clearly defined through the first mounting hole 501 to ensure the stability of the test bench mounting seat 1. The installation position of the first fixing bolt 503 is defined by the second mounting hole 502. The cross beam loading fixture 5 is fixedly connected by the first fixing bolt 503, thereby fixing the cross beam loading fixture 5. The beam loading tooling 5 and the upper balance disc 3; the third mounting assembly includes a connecting flange 701, a fourth mounting hole 702 and a fourth fixing bolt 703; the bottom end of the loading hydraulic lever 7 is provided with a connecting flange 701, the connecting flange 701 is provided on one side of the gantry base 6, and a fourth mounting hole 702 is provided on one side of the connecting flange 701. The fourth mounting hole 702 is provided in multiple groups, and the fourth mounting hole 702 is provided on one side of the gantry base 6. The fourth mounting hole 702 on one side of the gantry base 6 and the fourth mounting hole 702 on the side of the connecting flange 701 are connected to each other. The positions of the mounting holes 702 correspond to each other, and a fourth fixing bolt 703 is provided on the inner side of the fourth mounting hole 702. There are multiple groups of the fourth fixing bolts 703. The fourth fixing bolts 703 are threadedly connected to the fourth mounting holes 702. The position of the loading hydraulic lever 7 is fixed by the connecting flange 701. The fourth mounting hole 702 is used to clarify the installation position of the fourth fixing bolt 703. The fourth fixing bolt 703 is installed in the fourth mounting hole 702, thereby fixing the connecting flange 701 to the gantry base 6, so that the loading hydraulic lever 7 is fixed to the gantry base 6;

[0032] The first test component includes a cylinder protective shell 704, a cylinder piston 705, a cylinder oil inlet 706 and a cylinder oil outlet 707; a cylinder protective shell 704 is provided on the outside of the loading hydraulic lever 7, a cylinder piston 705 is provided on the inside of the loading hydraulic lever 7, a cylinder oil inlet 706 is provided on one side of the loading hydraulic lever 7, and a cylinder oil outlet 707 is provided on one side of the loading hydraulic lever 7. The loading hydraulic lever 7 is protected by the cylinder protective shell 704, and the cylinder piston 705 and the loading hydraulic lever 7 are slidably connected to each other. Oil is injected into the loading hydraulic lever 7 through the cylinder oil inlet 706 and discharged through the cylinder oil outlet 707, so that the cylinder piston 705 moves linearly under the action of the pressure oil, thereby converting hydraulic energy into mechanical energy and performing external work; the second test group The components include a sphere fixing seat 801, a sphere limiting seat 802 and a connecting sphere 803; a sphere fixing seat 801 is provided at one end of the standard force sensor 8, a sphere limiting seat 802 is provided on the bottom surface of the cross beam loading tooling 5, a connecting sphere 803 is provided on one side of the sphere fixing seat 801, the connecting sphere 803 is provided on the inner side of the sphere limiting seat 802, the connecting sphere 803 and the sphere limiting seat 802 are rotatably connected to each other, the position of the connecting sphere 803 is fixed by the sphere fixing seat 801, the connecting sphere 803 is fixed to one end of the standard force sensor 8, the sphere limiting seat 802 is used to rotate and connect the connecting sphere 803, and the connecting sphere 803 is rotated along the sphere limiting seat 802 to eliminate the influence of lateral force introduced by processing and installation during the test.

[0033] Before conducting the test, fix the connecting flange 701 to the bottom surface of the gantry base 6, install the fourth fixing bolts 703 into the fourth mounting holes 702 in sequence, and tighten the gantry base 6 with the fourth fixing bolts 703 to fix the loading hydraulic lever 7 to the gantry base 6. Then, place the upper balance disc 3 on one side of the cross beam loading fixture 5, and then rotate the first fixing bolts 503 into the second mounting holes 502 in sequence. Tighten the upper balance disc 3 with the first fixing bolts 503 to connect and fix the upper balance disc 3 to the cross beam loading fixture 5.

[0034] Subsequently, the limiting bolt 404 is rotated in the threaded hole 403 in sequence, and the fastening nut 405 is rotated in the T-shaped through hole 402 to fix the limiting bolt 404 to the upper balance disc 3. The first mounting plate 602 is supported and fixed by the gantry support 601. The first mounting plate 602 is aligned with the second mounting plate 603. The third fixing bolt 605 is rotated into the third mounting hole 604 in sequence. The first mounting plate 602 is locked and fixed by the third fixing bolt 605, thereby connecting and fixing the gantry support 601 and the lower balance disc 2. The installation position of the test bench mounting base 1 is determined through the first mounting hole 501. The test bench mounting base 1 is installed on one side of the lower balance disc 2, and the test bench mounting base 1 is fixed to the device at a 45° angle.

[0035] During the test operation, the hydraulic oil is injected into the loading hydraulic lever 7 through the oil cylinder inlet 706, and the loading hydraulic lever 7 is wrapped and protected by the oil cylinder protective shell 704, so that the hydraulic oil is discharged from the oil cylinder outlet 707, thereby driving the oil cylinder piston 705 to perform linear motion under the action of the pressure oil, thereby using the loading hydraulic lever 7 to apply thrust to the standard force sensor 8, and using the cross beam loading fixture 5 to evenly apply the thrust to the lower balance disc 2, and the real-time thrust data is monitored by the standard force sensor 8, so that the elastic connecting block 401 produces a small range of deformation, and according to the influence of the lateral force, the connecting ball 803 on the ball fixing seat 801 rotates along the ball limit seat 802;

[0036] When the test is overloaded, the standard force sensor 8 is overloaded, damaged or separated. Since there is a certain gap in the limit bolt 404 in the T-shaped through hole 402, when the upper balance disc 3 is overloaded, the upper balance disc 3 and the lower balance disc 2 are displaced upward to a certain extent, causing the elastic connecting block 401 to produce a certain deformation, and the lower balance disc 2 falls on the fastening nut 405, so that the lower balance disc 2 and the upper balance disc 3 are integrated through the limit bolt 404, so that the lower balance disc 2 and the upper balance disc 3 are subjected to force together, avoiding the overall collapse of the device and ensuring the overall stability of the device.

[0037] Through the above steps, the test bench mounting seat 1 is installed and fixed by setting the lower balance disc 2, the lower balance disc 2 and the upper balance disc 3 are connected and fixed by the balance component, the cross beam loading fixture 5 is installed and fixed by the first installation component, the cross beam loading fixture 5 is fixed to the bottom surface of the upper balance disc 3, the standard force sensor 8 is connected and fixed by the cross beam loading fixture 5, and the applied force value is evenly loaded to the lower balance disc 2 by the cross beam loading fixture 5, so that the thrust received by the lower balance disc 2 is uniform, ensuring that the test results of the device are accurate, the gantry base 6 is fixedly connected by the second installation component, and the lower balance disc 2 is further supported and fixed by the gantry base 6, the loading hydraulic lever 7 is fixed by the third installation component, and the loading hydraulic lever 7 is fixed to the gantry. On one side of the gantry base 6, the loading hydraulic lever 7 is controlled by the first test component to apply pressure, and the loading hydraulic lever 7 is used to accurately apply vertical pressure or lateral force to the standard force sensor 8, thereby simulating the thrust of the engine, and the engine thrust is tested by the standard force sensor 8, wherein the standard force sensor 8 has a range of 1MN and an accuracy level of 0.03. The standard force sensor 8 is connected and fixed to the cross-beam loading fixture 5 through the second test component. When the standard force sensor 8 is overloaded, damaged or separated, the lower balance disc 2 and the upper balance disc 3 are integrated to prevent accidents, thereby enhancing the overall stability of the test device, preventing the overall collapse of the device when an accident occurs, and ensuring the safety of on-site use.

[0038] The embodiments of the present invention are described in detail above with reference to the accompanying drawings. However, the present invention is not limited to the above embodiments. Various changes can be made within the scope of knowledge of those skilled in the art without departing from the spirit of the present invention.

Claims

1. A space engine thrust field test device with a stable structure, comprising a test bench mounting seat (1), characterized in that: The test bench also includes a lower balance disc (2), an upper balance disc (3), a balance assembly, a cross beam loading tool (5), a first mounting assembly, a gantry base (6), a second mounting assembly, a loading hydraulic lever (7), a third mounting assembly, a first test assembly, a standard force sensor (8) and a second test assembly; the bottom surface of the test bench mounting seat (1) is provided with a lower balance disc (2), the test bench mounting seat (1) is provided at a 45° angle on the upper surface of the lower balance disc (2), the lower portion of the lower balance disc (2) is provided with an upper balance disc (3), the lower portion of the lower balance disc (2) is concentrically corresponding to the upper portion of the upper balance disc (3), and one side of the upper balance disc (3) is provided with a lower balance disc (2). A balance assembly is provided, a cross beam loading tool (5) is provided on the bottom surface of the upper balance disc (3), a first mounting assembly is provided on one side of the cross beam loading tool (5), a gantry base (6) is provided below the cross beam loading tool (5), a second mounting assembly is provided on one side of the gantry base (6), a loading hydraulic lever (7) is provided on one side of the gantry base (6), a third mounting assembly is provided at the bottom end of the loading hydraulic lever (7), a first test assembly is provided on one side of the loading hydraulic lever (7), a standard force sensor (8) is provided at the other end of the loading hydraulic lever (7), and a second test assembly is provided at one end of the standard force sensor (8).

2. The aerospace engine thrust field test device with a stable structure according to claim 1, characterized in that: The balance assembly comprises an elastic connection block (401), a T-shaped through hole (402) and a threaded hole (403); an elastic connection block (401) is provided on one side of the lower balance disc (2), and the elastic connection block (401) is provided in multiple groups. The elastic connection block (401) is provided between the lower balance disc (2) and the upper balance disc (3); the other side of the elastic connection block (401) is fixedly connected to the upper balance disc (3); a T-shaped through hole (402) is provided on one side of the lower balance disc (2), and the T-shaped through hole (402) is provided in multiple groups; a threaded hole (403) is provided on one side of the upper balance disc (3), and the threaded hole (403) is provided in multiple groups. The positions of the threaded holes (403) and the T-shaped through holes (402) correspond to each other.

3. The aerospace engine thrust field test device with a stable structure according to claim 2, characterized in that: The balance assembly further comprises a limiting bolt (404) and a fastening nut (405); a limiting bolt (404) is provided on the inner side of the T-shaped through hole (402), one end of the limiting bolt (404) is threadedly connected to the threaded hole (403), and a fastening nut (405) is provided on the other end of the limiting bolt (404), wherein a gap is left between the fastening nut (405) and the T-shaped through hole (402).

4. The aerospace engine thrust field test device with a stable structure according to claim 2, characterized in that: The first mounting assembly includes a first mounting hole (501) and a second mounting hole (502); a first mounting hole (501) is provided on one side of the cross beam loading tool (5), and the first mounting hole (501) is provided in multiple groups; a second mounting hole (502) is provided on one side of the cross beam loading tool (5), and the second mounting hole (502) is provided in multiple groups; the second mounting holes (502) are provided at four corners of the cross beam loading tool (5); the second mounting holes (502) are provided on one side of the upper balance disc (3); and the second mounting holes (502) of the upper balance disc (3) correspond in position to the second mounting holes (502) of the cross beam loading tool (5).

5. The aerospace engine thrust field test device with a stable structure according to claim 4, characterized in that: The first mounting assembly further includes a first fixing bolt (503); a first fixing bolt (503) is provided on the inner side of the second mounting hole (502); a plurality of first fixing bolts (503) are provided, and the first fixing bolts (503) and the second mounting hole (502) are threadedly connected to each other.

6. The aerospace engine thrust field test device with a stable structure according to claim 4, characterized in that: The second mounting assembly comprises a gantry support (601), a first mounting plate (602) and a second mounting plate (603); the gantry support (601) is provided on the upper surface of the gantry base (6), the gantry support (601) is provided in multiple groups, the gantry support (601) is provided at the four corners of the gantry base (6), one end of the gantry support (601) is provided with a first mounting plate (602), the first mounting plate (602) is provided at one end of the gantry base (6) support, the second mounting plate (603) is provided on the outer side of the lower balance disc (2), the second mounting plate (603) is provided in multiple groups, and the first mounting plate (602) and the second mounting plate (603) are positioned correspondingly.

7. The aerospace engine thrust field test device with a stable structure according to claim 6, characterized in that: The second mounting assembly further includes a third mounting hole (604) and a third fixing bolt (605); a third mounting hole (604) is provided on one side of the first mounting plate (602), and a plurality of third mounting holes (604) are provided. The third mounting holes (604) are provided on one side of the second mounting plate (603), and a third fixing bolt (605) is provided on the inner side of the third mounting hole (604). The third fixing bolt (605) and the third mounting hole (604) are threadedly connected to each other.

8. The aerospace engine thrust field test device with a stable structure according to claim 6, characterized in that: The third mounting assembly includes a connecting flange (701), a fourth mounting hole (702) and a fourth fixing bolt (703); a connecting flange (701) is provided at the bottom end of the loading hydraulic lever (7), the connecting flange (701) is provided on one side of the gantry base (6), a fourth mounting hole (702) is provided on one side of the connecting flange (701), a plurality of fourth mounting holes (702) are provided, the fourth mounting holes (702) are provided on one side of the gantry base (6), the fourth mounting holes (702) on one side of the gantry base (6) correspond to the fourth mounting holes (702) on one side of the connecting flange (701), a fourth fixing bolt (703) is provided on the inner side of the fourth mounting hole (702), a plurality of fourth fixing bolts (703) are provided, and the fourth fixing bolt (703) and the fourth mounting hole (702) are threadedly connected to each other.

9. The aerospace engine thrust field test device with a stable structure according to claim 8, characterized in that: The first test assembly includes a cylinder protective housing (704), a cylinder piston (705), a cylinder oil inlet (706) and a cylinder oil outlet (707); the outer side of the loading hydraulic lever (7) is provided with a cylinder protective housing (704), the inner side of the loading hydraulic lever (7) is provided with a cylinder piston (705), the cylinder piston (705) and the loading hydraulic lever (7) are slidably connected to each other, a cylinder oil inlet (706) is provided on one side of the loading hydraulic lever (7), and a cylinder oil outlet (707) is provided on one side of the loading hydraulic lever (7).

10. The aerospace engine thrust field test device with a stable structure according to claim 8, characterized in that: The second test assembly includes a sphere fixing seat (801), a sphere limiting seat (802) and a connecting sphere (803); one end of the standard force sensor (8) is provided with the sphere fixing seat (801), the bottom surface of the cross beam loading fixture (5) is provided with the sphere limiting seat (802), one side of the sphere fixing seat (801) is provided with a connecting sphere (803), the connecting sphere (803) is provided on the inner side of the sphere limiting seat (802), and the connecting sphere (803) and the sphere limiting seat (802) are rotatably connected to each other.

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