Airspace engine thrust field test device with stable structure

Abstract

The invention relates to the technical field of airspace engine thrust testing, in particular to an airspace engine thrust field testing device with a stable structure, which comprises a test bed mounting seat, a lower balance disc, an upper balance disc, a balance assembly, a cross beam loading tool, a mounting assembly, a portal frame base, a loading hydraulic lever and a standard force transducer, a lower balance disc is arranged on the bottom surface of the test bed mounting seat, an upper balance disc is arranged below the lower balance disc, a balance assembly is arranged on one side of the upper balance disc, a cross beam loading tool is arranged on the bottom surface of the upper balance disc, a portal frame base is arranged below the cross beam loading tool, and a loading hydraulic lever is arranged on one side of the portal frame base; a standard force transducer is arranged at the other end of the loading hydraulic lever; through a secondary protection mode, the overall stability of the field test device is enhanced, overall collapse of the device when an accident occurs is effectively prevented, and the safety of field use is guaranteed, so that the thrust of the airspace engine is more accurately measured.

Description

Technical Field

[0001] The 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 in different working states (such as startup, acceleration, stable operation, shutdown, etc.) to provide accurate data basis for the rocket's orbit calculation, fuel consumption estimation, etc. According to the on-site test requirements, it is necessary to build a on-site test device, and the on-site loading range is 70% of the full range, which is 70t.

[0003] Most of the current installation structures of aerospace engine thrust field test devices are relatively simple, and the measuring balances are mostly fixed directly to the devices, 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, which affects 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 overall collapse and damage of the device, posing certain safety hazards and affecting the safety and stability of on-site test operations.

[0006] The technical scheme of the present invention is: a space engine thrust field test device 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 tooling, 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 an angle of 45° on 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 to each other. The positions are concentrically corresponding, a balance assembly is arranged on one side of the upper balance disc, a cross beam loading tooling is arranged on the bottom surface of the upper balance disc, a first installation assembly is arranged on one side of the cross beam loading tooling, a gantry base is arranged below the cross beam loading tooling, a second installation assembly is arranged on one side of the gantry base, a loading hydraulic lever is arranged on one side of the gantry base, a third installation assembly is arranged on the bottom end of the loading hydraulic lever, a first test assembly is arranged on one side of the loading hydraulic lever, a standard force sensor is arranged on the other end of the loading hydraulic lever, and a second test assembly is arranged 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 the cross-beam loading fixture, and the applied force value is evenly loaded and 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 result of the device is accurate, a second mounting assembly is used to fix the gantry base, the lower balance disc is further supported and fixed by the gantry base, a loading hydraulic lever position is fixed by a third mounting assembly, 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, wherein the standard force sensor has a range of 1MN and an accuracy level of 0.03. The standard force sensor and the cross-beam loading fixture are connected and fixed through the second test component. When the standard force sensor is overloaded, damaged or separated, the lower balance disc and the upper balance disc 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, 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, and the positions of the threaded holes correspond to those 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 the other end of the limiting bolt is arranged with a fastening nut, wherein a gap is left between the fastening nut and the T-shaped through hole.

[0010] Preferably, the first mounting component 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, and 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 arranged on the inner side of the second mounting hole, a plurality of first fixing bolts are arranged, 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 arranged on the upper surface of the gantry base, and the gantry support is arranged in multiple groups, and the gantry support is arranged at the four corners of the gantry base, and a first mounting plate is arranged at one end of the gantry support, and the first mounting plate is arranged at one end of the gantry base support, and a second mounting plate is arranged on the outer side of the lower balance disc, and the second mounting plate is arranged in multiple groups, and the positions of the first mounting plate and the second mounting plate correspond.

[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 arranged 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 and the fourth mounting hole are threadedly connected to each other.

[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 arranged on the outer side of the loading hydraulic lever, a cylinder piston is arranged on the inner side of the loading hydraulic lever, the cylinder piston and the loading hydraulic lever are slidingly connected to each other, a cylinder oil inlet is opened on one side of the loading hydraulic lever, and a cylinder oil outlet is opened on one side of the loading hydraulic lever.

[0016] Preferably, the second test assembly includes a sphere fixing seat, a sphere limiting seat and a connecting sphere; a sphere fixing seat is provided at one end of the standard force sensor, a sphere limiting seat is provided on 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 limiting seat, and the connecting sphere and the sphere limiting seat are rotatably connected to each other.

[0017] Beneficial effects of the present invention: 1. When installing the device, the test bench mounting seat 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 by the cross beam loading fixture. The force value is evenly loaded 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 to solve the problem that the structural stability of most aerospace engine thrust field test devices is often poor and there are certain safety hazards, which effectively enhances the overall stability of the test device; 2. During the test, fix the loading hydraulic lever to one side of the gantry base, use the loading hydraulic lever to accurately apply vertical pressure or lateral force, so as to apply 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 integrated with the upper balance disc. The two are subjected to force together, which can effectively prevent accidents during overload and avoid the overall collapse of the device, thus ensuring the safety of on-site testing. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 What is shown is a three-dimensional schematic diagram of a field test device for thrust of an aerospace engine with a stable structure according to the present invention; Figure 2What is shown is a cross-sectional three-dimensional structural schematic diagram of a balance assembly of an aerospace engine thrust field test device with a stable structure of the present invention; Figure 3 Shown is a schematic diagram of the three-dimensional structure of a balance assembly of a space engine thrust field test device with a stable structure according to the present invention; 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; 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; Figure 6 What is shown is a schematic diagram of the three-dimensional structure of the cross-section of a loading hydraulic lever of an aerospace engine thrust field test device with a stable structure according to the present invention. Description of reference numerals: 1. test bench mounting seat; 2. lower balance disc; 3. upper balance disc; 401. elastic connection 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; 603. second mounting hole; 604. first fixing bolt; 605. first mounting plate; 606. first mounting plate; 607. first mounting plate; 608. first mounting plate; 609. first mounting plate; 610. first mounting plate; 611. first mounting plate; 612. first mounting plate; 613. first mounting plate; 614. first mounting hole; 615. first mounting hole 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

[0019] The present invention will be further described below in conjunction with the accompanying drawings and embodiments.

[0020] See also Figure 1-Figure 6The present invention provides an embodiment: a field test device for thrust of an aerospace engine 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 an angle of 45° on the upper surface of the lower balance disc 2, an upper balance disc 3 is provided below the lower balance disc 2, and the lower balance disc 2 and the upper balance disc 3 are in contact with each other. The positions of the disks 3 correspond concentrically, a balance assembly is arranged on one side of the upper balance disk 3, a cross beam loading fixture 5 is arranged on the bottom surface of the upper balance disk 3, a first mounting assembly is arranged on one side of the cross beam loading fixture 5, a gantry base 6 is arranged below the cross beam loading fixture 5, a second mounting assembly is arranged on one side of the gantry base 6, a loading hydraulic lever 7 is arranged on one side of the gantry base 6, a third mounting assembly is arranged on the bottom end of the loading hydraulic lever 7, a first test assembly is arranged on one side of the loading hydraulic lever 7, a standard force sensor 8 is arranged on the other end of the loading hydraulic lever 7, and a second test assembly is arranged on one end of the standard force sensor 8.

[0021] See also Figure 2-Figure 4In the present embodiment, the balance assembly includes an elastic connecting block 401, a T-shaped through hole 402, a threaded hole 403, a limiting bolt 404 and a fastening nut 405; an elastic connecting block 401 is provided on one side of the lower balance disc 2, and the elastic connecting block 401 is provided with multiple groups. The elastic connecting block 401 is arranged between the lower balance disc 2 and the upper balance disc 3, and the other side of the elastic connecting block 401 is fixedly connected with 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 with multiple groups. A threaded hole 403 is provided on one side of the upper balance disc 3, and the threaded hole 403 is provided with multiple groups. The threaded hole 403 corresponds to the position of the T-shaped through hole 402. 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 the other end of the limiting bolt 404 is provided with a fastening nut The female 405 has a gap between the fastening nut 405 and the T-shaped through hole 402. The lower balance disc 2 and the upper balance disc 3 are connected and fixed by the elastic connecting block 401 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 with the upper balance disc 3. 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 safety of the test operation. 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 arranged 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 arranged 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 are in corresponding positions, 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 603. The second mounting plate 603 is connected to fix 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 arranged on the inner side of the third mounting hole 604. The third fixing bolt 605 is threadedly connected with the third mounting hole 604. The installation position of the third fixing bolt 605 is clearly defined through the third mounting hole 604, and 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.

[0022] 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, and 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 and the cross The second mounting hole 502 of the cross beam loading tool 5 corresponds to the position of the second mounting hole 502. A first fixing bolt 503 is arranged inside the second mounting hole 502. The first fixing bolt 503 is arranged in multiple groups. The first fixing bolt 503 and the second mounting hole 502 are threadedly connected to each other. The installation position of the test bench mounting seat 1 is clarified through the first mounting hole 501 to ensure the stability of the position of the test bench mounting seat 1. The installation position of the first fixing bolt 503 is clarified by the second mounting hole 502. The cross beam loading tool 5 is fixedly connected by the first fixing bolt 503, thereby fixing the cross beam loading tool 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 arranged on one side of the gantry base 6, and a fourth mounting hole 702 is opened on one side of the connecting flange 701. The fourth mounting hole 702 is opened in multiple groups, and the fourth mounting hole 702 is opened 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 one side of the connecting flange 701 are connected to the fourth mounting hole 703 on the other side of the connecting flange 701. The fourth mounting hole 702 corresponds to the position of the fourth mounting hole 702, and a fourth fixing bolt 703 is arranged on the inner side of the fourth mounting hole 702. The fourth fixing bolt 703 is provided with multiple groups. The fourth fixing bolt 703 and the fourth mounting hole 702 are threadedly connected to each other, and 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, and the fourth fixing bolt 703 is installed in the fourth mounting hole 702, so that the connecting flange 701 is fixed to the gantry base 6, so that the loading hydraulic lever 7 is fixedly connected to the gantry base 6; 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 outer side of the loading hydraulic lever 7, a cylinder piston 705 is provided on the inner side 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, the cylinder piston 705 and the loading hydraulic lever 7 are slidably connected to each other, the oil is injected into the loading hydraulic lever 7 by the cylinder oil inlet 706, and the oil is 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 ball fixing seat 801, a ball limiting seat 802 and a connecting ball 803; a ball fixing seat 801 is provided at one end of the standard force sensor 8, a ball limiting seat 802 is provided on the bottom surface of the cross beam loading tooling 5, a connecting ball 803 is provided on one side of the ball fixing seat 801, the connecting ball 803 is provided on the inner side of the ball limiting seat 802, the connecting ball 803 and the ball limiting seat 802 are rotatably connected to each other, the position of the connecting ball 803 is fixed by the ball fixing seat 801, the connecting ball 803 is fixed to one end of the standard force sensor 8, the connecting ball 803 is rotatably connected by the ball limiting seat 802, and the connecting ball 803 is rotated along the ball limiting seat 802 to eliminate the influence of lateral force introduced by processing and installation during the test.

[0023] Before the test operation, the connecting flange 701 is fixed to the bottom surface of the gantry base 6, and the fourth fixing bolts 703 are installed into the fourth mounting holes 702 in sequence, and the gantry base 6 is locked and fixed by the fourth fixing bolts 703, so that the loading hydraulic lever 7 is fixed to the gantry base 6, and then the upper balance disc 3 is placed on one side of the cross beam loading fixture 5, and then the first fixing bolts 503 are rotated into the second mounting holes 502 in sequence, and the upper balance disc 3 is locked and fixed by the first fixing bolts 503, so as to connect and fix the upper balance disc 3 and the cross beam loading fixture 5; Subsequently, the limiting bolt 404 is rotated in the threaded hole 403 in turn, and the fastening nut 405 is rotated in the T-shaped through hole 402, so as to fix the limiting bolt 404 to the upper balance disc 3, and the first mounting plate 602 is supported and fixed by the gantry support 601, and the first mounting plate 602 is aligned with the second mounting plate 603, and the third fixing bolt 605 is rotated into the third mounting hole 604 in turn, and the first mounting plate 602 is locked and fixed by the third fixing bolt 605, so as to connect and fix the gantry support 601 and the lower balance disc 2, and the installation position of the test bench mounting seat 1 is clarified through the first mounting hole 501, and the test bench mounting seat 1 is installed on one side of the lower balance disc 2, so that the test bench mounting seat 1 is fixed to the device at a 45° angle; When performing 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, so that the loading hydraulic lever 7 is used to apply thrust to the standard force sensor 8, and the cross beam loading fixture 5 is used 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 connection block 401 produces a small range of deformation, and the connection ball 803 on the ball fixing seat 801 is rotated along the ball limit seat 802 according to the influence of the lateral force; When the test is overloaded, the standard force sensor 8 is overloaded, damaged or separated. Since there is a certain gap in the T-shaped through hole 402 of the limit bolt 404, 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.

[0024] 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 tool 5 is installed and fixed by the first installation component, the cross beam loading tool 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 tool 5, and the applied force value is evenly loaded and distributed to the lower balance disc 2 by the cross beam loading tool 5, so that the thrust of the lower balance disc 2 is uniform, ensuring the accuracy of the device test result, 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, and the loading hydraulic lever 7 is fixed by the third installation component. The loading hydraulic lever 7 is fixed to the gantry base 6. 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.

[0025] The embodiments of the present invention are described in detail above with reference to the accompanying drawings, but the present invention is not limited to the above embodiments, and various changes can be made within the knowledge scope of those skilled in the art without departing from the spirit of the present invention.

Claims

1. An aerospace engine thrust field test device with a stable structure, comprising a test bench mounting seat (1), characterized in that: The test bench also comprises 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 lower balance disc (2) is arranged on the bottom surface of the test bench mounting seat (1); the test bench mounting seat (1) is arranged at an angle of 45° on the upper surface of the lower balance disc (2); an upper balance disc (3) is arranged below the lower balance disc (2); the positions of the lower balance disc (2) and the upper balance disc (3) are concentrically corresponding; one side of the upper balance disc (3) A balance assembly is provided, a cross-beam loading fixture (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 fixture (5), a gantry base (6) is provided below the cross-beam loading fixture (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 testing 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 testing 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 arranged on one side of the lower balance disc (2), and a plurality of elastic connection blocks (401) are arranged; the elastic connection block (401) is arranged 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 opened on one side of the lower balance disc (2), and a plurality of T-shaped through holes (402) are opened; a threaded hole (403) is opened on one side of the upper balance disc (3), and a plurality of threaded holes (403) are opened; and the positions of the threaded holes (403) and the T-shaped through holes (402) correspond.

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 arranged 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 the other end of the limiting bolt (404) is arranged with a fastening nut (405), 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 comprises 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 tooling (5), and the first mounting hole (501) is provided in a plurality of groups; a second mounting hole (502) is provided on one side of the cross beam loading tooling (5), and the second mounting hole (502) is provided in a plurality of groups; the second mounting holes (502) are provided at four corners of the cross beam loading tooling (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 tooling (5).

5. The aerospace engine thrust field test device with a stable structure according to claim 4, characterized in that: The first mounting assembly also includes a first fixing bolt (503); the first fixing bolt (503) is arranged inside the second mounting hole (502); a plurality of first fixing bolts (503) are arranged; 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 arranged on the upper surface of the gantry base (6), the gantry support (601) is arranged in multiple groups, the gantry support (601) is arranged at the four corners of the gantry base (6), one end of the gantry support (601) is arranged with a first mounting plate (602), the first mounting plate (602) is arranged at one end of the support of the gantry base (6), the second mounting plate (603) is arranged on the outer side of the lower balance disc (2), the second mounting plate (603) is arranged in multiple groups, and the first mounting plate (602) and the second mounting plate (603) are arranged in corresponding positions.

7. The aerospace engine thrust field test device with a stable structure according to claim 6, characterized in that: The second mounting assembly further comprises 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); 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); a third fixing bolt (605) is provided on the inner side of the third mounting hole (604); and 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 comprises 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 in position 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 comprises a cylinder protective housing (704), a cylinder piston (705), a cylinder oil inlet (706) and a cylinder oil outlet (707); the cylinder protective housing (704) is arranged on the outer side of the loading hydraulic lever (7), the cylinder piston (705) is arranged on the inner side of the loading hydraulic lever (7), the cylinder piston (705) and the loading hydraulic lever (7) are slidably connected to each other, the cylinder oil inlet (706) is opened on one side of the loading hydraulic lever (7), and the cylinder oil outlet (707) is opened 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 comprises a spherical fixing seat (801), a spherical limiting seat (802) and a connecting sphere (803); the spherical fixing seat (801) is arranged at one end of the standard force sensor (8), the spherical limiting seat (802) is arranged at the bottom surface of the cross beam loading fixture (5), a connecting sphere (803) is arranged at one side of the spherical fixing seat (801), the connecting sphere (803) is arranged on the inner side of the spherical limiting seat (802), and the connecting sphere (803) and the spherical limiting seat (802) are rotatably connected to each other.

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