A field testing device for measuring the thrust of aerospace engines

Abstract

This invention relates to the field of aerospace engine thrust measurement technology, and more particularly to a field testing device for aerospace engine thrust measurement. The technical solution is as follows: A field testing device for aerospace engine thrust measurement includes an engine mounting platform, a loading gantry, a protective pad, a mounting base, hydraulic jacks, hydraulic cylinders, a manual loading pump, a fixing bracket, oil pipes, a force measuring component, and a clamping component. A shock-absorbing component is installed on the bottom surface of the engine mounting platform, and a cooling component is installed inside the shock-absorbing component. Compared to traditional field testing devices for aerospace engine thrust measurement, which generally use a single loading method and may not effectively eliminate the influence of lateral forces or evenly distribute the loading force during loading, this field testing device for aerospace engine thrust measurement uses three sets of gantry loading devices, evenly arranged in a circle, to sequentially load the thrust balance, effectively improving the accuracy and reliability of the test.

Description

Technical Field

[0001] This invention relates to the field of aerospace engine thrust measurement technology, and in particular to a field testing device for measuring aerospace engine thrust. Background Technology

[0002] Thrust measurement devices are indispensable equipment in the development and testing of aerospace engines. They can simulate the engine's working environment on the ground and verify and evaluate the engine's performance, function, strength, reliability, and other aspects by accurately measuring the thrust generated by the engine and its related parameters.

[0003] Existing field testing equipment for measuring the thrust of aerospace engines generally adopts a single loading method. During the loading process, it may not be able to effectively eliminate the influence of lateral forces and cannot distribute the loading force evenly. At the same time, it does not consider the safety of the thrust measuring balance under abnormal conditions when measuring engine thrust, which may easily lead to deviations in the results.

[0004] To address the safety concerns of existing field testing devices for aerospace engine thrust measurement under abnormal conditions, which can easily lead to deviations in results, this new field testing device for aerospace engine thrust measurement employs three sets of gantry loading devices, evenly arranged in a circle, to sequentially load the thrust balance. This effectively improves the accuracy and reliability of the test. The ball-head fixture design ensures accurate transmission of the loading force, reducing test errors. Furthermore, limiting bolts are installed between the upper and lower plates of the thrust measuring balance, connected to the upper plate via threads and fitted with anti-loosening nuts. These bolts are connected to the lower plate via a T-shaped structure with a gap, ensuring that the force on the balance is not affected under normal conditions, but preventing damage to the balance under abnormal conditions and ensuring test safety. Summary of the Invention

[0005] To overcome the limitations of existing field testing devices for measuring aerospace engine thrust, which generally employ a single loading method, the influence of lateral forces may not be effectively eliminated during loading, and the loading force may not be evenly distributed. Furthermore, the safety of the thrust measuring balance under abnormal conditions during engine thrust measurement is not considered, which may easily lead to deviations in the results.

[0006] The technical solution of this invention is as follows: a field testing device for measuring the thrust of an aerospace engine, comprising an engine mounting platform, a shock-absorbing assembly, a cooling assembly, a fixing assembly, a loading gantry, a protective pad, a mounting base, a hydraulic jack, a hydraulic cylinder, a manual loading pump, a fixing bracket, oil pipes, a force measuring assembly, and a clamping assembly. The bottom surface of the engine mounting platform is provided with a shock-absorbing assembly, and the interior of the shock-absorbing assembly is provided with a cooling assembly. The surface of the engine mounting platform is provided with a fixing assembly, and both sides of the fixing assembly are provided with fixing brackets. Multiple sets of fixing brackets are provided, and the surface of the fixing brackets... The system is equipped with a loading gantry, of which there are three sets. The top surface of the loading gantry is covered with a protective pad with multiple anti-slip textures. The bottom surface of the loading gantry is equipped with a mounting base, and a hydraulic jack is mounted on the bottom surface of the mounting base. A hydraulic cylinder is mounted on one side of the mounting base and on the other side of the hydraulic jack. An oil pipe is mounted on the bottom surface of the hydraulic cylinder, and the hydraulic cylinder is connected to the hydraulic jack via the oil pipe. A manual loading pump is mounted on one side of the loading gantry, and a force measuring component is mounted on the bottom surface of the hydraulic jack. A clamping component is mounted on the surface of the engine mounting platform.

[0007] Preferably, the vibration generated during the thrust test of the aerospace engine is partially mitigated by a vibration damping component, and the high temperature generated during the thrust test is cooled by a cooling component, which effectively controls and manages the temperature, ensuring the normal operation of the test equipment and the accuracy of the test results. The loading gantry is fixedly installed by a fixing component and a fixing bracket. The loading gantry is supported by high-strength materials and has a robust structure, used to evenly distribute the loading force. Protective pads protect the surface of the loading gantry. Hydraulic jacks are installed using mounting bases, and the hydraulic jacks simulate… The thrust generated by the aerospace thrust engine during operation ensures that the thrust is evenly applied to the force measuring component. The thrust is then transmitted to the hydraulic jack through the piston movement of the hydraulic cylinder for thrust output. The hydraulic oil is ensured to flow smoothly between the hydraulic cylinder and the hydraulic jack through the oil pipe, thereby realizing the transmission of thrust. The hydraulic cylinder or hydraulic jack generates the required thrust by controlling the hydraulic pump through manual loading. The manual loading pump can convert mechanical energy into hydraulic energy through manual operation, and draw in or discharge hydraulic oil. The pressure simulated by the hydraulic jack is detected by the force measuring component, and the other required equipment is clamped by the clamping component.

[0008] Preferably, the shock absorption assembly includes a mounting cavity, a support base, a damping telescopic rod, a pressure-reducing spring, and a stop plate. The engine mounting frame has a mounting cavity inside, a support base is provided on the bottom surface of the engine mounting frame, a damping telescopic rod is provided on the surface of the support base, multiple sets of damping telescopic rods are provided, a pressure-reducing spring is provided on the outer side of the damping telescopic rod, and a stop plate is provided at the top of the damping telescopic rod.

[0009] Preferably, the cooling assembly includes a cooler, a coolant collection tank, a fixed base, and cooling nozzles. The cooler is installed on the top surface of the support base. The cooler is equipped with a cooling circulation system that circulates the coolant to the parts that need to be cooled. The coolant is composed of a highly conductive cooling medium. The surface of the cooler has a coolant collection tank. The fixed base is installed inside the coolant collection tank. Multiple sets of fixed bases are provided. The cooling nozzles are installed inside the fixed bases.

[0010] Preferably, the fixing components include a fixing base plate, limit bolts, T-slots, anti-loosening bolts, and a triaxial force measuring balance. The surface of the engine mounting frame is provided with a fixing base plate, the surface of the fixing base plate is provided with multiple sets of limit bolts, the surface of the fixing base plate is provided with a T-slot, the inside of the T-slot is provided with an anti-loosening bolt, and the top surface of the limit bolts is provided with a triaxial force measuring balance.

[0011] Preferably, the force measuring component includes a standard force sensor, a ball-head loading fixture, a mounting frame, and a force measuring indicator light. The standard force sensor is installed at the bottom of the hydraulic jack, and the ball-head loading fixture is installed at the bottom of the standard force sensor. The mounting frame is installed on one side of the loading gantry, and the force measuring indicator light is installed inside the mounting frame. There are multiple sets of force measuring indicator lights, and the force measuring indicator lights are electrically connected to the standard force sensor.

[0012] Preferably, the clamping assembly includes a mounting block, a support bracket, a hydraulic telescopic rod, a clamping fixture, and a rotating motor. The surface of the engine mounting frame is provided with mounting blocks, and multiple sets of mounting blocks are provided. The mounting blocks are arranged in pairs, with a support bracket provided on one side of the mounting block and a rotating motor provided on the other side of the mounting block.

[0013] Preferably, a hydraulic telescopic rod is provided on one side of the support bracket, and a clamping fixture is provided at one end of the hydraulic telescopic rod. The clamping fixture is made of non-slip material.

[0014] Preferably, a field testing device for measuring the thrust of an aerospace engine includes the following steps when conducting thrust testing:

[0015] S101: First, thrust loading and simulation are performed on the field testing device to ensure that all components operate normally;

[0016] S102: Perform thrust measurement and feedback, collect and record thrust simulation data in real time, and provide feedback.

[0017] As a preferred embodiment, a field testing device for measuring the thrust of an aerospace engine includes the following steps when performing thrust loading and simulation:

[0018] S201: Inspect each and every component of the engine mounting platform, shock absorber assembly, cooling assembly, mounting assembly, loading gantry, hydraulic jacks, hydraulic cylinders, manual loading pump, etc., to ensure that they are installed correctly and in good working order;

[0019] S202: Check whether the connections between the hydraulic cylinder, oil pipes and hydraulic jack are tight and whether there are any leaks, to ensure the integrity and stability of the hydraulic system;

[0020] S203: Activate the cooler in the cooling assembly to ensure the coolant can circulate and provide effective temperature control for subsequent thrust testing;

[0021] S204: Verify that all safety structures are in place to ensure safety during testing;

[0022] S205: Mechanical energy is converted into hydraulic energy by manually loading the pump at appropriate force and frequency;

[0023] S206: Under the action of the manual loading pump, hydraulic oil flows into the hydraulic cylinder through the oil pipe, pushing the piston forward;

[0024] S207: The piston movement of the hydraulic cylinder is converted into a vertically downward thrust through a hydraulic jack, simulating the thrust of a space engine during operation;

[0025] S208: The thrust generated by the hydraulic jack is evenly distributed onto the force-bearing surface of the three-dimensional force balance through the ball-head loading fixture, ensuring the accuracy and stability of the thrust measurement;

[0026] S209: During the thrust simulation, closely observe the stability of components such as the loading gantry and protective pads to ensure that they do not shake or shift.

[0027] Preferably, a field test device for measuring the thrust of an aerospace engine includes the following steps when performing thrust measurement and feedback:

[0028] S301: When thrust is applied to the triaxial force balance, its built-in high-precision thrust detection sensor starts working, converting mechanical force into an electrical signal;

[0029] S302: Electrical signals are transmitted to the data processing system via data cable or wireless transmission for real-time acquisition and recording;

[0030] S303: The data processing system performs preliminary processing on the acquired raw data, such as filtering and noise reduction, to improve measurement accuracy;

[0031] S304: The force indicator light illuminates the corresponding indicator light according to the electrical signal transmitted by the standard force sensor, intuitively displaying the current range of thrust.

[0032] S305: The data processing system can also display real-time thrust data on the screen in digital or graphical form for testing personnel to monitor at any time;

[0033] S306: After the test, the data processing system generates a detailed test report based on the collected data, including key indicators such as average thrust, peak thrust, and fluctuation range;

[0034] S307: Compare the thrust data in the test report with the design requirements or expected values ​​of the aerospace engine to assess whether its thrust performance meets the standards;

[0035] S308: Based on the comparison results, a comprehensive evaluation of the thrust performance of the aerospace engine is conducted;

[0036] S309: If the test results do not meet the design requirements, the testers can make suggestions for improvement to provide a reference for subsequent research and development work.

[0037] The beneficial effects of this invention are:

[0038] The loading gantry is fixedly installed using fixed components and brackets. The gantry is constructed of high-strength materials, ensuring a robust structure and even distribution of loading force. Protective pads protect the surface of the loading gantry. Hydraulic jacks are installed using mounting bases. These jacks simulate the thrust generated by an aerospace thrust engine during operation, ensuring the thrust is evenly applied to the force-measuring components. The thrust is transmitted to the hydraulic jacks via the piston movement of the hydraulic cylinders. Oil pipes ensure smooth flow of hydraulic oil between the hydraulic cylinders and jacks, facilitating thrust transfer. A manual loading pump controls the hydraulic cylinders or jacks to generate the required thrust. This pump, operated manually, converts mechanical energy into hydraulic energy, drawing in or expelling hydraulic oil. Attached Figure Description

[0039] Figure 1 The diagram shown is a first three-dimensional structural schematic of a field testing device for measuring the thrust of an aerospace engine according to the present invention.

[0040] Figure 2 The diagram shown is a second three-dimensional structural schematic of a field testing device for measuring the thrust of an aerospace engine according to the present invention.

[0041] Figure 3 The diagram shown is a three-dimensional structural illustration of the internal structure of a field testing device for measuring the thrust of an aerospace engine according to the present invention.

[0042] Figure 4The diagram shown is a partial three-dimensional structural schematic of a field testing device for measuring the thrust of an aerospace engine according to the present invention.

[0043] Figure 5 The diagram shown is a partial three-dimensional structural schematic of a field testing device for measuring the thrust of an aerospace engine according to the present invention.

[0044] Figure 6 The diagram shown is a schematic of the thrust loading and simulation process of an on-site testing device for measuring the thrust of an aerospace engine according to the present invention.

[0045] Figure 7 The diagram shown is a schematic of the thrust measurement and feedback process of a field test device for measuring the thrust of an aerospace engine according to the present invention.

[0046] Explanation of reference numerals in the attached drawings: 1. Engine mounting stand; 201. Mounting cavity; 202. Support base; 203. Damping telescopic rod; 204. Pressure relief spring; 205. Backing plate; 301. Cooler; 302. Coolant collection tank; 303. Fixed base; 304. Cooling nozzle; 401. Fixed base plate; 402. Limit bolt; 403. T-slot; 404. Anti-loosening bolt; 405. Three-dimensional force balance; 501. Loading... Gantry frame; 502, protective pad; 503, mounting base; 504, hydraulic jack; 505, hydraulic cylinder; 506, manual loading pump; 507, fixed bracket; 508, oil pipe; 601, standard force sensor; 602, ball-head loading fixture; 603, mounting bracket; 604, force indicator light; 701, mounting block; 702, support bracket; 703, hydraulic telescopic rod; 704, clamping fixture; 705, rotating motor. Detailed Implementation

[0047] The present invention will be further described below with reference to the accompanying drawings and embodiments.

[0048] Please see Figures 1-5This invention provides an embodiment of a field testing device for measuring the thrust of an aerospace engine, comprising an engine mounting platform 1, a vibration damping assembly, a cooling assembly, a fixing assembly, a loading gantry 501, a protective pad 502, a mounting base 503, a hydraulic jack 504, a hydraulic cylinder 505, a manual loading pump 506, a fixing bracket 507, an oil pipe 508, a force measuring assembly, and a clamping assembly. The vibration damping assembly is located on the bottom surface of the engine mounting platform 1, and the cooling assembly is located inside the vibration damping assembly. The fixing assembly is located on the surface of the engine mounting platform 1, and fixing brackets 507 are located on both sides of the fixing assembly. Multiple sets of fixing brackets 507 are provided, and the loading gantry 501 is located on the surface of the fixing brackets 507. The loading gantry 501 is provided with three sets. The top surface of the loading gantry 501 is provided with a protective pad 502, and the surface of the protective pad 502 is provided with multiple anti-slip textures. The bottom surface of the loading gantry 501 is provided with a mounting base 503, and the bottom surface of the mounting base 503 is provided with a hydraulic jack 504. A hydraulic cylinder 505 is provided on one side of the mounting base 503 and on the other side of the hydraulic jack 504. An oil pipe 508 is provided on the bottom surface of the hydraulic cylinder 505, and the hydraulic cylinder 505 and the hydraulic jack 504 are connected through the oil pipe 508. A manual loading pump 506 is provided on one side of the loading gantry 501. A force measuring component is provided on the bottom surface of the hydraulic jack 504. A clamping component is provided on the surface of the engine mounting frame 1.

[0049] Preferably, the vibration generated during the thrust test of the aerospace engine is partially mitigated by the vibration damping component, and the high temperature generated during the thrust test is cooled by the cooling component, which can effectively control and manage the temperature, ensuring the normal operation of the test equipment and the accuracy of the test results. The loading gantry 501 is fixedly installed by the fixing component and the fixing bracket 507. The loading gantry 501 is supported by high-strength materials and has a robust structure, which is used to evenly distribute the loading force. The surface of the loading gantry 501 is protected by the protective pad 502. The hydraulic jack 504 is installed by the mounting base 503, and the hydraulic jack 504 simulates aerospace... The thrust generated by the thrust engine during operation ensures that the thrust is evenly applied to the force measuring component. The thrust is transmitted to the hydraulic jack 504 through the piston movement of the hydraulic cylinder 505 for thrust output. The hydraulic oil is ensured to flow smoothly between the hydraulic cylinder 505 and the hydraulic jack 504 through the oil pipe 508, thereby realizing the transmission of thrust. The hydraulic cylinder 505 or the hydraulic jack 504 is controlled by the manual loading pump 506 to generate the required thrust. The manual loading pump 506 can convert mechanical energy into hydraulic energy through manual operation, and draw in or discharge hydraulic oil. The pressure simulated by the hydraulic jack 504 is detected by the force measuring component. The clamping component clamps the other required equipment.

[0050] Preferably, the damping assembly includes a mounting cavity 201, a support base 202, a damping telescopic rod 203, a pressure-reducing spring 204, and a stop plate 205. The mounting cavity 201 is provided inside the engine mounting frame 1. The support base 202 is provided on the bottom surface of the engine mounting frame 1. The damping telescopic rod 203 is provided on the surface of the support base 202. Multiple sets of damping telescopic rods 203 are provided. The pressure-reducing spring 204 is provided on the outer side of the damping telescopic rod 203. The stop plate 205 is provided at the top of the damping telescopic rod 203. In use, the damping telescopic rod 203 is accommodated by the mounting cavity 201, the damping telescopic rod 203 is installed by the support base 202, the damping telescopic rod 203 supports the engine mounting frame 1, the pressure vibration received by the damping telescopic rod 203 is relieved by the pressure-reducing spring 204, and the stop plate 205 connects the top of the damping telescopic rod 203 to the inside of the mounting cavity 201.

[0051] Preferably, the cooling assembly includes a cooler 301, a coolant collection tank 302, a fixed base 303, and a cooling nozzle 304. The cooler 301 is mounted on the top surface of the support base 202. The cooler 301 is equipped with a cooling circulation system that circulates coolant to the components that need cooling. The coolant is composed of a highly conductive cooling medium. The coolant collection tank 302 is formed on the surface of the cooler 301. The fixed base 303 is installed inside the coolant collection tank 302. Multiple sets of fixed bases 303 are provided. The cooling nozzle 304 is installed inside the fixed base 303. In use, the cooler 301 controls the heat generated during the thrust test of the thrust engine. The coolant flowing out is collected by the coolant collection tank 302. The cooling nozzle 304 is installed by the fixed base 303 and cools the external temperature during the test by the cooling nozzle 304.

[0052] Preferably, the fixing assembly includes a fixing base plate 401, limiting bolts 402, T-slots 403, anti-loosening bolts 404, and a triaxial force measuring balance 405. The fixing base plate 401 is provided on the surface of the engine mounting frame 1. Multiple sets of limiting bolts 402 are provided on the surface of the fixing base plate 401. T-slots 403 are formed on the surface of the fixing base plate 401, and anti-loosening bolts 404 are installed inside the T-slots 403. The triaxial force measuring balance 405 is provided on the top surface of the limiting bolts 402. In use, the limiting bolts 402 are installed using the fixing base plate 401, and the limiting bolts 402 prevent the triaxial force measuring balance 405 from being used for thrust measurement. Excessive displacement or deformation during measurement can be effectively prevented, ensuring the stability and accuracy of the triaxial force balance 405 during the measurement process. The anti-loosening bolt 404 is embedded and fixed by the T-slot 403, preventing the triaxial force balance 405 from loosening under vibration or impact. The T-slot 403 and the anti-loosening bolt 404 work together to ensure that the bolt remains tight during long-term use. The triaxial force balance 405 simultaneously measures the components of thrust in three directions in the thrust simulation. The triaxial force balance 405 has multiple built-in high-precision thrust detection sensors, which can realize accurate measurement of thrust.

[0053] Preferably, the force measuring assembly includes a standard force sensor 601, a ball-head loading fixture 602, a mounting bracket 603, and a force indicator light 604. The standard force sensor 601 is installed at the bottom of the hydraulic jack 504, and the ball-head loading fixture 602 is installed at the bottom of the standard force sensor 601. The mounting bracket 603 is installed on one side of the loading gantry 501, and the force indicator light 604 is installed inside the mounting bracket 603. Multiple sets of force indicator lights 604 are provided. The force indicator lights 604 are electrically connected to the standard force sensor 601. In use, the standard force sensor 601, which has multiple built-in sensing elements, converts mechanical force into electrical signals, thereby realizing the quantitative measurement of thrust. The ball-head loading fixture 602 can evenly distribute the thrust on the surface of the three-dimensional force measuring balance 405 during the thrust measurement process, preventing the thrust from concentrating. The force indicator lights 604 are installed on the mounting bracket 603, and the force indicator lights 604 provide feedback display on the force measurement status.

[0054] Preferably, the clamping assembly includes a mounting block 701, a support bracket 702, a hydraulic telescopic rod 703, a clamping fixture 704, and a rotary motor 705. The surface of the engine mounting frame 1 is provided with mounting blocks 701, and multiple sets of mounting blocks 701 are provided, with each mounting block 701 arranged in pairs. A support bracket 702 is provided on one side of the mounting block 701, and a rotary motor 705 is provided on the other side of the mounting block 701. In use, the rotary motor 705 is installed through the mounting block 701, and the rotary motor 705 drives the support bracket 702 to rotate, thereby supporting the other equipment.

[0055] Preferably, a hydraulic telescopic rod 703 is provided on one side of the support bracket 702, and a clamping fixture 704 is provided at one end of the hydraulic telescopic rod 703. The clamping fixture 704 is made of non-slip material. In use, the clamping fixture 704 is extended and retracted by the hydraulic telescopic rod 703, and the clamping fixture 704 is used to clamp and fix the other equipment.

[0056] Please see Figures 6-7 In this embodiment, a field testing device for measuring the thrust of an aerospace engine includes the following steps when conducting thrust testing:

[0057] S101: First, thrust loading and simulation are performed on the field testing device to ensure that all components operate normally;

[0058] S102: Perform thrust measurement and feedback, collect and record thrust simulation data in real time, and provide feedback.

[0059] As a preferred embodiment, a field testing device for measuring the thrust of an aerospace engine includes the following steps when performing thrust loading and simulation:

[0060] S201: Inspect each and every component of the engine mounting platform 1, including the shock absorption assembly, cooling assembly, fixing assembly, loading gantry 501, hydraulic jack 504, hydraulic cylinder 505, and manual loading pump 506, to ensure they are installed correctly and in good working order.

[0061] S202: Check whether the connections between hydraulic cylinder 505, oil pipe 508 and hydraulic jack 504 are tight and whether there are any leaks, to ensure the integrity and stability of the hydraulic system;

[0062] S203: Activate cooler 301 in the cooling assembly to ensure the coolant can circulate and provide effective temperature control for subsequent thrust testing;

[0063] S204: Verify that all safety structures are in place to ensure safety during testing;

[0064] S205: Mechanical energy is converted into hydraulic energy by manually loading pump 506 to pump at appropriate force and frequency;

[0065] S206: Under the action of the manual loading pump 506, hydraulic oil flows into the hydraulic cylinder 505 through the oil pipe 508, pushing the piston forward;

[0066] S207: The piston movement of hydraulic cylinder 505 is converted into a vertically downward thrust through hydraulic jack 504, simulating the thrust of a space engine during operation;

[0067] S208: The thrust generated by the hydraulic jack 504 is evenly distributed onto the force-bearing surface of the triaxial force-measuring balance 405 through the ball-head loading fixture 602, ensuring the accuracy and stability of the thrust measurement;

[0068] S209: During the thrust simulation, closely observe the stability of components such as the loading gantry 501 and protective pad 502 to ensure that they do not shake or shift.

[0069] Preferably, a field test device for measuring the thrust of an aerospace engine includes the following steps when performing thrust measurement and feedback:

[0070] S301: When thrust is applied to the triaxial force balance 405, its built-in high-precision thrust detection sensor starts working, converting mechanical force into an electrical signal;

[0071] S302: Electrical signals are transmitted to the data processing system via data cable or wireless transmission for real-time acquisition and recording;

[0072] S303: The data processing system performs preliminary processing on the acquired raw data, such as filtering and noise reduction, to improve measurement accuracy;

[0073] S304: The force indicator light 604 illuminates the corresponding indicator light according to the electrical signal transmitted by the standard force sensor 601, intuitively displaying the current range of thrust.

[0074] S305: The data processing system can also display real-time thrust data on the screen in digital or graphical form for testing personnel to monitor at any time;

[0075] S306: After the test, the data processing system generates a detailed test report based on the collected data, including key indicators such as average thrust, peak thrust, and fluctuation range;

[0076] S307: Compare the thrust data in the test report with the design requirements or expected values ​​of the aerospace engine to assess whether its thrust performance meets the standards;

[0077] S308: Based on the comparison results, a comprehensive evaluation of the thrust performance of the aerospace engine is conducted;

[0078] S309: If the test results do not meet the design requirements, the testers can make suggestions for improvement to provide a reference for subsequent research and development work.

[0079] The embodiments of the present invention have been described in detail above with reference to the accompanying drawings. However, the present invention is not limited to the above embodiments. Within the scope of knowledge possessed by those skilled in the art, various changes can be made without departing from the spirit of the present invention.

Claims

1. A field testing device for measuring the thrust of an aerospace engine, characterized in that: The components include an engine mounting stand (1), a shock absorber assembly, a cooling assembly, a fixing assembly, a loading gantry (501), a protective pad (502), a mounting base (503), a hydraulic jack (504), a hydraulic cylinder (505), a manual loading pump (506), a fixing bracket (507), an oil pipe (508), a force measuring assembly, and a clamping assembly. The bottom surface of the engine mounting stand (1) is provided with a shock absorber assembly, and the interior of the shock absorber assembly is provided with a cooling assembly. The surface of the engine mounting stand (1) is provided with a fixing assembly, and both sides of the fixing assembly are provided with fixing brackets (507). Multiple sets of fixing brackets (507) are provided. The surface of the fixing brackets (507) is provided with a loading gantry (501), and there are three sets of loading gantry (501). The top surface of the frame (501) is provided with a protective pad (502), and the surface of the protective pad (502) is provided with multiple anti-slip textures. The bottom surface of the loading gantry frame (501) is provided with a mounting base (503), the bottom surface of the mounting base (503) is provided with a hydraulic jack (504), one side of the mounting base (503) is provided with a hydraulic cylinder (505), one side of the hydraulic jack (504) is provided with a hydraulic pipe (508), and the hydraulic cylinder (505) and the hydraulic jack (504) are connected through the hydraulic pipe (508). One side of the loading gantry frame (501) is provided with a manual loading pump (506), the bottom surface of the hydraulic jack (504) is provided with a force measuring component, and the surface of the engine mounting platform (1) is provided with a clamping component.

2. The field testing device for measuring the thrust of an aerospace engine according to claim 1, characterized in that: The damping assembly includes a mounting cavity (201), a support base (202), a damping telescopic rod (203), a pressure relief spring (204), and a stop plate (205). The engine mounting stand (1) has a mounting cavity (201) inside. The bottom surface of the engine mounting stand (1) is provided with a support base (202). The surface of the support base (202) is provided with a damping telescopic rod (203). There are multiple sets of damping telescopic rods (203). A pressure relief spring (204) is provided on the outside of the damping telescopic rod (203). A stop plate (205) is provided at the top of the damping telescopic rod (203).

3. The field testing device for measuring the thrust of an aerospace engine according to claim 2, characterized in that: The cooling assembly includes a cooler (301), a coolant collection tank (302), a fixed base (303), and a cooling nozzle (304). The cooler (301) is provided on the top surface of the support base (202). The cooler (301) is provided with a cooling circulation system to circulate and transport the coolant to the parts that need to be cooled. The coolant is composed of a highly conductive cooling medium. The surface of the cooler (301) is provided with a coolant collection tank (302). The fixed base (303) is provided inside the coolant collection tank (302). Multiple sets of fixed bases (303) are provided. The cooling nozzle (304) is provided inside the fixed base (303).

4. The field testing device for measuring the thrust of an aerospace engine according to claim 3, characterized in that: The fixing components include a fixing base plate (401), a limiting bolt (402), a T-slot (403), an anti-loosening bolt (404), and a three-dimensional force measuring balance (405). The surface of the engine mounting stand (1) is provided with a fixing base plate (401), the surface of the fixing base plate (401) is provided with multiple sets of limiting bolts (402), the surface of the fixing base plate (401) is provided with a T-slot (403), the inside of the T-slot (403) is provided with an anti-loosening bolt (404), and the top surface of the limiting bolt (402) is provided with a three-dimensional force measuring balance (405).

5. The field testing device for measuring the thrust of an aerospace engine according to claim 4, characterized in that: The force measuring component includes a standard force sensor (601), a ball-head loading fixture (602), a mounting bracket (603), and a force measuring indicator (604). The standard force sensor (601) is installed at the bottom of the hydraulic jack (504), and the ball-head loading fixture (602) is installed at the bottom of the standard force sensor (601). The mounting bracket (603) is installed on one side of the loading gantry (501), and the force measuring indicator (604) is installed inside the mounting bracket (603). There are multiple sets of force measuring indicator (604), and the force measuring indicator (604) is electrically connected to the standard force sensor (601).

6. The field testing device for measuring the thrust of an aerospace engine according to claim 5, characterized in that: The clamping assembly includes a mounting block (701), a support bracket (702), a hydraulic telescopic rod (703), a clamping fixture (704), and a rotary motor (705). The surface of the engine mounting stand (1) is provided with mounting blocks (701). Multiple sets of mounting blocks (701) are provided, with each mounting block (701) arranged in pairs. A support bracket (702) is provided on one side of the mounting block (701), and a rotary motor (705) is provided on the other side of the mounting block (701).

7. The field testing device for measuring the thrust of an aerospace engine according to claim 6, characterized in that: A hydraulic telescopic rod (703) is provided on one side of the support bracket (702), and a clamping fixture (704) is provided at one end of the hydraulic telescopic rod (703). The clamping fixture (704) is made of non-slip material.

8. The field testing device for measuring the thrust of an aerospace engine according to claim 7, characterized in that: A field testing device for measuring the thrust of an aerospace engine includes the following steps during thrust testing: S101: First, thrust loading and simulation are performed on the field testing device to ensure that all components operate normally; S102: Perform thrust measurement and feedback, collect and record thrust simulation data in real time, and provide feedback.

9. The field testing device for measuring the thrust of an aerospace engine according to claim 8, characterized in that: A field testing device for measuring the thrust of an aerospace engine includes the following steps when performing thrust loading and simulation: S201: Inspect each and every component of the equipment, including the engine mounting stand (1), shock absorber assembly, cooling assembly, fixing assembly, loading gantry (501), hydraulic jack (504), hydraulic cylinder (505), and manual loading pump (506), to ensure that they are installed correctly and in good working order. S202: Check whether the connections between the hydraulic cylinder (505), oil pipe (508) and hydraulic jack (504) are tight and whether there are any leaks, to ensure the integrity and stability of the hydraulic system; S203: Activate the cooler (301) in the cooling assembly to ensure that the coolant can circulate and provide effective temperature control for subsequent thrust testing; S204: Verify that all safety structures are in place to ensure safety during testing; S205: Mechanical energy is converted into hydraulic energy by manually loading the pump (506) with appropriate force and frequency; S206: Under the action of the manual loading pump (506), hydraulic oil flows into the hydraulic cylinder (505) through the oil pipe (508), pushing the piston forward; S207: The piston movement of the hydraulic cylinder (505) is converted into a vertically downward thrust through the hydraulic jack (504), simulating the thrust of a space engine during operation; S208: The thrust generated by the hydraulic jack (504) is evenly distributed onto the force-bearing surface of the triaxial force balance (405) through the ball-head loading fixture (602), ensuring the accuracy and stability of the thrust measurement; S209: During the thrust simulation, closely observe the stability of components such as the loading gantry (501) and protective pad (502) to ensure that they do not shake or shift.

10. The field testing device for measuring the thrust of an aerospace engine according to claim 9, characterized in that: A field test device for measuring thrust of an aerospace engine includes the following steps when performing thrust measurement and feedback: S301: When thrust is applied to the triaxial force balance (405), its built-in high-precision thrust detection sensor starts working, converting mechanical force into an electrical signal; S302: Electrical signals are transmitted to the data processing system via data cable or wireless transmission for real-time acquisition and recording; S303: The data processing system performs preliminary processing on the acquired raw data, such as filtering and noise reduction, to improve measurement accuracy; S304: Force indicator light (604) illuminates the corresponding indicator light according to the electrical signal transmitted by the standard force sensor (601), intuitively displaying the current range of thrust. S305: The data processing system can also display real-time thrust data on the screen in digital or graphical form for testing personnel to monitor at any time; S306: After the test, the data processing system generates a detailed test report based on the collected data, including key indicators such as average thrust, peak thrust, and fluctuation range; S307: Compare the thrust data in the test report with the design requirements or expected values ​​of the aerospace engine to assess whether its thrust performance meets the standards; S308: Based on the comparison results, a comprehensive evaluation of the thrust performance of the aerospace engine is conducted; S309: If the test results do not meet the design requirements, the testers can make suggestions for improvement to provide a reference for subsequent research and development work.

Images