Field testing device for measuring thrust of airspace engine

Abstract

The invention relates to the technical field of airspace engine thrust measurement, in particular to a field test device for airspace engine thrust measurement. According to the technical scheme, the field testing device for measuring the thrust of the airspace engine comprises an engine mounting rack, a loading portal frame, a protection pad, a mounting base, a hydraulic jack, a hydraulic oil cylinder, a manual loading pump, a fixing support, an oil pipe, a force measuring assembly and a clamping assembly, and a damping assembly is arranged on the bottom face of the engine mounting rack; a cooling assembly is arranged in the damping assembly; compared with a traditional on-site testing device for measuring thrust of an airspace engine, the on-site testing device for measuring thrust of the airspace engine has the advantages that a single loading mode is generally adopted, the influence of lateral force cannot be effectively eliminated in the loading process, and loading force cannot be uniformly distributed, and the on-site testing device for measuring thrust of the airspace engine adopts three portal frame loading devices; and the thrust balances are sequentially loaded according to the circumferential uniform layout, so that the accuracy and the reliability of the test can be effectively improved.

Description

Technical Field

[0001] The invention relates to the technical field of aerospace engine thrust measurement, and in particular to a field test device for aerospace engine thrust measurement. Background Art

[0002] The thrust measurement device is an indispensable equipment in the development and testing of aerospace engines. It can simulate the working environment of the engine on the ground and verify and evaluate the performance, function, strength, reliability and other aspects of the engine by accurately measuring the thrust generated by the engine and its related parameters.

[0003] Existing field test devices for measuring aerospace engine thrust generally adopt a single loading method, which may not be able to effectively eliminate the influence of lateral force during the loading process and cannot evenly distribute the loading force. At the same time, the safety issues of the thrust measurement balance under abnormal conditions when measuring engine thrust are not considered, which can easily lead to deviations in the results.

[0004] Aiming at the safety problem of the thrust measuring balance in abnormal circumstances when measuring the engine thrust in the existing field test device for measuring the thrust of aerospace engines, which easily leads to the problem of deviation in the results, the field test device for measuring the thrust of aerospace engines adopts three groups of gantry loading devices, which are evenly arranged according to the circumference, and load the thrust balance in sequence, which can effectively improve the accuracy and reliability of the test. The design of the ball head tooling can effectively ensure the accurate transmission of the loading force and reduce the test error. At the same time, a limit bolt is installed between the upper and lower floors of the thrust measuring balance, which is connected to the upper floor through a thread, and an anti-loosening nut is installed. It is connected to the lower base plate through a T-shaped structure with a gap, which does not affect the force on the balance under normal circumstances, but can prevent the balance from being damaged under abnormal circumstances, ensuring the safety of the test. Summary of the invention

[0005] In order to overcome the existing field test equipment for aerospace engine thrust measurement, a single loading method is generally used. During the loading process, the influence of lateral force may not be effectively eliminated, and the loading force cannot be evenly distributed. At the same time, the safety of the thrust measurement balance under abnormal conditions when measuring the engine thrust is not considered, which can easily lead to deviations in the results.

[0006] The technical solution of the present invention is: a field test device for measuring the thrust of an aerospace engine, comprising an engine mounting stand, a shock absorbing assembly, a cooling assembly, a fixing assembly, a loading gantry, a protective pad, a mounting base, a hydraulic jack, a hydraulic oil cylinder, a manual loading pump, a fixing bracket, an oil pipe, a force measuring assembly and a clamping assembly, wherein the bottom surface of the engine mounting stand is provided with a shock absorbing assembly, the interior of the shock absorbing assembly is provided with a cooling assembly, the surface of the engine mounting stand is provided with a fixing assembly, both sides of the fixing assembly are provided with fixing brackets, a plurality of fixing brackets are provided, and the surface of the fixing brackets A loading gantry is provided, and there are three groups of loading gantries in total. A protection pad is provided on the top surface of the loading gantry, and a plurality of anti-slip grooves are provided on the surface of the protection pad. A mounting base is provided on the bottom surface of the loading gantry, and a hydraulic jack is provided on the bottom surface of the mounting base. A hydraulic cylinder is provided on one side of the mounting base, and an oil pipe is provided on the bottom surface of the hydraulic cylinder. The hydraulic cylinder is connected to the hydraulic jack through the oil pipe. A manual loading pump is provided on one side of the loading gantry, and a force measuring assembly is provided on the bottom surface of the hydraulic jack. A clamping assembly is provided on the surface of the engine mounting stand.

[0007] Preferably, the vibration generated during the thrust test of the aerospace engine is partially alleviated by the shock absorbing component, and the high temperature generated during the thrust test is cooled by the cooling component, so that the temperature can be effectively controlled and managed to ensure the normal operation of the test equipment and the accuracy of the test results. The loading gantry is fixedly installed by the fixing component, and the loading gantry is installed by the fixing bracket. The loading gantry is supported by high-strength materials and has a solid structure, which is used to evenly distribute the loading force. The surface of the loading gantry is protected by the protective pad, and the hydraulic jack is installed by the mounting base. The hydraulic jack is simulated by the hydraulic jack. The thrust generated by the aerospace thrust engine during operation ensures that the thrust can be evenly loaded onto the force measuring component, and is transmitted to the hydraulic jack for thrust output through the piston movement of the hydraulic cylinder. The oil pipe ensures that the hydraulic oil can move smoothly between the hydraulic cylinder and the hydraulic jack, thereby realizing the transmission of thrust. The manual loading pump is used to control the hydraulic cylinder or hydraulic jack to generate the required thrust. The manual loading pump can convert mechanical energy into hydraulic energy through human operation, inhale or discharge hydraulic oil, and detect the pressure simulated by the hydraulic jack through the force measuring component, and clamp the remaining required equipment through the clamping component.

[0008] Preferably, the shock absorbing assembly includes an installation cavity, a support base, a damping telescopic rod, a pressure relief spring and a back plate. The engine mounting stand is provided with an installation cavity inside, the bottom surface of the engine mounting stand is provided with a support base, the surface of the support base is provided with a damping telescopic rod, multiple groups of damping telescopic rods are provided, a pressure relief spring is provided on the outside of the damping telescopic rod, and a back plate is provided on the top of the damping telescopic rod.

[0009] Preferably, the cooling assembly includes a cooler, a coolant collecting tank, a fixed base and a cooling nozzle. The cooler is arranged on the top surface of the supporting base. A cooling circulation system is arranged in the cooler to circulate the coolant to the components that need to be cooled. The coolant is composed of a high conductivity cooling medium. A coolant collecting tank is arranged on the surface of the cooler. A fixed base is arranged inside the coolant collecting tank. The fixed base is provided with multiple groups, and a cooling nozzle is arranged inside the fixed base.

[0010] Preferably, the fixing assembly includes a fixed base plate, a limiting bolt, a T-slot, an anti-loosening bolt and a three-way force dynamometer. The surface of the engine mounting stand is provided with a fixed base plate, the surface of the fixed base plate is provided with multiple groups of limiting bolts, the surface of the fixed 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 limiting bolt is provided with a three-way force dynamometer.

[0011] Preferably, the force measuring assembly includes a standard force sensor, a ball head loading tooling, a mounting frame and a force measuring indicator light. A standard force sensor is arranged at the bottom end of the hydraulic jack, a ball head loading tooling is arranged at the bottom end of the standard force sensor, a mounting frame is arranged on one side of the loading gantry, a force measuring indicator light is arranged inside the mounting frame, multiple groups of force measuring indicator lights are arranged, and the force measuring indicator lights are electrically connected to the standard force sensor.

[0012] Preferably, the clamping assembly includes a mounting block, a supporting bracket, a hydraulic telescopic rod, a clamping fixture and a rotating motor. The surface of the engine mounting stand is provided with a mounting block. The mounting blocks are provided in multiple groups and are arranged in pairs. A supporting bracket is provided on one side of the mounting block and a rotating motor is 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 on one end of the hydraulic telescopic rod, and the clamping fixture is made of anti-slip material.

[0014] Preferably, a field test device for measuring thrust of an aerospace engine comprises the following steps when performing thrust testing: S101: First, thrust loading and simulation are performed on the field test device to ensure the normal operation of each component; S102: Thrust measurement and feedback are performed, and thrust simulation data is collected and recorded in real time and feedback is performed.

[0015] Preferably, a field test device for measuring thrust of aerospace engines comprises the following steps when performing thrust loading and simulation: S201: Check all equipment components such as the engine mounting stand, shock absorbing assembly, cooling assembly, fixing assembly, loading gantry, hydraulic jack, hydraulic cylinder, manual loading pump, etc. one by one to ensure that they are installed correctly and in good working condition; S202: Check whether the connection between the hydraulic cylinder, oil pipe and hydraulic jack is tight and whether there is any leakage to ensure the integrity and stability of the hydraulic system; S203: Start the cooler in the cooling assembly to ensure that the coolant can circulate and provide effective temperature control for subsequent thrust tests; S204: Confirm that all safety structures are in place to ensure safety during testing; S205: The mechanical energy is converted into hydraulic energy by manually loading the pump with appropriate force and frequency; S206: Under the action of the manual loading pump, the hydraulic oil flows into the hydraulic cylinder through the oil pipe, pushing the piston forward; S207: The piston movement of the hydraulic cylinder is converted into vertical downward thrust through the hydraulic jack, simulating the thrust of the aerospace engine at work; S208: The thrust generated by the hydraulic jack is evenly distributed to the force-bearing surface of the three-way force measuring balance through the ball head loading fixture to ensure the accuracy and stability of the thrust measurement; S209: During the thrust simulation, closely observe the stability of the loading gantry, protection pads and other components to ensure that they do not shake or move.

[0016] Preferably, a field test device for measuring thrust of aerospace engines comprises the following steps when performing thrust measurement and feedback: S301: When the thrust is applied to the three-axis force measuring balance, its built-in high-precision thrust detection sensor starts to work and converts the mechanical force into an electrical signal; S302: The electrical signal is sent to the data processing system via a data line or wireless transmission for real-time collection and recording; S303: The data processing system performs preliminary processing on the collected raw data, such as filtering, denoising, etc., to improve measurement accuracy; S304: The force indicator light turns on the corresponding indicator light according to the electrical signal transmitted by the standard force sensor, visually displaying the current thrust range; S305: The data processing system can also display the real-time thrust data in digital or graphical form on the screen for the test 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 thrust average value, peak value, fluctuation range, etc.; S307: Compare the thrust data in the test report with the design requirements or expected values ​​of the aerospace engine to evaluate whether its thrust performance meets the standards; S308: Based on the comparison results, conduct a comprehensive assessment of the thrust performance of the aerospace engine; S309: If the test results do not meet the design requirements, the tester can make improvement suggestions to provide reference for subsequent R&D work.

[0017] Beneficial effects of the present invention: The loading gantry is fixedly installed by a fixing component, and the loading gantry is installed by a fixing bracket. The loading gantry is supported by high-strength materials and has a solid structure, which is used to evenly distribute the loading force. The surface of the loading gantry is protected by a protective pad, and the hydraulic jack is installed by an installation base. The hydraulic jack simulates the thrust generated by the aerospace thrust engine when working, ensuring that the thrust can be evenly loaded on the force measuring component, and the thrust is transmitted to the hydraulic jack for thrust output through the piston movement of the hydraulic cylinder. The oil pipe ensures that the hydraulic oil can move smoothly between the hydraulic cylinder and the hydraulic jack, thereby realizing the transmission of thrust. The hydraulic cylinder or hydraulic jack is controlled by a manual loading pump to generate the required thrust. The manual loading pump can convert mechanical energy into hydraulic energy through human operation, and inhale or discharge hydraulic oil. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 Shown is a first three-dimensional structural schematic diagram of a field test device for measuring thrust of an aerospace engine according to the present invention; Figure 2 Shown is a second three-dimensional structural schematic diagram of a field test device for measuring thrust of an aerospace engine according to the present invention; Figure 3 Shown is a schematic diagram of the internal three-dimensional structure of a field test device for measuring thrust of an aerospace engine according to the present invention; Figure 4 Shown is a schematic diagram of a first partial three-dimensional structure of a field test device for measuring thrust of an aerospace engine according to the present invention; Figure 5 Shown is a second partial three-dimensional structural schematic diagram of a field test device for measuring thrust of an aerospace engine according to the present invention; Figure 6 Shown is a schematic diagram of thrust loading and simulation flow of a field test device for measuring thrust of an aerospace engine according to the present invention; Figure 7 Shown is a schematic diagram of thrust measurement and feedback flow of a field test device for measuring thrust of an aerospace engine according to the present invention; Description of reference numerals: 1. engine mounting stand; 201. mounting cavity; 202. support base; 203. damping telescopic rod; 204. pressure relief spring; 205. abutment plate; 301. cooler; 302. coolant collecting tank; 303. fixed base; 304. cooling nozzle; 401. fixed bottom plate; 402. limiting bolt; 403. T-slot; 404. anti-loosening bolt; 405. three-way force measuring balance; 501. loading Gantry; 502, protection pad; 503, mounting base; 504, hydraulic jack; 505, hydraulic cylinder; 506, manual loading pump; 507, fixing bracket; 508, oil pipe; 601, standard force sensor; 602, ball head loading tooling; 603, mounting bracket; 604, force indicator light; 701, mounting block; 702, supporting bracket; 703, hydraulic telescopic rod; 704, clamping fixture; 705, rotating motor. 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 5 The present invention provides an embodiment: a field test device for measuring thrust of aerospace engines, comprising an engine mounting stand 1, a shock absorbing assembly, a cooling assembly, a fixing assembly, a loading gantry 501, a protection pad 502, a mounting base 503, a hydraulic jack 504, a hydraulic oil cylinder 505, a manual loading pump 506, a fixing bracket 507, an oil pipe 508, a force measuring assembly and a clamping assembly, a shock absorbing assembly is arranged on the bottom surface of the engine mounting stand 1, a cooling assembly is arranged inside the shock absorbing assembly, a fixing assembly is arranged on the surface of the engine mounting stand 1, fixing brackets 507 are arranged on both sides of the fixing assembly, a plurality of fixing brackets 507 are arranged, and a loading gantry 501 is arranged on the surface of the fixing bracket 507, There are three groups of loading gantries 501. The top surface of the loading gantry 501 is provided with a protection pad 502, and the surface of the protection pad 502 is provided with multiple groups of anti-slip grooves. 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. One side of the mounting base 503 is provided with a hydraulic cylinder 505, and the bottom surface of the hydraulic cylinder 505 is provided with an oil pipe 508. The hydraulic cylinder 505 is connected to the hydraulic jack 504 through the oil pipe 508. A manual loading pump 506 is provided on one side of the loading gantry 501, and a force measuring component is provided on the bottom surface of the hydraulic jack 504. The surface of the engine mounting stand 1 is provided with a clamping component.

[0021] Preferably, the vibration generated during the thrust test of the aerospace engine is partially alleviated by the shock absorbing component, and the high temperature generated during the thrust test is cooled by the cooling component, so that the temperature can be effectively controlled and managed to ensure 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 loading gantry 501 is installed by the fixing bracket 507. The loading gantry 501 is supported by high-strength materials and has a solid structure for uniformly distributing 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 the aerospace The thrust generated by the thrust engine when working ensures that the thrust can be evenly loaded on the force measuring component, and is transmitted to the hydraulic jack 504 for thrust output through the piston movement of the hydraulic cylinder 505. The oil pipe 508 ensures that the hydraulic oil can move smoothly between the hydraulic cylinder 505 and the hydraulic jack 504, thereby realizing the transmission of thrust. The manual loading pump 506 is used to control the hydraulic cylinder 505 or the hydraulic jack 504 to generate the required thrust. The manual loading pump 506 can convert mechanical energy into hydraulic energy through human operation, inhale or discharge hydraulic oil, detect the pressure simulated by the hydraulic jack 504 through the force measuring component, and clamp the remaining required equipment through the clamping component.

[0022] Preferably, the shock absorbing assembly includes an installation cavity 201, a support base 202, a damping telescopic rod 203, a pressure relief spring 204 and a butt plate 205. The engine mounting pedestal 1 is provided with an installation cavity 201, the bottom surface of the engine mounting pedestal 1 is provided with a support base 202, the surface of the support base 202 is provided with a damping telescopic rod 203, multiple groups of damping telescopic rods 203 are provided, the outer side of the damping telescopic rod 203 is provided with a pressure relief spring 204, and the top of the damping telescopic rod 203 is provided with a butt plate 205. When in use, the damping telescopic rod 203 is accommodated by the installation cavity 201, the damping telescopic rod 203 is installed by the support base 202, the engine mounting pedestal 1 is supported by the damping telescopic rod 203, the pressure vibration received by the damping telescopic rod 203 is alleviated by the pressure relief spring 204, and the top of the damping telescopic rod 203 and the inside of the installation cavity 201 are connected by the butt plate 205.

[0023] Preferably, the cooling assembly includes a cooler 301, a coolant collecting tank 302, a fixed base 303 and a cooling nozzle 304. The cooler 301 is arranged on the top surface of the support base 202. A cooling circulation system is arranged in the cooler 301 to circulate the coolant to the components that need to be cooled. The coolant is composed of a high-conductivity cooling medium. A coolant collecting tank 302 is opened on the surface of the cooler 301. A fixed base 303 is arranged inside the coolant collecting tank 302. The fixed base 303 is provided with multiple groups. A cooling nozzle 304 is arranged inside the fixed base 303. When in use, the heat generated during the thrust test of the thrust engine is controlled by the cooler 301, the flowing coolant is collected by the coolant collecting tank 302, the cooling nozzle 304 is installed by the fixed base 303, and the external temperature during the test is cooled by the cooling nozzle 304.

[0024] Preferably, the fixing assembly includes a fixed base plate 401, a limiting bolt 402, a T-slot 403, an anti-loosening bolt 404 and a three-way force dynamometer 405. The surface of the engine mounting stand 1 is provided with a fixed base plate 401, the surface of the fixed base plate 401 is provided with multiple groups of limiting bolts 402, the surface of the fixed base plate 401 is provided with a T-slot 403, the interior 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-way force dynamometer 405. When in use, the limiting bolt 402 is installed through the fixed base plate 401, and the limiting bolt 402 is used to prevent the three-way force dynamometer 405 from being loosened during thrust measurement. Excessive displacement or deformation occurs during the measurement process, which can effectively ensure the stability and accuracy of the three-axis force dynamometer 405 during the measurement process. The anti-loosening bolt 404 is embedded and fixed through the T-slot 403. The anti-loosening bolt 404 prevents the three-axis force dynamometer 405 from loosening under vibration or impact conditions. The T-slot 403 and the anti-loosening bolt 404 can effectively ensure that the bolt remains in a tightened state during long-term use. The three-axis force dynamometer 405 simultaneously measures the components of the three directions in the thrust simulation. The three-axis force dynamometer 405 has multiple high-precision thrust detection sensors built in, which can achieve accurate measurement of the thrust.

[0025] Preferably, the force measuring assembly includes a standard force sensor 601, a ball head loading tooling 602, a mounting frame 603 and a force measuring indicator light 604. The bottom end of the hydraulic jack 504 is provided with a standard force sensor 601, the bottom end of the standard force sensor 601 is provided with a ball head loading tooling 602, a mounting frame 603 is provided on one side of the loading gantry 501, and a force measuring indicator light 604 is provided inside the mounting frame 603. There are multiple groups of force measuring indicator lights 604, and the force measuring indicator lights 604 are connected to the standard force sensor 601 by telecommunication. When in use, the standard force sensor 601 has multiple built-in sensing elements to convert mechanical force into electrical signals, thereby realizing quantitative measurement of thrust. The ball head loading tooling 602 can evenly distribute the thrust to the surface of the three-way force measuring balance 405 during the thrust measurement process to prevent thrust concentration. The force measuring indicator light 604 is installed through the mounting frame 603, and the force measuring condition is fed back and displayed through the force measuring indicator light 604.

[0026] Preferably, the clamping assembly includes a mounting block 701, a support bracket 702, a hydraulic telescopic rod 703, a clamping fixture 704 and a rotating motor 705. The surface of the engine mounting stand 1 is provided with a mounting block 701. There are multiple groups of mounting blocks 701, and the mounting blocks 701 are arranged in pairs. A supporting bracket 702 is provided on one side of the mounting block 701, and a rotating motor 705 is provided on the other side of the mounting block 701. When in use, the rotating motor 705 is installed through the mounting block 701, and the supporting bracket 702 is driven to rotate by the rotating motor 705, and the remaining equipment is supported by the supporting bracket 702.

[0027] Preferably, a hydraulic telescopic rod 703 is provided on one side of the support bracket 702, and a clamping fixture 704 is provided on one end of the hydraulic telescopic rod 703. The clamping fixture 704 is made of anti-slip material. When in use, the hydraulic telescopic rod 703 drives the clamping fixture 704 to extend and retract, and the clamping fixture 704 clamps and fixes the remaining equipment.

[0028] See also Figure 6-Figure 7 In this embodiment, a field test device for measuring thrust of an aerospace engine includes the following steps when performing a thrust test: S101: First, thrust loading and simulation are performed on the field test device to ensure the normal operation of each component; S102: Thrust measurement and feedback are performed, and thrust simulation data is collected and recorded in real time and feedback is performed.

[0029] Preferably, a field test device for measuring thrust of aerospace engines comprises the following steps when performing thrust loading and simulation: S201: Check all equipment components such as the engine mounting stand 1, the shock absorbing assembly, the cooling assembly, the fixing assembly, the loading gantry 501, the hydraulic jack 504, the hydraulic cylinder 505, the manual loading pump 506, etc. one by one to ensure that they are installed correctly and are in good working condition; S202: Check whether the connection between the hydraulic cylinder 505, the oil pipe 508 and the hydraulic jack 504 is tight and whether there is leakage to ensure the integrity and stability of the hydraulic system; S203: Start the cooler 301 in the cooling assembly to ensure that the coolant can circulate and provide effective temperature control for subsequent thrust tests; S204: Confirm that all safety structures are in place to ensure safety during testing; S205: By manually loading the pump 506 with appropriate force and frequency to pump, the mechanical energy is converted into hydraulic energy; S206: The hydraulic oil under the action of the manual loading pump 506 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 vertical downward thrust through the hydraulic jack 504, simulating the thrust of the aerospace engine at work; S208: The thrust generated by the hydraulic jack 504 is evenly distributed to the force surface of the three-way force measuring balance 405 through the ball head loading tool 602 to ensure the accuracy and stability of the thrust measurement; S209: During the thrust simulation, closely observe the stability of the loading gantry 501, the protection pad 502 and other components to ensure that they do not shake or move.

[0030] Preferably, a field test device for measuring thrust of aerospace engines comprises the following steps when performing thrust measurement and feedback: S301: When the thrust is loaded onto the three-way force measuring balance 405, its built-in high-precision thrust detection sensor starts working, converting the mechanical force into an electrical signal; S302: The electrical signal is sent to the data processing system via a data line or wireless transmission for real-time collection and recording; S303: The data processing system performs preliminary processing on the collected raw data, such as filtering, denoising, etc., to improve measurement accuracy; S304: force indicator light 604 according to the standard force sensor 601 transmits the electrical signal to light the corresponding indicator light, visually displaying the current thrust range; S305: The data processing system can also display the real-time thrust data in digital or graphical form on the screen for the test 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 thrust average value, peak value, fluctuation range, etc.; S307: Compare the thrust data in the test report with the design requirements or expected values ​​of the aerospace engine to evaluate whether its thrust performance meets the standards; S308: Based on the comparison results, conduct a comprehensive assessment of the thrust performance of the aerospace engine; S309: If the test results do not meet the design requirements, the tester can make improvement suggestions to provide reference for subsequent R&D work.

[0031] 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. A field test device for measuring thrust of an aerospace engine, characterized in that: The invention comprises an engine mounting platform (1), a shock absorbing component, a cooling component, a fixing component, a loading gantry (501), a protective pad (502), a mounting base (503), a hydraulic jack (504), a hydraulic oil cylinder (505), a manual loading pump (506), a fixing bracket (507), an oil pipe (508), a force measuring component and a clamping component. The bottom surface of the engine mounting platform (1) is provided with a shock absorbing component, the interior of the shock absorbing component is provided with a cooling component, the surface of the engine mounting platform (1) is provided with a fixing component, both sides of the fixing component are provided with fixing brackets (507), a plurality of fixing brackets (507) are provided, a loading gantry (501) is provided on the surface of the fixing bracket (507), and a total of three loading gantry (501) are provided. The top surface of the frame (501) is provided with a protection pad (502), and the surface of the protection pad (502) is provided with multiple groups of anti-skid grooves. 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). One side of the mounting base (503) is provided with a hydraulic cylinder (505), and one side of the hydraulic jack (504) is provided with an oil pipe (508). The hydraulic cylinder (505) is connected to the hydraulic jack (504) through the oil pipe (508). A manual loading pump (506) is provided on one side of the loading gantry (501), and a force measuring assembly is provided on the bottom surface of the hydraulic jack (504). A clamping assembly is provided on the surface of the engine mounting stand (1).

2. The on-site test device for measuring thrust of an aerospace engine according to claim 1, characterized in that: The shock absorbing assembly comprises a mounting cavity (201), a support base (202), a damping telescopic rod (203), a pressure relief spring (204) and a stop plate (205); the mounting cavity (201) is provided inside the engine mounting platform (1); the support base (202) is provided on the bottom surface of the engine mounting platform (1); the damping telescopic rod (203) is provided on the surface of the support base (202); a plurality of groups of the damping telescopic rod (203) are provided; a pressure relief spring (204) is provided on the outside of the damping telescopic rod (203); and a stop plate (205) is provided on the top end of the damping telescopic rod (203).

3. The on-site test device for measuring thrust of an aerospace engine according to claim 2, characterized in that: The cooling assembly comprises a cooler (301), a coolant collecting tank (302), a fixed base (303) and a cooling nozzle (304); the cooler (301) is arranged on the top surface of the supporting base (202); a cooling circulation system is arranged in the cooler (301) to circulate the coolant to the parts that need to be cooled; the coolant is composed of a high-conductivity cooling medium; a coolant collecting tank (302) is provided on the surface of the cooler (301); a fixed base (303) is arranged inside the coolant collecting tank (302); a plurality of fixed bases (303) are arranged; and a cooling nozzle (304) is arranged inside the fixed base (303).

4. The on-site test device for measuring thrust of an aerospace engine according to claim 1, characterized in that: The fixing assembly comprises 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 the fixing base plate (401), the surface of the fixing base plate (401) is provided with a plurality of groups 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 on-site test device for measuring thrust of an aerospace engine according to claim 1, characterized in that: The force measuring assembly comprises a standard force sensor (601), a ball head loading tool (602), a mounting frame (603) and a force measuring indicator light (604). The bottom end of the hydraulic jack (504) is provided with a standard force sensor (601), the bottom end of the standard force sensor (601) is provided with a ball head loading tool (602), one side of the loading gantry (501) is provided with a mounting frame (603), a force measuring indicator light (604) is provided inside the mounting frame (603), a plurality of force measuring indicator lights (604) are provided, and the force measuring indicator lights (604) are connected to the standard force sensor (601) in a telecommunication manner.

6. The on-site test device for measuring thrust of an aerospace engine according to claim 1, characterized in that: The clamping assembly comprises a mounting block (701), a supporting bracket (702), a hydraulic telescopic rod (703), a clamping fixture (704) and a rotating motor (705). The surface of the engine mounting stand (1) is provided with the mounting block (701). The mounting blocks (701) are provided in multiple groups. The mounting blocks (701) are arranged in pairs. The supporting bracket (702) is provided on one side of the mounting block (701), and the rotating motor (705) is provided on the other side of the mounting block (701).

7. The on-site test device for measuring thrust of aerospace engines 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 on one end of the hydraulic telescopic rod (703), wherein the clamping fixture (704) is made of a non-slip material.

8. A field test device for measuring thrust of an aerospace engine according to claims 1-7, characterized in that: A field test device for measuring thrust of an aerospace engine comprises the following steps when performing thrust testing: S101: First, thrust loading and simulation are performed on the field test device to ensure the normal operation of each component; S102: Thrust measurement and feedback are performed, and thrust simulation data is collected and recorded in real time and feedback is performed.

9. The on-site test device for measuring thrust of an aerospace engine according to claim 8, characterized in that: A field test device for measuring thrust of an aerospace engine comprises the following steps when performing thrust loading and simulation: S201: Check all equipment components such as the engine mounting stand (1), the shock absorbing assembly, the cooling assembly, the fixing assembly, the loading gantry (501), the hydraulic jack (504), the hydraulic cylinder (505), the manual loading pump (506) one by one to ensure that they are installed correctly and are in good working condition; S202: Check whether the connection between the hydraulic cylinder (505), the oil pipe (508) and the hydraulic jack (504) is tight and whether there is any leakage to ensure the integrity and stability of the hydraulic system; S203: Start the cooler (301) in the cooling assembly to ensure that the coolant can circulate and provide effective temperature control for subsequent thrust tests; S204: Confirm that all safety structures are in place to ensure safety during testing; S205: By manually loading the pump (506) with appropriate force and frequency to pump, the mechanical energy is converted into hydraulic energy; S206: The hydraulic oil flows into the hydraulic cylinder (505) through the oil pipe (508) under the action of the manual loading pump (506), pushing the piston forward; S207: The piston movement of the hydraulic cylinder (505) is converted into a vertical downward thrust through the hydraulic jack (504), simulating the thrust of the aerospace engine at work; S208: The thrust generated by the hydraulic jack (504) is evenly distributed to the force-bearing surface of the three-way force measuring 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 the loading gantry (501), the protection pad (502) and other components to ensure that they do not shake or move.

10. The on-site test device for measuring thrust of aerospace engines according to claim 8, characterized in that: A field test device for measuring thrust of an aerospace engine comprises the following steps when performing thrust measurement and feedback: S301: When the thrust is applied to the three-way force measuring balance (405), its built-in high-precision thrust detection sensor starts working and converts the mechanical force into an electrical signal; S302: The electrical signal is sent to the data processing system via a data line or wireless transmission for real-time collection and recording; S303: The data processing system performs preliminary processing on the collected raw data, such as filtering, denoising, etc., to improve measurement accuracy; S304: The force indicator light (604) lights up the corresponding indicator light according to the electrical signal transmitted by the standard force sensor (601), visually displaying the current thrust range; S305: The data processing system can also display the real-time thrust data in digital or graphical form on the screen for the test 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 thrust average value, peak value, fluctuation range, etc.; S307: Compare the thrust data in the test report with the design requirements or expected values ​​of the aerospace engine to evaluate whether its thrust performance meets the standards; S308: Based on the comparison results, conduct a comprehensive assessment of the thrust performance of the aerospace engine; S309: If the test results do not meet the design requirements, the tester can make improvement suggestions to provide reference for subsequent R&D work.

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