A device and method for measuring and evaluating thrust of an aircraft engine

Abstract

The invention discloses an aero-engine thrust measurement and evaluation device and method, and relates to the field of power test technology. The device comprises a closed shell buried under the ground, wherein a central axis is rotatably arranged at the central position inside the closed shell, and a magnetic resistance component for limiting the rotation of the central axis and the closed shell is arranged between the central axis and the closed shell, and corresponding resistance can be provided for the rotation of the central axis through the magnetic resistance component. A sealing cover is arranged at the upper end of the closed shell, and the sealing cover corresponds to the surface position, and a movable opening corresponding to the aircraft is arranged on the surface of the sealing cover. The present application is designed to address the deficiencies of the existing device, simplifies the way of fixing the aircraft, and enables the aircraft test to be in a relatively safe environment, and can also simulate the gas concentration and temperature at high altitude, thereby providing a more reliable test environment and improving the test accuracy.

Description

Technical Field

[0001] The present invention relates to the technical field of power testing, and in particular to a device and method for measuring and evaluating the thrust of an aero-engine. Background Art

[0002] The installation thrust test of aircraft engines plays an indispensable role in ensuring the normal flight of aircraft. At present, domestic thrust tests are mainly measured when the aircraft engines are not installed. There is a large difference between the thrust measured at this time and the thrust after installation. In order to ensure that the aircraft can fly safely and efficiently, and quickly repair faults that occur during flight, accurate thrust measurement data is indispensable. In response to this problem, the existing patent announcement number CN113218552B discloses a test device, which can not only ensure that the engine can be tested after installation, but also simplify the current complicated test system to quickly test the real-time installation thrust of the engine. However, when testing here, the bottom of the aircraft needs to be limited, and the aircraft is used to pull the spring for testing. Here, it can be found that the aircraft needs to be guided in one direction during the test. This kind of flight has huge power. If the spring breaks, it is easy to cause a safety accident. And after the test spring is stretched, when the vitality stops, the spring will reset again. Such a strong reset force will cause the flight to be pulled backward, and there are certain safety hazards.

[0003] Based on this, a device and method for measuring and evaluating the thrust of an aircraft engine is now provided, which can eliminate the drawbacks of existing devices. Summary of the invention

[0004] The purpose of the present invention is to provide an aircraft engine thrust measurement and evaluation device and method to solve the problems in the background technology.

[0005] To achieve the above object, the present invention provides the following technical solutions:

[0006] An aircraft engine thrust measurement and evaluation device comprises a closed shell buried under the ground, a central axis is rotatably arranged at the center position of the closed shell, a magnetic resistance component for limiting the rotation of the central axis and the closed shell is arranged between the central axis and the closed shell, and corresponding resistance can be provided for the rotation of the central axis through the magnetic resistance component, a sealing cover is arranged at the upper end of the closed shell for blocking, the sealing cover corresponds to the surface position, a movable opening corresponding to the aircraft is arranged on the surface of the sealing cover, and a door opening component is matched at the position of the movable opening, and a regulating component for adjusting the oxygen concentration inside the closed shell is arranged on the closed shell, because the aircraft is suspended at a high altitude during actual flight, and the oxygen concentration at high altitude is not the same, the higher the oxygen concentration is, the smaller the oxygen concentration is, and an oxygen sensor for detecting the oxygen inside the closed shell and a thermometer for detecting the temperature are also arranged inside the closed shell, and the magnetic resistance component, the regulating component, the oxygen sensor and the thermometer are electrically connected to the control panel;

[0007] The upper end of the central axis is connected to a horizontally arranged load-bearing cross plate through a connecting piece. Support wheels matching the bottom of the closed shell are provided at both ends of the load-bearing cross plate, so that the load-bearing cross plate can rotate smoothly in the closed shell. A positioning component for fixing the aircraft to be tested is provided at the upper end of the load-bearing cross plate. The positioning component can quickly fix the aircraft to be tested, thereby improving the test efficiency.

[0008] On the basis of the above technical solution, the present invention also provides the following optional technical solution:

[0009] In an optional solution: the positioning component includes a horizontally arranged positioning platform, and the positioning platform is connected to a lifting unit for driving the upward and downward movement thereof. The lifting unit can be used to lift the aircraft to the cover surface, so as to facilitate the sending out and sending in of the aircraft. Two identification columns are also provided on both sides of the upper end of the positioning platform, and a positioning unit for fixing the aircraft is also provided on the upper end of the positioning platform.

[0010] In an optional solution: the positioning unit includes two mounting base plates arranged near the two identification columns, each mounting base plate is provided with two transverse push rods, the output ends of the transverse push rods are connected to the clamping push rods, the clamping surfaces of the two clamping push rods are provided with clamping grooves corresponding to the bottom positioning strips of the aircraft, and multiple transverse guide rods are also provided on the outer side of the clamping push rods, and each transverse guide rod is slidably set with the transverse guide sleeve on the mounting base plate.

[0011] In an optional solution: the lifting unit includes two lifting push rods arranged on the upper end of the bearing cross plate, the upper ends of the lifting push rods are connected and fixed to the bottom of the positioning platform, and a plurality of lifting guide rods are arranged on the outside of the positioning platform, and the lower end of each lifting guide rod is slidably arranged with a lifting guide sleeve, and the lower end of the lifting guide sleeve is connected to the bearing cross plate.

[0012] In an optional solution: the connecting member includes a rotating arm connected to the upper end of the central axis, and a vertical connecting plate is provided on the other side of the rotating arm and is slidably arranged with the surface of the isolation ring, and reinforcing ribs are also provided between the exhaust buffer box and the rotating arm.

[0013] In an optional solution: the other end of the bearing transverse plate is slidably arranged with the inner wall of the closed shell, and the end of the bearing transverse plate is provided with a pressing wheel corresponding to the inner wall of the closed shell.

[0014] In an optional scheme: the regulating component includes an air supply loop arranged on the outside of the closed shell, the air supply loop and the closed shell are connected by multiple air vents, the air inlet end of the air supply loop is connected to the circulating air pump through the oxygen supply pipeline, the air exhaust end of the circulating air pump is connected to the exhaust buffer box through a connecting pipe, the exhaust buffer box is connected to the exhaust port on the top of the cover, the exhaust buffer box is connected to an oxygen cylinder group and a nitrogen cylinder group for providing oxygen and nitrogen, and the regulating component also includes an air conditioning unit arranged on the outside of the closed shell.

[0015] In an optional solution: the door opening assembly includes a movable sealing plate slidably arranged at the movable opening position, and one side of the movable sealing plate is connected to a transverse pushing rod for driving the movable sealing plate to move transversely.

[0016] In an optional solution: the magnetic resistance component includes a movable magnetic block arranged outside the central axis, and a plurality of fixed magnetic blocks are distributed in an array outside the movable magnetic block. The fixed magnetic block is an electromagnet, and an isolation ring is provided inside the closed shell outside the fixed magnetic block, and the outside of the isolation ring is wrapped with iron sheet.

[0017] Compared with the prior art, the present invention has the following beneficial effects:

[0018] 1. This application is designed to address the deficiencies of existing devices, simplify the way to fix the aircraft, and make the aircraft test in a relatively safe environment. It can also simulate the gas concentration and temperature at high altitude, thereby providing a more reliable test environment and improving the test accuracy.

[0019] 2. The resistance in this application can be adjusted in real time as needed to meet the testing requirements of different engine models. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a structural schematic diagram of the present invention.

[0021] Figure 2 It is a schematic diagram of the internal structure of the present invention.

[0022] Figure 3 It is a schematic diagram of the structure of the positioning component of the present invention.

[0023] Figure 4It is a schematic diagram of the lower structure of the positioning platform of the present invention.

[0024] Notes on figure marks: closed shell 11, air supply ring 12, connecting pipe 13, oxygen supply pipeline 14, circulating air pump 15, transverse push rod 16, exhaust buffer box 17, cover 18, movable cover plate 19, rotating arm 20, fixed magnetic block 21, movable magnetic block 22, isolation ring 23, support wheel 24, load-bearing cross plate 25, positioning component 26, vertical connecting plate 27, positioning platform 28, lifting push rod 29, identification column 30, pressing push rod 31, transverse guide rod 32, transverse push rod 33, transverse guide sleeve 34, mounting base plate 36, lifting guide rod 37, lifting guide sleeve 38. DETAILED DESCRIPTION

[0025] In order to make the purpose, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments.

[0026] In one embodiment, Figure 1-Figure 4 As shown, an aircraft engine thrust measurement and evaluation device includes a closed shell 11 buried below the ground, a central axis is rotatably arranged at the center position inside the closed shell 11, a magnetic resistance component for limiting the rotation of the central axis and the closed shell 11 is arranged, and the magnetic resistance component can provide corresponding resistance for the rotation of the central axis, so that aircraft with different power can rotate around the central axis at a uniform speed, so as to test their propulsion force. During the test here, the aircraft is in a state of motion as a whole, and the test accuracy is higher. A sealing cover 18 for blocking is provided at the upper end of the closed shell 11, and the sealing cover 18 corresponds to the surface position. In order to smoothly transport the aircraft to its surface, the surface of the cover 18 is provided with an active opening corresponding to the aircraft, and the position of the active opening is matched with a door opening component. The closed shell 11 is provided with a control component for adjusting the oxygen concentration inside it. Since the aircraft is suspended at a high altitude during actual flight, and the oxygen concentration at high altitude is not the same, the higher the oxygen concentration, the lower the oxygen concentration. At this time, the oxygen supply of the aircraft's combustion will inevitably be affected, thereby affecting the power of the aircraft. The closed shell 11 is also provided with an oxygen sensor for detecting the oxygen inside it and a thermometer for detecting the temperature. The temperature at different altitudes is also different, and different temperatures also affect the efficiency of combustion;

[0027] The upper end of the central axis is connected to a horizontally arranged load-bearing horizontal plate 25 through a connecting piece. Support wheels 24 matching the inner bottom of the closed shell 11 are provided at both ends of the load-bearing horizontal plate 25, so that the load-bearing horizontal plate 25 can rotate smoothly in the closed shell 11. A positioning component 26 for fixing the aircraft to be tested is provided at the upper end of the load-bearing horizontal plate 25. The positioning component 26 can quickly fix the aircraft to be tested, thereby improving the test efficiency.

[0028] The positioning component 26 includes a horizontally arranged positioning platform 28, and the positioning platform 28 is connected to a lifting unit for driving the positioning platform 28 to move up and down. The lifting unit can lift the aircraft to the surface of the cover 18, so as to facilitate the sending of the aircraft in and out. Two identification columns 30 are also arranged on both sides of the upper end of the positioning platform 28. The arrangement of the identification columns 30 provides a reference for moving the aircraft. When the aircraft is actually moved, it only needs to be moved between the two identification columns 30. A positioning unit for fixing the aircraft is also arranged on the upper end of the positioning platform 28. When the aircraft moves between the two identification columns 30, the positioning unit can quickly fix the aircraft.

[0029] The positioning unit includes two mounting base plates 36 arranged near the two identification columns 30, each mounting base plate 36 is provided with two transverse push rods 33, the output end of the transverse push rod 33 is connected to the pressing push rod 31, the clamping surfaces of the two pressing push rods 31 are provided with clamping grooves corresponding to the positioning strips at the bottom of the aircraft, and the outer side of the pressing push rod 31 is also provided with a plurality of transverse guide rods 32, each transverse guide rod 32 is slidably arranged with a transverse guide sleeve 34 on the mounting base plate 36, so that the two pressing push rods 31 can be driven to approach each other by the transverse push rod 33, thereby completing the rapid positioning of the aircraft;

[0030] The lifting unit includes two lifting push rods 29 arranged at the upper end of the bearing cross plate 25, the upper ends of the lifting push rods 29 are connected and fixed to the bottom of the positioning platform 28, and a plurality of lifting guide rods 37 are arranged on the outer side of the positioning platform 28, and the lower end of each lifting guide rod 37 is slidably arranged with a lifting guide sleeve 38, and the lower end of the lifting guide sleeve 38 is connected to the bearing cross plate 25, so that the lifting push rods 29 can generate a driving force on the positioning platform 28, so that the positioning platform 28 slides up and down along the lifting guide rods 37 and the lifting guide sleeve 38, thereby adjusting the height of the aircraft;

[0031] The connecting member includes a rotating arm 20 connected to the upper end of the central shaft, and a vertical connecting plate 27 is provided on the other side of the rotating arm 20 and is slidably arranged on the surface of the isolation ring 23. A reinforcing rib is also provided between the exhaust buffer box 17 and the rotating arm 20 to further improve the mechanical properties, so that the bearing cross plate 25 can be connected to the central shaft;

[0032] The other end of the bearing transverse plate 25 is slidably arranged with the inner wall of the closed shell 11, and the end of the bearing transverse plate 25 is provided with a pressing wheel corresponding to the inner wall of the closed shell 11, so that the bearing transverse plate 25 can rotate smoothly;

[0033] The regulating component includes an air supply loop 12 arranged on the outside of the closed shell 11, the air supply loop 12 and the closed shell 11 are connected through a plurality of vents, the air inlet end of the air supply loop 12 is connected to a circulating air pump 15 through an oxygen supply pipeline 14, the air extraction end of the circulating air pump 15 is connected to an exhaust buffer box 17 through a connecting pipe 13, the exhaust buffer box 17 is connected to an exhaust port on the top of a cover 18, and the exhaust buffer box 17 is connected to an oxygen cylinder group and a nitrogen cylinder group for providing oxygen and nitrogen, so that the oxygen concentration inside the closed shell 11 can be adjusted according to the test needs to correspond to the gas density at different altitudes;

[0034] The control component also includes an air conditioning unit disposed outside the closed housing 11, through which the temperature inside the closed housing 11 can be set to a target value, so that it can be more closely matched to the external environment;

[0035] The door opening assembly includes a movable sealing plate 19 slidably arranged at the movable opening position, one side of the movable sealing plate 19 is connected to a transverse push rod 16 for driving the movable sealing plate 19 to move transversely, and the transverse push rod 16 drives the movable sealing plate 19 to slide on the surface of the cover 18, so that the entire test environment is in a relatively closed state;

[0036] The magnetic resistance component includes an active magnetic block 22 arranged on the outside of the central axis, and a plurality of fixed magnetic blocks 21 are distributed in an array outside the active magnetic block 22. The fixed magnetic block 21 is an electromagnet. By energizing the fixed magnetic block 21, a corresponding resistance is generated between the active magnetic block 22 and the fixed magnetic block 21, which is suitable for testing different engine power. An isolation ring 23 is provided inside the closed shell 11 outside the fixed magnetic block 21. The outside of the isolation ring 23 is wrapped with iron sheet to isolate the influence of magnetic force on the aircraft.

[0037] The above embodiment discloses an aircraft engine thrust measurement and evaluation device, wherein, in actual use, the movable sealing plate 19 is first removed by the door opening assembly, and then the positioning platform 28 is sent out from the inside of the closed shell 11 by the lifting unit, so that the positioning platform 28 is flush with the surface of the cover 18, and then the approximate position is determined by the identification column 30, and the aircraft is transferred to the positioning platform 28 by a tractor, and then the aircraft is quickly positioned by the positioning unit. After the positioning is completed, the aircraft is sent into the closed shell 11 by the lifting unit, and then the opening on the cover 18 is sealed by the movable sealing plate 19, and then the oxygen concentration and temperature inside the closed shell 11 are adjusted according to requirements by the control assembly, and then the resistance value of the magnetic assembly is set, and then the aircraft is started, so that the power generated by the aircraft can drive the load-bearing cross plate 25 to rotate, and then the thrust of the engine is calculated based on the resistance and the length of the lever arm.

[0038] The above is only a specific implementation of the present disclosure, but the protection scope of the present disclosure is not limited thereto. Any person skilled in the art who is familiar with the technical field can easily think of changes or substitutions within the technical scope disclosed in the present disclosure, which should be included in the protection scope of the present disclosure. Therefore, the protection scope of the present disclosure should be based on the protection scope of the claims.

Claims

1. An aircraft engine thrust measurement and evaluation device, comprising a closed housing (11) buried below the ground, wherein a central axis is rotatably arranged at the central position of the closed housing (11), characterized in that: A magnetic resistance component for limiting the rotation of the central axis and the closed shell (11) is provided between the central axis and the closed shell (11), and the magnetic resistance component can provide corresponding resistance for the rotation of the central axis. A sealing cover (18) is provided at the upper end of the closed shell (11) for blocking, and the sealing cover (18) corresponds to the position on the ground. A movable opening corresponding to the aircraft is provided on the surface of the sealing cover (18), and a door opening component is matched at the position of the movable opening. A regulating component for adjusting the oxygen concentration inside the closed shell (11) is provided. An oxygen sensor for detecting the oxygen inside the closed shell (11) and a thermometer for detecting the temperature are also provided inside the closed shell (11). The magnetic resistance component, the regulating component, the oxygen sensor and the thermometer are electrically connected to the control panel. The upper end of the central axis is connected to a horizontally arranged load-bearing transverse plate (25) through a connecting piece, and support wheels (24) matching the inner bottom of the closed shell (11) are provided at both ends of the load-bearing transverse plate (25), and a positioning component (26) for fixing the aircraft to be tested is provided at the upper end of the load-bearing transverse plate (25).

2. The aircraft engine thrust measurement and evaluation device according to claim 1, characterized in that: The positioning component (26) comprises a horizontally arranged positioning platform (28), the positioning platform (28) being connected to a lifting unit for driving the positioning platform (28) to move up and down, and the lifting unit can be used to lift the aircraft to the surface of the cover (18), so as to facilitate the sending out and sending in of the aircraft, and two identification columns (30) are also arranged on both sides of the upper end of the positioning platform (28), and the upper end of the positioning platform (28) is also provided with a positioning unit for fixing the aircraft.

3. The aircraft engine thrust measurement and evaluation device according to claim 2, characterized in that: The positioning unit comprises two mounting base plates (36) arranged near two identification columns (30), each mounting base plate (36) is provided with two transverse push rods (33), the output ends of the transverse push rods (33) are connected to the pressing push rods (31), the clamping surfaces of the two pressing push rods (31) are provided with clamping grooves corresponding to the positioning strips at the bottom of the aircraft, and the outer sides of the pressing push rods (31) are also provided with a plurality of transverse guide rods (32), each transverse guide rod (32) is slidably arranged with a transverse guide sleeve (34) on the mounting base plate (36).

4. The aircraft engine thrust measurement and evaluation device according to claim 2, characterized in that: The lifting unit comprises two lifting push rods (29) arranged at the upper end of the bearing transverse plate (25), the upper ends of the lifting push rods (29) are connected and fixed to the bottom of the positioning platform (28), and a plurality of lifting guide rods (37) are arranged on the outer side of the positioning platform (28), and the lower end of each lifting guide rod (37) is slidably arranged with a lifting guide sleeve (38), and the lower end of the lifting guide sleeve (38) is connected to the bearing transverse plate (25).

5. The aircraft engine thrust measurement and evaluation device according to claim 1, characterized in that: The connecting member comprises a rotating arm (20) connected to the upper end of the central axis, and a vertical connecting plate (27) is provided on the other side of the rotating arm (20) and is slidably arranged on the surface of the isolation ring (23), and reinforcing ribs are also provided between the exhaust buffer box (17) and the rotating arm (20).

6. The aircraft engine thrust measurement and evaluation device according to claim 5, characterized in that: The other end of the bearing transverse plate (25) is slidably arranged with the inner wall of the closed shell (11), and a pressing wheel corresponding to the inner wall of the closed shell (11) is provided at the end of the bearing transverse plate (25).

7. The aircraft engine thrust measurement and evaluation device according to claim 1, characterized in that: The regulating component includes an air supply loop (12) arranged on the outside of the closed shell (11), and the air supply loop (12) and the closed shell (11) are connected through a plurality of vents. The air inlet end of the air supply loop (12) is connected to a circulating air pump (15) through an oxygen supply pipeline (14), and the air extraction end of the circulating air pump (15) is connected to an exhaust buffer box (17) through a connecting pipe (13). The exhaust buffer box (17) is connected to an exhaust port on the top of a sealing cover (18), and the exhaust buffer box (17) is connected to an oxygen cylinder group and a nitrogen cylinder group for providing oxygen and nitrogen. The regulating component also includes an air conditioning unit arranged on the outside of the closed shell (11).

8. The aircraft engine thrust measurement and evaluation device according to claim 1, characterized in that: The door opening assembly comprises a movable sealing plate (19) slidably arranged at the movable opening position, and one side of the movable sealing plate (19) is connected to a transverse pushing rod (16) for driving the movable sealing plate (19) to move transversely.

9. The aircraft engine thrust measurement and evaluation device according to claim 1, characterized in that: The magnetic resistance component comprises a movable magnetic block (22) arranged outside the central axis, a plurality of fixed magnetic blocks (21) are distributed in an array outside the movable magnetic block (22), the fixed magnetic block (21) is an electromagnet, an isolation ring (23) is provided inside the closed shell (11) outside the fixed magnetic block (21), and the outside of the isolation ring (23) is wrapped with iron sheet.

10. An evaluation method for the aircraft engine thrust measurement evaluation device according to any one of claims 1 to 9, characterized in that: The following steps are involved: Step 1: first, the movable sealing plate (19) is removed by the door opening assembly, and then the positioning platform (28) is sent out from the inside of the closed housing (11) by the lifting unit, so that the positioning platform (28) is flush with the surface of the sealing cover (18); Step 2: The aircraft is transferred to the positioning platform (28) by a tractor, and then the positioning unit is used to quickly position the aircraft. After the positioning is completed, the aircraft is sent into the closed housing (11) by the lifting unit, and then the opening of the cover (18) is blocked by the movable sealing plate (19); Step 3: Use the control component to adjust the oxygen concentration and temperature inside the closed shell (11) as required, then set the resistance value of the magnetic component, and then start the aircraft so that the power generated by the aircraft can drive the load-bearing cross plate (25) to rotate, and then calculate the thrust of the engine based on the resistance and the length of the lever arm.

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