Aircraft rotor testing equipment

Abstract

This application relates to an aircraft rotor testing device. The aircraft rotor testing device includes: a test bench and an upper rotor testing device and a lower rotor testing device respectively mounted on the test bench; the upper rotor testing device includes an upper rotor drive component, a first force sensor, and a first torque sensor. The upper rotor drive component drives the upper test rotor to rotate, the first force sensor measures the tension on the upper test rotor, and the first torque sensor measures the torque experienced by the upper test rotor during rotation; the lower rotor testing device includes a lower rotor drive component, a second force sensor, and a second torque sensor. The lower rotor drive component drives the lower test rotor to rotate, the second force sensor measures the tension on the lower test rotor, and the second torque sensor measures the torque experienced by the lower test rotor during rotation. The solution provided by this application can simultaneously test two rotors arranged vertically.

Description

Technical Field

[0001] This application relates to the field of aircraft testing technology, and in particular to an aircraft rotor testing device. Background Technology

[0002] The rotor is a critical component of an aircraft, providing lift and enabling flight. Its performance directly determines the aircraft's performance and reliability, thus requiring testing. Current rotor testing equipment typically tests only a single rotor. However, in actual flight, for redundancy, safety, and efficiency, two sets of rotors are often used to support flight maneuvers. Existing rotor test benches only test individual rotors without considering the inter-rotor interactions, failing to reflect actual flight conditions and resulting in significant errors in the test data. Summary of the Invention

[0003] To address or partially address the problems existing in the related technologies, this application provides an aircraft rotor testing device capable of simultaneously testing two rotors arranged vertically.

[0004] This application provides an aircraft rotor testing device, comprising: a test bench and an upper rotor testing device and a lower rotor testing device respectively disposed on the test bench; the upper rotor testing device includes an upper rotor drive component, a first force sensor and a first torque sensor, the upper rotor drive component is used to drive the upper test rotor to rotate, the first force sensor is used to test the tension force on the upper test rotor, and the first torque sensor is used to test the torque on the upper test rotor when it rotates; the lower rotor testing device includes a lower rotor drive component, a second force sensor and a second torque sensor, the lower rotor drive component is used to drive the lower test rotor to rotate, the lower test rotor is disposed vertically opposite to the upper test rotor, the second force sensor is used to test the tension force on the lower test rotor, and the second torque sensor is used to test the torque on the lower test rotor when it rotates.

[0005] The technical solution provided in this application may include the following beneficial effects: by setting the upper test rotor on the upper rotor test device and the lower test rotor on the lower rotor test device vertically, when driving the upper test rotor and the lower test rotor to rotate, the tension and torque on the upper test rotor can be measured by the first force sensor and the first torque sensor, and the tension and torque on the lower test rotor can be measured by the second force sensor and the second torque sensor. Therefore, the force test of the vertically arranged dual rotors can be performed simultaneously.

[0006] It should be understood that the above general description and the following detailed description are exemplary and explanatory only, and do not limit this application. Attached Figure Description

[0007] The above and other objects, features and advantages of this application will become more apparent from the more detailed description of exemplary embodiments thereof in conjunction with the accompanying drawings, wherein the same reference numerals generally represent the same components in the exemplary embodiments thereof.

[0008] Figure 1 This is a schematic diagram of the structure of the aircraft rotor testing equipment shown in the embodiments of this application;

[0009] Figure 1a This is another structural schematic diagram of the aircraft rotor testing equipment shown in the embodiments of this application;

[0010] Figure 1b This is another structural schematic diagram of the aircraft rotor testing equipment shown in the embodiments of this application;

[0011] Figure 2 This is a schematic diagram of the structure of the upper rotor testing device shown in the embodiments of this application;

[0012] Figure 3 This is an assembly diagram of the first upper mounting plate and the first lower mounting plate shown in an embodiment of this application;

[0013] Figure 4 This is a schematic diagram of the structure of the lower rotor testing device shown in the embodiments of this application;

[0014] Figure 5 This is another structural schematic diagram of the lower rotor testing device shown in the embodiments of this application, in which the lower rotor mounting base is hidden;

[0015] Figure 6 This is a schematic diagram of the structure of the lower rotor mounting base shown in the embodiments of this application;

[0016] Figure 7 This is an assembly diagram of the second upper mounting plate and the second lower mounting plate shown in an embodiment of this application.

[0017] Figure label:

[0018] 1-Test stand, 11-Upper rotor mounting stand, 111-Crossbeam, 112-Side bracket, 113-Beam mounting plate, 12-Lower rotor mounting stand;

[0019] 2-Upper rotor testing device, 21-Upper test rotor, 22-Upper rotor base, 23-Upper drive component mounting seat, 24-Upper torque sensor mounting seat, 25-First force sensor, 26-Upper rotor drive component, 27-First torque sensor, 28-First guide rod, 29-First upper mounting plate, 210-First lower mounting plate, 220-First connecting plate, 230-Upper rotor mounting flange, 240-First coupling, 250-Locking plate, 260-Second connecting plate, 270-Third connecting plate;

[0020] 3-Lower rotor testing device, 31-Lower test rotor, 32-Force sensor mounting base, 321-Second upper mounting plate, 322-Second lower mounting plate, 323-Fourth connecting plate, 33-Lower rotor mounting base, 331-Slide groove, 332-Through hole, 34-Lower drive component mounting base, 35-Lower torque sensor mounting base, 36-Second force sensor, 37-Lower rotor drive component, 38-Second torque sensor, 39-Lifting mechanism, 391-Lifting motor, 392-Lifting rod, 310-Modible base, 320-Lower rotor mounting flange, 330-Second coupling, 340-Protrusion, 350-Third guide rod, 360-Linear guide rail, 370-Slider;

[0021] 4- Upper motor controller;

[0022] 5- Lower motor controller. Detailed Implementation

[0023] Embodiments of this application will now be described in more detail with reference to the accompanying drawings. While embodiments of this application are shown in the drawings, it should be understood that this application may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided to make this application more thorough and complete, and to fully convey the scope of this application to those skilled in the art.

[0024] It should be understood that although the terms "first," "second," "third," etc., may be used in this application to describe various information, this information should not be limited to these terms. These terms are only used to distinguish information of the same type from one another. For example, without departing from the scope of this application, first information may also be referred to as second information, and similarly, second information may also be referred to as first information. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this application, "multiple" means two or more, unless otherwise explicitly specified.

[0025] In the description of this application, it should be understood that the terms "length", "width", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this application.

[0026] Unless otherwise expressly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0027] The rotor is a critical component of an aircraft, providing lift and enabling flight. Its performance directly determines the aircraft's performance and reliability, thus requiring testing. Current rotor testing equipment typically tests only a single rotor. However, in actual flight, for redundancy, safety, and efficiency, two sets of rotors are often used to support flight maneuvers. Existing rotor test benches only test individual rotors without considering the inter-rotor interactions, failing to reflect actual flight conditions and resulting in significant errors in the test data.

[0028] To address the aforementioned issues, this application provides an aircraft rotor testing device capable of simultaneously testing two rotors arranged vertically.

[0029] The technical solutions of the embodiments of this application are described in detail below with reference to the accompanying drawings.

[0030] like Figures 1 to 5 As shown, this application provides an aircraft rotor testing device, including a test bench 1 and an upper rotor testing device 2 and a lower rotor testing device 3 respectively mounted on the test bench 1.

[0031] The upper rotor testing device 2 includes an upper rotor drive 26, a first force sensor 25, and a first torque sensor 27. The upper rotor drive 26 is used to drive the upper test rotor 21 to rotate, the first force sensor 25 is used to test the tension on the upper test rotor 21, and the first torque sensor 27 is used to test the torque when the upper test rotor 21 rotates.

[0032] The lower rotor testing device 3 includes a lower rotor drive 37, a second force sensor 36, and a second torque sensor 38. The lower rotor drive 37 is used to drive the lower test rotor 31 to rotate. The lower test rotor 31 is arranged vertically opposite to the upper test rotor 21. The second force sensor 36 is used to test the tension on the lower test rotor 31, and the second torque sensor 38 is used to test the torque on the lower test rotor 31 when it rotates.

[0033] By arranging the upper test rotor 21 of the upper rotor test device 2 and the lower test rotor 31 of the lower rotor test device 3 vertically, when the upper test rotor 21 and the lower test rotor 31 are driven to rotate, the tension and torque on the upper test rotor 21 can be measured by the first force sensor 25 and the first torque sensor 27, and the tension and torque on the lower test rotor 31 can be measured by the second force sensor 36 and the second torque sensor 38. Therefore, the forces on the vertically arranged dual rotors can be tested simultaneously to test the effects of rotor rotation.

[0034] Specifically, both the first force sensor 25 and the second force sensor 36 are tension and compression sensors. During detection, the airflow generated by the rotation of the upper test rotor 21 and the lower test rotor 31 is downward, and the upper test rotor 21 and the lower test rotor 31 are subjected to upward tension respectively. Both the upper rotor drive component 26 and the lower rotor drive component 37 are motors.

[0035] In some embodiments, during testing, only one test rotor may be driven to rotate to verify the force situation when a single rotor rotates. For example, when only the upper test rotor 21 is tested, the lower test rotor 31 may be mounted on the lower rotor testing device 3, but the lower test rotor 31 may not be driven to rotate, or as... Figure 1a As shown, the lower test rotor 31 is not mounted on the lower rotor test device 3. When only the lower test rotor 31 is tested, the upper test rotor 21 can be mounted on the upper rotor test device 2, but the upper test rotor 21 is not driven to rotate, or as shown... Figure 1b As shown, the upper test rotor 21 is not installed on the upper rotor test device 2.

[0036] In one embodiment, such as Figure 2 As shown, the upper rotor testing device 2 also includes an upper rotor base 22, an upper drive component mounting base 23, and an upper torque sensor mounting base 24 arranged sequentially from top to bottom. The upper rotor base 22 is fixedly connected to the test bench 1. The first force sensor 25 is connected between the upper rotor base 22 and the upper drive component mounting base 23. The upper drive component mounting base 23 can move up and down relative to the upper rotor base 22. The upper rotor drive component 26 is located on the upper drive component mounting base 23. The first torque sensor 27 is located on the upper torque sensor mounting base 24. The output end of the upper rotor drive component 26 is connected to the upper test rotor 21 through the first torque sensor 27.

[0037] Specifically, when the upper test rotor 21 rotates, it is subjected to an upward force, which is transmitted from the upper test rotor 21 to the upper drive component mounting base 23 via the first torque sensor 27 and the upper rotor drive component 26. This causes the upper drive component mounting base 23 to move upward relative to the upper rotor base 22 and press against the first force sensor 25. The first force sensor 25 detects the tension value of the upper test rotor 21. At the same time, the first torque sensor 27 can measure the torque generated by the rotation of the upper test rotor 21, providing a reference for the design. The upper end of the rotating shaft of the first torque sensor 27 is connected to the output shaft of the upper rotor drive 26 through the first coupling 240, and the lower end of the rotating shaft of the first torque sensor 27 is connected to the upper test rotor 21 through the upper rotor mounting flange 230. The first torque sensor 27 is fixedly connected to the upper torque sensor mounting base 24, the upper rotor drive 26 is fixedly connected to the upper drive component mounting base 23, the lower end of the upper drive component mounting base 23 is fixedly connected to the upper end of the upper torque sensor mounting base 24, the upper end of the upper drive component mounting base 23 is slidably connected to the lower end of the upper rotor base 22 in the longitudinal direction, and the upper end of the upper rotor base 22 is fixedly connected to the test bench 1.

[0038] In one embodiment, a first guide rod 28 is provided between the upper rotor base 22 and the upper drive component mounting seat 23. The first guide rod 28 is used to guide the upper drive component mounting seat 23 when it moves up and down relative to the upper rotor base 22. Specifically, the upper end of the first guide rod 28 can be fixedly connected to the upper rotor base 22, and the lower end of the first guide rod 28 is slidably connected to the upper drive component mounting seat 23. The upper drive component mounting seat 23 can slide up and down along the first guide rod 28 to compress the first force sensor 25.

[0039] In one embodiment, such as Figure 2 and Figure 3 As shown, the upper rotor testing device 2 also includes a first upper mounting plate 29 and a first lower mounting plate 210. The first upper mounting plate 29 is fixedly connected to the lower end of the upper rotor base 22, and the first lower mounting plate 210 is fixedly connected to the upper end of the upper drive component mounting seat 23. The first force sensor 25 is connected between the first upper mounting plate 29 and the first lower mounting plate 210. The first upper mounting plate 29 and the first lower mounting plate 210 are respectively provided with openings to facilitate the installation of the first force sensor 25.

[0040] Specifically, the openings on the first upper mounting plate 29 and the first lower mounting plate 210 are rectangular, positioned relative to the first force sensor 25. These rectangular openings facilitate the adjustment and installation of the first force sensor 25. For example... Figure 3As shown, the first upper mounting plate 29 is connected to the upper rotor base 22 via a first connecting plate 220. There are two first connecting plates 220, positioned opposite each other on both sides of the first upper mounting plate 29. The first lower mounting plate 210 is connected to the upper drive component mounting base 23 via a second connecting plate 260 and a third connecting plate 270. There are two second connecting plates 260 and two third connecting plates 270. The two second connecting plates 260 are positioned opposite each other on the front and rear sides of the first lower mounting plate 210, and the two third connecting plates 270 are positioned opposite each other on the left and right sides of the first lower mounting plate 210. During installation, the first force sensor 25 can be first assembled between the first upper mounting plate 29 and the first lower mounting plate 210, and then the assembled unit can be installed between the upper rotor base 22 and the upper drive component mounting base 23 for easier assembly.

[0041] In one embodiment, such as Figure 2 and Figure 3 As shown, the upper rotor testing device 2 also includes a locking plate 250, which is used to limit the distance that the upper drive component mounting base 23 moves relative to the upper rotor base 22. One end of the locking plate 250 is fixedly connected to the upper rotor base 22, and the other end is slidably connected to the upper drive component mounting base 23.

[0042] Specifically, the upper end of the locking plate 250 is fixed to the first connecting plate 220, and then fixedly connected to the upper rotor base 22. The lower end of the locking plate 250 is provided with an elongated hole. The bolt provided on the third connecting plate 270 passes through the elongated hole. The upper drive component mounting seat 23 can drive the bolt to move up and down in the elongated hole through the third connecting plate 270, and move from one end of the elongated hole to the other end. The upper and lower ends of the elongated hole restrict the range of movement of the upper drive component mounting seat 23.

[0043] In some embodiments, one end of the locking plate 250 can be slidably connected to the upper rotor base 22, and the other end of the locking plate 250 can be fixedly connected to the upper drive component mounting seat 23, which can also limit the range of vertical movement of the upper drive component mounting seat 23.

[0044] In one embodiment, such as Figure 4 and Figure 5 As shown, the lower rotor testing device 3 also includes a lower rotor mounting base 33, a lower drive component mounting base 34, a lower torque sensor mounting base 35, and a force sensor mounting base 32. The force sensor mounting base 32 is mounted on the test bench 1, and the second force sensor 36 is mounted on the force sensor mounting base 32. The lower rotor mounting base 33 is connected to the test bench 1 through the force sensor mounting base 32 and the second force sensor 36.

[0045] The lower drive component mounting base 34 is connected to the lower rotor mounting base 33. The lower rotor drive component 37 is located on the lower drive component mounting base 34. The lower torque sensor mounting base 35 is connected to the lower drive component mounting base 34. The second torque sensor 38 is located on the lower torque sensor mounting base 35. The lower rotor drive component 37 is connected to the lower test rotor 31 through the second torque sensor 38.

[0046] Specifically, during testing, the lower test rotor 31 is subjected to an upward force generated by the airflow, i.e., the lower test rotor 31 is subjected to an upward pull. The pull is transmitted to the second force sensor 36 after passing through the lower test rotor 31, the second torque sensor 38, the lower rotor drive component 37, the lower drive component mounting base 34, and the lower rotor mounting base 33. This causes the lower rotor mounting base 33 to move upward relative to the test bench 1, and stretches the second force sensor 36. The second force sensor 36 thus detects the pull value of the lower test rotor 31. At the same time, the second torque sensor 38 can measure the torque generated by the rotation of the lower test rotor 31, providing a reference for the design. The lower end of the rotating shaft of the second torque sensor 38 is connected to the output shaft of the lower rotor drive 37 through the second coupling 330, and the upper end of the rotating shaft of the second torque sensor 38 is connected to the second rotor blade through the lower rotor mounting flange 320. The second torque sensor 38 is fixedly connected to the lower torque sensor mounting base 35, and the lower rotor drive 37 is fixedly connected to the lower drive mounting base 34. The upper end of the lower drive mounting base 34 is fixedly connected to the lower end of the lower torque sensor mounting base 35.

[0047] In one embodiment, the lower rotor testing device 3 further includes a lifting mechanism 39. The lower drive component mounting base 34 and the lower rotor mounting base 33 are slidably connected in the vertical direction. The lifting mechanism 39 is used to drive the lower drive component mounting base 34 to rise and fall, thereby changing the distance between the lower test rotor 31 and the upper test rotor 21. Specifically, the lifting mechanism 39 drives the lower drive component mounting base 34 to rise and fall to change the height of the lower test rotor 31, thereby enabling the measurement of the force on the dual rotors at different spacings and verifying whether there is propulsion.

[0048] In one embodiment, such as Figures 4 to 6As shown, a movable base 310 is fixedly provided at the lower end of the lower drive component mounting base 34. The movable base 310 is slidably connected to the lower rotor mounting base 33 in the vertical direction. The lifting mechanism 39 is used to drive the movable base 310 to rise and fall. The side wall of the lower rotor mounting base 33 is provided with a sliding groove. The movable base 310 is provided with a protrusion 340, and a third guide rod 350 is provided on the protrusion 340. The third guide rod 350 is located within the sliding groove. When the movable base 310 rises and falls, the third guide rod 350 slides up and down along the sliding groove. The third guide rod 350 cooperates with the sliding groove to guide the movable base 310. A linear guide rail 360 can also be provided on the inner wall of the lower rotor mounting base 33. The movable base 310 is slidably connected to the linear guide rail 360 through a slider 370 to facilitate the sliding of the movable base 310 relative to the lower rotor mounting base 33.

[0049] In one embodiment, the lifting mechanism 39 includes a lifting motor 391 and a lifting rod 392. The lifting motor 391 is used to drive the lifting rod 392 to lift. The lifting motor 391 is connected to the lower rotor mounting base 33, and the lifting rod 392 is connected to the lower drive component mounting base 34.

[0050] Specifically, the lifting rod 392 can be a lead screw. The upper end of the lifting rod 392 passes through the force sensor mounting base 32 and the lower rotor mounting base 33 and is fixedly connected to the movable base 310. The bottom of the lower rotor mounting base 33 is provided with a through hole for the lifting rod 392 to pass through. When the lifting rod 392 is raised or lowered, it drives the lower drive component mounting base 34 to rise or fall through the movable base 310. The tension on the lower test rotor 31 can be transmitted to the lower rotor mounting base 33 through the lifting mechanism 39.

[0051] In one embodiment, the force sensor mounting base 32 includes a second upper mounting plate and a second lower mounting plate. The second lower mounting plate is fixedly connected to the test bench 1. The second force sensor 36 is connected between the second upper mounting plate and the second lower mounting plate. The second upper mounting plate can move up and down relative to the second lower mounting plate. The lower rotor mounting base 33 is connected to the second upper mounting plate.

[0052] Specifically, the tension force on the lower test rotor 31, after passing through the lower rotor mounting base 33 and the second upper mounting plate, acts on the second force sensor 36, where, for example... Figure 6 As shown, the second upper mounting plate and the second lower mounting plate are connected by a fourth connecting plate. The fourth connecting plate is fixedly connected to the second lower mounting plate and movably connected to the second upper mounting plate, meaning the second upper mounting plate can move up and down relative to the fourth connecting plate to pull or compress the second force sensor 36. The lifting motor 391 can be fixedly mounted on the second upper mounting plate. Both the second upper and lower mounting plates have rectangular mounting holes in their middle sections to facilitate the installation of the lifting motor 391. The second upper and lower mounting plates also have rectangular openings relative to the second force sensor 36 to facilitate the installation of the second force sensor 36.

[0053] In one embodiment, such as Figure 1 As shown, the test bench 1 includes an upper rotor mounting bench 11 and a lower rotor mounting bench 12. The upper rotor mounting bench 11 includes a crossbeam 111 and side supports 112 on both sides of the crossbeam 111. The upper rotor testing device 2 is mounted on the crossbeam 111, and the lower rotor testing device 3 is mounted on the lower rotor mounting bench 12. The lower ends of the side supports 112 and the lower rotor mounting bench 12 are fixed to the ground. The two side supports 112 on both sides of the crossbeam 111 are arranged opposite each other. The upper end of the side supports 112 is provided with a beam mounting plate 113, and the end of the crossbeam 111 is fixedly connected to the beam mounting plate 113. An upper motor controller 4 is also provided on the crossbeam 111 to control the rotation of the upper rotor drive component 26. A lower motor controller 5 is provided on the lower rotor mounting bench 12 to control the rotation of the lower rotor drive component 37.

[0054] Optionally, the lower rotor mounting platform 12 is a quadrangular prism with a smaller top and a larger bottom. The lower rotor mounting platform 12 can be a cement platform or a steel platform.

[0055] In the aircraft rotor testing equipment provided in this application embodiment, the pressure and torque on the upper test rotor 21 and the tension and torque on the lower test rotor 31 are tested simultaneously. Weighing can be performed before the test. Assuming the total weight of the upper drive component mounting base 23, upper torque sensor mounting base 24, upper rotor drive component 26, first coupling 240, first torque sensor 27, upper test rotor 21, and upper rotor mounting flange 230 is G1, during the test, the electrical cabinet simultaneously supplies power to the upper motor drive controller and the lower motor drive controller. The upper motor drive controller controls the upper rotor drive component 26 to rotate counterclockwise at 1000 rpm. The shaft of the upper rotor drive component 26 is connected to the first coupling 24. The upper test rotor 21 is driven to rotate counterclockwise. At the same time, the lower motor drive controller controls the lower rotor drive component 37 to rotate clockwise at 1000 rpm. The shaft of the lower rotor drive component 37 drives the lower test rotor 31 to rotate clockwise through the second coupling 330. At this time, the data can be collected by the data acquisition device. The data of the first force sensor 25 and the second force sensor 36 are read as F1 and F2 respectively. The data of the first torque sensor 27 and the second torque sensor 38 are read as T1 and T2 respectively. Then the actual lift generated by the upper test rotor 21 should be F1-G1 and the torque should be T1. The actual lift generated by the lower test rotor 31 should be F2 and the torque should be T2. It should be noted that when the upper test rotor 21 rotates counterclockwise, it generates a downward airflow (i.e., an upward thrust). At this time, the first force sensor 25 reads the upward thrust value. Conversely, when the lower test rotor 31 rotates clockwise, it generates a downward airflow (i.e., an upward thrust). At this time, the second force sensor 36 reads the upward thrust value. After stopping the machine, the height of the upper test rotor 21 can be adjusted via the lifting mechanism 39, changing the distance between the upper and lower test rotors 31. This allows for testing the thrust and torque values ​​at different blade pitches, thus demonstrating the influence of blade pitch on the thrust and torque between the blades. Based on the above principle of testing the thrust and torque of a dual-blade rotor, it is possible to derive separate tests for the upper blade's thrust and torque, as well as separate tests for the lower blade's thrust and torque.

[0056] In summary, the aircraft rotor testing equipment provided in this application has the following advantages:

[0057] 1. It can simultaneously test the tension and torque of the rotor blades of a vertically arranged twin-rotor aircraft.

[0058] 2. Rotor failure involves serious safety issues. This testing equipment can provide a reference for the reliability testing of dual rotor blades and further improve the verification of rotor safety.

[0059] 3. The distance between the two blades can be adjusted, and the blades can be tested for propulsion, which can further provide a basis for design. It does not require the whole machine to be assembled and disassembled every time, saving time, improving efficiency, and reducing costs. Moreover, the testing equipment has a simple structure and is easy to operate.

[0060] The solution of this application has been described in detail above with reference to the accompanying drawings. In the above embodiments, the descriptions of each embodiment have different focuses; for parts not described in detail in a certain embodiment, please refer to the relevant descriptions of other embodiments. Those skilled in the art should also understand that the actions and modules involved in the specification are not necessarily essential to this application. Furthermore, it is understood that the steps in the method of this application embodiment can be adjusted, combined, and deleted according to actual needs, and the modules in the device of this application embodiment can be combined, divided, and deleted according to actual needs.

[0061] The various embodiments of this application have been described above. These descriptions are exemplary and not exhaustive, nor are they limited to the disclosed embodiments. Many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments. The terminology used herein is chosen to best explain the principles, practical application, or improvement of the technology in the market, or to enable others skilled in the art to understand the embodiments disclosed herein.

Claims

1. An aircraft rotor testing apparatus, characterized by, The test device comprises: a test bench and an upper rotor test device and a lower rotor test device arranged on the test bench respectively; the upper rotor test device comprises an upper rotor driving member, a first force sensor and a first torque sensor, the upper rotor driving member is used to drive the upper test rotor to rotate, the first force sensor is used to test the tension of the upper test rotor, and the first torque sensor is used to test the torque of the upper test rotor when rotating; the lower rotor test device comprises a lower rotor driving member, a second force sensor and a second torque sensor, the lower rotor driving member is used to drive the lower test rotor to rotate, the lower test rotor is arranged opposite to the upper test rotor, the second force sensor is used to test the tension of the lower test rotor, and the second torque sensor is used to test the torque of the lower test rotor when rotating; the upper rotor test device further comprises an upper rotor base, an upper driving member mounting seat and an upper torque sensor mounting seat arranged in sequence from top to bottom, the upper rotor base is connected with the test bench, the first force sensor is connected between the upper rotor base and the upper driving member mounting seat, the upper driving member mounting seat can move up and down relative to the upper rotor base, the upper rotor driving member is arranged on the upper driving member mounting seat, the first torque sensor is arranged on the upper torque sensor mounting seat, and the output end of the upper rotor driving member is connected with the upper test rotor through the first torque sensor.

2. The aircraft rotor test device according to claim 1, wherein: a first guide rod is arranged between the upper rotor base and the upper driving member mounting seat, and the first guide rod is used to guide the upper driving member mounting seat when the upper driving member mounting seat moves up and down relative to the upper rotor base.

3. The aircraft rotor test device according to claim 2, wherein: the upper rotor test device further comprises a first upper mounting plate and a first lower mounting plate, the first upper mounting plate is connected with the lower end of the upper rotor base, the first lower mounting plate is connected with the upper end of the upper driving member mounting seat, the first force sensor is connected between the first upper mounting plate and the first lower mounting plate, and the first upper mounting plate and the first lower mounting plate are respectively provided with an opening to facilitate the installation of the first force sensor.

4. The aircraft rotor test device according to claim 1, wherein: the upper rotor test device further comprises a locking plate, the locking plate is used to limit the distance of the movement of the upper driving member mounting seat relative to the upper rotor base; one end of the locking plate is fixedly connected with the upper rotor base, and the other end of the locking plate is slidably connected with the upper driving member mounting seat; or one end of the locking plate is slidably connected with the upper rotor base, and the other end of the locking plate is fixedly connected with the upper driving member mounting seat.

5. The aircraft rotor test device according to claim 1, wherein: The lower rotor testing device further comprises a lower rotor mounting base, a lower driving element mounting base, a lower torque sensor mounting base and a force sensor mounting base, the force sensor mounting base is arranged on the testing bench, the second force sensor is arranged on the force sensor mounting base, and the lower rotor mounting base is connected with the testing bench through the force sensor mounting base and the second force sensor; The lower driving element mounting base is connected with the lower rotor mounting base, the lower rotor driving element is arranged on the lower driving element mounting base, the lower torque sensor mounting base is connected with the lower driving element mounting base, the second torque sensor is arranged on the lower torque sensor mounting base, and the lower rotor driving element is connected with the lower testing rotor through the second torque sensor.

6. The aircraft rotor testing device according to claim 5, characterized in that: The lower rotor testing device further comprises a lifting mechanism, the lower driving element mounting base and the lower rotor mounting base are connected in a sliding mode in the vertical direction, and the lifting mechanism is used to drive the lower driving element mounting base to lift to change the distance between the lower testing rotor and the upper testing rotor.

7. The aircraft rotor testing device according to claim 6, characterized in that: The lifting mechanism comprises a lifting motor and a lifting rod, the lifting motor is used to drive the lifting rod to lift, the lifting motor is connected with the lower rotor mounting base, and the lifting rod is connected with the lower driving element mounting base.

8. The aircraft rotor testing device according to claim 5, characterized in that: The force sensor mounting base comprises a second upper mounting plate and a second lower mounting plate, the second lower mounting plate is connected with the testing bench, the second force sensor is connected between the second upper mounting plate and the second lower mounting plate, the second upper mounting plate can move up and down relative to the second lower mounting plate, and the lower rotor mounting base is connected with the second upper mounting plate.

9. The aircraft rotor testing device according to claim 1, characterized in that: The testing bench comprises an upper rotor mounting bench and a lower rotor mounting bench, the upper rotor mounting bench comprises a cross beam and side supports arranged on both sides of the cross beam, the upper rotor testing device is arranged on the cross beam, and the lower rotor testing device is arranged on the lower rotor mounting bench.

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