Test benches, test devices and test systems for aircraft motor reducers

Abstract

This utility model relates to a test bench, test device, and test system for an aircraft motor reducer. The test bench includes a motor mounting structure and a reducer mounting structure. The motor mounting structure includes a mounting cylinder and a mounting base plate located at one end of the mounting cylinder. The mounting base plate can mount the motor, and the mounting cylinder can surround the outside of the motor. The reducer mounting structure includes a docking cylinder detachably connected to the other end of the mounting cylinder. The end of the docking cylinder away from the mounting cylinder allows the reducer to pass through. The docking cylinder can mount a reducer with a portion located inside and a portion located outside the docking cylinder. The docking cylinder or mounting cylinder has a clearance area, which connects the inside and outside of the docking cylinder or the inside and outside of the mounting cylinder. The clearance area corresponds to the connection area of ​​the motor and the reducer, allowing the motor and reducer to connect at the clearance area. The aircraft test system includes an aircraft test device, which includes the aforementioned test bench, and is capable of conducting ground tests on the motor and reducer.

Description

Technical Field

[0001] This utility model relates to the field of aircraft technology, and in particular to a test bench, test device and test system for an aircraft motor reducer. Background Technology

[0002] With the gradual development of the low-altitude economy, various types of electric vertical takeoff and landing (eVTOL) aircraft are being rapidly developed. Testing methods for eVTOL components also need to be developed accordingly. For example, traditional theoretical calculations and simulations are no longer sufficient for testing eVTOL components such as motors and reducers. Actual testing of these components is necessary; that is, before installation, ground tests of the motors, reducers, and other components are required to ensure the eVTOL functions properly after installation. Utility Model Content

[0003] Therefore, it is necessary to provide a test bench for the motor and reducer of an aircraft that can be used for ground testing of motors and reducers.

[0004] This utility model provides a test bench for an aircraft motor reducer, comprising:

[0005] A motor mounting structure includes a mounting base plate and a mounting cylinder disposed on the mounting base plate, the mounting base plate being used to mount a motor, and the mounting cylinder being used to surround the outside of the motor; and

[0006] The reducer mounting structure includes a docking cylinder, which is detachably connected to the end of the mounting cylinder away from the mounting base plate. The end of the docking cylinder away from the mounting cylinder is used for the reducer to pass through, and the docking cylinder is used to mount a reducer with part inside the docking cylinder and part outside the docking cylinder.

[0007] The docking cylinder or the mounting cylinder has a clearance area, which connects the interior and exterior of the docking cylinder or the interior and exterior of the mounting cylinder. The clearance area corresponds to the connection area of ​​the motor and the reducer, so that the motor and the reducer can be connected at the clearance area.

[0008] In one embodiment, the mounting cylinder is detachably connected to the mounting base plate; and / or

[0009] The mounting cylinder has heat dissipation holes connecting the interior and exterior of the mounting cylinder; and / or

[0010] The mounting cylinder includes a plurality of mounting legs disposed on the mounting base plate, the plurality of mounting legs being arranged at intervals along the circumference of the mounting cylinder; and / or

[0011] It also includes an adjustment structure, which is disposed on the mounting base plate and is used to adjust the angle between the mounting base plate and the test platform.

[0012] In one embodiment, the mounting cylinder includes a plurality of mounting legs disposed on the mounting base plate, and the plurality of mounting legs are arranged at intervals along the circumference of the mounting cylinder;

[0013] The mounting legs are detachably connected to the mounting base plate; and / or

[0014] The mounting leg includes a rod and a first end and a second end respectively located at both ends of the rod. The first end is connected to the mounting base plate, and the second end is connected to the docking cylinder. In the circumferential direction of the mounting cylinder, the two sides of the first end are located outside the two sides of the rod, and the two sides of the second end are located outside the two sides of the rod; and / or

[0015] In the arrangement direction of the mounting cylinder and the docking cylinder, the mounting leg has a weight-reducing hole in the middle; and / or

[0016] The mounting cylinder further includes a fixing frame, the number of which is the same as the number of mounting legs, and each fixing frame connects to two adjacent mounting legs; and / or

[0017] The mounting cylinder also includes a reinforcing frame, which is connected to the ends of the plurality of mounting legs away from the mounting base plate.

[0018] In one embodiment, the mounting cylinder includes mounting legs, a fixing frame, and a reinforcing frame. The mounting legs are disposed on the mounting base plate, and there are multiple mounting legs. The multiple mounting legs are arranged at intervals along the circumference of the mounting cylinder. The number of fixing frames is the same as the number of mounting legs, and each fixing frame connects to two adjacent mounting legs. The reinforcing frame is connected to the ends of the multiple mounting legs away from the mounting base plate.

[0019] The fixed frame is detachably connected to the mounting legs; and / or

[0020] The fixing frame has heat dissipation holes connecting the interior and exterior of the mounting cylinder; and / or

[0021] The reinforcing frame is detachably connected to the mounting leg; and / or

[0022] The reinforcing frame includes an annular column, two end plates located at both ends of the annular column, and reinforcing ribs connecting the two end plates.

[0023] In one embodiment, the docking cylinder includes a plurality of docking legs arranged at circumferential intervals along the docking cylinder, and the plurality of docking legs are detachably connected to the mounting cylinder.

[0024] In one embodiment, two adjacent mating legs define a gap, and the clearance area includes at least one of the gaps; and / or

[0025] The docking cylinder also includes an adapter frame, which is detachably disposed at one end of the plurality of docking legs near the mounting cylinder.

[0026] In one embodiment, the system further includes an adjustment structure disposed on the mounting base plate for adjusting the angle between the mounting base plate and the test bench surface.

[0027] The adjustment structure includes a support foot located on the side of the mounting base plate away from the mounting cylinder. There are multiple support feet, which are arranged at intervals along the circumference of the mounting cylinder. The mounting base plate can be placed on the test bench through the multiple support feet.

[0028] The mounting base plate has a first side and a second side. The support foot located on the first side is the first support foot, and the support foot located on the second side is the second support foot. The first support foot has multiple connection positions that connect to the mounting base plate. When the connection position between the mounting base plate and the first support foot is changed, the angle between the mounting base plate and the test bench surface changes accordingly.

[0029] This utility model also provides a test device for an aircraft, comprising:

[0030] The aforementioned test bench for the motor reducer of the aircraft;

[0031] The motor is located inside the mounting cylinder and is detachably connected to the mounting base plate; and

[0032] The reducer is partially located inside the docking cylinder and partially located outside the docking cylinder, and is detachably connected to the motor. The connection area between the reducer and the motor is exposed outside the clearance area.

[0033] This utility model also provides a test system for an aircraft, including:

[0034] support;

[0035] As in the aforementioned test apparatus for aircraft, the mounting base is detachably mounted on the end of the support that is furthest from the ground;

[0036] The blades are disposed on the portion of the reducer located outside the docking cylinder; and

[0037] A vibration detector, a noise detector, and a temperature detector are respectively disposed on the mounting cylinder or the docking cylinder.

[0038] In one embodiment, the distance from the ground to the end of the support is greater than or equal to 2 meters; and / or

[0039] The motor has a first flange, and the reducer has a second flange at one end near the motor. The motor and the reducer are connected via the first flange and the second flange; and / or

[0040] The reducer has a third flange at the end away from the motor, and the blade has a hub connected to the third flange.

[0041] The aforementioned test bench for the aircraft's motor and reducer can be used to assemble the motor and reducer to form a test apparatus for the aircraft. This test apparatus, in conjunction with other components, allows for the testing of the motor and reducer.

[0042] When assembling the motor and reducer on the aforementioned aircraft's motor and reducer test bench, the motor can be first placed inside the mounting cylinder, and then mounted on the mounting base plate using bolts and other components. Next, a docking cylinder can be installed at the end of the mounting cylinder away from the mounting base plate using bolts and other components. Then, the reducer can be inserted into the end of the docking cylinder away from the mounting cylinder, with part of the reducer located inside the docking cylinder and part outside. The reducer can then be mounted on the docking cylinder using bolts and other components. Finally, the motor and reducer can be connected at the clearance area using bolts and other components.

[0043] In the aforementioned test rig for the motor and reducer of the aircraft, the docking cylinder and the mounting cylinder are rigidly connected by bolts and other components, ensuring the stability of the test rig structure and effectively increasing stability during the experiment. Furthermore, in the test device for the aforementioned aircraft, the motor and reducer are rigidly connected by bolts and other components. Simultaneously, the motor is rigidly connected to the mounting base plate, and the reducer is rigidly connected to the docking cylinder. The entire assembly consisting of the motor and reducer has two connection points on the test rig, ensuring a secure connection between the motor and reducer and the test rig, effectively increasing stability during the experiment.

[0044] When the aforementioned aircraft's test device, in conjunction with other components (vibration detectors, noise detectors, temperature detectors, support frame, and propeller blades), tests are conducted on the motor and reducer, the propeller blades can first be installed on the portion of the reducer outside the docking cylinder of the test device. Then, the test device is mounted on the end of the support frame away from the ground (the mounting base is secured to the support frame using bolts and other components). Next, after the motor and reducer are powered on, their operation is controlled to drive the propeller blades. Through the coordinated operation of the vibration detectors, noise detectors, temperature detectors, and other components, the effects of the motor and reducer's torque and speed on vibration, noise, and thermal management are verified. This determines whether the vibration, noise, and heat generation of the motor and reducer meet standards, thereby assessing the stability and risks of the motor and reducer under test conditions. This improves the overall power system of the aircraft, ensuring its normal operation after successful ground testing.

[0045] The aforementioned test bench for the motor and reducer of the aircraft has a robust structure, which effectively increases stability during the experiment. Furthermore, the test bench can securely fix the motor and reducer, further enhancing stability during testing. Therefore, the aforementioned test bench for the motor and reducer of the aircraft can be used for ground testing of the motor and reducer. Attached Figure Description

[0046] Various other advantages and benefits will become apparent to those skilled in the art upon reading the detailed description of the preferred embodiments below. The accompanying drawings are for illustrative purposes only and are not intended to limit the scope of this application. Furthermore, the same reference numerals denote the same parts throughout the drawings. In the drawings:

[0047] Figure 1 This is a schematic diagram of the structure of a test device for an aircraft according to an embodiment of the present invention;

[0048] Figure 2 for Figure 1 A schematic diagram of the bottom structure of the test device for the aircraft shown;

[0049] Figure 3 for Figure 1 An exploded view of the test setup for the aircraft shown.

[0050] Figure 4 for Figure 1 The experimental setup for the aircraft shown omits a schematic diagram of the motor's structure.

[0051] Figure 5 This is a schematic diagram of the structure of a test bench for the motor reducer of an aircraft according to an embodiment of the present invention. Detailed Implementation

[0052] To make the above-mentioned objectives, features, and advantages of this application more apparent and understandable, the specific embodiments of this application are described in detail below with reference to the accompanying drawings. Many specific details are set forth in the following description to provide a thorough understanding of this application. However, this application can be implemented in many other ways different from those described herein, and those skilled in the art can make similar modifications without departing from the spirit of this application. Therefore, this application is not limited to the specific embodiments disclosed below.

[0053] In the description of this application, it should be understood that, where they appear, the terms “center,” “longitudinal,” “lateral,” “length,” “width,” “thickness,” “upper,” “lower,” “front,” “rear,” “left,” “right,” “vertical,” “horizontal,” “top,” “bottom,” “inner,” “outer,” “clockwise,” “counterclockwise,” “axial,” “radial,” and “circumferential” indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used 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. Therefore, they should not be construed as limitations on this application.

[0054] Furthermore, where applicable, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this application, "multiple" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0055] In this application, unless otherwise expressly specified and limited, the terms "installation," "connection," "joining," "fixing," etc., shall be interpreted broadly. For example, they may refer to a fixed connection, a detachable connection, or an integral part; they may refer to a mechanical connection or an electrical connection; they may refer to a direct connection or an indirect connection through an intermediate medium; they may refer to the internal communication of two components or the interaction between two components, unless otherwise expressly limited. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0056] In this application, unless otherwise expressly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "on top of," and "over" the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0057] It should be noted that, if an element is described as "fixed to" or "set on" another element, it can be directly on the other element or there may be an intervening element. When an element is described as "connected to" another element, it can be directly connected to the other element or there may be an intervening element. The terms "vertical," "horizontal," "upper," "lower," "left," "right," and similar expressions used herein are for illustrative purposes only and do not represent the only possible implementation.

[0058] like Figures 1-5 As shown, an embodiment of the present invention provides a test apparatus 10 for an aircraft. The test apparatus 10 for the aircraft includes a motor 12, a reducer 14, and a test bench 16 for the aircraft's motor and reducer.

[0059] The aircraft motor and reducer test bench 16 includes a motor mounting structure 200 and a reducer mounting structure 300. The motor mounting structure 200 includes a mounting base plate 210 and a mounting cylinder 220 disposed on the mounting base plate 210. The mounting base plate 210 is used to mount a motor 12. The mounting cylinder 220 is used to surround the outside of the motor 12. The reducer mounting structure 300 includes a docking cylinder 310. The docking cylinder 310 is detachably connected to the end of the mounting cylinder 220 away from the mounting base plate 210. The end of the docking cylinder 310 away from the mounting cylinder 220 is used for the reducer 14 to pass through, and the docking cylinder 310 is used to mount the reducer 14, which is partially located inside the docking cylinder 310 and partially located outside the docking cylinder 310. The docking cylinder 310 or the mounting cylinder 220 has a clearance area 16a, which connects the interior and exterior of the docking cylinder 310 or the interior and exterior of the mounting cylinder 220. The clearance area 16a corresponds to the connection area 14a of the motor 12 and the reducer 14, so that the motor 12 and the reducer 14 are connected at the clearance area 16a.

[0060] The aforementioned test bench 16 for the motor and reducer of the aircraft can be used to assemble the motor 12 and the reducer 14 to form the test apparatus 10 for the aircraft. The test apparatus 10 for the aircraft, in conjunction with other components, can be used to test the motor 12 and the reducer 14.

[0061] When assembling the motor 12 and reducer 14 on the aforementioned aircraft motor and reducer test bench 16, the motor 12 can be first placed inside the mounting cylinder 220, and then mounted on the mounting base plate 210 using bolts or other components. Next, a docking cylinder 310 can be installed at the end of the mounting cylinder 220 away from the mounting base plate 210 using bolts or other components. Then, the reducer 14 can be inserted into the end of the docking cylinder 310 away from the mounting cylinder 220, so that part of the reducer 14 is located inside the docking cylinder 310 and part of the reducer 14 is located outside the docking cylinder 310. Then, the reducer 14 can be mounted on the docking cylinder 310 using bolts or other components. Finally, the motor 12 and reducer 14 can be connected at the clearance area 16a using bolts or other components.

[0062] In the aforementioned test bench 16 for the motor and reducer of the aircraft, the docking cylinder 310 and the mounting cylinder 220 are rigidly connected by bolts and other components, ensuring the stability of the test bench structure and effectively increasing stability during the experiment. Furthermore, in the aforementioned test device 10 for the aircraft, the motor 12 and the reducer 14 are rigidly connected by bolts and other components. Simultaneously, the motor 12 is rigidly connected to the mounting base plate 210, and the reducer 14 is rigidly connected to the docking cylinder 310. The entire assembly consisting of the motor 12 and the reducer 14 has two connection points on the aforementioned test bench 16 for the motor and reducer of the aircraft, thus ensuring a secure connection between the motor 12 and the reducer 14 and the test bench, effectively increasing stability during the experiment.

[0063] When the test device 10 of the aforementioned aircraft, in conjunction with other components (vibration detector, noise detector, temperature detector, support, and propeller blades), tests the motor 12 and reducer 14, the propeller blades can first be installed on the portion of the reducer 14 located outside the docking cylinder 310 of the test device 10. Then, the test device 10 is installed on the end of the support away from the ground (the mounting base 210 is installed on the support using bolts and other components). Next, after the motor 12 and reducer 14 are powered on, they are controlled to operate, driving the propeller blades. Through the coordinated operation of components such as the vibration detector, noise detector, and temperature detector, the effects of the torque and speed of the motor 12 and reducer 14 on vibration, noise, and thermal management are verified. It is determined whether the vibration, noise, and heat generation of the motor 12 and reducer 14 meet the standards, thus determining the stability and risk of the motor 12 and reducer 14 under test conditions. This improves the overall power system of the aircraft, ensuring its normal operation after successful ground testing.

[0064] The aforementioned test bench 16 for the motor and reducer of the aircraft has a robust structure, which effectively increases stability during the experiment. Furthermore, the test bench 16 can firmly secure the motor 12 and reducer 14, further enhancing stability during the experiment. Therefore, the test bench 16 can be used to conduct ground tests on the motor 12 and reducer 14.

[0065] In this embodiment, the clearance area 16a is located on the docking cylinder 310. Thus, the height of the mounting cylinder 220 can be less than the height of the motor 12, and the portion of the motor 12 protruding from the mounting cylinder 220 can extend into the docking cylinder 310 to connect with the reducer 14. This avoids the docking cylinder 310 being too small in height (the reducer 14 is typically smaller than the motor 12; if the clearance area 16a is located on the mounting cylinder 220, then part of the reducer 14 would need to extend into the mounting cylinder 220, resulting in the docking cylinder 310 being too small in height), thus minimizing the difference between the height of the mounting cylinder 220 and the docking cylinder 310. It is understood that in other embodiments, the clearance area 16a can also be located on the mounting cylinder 220.

[0066] In this embodiment, the mounting cylinder 220 has heat dissipation holes 224a connecting the interior and exterior of the mounting cylinder 220. This greatly facilitates heat dissipation for the motor 12. It is understood that in other embodiments, when the clearance area 16a is located on the mounting cylinder 220, the motor 12 can dissipate heat through the clearance area 16a, in which case the heat dissipation holes 224a can be omitted. It is also understood that in other embodiments, heat dissipation holes 224a can be provided on the mounting base plate 210.

[0067] In this embodiment, the mounting cylinder 220 and the mounting base plate 210 are detachably connected. Thus, the mounting cylinder 220 and the mounting base plate 210 adopt a modular design, allowing for quick assembly and disassembly of the mounting cylinder 220 and the mounting base plate 210 according to specific needs during actual operation. This not only improves testing efficiency but also significantly reduces maintenance costs. It is understood that in other embodiments, the mounting cylinder 220 and the mounting base plate 210 can also be welded or bonded.

[0068] In this embodiment, the mounting cylinder 220 includes a plurality of mounting legs 222 disposed on the mounting base plate 210. The plurality of mounting legs 222 are arranged at intervals along the circumference of the mounting cylinder 220, meaning the mounting cylinder 220 is circumferentially discontinuous. Compared to a circumferentially continuous mounting cylinder 220, a circumferentially discontinuous mounting cylinder 220 is easier to manufacture and can reduce costs. It is understood that in other embodiments, the mounting cylinder 220 may also be a circumferentially continuous mounting cylinder 220.

[0069] In this embodiment, the mounting leg 222 includes a rod and a first end and a second end respectively located at both ends of the rod. The first end is connected to the mounting base plate 210. The second end is connected to the docking cylinder 310. In the circumferential direction of the mounting cylinder 220, the two sides of the first end are located outside the two sides of the rod, and the two sides of the second end are also located outside the two sides of the rod. That is, in this embodiment, the mounting leg 222 is designed in an "I" shape, which provides better support and allows the test bench to maintain structural stability even under heavy loads.

[0070] In this embodiment, the mounting leg 222 (first end) is detachably connected to the mounting base plate 210. This makes it very easy to achieve a detachable connection between the mounting cylinder 220 and the mounting base plate 210. Specifically, in this embodiment, the bottom (first end) of the mounting leg 222 is fixed to the corresponding hole on the mounting base plate 210 by screws.

[0071] In this embodiment, in the arrangement direction of the mounting cylinder 220 and the docking cylinder 310, the middle part (rod part) of the mounting leg 222 has a weight-reducing hole 222a, which connects the inside and outside of the mounting cylinder 220. The setting of the weight-reducing hole 222a not only reduces the weight of the entire test bench, but also enhances its wind pressure resistance and stability, and the weight-reducing hole 222a can also dissipate heat.

[0072] In this embodiment, the mounting cylinder 220 also includes a fixing frame 224. The number of fixing frames 224 is the same as the number of mounting legs 222, and each fixing frame 224 connects to two adjacent mounting legs 222. Thus, multiple mounting legs 222 and multiple fixing frames 224 cooperate to form a circumferentially continuous cylinder, which can better protect the motor 12. Using both mounting legs 222 and fixing frames 224 to form a circumferentially continuous cylinder, with the mounting legs 222 as the core structure and the fixing frames 224 as the auxiliary structure, is easier to manufacture and can reduce costs compared to using only one component to form a circumferentially continuous cylinder.

[0073] In this embodiment, the heat dissipation hole 224a is located on the fixed frame 224. In the circumferential direction of the mounting cylinder 220, the area of ​​the fixed frame 224 is typically larger than the area of ​​the mounting leg 222. Providing the heat dissipation hole 224a on the fixed frame 224 allows for a larger heat dissipation area.

[0074] In this embodiment, the fixed frame 224 and the mounting legs 222 are detachably connected. Thus, the fixed frame 224 and the mounting legs 222 adopt a modular design, allowing for quick assembly and disassembly of the fixed frame 224 and the mounting legs 222 according to specific needs during actual operation. This not only improves testing efficiency but also significantly reduces maintenance costs. Specifically, in this embodiment, the rod portion of the mounting cylinder 220 has holes on both sides (three holes on each side), and the fixed frame 224 also has holes on both sides. Bolts connect the holes of the mounting legs 222 to the holes of the fixed frame 224.

[0075] In this embodiment, the mounting cylinder 220 further includes a reinforcing frame 226. The reinforcing frame 226 is connected to the ends of the plurality of mounting legs 222 away from the mounting base plate 210. The reinforcing frame 226 can reinforce the plurality of mounting legs 222 and the plurality of fixed frames 224, thereby making the structure of the mounting cylinder 220 more stable.

[0076] In this embodiment, the reinforcing frame 226 and the mounting leg 222 are detachably connected. Thus, the reinforcing frame 226 and the mounting leg 222 adopt a modular design, allowing for quick assembly and disassembly of the reinforcing frame 226 and the mounting leg 222 according to specific needs during actual operation. This not only improves testing efficiency but also significantly reduces maintenance costs.

[0077] In this embodiment, the reinforcing frame 226 includes an annular column, two end plates located at both ends of the annular column, and reinforcing ribs connecting the two end plates. These reinforcing ribs can effectively distribute and bear the load generated during the test, ensuring the stability of the entire test bench and further enhancing the stability and load-bearing capacity of the test bench.

[0078] In this embodiment, the docking cylinder 310 includes a plurality of docking legs 312 arranged at intervals along the circumference of the docking cylinder 310. The plurality of docking legs 312 are detachably connected to the mounting cylinder 220. This facilitates the formation of a docking cylinder 310 with one end larger than the other, making it easy for the larger-opening end of the docking cylinder 310 to dock with the mounting cylinder 220, and also easy for the smaller-opening end of the docking cylinder 310 to be adapted to the reducer 14. Furthermore, adjacent docking legs 312 can define a gap, and the clearance area 16a can include at least one gap, thus facilitating the formation of the clearance area 16a.

[0079] In this embodiment, the docking cylinder 310 further includes an adapter frame 314. The adapter frame 314 is disposed at one end of the plurality of docking legs 312 near the mounting cylinder 220. The adapter frame 314 is detachably connected to the mounting cylinder 220. Thus, when the plurality of docking legs 312 are not assembled onto the mounting cylinder 220, the docking cylinder 310 can be formed by assembling them onto the adapter frame 314.

[0080] In this embodiment, the holes in the adapter frame 314, the reinforcing frame 226, and the mounting leg 222 (second end) are coaxial, and bolts are used to connect the holes in the adapter frame 314, the reinforcing frame 226, and the mounting leg 222 (second end). This simplifies the assembly of the adapter frame 314, the reinforcing frame 226, and the mounting leg 222 (second end).

[0081] In this embodiment, the docking leg 312 and the adapter frame 314 are detachably connected. Thus, the docking leg 312 and the adapter frame 314 adopt a modular design. In actual operation, the docking leg 312 and the adapter frame 314 can be quickly assembled and disassembled according to specific needs, which not only improves testing efficiency but also significantly reduces maintenance costs. Furthermore, when the model of the motor 12 changes, resulting in a change in the height of the motor 12, the shorter adapter frame 314 can be replaced with a taller adapter frame 314 (other structures do not need to be changed) to test the taller motor 12 and reducer 14. This allows the test bench to accommodate multiple models of motor 12, providing versatility.

[0082] In this embodiment, the test bench 16 also includes an adjustment structure 400. The adjustment structure 400 is disposed on the mounting base plate 210 and is used to adjust the angle between the mounting base plate 210 and the test bench surface (support). This allows for the simulation of more operating conditions of the aircraft.

[0083] In this embodiment, the adjustment structure 400 includes support feet located on the side of the mounting base plate 210 away from the mounting cylinder 220. Multiple support feet are provided and arranged at intervals along the circumference of the mounting cylinder 220. The mounting base plate 210 can be placed on the test bench surface via these multiple support feet.

[0084] In this embodiment, the mounting base plate 210 and the support legs are detachably connected. Thus, the mounting base plate 210 and the support legs adopt a modular design, allowing for quick assembly and disassembly of the base plate 210 and support legs according to specific needs during actual operation. This not only improves testing efficiency but also significantly reduces maintenance costs. Specifically, in this embodiment, the mounting base plate 210 and the support legs are connected by bolts.

[0085] In this embodiment, the support leg is detachably connected to the test platform (support). Specifically, in this embodiment, the support leg is connected to the test platform (support) by bolts.

[0086] In this embodiment, the mounting base plate 210 has a first side and a second side facing each other. The support foot located on the first side is a first support foot 410, and the support foot located on the second side is a second support foot 420. The first support foot 410 has multiple connection positions 400a that connect to the mounting base plate 210. When the connection position 400a between the mounting base plate 210 and the first support foot 410 is changed, the angle between the mounting base plate 210 and the test bench surface changes accordingly. This makes it very convenient to adjust the angle between the mounting base plate 210 and the test bench surface (support). Specifically, in this embodiment, there are two first support feet 410 and two second support feet 420. The first support foot 410 has three connection positions 400a, and the second support foot 420 has one connection position 400a.

[0087] In this embodiment, the motor 12 is located inside the mounting cylinder 220 and is detachably connected to the mounting base plate 210. The reducer 14 is partially located inside the docking cylinder 310 and partially located outside the docking cylinder 310, and is detachably connected to the motor 12. The connection area 14a between the reducer 14 and the motor 12 is exposed outside the clearance area 16a.

[0088] In this embodiment, the motor 12 is bolted to the end near the mounting base plate 210, which has holes and mounting base plate 210 holes.

[0089] In this embodiment, the motor 12 has a first flange 12a. The reducer 14 has a second flange 14b at one end near the motor 12. The motor 12 and the reducer 14 are connected via the first flange 12a and the second flange 14b. Specifically, in this embodiment, the first flange 12a and the second flange 14b are connected by bolts.

[0090] This utility model also provides a test system for an aircraft. The test system for the aircraft includes the aforementioned test device 10, support frame, propeller blades, vibration detector, noise detector, and temperature detector.

[0091] The mounting base 210 of the aircraft's motor reducer test bench 16 is detachably mounted on the end of the support away from the ground. The propeller blades are mounted on the portion of the reducer 14 located outside the docking cylinder 310. Vibration detectors, noise detectors, and temperature detectors are respectively mounted on the mounting cylinder 220 or the docking cylinder 310 of the aircraft's motor reducer test bench 16.

[0092] In this embodiment, the distance between the end of the support and the ground is greater than or equal to 2 meters. This better simulates the actual height of the motor 12 and the reducer 14 on the aircraft.

[0093] In this embodiment, the reducer 14 has a third flange 14c at the end away from the motor 12. The blade has a hub, which is connected to the third flange 14c.

[0094] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0095] The embodiments described above are merely illustrative of several implementation methods of this application, and while the descriptions are specific and detailed, they should not be construed as limiting the scope of this patent application. It should be noted that those skilled in the art can make various modifications and improvements without departing from the concept of this application, and these all fall within the protection scope of this application. Therefore, the protection scope of this patent application should be determined by the appended claims.

Claims

1. An electric machine reducer test bench for an aircraft, characterized in that, include: The motor mounting structure includes a mounting base plate and a mounting cylinder disposed on the mounting base plate. The mounting base plate is used to mount the motor, and the mounting cylinder is used to surround the outside of the motor. as well as The reducer mounting structure includes a docking cylinder, which is detachably connected to the end of the mounting cylinder away from the mounting base plate. The end of the docking cylinder away from the mounting cylinder is used for the reducer to pass through, and the docking cylinder is used to mount a reducer with part inside the docking cylinder and part outside the docking cylinder. The docking cylinder or the mounting cylinder has a clearance area, which connects the interior and exterior of the docking cylinder or the interior and exterior of the mounting cylinder. The clearance area corresponds to the connection area of ​​the motor and the reducer, so that the motor and the reducer can be connected at the clearance area.

2. The aircraft motor reducer test bench of claim 1, wherein, The mounting cylinder is detachably connected to the mounting base plate; and / or The mounting cylinder has heat dissipation holes connecting the interior and exterior of the mounting cylinder; and / or The mounting cylinder includes a plurality of mounting legs disposed on the mounting base plate, the plurality of mounting legs being arranged at intervals along the circumference of the mounting cylinder; and / or It also includes an adjustment structure, which is disposed on the mounting base plate and is used to adjust the angle between the mounting base plate and the test platform.

3. The aircraft motor reducer test bench of claim 1, wherein, The mounting cylinder includes a plurality of mounting legs disposed on the mounting base plate, and the plurality of mounting legs are arranged at intervals along the circumference of the mounting cylinder; The mounting legs are detachably connected to the mounting base plate; and / or The mounting leg includes a rod and a first end and a second end respectively located at both ends of the rod. The first end is connected to the mounting base plate, and the second end is connected to the docking cylinder. In the circumferential direction of the mounting cylinder, the two sides of the first end are located outside the two sides of the rod, and the two sides of the second end are located outside the two sides of the rod. and / or In the arrangement direction of the mounting cylinder and the docking cylinder, the mounting leg has a weight-reducing hole in the middle; and / or The mounting cylinder further includes a fixing frame, the number of which is the same as the number of mounting legs, and each fixing frame connects to two adjacent mounting legs; and / or The mounting cylinder also includes a reinforcing frame, which is connected to the ends of the plurality of mounting legs away from the mounting base plate.

4. The test bench for the motor reducer of an aircraft as described in claim 1, characterized in that, The mounting cylinder includes mounting legs, a fixing frame, and a reinforcing frame. The mounting legs are disposed on the mounting base plate. There are multiple mounting legs, which are arranged at intervals along the circumference of the mounting cylinder. The number of fixing frames is the same as the number of mounting legs, and each fixing frame connects to two adjacent mounting legs. The reinforcing frame is connected to the end of each mounting leg away from the mounting base plate. The fixed frame is detachably connected to the mounting legs; and / or The fixing frame has heat dissipation holes connecting the interior and exterior of the mounting cylinder; and / or The reinforcing frame is detachably connected to the mounting leg; and / or The reinforcing frame includes an annular column, two end plates located at both ends of the annular column, and reinforcing ribs connecting the two end plates.

5. The aircraft motor reducer test bench of claim 1, wherein, The docking cylinder includes a plurality of docking legs arranged at intervals along the circumference of the docking cylinder, and the plurality of docking legs are detachably connected to the mounting cylinder.

6. The aircraft motor reducer test bench of claim 5, wherein, Two adjacent docking legs define a gap, and the clearance area includes at least one of the gaps; and / or The docking cylinder also includes an adapter frame, which is detachably disposed at one end of the plurality of docking legs near the mounting cylinder.

7. The aircraft motor reducer test bench of claim 1, wherein, It also includes an adjustment structure, which is disposed on the mounting base plate and is used to adjust the angle between the mounting base plate and the test platform. The adjustment structure includes a support foot located on the side of the mounting base plate away from the mounting cylinder. There are multiple support feet, which are arranged at intervals along the circumference of the mounting cylinder. The mounting base plate can be placed on the test bench through the multiple support feet. The mounting base plate has a first side and a second side. The support foot located on the first side is the first support foot, and the support foot located on the second side is the second support foot. The first support foot has multiple connection positions that connect to the mounting base plate. When the connection position between the mounting base plate and the first support foot is changed, the angle between the mounting base plate and the test bench surface changes accordingly.

8. A test device for an aircraft, characterized in that include: Test bench for the motor reducer of an aircraft as described in any one of claims 1-7; The motor is located inside the mounting cylinder and is detachably connected to the mounting base plate. as well as The reducer is partially located inside the docking cylinder and partially located outside the docking cylinder, and is detachably connected to the motor. The connection area between the reducer and the motor is exposed outside the clearance area.

9. A test system for an aircraft, characterized in that include: support; The test apparatus for the aircraft as described in claim 8, wherein the mounting base is detachably mounted on the end of the bracket away from the ground; The blades are located on the portion of the reducer outside the docking cylinder; as well as A vibration detector, a noise detector, and a temperature detector are respectively disposed on the mounting cylinder or the docking cylinder.

10. The test system of claim 9, wherein, The distance from the ground to the end of the support is greater than or equal to 2 meters; and / or The motor has a first flange, and the reducer has a second flange at one end near the motor. The motor and the reducer are connected through the first flange and the second flange. and / or The reducer has a third flange at the end away from the motor, and the blade has a hub connected to the third flange.

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