Aircraft power testing device

Abstract

The utility model discloses an aircraft power test device, comprising a rack used for installing an aircraft; the transfer assembly comprises a lifting mechanism and a moving mechanism, the moving mechanism can move in a plane perpendicular to the up-down direction, and the lifting mechanism is arranged on the moving mechanism, connected with the rack and used for driving the rack to move in the up-down direction so that the rack can be switched between a supporting state and a moving state; the rack is supported on a placing surface used for placing the moving mechanism, and in the moving state, the rack is suspended on the placing surface. According to the aircraft power testing device of the utility model, the overall transfer of the aircraft power testing device is realized through the moving mechanism.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft, in particular to an aircraft power testing device. Background Art

[0002] With the continuous development of science and technology, electric vertical take-off and landing aircraft, as a new type of transportation for urban air traffic and future travel, are increasingly receiving attention from the aviation and automotive fields. Electric vertical take-off and landing aircraft have unique advantages such as low operating costs, low noise, easy take-off and landing, low security requirements, and fast cruising speed, giving them a broader market prospect.

[0003] The electric vertical take-off and landing aircraft includes a power system, a high-voltage system, a flight control system, an avionics system, etc. The power system usually uses a distributed electric drive and has multiple independent vertical take-off and landing units. During the development stage, there may be voltage pulsation shocks after the integration of multiple power systems, electromagnetic interference in the high and low voltage systems, and a lack of flight control functions. Therefore, it is necessary to test in advance to discover problems in various systems and subsystems in advance, saving a lot of development costs and time costs. However, since the test device integrates many systems and is heavy, and needs to be tested in outdoor space, the transfer of the test device is an urgent problem to be solved. Utility Model Content

[0004] The utility model aims to solve at least one of the technical problems existing in the prior art. To this end, the utility model provides an aircraft power test device, which can be transferred to a testing location through a moving mechanism.

[0005] According to an embodiment of the utility model, the aircraft power testing device includes: a test bench for installing an aircraft; a transfer assembly, the transfer assembly including a lifting mechanism and a moving mechanism, the moving mechanism can move in a plane perpendicular to the up and down direction, the lifting mechanism is arranged on the moving mechanism and is connected to the test bench, and is used to drive the test bench to move along the up and down direction so that the test bench can switch between a supporting state and a moving state. In the supporting state, the test bench is supported on a placement surface for placing the moving mechanism, and in the moving state, the test bench is suspended above the placement surface.

[0006] According to the aircraft power test device of the embodiment of the utility model, the test bench is used to install the aircraft, and the transfer assembly includes a lifting mechanism and a moving mechanism. The moving mechanism can move in a plane perpendicular to the up and down direction. The lifting mechanism is arranged on the moving mechanism and is connected to the test bench, and is used to drive the test bench to move in the up and down direction so that the test bench can switch between a supporting state and a moving state. In the supporting state, the test bench is supported on a placement surface for placing the moving mechanism. In the moving state, the test bench is suspended on the placement surface, thereby realizing the overall transfer of the aircraft power test device.

[0007] In some embodiments of the utility model, the stand includes: an upper base plate, the lifting mechanism is connected to the upper base plate; a lower base plate, the lower base plate is located below the upper base plate and is spaced apart from the upper base plate; and a column, the column is arranged between the upper base plate and the lower base plate and the upper and lower ends are respectively connected to the upper base plate and the lower base plate.

[0008] In some embodiments of the utility model, the moving mechanism includes: a moving frame, the moving frame is located between the upper base plate and the lower base plate, and the lower end of the lifting mechanism is connected to the moving frame; a universal wheel, the universal wheel is arranged at the lower end of the moving frame, and the lower base plate has a matching hole for the universal wheel to pass through.

[0009] In some embodiments of the utility model, the mobile frame includes a plurality of movable arms spaced apart along the circumferential direction of the frame, one ends of the plurality of movable arms are connected to each other and to the lifting mechanism, and the other ends extend radially outwardly toward the frame and are each provided with the universal wheel, and the matching holes are a plurality of ones that match one by one with the plurality of universal wheels.

[0010] In some embodiments of the utility model, a linear bearing is provided on the movable frame, and the column is inserted into the linear bearing.

[0011] In some embodiments of the present invention, the columns are multiple and spaced apart along the circumferential direction of the upper base plate, and the linear bearings are multiple and correspond one to one with the columns.

[0012] In some embodiments of the present invention, it also includes: an anti-tilt assembly, wherein the anti-tilt assembly is arranged at the radial outer end of the frame, and the anti-tilt assembly is a plurality of assemblies spaced apart along the circumferential direction of the frame, and in the supporting state, the lower end of the anti-tilt assembly is supported on a placement surface for placing the moving mechanism, and in the moving state, the lower end of the anti-tilt assembly is spaced apart from the placement surface for placing the moving mechanism.

[0013] In some embodiments of the utility model, the aircraft includes a plurality of arms, and the plurality of arms are spaced apart along the circumferential direction of the test bench. One end of each arm in the length direction is connected to the test bench, and the other end is provided with a driving mechanism and a propeller. The driving mechanism includes at least two motors and a plurality of motor controllers corresponding one-to-one to the motors. The propellers are a plurality corresponding one-to-one to the motors, and each motor is respectively connected to the corresponding propeller and the motor controller. The aircraft power testing device also includes: a data acquisition system and a sensor assembly. The data acquisition system is connected to the test bench, and the sensor assembly is arranged on the arm, and the sensor assembly is communicatively connected to the data acquisition system.

[0014] In some embodiments of the utility model, it also includes: a flight control power supply system, which is communicatively connected to the drive mechanism and is arranged on the platform; a distribution box, which is arranged on the platform, the distribution box is connected to the high-voltage power supply, and the wiring harness led out of the distribution box is connected to each of the motor controllers in turn.

[0015] In some embodiments of the utility model, it also includes: an adjustment foot cup, which is connected to the stand and located between the stand and the placement surface. In the moving state, the adjustment foot cup is suspended above the placement surface. In the supporting state, the adjustment foot cup is used to adjust the distance between the stand and the placement surface.

[0016] Additional aspects and advantages of the present invention will be given in part in the following description, and in part will become apparent from the following description, or will be learned through the practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The above and / or additional aspects and advantages of the present invention will become apparent and easily understood from the description of the embodiments in conjunction with the following drawings, in which:

[0018] Figure 1 It is a structural diagram of an aircraft power test device and an aircraft according to an embodiment of the utility model;

[0019] Figure 2 It is a structural diagram of a stand according to an embodiment of the utility model;

[0020] Figure 3 is a structural diagram of a transfer assembly according to an embodiment of the utility model;

[0021] Figure 4 is a structural diagram of an anti-tilt assembly according to an embodiment of the utility model;

[0022] Figure 5 is a structural diagram of an aircraft according to an embodiment of the utility model;

[0023] Figure 6 is a structural diagram of a data acquisition system according to an embodiment of the utility model;

[0024] Figure 7 is a structural diagram of a flight control power supply system according to an embodiment of the utility model;

[0025] Figure 8 It is a principle schematic diagram of a data acquisition system according to an embodiment of the utility model;

[0026] Fig. 9 It is a schematic diagram of the principle of the flight control power supply system according to an embodiment of the utility model;

[0027] Fig.10 It is a schematic diagram of the principle of the high-voltage system arrangement according to an embodiment of the utility model.

[0028] Reference numerals:

[0029] 100. Aircraft power test equipment;

[0030] 1. Stand; 11. Upper base plate; 12. Lower base plate; 121. Matching hole; 122. First adjustment foot cup; 13. Column; 14. Assembly plate;

[0031] 2. Transfer assembly; 21. Lifting mechanism; 22. Moving mechanism; 221. Moving frame; 2211. Moving arm; 2212. Linear bearing; 222. Universal wheel;

[0032] 3. Anti-tilt assembly; 31. First plate; 32. Second plate; 33. Third plate; 34. Second adjustment foot cup;

[0033] 4. Data acquisition system; 41. Mounting bracket; 42. Data acquisition package;

[0034] 5. Flight control power supply system; 51. Fixing plate; 52. Flight control power supply module;

[0035] 6. Power distribution box;

[0036] 200. Aircraft;

[0037] 7. Support arm;

[0038] 8. driving mechanism; 81. motor; 82. motor controller;

[0039] 9. Propeller. DETAILED DESCRIPTION

[0040] The embodiments of the present invention are described in detail below, and examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and cannot be understood as limiting the present invention.

[0041] In the description of the present utility model, it is necessary to understand that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present utility model and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present utility model. In addition, features defined as "first" and "second" may explicitly or implicitly include one or more of such features. In the description of the present utility model, unless otherwise specified, "multiple" means two or more.

[0042] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installation", "connection" and "connection" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0043] The aircraft power testing device 100 according to an embodiment of the present invention will be described below with reference to the accompanying drawings.

[0044] like Figure 1-Figure 3 As shown, an aircraft power testing device 100 according to an embodiment of the present utility model includes a test bench 1 and a transfer assembly 2 .

[0045] Among them, the stand 1 is used to install the aircraft 200, the transfer assembly 2 includes a lifting mechanism 21 and a moving mechanism 22, the moving mechanism 22 can move in a plane perpendicular to the up and down direction, the lifting mechanism 21 is arranged on the moving mechanism 22 and is connected to the stand 1, and is used to drive the stand 1 to move in the up and down direction so that the stand 1 can switch between a supporting state and a moving state. In the supporting state, the stand 1 is supported on a placement surface for placing the moving mechanism 22, and in the moving state, the stand 1 is suspended on the placement surface.

[0046] It can be understood that the bench 1 is used to install the aircraft 200 and the device for testing the aircraft 200, so that the aircraft 200 and the test device are integrated on the bench 1, which is convenient for the transfer of the aircraft power test device 100. When the assembled aircraft power test device 100 needs to be moved to the test site, the bench 1 is first driven to move upward by the lifting mechanism 21 so that the bench 1 is in a moving state. At this time, the bench 1 is suspended on the placement surface for placing the moving mechanism 22. Since the lifting mechanism 21 is arranged on the moving mechanism 22 and connected to the bench 1, the moving mechanism 22 moves in a plane perpendicular to the up and down direction to drive the bench 1 to move to the test site, and then the bench 1 is driven to move downward by the lifting mechanism 21 so that the bench 1 is transformed from the moving state to the supporting state. At this time, the bench 1 is supported on the placement surface for placing the moving mechanism 22, thereby realizing the transfer of the aircraft power test device 100 as a whole, which is convenient for the aircraft power test device 100 to be transferred to the outdoors to test the aircraft 200.

[0047] According to the aircraft power test device 100 of the embodiment of the utility model, the test bench 1 is used to install the aircraft 200, and the transfer assembly 2 includes a lifting mechanism 21 and a moving mechanism 22. The moving mechanism 22 can move in a plane perpendicular to the up and down direction. The lifting mechanism 21 is arranged on the moving mechanism 22 and is connected to the test bench 1, and is used to drive the test bench 1 to move in the up and down direction so that the test bench 1 can switch between a supporting state and a moving state. In the supporting state, the test bench 1 is supported on a placement surface for placing the moving mechanism 22. In the moving state, the test bench 1 is suspended on the placement surface for placing the moving mechanism 22, thereby realizing the overall transfer of the aircraft power test device 100.

[0048] In some embodiments of the present invention, the aircraft power test device 100 further includes: an adjustment foot cup, wherein the adjustment foot cup is connected to the stand 1 and is located between the stand 1 and the placement surface, and in the moving state, the adjustment foot cup is suspended above the placement surface, and in the supporting state, the adjustment foot cup is used to adjust the distance between the stand 1 and the placement surface.

[0049] Therefore, when the assembled aircraft power test device 100 needs to be moved to the inspection location, the lifting mechanism 21 is first used to drive the stand 1 to move upward so that the stand 1 is in a moving state. At this time, the stand 1 and the adjustment foot cup are suspended on the placement surface for placing the moving mechanism 22. The moving mechanism 22 moves in a plane perpendicular to the up and down direction to drive the stand 1 to move to the test location, and then the lifting mechanism 21 is used to drive the stand 1 to move downward so that the stand 1 is changed from the moving state to the supporting state. The adjustment foot cup is used to adjust the distance between the stand 1 and the placement surface so that the lower surface of the stand is located in the same plane, thereby ensuring the overall stability and safety of the stand 1, and then ensuring the reliability of the aircraft power test device 100 in testing the aircraft 200.

[0050] In some embodiments of the present invention, Figure 1 and Figure 2 As shown, the stand 1 includes an upper bottom plate 11, a lower bottom plate 12 and a column 13. The lifting mechanism 21 is connected to the upper bottom plate 11, the lower bottom plate 12 is located below and spaced from the upper bottom plate 11, and the column 13 is arranged between the upper bottom plate 11 and the lower bottom plate 12, and the upper and lower ends are connected to the upper bottom plate 11 and the lower bottom plate 12 respectively.

[0051] Thus, the lifting mechanism 21 drives the upper base plate 11 to move in the up-down direction to drive the stand 1 to move in the up-down direction, thereby realizing the switching of the stand 1 between the supporting state and the moving state. At the same time, such a setting facilitates the arrangement of the aircraft 200 installed on the stand 1 and the device for testing the aircraft 200. For example, the test device includes a data acquisition system 4, a flight control power supply system 5, a remote wireless measurement and control system transmission, etc. The aircraft 200 is connected to the upper base plate 11, and the test device is connected to the upper base plate 11 and the lower base plate 12. At the same time, the upper base plate 11 and the lower base plate 12 are connected through the column 13 to improve the overall reliability of the stand 1.

[0052] In some embodiments of the present invention, Figure 1 and Figure 2 As shown, the adjustment foot cups include a plurality of first adjustment foot cups 122, which are arranged at the lower end of the lower base plate 12, and the plurality of first adjustment foot cups 122 are spaced apart along the circumferential direction of the lower base plate 12. Thus, after the aircraft power test device 100 is moved to the test site and the test bench 1 is in the supporting state, the distance between the lower base plate 12 and the placement surface for placing the moving mechanism 22 is adjusted by the plurality of first adjustment foot cups 122 so that the lower base plate 12 is located in the same plane, thereby ensuring the overall stability of the test bench 1.

[0053] In some embodiments of the present invention, Figure 1-Figure 3 As shown, the mobile mechanism 22 includes a mobile frame 221 and a universal wheel 222. The mobile frame 221 is located between the upper base plate 11 and the lower base plate 12, the lower end of the lifting mechanism 21 is connected to the mobile frame 221, the universal wheel 222 is arranged at the lower end of the mobile frame 221, and the lower base plate 12 has a matching hole 121 for the universal wheel 222 to pass through. Therefore, through such an arrangement, when the stand 1 is in a moving state, the universal wheel 222 passes through the matching hole 121 and moves in a plane perpendicular to the up and down direction to drive the stand 1 to move to the test place.

[0054] Furthermore, the universal wheel 222 can be switched between a locked state and a sliding state. When the test bench 1 is in a supporting state, the universal wheel 222 is in a locked state, thereby ensuring the stability of the aircraft power test device 100 when it reaches the test site; when the test bench 1 is in a moving state, the universal wheel 222 is in a sliding state, thereby enabling the universal wheel 222 to drive the test bench 1 to move to the test site. It should be noted that the specific structure of the universal wheel 222 is known to ordinary technicians in this field and will not be described in detail here.

[0055] In some embodiments of the present invention, Figure 3 As shown, the movable frame 221 includes a plurality of movable arms 2211 spaced apart along the circumferential direction of the platform 1, one end of the plurality of movable arms 2211 are connected to each other and to the lifting mechanism 21, and the other end extends radially outwardly toward the platform 1 and is provided with a universal wheel 222, and the matching holes 121 are a plurality of which match one by one with the plurality of universal wheels 222.

[0056] Thus, through such a setting, multiple universal wheels 222 can drive the test bench 1 to move to the test site, thereby improving the reliability of the transfer mechanism. At the same time, one end of multiple moving arms 2211 is connected to each other and to the lifting mechanism 21, and the other end extends radially outward toward the test bench 1 and is provided with universal wheels 222, so that the distances from multiple universal wheels 222 to the center point of the test bench 1 are equal, further ensuring the stability of the universal wheels 222 driving the test bench 1 to move to the test site, and such a setting facilitates the connection between multiple moving arms 2211 and the lifting mechanism 21, reducing the difficulty of assembly. It should be noted that the above radial direction refers to the radial direction of a circle with the center point of the test bench 1 as the center.

[0057] In some embodiments of the present invention, Figure 3 As shown, a linear bearing 2212 is provided on the moving frame 221, and the column 13 is inserted into the linear bearing 2212. Therefore, when the lifting mechanism 21 drives the gantry 1 to move in the up and down directions, the column 13 inserted into the linear bearing 2212 plays a guiding and supporting role, which ensures that the gantry 1 switches smoothly between the supporting state and the moving state, thereby improving the reliability of the aircraft power test device 100.

[0058] In some embodiments of the present invention, Figure 1-Figure 3 As shown, the columns 13 are multiple and spaced apart in the circumferential direction of the upper base plate 11, and the linear bearings 2212 are multiple and correspond to the columns 13. Therefore, the linear bearings 2212 corresponding to the columns 13 are sequentially passed through the multiple columns 13, and the lifting mechanism 21 drives the platform 1 to move in the up and down direction to further play a guiding and supporting role, thereby improving the reliability of the aircraft power test device 100.

[0059] In some embodiments, Figure 1-Figure 3 As shown, the stand 1 includes an upper base plate 11, a lower base plate 12 and a plurality of columns 13. The lifting mechanism 21 is connected to the upper base plate 11, the lower base plate 12 is located below and spaced from the upper base plate 11, and the plurality of columns 13 are spaced from each other along the circumferential direction of the upper base plate 11. The plurality of columns 13 are all arranged between the upper base plate 11 and the lower base plate 12, and the upper and lower ends are connected to the upper base plate 11 and the lower base plate 12 respectively. The movable frame 221 includes a plurality of movable arms 2211 spaced apart in the circumferential direction of the stage 1 and corresponding one-to-one to the plurality of columns 13. One ends of the plurality of movable arms 2211 are connected to each other and to the lifting mechanism 21, and the other ends extend radially outwardly toward the stage 1 and are each provided with a universal wheel 222 and a linear bearing 2212. The universal wheel 222 and the linear bearing 2212 are respectively located on both sides of the movable arm 2211 in the up and down directions and the universal wheel 222 is located at the lower end of the linear bearing 2212. The lower base plate 12 has a plurality of matching holes 121 for the plurality of universal wheels 222 to pass through respectively.

[0060] Therefore, by sequentially passing through a plurality of columns 13 and corresponding linear bearings 2212, the stand 1 and the movable frame 221 can generate relative movement in the up-and-down directions, thereby realizing the change of the supporting state and the moving state in the process that the lifting mechanism 21 drives the stand 1 to move in the up-and-down directions. The linear bearings 2212 play a guiding and supporting role in the process that the lifting mechanism 21 drives the stand 1 to move in the up-and-down directions, thereby further improving the reliability of the aircraft power testing device 100.

[0061] At the same time, since the lower bottom plate 12 is located below the multiple moving arms 2211, and the lower bottom plate 12 is provided with multiple matching holes 121 for the multiple universal wheels 222 to pass through respectively, the travel range of the stand 1 along the up and down movement is limited to only the distance between the placement surface and the moving arms 2211 (i.e., the height of the universal wheels 222 along the up and down direction). Therefore, in the moving state, the lifting mechanism 21 drives the stand 1 to move upward, so that the stand 1 is suspended on the placement surface and the universal wheels 222 are in contact with the placement surface, so that the universal wheels 222 move in a plane perpendicular to the up and down direction to drive the stand 1 to move to the test place; in the supporting state, the lifting mechanism 21 drives the stand 1 to move downward, so that the stand 1 is in contact with the placement surface, so that the universal wheels 222 cannot play a moving role, thereby ensuring the support stability of the aircraft power test device 100. Therefore, through such a setting, the test bench 1 can achieve switching between the supporting state and the moving state within a smaller movement range, and the switching speed is faster. At the same time, the movement range of the lifting mechanism 21 is also shorter, which is beneficial to extend the service life of the aircraft power test device 100 and improve the overall reliability.

[0062] In some embodiments of the present invention, Figure 1 and Figure 4As shown, the aircraft power test device 100 further includes an anti-tilt assembly 3. The anti-tilt assembly 3 is arranged at the radial outer end of the test bench 1, and the anti-tilt assembly 3 is a plurality of anti-tilt assemblies 3 spaced apart along the circumferential direction of the test bench 1. In the supporting state, the lower end of the anti-tilt assembly 3 is supported on the placement surface for placing the moving mechanism 22, and in the moving state, the lower end of the anti-tilt assembly 3 is spaced apart from the placement surface for placing the moving mechanism 22.

[0063] It can be understood that when the assembled aircraft power test device 100 needs to be moved to the inspection location, the lifting mechanism 21 is first used to drive the test bench 1 to move upward so that the test bench 1 is in a mobile state. At this time, the lower ends of the test bench 1 and the anti-roll assembly 3 are separated from the placement surface for placing the mobile mechanism 22. Since the lifting mechanism 21 is arranged on the mobile mechanism 22 and connected to the test bench 1, the mobile mechanism 22 moves in a plane perpendicular to the up and down direction to drive the test bench 1 to move to the test location, and then the lifting mechanism 21 is used to drive the test bench 1 to move downward so that the test bench 1 is changed from a mobile state to a supporting state. At this time, the lower ends of the test bench 1 and the anti-roll assembly 3 are supported on the placement surface for placing the mobile mechanism 22, so that when the test bench 1 is in the supporting state, the stability of the test bench 1 is further improved by the anti-roll assembly 3, thereby ensuring the reliability of the aircraft power test device 100.

[0064] In some embodiments of the present invention, Figure 1 and Figure 4 As shown, the anti-tilt assembly 3 includes a first plate 31, a second plate 32 and a third plate 3, and the adjustment foot cup includes a second adjustment foot cup 34. The first plate 31 extends in the up-down direction, the second plate 32 extends in a direction perpendicular to the up-down direction, one end of the third plate 33 in the length direction is connected to one end of the second plate 32 in the length direction and the lower end is provided with a second adjustment foot cup 34, the other end of the third plate 33 in the length direction is connected to the upper bottom plate 11, the other end of the second plate 32 in the length direction is connected to the lower bottom plate 12, the two ends of the first plate 31 in the length direction are respectively connected to the middle area of ​​the third plate 33 and the middle area of ​​the second plate 32, the second adjustment foot cup 34 is located on the side of the first plate 31 away from the stand 1, and the first plate 31, the second plate 32 and the third plate 33 surround to form a triangle. Therefore, after the aircraft power test device 100 is moved to the test site and the test bench 1 is in a supported state, such a setting is used to realize the anti-dumping function of the test bench 1 through the anti-dump assembly 3, and the distance from the lower base plate 12 to the placement surface for placing the moving mechanism 22 is adjusted through multiple second adjustment foot cups 34 so that the lower base plate 12 is located in the same plane, thereby ensuring the reliability of the aircraft power test device 100.

[0065] In some embodiments of the present invention, the lifting mechanism 21 is a jack. It is understandable that the jack is provided on the moving mechanism 22 and connected to the test bench 1. When the aircraft power test device 100 needs to be transferred, the test bench 1 is driven by the jack to move in the up and down direction so that the test bench 1 is switched between the supporting state and the moving state.

[0066] In some embodiments of the present invention, Figure 1 , Figure 5 , Figure 6 and Figure 8 As shown, the aircraft 200 includes a plurality of arms 7, and the plurality of arms 7 are spaced apart along the circumferential direction of the test bench 1. One end of each arm 7 in the length direction is connected to the test bench 1, and the other end is provided with a driving mechanism 8 and a propeller 9. The driving mechanism 8 includes at least two motors 81 and a plurality of motor controllers 82 corresponding one to one with the motors 81. The propellers 9 are a plurality corresponding one to one with the motors 81, and each motor 81 is connected to the corresponding propeller 9 and the motor controller 82. The aircraft power test device 100 also includes a data acquisition system 4 and a sensor assembly. The data acquisition system 4 is connected to the test bench 1, and the sensor assembly is arranged on the arm 7, and the sensor assembly is communicatively connected to the data acquisition system 4.

[0067] It is understandable that, during the process of the aircraft power test device 100 testing the aircraft 200, the propeller 9 is mainly used as the load of the motor 81, and generates a reverse force to block the rotation of the motor 81 when rotating. Therefore, the various data during the rotation of the propeller 9 are collected by the sensor assembly, and the data collected by the sensor assembly are collected by the data acquisition system 4 to realize the test of the aircraft power test device 100. At the same time, propellers 9 of different sizes or models will have different current, voltage, and temperature performances when running at different speeds. By replacing the propeller 9, different aircraft 200 can be tested, thereby improving the versatility of the aircraft power test device 100. In addition, the motor controller 82 receives instructions and monitors the operating status of the motor 81, so as to realize the precise adjustment of the motor 81, and the motor controller 82 can adjust the speed, steering and other parameters of the motor 81 according to the needs of the aircraft 200, and further monitor the test process of the aircraft power test device 100 on the aircraft 100.

[0068] Optionally, the sensor assembly includes at least one of a voltage sensor, a current sensor, a photoelectric speed sensor, a temperature sensor and a vibration acceleration sensor. Figure 8As shown, the voltage of the corresponding motor 81, the current of the motor 81, the speed of the propeller 9 and the temperature of the motor 81 are measured in real time through a voltage sensor, a current sensor, a photoelectric speed sensor and a temperature sensor, and the measured data are converted into signals and transmitted to the data acquisition system 4. The calibration of a single and multiple power systems composed of the drive mechanism 8 and the propeller 9 and the verification of the logical functions of different systems are realized through real-time transient or steady-state measurement of voltage, current, speed and temperature.

[0069] In some embodiments of the utility model, the support arm 7 and the upper base plate 11 are connected by bolts, thereby realizing the connection between the support arm 7 and the stand 1. Furthermore, a positioning pin is provided at one end of the support arm 7 close to the stand 1, and the positioning pin cooperates with the positioning hole of the upper base plate 11 to facilitate the connection between the support arm 7 and the upper base plate 11, thereby reducing the difficulty of assembly.

[0070] In some embodiments of the utility model, the data acquisition system 4 includes a mounting bracket 41 and a data acquisition package 42, the data acquisition package 42 includes a data acquisition power supply module and a data acquisition computer, the mounting bracket 41 is located between the upper base plate 11 and the lower base plate 12 and is respectively connected to the upper base plate 11 and the lower base plate 12 by bolts, the data acquisition package 42 is located on the mounting bracket 41, the data acquisition power supply module and the data acquisition computer are respectively communicated with the sensor assembly, thereby realizing the connection between the data acquisition system 4 and the stand 1.

[0071] In some embodiments of the present invention, Figure 1 and Figure 7-10 As shown, the aircraft power test device 100 also includes a flight control power supply system 5 and a distribution box 6. The flight control power supply system 5 is connected to the drive mechanism 8 in communication and is arranged on the test bench 1. The distribution box 6 is connected to the high-voltage power supply. The distribution box 6 is located on the test bench 1. The wiring harness led out of the distribution box 6 is connected to each motor controller 82 in turn. Thus, the high-voltage power supply distributes power to multiple motor controllers 82 of multiple drive mechanisms 8 through the distribution box 6, and the flight control power supply system 5 controls the operation of the corresponding motors 81 through the multiple motor controllers 82, so that the multiple propellers 9 on the multiple arms 7 can run simultaneously or separately, thereby realizing the joint debugging, functional verification, and logic optimization of the power system composed of the drive mechanism 8 and the propeller 9, the high-voltage power supply system, and the flight control power supply system 5.

[0072] Furthermore, if Figure 1 As shown, the power distribution box 6 is located at the upper end of the upper base plate 11 and is connected to the upper base plate 11. The wiring harness led out of the power distribution box 6 is connected to the motor controller 82 and the motor 81 in sequence, and the rotor of the motor 81 is connected to the propeller 9. Thus, the high-voltage power supply is supplied to the motor 81 through the power distribution box 6 and the motor controller 82 in sequence.

[0073] Furthermore, the stand 1 also includes an assembly plate 14, which is located at the upper end of the upper base plate 11 and is connected to the upper base plate 11 and one end of the propeller 9 close to the upper base plate 11. The distribution box 6 is located at the upper end of the assembly plate 14 and is connected to the assembly plate 14, thereby realizing the connection between the distribution box 6 and the upper base plate 11.

[0074] Furthermore, the support arm 7 is provided with a motor mounting seat for mounting the motor 81 and a motor controller mounting seat for mounting the motor controller 82, thereby facilitating the installation of the motor 81 through the motor mounting seat and facilitating the installation of the motor controller 82 through the motor controller mounting seat.

[0075] In some embodiments of the present invention, Figure 7 As shown, the flight control power supply system 5 includes a fixed plate 51 and a flight control power supply module 52. The fixed plate 51 is located between the upper base plate 11 and the lower base plate 12 and is connected to the upper base plate 11 and the lower base plate 12 respectively by bolts. The flight control power supply module 52 is located on the fixed plate 51 and is communicatively connected to the driving mechanism 8, thereby realizing the connection between the flight control power supply system 5 and the test bench 1.

[0076] In some embodiments of the present invention, the aircraft power test device 100 also includes a remote wireless measurement and control transmission system (not shown in the figure), which is connected to the test bench 1, and is respectively connected to the data acquisition system 4 and the flight control power supply system 5. Thus, the remote wireless measurement and control transmission system fuses the data signals collected by the data acquisition system 4 and the preferences of the flight control power supply system 5, and synchronizes and displays the data in the cloud through the radio station and 5G signal. The remote control personnel can access the cloud to display the data in real time through the computer, send control instructions to the flight control, realize the remote measurement and control closed loop, and thus realize remote wireless control, so that the staff can stay away from the test site of the aircraft power test device 100 to ensure safety.

[0077] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "illustrative embodiments", "examples", "specific examples", or "some examples" means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the utility model. In this specification, the schematic representation of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner.

[0078] Although the embodiments of the present invention have been shown and described, those skilled in the art will appreciate that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the claims and their equivalents.

Claims

1. An aircraft power test device, characterized in that: include: a stand for mounting the aircraft; A transfer assembly, wherein the transfer assembly includes a lifting mechanism and a moving mechanism, wherein the moving mechanism can move in a plane perpendicular to the up-down direction, and the lifting mechanism is arranged on the moving mechanism and connected to the stage, and is used to drive the stage to move along the up-down direction so that the stage can switch between a supporting state and a moving state. In the supporting state, the stage is supported on a placement surface for placing the moving mechanism, and in the moving state, the stage is suspended above the placement surface.

2. The aircraft power test device according to claim 1, characterized in that: The stand comprises: An upper bottom plate, the lifting mechanism being connected to the upper bottom plate; a lower bottom plate, the lower bottom plate being located below and spaced apart from the upper bottom plate; A column is arranged between the upper base plate and the lower base plate, and the upper and lower ends of the column are respectively connected to the upper base plate and the lower base plate.

3. The aircraft power test device according to claim 2, characterized in that: The moving mechanism comprises: A movable frame, the movable frame is located between the upper base plate and the lower base plate, and the lower end of the lifting mechanism is connected to the movable frame; A universal wheel is arranged at the lower end of the movable frame, and the lower bottom plate has a matching hole for the universal wheel to pass through.

4. The aircraft power test device according to claim 3, characterized in that: The movable frame includes a plurality of movable arms spaced apart along the circumferential direction of the frame, one end of the plurality of movable arms are connected to each other and to the lifting mechanism, and the other end extends radially outward from the frame and is provided with the universal wheel, and the matching holes are a plurality of holes that match one by one with the plurality of universal wheels.

5. The aircraft power test device according to claim 3, characterized in that: The movable frame is provided with a linear bearing, and the column is inserted into the linear bearing.

6. The aircraft power test device according to claim 5, characterized in that: The columns are multiple and spaced apart along the circumferential direction of the upper base plate, and the linear bearings are multiple and correspond one to one with the columns.

7. The aircraft power test device according to claim 1, characterized in that: Also includes: An anti-tilt assembly is arranged at the radial outer end of the frame, and the anti-tilt assembly is a plurality of assemblies spaced apart along the circumferential direction of the frame. In the supporting state, the lower end of the anti-tilt assembly is supported on a placement surface for placing the moving mechanism, and in the moving state, the lower end of the anti-tilt assembly is spaced apart from the placement surface for placing the moving mechanism.

8. The aircraft power test device according to claim 1, characterized in that: The aircraft comprises a plurality of arms, the plurality of arms are spaced apart along the circumferential direction of the platform, one end of each arm in the length direction is connected to the platform, and the other end is provided with a driving mechanism and a propeller, the driving mechanism comprises at least two motors and a plurality of motor controllers corresponding to the motors one by one, the propellers are a plurality corresponding to the motors one by one, and each motor is respectively connected to the corresponding propeller and the motor controller, and the aircraft power test device further comprises: A data acquisition system and a sensor assembly, wherein the data acquisition system is connected to the stand, the sensor assembly is arranged on the support arm, and the sensor assembly is communicatively connected to the data acquisition system.

9. The aircraft power test device according to claim 8, characterized in that: Also includes: A flight control power supply system, the flight control power supply system is communicatively connected with the driving mechanism and is arranged on the platform; A power distribution box is arranged on the stand, the power distribution box is connected to a high voltage power supply, and a wiring harness led out of the power distribution box is connected to each of the motor controllers in turn.

10. The aircraft power test device according to claim 1, characterized in that: Also includes: An adjustment foot cup is connected to the stand and is located between the stand and the placement surface. In the moving state, the adjustment foot cup is suspended above the placement surface. In the supporting state, the adjustment foot cup is used to adjust the distance between the stand and the placement surface.

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