Performance test device for rotor UAV power components

Abstract

The present invention discloses a performance testing device for a rotor UAV power assembly, comprising: an equipment stand, a force measuring unit, a speed measuring unit, a protection assembly and a control and display unit. The equipment stand is used to fix electrical components, collect current and voltage parameters of the UAV rotor power assembly, and support the force measuring unit, the speed measuring unit, the protection assembly and the display unit. The force measuring unit is used to fix the rotor UAV power assembly and collect rotor lift data at the same time; the speed measuring unit is used to collect rotor speed data; the protection assembly is used for the safety protection of operators; the control and display unit is used to fix the power supply and signal interface, and the display assembly. The purpose of the present invention is to provide a performance testing device for a rotor UAV power assembly, which is capable of collecting and measuring data information such as lift, speed, current, voltage, etc. of the power assembly, and provides experimental equipment for performance experiments and analysis of rotor UAV power assemblies.

Description

Technical Field

[0001] The invention belongs to the technical field of devices for testing and experimenting power parameters of a power system of a rotary-wing unmanned aerial vehicle, and in particular relates to a performance testing device for a power component of a rotary-wing unmanned aerial vehicle. Background Art

[0002] At present, UAV technology is developing rapidly, and the application fields of UAV are constantly expanding. The power system is a key component of UAV and a key factor affecting the performance of UAV. Accurately measuring the performance parameters of UAV power system is the key work to study and improve the power performance of UAV. However, there are few UAV power system test devices on the current market; the existing test devices have problems such as incomplete or relatively single test parameters and large ground effect. Summary of the invention

[0003] The purpose of the present invention is to provide a performance testing device for a rotor UAV power assembly to solve the problems existing in the background technology.

[0004] To achieve the above-mentioned purpose, the present invention provides the following technical solution: a performance test device for a rotorcraft unmanned aerial vehicle power assembly, characterized in that it is composed of an equipment stand (1), a force measuring unit (2), a speed measuring unit (3), a protection component (4) and a control and display unit (5). The equipment stand (1) is used to fix electrical components; the force measuring unit (3) is fixed on the equipment stand (1); the speed measuring unit (3) is fixed on the equipment stand (1); the protection component (4) is fixed on the equipment stand (1); and the control and display unit (5) is fixed on the equipment stand (1).

[0005] Preferably, the force measuring unit (2) includes a motor fixing plate (9), a support rod (10), a force transmission rod (11), a force transmission rod support (12), a lever suspension beam (13), a level bubble (14), a lever support (15), a suspension beam center axis (26), a rolling bearing (27), a positioning ring (28), a support end cover (29), a sensor upper support (16), a connecting rod (17), a tension sensor (18), an adjusting screw (19), a sensor lower support (20), a balancing block (21), etc. The motor fixing plate (9) is fixed to the support rod (10) by screws; the support rod (10) is installed on the force transmission rod (11) by a pin shaft; the force transmission rod (11) is a hollow structure and is fixed to the force transmission rod support (12) by a pin shaft; the force transmission rod support (12) is fixed to the lever suspension beam (13) by screws; the lever suspension beam (13) is provided with a square hole, a fixed circular hole, and a force sensor connecting circular hole; the level bubble (14) is glued and installed in the square hole of the lever suspension beam (13); the lever support (15) is provided with a bearing hole and a fixed hole, and is fixed to the equipment stand (1) by screws; the outer ring of the rolling bearing (27) is transitionally matched with the inner ring of the bearing hole of the lever support (15); the suspension beam center axis (26) is transitionally matched with the fixed circular hole of the lever suspension beam (13) and the rolling bearing (2 7) inner ring transition fit; the support end cover (29) is screwed to the lever support (15) for sealing and limiting the suspension beam center axis (26); the sensor lower support (20) is installed on the lever suspension beam (13) by screws; the adjusting screw (19) is connected to the sensor lower support (20) by stud screws; one end of the adjusting screw (19) is threadedly connected to the stud screw, and the other end is threadedly connected to the tension sensor (18); the tension sensor (18) is threadedly connected to the connecting rod (17); the connecting rod (17) is fixed to the sensor upper support (16); the sensor upper support (16) is threadedly connected to the equipment stand (1); the balancing block (21) is provided with a square hole and is installed at the end of the suspension beam center axis (26) for leveling the suspension beam center axis (26).

[0006] Preferably, the speed measuring unit (3) comprises a horizontal guide plate (39), an inclined support (40), a movable guide seat (36), a guide seat pressure plate (38), a guide seat pull plate (42), a pull-out bottom rod (35), a locking nut (34), a pull-out rod (33), etc. The horizontal guide plate (39) is an open U-shaped structure, with a straight guide groove and a fixing circular hole on the upper surface, and a supporting circular hole on the lower surface, and is fixed to the equipment stand (1) by screws through the fixing circular hole; the upper end of the inclined support (40) is fixed to the horizontal guide plate (39), and the lower end is fixed to the equipment stand (1), so as to support the horizontal guide plate (39); the guide seat pressure plate (38) is a three-step flat plate structure, fixed on the horizontal guide plate (39), and placed in the straight guide groove of the horizontal guide plate (39); the guide seat pull plate (42) and the guide seat pressure plate (38) are connected together by adjusting screws, and the upper plate of the horizontal guide plate (39) is located between the two; the pull-out bottom rod (35) is a hollow structure, with a plurality of slots circumferentially provided on the upper part, and is fixed to the movable guide seat (36) by pin connection; the pull-out rod (33) is installed in the middle hole of the pull-out bottom rod (35), and is locked by the locking nut (34); the speed sensor (32) is threadedly connected to the upper part of the pull-out rod (33).

[0007] Preferably, the protection component (4) comprises a fan-shaped grid, a grid cable fixing strip, a protection bracket, and a protection grid cable, wherein the grid cable fixing strip has a series of circular holes and is welded to the inner edge of the fan-shaped grid; the protection grid cable is installed on the grid cable fixing strip; the protection bracket is welded to the fan-shaped grid and is connected to the equipment stand by bolts.

[0008] Preferably, the control and display unit (5) comprises a control box, a display screen, a switch, an indicator light, a signal line interface, and a power line interface, wherein the control box is connected to the desktop of the equipment stand by bolts; the display screen is fixed to the control box for displaying real-time test data; the power interface and the signal line interface are fixed to the control box; and the indicator light is fixed to the control box for indicating that the equipment is powered on and in working status.

[0009] Preferably, the equipment stand comprises a steel frame and a storage tray.

[0010] The beneficial effects of the present invention are as follows: the present invention has the performance testing function of the rotor UAV power component, can collect and measure data information such as lift, rotation speed, current, voltage, etc. of the power component, and provides experimental equipment for the performance experiment and performance analysis of the rotor UAV power component. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] Figure 1 It is an axonometric view of the present invention.

[0012] Figure 2It is an axonometric view of the components of the force measuring unit (2) of the present invention.

[0013] Figure 3 It is a cross-sectional view taken along line AA of the force measuring unit (2) of the present invention.

[0014] Figure 4 The invention is a fixing plate assembly used for testing a complete unmanned aerial vehicle.

[0015] Figure 5 It is an axonometric diagram of the components of the speed measuring unit (3) of the present invention.

[0016] Figure 6 It is a BB cross-sectional view of the speed measuring unit (3) of the present invention. DETAILED DESCRIPTION

[0017] The specific implementation of the present invention is described in detail below with reference to the accompanying drawings and preferred embodiments.

[0018] In order to solve the problems of incomplete or relatively single test parameters and large ground effect of existing test devices, the present invention provides a power performance test device for a rotor UAV power system, which can test performance parameters such as lift, current, voltage, and speed of the UAV power system, and can also carry out lift efficiency and propeller efficiency experiments, load factor experiments, etc. of the rotor UAV.

[0019] The inventive concept of the present invention is as follows: the present invention provides a lever-type UAV power performance testing device, which uses a support rod to keep the object to be tested away from the ground and measures the lift of the UAV in a real flight state, thereby reducing the ground effect and improving the measurement accuracy; using a tension sensor, a photoelectric sensor, a voltage and current sensor to synchronously measure the relevant performance parameters of the UAV power system; including an equipment stand, and a force measuring unit 2, a speed measuring unit 3, a protection component 4 and a control display unit 5 fixed thereon.

[0020] A storage box 6 is arranged at the lower side of the equipment stand 1, a push rod 7 is arranged at the right end through a stud connection, a caster 8 is arranged at the bottom end, a table is arranged at the upper part, and an electrical appliance fixing plate is installed under the table for installing and fixing a switching power supply, a current sensor, a voltage sensor and a data acquisition card.

[0021] The force measuring unit 2 is fixed to the equipment stand 1 by bolt connection through the lever support 15 and the upper support 16 of the sensor. The lever suspension beam 13 is installed on the lever support 15 through the suspension beam middle axis 26, the rolling bearing 27, and the positioning ring 28, and the support end cover 29 is installed on the lever support 15 by screw connection. A square hole is opened in the middle of the left end of the lever suspension beam 13 for gluing and installing the level bubble 14, and the level bubble 14 is used to indicate whether the lever suspension beam 13 is in a horizontal position. A round hole is opened at the left end of the lever suspension beam 13 for screw connection and installation of the force transmission rod support 12. A round hole and a pin hole are opened above the force transmission rod support 12 for installing and fixing the force transmission rod 11. The main body of the force transmission rod 11 is a hollow round tube, and the support rod 10 is installed above it by pin connection. The motor fixing plate 9 is installed on the support rod 10 by screw connection. A round hole is opened in the middle of the right end of the lever suspension beam 13 for bolt connection to the lower support 20 of the sensor. The upper part of the sensor lower support 20 is provided with a light hole for screwing the adjusting screw 19. The adjusting screw is provided with a tension sensor 18 through a stud. The tension sensor 18 is installed on the sensor upper support 16 through a connecting rod 17. The left end of the lever suspension beam 13 is provided with a balance block 21 in a loose fit manner. The lower part of the balance block 21 is provided with a threaded hole, and the balance block lower baffle 22 is installed in a screw connection manner. The middle part of the balance block lower baffle 22 is provided with a threaded hole for installing a fastening screw 23. When the balance block 21 is moved to adjust the horizontal position of the lever suspension beam 13, the fastening screw 23 is loosened; after adjustment, when the lever suspension beam 13 is in a horizontal position, the fastening screw 23 is tightened. In addition, when the device is used to test the entire drone, the support rod 10 together with the motor fixing plate 9 is removed, and the drone fixing component consisting of the drone fixing plate 31 and the drone support rod 31 is installed on the force transmission rod 11 for the lift test of the entire drone.

[0022] The speed measuring unit 3 is composed of a horizontal guide plate 39, an inclined support 40, a movable guide seat 36, a guide seat pressure plate 38, a guide seat pull plate 42, a pull-out bottom rod 35, a locking nut 34, a pull-out rod 33, etc. The right end of the horizontal guide plate 39 is provided with two light holes, and is installed on the equipment stand 1 by bolts; the inclined support 40 is installed on the horizontal guide plate 39 at the left end by bolts, and is installed on the equipment stand 1 at the right end, and is used to support the horizontal guide plate 39. The guide seat pressure plate 38 is installed at the lower end of the movable guide seat 36 by screws, and the guide seat pressure plate 38 is placed in the middle groove of the horizontal guide plate 39. Light holes are provided at both ends of the guide seat pressure plate 38, and threaded holes are provided at both ends of the guide seat pull plate 42. The guide seat pull plate 42 is fastened and installed through the light holes by means of locking screws 37. The upper panel of the horizontal guide plate 39 is located between the guide seat pressure plate 38 and the guide seat pull plate 42. When the locking screws 37 are loosened, the movable guide seat 36 can be moved left and right on the horizontal guide plate 39 to adjust the horizontal position between the speed sensor 32 and the object to be measured. The movable guide seat 36 is provided with a circular mounting hole for installing the pull-out bottom rod 35, and is fixed by a pin connection. The pull-out bottom rod 35 is a hollow circular tube, and an external thread and a conical grid structure are provided on the upper part. The pull-out rod 33 is installed in the circular hole of the pull-out bottom rod 35, and is fastened and locked by means of a locking nut 34. By loosening the locking nut 34, the vertical position between the speed sensor 32 and the object to be measured can be adjusted.

[0023] The control and display unit 5 is mounted on the desktop of the equipment stand 1 by screws, and a power switch, an indicator light, a display screen and a power connector are installed on the control and display unit 5.

[0024] The protection assembly 4 is connected to the left end surface of the platform steel frame by bolts and is fan-shaped.

[0025] Before the test experiment, the present invention installs the motor or drone of the object to be tested on the motor fixing plate 9 or the drone fixing plate 30, and then adjusts the balance block 21 by observing the level bubble 14 to make the lever suspension beam 13 horizontal, and at the same time, the tension sensor 18 is reset to zero; loosen the locking screw 37, adjust the horizontal position of the movable guide seat 36, and after the speed sensor 32 is in a suitable horizontal position, tighten the locking screw 37; loosen the locking nut 34, adjust the pull rod 33, and after the speed sensor 32 is in a suitable vertical position, tighten the locking nut 34. During the test, the motor or drone control signal is given, the rotor of the object to be tested rotates to generate lift, the tension sensor 18 detects the lift, the speed sensor 32 tests to obtain the motor speed, and the voltage and current sensors synchronously detect to obtain the voltage and current.

[0026] It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the principles of the present invention, and these improvements and modifications should also be regarded as within the scope of protection of the present invention.

Claims

1. A performance test device for a rotorcraft UAV power assembly, characterized in that: The device is composed of an equipment stand (1), a force measuring unit (2), a speed measuring unit (3), a protection component (4) and a control and display unit (5); the equipment stand (1) is used to fix electrical components; the force measuring unit (2) is fixed on the equipment stand (1); and the speed measuring unit (3) is fixed on the equipment stand (1); The protection component (4) is fixed on the equipment stand (1); the control display unit (5) is fixed on the equipment stand (1); The force measuring unit (2) comprises a motor fixing plate (9), a support rod (10), a force transmission rod (11), a force transmission rod support (12), a lever suspension beam (13), a level bubble (14), a lever support (15), a suspension beam center axis (26), a rolling bearing (27), a positioning ring (28), a support end cover (29), a sensor upper support (16), a connecting rod (17), a tension sensor (18), an adjusting screw (19), a sensor lower support (20) and a balancing block (21); the motor fixing plate (9) is fixed to the support by screws. The seat rod (10) is mounted on the force transmission rod (11) through a pin shaft; the force transmission rod (11) is a hollow structure and is fixed to the force transmission rod support (12) through a pin shaft; the force transmission rod support (12) is fixed to the lever suspension beam (13) through screws; the lever suspension beam (13) is provided with a square hole, a fixing round hole, and a force sensor connecting round hole; the level bubble (14) is glued and installed in the square hole of the lever suspension beam (13); the lever support (15) is provided with a bearing hole and a fixing hole and is fixed to the equipment through screws. The outer ring of the rolling bearing (27) is transitionally matched with the inner ring of the bearing hole of the lever support (15); the central axis of the suspension beam (26) is transitionally matched with the fixed circular hole of the lever suspension beam (13), and is transitionally matched with the inner ring of the rolling bearing (27); the support end cover (29) is screwed to the lever support (15) to seal and limit the central axis of the suspension beam (26); the lower support (20) of the sensor is installed on the lever suspension beam (13) by screws; the adjusting screw (19) is connected to the lower support (20) of the sensor The support (20) is connected by a stud screw; one end of the adjusting screw (19) is threadedly connected to the stud screw, and the other end is threadedly connected to the tension sensor (18); the tension sensor (18) is threadedly connected to the connecting rod (17); the connecting rod (17) is fixed to the upper support (16) of the sensor; the upper support (16) of the sensor is threadedly connected to the equipment stand (1); the balancing block (21) is provided with a square hole and is installed at the end of the lever suspension beam (13) for leveling the suspension beam center axis (26); The speed measuring unit (3) comprises a horizontal guide plate (39), an inclined support (40), a movable guide seat (36), a guide seat pressure plate (38), a guide seat pull plate (42), a pull-out bottom rod (35), a locking nut (34) and a pull-out rod (33); the horizontal guide plate (39) is an open U-shaped structure, with a straight guide groove and a fixing circular hole on the upper surface, and a supporting circular hole on the lower surface, and is fixed to the equipment stand (1) by screws through the fixing circular hole; the upper end of the inclined support (40) is fixed to the horizontal guide plate (39), and the lower end is fixed to the equipment stand (1), and is used to support the horizontal guide plate (39); the guide The seat pressure plate (38) is fixed on the horizontal guide plate (39) and placed in the straight guide groove of the horizontal guide plate (39); the guide seat pull plate (42) and the guide seat pressure plate (38) are connected together by adjusting screws, and the upper plate of the horizontal guide plate (39) is located between the two; the pull-out bottom rod (35) is a hollow structure, with a plurality of slots circumferentially provided on the upper part, and is fixed to the movable guide seat (36) by pin connection; the pull-out rod (33) is installed in the middle hole of the pull-out bottom rod (35) and is locked by the locking nut (34); the speed sensor (32) is threadedly connected to the upper part of the pull-out rod (33).

2. The performance test device for a rotorcraft UAV power assembly according to claim 1, characterized in that: The protection component (4) comprises a fan-shaped grid, a grid cable fixing strip, a protection bracket and a protection grid cable, wherein the grid cable fixing strip has a series of round holes and is welded to the inner edge of the fan-shaped grid; the protection grid cable is installed on the grid cable fixing strip; the protection bracket is welded to the fan-shaped grid and connected to the equipment stand by bolts.

3. The performance testing device for a rotorcraft UAV power assembly according to claim 1, characterized in that: The control display unit (5) comprises a control box, a display screen, a switch, an indicator light, a signal line interface, and a power line interface. The control box is connected to the desktop of the equipment stand by bolts; the display screen is fixed on the control box and is used to display real-time test data; the power line interface and the signal line interface are fixed on the control box; and the indicator light is fixed on the control box and is used to indicate that the equipment is powered on and in working condition.

4. The performance test device for a rotorcraft UAV power assembly according to claim 1, characterized in that: Equipment rack includes steel frame and storage tray.

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