阅读说明：本技术 旋翼无人机动力组件的性能测试装置 (Performance testing device for power assembly of rotor wing unmanned aerial vehicle ) 是由 韩金玉 王守志 刘琼 李磊 尹士轩 于 2020-12-07 设计创作，主要内容包括：本发明公开了一种旋翼无人机动力组件的性能测试装置,包括：设备台架、测力单元、测速单元、防护组件和操控显示单元。设备台架用于固定电气器件,采集无人机旋翼动力组件的电流与电压参数,支撑测力单元、测速单元、防护组件和显示单元。测力单元用于固定旋翼无人机动力组件,同时采集旋翼升力数据；测速单元用于采集旋翼转速数据；防护组件用于操作人员的安全防护；操控显示单元用于固定电源及信号接口、显示组件。本发明的目的在于提供一种旋翼无人机动力组件的性能测试装置,能够采集测量动力组件的升力、转速、电流、电压等数据信息,为分析旋翼无人机动力组件的性能实验及分析提供实验装备。(The invention discloses a performance testing device of a power assembly of a rotor wing unmanned aerial vehicle, which comprises: the device comprises a device rack, a force measuring unit, a speed measuring unit, a protection assembly and a control display unit. The equipment rack is used for fixing an electrical device, collecting current and voltage parameters of a rotor power assembly of the unmanned aerial vehicle, and supporting the force measuring unit, the speed measuring unit, the protective assembly and the display unit. The force measuring unit is used for fixing a power assembly of the rotor unmanned aerial vehicle and collecting lift force data of the rotor at the same time; the speed measuring unit is used for acquiring the rotating speed data of the rotor wing; the protection component is used for protecting the safety of operators; the control display unit is used for fixing the power supply, the signal interface and the display component. The invention aims to provide a performance testing device of a power assembly of a rotor wing unmanned aerial vehicle, which can collect and measure data information of the power assembly, such as lift force, rotating speed, current, voltage and the like, and provides experimental equipment for performance experiment and analysis of the power assembly of the rotor wing unmanned aerial vehicle.)

1. The utility model provides a rotor unmanned aerial vehicle power component's capability test device which characterized in that comprises equipment rack (1), dynamometry unit (2), unit (3) tests the speed, protection component (4) and control display element (5). The equipment rack (1) is used for fixing an electrical device; the force measuring unit (3) is fixed on the equipment rack (1); the speed measuring unit (3) is fixed on the equipment rack (1); the protection component (4) is fixed on the equipment rack (1); the control display unit (5) is fixed on the equipment rack (1).

2. The device of claim 1, wherein the device is configured to test performance of a rotorcraft power module, the device comprising: the force measuring unit (2) comprises a motor fixing disc (9), a support rod (10), a dowel bar (11), a dowel bar support (12), a lever suspension beam (13), a horizontal bubble (14), a lever support (15), a suspension beam middle shaft (26), a rolling bearing (27) positioning ring (28), a support end cover (29), a sensor upper support (16), a connecting rod (17), a tension sensor (18), an adjusting screw rod (19), a sensor lower support (20), a balance block (21) and the like. The motor fixing disc (9) is fixed on the support rod (10) through a screw; the support rod (10) is arranged on the dowel bar (11) through a pin shaft; the dowel bar (11) is of a hollow structure and is fixed on the dowel bar support (12) through a pin shaft; the dowel bar support (12) is fixed on the lever suspension beam (13) through a screw; the lever suspension beam (13) is provided with a square hole, a fixed round hole and a force measuring sensor connecting round hole; the horizontal bubble (14) is arranged in a square hole of the lever suspension beam (13) in a gluing way; the lever support (15) is provided with a bearing hole and a fixing hole and is fixed on the equipment rack (1) through a screw; the outer ring of the rolling bearing (27) is in transition fit with the inner ring of the bearing hole of the lever support (15); the suspension beam center shaft (26) is in transition fit with a fixed round hole of the lever suspension beam (13) and is in transition fit with an inner ring of the rolling bearing (27); the support end cover (29) is in screw connection with the lever support (15) and is used for sealing and limiting the suspension beam middle shaft (26); the sensor lower support (20) is mounted on the lever suspension beam (13) through a screw; the adjusting screw rod (19) is connected with the lower sensor support (20) through a double-headed screw; one end of the adjusting screw rod (19) is connected to the double-ended screw in a threaded manner, and the other end of the adjusting screw rod is connected to the tension sensor (18) in a threaded manner; the tension sensor (18) is connected to the connecting rod (17) in a threaded manner; the connecting rod (17) is fixed on the sensor upper support (16); the sensor upper support (16) is in threaded connection with the equipment rack (1); the balance block (21) is provided with a square hole, is arranged at the tail end of the suspension beam center shaft (26) and is used for leveling the suspension beam center shaft (26).

3. The device of claim 1, wherein the device is configured to test performance of a rotorcraft power module, the device comprising: the speed measuring unit (3) comprises a horizontal guide plate (39), an inclined support (40), a movable guide seat (36), a guide seat pressing plate (38), a guide seat pulling plate (42), a pulling bottom rod (35), a locking nut (34), a pulling rod (33) and the like, wherein the horizontal guide plate (39) is of an open-ended structure in a shape like a Chinese character 'hui', the upper surface of the horizontal guide plate is provided with a straight guide groove and a fixing round hole, the lower surface of the horizontal guide plate is provided with a supporting round hole, and the horizontal guide plate is fixed on the equipment rack (1) through the fixing round hole; the upper end of the inclined support (40) is fixed on the horizontal guide plate (39), and the lower end of the inclined support is fixed on the equipment rack (1) and is used for supporting the horizontal guide plate (39); the guide seat pressing plate (38) is of a three-step flat plate structure, is fixed on the horizontal guide plate (39) and is arranged in the straight guide groove of the horizontal guide plate (39); the guide seat pulling plate (42) and the guide seat pressing plate (38) are connected together through adjusting screws, and an upper plate of the horizontal guide plate (39) is located between the guide seat pulling plate and the guide seat pressing plate; the drawing bottom rod (35) is of a hollow structure, a plurality of grooves are formed in the upper portion of the drawing bottom rod in the circumferential direction, and the drawing bottom rod is fixed on the movable guide seat (36) through pin connection; the drawing rod (33) is arranged in a middle hole of the drawing bottom rod (35) and is locked by the locking nut (34); the speed measuring sensor (32) is in threaded connection with the upper part of the drawing rod (33).

4. The device of claim 1, wherein the device is configured to test performance of a rotorcraft power module, the device comprising: the protective assembly (4) comprises a fan-shaped net rack, a net wire fixing strip, a protective bracket and a protective net wire, wherein the net wire fixing strip is provided with a series of round holes and is welded on the inner edge of the fan-shaped net rack; the protective net wire is arranged on the net wire fixing strip; the protective bracket is welded on the fan-shaped net rack and connected on the equipment rack through bolts.

5. The device of claim 1, wherein the device is configured to test performance of a rotorcraft power module, the device comprising: the control display unit (5) comprises a control box, a display screen, a switch, an indicator lamp, a signal line interface and a power line interface, and the control box is connected to the desktop of the equipment rack through a bolt; the display screen is fixed on the control box and used for displaying real-time test data; the power supply interface and the signal line interface are fixed on the control box; the indicator light is fixed on the control box and used for indicating the power-on and working states of the equipment.

6. The device of claim 1, wherein the device is configured to test performance of a rotorcraft power module, the device comprising: the equipment rack comprises a steel frame and a storage plate.

Technical Field

The invention belongs to the technical field of devices for testing and experiments of power parameters of a power system of a rotor wing unmanned aerial vehicle, and particularly relates to a testing device for the power system of the rotor wing unmanned aerial vehicle.

Background

At present, the unmanned aerial vehicle technology develops rapidly, and unmanned aerial vehicle application continuously expands. The power system is a key component of the unmanned aerial vehicle and is also a key factor influencing the performance of the unmanned aerial vehicle. The accurate measurement of the performance parameters of the unmanned aerial vehicle power system is the key work for researching and improving the power performance of the unmanned aerial vehicle. But in the current market, the unmanned aerial vehicle power system testing device is less; the existing testing device has the problems of incomplete or single testing parameters, large ground effect and the like.

Disclosure of Invention

The invention aims to provide a testing device for a power system of a rotor wing unmanned aerial vehicle, which is used for solving the problems in the background technology.

In order to achieve the purpose, the invention provides the following technical scheme: the utility model provides a rotor unmanned aerial vehicle power component's capability test device which characterized in that comprises equipment rack (1), dynamometry unit (2), unit (3) tests the speed, protection component (4) and control display element (5). The equipment rack (1) is used for fixing an electrical device; the force measuring unit (3) is fixed on the equipment rack (1); the speed measuring unit (3) is fixed on the equipment rack (1); the protection component (4) is fixed on the equipment rack (1); the control display unit (5) is fixed on the equipment rack (1).

Preferably, the force measuring unit (2) comprises a motor fixing disc (9), a support rod (10), a dowel bar (11), a dowel bar support (12), a lever suspension beam (13), a horizontal bubble (14), a lever support (15), a suspension beam middle shaft (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 rod (19), a sensor lower support (20), a balance block (21) and the like. The motor fixing disc (9) is fixed on the support rod (10) through a screw; the support rod (10) is arranged on the dowel bar (11) through a pin shaft; the dowel bar (11) is of a hollow structure and is fixed on the dowel bar support (12) through a pin shaft; the dowel bar support (12) is fixed on the lever suspension beam (13) through a screw; the lever suspension beam (13) is provided with a square hole, a fixed round hole and a force measuring sensor connecting round hole; the horizontal bubble (14) is arranged in a square hole of the lever suspension beam (13) in a gluing way; the lever support (15) is provided with a bearing hole and a fixing hole and is fixed on the equipment rack (1) through a screw; the outer ring of the rolling bearing (27) is in transition fit with the inner ring of the bearing hole of the lever support (15); the suspension beam center shaft (26) is in transition fit with a fixed round hole of the lever suspension beam (13) and is in transition fit with an inner ring of the rolling bearing (27); the support end cover (29) is in screw connection with the lever support (15) and is used for sealing and limiting the suspension beam middle shaft (26); the sensor lower support (20) is mounted on the lever suspension beam (13) through a screw; the adjusting screw rod (19) is connected with the lower sensor support (20) through a double-headed screw; one end of the adjusting screw rod (19) is connected to the double-ended screw in a threaded manner, and the other end of the adjusting screw rod is connected to the tension sensor (18) in a threaded manner; the tension sensor (18) is connected to the connecting rod (17) in a threaded manner; the connecting rod (17) is fixed on the sensor upper support (16); the sensor upper support (16) is in threaded connection with the equipment rack (1); the balance block (21) is provided with a square hole, is arranged at the tail end of the suspension beam center shaft (26) and is used for leveling the suspension beam center shaft (26).

Preferably, the speed measuring unit (3) comprises a horizontal guide plate (39), an inclined support (40), a movable guide seat (36), a guide seat pressing plate (38), a guide seat pulling plate (42), a pulling bottom rod (35), a locking nut (34), a pulling rod (33) and the like, the horizontal guide plate (39) is of an open-square-shaped structure, the upper surface of the horizontal guide plate is provided with a straight guide groove and a fixing round hole, the lower surface of the horizontal guide plate is provided with a supporting round hole, and the horizontal guide plate is fixed on the equipment rack (1) through the fixing round hole by a screw; the upper end of the inclined support (40) is fixed on the horizontal guide plate (39), and the lower end of the inclined support is fixed on the equipment rack (1) and is used for supporting the horizontal guide plate (39); the guide seat pressing plate (38) is of a three-step flat plate structure, is fixed on the horizontal guide plate (39) and is arranged in the straight guide groove of the horizontal guide plate (39); the guide seat pulling plate (42) and the guide seat pressing plate (38) are connected together through adjusting screws, and an upper plate of the horizontal guide plate (39) is located between the guide seat pulling plate and the guide seat pressing plate; the drawing bottom rod (35) is of a hollow structure, a plurality of grooves are formed in the upper portion of the drawing bottom rod in the circumferential direction, and the drawing bottom rod is fixed on the movable guide seat (36) through pin connection; the drawing rod (33) is arranged in a middle hole of the drawing bottom rod (35) and is locked by the locking nut (34); the speed measuring sensor (32) is in threaded connection with the upper part of the drawing rod (33).

Preferably, the protection assembly (4) comprises a fan-shaped net rack, a net line fixing strip, a protection bracket and a protection net line, wherein the net line fixing strip is provided with a series of round holes and welded on the inner edge of the fan-shaped net rack; the protective net wire is arranged on the net wire fixing strip; the protective bracket is welded on the fan-shaped net rack and connected on the equipment rack through bolts.

Preferably, 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, and the control box is connected to the desktop of the equipment rack through a bolt; the display screen is fixed on the control box and used for displaying real-time test data; the power supply interface and the signal line interface are fixed on the control box; the indicator light is fixed on the control box and used for indicating the power-on and working states of the equipment.

Preferably, the equipment rack comprises a steel frame and a storage tray.

The invention has the beneficial effects that: the rotor unmanned aerial vehicle power assembly performance testing device has the performance testing function of the rotor unmanned aerial vehicle power assembly, can collect and measure data information of the power assembly such as lift force, rotating speed, current, voltage and the like, and provides experimental equipment for performance experiments and performance analysis of the rotor unmanned aerial vehicle power assembly.

Drawings

Fig. 1 is an isometric view of the present invention.

Fig. 2 is an isometric view of a component of the force cell (2) of the present invention.

FIG. 3 is a sectional view A-A of the force-measuring cell (2) according to the invention.

Fig. 4 is a fixed disc component for testing the whole unmanned aerial vehicle.

Fig. 5 is an isometric view of a component of the tachometer unit (3) of the present invention.

Fig. 6 is a B-B cross-sectional view of the tacho unit (3) of the present invention.

Detailed Description

The following detailed description of the preferred embodiments will be made with reference to the accompanying drawings.

In order to solve the problems that the existing testing device is incomplete or single in testing parameters, large in ground effect and the like, the invention provides the device for testing the dynamic performance of the power system of the rotor wing unmanned aerial vehicle, which can test the performance parameters of the power system of the unmanned aerial vehicle, such as lift force, current, voltage, rotating speed and the like, and can also carry out lift effect and paddle effect experiments, load factor experiments and the like of the rotor wing unmanned aerial vehicle.

The invention idea of the invention is as follows: the invention provides a lever type unmanned aerial vehicle power performance testing device, which is characterized in that a tested object is far away from the ground through a support rod, the lifting force of an unmanned aerial vehicle is measured in a real flight state, the ground effect is reduced, and the measurement precision is improved; synchronously measuring related performance parameters of the unmanned aerial vehicle power system by adopting a tension sensor, a photoelectric sensor and a voltage and current sensor; comprises an equipment rack, a force measuring unit 2, a speed measuring unit 3, a protection component 4 and an operation display unit 5 which are fixed on the equipment rack.

The lower side of the equipment rack 1 is provided with a storage box 6, the right end of the equipment rack is connected with a push rod 7 through a stud, the bottom end of the equipment rack is provided with a caster 8, the upper part of the equipment rack is provided with a table board, and an electric appliance fixing plate is arranged below the table board and used for installing and fixing a switching power supply, a current sensor, a voltage sensor and a data acquisition card.

The force measuring unit 2 is fixed on the equipment rack 1 through a lever support 15 and a sensor upper support 16 in a bolt connection mode. The lever suspension beam 13 is mounted on the lever support 15 through a suspension beam middle shaft 26, a rolling bearing 27 and a positioning ring 28, and a support end cover 29 is mounted on the lever support 15 in a screw connection mode. The middle part of the left end of the lever suspension beam 13 is provided with a square hole for glue joint installation of a horizontal bubble 14, and the horizontal bubble 14 is used for indicating whether the lever suspension beam 13 is in a horizontal position. And a round hole is formed at the left end of the lever suspension beam 13 and used for connecting and installing the dowel bar support 12 through a screw. Round holes and pin holes are formed above the dowel bar support 12 and used for installing and fixing the dowel bars 11. The main body of the dowel bar 11 is a hollow round tube, a support bar 10 is arranged above the dowel bar in a pin connection mode, and the support bar 10 is provided with a motor fixing disc 9 in a screw connection mode. And a round hole is formed in the middle of the right end of the lever suspension beam 13 and used for being connected with the lower sensor support 20 through a bolt. The upper part of the sensor lower support 20 is provided with a unthreaded hole for connecting an adjusting screw rod 19 through a screw. The adjusting screw is provided with a tension sensor 18 through a stud. The tension sensor 18 is mounted on the sensor upper support 16 by a connecting rod 17. The left end of the lever suspension beam 13 is provided with a balance block 21 in a loose fit mode, the lower portion of the balance block 21 is provided with a threaded hole, a balance block lower baffle 22 is installed in a screw connection mode, and the middle portion of the balance block lower baffle 22 is provided with a threaded hole for installing a fastening screw 23. When the balance weight 21 is moved and the horizontal position of the lever suspension beam 13 is adjusted, the fastening screw 23 is loosened; after adjustment, the fastening screw 23 is tightened when the lever suspension beam 13 is in the horizontal position. In addition, when the device is used for testing the whole unmanned aerial vehicle, take off support pole 10 together with motor fixed disk 9, install the unmanned aerial vehicle fixed part that unmanned aerial vehicle fixed disk 31 and unmanned aerial vehicle support pole 31 constitute on dowel steel 11 for the lift test of unmanned aerial vehicle whole.

The speed measuring unit 3 comprises a horizontal guide plate 39, an inclined support 40, a movable guide seat 36, a guide seat pressing plate 38, a guide seat pulling plate 42, a pulling bottom rod 35, a locking nut 34, a pulling rod 33 and the like. Two unthreaded holes are formed in the right end of the horizontal guide plate 39 and are mounted on the equipment rack 1 through bolts; the inclined support 40 is mounted on the horizontal guide plate 39 through the left end of the bolt, and the right end of the inclined support is mounted on the equipment rack 1 and used for supporting the horizontal guide plate 39. The lower end of the movable guide seat 36 is provided with a guide seat pressing plate 38 through a screw, and the guide seat pressing plate 38 is arranged in a middle groove of a horizontal guide plate 39. The two ends of the guide seat pressing plate 38 are provided with unthreaded holes, the two ends of the guide seat pulling plate 42 are provided with threaded holes, the guide seat pulling plate 42 is tightly installed through the unthreaded holes by adopting locking screws 37, and the upper panel of the horizontal guide plate 39 is positioned between the guide seat pressing plate 38 and the guide seat pulling plate 42; when the locking screw 37 is loosened, the movable guide 36 can move left and right on the horizontal guide plate 39, and the horizontal position between the speed measuring sensor 32 and the object to be measured is adjusted. The movable guide seat 36 is provided with a circular mounting hole for mounting the drawing bottom rod 35 and is connected and fixed by a pin; the drawing bottom rod 35 is a hollow round pipe, the upper portion of the drawing bottom rod is provided with external threads and a conical grid structure, and the drawing rod 33 is installed in a round hole of the drawing bottom rod 35 and fastened and locked through a locking nut 34. The vertical position between the speed measuring sensor 32 and the measured object can be adjusted by loosening the locking nut 34.

The control display unit 5 is installed on the desktop of the equipment rack 1 through screws, and a power switch, an indicator light, a display screen and a power connector are installed on the control display unit.

The protection component 4 is connected to the left end face of the platform steel frame through a bolt and is fan-shaped.

Before a test experiment, a tested object motor or an unmanned aerial vehicle is integrally arranged on a motor fixing disc 9 or an unmanned aerial vehicle fixing disc 30, then a balance block 21 is adjusted to enable a lever suspension beam 13 to be horizontal by observing a horizontal bubble 14, and meanwhile, a tension sensor 18 is enabled to return to zero; loosening the locking screw 37, adjusting the horizontal position of the movable guide seat 36 to enable the speed measuring sensor 32 to be in a proper horizontal position, and then screwing down the locking screw 37; and loosening the locking nut 34, adjusting the drawing rod 33 to enable the speed measuring sensor 32 to be in a proper vertical position, and then screwing the locking nut 34. During testing, a motor or unmanned aerial vehicle complete machine control signal is given, the rotor of the tested object rotates to generate lift force, the tension sensor 18 detects the lift force, the speed sensor 32 obtains the rotating speed of the motor through testing, and meanwhile, the voltage and the current sensor synchronously detect to obtain voltage and current.

It should be noted that, for those skilled in the art, without departing from the principle of the present invention, several improvements and modifications can be made, and these improvements and modifications should also be construed as the protection scope of the present invention.