CN204536507U - A kind of unmanned plane motor and blade matching performance testing apparatus - Google Patents

A kind of unmanned plane motor and blade matching performance testing apparatus Download PDF

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Publication number
CN204536507U
CN204536507U CN201520266455.8U CN201520266455U CN204536507U CN 204536507 U CN204536507 U CN 204536507U CN 201520266455 U CN201520266455 U CN 201520266455U CN 204536507 U CN204536507 U CN 204536507U
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China
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motor
bar
blade
unmanned plane
dynamometer
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CN201520266455.8U
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Chinese (zh)
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曹飞
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Beijing Zhongfei Aiwei Aerospace Technology Co Ltd
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Beijing Zhongfei Aiwei Aerospace Technology Co Ltd
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Abstract

The utility model relates to a kind of unmanned plane motor and blade matching performance testing apparatus, comprise measuring equipment case part and experiment frame part, described measuring equipment case part comprises supply unit, control device, timer, voltage table, dynamometer and tachometer gage, equipment box is provided with power switch, timer reset switch and motor speed adjusting knob; Experiment frame part comprises L-type bar, motor mounting plate, hinge base and device for measuring force, L-type bar comprises cross bar and montant, cross bar and montant junction are provided with hinge base, the other end of cross bar arranges device for measuring force, device for measuring force connects dynamometer, and montant is provided with motor, and motor connects blade, hinge base side is arranged on cross bar, and opposite side fixes on the ground.Advantage applies of the present utility model exists: the time-varying parameter that simultaneously can be obtained motor speed by various proving installation, can on ground in the face of the operating mode of blade and motor detects.

Description

A kind of unmanned plane motor and blade matching performance testing apparatus
Technical field
The utility model relates to unmanned air vehicle technique field, is specifically related to a kind of unmanned plane motor and blade matching performance testing apparatus.
Background technology
Unmanned plane is a kind of unmanned vehicle handled by radio robot or self presetting apparatus.
Unmanned plane all has larger application at military civil area at present.Especially at civil area, in the industry such as police, city management, agricultural, geology, meteorology, electric power, rescue and relief work, video capture, the purposes of unmanned plane is very extensive.
Existing technical scheme is by data determination blade model, motor model, the blade provided according to producer and motor data carry out selecting and mating, in practical flight, observe throttle working condition judge whether blade mates with motor with unmanned plane acceleration, the requirement of accurate match can not be reached, there is potential safety hazard or motor performance waste.
Usually adopt theoretical calculation, empirical estimating and directly carry out flying to observe the working condition of blade at present.The shortcoming of theoretical calculation and empirical estimating is can not accurately obtain machine operation parameter, has gap with actual conditions.Direct flight can bring a lot of unsafe factor, may cause crushing damage, there is very large hidden danger to unmanned plane.Each model blade and motor are difficult to make contrast.
Utility model content
The utility model, for overcoming deficiency of the prior art, provides a kind of unmanned plane motor and the blade matching performance testing apparatus of accurate performance coupling.
For achieving the above object, the utility model discloses following technical scheme:
A kind of unmanned plane motor and blade matching performance testing apparatus, comprise measuring equipment case part and experiment frame part, described measuring equipment case part comprises equipment box, equipment box comprises supply unit, control device, timer, voltage table, dynamometer and tachometer gage, control device connection timer, voltage table, dynamometer and tachometer gage, equipment box is provided with power switch, timer reset switch and motor speed adjusting knob, power switch connects supply unit, motor speed adjusting knob connection control device, timer reset switch connection timer; Experiment frame part comprises L-type bar, motor mounting plate, base and device for measuring force, L-type bar comprises cross bar and montant, cross bar and montant junction are provided with base, at the other end of cross bar, device for measuring force is set, device for measuring force is placed on the ground, the dynamometer of device for measuring force connection device case, montant top is provided with motor mounting plate, motor mounting plate is provided with motor, motor connection control device, motor-driven connects blade, and base is hinge base, hinge base side is arranged on cross bar by hinges, and opposite side fixes on the ground.
Further, described cross bar, montant are that rigid unitary connects.
Further, described device for measuring force is the combination unit of force block and dynamometer dynamometry part, and dynamometer dynamometry part is arranged on bottom force block.
Further, described force block and cross bar are for being rigidly connected.
Further, the rigid connector between force block and cross bar is rigid rod.
Further, described equipment box is also provided with timer display, voltage table display, dynamometer display and tachometer gage display.
Further, described timer display, voltage table display, dynamometer display and tachometer gage display are light-emitting diode display.
Further, described blade to montant produce the direction of pulling force be level left.
A kind of unmanned plane motor disclosed in the utility model and blade matching performance testing apparatus, have following beneficial effect:
The technical matters that the pulling force solving blade generation in prior art is not easily measured, can obtain the time-varying parameter of motor speed simultaneously by various proving installation, can on ground in the face of the operating mode of blade and motor detect.
Accompanying drawing explanation
Fig. 1 is the structural representation of measuring equipment case,
Fig. 2 is the structural representation of experiment frame part,
Fig. 3 is the stressed schematic diagram of experiment frame,
Wherein:
1-power switch 2-timer reset switch
3-motor speed adjusting knob 4-timer display
5-voltage table display 6-dynamometer display
7-tachometer gage display 8-motor mounting plate
9-blade 10-montant
11-hinges 12-hinge base
13-cross bar 14-device for measuring force
Embodiment
Also with reference to accompanying drawing, the utility model is further described below in conjunction with embodiment.
Described a kind of unmanned plane motor and blade matching performance testing apparatus comprise measuring equipment case part and experiment frame part.
Refer to Fig. 1, Fig. 1 is the structural representation of measuring equipment case.Described measuring equipment case part comprises equipment box, equipment box comprises supply unit, control device, timer, voltage table, dynamometer and tachometer gage, control device connection timer, voltage table, dynamometer and tachometer gage, equipment box is provided with power switch 1, timer reset switch 2 and motor speed adjusting knob 3, power switch 1 connects supply unit, motor speed adjusting knob 3 connection control device, timer reset switch 2 connection timer.
Refer to Fig. 2, Fig. 2 is the structural representation of experiment frame part.Described experiment frame part comprises L-type bar, motor mounting plate 8, base and device for measuring force 14, and L-type bar comprises cross bar 13 and montant 10, and cross bar 13 and montant 10 junction are provided with base; At the other end of cross bar 13, device for measuring force 14 is set, device for measuring force 14 is placed on the ground, the dynamometer of device for measuring force 14 connection device case, montant 10 top is provided with motor mounting plate 8, and motor mounting plate 8 is provided with motor, motor connection control device, motor-driven connects blade 9, base is hinge base 12, and hinge base 12 side is arranged on cross bar 13 by hinges 11, and opposite side fixes on the ground.
Consider actual needs, cross bar 13, montant 10 are rigid unitary connection; Device for measuring force 14 can be overall device for measuring force also can be the combination unit of force block and dynamometer dynamometry part, dynamometer dynamometry part is arranged on bottom force block, force block and cross bar are for being rigidly connected, and rigid connector is rigid rod, and rigid rod plays support and intermal force; Equipment box is also provided with timer display 4, voltage table display 5, dynamometer display 6 and tachometer gage display 7, above display is light-emitting diode display.
Refer to Fig. 3, Fig. 3 is the stressed schematic diagram of experiment frame.Main stressed as follows except gravity under nominal situation:
F tfor the pulling force that blade 9 produces, the direction that blade 9 pairs of montants 10 produce pulling force be level left;
F nfor device is subject to the acting force of ground (device for measuring force 14), corresponding, device to the pressure of device for measuring force 14 should be and F ndeng reverse greatly;
F oxfor hinge O place horizontal direction force;
F oyfor hinge O place vertical is stressed.
According to system balancing condition, O point equalising torque ∑ M o=0, after obtained A point stress value by device for measuring force 14, the pulling force that blade 9 produces can be obtained, reaction blade 9 working condition.
Principle illustrates:
Measurement parameter (unit): input voltage U (V), value of thrust F (N) working time t (s), rotating speed V (rad/min)
Voltage table: measuring voltage, makes motor work under rated voltage;
Dynamometer: measure device for measuring force 14 point stress value, thus calculate the pulling force that blade 9 produces;
Timer: surveying work time, obtains the accelerating sections time (from starting to nominal situation), the motor blade system working time under nominal situation;
Tachometer gage: measure motor speed, idler revolutions time non-loaded and the load speed after being connected with blade 9.
O place is hinges, and rotation axis OZ and OA axle, OB axle form right-handed system, and OA axle, OB axle are for being rigidly connected, and namely AOB is integrated, and are connected between AOB with base by hinges 11, and its motion state is can rotate around hinge axis OZ.
Produce thrust after blade 9 rotates, AOB has the trend rotated counterclockwise around OZ axle, and base produces pressure to device for measuring force thus, obtains required by data are, i.e. F n× OA=F r× OB.
When machine operation, can the parameter such as measuring voltage, rotating speed thus know machine operation situation, indirectly can know that blade produces pulling force size by dynamometer, finally provide reference for whether different blade mates with motor combination.
The above is only preferred implementation of the present utility model; should be understood that; for those of ordinary skill in the art; do not departing under prerequisite of the present utility model; the some improvement can also made the utility model and supplement; these improve and supplement, and also should be considered as protection domain of the present utility model.

Claims (8)

1. a unmanned plane motor and blade matching performance testing apparatus, it is characterized in that, comprise measuring equipment case part and experiment frame part, described measuring equipment case part comprises equipment box, equipment box comprises supply unit, control device, timer, voltage table, dynamometer and tachometer gage, control device connection timer, voltage table, dynamometer and tachometer gage, equipment box is provided with power switch, timer reset switch and motor speed adjusting knob, power switch connects supply unit, motor speed adjusting knob connection control device, timer reset switch connection timer, experiment frame part comprises L-type bar, motor mounting plate, base and device for measuring force, L-type bar comprises cross bar and montant, cross bar and montant junction are provided with base, at the other end of cross bar, device for measuring force is set, device for measuring force is placed on the ground, the dynamometer of device for measuring force connection device case, montant top is provided with motor mounting plate, motor mounting plate is provided with motor, motor connection control device, motor-driven connects blade, and base is hinge base, hinge base side is arranged on cross bar by hinges, and opposite side fixes on the ground.
2. a kind of unmanned plane motor according to claim 1 and blade matching performance testing apparatus, is characterized in that, described cross bar, montant are that rigid unitary connects.
3. a kind of unmanned plane motor according to claim 1 and blade matching performance testing apparatus, is characterized in that, described device for measuring force is the combination unit of force block and dynamometer dynamometry part, and dynamometer dynamometry part is arranged on bottom force block.
4. a kind of unmanned plane motor according to claim 3 and blade matching performance testing apparatus, is characterized in that, described force block and cross bar are for being rigidly connected.
5. a kind of unmanned plane motor according to claim 4 and blade matching performance testing apparatus, is characterized in that, the rigid connector between force block and cross bar is rigid rod.
6. a kind of unmanned plane motor according to claim 1 and blade matching performance testing apparatus, is characterized in that, described equipment box is also provided with timer display, voltage table display, dynamometer display and tachometer gage display.
7. a kind of unmanned plane motor according to claim 6 and blade matching performance testing apparatus, is characterized in that, described timer display, voltage table display, dynamometer display and tachometer gage display are light-emitting diode display.
8. a kind of unmanned plane motor according to claim 1 and blade matching performance testing apparatus, is characterized in that, described blade to montant produce the direction of pulling force be level left.
CN201520266455.8U 2015-04-28 2015-04-28 A kind of unmanned plane motor and blade matching performance testing apparatus Active CN204536507U (en)

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Application Number Priority Date Filing Date Title
CN201520266455.8U CN204536507U (en) 2015-04-28 2015-04-28 A kind of unmanned plane motor and blade matching performance testing apparatus

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Application Number Priority Date Filing Date Title
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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105116333A (en) * 2015-09-14 2015-12-02 南京工程学院 Measuring apparatus for motor tension linearity of multi-rotor type aircraft, and control system and method thereof
CN107192532A (en) * 2017-06-09 2017-09-22 昆明理工大学 A kind of measurement apparatus and measuring method of four-axle aircraft brushless electric machine thrust coefficient
CN107356433A (en) * 2017-06-09 2017-11-17 昆明理工大学 A kind of measurement apparatus and measuring method of four-axle aircraft brushless electric machine torque coefficient

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105116333A (en) * 2015-09-14 2015-12-02 南京工程学院 Measuring apparatus for motor tension linearity of multi-rotor type aircraft, and control system and method thereof
CN105116333B (en) * 2015-09-14 2017-11-03 南京工程学院 Multi-rotor aerocraft motor pulling force linearity measurement apparatus and its control system and method
CN107192532A (en) * 2017-06-09 2017-09-22 昆明理工大学 A kind of measurement apparatus and measuring method of four-axle aircraft brushless electric machine thrust coefficient
CN107356433A (en) * 2017-06-09 2017-11-17 昆明理工大学 A kind of measurement apparatus and measuring method of four-axle aircraft brushless electric machine torque coefficient
CN107356433B (en) * 2017-06-09 2019-05-10 昆明理工大学 A kind of measuring device and measuring method of four-axle aircraft brushless motor torque coefficient
CN107192532B (en) * 2017-06-09 2019-05-14 昆明理工大学 A kind of measuring device and measuring method of four-axle aircraft brushless motor thrust coefficient

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