CN207045785U - A kind of electronic unmanned plane dynamical system is test bed and test system - Google Patents
A kind of electronic unmanned plane dynamical system is test bed and test system Download PDFInfo
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- CN207045785U CN207045785U CN201720677049.XU CN201720677049U CN207045785U CN 207045785 U CN207045785 U CN 207045785U CN 201720677049 U CN201720677049 U CN 201720677049U CN 207045785 U CN207045785 U CN 207045785U
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- 238000012360 testing method Methods 0.000 title claims abstract description 86
- 238000005183 dynamical system Methods 0.000 title abstract 6
- 230000001133 acceleration Effects 0.000 claims abstract description 19
- 230000003014 reinforcing effect Effects 0.000 claims description 24
- 238000005299 abrasion Methods 0.000 abstract description 4
- 230000000712 assembly Effects 0.000 abstract 1
- 238000000429 assembly Methods 0.000 abstract 1
- 238000001514 detection method Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000000903 blocking effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Abstract
The utility model discloses a kind of electronic unmanned plane dynamical system is test bed and test system.The electronic unmanned plane dynamical system it is test bed including：Support frame, it includes a supporting section, and electron speed regulator is arranged on supporting section；Slide assemblies, what it included being connected with each other determines slide rail and dynamic slide rail, and dynamic slide rail can move along a straight line on slide rail is determined；Slide rail is determined on support frame；Motor mounting rack, motor mounting rack are connected with dynamic slide rail, and motor is arranged on motor mounting rack, and the direction of motion of linear motion of the axis direction of the output shaft of motor with determining slide rail is identical；Posture and acceleration transducer, it is arranged on motor mounting rack.The test bed vibration frequency that electronic unmanned plane dynamical system is monitored by posture and acceleration transducer of electronic unmanned plane dynamical system of the application, so as to assess the quality of whether serious and propeller the dynamic balance performance of the abrasion condition of motor in electronic unmanned plane dynamical system.
Description
Technical Field
The utility model relates to an unmanned aerial vehicle driving system tests technical field, especially relates to an electronic unmanned aerial vehicle driving system test bench and electronic unmanned aerial vehicle driving system test system.
Background
The unmanned plane is called unmanned plane for short, and is called UAV for short in English, and is an unmanned plane operated by utilizing a radio remote control device and a self-contained program control device, and can carry various loads to complete various complex tasks.
The electric unmanned aerial vehicle power system mainly comprises a motor, an electronic speed regulator and a matched propeller. The heart of the unmanned aerial vehicle is a basic guarantee that various unmanned aerial vehicle systems can work normally, and the failure of the power system is one of important reasons for causing crash accidents of the multi-rotor unmanned aerial vehicle, so that the power system is very important to be tested.
Whether test driving system can reach unmanned aerial vehicle's design index or whether test driving system's wearing and tearing have influenced its performance can both provide important guarantee for unmanned aerial vehicle's safe work, the crash accident that the prevention probably takes place because driving system arouses.
The existing power system testing equipment cannot completely test the self quality and performance of the unmanned aerial vehicle power system. The motor rotor among the driving system is relatively poor with the axiality assembly of pivot or takes place wearing and tearing or the propeller dynamic balance is relatively poor the time dynamic group motor can carry out the rotational motion of similar eccentric wheel, along with the increase of driving system operating time, the motor shaft can seriously wear and tear until making driving system inefficacy to cause the crash accident.
The self quality or the abrasion degree of the power system can be judged whether to be in a qualified range only by testing the vibration frequency of the whole power system and comparing the vibration frequency with a qualified numerical value, and the existing power system testing equipment cannot perform the test.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide an electronic unmanned aerial vehicle driving system test bench overcomes or alleviates at least one above-mentioned defect of prior art at least.
In order to achieve the purpose, the utility model provides an electric unmanned aerial vehicle power system test bench, which is used for testing an electric unmanned aerial vehicle power system, wherein the electric unmanned aerial vehicle power system comprises a motor, a propeller and an electronic speed regulator, and the propeller is connected with the output end of the motor; the electronic governor with the motor is connected, electronic unmanned aerial vehicle driving system test bench includes: the supporting frame comprises a supporting section, and the electronic speed regulator is arranged on the supporting section; the sliding assembly comprises a fixed sliding rail and a movable sliding rail which are connected with each other, and the movable sliding rail can linearly move on the fixed sliding rail; the fixed slide rail is arranged on the support frame; the motor mounting frame is connected with the movable sliding rail, the motor is mounted on the motor mounting frame, and the axial direction of an output shaft of the motor is the same as the movement direction of the linear movement of the fixed sliding rail; the attitude and acceleration sensor is mounted on the motor mounting frame; the attitude and acceleration sensor is used for detecting the attitude angle and the attitude angular velocity of the motor when the motor works.
Preferably, the test bench for the power system of the electric unmanned aerial vehicle further comprises a tension sensor, the tension sensor is installed on the supporting section, and a testing end of the tension sensor is connected with the movable sliding rail.
Preferably, the test stand for the power system of the electric unmanned aerial vehicle further comprises a temperature sensor, and the temperature sensor is installed on the outer surface of the motor.
Preferably, the test bench for the power system of the electric unmanned aerial vehicle further comprises a torque sensor, the torque sensor is installed on the supporting section, the torque sensor comprises a torque testing section, and the torque testing section is at least partially installed on the motor installation frame.
Preferably, the test bench for the power system of the electric unmanned aerial vehicle further comprises a wireless communication system, and the wireless communication system is respectively connected with the attitude and acceleration sensor, the tension sensor, the temperature sensor and the torque sensor.
Preferably, the support frame further comprises a fixed platform, and one end of the support section is mounted on the fixed platform.
Preferably, the support frame comprises a first section, a second section, a third section and a fourth section, and one end of the first section, the second section, the third section and the fourth section is shared; the supporting section is arranged at one end shared by the first section, the second section, the third section and the fourth section; the supporting frame further comprises a first reinforcing foot rest, a second reinforcing foot rest, a third reinforcing foot rest and a fourth reinforcing foot rest; the first reinforcing foot stool is installed between the first section and the support section; the second reinforcing foot rest is arranged between the second section and the supporting section; the third reinforcing foot rest is arranged between the third section and the supporting frame; the fourth reinforcing foot rest is installed between the fourth section and the supporting frame.
Preferably, the fixed slide rail is provided with a clamping portion, and the clamping portion is used for limiting the moving distance of the movable slide rail.
Preferably, the support section comprises a first support section, a second support section and a locking device, and one end of the first support section is mounted on the fixed platform; the second support section is sleeved on the first support section and can move telescopically relative to the first support section; the locking device is used for fixing the relative position of the first support section and the second support section.
The application also provides an electric unmanned aerial vehicle power system test system, electric unmanned aerial vehicle power system test system includes test terminal and electric unmanned aerial vehicle power system test bench, electric unmanned aerial vehicle power system test bench be as above electric unmanned aerial vehicle power system test bench.
The electric unmanned aerial vehicle power system test bench monitors the vibration frequency of the electric unmanned aerial vehicle power system through the attitude and acceleration sensor, and therefore whether the abrasion condition of a motor in the electric unmanned aerial vehicle power system is serious and the dynamic balance performance of a propeller is evaluated.
Whether power, pulling force and the vibration that produces meet the detection of requirement is carried out on the basis of aassessment to improve unmanned aerial vehicle security performance.
Drawings
Fig. 1 is a schematic structural diagram of an electric unmanned aerial vehicle power system test bench according to an embodiment of the present invention.
Reference numerals
Detailed Description
In order to make the purpose, technical solution and advantages of the present invention clearer, the following will combine the drawings in the embodiments of the present invention to perform more detailed description on the technical solution in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present invention, and should not be construed as limiting the present invention. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention. Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
In the description of the present invention, it is to be understood that the terms "central", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience of description and for simplicity of description, and do not indicate or imply that the device or element so referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be considered as limiting the scope of the invention.
Fig. 1 is a schematic structural diagram of an electric unmanned aerial vehicle power system test bench according to an embodiment of the present invention.
As shown in fig. 1, the test stand for testing the power system of the electric unmanned aerial vehicle is used for testing the power system of the electric unmanned aerial vehicle, the power system of the electric unmanned aerial vehicle comprises a motor 1, a propeller 2 and an electronic speed regulator 3, and the propeller 2 is connected with the output end of the motor 1; the electronic speed regulator 3 is connected with the motor 1, and the test bench for testing the power system of the electric unmanned aerial vehicle comprises a support frame 4, a sliding assembly 5, a motor mounting frame 6 and a posture and acceleration sensor 7.
Referring to fig. 1, the supporting frame 4 includes a supporting section 41, and the electronic governor 3 is mounted on the supporting section 41; the sliding assembly 5 comprises a fixed sliding rail and a movable sliding rail which are connected with each other, and the movable sliding rail can move on the fixed sliding rail in a straight line; the fixed slide rail is arranged on the support frame 4; the motor mounting frame 6 is connected with the movable sliding rail, the motor 1 is mounted on the motor mounting frame 6, and the axial direction of the output shaft of the motor 1 is the same as the linear motion direction of the fixed sliding rail (namely the moving direction of the fixed sliding rail is consistent with the axial direction of the output shaft of the motor); the attitude and acceleration sensor 7 is arranged on the motor mounting frame 6; the attitude and acceleration sensor 7 is used for detecting an attitude angle and an attitude angular velocity of the motor when the motor works.
The electric unmanned aerial vehicle power system test bench monitors the vibration frequency of the electric unmanned aerial vehicle power system through the attitude and acceleration sensor, and therefore whether the abrasion condition of the electric unmanned aerial vehicle power system is serious and whether the dynamic balance performance is good or not are evaluated. For example, the data refresh rate of the attitude and acceleration sensors is 4 to 5 times the natural frequency of the motor. After discrete acceleration data generated by the vibration of the power system are collected, the data are led into analysis software to be subjected to Fourier transform, and amplitude-frequency and phase-frequency characteristics of the data are obtained, so that the vibration frequency is obtained.
In this embodiment, the attitude and acceleration sensors include a three-axis gyroscope, a three-axis accelerometer, a three-axis magnetometer, a barometer, and a thermometer.
Whether power, pulling force and the vibration that produces meet the detection of requirement is carried out on the basis of aassessment to improve unmanned aerial vehicle security performance.
Referring to fig. 1, in this embodiment, the test bench for the power system of the electric unmanned aerial vehicle further includes a tension sensor 8, the tension sensor 8 is installed on the support section 41, and a test end of the tension sensor 8 is connected with the movable slide rail. The tension sensor 8 can detect the magnitude of the force generated by the propeller when the motor is in operation.
Referring to fig. 1, in the present embodiment, the electric unmanned aerial vehicle power system test stand further includes a temperature sensor 9, and the temperature sensor 9 is installed on an outer surface of the motor 1. The motor temperature can be monitored in real time by the temperature sensor 9.
Referring to fig. 1, in the present embodiment, the electric unmanned aerial vehicle power system test bench further includes a torque sensor 10, the torque sensor 10 is mounted on the support section 41, the torque sensor 10 includes a torque test section 101, and the torque test section 101 is at least partially mounted on the motor mounting bracket 6. When the motor works, the torque sensor can detect the torque transmitted to the motor mounting frame by the motor.
Referring to fig. 1, in the present embodiment, the test bench for the power system of the electric unmanned aerial vehicle further includes a wireless communication system 11, and the wireless communication system 11 is respectively connected to the attitude and acceleration sensor 7, the tension sensor 8, the temperature sensor 9, and the torque sensor 10. The attitude and acceleration sensor, the tension sensor, the temperature sensor and the torque sensor can transmit the detected information to the wireless communication system, and then can transmit the detected information to other terminals or storage devices through the wireless communication system.
Referring to fig. 1, in the present embodiment, the supporting frame 4 further includes a fixing platform 42, and one end of the supporting section 41 is mounted on the fixing platform 42.
The supporting frame comprises a first section, a second section, a third section and a fourth section, wherein one end of the first section, one end of the second section, one end of the third section and one end of the fourth section are shared; the supporting section is arranged at one end shared by the first section, the second section, the third section and the fourth section; the supporting frame further comprises a first reinforcing foot frame, a second reinforcing foot frame, a third reinforcing foot frame and a fourth reinforcing foot frame; a first reinforcing foot rest is mounted between the first section and the support section; a second reinforcing foot rest is mounted between the second section and the support section; a third reinforcing foot rest is arranged between the third section and the supporting frame; the fourth reinforcing foot rest is arranged between the fourth section and the supporting frame. By adopting the mode, the stability of the whole test bed for the power system of the electric unmanned aerial vehicle can be improved, and the situation that the test bed for the power system of the electric unmanned aerial vehicle is driven or the supporting frame is driven due to the movement of the propeller is prevented, so that data distortion is caused.
In this embodiment, the fixed slide rail is provided with a blocking portion for limiting the moving distance of the brake slide rail. The clamping part is added to prevent the propeller from driving the movable slide rail to separate from the fixed slide rail when the propeller rotates at high speed.
Advantageously, in an alternative embodiment, the support section comprises a first support section, a second support section and a locking means, one end of the first support section being mounted on the fixed platform; the second support section is sleeved on the first support section and can move in a telescopic manner relative to the first support section; the locking device is used for fixing the relative position of the first support section and the second support section. By adopting the structure, the size of the support section can be adjusted, so that different propellers can be tested conveniently.
The application also provides an electric unmanned aerial vehicle power system test system, which comprises a test terminal and an electric unmanned aerial vehicle power system test bench, wherein the electric unmanned aerial vehicle power system test bench is as above. The information transmitted to the test terminal by the test bed of the power system of the electric unmanned aerial vehicle can be processed and analyzed by the test terminal, so that the performance of the power system of the electric unmanned aerial vehicle can be detected.
Finally, it should be pointed out that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit it. Although the present invention has been described in detail with reference to the foregoing embodiments, it should be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; such modifications and substitutions do not depart from the spirit and scope of the present invention in its corresponding aspects.
Claims (10)
1. A test bench for testing an electric unmanned aerial vehicle power system is used for testing the electric unmanned aerial vehicle power system, the electric unmanned aerial vehicle power system comprises a motor (1), a propeller (2) and an electronic speed regulator (3), and the propeller (2) is connected with the output end of the motor (1); electronic governor (3) with motor (1) are connected, its characterized in that, electronic unmanned aerial vehicle driving system test bench includes:
the supporting frame (4), the supporting frame (4) comprises a supporting section (41), and the electronic governor (3) is installed on the supporting section (41);
the sliding assembly (5) comprises a fixed sliding rail and a movable sliding rail which are connected with each other, and the movable sliding rail can linearly move on the fixed sliding rail; the fixed slide rail is arranged on the support frame (4);
the motor mounting rack (6) is connected with the movable sliding rail, the motor (1) is mounted on the motor mounting rack (6), and the axial direction of an output shaft of the motor (1) is the same as the moving direction of the linear motion of the fixed sliding rail;
the attitude and acceleration sensor (7), the attitude and acceleration sensor (7) is installed on the motor mounting rack (6); wherein,
and the attitude and acceleration sensor (7) is used for detecting the attitude angle and the attitude angular velocity of the motor when the motor works.
2. The electric unmanned aerial vehicle power system test bench of claim 1, characterized in that, the electric unmanned aerial vehicle power system test bench further comprises a tension sensor (8), the tension sensor (8) is installed on the supporting section (41), and the testing end of the tension sensor (8) is connected with the movable sliding rail.
3. The electric unmanned aerial vehicle power system test bench of claim 2, characterized in that, the electric unmanned aerial vehicle power system test bench further comprises a temperature sensor (9), and the temperature sensor (9) is installed on the outer surface of the motor (1).
4. The electric unmanned aerial vehicle powertrain test stand of claim 3, further comprising a torque sensor (10), the torque sensor (10) mounted on the support section (41), the torque sensor (10) comprising a torque test section (101), the torque test section (101) mounted at least partially on the motor mount (6).
5. The electric unmanned aerial vehicle power system test bench of claim 4, characterized in that, the electric unmanned aerial vehicle power system test bench further comprises a wireless communication system (11), and the wireless communication system (11) is respectively connected with the attitude and acceleration sensor (7), the tension sensor (8), the temperature sensor (9) and the torque sensor (10).
6. The test bench for testing the electric unmanned aerial vehicle power system according to claim 5, wherein the supporting frame (4) further comprises a fixed platform (42), and one end of the supporting section (41) is installed on the fixed platform (42).
7. The test bench for testing the power system of the electric unmanned aerial vehicle according to claim 6, wherein the supporting frame (4) comprises a first section, a second section, a third section and a fourth section, and the first section, the second section, the third section and the fourth section share one end;
the supporting section (41) is arranged at one end shared by the first section, the second section, the third section and the fourth section;
the supporting frame (4) further comprises a first reinforcing foot rest, a second reinforcing foot rest, a third reinforcing foot rest and a fourth reinforcing foot rest;
the first reinforcing foot rest is mounted between the first section and the support section (41);
the second reinforcing foot-rest is mounted between the second section and the support section (41);
the third reinforcing foot rest is arranged between the third section and the support frame (4);
the fourth reinforcing foot rest is arranged between the fourth section and the supporting frame (4).
8. The test bed for testing the electric unmanned aerial vehicle power system according to claim 6, wherein the fixed slide rail is provided with a clamping portion, and the clamping portion is used for limiting the moving distance of the movable slide rail.
9. The electric unmanned aerial vehicle power system test bench of claim 6, characterized in that the support section (41) comprises a first support section, a second support section and a locking device, one end of the first support section is mounted on the fixed platform;
the second support section is sleeved on the first support section and can move telescopically relative to the first support section;
the locking device is used for fixing the relative position of the first support section and the second support section.
10. An electric unmanned aerial vehicle power system test system, characterized in that, the electric unmanned aerial vehicle power system test system includes test terminal and electric unmanned aerial vehicle power system test bed, the electric unmanned aerial vehicle power system test bed is as in any one of claims 1 to 9.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720677049.XU CN207045785U (en) | 2017-06-12 | 2017-06-12 | A kind of electronic unmanned plane dynamical system is test bed and test system |
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| CN201720677049.XU CN207045785U (en) | 2017-06-12 | 2017-06-12 | A kind of electronic unmanned plane dynamical system is test bed and test system |
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| CN109142055A (en) * | 2018-09-03 | 2019-01-04 | 南京航空航天大学 | A kind of rotary wing performance multi-function test stand |
| CN110282155A (en) * | 2019-07-03 | 2019-09-27 | 中国人民解放军国防科技大学 | Two-degree-of-freedom unmanned aerial vehicle power test system |
| CN111409857A (en) * | 2020-04-21 | 2020-07-14 | 涵涡智航科技(玉溪)有限公司 | Measuring device for torque and lift of aircraft power system |
| CN111977028A (en) * | 2020-08-24 | 2020-11-24 | 江苏兰菱机电科技有限公司 | Testing arrangement of unmanned aerial vehicle motor and screw combination |
| CN111999029A (en) * | 2020-10-26 | 2020-11-27 | 中国空气动力研究与发展中心低速空气动力研究所 | Supporting device for propeller test |
| CN113176059A (en) * | 2021-03-31 | 2021-07-27 | 南京航空航天大学 | Two-dimensional plane vibration test bed based on rotating force excitation |
| CN113365919A (en) * | 2020-06-23 | 2021-09-07 | 深圳市大疆创新科技有限公司 | Test equipment, test method and flight test system |
| CN113636103A (en) * | 2021-10-14 | 2021-11-12 | 南京鹿达电器有限公司 | Unmanned aerial vehicle vibration testing arrangement |
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- 2017-06-12 CN CN201720677049.XU patent/CN207045785U/en active Active
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| CN109142055B (en) * | 2018-09-03 | 2020-06-09 | 南京航空航天大学 | Rotor performance comprehensive test platform |
| CN109142055A (en) * | 2018-09-03 | 2019-01-04 | 南京航空航天大学 | A kind of rotary wing performance multi-function test stand |
| CN110282155A (en) * | 2019-07-03 | 2019-09-27 | 中国人民解放军国防科技大学 | Two-degree-of-freedom unmanned aerial vehicle power test system |
| CN111409857A (en) * | 2020-04-21 | 2020-07-14 | 涵涡智航科技(玉溪)有限公司 | Measuring device for torque and lift of aircraft power system |
| CN113365919A (en) * | 2020-06-23 | 2021-09-07 | 深圳市大疆创新科技有限公司 | Test equipment, test method and flight test system |
| WO2021258310A1 (en) * | 2020-06-23 | 2021-12-30 | 深圳市大疆创新科技有限公司 | Test device, test method and flight test system |
| CN111977028A (en) * | 2020-08-24 | 2020-11-24 | 江苏兰菱机电科技有限公司 | Testing arrangement of unmanned aerial vehicle motor and screw combination |
| CN111999029B (en) * | 2020-10-26 | 2021-01-12 | 中国空气动力研究与发展中心低速空气动力研究所 | Supporting device for propeller test |
| CN111999029A (en) * | 2020-10-26 | 2020-11-27 | 中国空气动力研究与发展中心低速空气动力研究所 | Supporting device for propeller test |
| CN113176059A (en) * | 2021-03-31 | 2021-07-27 | 南京航空航天大学 | Two-dimensional plane vibration test bed based on rotating force excitation |
| CN113176059B (en) * | 2021-03-31 | 2023-05-23 | 南京航空航天大学 | Two-dimensional plane vibration test bed based on rotation force excitation |
| CN113636103A (en) * | 2021-10-14 | 2021-11-12 | 南京鹿达电器有限公司 | Unmanned aerial vehicle vibration testing arrangement |
| CN113636103B (en) * | 2021-10-14 | 2022-06-24 | 南京鹿达电器有限公司 | Unmanned aerial vehicle vibration testing device |
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Address after: No. 66, Zizhuyuan Road, Haidian District, Beijing 100048 Patentee after: China Software Evaluation Center Country or region after: China Address before: 100081 No. 66, Zizhuyuan Road, Haidian District, Beijing Patentee before: COMPUTER AND MICROELECTRONICS DEVELOPMENT RESEARCH CENTER, MINISTRY OF INDUSTRY AND INFORMATION TECHNOLOGY (CHINA SOFTWARE TESTING CENTER) Country or region before: China |
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