CN203845025U - Unmanned aerial vehicle power testing system - Google Patents
Unmanned aerial vehicle power testing system Download PDFInfo
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- CN203845025U CN203845025U CN201420014636.7U CN201420014636U CN203845025U CN 203845025 U CN203845025 U CN 203845025U CN 201420014636 U CN201420014636 U CN 201420014636U CN 203845025 U CN203845025 U CN 203845025U
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- linear bearing
- motor
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- power supply
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Abstract
The utility model discloses an unmanned aerial vehicle power testing system comprising a rectangular profile frame, a power supply, a data acquiring card and a personal computer. A rectangular testing platform perpendicular to the bottom of the profile frame is arranged in the profile frame along the length and is provided with at least one linear bearing, a pressure/tension sensor is arranged in the linear bearing, a cylindrical shaft is connected into the linear bearing, the linear bearing at the end of the cylindrical shaft is fixed to a motor transversely, the rotary shaft of the motor is connected to the rotary connecting shaft, the tail end of the rotary connecting shaft is fixedly connected to the end of the cylindrical shaft, the end of the cylindrical shaft is provided with blades provided with a rotating speed sensor, a data acquiring card is electrically connected to the pressure/tension sensor and the rotating speed sensor electrically and is connected to the personal computer through a serial port, and the power supply supplies power for the personal computer, the data acquiring card and the motor. According to the system, by means of the sensor and a signal generator, tests in different throttle ranges can be completed automatically, and the accurate design basis for the power system of an unmanned aerial vehicle can be provided.
Description
Technical field
The utility model relates to Unmanned Aircraft Systems (UAS) configuration subsystem, particularly a kind of unmanned plane dynamic test system.
Background technology
Once unmanned plane determines to adopt electric-powered scheme at design phase, just need to test all sidedly alternative power system, the lower pulling force that can provide of collocation of different batteries, governor, electrical motor, screw propeller and the rotating speed of correspondence thereof, moment of torsion, voltage, electric current etc. are provided.Wherein, the weight of battery has influence on the total weight of aircraft, capacity of cell and size of current have influence on again the cruise duration of aircraft, the pulling force that screw propeller provides has directly determined the thrust-weight ratio of aircraft, these crucial data have conclusive impact to the performance of whole unmanned plane, and whether it accurately even directly has influence on the success or failure of development and design work.Therefore, at the design initial stage, set up a set of succinctly, effectively, electric-powered system test platform is very necessary and crucial accurately.
Therefore urgently develop a kind of unmanned plane dynamic test system.
Summary of the invention
The purpose of this utility model is that a kind of unmanned plane dynamic test system will be provided.
For achieving the above object, the utility model is implemented according to following technical scheme:
A kind of unmanned plane dynamic test system, comprise a rectangular-shaped section material frame, power supply, data collecting card and pc machine, the one test rectangle platform perpendicular to section material frame bottom surface is set in section material frame along its length, one side of test platform is fixed on the centerline of the left side of section material frame, at least one linear bearing is set on described test platform, in linear bearing, be provided with pressure/pulling force sensor, in linear bearing, be connected with cylinder axis, on the linear bearing of described cylinder axis end, be laterally fixedly installed motor, in the rotating shaft of motor, connect Coupling Shaft, switching the tip of the axis is fixedly connected with the end of cylinder axis, the end of cylinder axis arranges blade, on described blade, tachogen is set, the acquisition of signal end of data collecting card is electrically connected with the signal output part of pressure/pulling force sensor and tachogen respectively, data collecting card connects pc machine by serial port, described power supply is pc machine, data collecting card, motor power supply.
As further preferred version of the present utility model, the power input end of described motor is connected with governor and current sensor, the acquisition of signal end of the signal output part connection data capture card of described governor and current sensor.
As further preferred version of the present utility model, upper surface and the right side of described section material frame are provided with wire net.
Compared with prior art, the utility model can be tested pulling force, rotating speed, the electric current of unmanned plane power system under different rotating speeds control signal scope, and pass through real-time data acquisition, signal value record is shown on PC machine, in order to performance and the throttle-dynamic curve of determination and analysis Mechatronic Systems, with respect to the free-standing detecting instrument of tradition, this system has synchronous data collection and analysis ability, and can simulate to greatest extent the real working condition of unmanned plane power system.
Brief description of the drawings
Fig. 1 is structural representation of the present utility model;
Fig. 2 is electrical structure block diagram of the present utility model.
Detailed description of the invention
Below in conjunction with accompanying drawing and specific embodiment, the utility model is further described, is used for explaining the utility model in illustrative examples and the explanation of this utility model, but not as to restriction of the present utility model.
As Fig. 1, a kind of unmanned plane dynamic test system shown in Fig. 2, comprise a rectangular-shaped section material frame 1, power supply, data collecting card and pc machine, the one test rectangle platform 2 perpendicular to section material frame 1 bottom surface is set in section material frame 1 along its length, one side of test platform 2 is fixed on the centerline of the left side of section material frame 1, at least one linear bearing 3 is set on described test platform 2, in linear bearing 3, be provided with pressure/pulling force sensor, in linear bearing 3, be connected with cylinder axis 4, on the linear bearing 3 of described cylinder axis 4 ends, be laterally fixedly installed motor, in the rotating shaft of motor, connect Coupling Shaft, switching the tip of the axis is fixedly connected with the end of cylinder axis 4, the end of cylinder axis 4 arranges blade 5, on described blade 5, tachogen is set, the acquisition of signal end of data collecting card is electrically connected with the signal output part of pressure/pulling force sensor and tachogen respectively, data collecting card is responsible for gathering pressure/pulling force and the rotating speed electric signal that pressure/pulling force sensor and tachogen collect, and be real-time transmitted to pc machine by serial port, described power supply is pc machine, data collecting card, motor power supply.
The power input end of described motor is connected with governor and current sensor, the acquisition of signal end of the signal output part connection data capture card of described governor and current sensor.Data collecting card is responsible for gathering FM signal and the electric current electric signal that governor and current sensor collect, and is real-time transmitted to pc machine by serial port.
Cause personal injury for preventing that blade from flying out, the upper surface of described section material frame 1 and right side are provided with wire net 6.
The technical solution of the utility model is not limited to the restriction of above-mentioned specific embodiment, and every technology distortion of making according to the technical solution of the utility model, within all falling into protection domain of the present utility model.
Claims (3)
1. a unmanned plane dynamic test system, it is characterized in that, comprise a rectangular-shaped section material frame (1), power supply, data collecting card and pc machine, the one test rectangle platform (2) perpendicular to section material frame (1) bottom surface is set in section material frame (1) along its length, one side of test platform (2) is fixed on the centerline of the left side of section material frame (1), at least one linear bearing (3) is set on described test platform (2), linear bearing is provided with pressure/pulling force sensor in (3), in linear bearing (3), be connected with cylinder axis (4), on the linear bearing (3) of described cylinder axis (4) end, be laterally fixedly installed motor, in the rotating shaft of motor, connect Coupling Shaft, switching the tip of the axis is fixedly connected with the end of cylinder axis (4), the end of cylinder axis (4) arranges blade (5), described blade arranges tachogen on (5), the acquisition of signal end of data collecting card is electrically connected with the signal output part of pressure/pulling force sensor and tachogen respectively, data collecting card connects pc machine by serial port, described power supply is pc machine, data collecting card, motor power supply.
2. unmanned plane dynamic test system according to claim 1, is characterized in that: the power input end of described motor is connected with governor and current sensor, the acquisition of signal end of the signal output part connection data capture card of described governor and current sensor.
3. unmanned plane dynamic test system according to claim 1, is characterized in that: the upper surface of described section material frame (1) and right side are provided with wire net (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420014636.7U CN203845025U (en) | 2014-01-10 | 2014-01-10 | Unmanned aerial vehicle power testing system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420014636.7U CN203845025U (en) | 2014-01-10 | 2014-01-10 | Unmanned aerial vehicle power testing system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203845025U true CN203845025U (en) | 2014-09-24 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201420014636.7U Expired - Fee Related CN203845025U (en) | 2014-01-10 | 2014-01-10 | Unmanned aerial vehicle power testing system |
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| CN (1) | CN203845025U (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104590582A (en) * | 2014-10-16 | 2015-05-06 | 安徽泽众安全科技有限公司 | Aircraft paddle effect testing device |
| CN105044599A (en) * | 2015-07-24 | 2015-11-11 | 华南农业大学 | Unmanned aerial vehicle motor-propeller efficiency test device and method |
| CN105730716A (en) * | 2016-04-08 | 2016-07-06 | 东莞市瑞科五金塑胶制品有限公司 | Multifunction power system analysis meter of multi-rotor-wing unmanned aerial vehicle |
| CN105819000A (en) * | 2016-03-19 | 2016-08-03 | 沈阳飞机工业（集团）有限公司 | Multifunctional test table for unmanned aerial vehicle power system and test method of multifunctional test table |
| CN105947233A (en) * | 2016-06-22 | 2016-09-21 | 北方信息控制集团有限公司 | Multi-rotor power testing device and method |
| CN109933046A (en) * | 2019-03-21 | 2019-06-25 | 成都凯天电子股份有限公司 | Unmanned plane undercarriage control controller test system |
| 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 |
-
2014
- 2014-01-10 CN CN201420014636.7U patent/CN203845025U/en not_active Expired - Fee Related
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104590582A (en) * | 2014-10-16 | 2015-05-06 | 安徽泽众安全科技有限公司 | Aircraft paddle effect testing device |
| CN105044599A (en) * | 2015-07-24 | 2015-11-11 | 华南农业大学 | Unmanned aerial vehicle motor-propeller efficiency test device and method |
| CN105044599B (en) * | 2015-07-24 | 2018-03-20 | 华南农业大学 | A kind of efficiency test device and method suitable for unmanned plane motor oar |
| CN105819000A (en) * | 2016-03-19 | 2016-08-03 | 沈阳飞机工业（集团）有限公司 | Multifunctional test table for unmanned aerial vehicle power system and test method of multifunctional test table |
| CN105819000B (en) * | 2016-03-19 | 2018-01-05 | 沈阳飞机工业（集团）有限公司 | Unmanned plane dynamical system multi-function test stand and its test method |
| CN105730716A (en) * | 2016-04-08 | 2016-07-06 | 东莞市瑞科五金塑胶制品有限公司 | Multifunction power system analysis meter of multi-rotor-wing unmanned aerial vehicle |
| CN105947233A (en) * | 2016-06-22 | 2016-09-21 | 北方信息控制集团有限公司 | Multi-rotor power testing device and method |
| CN109933046A (en) * | 2019-03-21 | 2019-06-25 | 成都凯天电子股份有限公司 | Unmanned plane undercarriage control controller test system |
| CN109933046B (en) * | 2019-03-21 | 2023-11-10 | 成都凯天电子股份有限公司 | Unmanned aerial vehicle undercarriage retraction controller test system |
| 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 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140924 Termination date: 20180110 |