CN204184580U - A kind of aircraft blade power effect proving installation - Google Patents
A kind of aircraft blade power effect proving installation Download PDFInfo
- Publication number
- CN204184580U CN204184580U CN201420598918.6U CN201420598918U CN204184580U CN 204184580 U CN204184580 U CN 204184580U CN 201420598918 U CN201420598918 U CN 201420598918U CN 204184580 U CN204184580 U CN 204184580U
- Authority
- CN
- China
- Prior art keywords
- blade
- motor
- support
- bellows
- battery
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn - After Issue
Links
Landscapes
- Wind Motors (AREA)
- Force Measurement Appropriate To Specific Purposes (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The utility model relates to a kind of aircraft blade power effect proving installation, be made up of blade (1), bellows (9), fan (10), battery (7), support (8), bellows (9) front and top are all provided with fan (10), in bellows (9), a support (8) is installed, support (8) left end connects a battery (7), an in-situ testing device (a) is installed on support (8) top, and its in-situ testing device (a) right-hand member connects a blade (1); The beneficial effects of the utility model are: can the thrust magnitude that produced by blade of Measurement accuracy; Directly calculate battery, power valid value between motor and blade; By the slide rail of design, the equivalence transmission of lift value can be realized.
Description
Technical field
The utility model relates to the proving installation of power effect relationship between blade for testing multi-rotor aerocraft and other instruments and motor, is provided the power valid value of optimal proportion by contrast, and then improves the performance of multi-rotor aerocraft.
Background technology
Multi-rotor aerocraft have be active in one's movements, simple feature of can hovering, take off and land, what can be used for important place patrols and examines inspection, the acquisition of field data and the track and localization of target.Therefore, patrol and examine inspection at forest fire protection, high-tension bus-bar, accident scene obtains, hit the fields such as terrified crime important application.The power pack section of multi-rotor aerocraft generally relies on battery to be feeding electric motors, is obtained the power of lift-off by the fast rotational of blade.When the power of self gravitation and blade reaches balance, just can hover over aerial.By the change of each blade rotative speed, the change of heading can be controlled.Multi-rotor aerocraft generally adopts battery as propulsion source.In order to reduce energy consumption, increase the flight time of aircraft, need to play the highest efficiency of blade.This just requires battery, reaches optimum coordinating between motor with blade, produces maximum power effect.
The power effect of blade is core design foundation and the product design basis for estimation of multi-rotor aerocraft.At present about the product of the device shortage standard of blade power effect test.
This patent by appropriate design, adopts the mode of setting pressure sensor that the power that blade produces directly is changed, exported, and inputs in computer with the voltage of motor, power synchronous.By Fitting Analysis, directly to valid value of exerting oneself.Solve power effect and measure the inaccuracy of structure and the trouble of power effect manual calculations.And by the device of a set of simulating chamber exogenous wind of design, the power effect situation of blade in flight course can be simulated really.
Utility model content
The utility model object provides one to be applied in, and carry-on structure is simple, failure-free blade power effect proving installation.
Main structure of the present utility model is: by blade, bellows, fan, battery, prop up and be configured to, bellows front and top are all provided with fan, in bellows, a support is installed, support left end connects a battery, cantilever tip installs an in-situ testing device, its in-situ testing device right-hand member connects a blade, in-situ testing device is by motor, pressure sensor, motor stationary magazine creel is formed, motor end arranges a motor stationary magazine creel, its motor stationary magazine creel inwall installs a pressure sensor, in motor stationary magazine creel, a motor fixing plate is vertically installed in center, its motor fixing plate is provided with control circuit board.
The beneficial effects of the utility model are: can the thrust magnitude that produced by blade of Measurement accuracy; Directly calculate battery, power valid value between motor and blade; By the slide rail of design, the equivalence transmission of lift value can be realized; By simulation wind apparatus, can the lift of measurement blade of original position, also can detect the impact of wind on aircraft flight stability.
accompanying drawing explanation:
Fig. 1 is the utility model product front view;
Fig. 2 is the utility model product situ proving installation enlarged drawing;
Fig. 3 is the utility model product top fan planar view;
Fig. 4 is the utility model product work schematic diagram.
detailed description of the invention:
below in conjunction with the drawings and specific embodiments, the utility model is described in further detail
As shown in drawings, a kind of aircraft blade power effect proving installation, by blade 1, bellows 9, fan 10, battery 7, support 8 is formed, bellows 9 front and top are all provided with fan 10, in bellows 9, a support 8 is installed, support 8 left end connects a battery 7, an in-situ testing device a is installed on support 8 top, its in-situ testing device a right-hand member connects a blade 1, in-situ testing device a is by motor 2, pressure sensor 6, motor stationary magazine creel 5 is formed, motor 2 end arranges a motor stationary magazine creel 5, its motor stationary magazine creel 5 inwall installs a pressure sensor 6, in motor stationary magazine creel 5, a motor fixing plate 3 is vertically installed in center, its motor fixing plate 3 is provided with control circuit board 4.
As shown in Figure 1, 2, the present invention includes 1. blades, 2. motor, 3. motor fixing plate, 4. control circuit board, 5. motor stationary magazine creel, 6. pressure sensor, 7. battery, 8. support, 9. bellows, 10. fan.Fig. 3 is fan assembly top graph, battery 7 is powered for motor 2 by control circuit board 4, blade 1 rotates, produce power, motor fixing plate 3 is stressed to travel forward, power is applied directly to above motor stationary magazine creel 5, because installed pressure sensor 6 on stationary magazine creel, so motor fixing plate 3 will directly act on pressure sensor 6, the pressure experienced is converted into electric signal transmission to main frame by pressure sensor 6, main frame, by matching, calculating, directly can provide the lift value of motor under different capacity and the power valid value of motor.
Claims (1)
1. an aircraft blade power effect proving installation, by blade (1), bellows (9), fan (10), battery (7), support (8) is formed, bellows (9) front and top are all provided with fan (10), in bellows (9), a support (8) is installed, support (8) left end connects a battery (7), an in-situ testing device (a) is installed on support (8) top, its in-situ testing device (a) right-hand member connects a blade (1), it is characterized in that: in-situ testing device (a) is by motor (2), pressure sensor (6), motor stationary magazine creel (5) is formed, motor (2) end arranges a motor stationary magazine creel (5), its motor stationary magazine creel (5) inwall installs a pressure sensor (6), a motor fixing plate (3) is vertically installed in motor stationary magazine creel (5) interior center, its motor fixing plate (3) is provided with control circuit board (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420598918.6U CN204184580U (en) | 2014-10-16 | 2014-10-16 | A kind of aircraft blade power effect proving installation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420598918.6U CN204184580U (en) | 2014-10-16 | 2014-10-16 | A kind of aircraft blade power effect proving installation |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204184580U true CN204184580U (en) | 2015-03-04 |
Family
ID=52616597
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420598918.6U Withdrawn - After Issue CN204184580U (en) | 2014-10-16 | 2014-10-16 | A kind of aircraft blade power effect proving installation |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204184580U (en) |
Cited By (3)
| 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 |
| CN104713671A (en) * | 2015-04-01 | 2015-06-17 | 北京象限科技有限公司 | Force effect tester |
| CN105510702A (en) * | 2016-01-26 | 2016-04-20 | 西北农林科技大学 | Effort testing device for electric multi-rotor aircraft |
-
2014
- 2014-10-16 CN CN201420598918.6U patent/CN204184580U/en not_active Withdrawn - After Issue
Cited By (4)
| 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 |
| CN104590582B (en) * | 2014-10-16 | 2017-11-21 | 安徽泽众安全科技有限公司 | A kind of aircraft blade power imitates test device |
| CN104713671A (en) * | 2015-04-01 | 2015-06-17 | 北京象限科技有限公司 | Force effect tester |
| CN105510702A (en) * | 2016-01-26 | 2016-04-20 | 西北农林科技大学 | Effort testing device for electric multi-rotor aircraft |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN204184580U (en) | A kind of aircraft blade power effect proving installation | |
| CN202994470U (en) | Dynamic performance testing system for pilotless aircraft | |
| CN104590582A (en) | Aircraft paddle effect testing device | |
| CN203845025U (en) | Unmanned aerial vehicle power testing system | |
| CN105205264B (en) | Predict the test method of pumped-storage power generation motor rotor component service life | |
| US11411474B1 (en) | Systems and methods for monitoring health of a motor | |
| CN103558843A (en) | Automatic amplitude modulation frequency scanning method for airplane servo elasticity frequency response test | |
| CN202501972U (en) | Airplane model force-measuring wind tunnel | |
| CN209467351U (en) | A kind of Portable aircraft basket ring control system test equipment | |
| CN205045010U (en) | Many rotors unmanned vehicles capability test platform | |
| CN103605076A (en) | Small electric unmanned aerial vehicle motor testing device | |
| CN105044599A (en) | Unmanned aerial vehicle motor-propeller efficiency test device and method | |
| CN108414935A (en) | A kind of agricultural unmanned plane electric efficiency test platform of more rotors in interior and method | |
| CN107884716A (en) | A kind of method for assessing battery management system voltage acquisition precision | |
| Zhao et al. | Design and implementation of an innovative airborne electric propulsion measure system of fixed-wing UAV | |
| CN102519640A (en) | Tester and testing method for testing pull and rotating speed of motor of minitype unmanned aerial vehicle | |
| CN204536507U (en) | A kind of unmanned plane motor and blade matching performance testing apparatus | |
| CN103434656B (en) | Rigidity simulator with variable rigidity | |
| CN205300888U (en) | A test model for measuring rudder face hinge moment | |
| Nagy et al. | Advanced data acquisition system for wind energy applications | |
| CN107656091B (en) | A kind of wind measurement method and its system based on air-blower control sensor | |
| CN106872085B (en) | Automatic testing arrangement of unmanned aerial vehicle horn kinetic energy efficiency | |
| Van der Woude et al. | Dynamic structural modelling of wind turbines using comsol multiphysics | |
| CN204903726U (en) | Be suitable for efficiency testing arrangement of unmanned aerial vehicle motor - oar | |
| CN203688673U (en) | Alti-electrograph |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20150304 Effective date of abandoning: 20171121 |
|
| AV01 | Patent right actively abandoned |