CN104713671A - Force effect tester - Google Patents
Force effect tester Download PDFInfo
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- CN104713671A CN104713671A CN201510150466.4A CN201510150466A CN104713671A CN 104713671 A CN104713671 A CN 104713671A CN 201510150466 A CN201510150466 A CN 201510150466A CN 104713671 A CN104713671 A CN 104713671A
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- China
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- tester
- power effect
- mounting rack
- motor mounting
- chip microcomputer
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- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention provides a force effect tester. The force effect tester comprises a base, slide guide rails which are symmetrically arranged on the base, a slide end which is fixed on the slide guide rails, a motor mounting rack which is fixed at the slide end, and a tensile force tester which is connected with the slide end, wherein a test circuit board with an onboard master control single chip microcomputer is arranged on the motor mounting rack; the single chip microcomputer is used for testing integral voltage and current through a sensor with a power supply plate, reading results of the tensile force tester, calculating the force effect by combining various results according to the set program, and displaying and recording the force effect on the single chip microcomputer and a display device thereof; the test circuit board 5 further can be connected with a remote-control receiver to supply power to the receiver, and a control signal of the receiver can be connected to control power transfer.
Description
Technical field
The present invention relates to a kind of testing tool, particularly relate to a kind of tester measuring motor and screw propeller body force effect, belong to field of test instrument.
Background technology
In Electric aircraft R&D process, needing to calculate flight efficiency, therefore need to detect acquisition key parameter at this--power is imitated.So power effectiveness is for weighing the index between power consumption and execution efficiency, when can be directly used in calculating boat.In order to obtain power effect, then need to adopt specialty for testing the instrument of electric propulsion system efficiency, i.e. power effect testing tool.
Existing power effect test mode is, the blade needing test force to imitate is directly connected on the motor fixing plate in motor stationary magazine creel, and on motor stationary magazine creel setting pressure sensor, motor fixing plate will directly act on pressure transducer 6, and the pressure experienced is converted into electrical signal transfer to main frame (see patent documentation CN204184580U) by pressure transducer 6.Because motor fixing plate does not adopt suitable fixed form, therefore the moment of torsion of blade and motor can produce lateral effect to motor fixing plate, thus affect the signals collecting of pressure transducer further, simultaneously owing to needing the flexible power overcoming support, pressure transducer is made to be difficult to obtain pressure value accurately.
The existence of these problems makes existing power effect sensor be difficult to the power effect parameter of Accurate Determining Electric aircraft.
Summary of the invention
The object of the invention is to obtain power effect parameter accurately, thus realize obtaining high-precision electric propulsion system whole efficiency parameter-i.e. power effect.
Technical scheme of the present invention is: base 2 installed two symmetrical rail plates 3, be fixed to by sliding end 4 on symmetrical rail plate 3, sliding end 4 fixedly mounts motor mounting rack 6, tension tester 1 is fixedly connected with by modes such as bolts with sliding end.On motor mounting rack 6 can the battery of adaptive different model, electricity adjust, motor and screw propeller.Motor mounting rack 6 is provided with testing circuit board 5, testing circuit board 5 has plate to carry main control singlechip.This single-chip microcomputer can carry out the test of global voltage electric current by the sensor of power supply board, and reads the result of tension tester, and the various result computing power effect of the program synthesis then by setting, shows power effect and be recorded in single-chip microcomputer and display device thereof.Described testing circuit board 5 can also connect remote-control receiver, powers to receiver, and can the control signal of UNICOM's receiver, adjusts for controlling electricity.
The invention has the advantages that:
(1) can adaptive all power systems, one-shot measurement, without the need to separately measuring result of calculation again, is beneficial to the efficiency measurement of technical flight device;
(2) adopt double sided slider bar design, improve durability, the firm dynamic range that can be adaptive of structure comparison is wider, can eliminate the impact of Motor torque on system testing;
(3) directly carry out voltage and current measurement at feeder ear, power erecting frame carries out tension measurement, without the need to power supply;
Power effect tester inside provided by the invention is integrated with the measurement of electric current and voltage, the measurement of integrated pulling force, and integrated single-chip microcomputer is used for the power effect numerical value of calculating and real motor in real time, can control throttle size, thus the power effect directly completed in different operating mode situation is measured and is recorded power effect curve.
Accompanying drawing explanation
Fig. 1 is stereographic map of the present invention;
1 tension tester 2 base 3 slide rail guide rail 4 sliding end 5 testing circuit board 6 motor mounting rack.
Embodiment
Below in conjunction with drawings and Examples, the present invention is described in further detail:
As shown in Figure 1, the invention discloses a kind of power effect tester adopting double sided slider bar to design, base 2 arranges two symmetrical rail plates 3, sliding end 4 is fixed on symmetrical rail plate 3, above sliding end 4, fixedly mount motor mounting rack 6, tension tester 1 is fixedly connected with by modes such as bolts with sliding end.Motor mounting rack 6 adaptive can be provided with the battery of different model, electricity tune, motor and screw propeller.Motor mounting rack 6 is provided with testing circuit board 5, testing circuit board 5 has plate to carry main control singlechip.Battery is connected to the input end of testing circuit board, the supply lines adjust electricity and control line are connected to the output terminal of testing circuit board 5, and the output terminal that electricity is adjusted is connected to motor, and fixed electrical machinery and screw propeller.The output terminal of remote-control receiver is connected to the special purpose interface of testing circuit board.
First according to the requirement calibration telepilot that electricity is adjusted, then by power that the Throttle Opening Control motor of telepilot rotates, plate carries single-chip microcomputer can carry out global voltage electric current test by the sensor of power supply board, and read the result of tension tester, then the various result computing power effect of the program synthesis by setting, and four LED readout instruments show voltage, electric current, Larry and power effect numerical value in real time, all use four position effective digitals.
Claims (5)
1. a power effect tester, comprise base (2), motor mounting rack (6) and single-chip microcomputer, it is characterized in that: described tester also has rail plate (3), described rail plate (3) is also connected with sliding end (4), described sliding end (4) the described motor mounting rack of upper fixed installation (6), described motor mounting rack (6) is provided with testing circuit board (5).
2. a power effect tester as claimed in claim 1, is characterized in that: described testing circuit board (5) is upper also has plate to carry main control singlechip.
3. a power effect tester as claimed in claim 2, is characterized in that: described plate carries the test that single-chip microcomputer can carry out global voltage electric current, and reads the result of tension tester, the various result computing power effect of the program synthesis then by setting.
4. a power effect tester as claimed in claim 3, is characterized in that: described power effect tester also has four LED readout instruments, for showing voltage, electric current, Larry and power effect numerical value in real time, all uses four position effective digitals.
5. the power effect tester as described in as arbitrary in claim 1-4, is characterized in that: described rail plate (3) at least two, and is symmetrical set.。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510150466.4A CN104713671A (en) | 2015-04-01 | 2015-04-01 | Force effect tester |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510150466.4A CN104713671A (en) | 2015-04-01 | 2015-04-01 | Force effect tester |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104713671A true CN104713671A (en) | 2015-06-17 |
Family
ID=53413192
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510150466.4A Pending CN104713671A (en) | 2015-04-01 | 2015-04-01 | Force effect tester |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104713671A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105510702A (en) * | 2016-01-26 | 2016-04-20 | 西北农林科技大学 | Effort testing device for electric multi-rotor aircraft |
| CN108845256A (en) * | 2018-06-20 | 2018-11-20 | 天津中德应用技术大学 | Unmanned plane dynamic test system |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4055996A (en) * | 1975-09-11 | 1977-11-01 | Robert Bosch Gmbh | Automotive vehicle performance test stand system and performance measuring method |
| CN201532277U (en) * | 2009-10-19 | 2010-07-21 | 浙江电力职业技术学院 | Fastener axial force-torque combination testing machine |
| US7836782B2 (en) * | 2008-05-21 | 2010-11-23 | Michigan Scientific Corporation | Motor pump torque transducer |
| CN203323726U (en) * | 2013-05-31 | 2013-12-04 | 江苏超力电器有限公司 | Direct-current motor axial play detection tool |
| CN204184580U (en) * | 2014-10-16 | 2015-03-04 | 安徽泽众安全科技有限公司 | A kind of aircraft blade power effect proving installation |
-
2015
- 2015-04-01 CN CN201510150466.4A patent/CN104713671A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4055996A (en) * | 1975-09-11 | 1977-11-01 | Robert Bosch Gmbh | Automotive vehicle performance test stand system and performance measuring method |
| US7836782B2 (en) * | 2008-05-21 | 2010-11-23 | Michigan Scientific Corporation | Motor pump torque transducer |
| CN201532277U (en) * | 2009-10-19 | 2010-07-21 | 浙江电力职业技术学院 | Fastener axial force-torque combination testing machine |
| CN203323726U (en) * | 2013-05-31 | 2013-12-04 | 江苏超力电器有限公司 | Direct-current motor axial play detection tool |
| CN204184580U (en) * | 2014-10-16 | 2015-03-04 | 安徽泽众安全科技有限公司 | A kind of aircraft blade power effect proving installation |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105510702A (en) * | 2016-01-26 | 2016-04-20 | 西北农林科技大学 | Effort testing device for electric multi-rotor aircraft |
| CN108845256A (en) * | 2018-06-20 | 2018-11-20 | 天津中德应用技术大学 | Unmanned plane dynamic test system |
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Legal Events
| Date | Code | Title | Description |
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| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| DD01 | Delivery of document by public notice |
Addressee: Beijing quadrant Science and Technology Ltd. Document name: Notification of Publication and of Entering the Substantive Examination Stage of the Application for Invention |
|
| C41 | Transfer of patent application or patent right or utility model | ||
| CB03 | Change of inventor or designer information |
Inventor after: Zhang Dongmei Inventor before: Yang Jiong |
|
| COR | Change of bibliographic data | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20151104 Address after: 100085 Beijing city Haidian District Shuangqing Road No. 3 room 31029 Applicant after: BEIJING XIANGXIAN SPATIAL TECHNOLOGY CO., LTD. Address before: 100191, Haidian District, Zhichun Road Beijing No. 22 tower, 207 Applicant before: Beijing quadrant Science and Technology Ltd. Applicant before: Yang Jiong |
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| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20150617 |
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| WD01 | Invention patent application deemed withdrawn after publication |