CN204587330U - Unmanned plane tractive performance test macro - Google Patents
Unmanned plane tractive performance test macro Download PDFInfo
- Publication number
- CN204587330U CN204587330U CN201420827374.6U CN201420827374U CN204587330U CN 204587330 U CN204587330 U CN 204587330U CN 201420827374 U CN201420827374 U CN 201420827374U CN 204587330 U CN204587330 U CN 204587330U
- Authority
- CN
- China
- Prior art keywords
- adaptor
- unmanned plane
- test macro
- performance test
- transmitter shaft
- 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.)
- Active
Links
Landscapes
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The utility model discloses a kind of unmanned plane tractive performance test macro, comprising: bearing; Adaptor: the top being positioned at described bearing, engine installation is fixed on this adaptor; Tensile tester, to be fixed on described bearing and to be positioned at the below of described adaptor, for measuring the lift of described engine installation; Coupling assembling, is arranged between described adaptor and described tensile tester, and can is connected with described tensile tester by described adaptor rapidly or take apart.Adopt technique scheme, can detect the lift of tested engine installation exactly, for the judgement of the unmanned plane quality of production and R&D process provide failure-free test parameter, and testing jig integral structure is simple and easy to use, support effect is good, thus provides guarantee for the measuring accuracy of test macro.
Description
Technical field
The utility model relates to unmanned air vehicle technique field, particularly relates to a kind of unmanned plane tractive performance test macro.
Background technology
Unmanned plane is the not manned craft utilizing radio robot to handle with the process controller provided for oneself.Rotor wing unmanned aerial vehicle is one important in unmanned plane, rotor wing unmanned aerial vehicle is divided into again the types such as single rotor, DCB Specimen, many rotors, rotor unmanned aircraft, particularly multi-rotor aerocraft, due to features such as its landing flexible, easy manipulation, good stabilities, be widely used in the purposes such as aerial reconnaissance, supervision, trunking traffic, rescue, small size mapping.The rotor lift value of rotor wing unmanned aerial vehicle is core design foundation and the product design basis for estimation of the type aircraft, and rotor lift value is relevant to motor performance, test macro at present for motor performance does not also have ripe product, to judge in the quality of production and to provide foundation in R&D process, and existing test system structure is complicated, measuring accuracy is poor.
Utility model content
Main purpose of the present utility model is to provide a kind of unmanned plane tractive performance test macro, is intended to solve the technical matters that existing test system structure is complicated, measuring accuracy is poor.
For achieving the above object, the utility model provides a kind of unmanned plane tractive performance test macro, comprising: bearing; Adaptor: the top being positioned at described bearing, engine installation is fixed on this adaptor; Tensile tester, to be fixed on described bearing and to be positioned at the below of described adaptor, for measuring the lift of described engine installation; Coupling assembling, is arranged between described adaptor and described tensile tester, and can is connected with described tensile tester by described adaptor rapidly or take apart.
Preferably, described unmanned plane tractive performance test macro also comprises testing jig, described testing jig comprises outer cover and the interior support being located at described outer cover, described bearing is fixed on described support, described support is installed on described outer cover apart from the position of the bottom certain distance of described outer cover, described outer cover is densely covered with the through hole for air circulation.
Preferably, described unmanned plane tractive performance test macro also comprises to be located in described outer cover: noise testing meter, is fixed on described bearing and also arranges, for detecting the operation noise of described engine installation near described engine installation; And/or measurement of rotating speed meter, to be fixed on described bearing and to be positioned at the below of described blade, the number of turns rotated for blade described in unit time inside counting is to calculate the rotating speed of described motor.
Preferably, described unmanned plane tractive performance test macro also comprises to be located in described outer cover: capture apparatus, just described tensile tester, noise testing meter and measurement of rotating speed meter are arranged, for obtaining the reading of described tensile tester, noise testing meter and measurement of rotating speed meter and spreading out of.
Preferably, described adaptor is thermal insulation material, and described unmanned plane tractive performance test macro also comprises the temperature test meter be located in described outer cover, for measuring the temperature of the motor of described engine installation.
Preferably, described coupling assembling comprises the first transmitter shaft and the second transmitter shaft that removably connect, and one end and the described adaptor of described first transmitter shaft are fixed, and the other end is provided with the first hook or the first link; One end and the described tensile tester of described second transmitter shaft are fixed, and the other end is provided with the second hook; Or the other end of described first transmitter shaft is provided with the first spiro connecting piece, the other end of described second transmitter shaft is provided with second spiro connecting piece that can be spirally connected with described first spiro connecting piece.
Preferably, described bearing comprises two hold-down arms be arranged symmetrically with and the first connecting panel connected between two described hold-down arms and the second connecting panel, described first connecting panel is positioned at the top of described second connecting panel, described adaptor is fixed on the upper end of described first connecting panel, described first connecting panel and described second connecting panel offer respectively at the position of described first transmitter shaft of correspondence the through hole passed for described first transmitter shaft, are provided with the linear bearing with described first transmitter shaft bearing fit in the through hole of described second connecting panel.
Preferably, described first transmitter shaft is provided with the first radially outwardly annular lip, described first annular lip is positioned at the top of described second connecting panel, described first transmitter shaft is arranged with the support spring between described first annular lip and described linear bearing.
Preferably, described first transmitter shaft is provided with the second radially outwardly annular lip, described second annular lip is positioned at the top of described second connecting panel, and in described engine installation off-duty state, described second connecting panel supports described second annular lip.
Preferably, described tensile tester has Protection Counter Functions.
A kind of unmanned plane tractive performance test macro provided by the utility model, tested engine installation and tensile tester is connected by the adaptor that only can move up and down, therefore can reduce tested engine installation produce the impact of torsion, thus detect the lift of tested engine installation exactly, for the judgement of the unmanned plane quality of production and R&D process provide failure-free test parameter, and testing jig integral structure is simple and easy to use, support effect is good, thus provides guarantee for the measuring accuracy of test macro.
Accompanying drawing explanation
Fig. 1 is the part-structure assembling schematic diagram of unmanned plane tractive performance test macro preferred embodiment of the present utility model;
Fig. 2 is the structural representation of the adaptor used in unmanned plane tractive performance test macro of the present utility model.
The realization of the utility model object, functional characteristics and advantage will in conjunction with the embodiments, are described further with reference to accompanying drawing.
Detailed description of the invention
Should be appreciated that specific embodiment described herein only in order to explain the utility model, and be not used in restriction the utility model.
The utility model provides a kind of unmanned plane tractive performance test macro, for testing the performance of the engine installation 600 on unmanned plane, wherein, and the blade 620 that this engine installation 600 comprises motor 610 and is connected in the rotating shaft of this motor 610.
See Fig. 1 and Fig. 2, in a preferred embodiment, this unmanned plane tractive performance test macro comprises bearing 100, adaptor 200 above bearing 100, is fixed on bearing 100 and tensile tester 700 in the below of adaptor 200 and the coupling assembling that is arranged between adaptor 200 and tensile tester 700.Wherein, adaptor 200 is fixed with engine installation 600; Adaptor 200 can be connected with tensile tester 700 or take apart by coupling assembling rapidly; Tensile tester 700 is for measuring the lift of engine installation 600.
Wherein, bearing 100 comprises two hold-down arms be arranged symmetrically with 110, first connecting panel 120, second connecting panel 130, the 3rd connecting panel 140, adaptor mount pad 150 and tensile tester mount pad 400.First connecting panel 120, second connecting panel 130 and the 3rd connecting panel 140 are all fixed by screws between two hold-down arms 110, and the first connecting panel 120, second connecting panel 130 and the 3rd connecting panel 140 be arranged in parallel from top to bottom successively, first connecting panel 120 is arranged on the top of hold-down arm 110, to save space.The plate face of above-mentioned three connecting panels all offers some lightening holes for expendable weight, supported on both sides arm 110 is connected from top to bottom by three spaced apart connecting panels, integrally-built Rigidity and strength is higher, good stability, is the prerequisite ensureing higher measuring accuracy.
Adaptor mount pad 150 is fixed on the first connecting panel 120, for installing adaptor 200; Tensile tester mount pad 400 to be arranged on the 3rd connecting panel 140 and to be positioned at below it, and for fixing tensile tester 700, tensile tester mount pad 400 is positioned at immediately below adaptor mount pad 150 simultaneously.On first connecting panel 120, second connecting panel 130 and the 3rd connecting panel 140, correspondence position offers the through hole passed for coupling assembling, in the through hole of wherein the second connecting panel 130, the linear bearing 131 with coupling assembling bearing fit is installed, can guarantee that the axis of coupling assembling linearly bearing 131 moves up and down thus, and then improve the measuring accuracy of unmanned plane tractive performance test macro.
Concrete, adaptor mount pad 150 has the accommodation space of accommodating adaptor 200, and adaptor 200 freely up and down can move along the sidewall of accommodation space.Adaptor 200 is roughly in cube, and the face shaping of the shape of accommodation space and adaptor 210 is suitable, is fitted by the sidewall (i.e. adaptor mount pad 150) of the peripheric surface and accommodation space that make adaptor 200 and can limit adaptor 200 and produce rotation in the horizontal plane.Should be appreciated that the exemplarily shape of adaptor 200 shown in Fig. 2, adaptor 200 can also be other any suitable shapes in other embodiments, and the utility model is not restricted this.
It should be noted that, the top of the accommodation space of adaptor mount pad 150 is opened wide and is arranged, installing space is provided to give engine installation 600, adaptor 200 can load accommodation space from the top of the accommodation space of adaptor mount pad 150, also can load accommodation space from a side of this accommodation space, and mode is assembled for the latter, a side of accommodation space should be opened when dismounting adaptor 200.In the present embodiment, the accommodation space of adaptor mount pad 150 is enclosed by multiple baffle plate and is formed, particularly, accommodation space is square, the upper end of bearing 100 is provided with four end to end baffle plates successively, wherein two are just extended with limiting section in opposite directions to the upper end of the baffle plate arranged, namely these two cross-sectional planes with the baffle plate of limiting section are roughly in falling " L " font, one of them baffle plate be connected between these two baffle plates with limiting section detachably gets off and passes in and out accommodation space for adaptor 200, by arranging limiting section on baffle plate, the movement travel of adaptor 200 in the vertical direction can be limited, thus guarantee the safety in motor performance test process.
Consider on most of motor 610 for tapped bore fixing for motor 610 being arranged on the bottom of motor 610, adaptor 200 offers and somely runs through the connecting through hole 212 of the both ends of the surface up and down of adaptor 200 around its center arrangement, the bottom of motor 610 and the upper surface of adaptor 200 offset, namely when mounted motor 610, screw is locked with motor 610 from the lower surface of adaptor 200 through connecting through hole 212, for this assembling mode, obviously need adaptor 210 to take out from the accommodation space of adaptor 200 when dismounting motor 610.
The upper end of adaptor 200 is used for rigidly-fixed power plant 600, the lower end of adaptor 200 connects coupling assembling, wherein, coupling assembling comprises the first transmitter shaft 300 and the second transmitter shaft 710, the upper end of the first transmitter shaft 300 is connected with the lower end of adaptor 200, its lower end is connected with the upper end detouchable of the second transmitter shaft 710, and lower end and the tensile tester 700 of the second transmitter shaft 710 are fixed.Concrete, the lower end of adaptor 200 is provided with the T-slot 211 of the relative both sides running through adaptor 200, the upper end of the first transmitter shaft 300 is formed with the connecting portion (not shown) with T-slot 211 grafting adaptation, such as this connecting portion is the radially outwardly annular lip that the first transmitter shaft 300 is arranged, thus by making the first transmitter shaft 300 be connected with adaptor 200 by connecting portion plug-in mounting to T-slot 211, that is in the process of accommodation space adaptor 200 being loaded adaptor mount pad 150, make the connecting portion of the first transmitter shaft 300 be inserted in T-slot 211 simultaneously, and in the process of being taken out from the accommodation space of adaptor mount pad 150 by adaptor 200, make the connecting portion of the first transmitter shaft 300 skid off from T-slot 211 simultaneously, i.e. adaptor 200 and adaptor mount pad 150, simultaneously disassembly process between first transmitter shaft 300 carries out, it is more convenient to operate.Wherein the T-slot 211 of the present embodiment can also be substituted by other any suitable chutes, and the fit structure with dovetail furrow grafting adaptation correspondingly, is arranged in the upper end of the first transmitter shaft 300 by such as dovetail furrow.
The lower end of the first transmitter shaft 300 and the upper end detouchable connection mode of the second transmitter shaft 710 have multiple, as shown in the figure, the lower end of the first transmitter shaft 300 is provided with the first hook or the first link, the upper end of the second transmitter shaft 710 is provided with can be linked up with first or the first link is mutually hung second of conjunction and linked up with, by such hook or hanging ring structure, first transmitter shaft 300 and the second transmitter shaft 710 can be coupled together or take apart fast speed, also fast speed the lift of engine installation 600 can be passed to tensile tester 700, and the first transmitter shaft 300 and the second transmitter shaft 710 are rigid construction, thus reduce the loss of lift in transmittance process, be conducive to the accuracy improving test data.
Certainly in other embodiments, also can be that the lower end of the first transmitter shaft 300 is provided with the first hook, the upper end of the second transmitter shaft 710 is provided with can link up with mutual second the linking up with or the second link of closing of hanging with first, can reach above-mentioned effect equally.Above-mentioned two embodiments are all that the first transmitter shaft 300 and the second transmitter shaft 710 mount mutually, first transmitter shaft 300 and the second transmitter shaft 710 can also be mutually be spirally connected, lower end as the first transmitter shaft 300 is screw-rod structure, and the upper end of the second transmitter shaft 710 is Screw hole structure.Certainly can also be that the lower end of the first transmitter shaft 300 and the upper end of the second transmitter shaft 710 are screw-rod structure, be coupled together by the upper end of another swivel nut by the lower end of the first transmitter shaft 300 and the second transmitter shaft 710.
In order to improve measuring accuracy, the dead in line of motor 610, first transmitter shaft 300 and the second transmitter shaft 710 is made by adjustment, thus avoid producing the impact of torsion on lift test data between motor 610, first transmitter shaft 300 and the second transmitter shaft 710, reach the measuring accuracy improving unmanned plane tractive performance test macro.
In order to eliminate the gravity of adaptor 200 and coupling assembling to the impact of the displayed value of tensile tester 700, directly can read by the lift value of engine installation 600 from tensile tester 700, in a preferred embodiment, tensile tester 700 has Protection Counter Functions.As carried out clear operation to tensile tester 700 before testing, like this when engine installation 600 runs, the lift of blade just can directly read on tensile tester 700.Certain tensile tester 700 also can not possess Protection Counter Functions, now need to record the reading that test engine installation 600 runs front tensile tester 700, if before engine installation 600 runs, first transmitter shaft 300 and the second transmitter shaft 710 do not have connection to be in not contact condition, then when engine installation 600 runs, the lift of blade 620 deducts the gravity of the reading of precedence record, the gravity of engine installation 600, the gravity of adaptor 200 and the first transmitter shaft 300 with regard to the reading equaling current tensile tester 700.If before engine installation 600 runs, the first transmitter shaft 300 is connected with the second transmitter shaft 710, then, when engine installation 600 runs, the lift of blade deducts the reading of precedence record with regard to the reading equaling current tensile tester 700.
Before engine installation 600 runs, the first transmitter shaft 300 and the second transmitter shaft 710 do not have connection to be in not contact condition, and as shown in Figure 1, the first connecting panel 120 supports adaptor 200, and then supporting motive force device 600 and the first transmitter shaft 300.Certainly in other embodiments, first connecting panel 120 also can not support adaptor 200, first transmitter shaft 300 is provided with the first radially outwardly annular lip 320, this first annular lip 320 is positioned at the top of the second connecting panel 130, and the support spring 500 the first transmitter shaft 300 is arranged with between the first annular lip 320 and linear bearing 131, support spring 500 is in elastic compression, to offset the gravity of engine installation 600, the gravity of adaptor 200 and the gravity of the first transmitter shaft 300, thus simplify the treating process of test data.Can certainly be on the first transmitter shaft 300, be provided with the second radially outwardly annular lip (not shown), this second annular lip is positioned at the top of the second connecting panel 130, in engine installation 600 off-duty state, second connecting panel 130 supports the second annular lip, and then supporting motive force device 600, adaptor 200 and the first transmitter shaft 300, the treating process of test data can be simplified equally.
As shown in the figure, tensile tester mount pad 400 comprise vertically arrange for for tensile tester 700 against backboard 410 and be vertically installed in backboard 410 for the base plate 420 supporting tensile tester 700, the upper end of backboard 410 is connected with the 3rd connecting panel 140, and backboard 410 is provided with multiple movable pressing board 411 that tensile tester 700 can be pressed on backboard 410.The backboard 410 of the present embodiment and base plate 420 can make respectively shaping after be connected by screw, also can be that integral production is shaping, than the parts that backboard 410 as shown in Figure 1 and base plate 420 are two splits settings, backboard 410 is in tabular, base plate 420 is in L-type plate, wherein one side is close to backboard 410 and is fixed by screw lock, another side is for supporting tensile tester 700, certain backboard 410 and base plate 420 can also be other any suitable shapes, and the utility model is not restricted this.
This unmanned plane tractive performance test macro also comprises testing jig, this testing jig comprises outer cover and the interior support being located at outer cover, outer cover is square shade, bearing 100 is fixed on support, the position of the bottom certain distance of support distance outer cover is installed on outer cover, outer cover is densely covered with the through hole for air circulation.The position of the bottom certain distance of support distance outer cover is installed on the space needed for air flowing that outer cover can provide blade 620 to stir; outer cover is densely covered with the through hole for air circulation; extraneous air disturbing influence blade 620 can be avoided on the one hand; the air circulation of outer cover inside and outside can be ensured on the other hand, can also play a protective role simultaneously.
In order to test the operation noise of engine installation 600, this unmanned plane dynamic test system also comprises noise testing meter (not shown), noise testing meter is fixed on bearing 100, arrange near engine installation 600, as being arranged on a hold-down arm 110 of bearing 100, for detecting the operation noise of engine installation 600.
In order to the rotating speed of testing of electric motors 610, this unmanned plane tractive performance test macro also comprises and measurement of rotating speed meter (not shown), measurement of rotating speed meter is fixed on bearing 100, be arranged on the below of blade 620, as being arranged on a hold-down arm 110 of bearing 100 (if noise testing meter is arranged on a hold-down arm 110 of bearing 100, so measurement of rotating speed meter is arranged on another hold-down arm 110 of bearing 100), for the number of turns that rotates at unit time inside counting blade 620 to calculate the rotating speed of motor 610.
In order to test the running temperature of engine installation 600, adaptor 200 is made up of the material with heat-proof quality, such as plastics, nylon etc., avoid the temperature rise of engine installation 600 to be passed to other positions of unmanned plane tractive performance test macro by adaptor 200, thus can accurately detect engine installation 600 run a period of time after temperature rise.
In view of the tensile tester 700 of the present embodiment, noise testing meter and measurement of rotating speed meter all adopt the mode of direct digital display to export test value, conveniently record the multiple test datas in test process, this unmanned plane tractive performance test macro also comprises capture apparatus (not shown), capture apparatus can be arranged on protective cover or support, configure one or more taking lens, for to tensile tester 700, noise testing meter and measurement of rotating speed meter are taken, and by the image transmission of shooting to control setup, such as showing multiple test data with on the industrial computer of read-out.
According to the technical scheme of the utility model embodiment, the lift of tested engine installation 600 can be detected exactly, for the judgement of the unmanned plane quality of production and R&D process provide failure-free test parameter, and testing jig integral structure is simple and easy to use, support effect is good, thus provides guarantee for the measuring accuracy of test macro.
These are only preferred embodiment of the present utility model; not thereby the scope of the claims of the present utility model is limited; every utilize the utility model specification sheets and accompanying drawing content to do equivalent structure or equivalent flow process conversion; or be directly or indirectly used in other relevant technical fields, be all in like manner included in scope of patent protection of the present utility model.
Claims (10)
1. a unmanned plane tractive performance test macro, is characterized in that, comprising:
Bearing;
Adaptor: the top being positioned at described bearing, engine installation is fixed on this adaptor;
Tensile tester, to be fixed on described bearing and to be positioned at the below of described adaptor, for measuring the lift of described engine installation;
Coupling assembling, is arranged between described adaptor and described tensile tester, and can is connected with described tensile tester by described adaptor rapidly or take apart.
2. unmanned plane tractive performance test macro as claimed in claim 1, it is characterized in that, described unmanned plane tractive performance test macro also comprises testing jig, described testing jig comprises outer cover and the interior support being located at described outer cover, described bearing is fixed on described support, described support is installed on described outer cover apart from the position of the bottom certain distance of described outer cover, described outer cover is densely covered with the through hole for air circulation.
3. unmanned plane tractive performance test macro as claimed in claim 2, it is characterized in that, described unmanned plane tractive performance test macro also comprises to be located in described outer cover:
Noise testing meter, is fixed on described bearing and also arranges, for detecting the operation noise of described engine installation near described engine installation; And/or,
Measurement of rotating speed meter, to be fixed on described bearing and to be positioned at the below of the blade of described engine installation, and the number of turns rotated for blade described in unit time inside counting is to calculate the rotating speed of the motor of described engine installation.
4. unmanned plane tractive performance test macro as claimed in claim 3, it is characterized in that, described unmanned plane tractive performance test macro also comprises to be located in described outer cover:
Capture apparatus, is just arranged, for obtaining the reading of described tensile tester, noise testing meter and measurement of rotating speed meter and spreading out of described tensile tester, noise testing meter and measurement of rotating speed meter.
5. unmanned plane tractive performance test macro as claimed in claim 3, it is characterized in that, described adaptor is thermal insulation material, and described unmanned plane tractive performance test macro also comprises the temperature test meter be located in described outer cover, for measuring the temperature of the motor of described engine installation.
6. the unmanned plane tractive performance test macro according to any one of claim 1 to 5, it is characterized in that, described coupling assembling comprises the first transmitter shaft and the second transmitter shaft that removably connect, one end and the described adaptor of described first transmitter shaft are fixed, and the other end is provided with the first hook or the first link; One end and the described tensile tester of described second transmitter shaft are fixed, and the other end is provided with the second hook; Or the other end of described first transmitter shaft is provided with the first spiro connecting piece, the other end of described second transmitter shaft is provided with second spiro connecting piece that can be spirally connected with described first spiro connecting piece.
7. unmanned plane tractive performance test macro as claimed in claim 6, it is characterized in that, described bearing comprises two hold-down arms be arranged symmetrically with and the first connecting panel connected between two described hold-down arms and the second connecting panel, described first connecting panel is positioned at the top of described second connecting panel, described adaptor is fixed on the upper end of described first connecting panel, described first connecting panel and described second connecting panel offer respectively at the position of described first transmitter shaft of correspondence the through hole passed for described first transmitter shaft, linear bearing with described first transmitter shaft bearing fit is installed in the through hole of described second connecting panel.
8. unmanned plane tractive performance test macro as claimed in claim 7, it is characterized in that, described first transmitter shaft is provided with the first radially outwardly annular lip, described first annular lip is positioned at the top of described second connecting panel, described first transmitter shaft is arranged with the support spring between described first annular lip and described linear bearing.
9. unmanned plane tractive performance test macro as claimed in claim 7, it is characterized in that, described first transmitter shaft is provided with the second radially outwardly annular lip, described second annular lip is positioned at the top of described second connecting panel, in described engine installation off-duty state, described second connecting panel supports described second annular lip.
10. the unmanned plane tractive performance test macro according to any one of claim 1 to 5, it is characterized in that, described tensile tester has Protection Counter Functions.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420827374.6U CN204587330U (en) | 2014-12-23 | 2014-12-23 | Unmanned plane tractive performance test macro |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420827374.6U CN204587330U (en) | 2014-12-23 | 2014-12-23 | Unmanned plane tractive performance test macro |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204587330U true CN204587330U (en) | 2015-08-26 |
Family
ID=53923511
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420827374.6U Active CN204587330U (en) | 2014-12-23 | 2014-12-23 | Unmanned plane tractive performance test macro |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204587330U (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN106347705A (en) * | 2016-10-31 | 2017-01-25 | 安徽理工大学 | Rotor lift force testing system for unmanned aerial vehicle |
| CN106394931A (en) * | 2016-11-28 | 2017-02-15 | 中国科学院长春光学精密机械与物理研究所 | Multifunctional electric detecting platform for propeller of unmanned aerial vehicle |
| CN106828971A (en) * | 2016-12-13 | 2017-06-13 | 南昌航空大学 | A kind of experimental provision for measuring single duct and single duct aircraft lift |
| CN108639377A (en) * | 2018-06-29 | 2018-10-12 | 长沙市云智航科技有限公司 | A kind of aircraft lift test device and method |
| CN108820248A (en) * | 2018-05-29 | 2018-11-16 | 上海歌尔泰克机器人有限公司 | A kind of unmanned plane dynamical system test platform |
| CN108839816A (en) * | 2018-05-24 | 2018-11-20 | 江苏理工学院 | A kind of multi-functional unmanned plane rotor system performance testing device |
| CN109071040A (en) * | 2017-12-22 | 2018-12-21 | 深圳市大疆创新科技有限公司 | The test equipment of the blade dismounting aging of unmanned vehicle |
| CN112706942A (en) * | 2020-11-11 | 2021-04-27 | 北京共创晶桔科技服务有限公司 | Unmanned aerial vehicle aging testing platform |
| CN108639377B (en) * | 2018-06-29 | 2024-06-04 | 长沙市云智航科技有限公司 | Device and method for testing lift force of aircraft |
-
2014
- 2014-12-23 CN CN201420827374.6U patent/CN204587330U/en active Active
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN106347705A (en) * | 2016-10-31 | 2017-01-25 | 安徽理工大学 | Rotor lift force testing system for unmanned aerial vehicle |
| CN106394931A (en) * | 2016-11-28 | 2017-02-15 | 中国科学院长春光学精密机械与物理研究所 | Multifunctional electric detecting platform for propeller of unmanned aerial vehicle |
| CN106828971A (en) * | 2016-12-13 | 2017-06-13 | 南昌航空大学 | A kind of experimental provision for measuring single duct and single duct aircraft lift |
| CN106828971B (en) * | 2016-12-13 | 2019-04-02 | 南昌航空大学 | A kind of experimental provision measuring single duct and single duct aircraft lift |
| CN109071040A (en) * | 2017-12-22 | 2018-12-21 | 深圳市大疆创新科技有限公司 | The test equipment of the blade dismounting aging of unmanned vehicle |
| CN108839816A (en) * | 2018-05-24 | 2018-11-20 | 江苏理工学院 | A kind of multi-functional unmanned plane rotor system performance testing device |
| CN108820248A (en) * | 2018-05-29 | 2018-11-16 | 上海歌尔泰克机器人有限公司 | A kind of unmanned plane dynamical system test platform |
| CN108639377A (en) * | 2018-06-29 | 2018-10-12 | 长沙市云智航科技有限公司 | A kind of aircraft lift test device and method |
| CN108639377B (en) * | 2018-06-29 | 2024-06-04 | 长沙市云智航科技有限公司 | Device and method for testing lift force of aircraft |
| CN112706942A (en) * | 2020-11-11 | 2021-04-27 | 北京共创晶桔科技服务有限公司 | Unmanned aerial vehicle aging testing platform |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN204587330U (en) | Unmanned plane tractive performance test macro | |
| CN109018430B (en) | Rotorcraft blade performance test bench | |
| CN104596692A (en) | Propeller thrust measuring device for small boat | |
| CN103363935B (en) | Full-automatic worm wheel double-meshing measuring machine | |
| CN106092441B (en) | A kind of simulator stand measuring dynamic balancing data | |
| CN105044599A (en) | Unmanned aerial vehicle motor-propeller efficiency test device and method | |
| CN209513146U (en) | A kind of torque calibrating device of large torque sensor | |
| CN205809193U (en) | A kind of pantograph dynamic characteristic test laboratory table | |
| CN203688050U (en) | Automatic drying, cooling, balancing and weighing device | |
| CN104179708A (en) | Comprehensive performance testing platform of high-speed magnetic levitation blower | |
| CN213544762U (en) | Turbine motor simulation test equipment with different environment simulation | |
| CN203376110U (en) | Torque verification device of torque sensor | |
| CN202676372U (en) | Dynamic balancing machine used for detecting unbalancing amount position of cross-flow fan blade | |
| CN105083585A (en) | Balance test system of four-rotor aircraft | |
| CN219101667U (en) | Ventilator test device | |
| CN207832475U (en) | A kind of electrical property and mechanical performance comprehensive test device | |
| CN109813521B (en) | Plant protection unmanned aerial vehicle wind field detection device | |
| CN206488931U (en) | Tyre noise test device and tyre noise data collecting system | |
| CN210942309U (en) | Power test bench | |
| CN109060223A (en) | Band paddle unmanned plane liter helps real-time testing system | |
| CN204881943U (en) | Measurement device for fluid friction moment | |
| CN204903726U (en) | Be suitable for efficiency testing arrangement of unmanned aerial vehicle motor - oar | |
| CN209264238U (en) | A kind of plant protection drone wind field detection device | |
| CN102901646A (en) | Test bed of cooling device of motor train unit | |
| CN113556912A (en) | Special case device of automatic instrument and meter convenient to maintain |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C41 | Transfer of patent application or patent right or utility model | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20160303 Address after: Baoan District Shiyan street Shenzhen city Guangdong province 518108 Songbai road Tangtou junctions electric science and Technology Park Patentee after: Shenzhen Aee Technology Co., Ltd. Address before: Baoan District Shiyan street Shenzhen city Guangdong province 518108 Songbai road Tangtou junctions electric science and Technology Park Patentee before: Shenzhen Aee Technology Co., Ltd. Patentee before: Shenzhen Aee Technology Co., Ltd. |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20191216 Address after: Room 812, enterprise service center, No. 17, section 3, west section of Changjiang North Road, Lingang Economic Development Zone, Yibin City, Sichuan Province Patentee after: Sichuan Yidian Aviation Technology Co., Ltd Address before: Baoan District Shiyan street Shenzhen city Guangdong province 518108 Songbai road Tangtou junctions electric science and Technology Park Patentee before: Shenzhen Yidian Aviation Technology Co., Ltd. |