CN205952341U - Many rotor unmanned aerial vehicle stability testing device - Google Patents
Many rotor unmanned aerial vehicle stability testing device Download PDFInfo
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- CN205952341U CN205952341U CN201620867916.1U CN201620867916U CN205952341U CN 205952341 U CN205952341 U CN 205952341U CN 201620867916 U CN201620867916 U CN 201620867916U CN 205952341 U CN205952341 U CN 205952341U
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- unmanned aerial
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- aerial vehicles
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Abstract
The utility model discloses a many rotor unmanned aerial vehicle stability testing device, including test platform and test data processing unit, test platform includes base, center pin, spider and rotor dead lever, well spindle connection base and spider, a plurality of rotor dead levers are located duplex winding center pin periphery setting on the coplanar, rotor dead lever one end connection center axle, the other end are equipped with the tongs that is used for single rotor arm of fixed unmanned aerial vehicle, the tongs top has set firmly pressure sensor, test data processing unit includes data acquisition module, data transmission module, data disaply moudle and treater, data acquisition module is connected respectively to the output of pressure sensor and spring tension meter among the test platform, data transmission to treater that data acquisition module will gather, the treater pass through the data transmission module with data transmission to the data disaply moudle in order to show data. The utility model discloses can be applicable to different rotor quantity unmanned aerial vehicle's stability testing, the concurrent operation is simple and easy, conveniently carries.
Description
Technical field
The utility model is related to unmanned plane stability test technical field, and particularly a kind of many rotor wing unmanned aerial vehicles stability is surveyed
Trial assembly is put.
Background technology
In recent years, many rotor wing unmanned aerial vehicles with its small volume, safety, application flexibly, operating efficiency extensively should the features such as high
For every field.But many rotor wing unmanned aerial vehicles cost is high, fragile, in order to allow many rotor wing unmanned aerial vehicles smoothly to fly, therefore right
The parameters such as the load performance of unmanned plane, wind resistance, stability carry out testing particularly important.
At present, the measuring technology that many rotor wing unmanned aerial vehicles Testing Platform is adopted is ripe not enough, in actual applications
Actually rare.And there is problems with current many rotor wing unmanned aerial vehicles test platform：
First, it is merely able to test the unmanned plane of single quantity rotor it is impossible to meet the stability test to various many rotors；
For many rotor wing unmanned aerial vehicles fan, unmanned plane laboratory, they may have four rotors or six rotors even eight rotors in hand
Two or more aircraft, traditional stability test platform can only test four rotors, and different for rotor quantity, and angle is not
One six rotors, this complete equipment just cannot use；
Second, existing stability test platform by volume is huge, and cost is high, and mostly unmanned plane manufacturer is using it is impossible to meet
Unmanned plane fan's economy, portable requirement.Damage for carrying out meeting with process of the test using unmanned plane, repaired
Afterwards, if stability test can not be carried out first with platform but directly take the real mode flying it is likely that causing unmanned plane
Damage again, bring huge economic loss.And current unmanned plane test platform volume is big, family can not be taken to by user
Outer flying field, nor realize the demand that commonly many rotors fan can buy.
Content of the invention
The purpose of this utility model is to provide a kind of many rotor wing unmanned aerial vehicles stability test device, and it can be applied to not
With the stability test of rotor quantity unmanned plane, operate simple simultaneously, be convenient for carrying.
The technical scheme that the utility model is taken is specially：A kind of many rotor wing unmanned aerial vehicles stability test device, including survey
Examination platform and test data processing unit；Wherein：
Test platform includes base, central shaft, spider and rotor fix bar；Central axis in spider card, and
One end connect base, the other end run through and the spider that is connected in the middle part of；Rotor fix bar quantity be multiple, in the same plane simultaneously
Around the setting of central shaft peripheral part；Rotor fix bar one end penetrates spider and connects central shaft, and the other end is provided with for fixing unmanned
The handgrip of machine single rotor arm；It is provided with pressure sensor above handgrip；
Test data processing unit includes data acquisition module, data transmission module, data disaply moudle and processor；Survey
In examination platform, the output end of pressure sensor and spring tension meter connects data acquisition module respectively, and data acquisition module will gather
The data transfer arriving is to processor；Processor sends data to data disaply moudle by data transmission module and shows number
According to.
Further, in the utility model, it is installed with above spider for shooting propeller aircraft rotary state
Photographing module.Photographing module can adopt existing various cameras, or carries out being wirelessly transferred of image using smart mobile phone.
Further, the utility model also includes protective cover, and protective cover covers at test platform peripheral part.Can ensure to try
The security tested.
Preferably, the base of test platform is provided with multiple fixing holes, and base is fixedly provided with level meter.By screw etc.
Rigidly fix thing and pass through fixing hole, base can be fixed.The setting of level meter can supply operator in base fixation procedure
Reference, whether base is horizontality, thus can ensure that test process is not affected by floor installation.Further, test and put down
The base of platform is arranged for hollow, and base is provided with weight hand-hole.Being not suitable for the ground that drills through, can in the past in hollow base plus
Enter weighted material, not only reduce weight when carrying and adapt to various ground again.
Preferably, in the utility model, central shaft includes threaded upper shaft part and lower shaft part, and lower shaft part lower end is spirally connected
Base.Central shaft can be split as needed with base or be installed, and needs can be facilitated after fractionation to carry, and can pass through central shaft
The rotation adjustment height apart from ground for the spider and base between or between upper shaft part and lower shaft part, to adapt to differing heights
Unmanned plane.
Preferably, in the utility model, rotor fix bar includes threaded canned paragraph and telescopic section, and canned paragraph connects
The opposite end of telescopic section one end rotates and connects central shaft.When not needing test, telescopic section can be rotated to canned paragraph side, to contract
The length of short rotor fix bar.The unmanned plane rotor arm of different lengths can be adapted in testing by the rotation of telescopic section.For
Convenience is fixed to each rotor according to the length of unmanned plane rotor arm, the canned paragraph of rotor fix bar in the utility model
With distance scale is respectively equipped with telescopic section, can according to scale ensure for same unmanned plane each rotor fixed position phase
With.Additionally, being alternatively slidably connected between the canned paragraph of rotor fix bar and central shaft：The circumferentially disposed slide rail of central shaft, rotor
The canned paragraph end of fix bar is slidably connected in slide rail.
Preferably, in order to adapt to different unmanned plane rotor quantity, the quantity of rotor fix bar is 8；Spider includes
Upper disk surface and lower card, are provided with two or more pillar between upper disk surface and lower card, pillar two ends respectively pass through screw be connected on
Card and lower card.Further, struts number is 4, is uniformly distributed on same circumference, and each pillar is perpendicular to center
Disk card, upper disk surface and lower card is provided with the fixing hole corresponding with strut ends so that screw can be upper from spider
Side or lower section pass through fixing hole, so with strut ends bolt；Two relative pillars are considered as a pair, cross respectively two to
Diameter line is made in post and the center of circle, and two diameter lines intersect and spider is divided into four parts, setting in the spider of each part
There are two rotor fix bars, two rotor fix bars can move or fixing in the angular range that appropriate section covers.As：Four
Partial split position angle is 15 °, 105 °, 195 °, 285 °, 8 rotor fix bars can correspond to respectively 0 °, 45 °, 90 °,
135°、180°、225°、270°、315°；When unmanned plane is only four axles, 0 °, 90 °, 180 °, 270 ° four orientation can be used
Rotor fix bar；When aircraft be six axles when, can be suitable 6 rotor fix bars are moved to 0 °, 60 °, 120 °, 180 °,
240 °, be fixed again at 300 °, measure.
Preferably, in test data processing unit of the present utility model, data transmission module adopts wireless transport module, place
Reason device passes through to carry out radio communication between data transmission module and data disaply moudle.Wireless transport module can adopt infrared, blue
The existing Radio Transmission Technology such as tooth, Wifi.Data disaply moudle can be set using the portable movement such as computer or pad, mobile phone
Standby.
The beneficial effects of the utility model are：Device volume is little, is convenient for carrying, and test process is simple to operate, easy to use,
Practicality is stronger, can carry out volume production simultaneously and reach penetration and promotion effect, facilitate unmanned plane user when needed to unmanned plane
Carry out performance test, reduce the probability of damage of unmanned plane during flying device.
Brief description
Fig. 1 show the utility model test platform part-structure schematic diagram；
Fig. 2 show base and central shaft mounting structure schematic diagram；
Fig. 3 show rotor fix bar mounting structure schematic diagram；
Fig. 4 show handgrip and pressure sensor structure schematic diagram；
Fig. 5 show spider mounting structure schematic diagram；
The schematic diagram of spider card shown in Fig. 6；
Fig. 7 show test data processing unit schematic block diagram.
Specific embodiment
Further describe below in conjunction with the drawings and specific embodiments.
In conjunction with Fig. 1 to Fig. 7, many rotor wing unmanned aerial vehicles stability test device of the present utility model, including test platform and survey
Examination data processing unit；Wherein：
Test platform includes base 1, central shaft 2, spider 3 and rotor fix bar；Central shaft 2 is perpendicular to spider 3 disk
Face, and one end connect base 1, the other end run through and the spider 3 that is connected in the middle part of；Rotor fix bar quantity is multiple, positioned at same
In plane and around the setting of central shaft peripheral part；Rotor fix bar one end penetrates spider 3 and connects central shaft 2, and the other end is provided with use
Handgrip 4 in fixing unmanned plane single rotor arm；It is installed with pressure sensor 6 above handgrip 4；
Test data processing unit includes data acquisition module, data transmission module, data disaply moudle and processor；Survey
In examination platform, the output end of pressure sensor and spring tension meter connects data acquisition module respectively, and data acquisition module will gather
The data transfer arriving is to processor；Processor sends data to data disaply moudle by data transmission module and shows number
According to.
In order to more comprehensively obtain rotary wing performance data, it is installed with for shooting rotor above the utility model spider
The photographing module of propeller rotational state.Photographing module can adopt existing various cameras, or carries out figure using smart mobile phone
Being wirelessly transferred of picture.
Embodiment
Fig. 1 to Fig. 7 show a kind of specific embodiment of the present utility model, and with reference to Fig. 1 and Fig. 2, center, 2 include screw thread
The upper shaft part 22 connecting and lower shaft part 23, lower shaft part 23 lower end is spirally connected base 1.Central shaft 2 can be torn open as needed with base 1
Divide or install, needs after fractionation, can be facilitated to carry, and can pass through between central shaft 2 and base 1 or upper shaft part 22 and lower shaft part 23
Between rotation adjustment the height apart from ground for the spider 3, to adapt to the unmanned plane of differing heights.Central shaft top arranges block
21, with fixed center disk 3.
With reference to Fig. 1 and Fig. 3, rotor fix bar includes threaded 41 and the telescopic section 42 of fixing, and canned paragraph 41 connects to be stretched
The opposite end of contracting section 42 one end rotates and connects central shaft 2.When not needing test, can be by telescopic section 42 to canned paragraph 41 1 sidespin
Turn, to shorten the length of rotor fix bar.The unmanned plane of different lengths can be adapted in testing by the rotation of telescopic section 42
Rotor arm.According to the length of unmanned plane rotor arm, each rotor is fixed for convenience, the canned paragraph of rotor fix bar and
Distance scale is respectively equipped with telescopic section, can be ensured according to scale identical for each rotor fixed position of same unmanned plane.
With reference to Fig. 3, taking two rotor fix bars as a example, telescopic section 42 is enclosed within central shaft 2 by annulus 43 and and central shaft
Closely nested.Because all rotor fix bars will be ensured all in same level, so the bend pipe by suitable length and camber
44 connect rotor fix bar and its corresponding annulus 43 so that the canned paragraph 41 of corresponding top annulus 43 is realized and lower section expansion link
On sustained height, apart from the more remote annulus of rotor fix bar place plane its be used for be connected section 41 bend pipe deformation more
Greatly.
With reference to Fig. 4, handgrip 5 is the frame-type of upper end closed, and inside top arranges pressure sensor 6, the hinged rotation in handgrip 5 side
Wing fix bar telescopic section 42, opposite side can be fixing by latching 44.Rotor rotational produces lift and makes rotor arm be subject to climbing power,
And then rotor arm contact, to the pressure sensor 3 being installed on handgrip top, thus obtains the unmanned plane motor work of required detection
When lift.
With reference to Fig. 5 and Fig. 6, in order to adapt to different unmanned plane rotor quantity, the quantity of the present embodiment rotor fix bar is 8
Individual；Spider 3 includes upper disk surface 31 and lower card 32, is provided with 4 pillars 33,33 liang of pillar between upper disk surface 31 and lower card 32
End is connected upper disk surface 31 and lower card 32 by screw 34 respectively.4 each pillars 33 are uniformly distributed on same circumference, and each
Post 33 perpendicular to spider card, upper disk surface 31 and lower card 32 be provided with the fixing hole corresponding with pillar 33 end so that
Screw 34 can pass through fixing hole above or below spider, so with pillar 33 end bolt；Relative by two
Pillar 33 is considered as a pair, crosses two respectively and makees diameter line to pillar and the spider center of circle, two diameter lines intersect and split spider
For four parts, it is provided with two rotor fix bars in the spider of each part, two rotor fix bars can be in appropriate section
Move in the angular range covering or fixing.Reference Fig. 6, such as：The split position angle of four parts be 15 °, 105 °, 195 °,
285 °, 8 rotor fix bars can correspond to 0 °, 45 °, 90 °, 135 °, 180 °, 225 °, 270 °, 315 ° respectively；When unmanned plane is only
The rotor fix bar in 0 °, 90 °, 180 °, 270 ° four orientation during four axles, can be used；When aircraft be six axles when, can be suitable general
6 rotor fix bars move to 0 °, 60 °, 120 °, 180 °, 240 °, be fixed again at 300 °, measure.
With reference to shown in Fig. 7, in test data processing unit, data transmission module adopts wireless transport module, and processor passes through
Carry out radio communication between data transmission module and data disaply moudle.Wireless transport module can adopt infrared, bluetooth, Wifi etc.
Existing Radio Transmission Technology.Data disaply moudle can be using the portable mobile device such as computer or pad, mobile phone.Data is adopted
Collection, process and transmission all adopt prior art.
Embodiment two
On the basis of embodiment one, embodiment two also sets up protective cover, and protective cover covers at test platform peripheral part.Can
The security of guarantee test.
The base of test platform is provided with multiple fixing holes, and base is fixedly provided with level meter.Rigidly solid by screw etc.
Earnest passes through fixing hole, can be fixed base.The setting of level meter can supply operator's reference, bottom in base fixation procedure
Whether seat is horizontality, thus can ensure that test process is not affected by floor installation.Further, the base of test platform
Arrange for hollow, base is provided with weight hand-hole.Being not suitable for the ground that drills through, weightening material can be added in hollow base in the past
Material, not only reduces weight and adapts to various ground again when carrying.
The utility model is in use, first passing through cement nail etc. and fix base taking the many rotor wing unmanned aerial vehicles of eight axles as a example
On the ground, the ground being drilled through in inconvenience, can carry out the filling of principal characteristic material.It is adjusted further according to level meter with true
Water conservation is put down.During use, 8 rotor fix bars correspond to 0 °, 45 °, 90 °, 135 °, 180 °, 225 °, 270 °, 315 ° of position respectively
And fix pillar, then pole length is fixed according to each rotor of unmanned plane rotor arm lengths adjustment, then open handgrip with fixation
Rotor arm.
Check many rotor wing unmanned aerial vehicles hardware and connect unmanned electromechanical source, control rotor rotational speed from slow to fast, counting
Read surveyed data according to display module, then can be had problems according to the many rotor wing unmanned aerial vehicles of data analysis, take countermeasure.
If carrying out the stability measurement of six rotor wing unmanned aerial vehicles, need loosen respective strut, will positioned at 60 °,
120 °, 240 °, 320 ° of correspondence position screws open, then the former rotor fix bar 45 is rotated to 60 °, the former rotation at 135 °
Wing fix bar rotates to 120 °, and the former rotor fix bar at 225 ° rotates to 240 °, the former rotor fix bar at 315 ° rotate to
300 °, respective strut and screw are being retightened；Keep in situ positioned at 0 ° and 180 ° of rotor fix bar, former at 90 ° and
270 ° of rotor fix bar indentation spider, is so just transformed into the required platform of six rotor detections.
The utility model device volume is little, is convenient for carrying, and test process is simple to operate, easy to use, and practicality is stronger, with
When can carry out volume production and reach penetration and promotion effect, facilitate unmanned plane user that when needed unmanned plane is carried out with performance test,
Reduce the probability of damage of unmanned plane during flying device.
Above-described only presently preferred embodiments of the present invention, not in order to limit the present invention, every essence in the present invention
Within god and principle, any modification, equivalent substitution and improvement made etc., all should be contained within protection scope of the present invention.
Claims (10)
1. a kind of many rotor wing unmanned aerial vehicles stability test device, is characterized in that, including test platform and test data processing unit；
Wherein：
Test platform includes base, central shaft, spider and rotor fix bar；Central axis are in spider card, and one end
Connect base, the other end run through and the spider that is connected in the middle part of；Rotor fix bar quantity be multiple, in the same plane and around in
Heart axle peripheral part is arranged；Rotor fix bar one end penetrates spider and connects central shaft, and the other end is provided with for fixing unmanned plane list
The handgrip of individual rotor arm；It is installed with pressure sensor above handgrip；
Test data processing unit includes data acquisition module, data transmission module, data disaply moudle and processor；Test is flat
In platform, the output end of pressure sensor and spring tension meter connects data acquisition module respectively, and data acquisition module will collect
Data transfer is to processor；Processor sends data to data disaply moudle with display data by data transmission module.
2. many rotor wing unmanned aerial vehicles stability test device according to claim 1, is characterized in that, fixing peace above spider
Equipped with the photographing module for shooting propeller aircraft rotary state.
3. many rotor wing unmanned aerial vehicles stability test device according to claim 1, is characterized in that, also includes protective cover, protects
Guard shield covers at test platform peripheral part.
4. the many rotor wing unmanned aerial vehicles stability test device according to any one of claims 1 to 3, is characterized in that, test is flat
The base of platform is provided with multiple fixing holes, and base is fixedly provided with level meter.
5. many rotor wing unmanned aerial vehicles stability test device according to claim 4, is characterized in that, the base of test platform is
Hollow is arranged, and base is provided with weight hand-hole.
6. the many rotor wing unmanned aerial vehicles stability test device according to any one of claims 1 to 3, is characterized in that, central shaft
Including threaded upper shaft part and lower shaft part, lower shaft part lower end is spirally connected base.
7. the many rotor wing unmanned aerial vehicles stability test device according to any one of claims 1 to 3, is characterized in that, rotor is solid
Fixed pole includes threaded canned paragraph and telescopic section, and the opposite end that canned paragraph connects telescopic section one end rotates connection central shaft.
8. many rotor wing unmanned aerial vehicles stability test device according to claim 7, is characterized in that, the fixation of rotor fix bar
It is respectively equipped with distance scale in section and telescopic section.
9. many rotor wing unmanned aerial vehicles stability test device according to claim 8, is characterized in that, the quantity of rotor fix bar
For 8；
Spider includes upper disk surface and lower card, and upper disk surface is vertical with lower card to be provided with 4 pillars, and 4 pillars are uniformly distributed
On same circumference, upper disk surface and lower card are provided with the fixing hole corresponding with strut ends so that screw can be therefrom
Above or below cartridge pass through fixing hole, and then with strut ends bolt；
Two relative pillars are considered as a pair, cross two respectively and diameter line is made to pillar and the center of circle, then two diameter lines intersect and incite somebody to action
Spider is divided into four parts, is provided with two rotor fix bars, two rotor fix bars can in the spider of each part
Move in the angular range that appropriate section covers or fixing.
10. the many rotor wing unmanned aerial vehicles stability test device according to any one of claims 1 to 3, is characterized in that, tests number
Adopt wireless transport module according to data transmission module in processing unit, processor passes through data transmission module and data disaply moudle
Between carry out radio communication.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620867916.1U CN205952341U (en) | 2016-08-11 | 2016-08-11 | Many rotor unmanned aerial vehicle stability testing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620867916.1U CN205952341U (en) | 2016-08-11 | 2016-08-11 | Many rotor unmanned aerial vehicle stability testing device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205952341U true CN205952341U (en) | 2017-02-15 |
Family
ID=57974655
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620867916.1U Expired - Fee Related CN205952341U (en) | 2016-08-11 | 2016-08-11 | Many rotor unmanned aerial vehicle stability testing device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205952341U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108163229A (en) * | 2018-01-24 | 2018-06-15 | 东南大学 | Flapping wing robot lift thrust detecting system synchronous with wing movable information and method |
| CN108267307A (en) * | 2018-01-19 | 2018-07-10 | 辽宁工程技术大学 | A kind of experimental provision for simulating marine propeller erosive wear |
-
2016
- 2016-08-11 CN CN201620867916.1U patent/CN205952341U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108267307A (en) * | 2018-01-19 | 2018-07-10 | 辽宁工程技术大学 | A kind of experimental provision for simulating marine propeller erosive wear |
| CN108163229A (en) * | 2018-01-24 | 2018-06-15 | 东南大学 | Flapping wing robot lift thrust detecting system synchronous with wing movable information and method |
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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: 20170215 Termination date: 20180811 |