CN206544607U - A kind of multiple freedom small-sized unmanned aerial vehicle testboard - Google Patents
A kind of multiple freedom small-sized unmanned aerial vehicle testboard Download PDFInfo
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- CN206544607U CN206544607U CN201720054105.4U CN201720054105U CN206544607U CN 206544607 U CN206544607 U CN 206544607U CN 201720054105 U CN201720054105 U CN 201720054105U CN 206544607 U CN206544607 U CN 206544607U
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- entablature
- pallet
- unmanned aerial
- sill
- aerial vehicle
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Abstract
The utility model is related to a kind of multiple freedom small-sized unmanned aerial vehicle testboard, this new structure is succinct, it is simple to operate, it disclosure satisfy that the testbed of 15Kg take-off weight multi-rotor unmanned aerial vehicles, testboard pallet can move (up and down ≮ 1.5m strokes, 360 ° of courses, ± 30 °~± 50 ° pitching and ± 30 °~± 50 ° rollings) with four-degree-of-freedom, and testboard pallet overcomes deadweight when moving up and down.Testboard main girder frame is that support lifting rope is installed above special cross-sectional aluminum alloy section bar, and main girder frame, and can mitigate construction weight can also increase its bending rigidity.Basetray is connected with disk using ball head structure, can realize multiple degrees of freedom flexible motion.
Description
Technical field
The utility model belongs to aviation field, more particularly to a kind of multiple freedom small-sized unmanned aerial vehicle testboard.
Background technology
The SUAV newly researched and developed can all carry out flight attitude simulation test before being taken a flight test after the completion of assembling, detect nothing
Whether man-machine in-flight each function normal, aircraft awing occur climb, land, pitching and roll attitude.In above-mentioned work
Make under state, it is most important in making aircraft in testboard up conversion and keeping various flight attitudes to be tested in plane simulation.In the past
Same category of device is tested for relatively large plane simulation, and equipment is complex, cumbersome.With the development of SUAV,
The species of SUAV is more and more, and coverage is more and more wider, and bearing for task is increasingly difficult to.SUAV ground is surveyed
Test stand being capable of full simulation SUAV flight attitude, completion data test.
The content of the invention
Goal of the invention
Realize that one kind is simple for structure, it is simple to operate, the testbed of 30Kg take-off weight multi-rotor unmanned aerial vehicles is met,
Multifreedom motion (up and down ≮ 1.5m strokes, 360 ° of courses, ± 30 °~± 50 ° pitching and ± 30 °~± 50 ° rollings) has been sought,
Testboard need to overcome deadweight when moving up and down.
Technical scheme
A kind of multiple freedom small-sized unmanned aerial vehicle testboard is provided, including main girder frame 1, pallet 2, basetray, connecting rod,
Ballast box 3 and bearing 4；
Described main girder frame 1 includes the entablature and sill that be arranged in parallel, and entablature and sill with 4 turns of bearing
Axle is connected；
One end of entablature and sill is connected with basetray rotating shaft, and the other end of entablature and sill is with connecting
Bar rotating shaft is connected, i.e., entablature, sill, basetray and connecting rod constitute quadrangle rotating mechanism；The other end of entablature is also
It is fixedly connected with ballast box 3.Pallet includes pallet joint and rotating disk, and pallet joint is coaxial socket with rotating disk, and can be mutual
Rotate, connected between pallet joint and basetray for bulb cup-and-ball joint.
Further, the top of main girder frame 1 is provided with longeron and lifting rope 5, the longeron of lifting rope 5 and entablature and sill, to carry
The rigidity of high main girder frame 1.
Further, rotating disk is applied to install unmanned plane；
Further, bearing 4 includes base and vertical beam, and described base and vertical beam can be rotated mutually, and entablature is with
Crossbeam is connected with vertical beam rotating shaft.
Further, it is provided with angular contact ball bearing between pallet joint and rotating disk.
Further, described pallet joint is provided with ball-and-socket, and basetray top is provided with bulb.
Beneficial effect
The utility model can realize tray support by adjusting counterweight and main girder frame hinge connection according to aircraft weight
Aircraft overcomes deadweight when moving up and down.Main girder frame is that support lifting rope is installed above special cross-sectional aluminum alloy section bar, and main girder frame, both
Construction weight, which can be mitigated, can also increase its bending rigidity.Basetray is connected with disk using ball head structure, can be realized many
Free degree flexible motion.
Brief description of the drawings
Fig. 1 is the utility model structural representation；
Fig. 2 is the utility model basetray structural representation；
Fig. 3 is the utility model main girder frame type sectional view；
Fig. 4 is 360 ° of course free degree schematic diagrames of the utility model；
Fig. 5 is that the utility model freely up and down spends schematic diagram；
Wherein, 1- main girder frames, 2- pallets, 3- ballast boxes, 4- bearings, 5- supports lifting rope, 6- disks, 7- bulbs, 8- pallets
Base.
Embodiment
The utility model is described in further detail below in conjunction with the accompanying drawings, Fig. 1 is referred to Fig. 5.
A kind of multiple freedom small-sized unmanned aerial vehicle testboard is provided, including main girder frame 1, pallet 2, basetray, connecting rod,
Ballast box 3 and bearing 4；
Described main girder frame 1 includes the entablature and sill that be arranged in parallel, and entablature and sill with 4 turns of bearing
Axle is connected；
One end of entablature and sill is connected with basetray rotating shaft, and the other end of entablature and sill is with connecting
Bar rotating shaft is connected, i.e., entablature, sill, basetray and connecting rod constitute quadrangle rotating mechanism；The other end of entablature is also
It is fixedly connected with ballast box 3.Pallet includes pallet joint and rotating disk, and pallet joint is coaxial socket with rotating disk, and can be mutual
Rotate, connected between pallet joint and basetray for bulb cup-and-ball joint.
Further, the top of main girder frame 1 is provided with longeron and lifting rope 5, the longeron of lifting rope 5 and entablature and sill, to carry
The rigidity of high main girder frame 1.
Further, rotating disk is applied to install unmanned plane；
Further, bearing 4 includes base and vertical beam, and described base and vertical beam can be rotated mutually, and entablature is with
Crossbeam is connected with vertical beam rotating shaft.
Further, it is provided with angular contact ball bearing between pallet joint and rotating disk.Pacified in pairs using angular contact ball bearing
Pretend as fulcrum, large axial force, stability of the increase main girder frame in motion process can be born.
The utility model is reached and left end pallet balance by configuring balancing weight in right-hand member ballast box 3.It can realize winged
Machine on testboard four-degree-of-freedom motion (up and down ≮ 1.5m strokes, 360 ° of courses, ± 30 °~± 50 ° pitching and ± 30 °~±
50 ° of rollings).And need to overcome deadweight when realizing the up and down motion of testboard pallet 1.
When course motion in 360 ° of flight test vehicle, pallet disk can be rotated with 360 ° with aircraft, as shown in sketch 5.Support
Disk disk mo(u)ld bottom half face is provided with multi-directional ball.
When flight test vehicle climbs or drops height, aircraft is moved upwardly or downwardly with pallet.Basetray is in whole process
In with pallet move up and down and slide, play a part of support and protect.
When elevating movement in flight test vehicle ± 30 °~± 50 °, pallet disk can be with ± 30 °~± 50 ° with aircraft pitch
Motion.Disk and basetray are combined by ball head structure assembling, it is possible to achieve disk rotational, as shown in sketch 2.
When tumbling motion in flight test vehicle ± 45 °, pallet disk can be with ± 45 ° with aircraft tumbling motion.
Claims (5)
1. a kind of multiple freedom small-sized unmanned aerial vehicle testboard, including main girder frame (1), pallet (2), basetray, connecting rod, match somebody with somebody
Loaded van (3) and bearing (4)；
Described main girder frame includes the entablature and sill be arrangeding in parallel, and entablature and sill connect with bearing rotating shaft
Connect；One end of entablature and sill is connected with basetray rotating shaft, and the other end of entablature and sill turns with connecting rod
Axle is connected, i.e., entablature, sill, basetray and connecting rod constitute quadrangle rotating mechanism；The other end of entablature also with
Loaded van is fixedly connected；Pallet includes pallet joint and rotating disk, and pallet joint is coaxial socket with rotating disk, and can mutually be rotated,
Connected between pallet joint and basetray for bulb cup-and-ball joint.
2. a kind of multiple freedom small-sized unmanned aerial vehicle testboard according to claim 1, it is characterised in that：In main girder frame
Side is provided with longeron and lifting rope, to improve the rigidity of main girder frame.
3. a kind of multiple freedom small-sized unmanned aerial vehicle testboard according to claim 1, it is characterised in that：Rotating disk is applicable
In installation unmanned plane.
4. a kind of multiple freedom small-sized unmanned aerial vehicle testboard according to claim 1, it is characterised in that：Bearing includes
Base and vertical beam, described base and vertical beam can be rotated mutually, and entablature and sill are connected with vertical beam rotating shaft.
5. a kind of multiple freedom small-sized unmanned aerial vehicle testboard according to claim 1, it is characterised in that：Pallet joint
Angular contact ball bearing is provided between rotating disk.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720054105.4U CN206544607U (en) | 2017-01-18 | 2017-01-18 | A kind of multiple freedom small-sized unmanned aerial vehicle testboard |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720054105.4U CN206544607U (en) | 2017-01-18 | 2017-01-18 | A kind of multiple freedom small-sized unmanned aerial vehicle testboard |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206544607U true CN206544607U (en) | 2017-10-10 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201720054105.4U Active CN206544607U (en) | 2017-01-18 | 2017-01-18 | A kind of multiple freedom small-sized unmanned aerial vehicle testboard |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107651213A (en) * | 2017-04-26 | 2018-02-02 | 天津中德应用技术大学 | Dynamic equilibrium machinery arm |
| CN109466795A (en) * | 2018-12-04 | 2019-03-15 | 湖南山河科技股份有限公司 | A kind of unmanned helicopter automatically testing platform |
| CN109823566A (en) * | 2018-12-29 | 2019-05-31 | 清华大学 | A kind of vertically taking off and landing flyer flight control system test platform |
| CN113044239A (en) * | 2019-12-26 | 2021-06-29 | 中国航空工业集团公司西安飞机设计研究所 | Supporting structure of two-degree-of-freedom test bed |
| CN113212797A (en) * | 2021-06-23 | 2021-08-06 | 天津斑斓航空科技有限公司 | Unmanned aerial vehicle debugging device and method |
-
2017
- 2017-01-18 CN CN201720054105.4U patent/CN206544607U/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107651213A (en) * | 2017-04-26 | 2018-02-02 | 天津中德应用技术大学 | Dynamic equilibrium machinery arm |
| CN109466795A (en) * | 2018-12-04 | 2019-03-15 | 湖南山河科技股份有限公司 | A kind of unmanned helicopter automatically testing platform |
| CN109466795B (en) * | 2018-12-04 | 2022-03-29 | 湖南山河科技股份有限公司 | Automatic test platform of unmanned helicopter |
| CN109823566A (en) * | 2018-12-29 | 2019-05-31 | 清华大学 | A kind of vertically taking off and landing flyer flight control system test platform |
| CN113044239A (en) * | 2019-12-26 | 2021-06-29 | 中国航空工业集团公司西安飞机设计研究所 | Supporting structure of two-degree-of-freedom test bed |
| CN113212797A (en) * | 2021-06-23 | 2021-08-06 | 天津斑斓航空科技有限公司 | Unmanned aerial vehicle debugging device and method |
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Legal Events
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: 610041 Wuhou Temple street, Chengdu, Chengdu, Sichuan Patentee after: Chengdu Katie Seiko technology Co., Ltd. Address before: 610041 Wuhou Temple street, Chengdu City, Chengdu, Chengdu, Sichuan Patentee before: Manufacturing center of Chengdu aircraft design and Research Institute |