CN205150273U - 6 -degree of freedom unmanned aerial vehicle attitude control testing arrangement - Google Patents
6 -degree of freedom unmanned aerial vehicle attitude control testing arrangement Download PDFInfo
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- CN205150273U CN205150273U CN201520850108.XU CN201520850108U CN205150273U CN 205150273 U CN205150273 U CN 205150273U CN 201520850108 U CN201520850108 U CN 201520850108U CN 205150273 U CN205150273 U CN 205150273U
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Abstract
The utility model provides a 6 -degree of freedom unmanned aerial vehicle attitude control testing arrangement, including base, frame, three degree of freedom joints, a rotating device, first revolute pair, the 2nd rotating device, second revolute pair, installing module, third revolute pair and unmanned aerial vehicle module, wherein: the base is fixed in ground or table surface, be connected through three degree of freedom joints between frame and the base, a rotating device is connected through first revolute pair with the frame, the second revolute pair of passing through the 2nd rotating device and a rotating device realizes connecting, installing module and the 2nd rotating device are connected through the third revolute pair, the unmanned aerial vehicle module is installed on installing module, through above connected mode for the unmanned aerial vehicle module possess the spatial movement of six degrees of freedom. The utility model discloses space usage is very little, can carry out unmanned aerial vehicle's indoor debugging, has avoided the complicated flow of outdoor debugging to avoid debugging the unsafe factor that the in -process caused to crowd and unmanned aerial vehicle.
Description
Technical field
The utility model relates to technical field of aerospace, is specifically related to a kind of six degree of freedom UAV Attitude and controls proving installation.
Background technology
Robot airplane is called for short " unmanned plane ", and english abbreviation is " UAV ", is the not manned aircraft utilizing radio robot to handle with the process controller provided for oneself.Can be divided into from technical standpoint definition: depopulated helicopter, unmanned fixed-wing aircraft, unmanned multi-rotor aerocraft, unmanned airship, unmanned parasol etc.
From development prospect, the development prospect of unmanned plane is immeasurable.Taking photo by plane, express delivery, post-disaster search and rescue, the field such as data acquisition, unmanned plane is all shown up prominently.Although in aspects such as supervision, Development of UAV still exists bottleneck, at present, unmanned plane industrial chain flourish has been undisputable fact.Unmanned plane+sector application is the real firm need of unmanned plane.At present taking photo by plane, agricultural plant protection, the field such as mapping application, expanded the purposes of unmanned plane itself greatly.
Along with the continuous progress of unmanned air vehicle technique, its performance is become better and better, and the function of realization becomes increasingly abundant.Meanwhile, the development cost of unmanned plane is also more and more higher, when the natural environment of dangerous complexity, has paid great cost.The safety of each airborne equipment of Unmanned Aircraft Systems (UAS), reliability cause the concern of people day by day, therefore build a set of comprehensive unmanned aerial vehicle comprehensive test platform more and more important and urgent.
There are some outstanding problems in the test equipment of current China unmanned plane, as lacked unified planning, function singleness, normalisation, seriation and generalization degree are low.This just requires that modern unmanned plane comprehensive performance testing system can meet and more fully tests needs: at unmanned plane development phase, can carry out actv. detection and assessment to UAV Flight Control rate; In the flight preparation stage, convenience and comprehensive functional detection can be carried out to flight control system; After flight terminates, ex-post analysis, simulation and fault zero can be carried out to aloft fault; In follow-up development, can test amended flight control system and verify.
Utility model content
The purpose of this utility model, be intended to for the developer of unmanned plane provides a kind of six degree of freedom UAV Attitude to control proving installation, the debugging efforts of unmanned plane can be made to become convenient, efficient, safety, and can make the attitude of unmanned plane in debug process, have required space six degree of freedom (pitching, driftage, roll, all around, lifting), thus promote the process of flight control system exploitation
The technical solution adopted in the utility model is:
The utility model provides a kind of six degree of freedom UAV Attitude to control proving installation, comprise base, framework, three degree of freedom joint, the first wheel word, the first revolute pair, the second wheel word, the second revolute pair, installation module, the 3rd revolute pair and unmanned plane module, wherein: described base is fixed on ground or work top; Be connected by described three degree of freedom joint between described framework with described base, thus make described framework have all around, lifting three degree of freedom; Described first wheel word is connected by described first revolute pair with described framework, thus makes described first wheel word have rotary freedom around X-direction; Realize connecting by described second revolute pair between described second wheel word and described first wheel word, thus make described second wheel word have rotary freedom around Y direction; Be connected by described 3rd revolute pair between described installation module with described second wheel word, thus make described installation module have the rotary freedom of around the Z-axis direction; Described unmanned plane module is installed on described installation module; By above connection mode, make described unmanned plane module have rotary freedom around X, Y, Z axis three directions and pitching, driftage, roll, and all around, lifting, amount to the space motion of six-freedom degree.
Preferably, described framework is rigidly connected by a sliding bar and frame and forms, and sliding bar is connected by three degree of freedom joint with base, thus the connection of implementation framework and base.
Preferably, described three degree of freedom joint is realized by universal-joint, bearing array mode, sliding bar realizes all around, lifting three degree of freedom by three degree of freedom joint, and drive frame to realize all around, lifting three degree of freedom, thus framework is made to have the space motion of all around, lifting three degree of freedom.
Preferably, the first described revolute pair is bearing, and the first revolute pair is rotated around X-direction, thus drive the first wheel word has the rotary freedom around X-direction.
Preferably, the second described revolute pair is bearing, and the second revolute pair is rotated around Y direction, thus drive the second wheel word has the rotary freedom around Y direction.
Preferably, the 3rd described revolute pair is bearing, and the 3rd revolute pair is rotated around Z-direction, thus drive installation module has the rotary freedom around Z-direction.
When building, the combined action of installation module and base will ensure the safety of unmanned plane module, make it the flight debugging carrying out flight control system in rational claimed range, ensure the personal safety of commissioning staff, make debugging efforts can carry out low-level flight in indoor simultaneously, avoid the Complicated Flow of outdoor debugging and it is to the rigors of meteorological conditions, and the generation of air crash accident can be avoided, reduce R&D costs.
Compared with prior art, the utility model has following beneficial effect:
The utility model is used for controlling to carry out six degree of freedom HWIL simulation to the flight attitude stability of unmanned plane (being mainly used in the unmanned plane of many rotors and helicopter type); This utility model space uses very little, can carry out the debugging of unmanned plane, avoid the Complicated Flow of outdoor debugging, and avoid in debug process the safety hazard that crowd and unmanned plane cause.This utility model is based on mechanical six degree of freedom Design of Mechanical Structure principle, after unmanned plane carries out semi-physical real-time simulation by said system, developer just can by determining aircraft aloft actual parameter on the spot to the monitoring of flight correlation parameter and exploration in debug process, from guaranteeing that the attitude of unmanned plane flight course on the spot is steady, reach the effect that UAV Attitude controls test; Meanwhile, this device can carry out safe debugging in indoor, and the property damage brought due to air crash when decreasing outdoor flight and fatal accident, reduce the research and development difficulty of unmanned plane product, promote developing rapidly of unmanned plane industry.
Accompanying drawing explanation
Fig. 1 is the integrated stand composition of the utility model one embodiment;
Fig. 2 is the unmanned plane during flying attitude instruction diagram of the utility model one embodiment;
In figure: framework 1, first wheel word 2, second wheel word 3, installation module 4, unmanned plane module 5, three degree of freedom joint 6, base 7, first revolute pair 8, second revolute pair 9, the 3rd revolute pair 10.
Detailed description of the invention
Below in conjunction with accompanying drawing, the utility model is described in detail.Following examples will contribute to those skilled in the art and understand the utility model further, but not limit utility model in any form.It should be pointed out that to one skilled in the art, not departing under prerequisite of the present utility model, some distortion and improvement can also be made.These all belong to protection domain of the present utility model.
As shown in Figure 1, a kind of six degree of freedom UAV Attitude controls proving installation, comprise framework 1, first wheel word 2, second wheel word 3, installation module 4, unmanned plane module 5, three degree of freedom joint 6, base 7, wherein: base 7 is fixed on the fixed surface such as ground or desktop, and and connected by three degree of freedom joint 6 between framework 1, thus make framework 1 have all around, lifting three degree of freedom; First wheel word 2 is connected by the first revolute pair 8 with framework 1, thus makes the first wheel word 2 have rotary freedom around X-direction; Connected by the second revolute pair 9 between second wheel word 3 and the first wheel word 2, thus make the second wheel word 3 have rotary freedom around Y direction; Connected by the 3rd revolute pair 10 between installation module 4 and the second wheel word 3, thus make installation module 4 have the rotary freedom of around the Z-axis direction; Unmanned plane module 5 is installed on installation module 4; By above-mentioned connection mode, make unmanned plane module 5 have rotary freedom around X, Y, Z axis three directions and pitching, driftage, roll, and all around, lifting, amount to the space motion of six-freedom degree.
In the present embodiment, when building, the combined action of installation module 4 and base 7 will ensure the safety of unmanned plane module 5, make it the flight debugging carrying out flight control system in rational claimed range, ensure the personal safety of commissioning staff, make debugging efforts can carry out low-level flight in indoor simultaneously, avoid the Complicated Flow of outdoor debugging and it is to the rigors of meteorological conditions, and the generation of air crash accident can be avoided, reduce R&D costs.
After device is built, adopt the emulation software module coordinated with it, emulation software module is connected with unmanned plane module 5 by wired or wireless mode, and realizing in real time online, the various piece combined action of whole device can make unmanned plane under the environment of safety, carry out space six-degree-of-freedom posture comprehensive debugging required in pose stabilization control debug process; Developer, by determining the aloft actual parameter of unmanned plane module to the monitoring of flight correlation parameter and exploration in debug process, from guaranteeing that the attitude of unmanned plane module flight course is steady, reaches the effect that UAV Attitude controls test.
In one embodiment, described framework 1 is rigidly connected by a sliding bar and frame and forms, and sliding bar is connected by three degree of freedom joint 6 with base 7, thus the connection of implementation framework 1 and base 7.
In one embodiment, described three degree of freedom joint 6 is realized by universal-joint, bearing array mode, sliding bar realizes all around, lifting three degree of freedom by three degree of freedom joint 6, and drive frame to realize all around, lifting three degree of freedom, thus framework 1 is made to have the space motion of all around, lifting three degree of freedom.
The first described revolute pair 8 is bearing, and the first revolute pair 8 is rotated around X-direction (pitching), thus drive the first wheel word 2 has the rotary freedom around X-direction (pitching).
The second described revolute pair 9 is bearing, and the second revolute pair 9 is rotated around Y direction (driftage), thus drive the second wheel word 3 has the rotary freedom around Y direction (driftage).
The 3rd described revolute pair 10 is bearing, and the 3rd revolute pair 10 is rotated around Z-direction (roll), thus drive installation module 4 has the rotary freedom around Z-direction (roll).
Above-mentioned X-axis, Y-axis, Z axis are three axles (as shown in Figure 2) of rectangular coordinate system in space.
The present embodiment is intended to carry out semi-physical real-time simulation test to unmanned plane during flying attitude control system stability, comprising the pitching of unmanned plane, driftage, roll, all around, lifting (as Fig. 2), amounts to six-freedom degree.Adopt in the simulation software coordinated to the real-time adjustment of every flight parameter with develop stable flight control system to the observation of flight attitude stability.
The present embodiment in use, needs the flight control system of unmanned plane installed and power on, and carries out the pitching of unmanned plane, driftage, roll, all around, dipping and heaving by manipulating unmanned plane.
Device described in the present embodiment is based on mechanical six degree of freedom Design of Mechanical Structure principle, dynamic response during by running on this device unmanned plane, adjustment control policy that can be real-time and correlation parameter, facilitate scientific research personnel and engineer's (especially lacking the developer of flight manipulation experience) to carry out exploitation and debugging efforts that unmanned plane flies control products; Simultaneously, this simulator can carry out safe debugging in indoor, and the property damage brought due to air crash when decreasing outdoor flight and fatal accident, reduce the research and development difficulty of unmanned plane product, promote developing rapidly of unmanned plane industry.
Above specific embodiment of the utility model is described.It is to be appreciated that the utility model is not limited to above-mentioned particular implementation, those skilled in the art can make various distortion or amendment within the scope of the claims, and this does not affect flesh and blood of the present utility model.
Claims (6)
1. a six degree of freedom UAV Attitude controls proving installation, it is characterized in that, comprise base, framework, three degree of freedom joint, the first wheel word, the first revolute pair, the second wheel word, the second revolute pair, installation module, the 3rd revolute pair and unmanned plane module, wherein: described base is fixed on ground or work top; Be connected by described three degree of freedom joint between described framework with described base, thus make described framework have all around, lifting three degree of freedom; Described first wheel word is connected by described first revolute pair with described framework, thus makes described first wheel word have rotary freedom around X-direction; Realize connecting by described second revolute pair between described second wheel word and described first wheel word, thus make described second wheel word have rotary freedom around Y direction; Be connected by described 3rd revolute pair between described installation module with described second wheel word, thus make described installation module have the rotary freedom of around the Z-axis direction; Described unmanned plane module is installed on described installation module; By above connection mode, make described unmanned plane module have rotary freedom around X, Y, Z axis three directions and pitching, driftage, roll, and all around, lifting, amount to the space motion of six-freedom degree.
2. a kind of six degree of freedom UAV Attitude according to claim 1 controls proving installation, it is characterized in that, described framework is rigidly connected by a sliding bar and frame and forms, and sliding bar is connected by three degree of freedom joint with base, thus the connection of implementation framework and base.
3. a kind of six degree of freedom UAV Attitude according to claim 1 controls proving installation, it is characterized in that, described three degree of freedom joint is realized by universal-joint, bearing array mode, sliding bar realizes all around, lifting three degree of freedom by three degree of freedom joint, and drive frame to realize all around, lifting three degree of freedom, thus framework is made to have the space motion of all around, lifting three degree of freedom.
4. a kind of six degree of freedom UAV Attitude according to any one of claim 1-3 controls proving installation, it is characterized in that, the first described revolute pair is bearing, and the first revolute pair is rotated around X-direction, thus drive the first wheel word has the rotary freedom around X-direction.
5. a kind of six degree of freedom UAV Attitude according to any one of claim 1-3 controls proving installation, it is characterized in that, the second described revolute pair is bearing, and the second revolute pair is rotated around Y direction, thus drive the second wheel word has the rotary freedom around Y direction.
6. a kind of six degree of freedom UAV Attitude according to any one of claim 1-3 controls proving installation, it is characterized in that, the 3rd described revolute pair is bearing, and the 3rd revolute pair is rotated around Z-direction, thus drive installation module has the rotary freedom around Z-direction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201520850108.XU CN205150273U (en) | 2015-10-29 | 2015-10-29 | 6 -degree of freedom unmanned aerial vehicle attitude control testing arrangement |
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| CN201520850108.XU CN205150273U (en) | 2015-10-29 | 2015-10-29 | 6 -degree of freedom unmanned aerial vehicle attitude control testing arrangement |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105270650A (en) * | 2015-10-29 | 2016-01-27 | 上海交通大学 | Attitude control test device for six-degree-of-freedom unmanned aerial vehicle |
| CN106742051A (en) * | 2016-11-28 | 2017-05-31 | 歌尔科技有限公司 | A kind of aircraft hovering functional stabilization method of testing and system |
-
2015
- 2015-10-29 CN CN201520850108.XU patent/CN205150273U/en not_active Withdrawn - After Issue
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105270650A (en) * | 2015-10-29 | 2016-01-27 | 上海交通大学 | Attitude control test device for six-degree-of-freedom unmanned aerial vehicle |
| CN106742051A (en) * | 2016-11-28 | 2017-05-31 | 歌尔科技有限公司 | A kind of aircraft hovering functional stabilization method of testing and system |
| CN106742051B (en) * | 2016-11-28 | 2023-07-21 | 歌尔科技有限公司 | Aircraft hovering function stability testing method and system |
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| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20160413 Effective date of abandoning: 20180420 |