CN103010483A - Two-DOF (Degrees of Freedom) test platform for micro aerial vehicle - Google Patents
Two-DOF (Degrees of Freedom) test platform for micro aerial vehicle Download PDFInfo
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- CN103010483A CN103010483A CN2012105004565A CN201210500456A CN103010483A CN 103010483 A CN103010483 A CN 103010483A CN 2012105004565 A CN2012105004565 A CN 2012105004565A CN 201210500456 A CN201210500456 A CN 201210500456A CN 103010483 A CN103010483 A CN 103010483A
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- turntable
- lower turntable
- rotating shafts
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Abstract
A two-DOF (Degrees of Freedom) test platform for a micro aerial vehicle is applied to flight static debugging and posture simulation of a micro four-axis aerial vehicle and belongs to the electromechanical field. Rotating shafts (2) are fixed on a lower turntable (3); an upper turntable (7) and the lower turntable (3) are connected through two rotating shafts (2) connected to form a straight line and can rotate around the two rotating shafts (2) through which the upper turntable (7) and the lower turntable (3) are connected; two rotating shafts (2) of the lower turntable (3), not connected with the upper turntable (7), are respectively connected with two pillars (4); the lower turntable (3) can rotate around the two rotating shafts (2) connected with the pillars (4); and the two pillars (4) are fixed on a base (6). The two-DOF test platform is light in weight, small in size and light and convenient in rotation, and causes small interference to the micro four-axis aerial vehicle, and low energy consumption is caused when the aerial vehicle overcomes rotational friction and rotational inertia on the test platform during a test. The two-DOF test platform has a real aerial vehicle test result and has a better simulation effect.
Description
Technical field
The present invention relates to a kind of two-freedom minute vehicle test platform, be applied to flight static debugging and the attitude-simulating of miniature four-axle aircraft, belong to dynamo-electric field.
Background technology
At present, more and more, more and more deep to the research of four-axle aircraft both at home and abroad.Wherein, miniature four-axle aircraft is one of them branch.When controlling design in the attitude of the miniature four-axle aircraft of research with to it, the researchist is usually worried in carrying out static flight simulation to aircraft.Because live flight has been full of the danger of air crash regularly, miniature four-axle aircraft is made complicated, and cost is not low.Therefore the mechanical device of designing the static flight simulation of the miniature four-axle aircraft of a cover and being used for flight attitude control research becomes very necessary.
Summary of the invention
The object of the present invention is to provide a kind of mechanical platform for miniature four-axle aircraft flight static debugging and attitude-simulating test.
To achieve these goals, the present invention has taked following technical scheme:
Two-freedom minute vehicle test platform, it includes two upper turntable location jackscrews 1, four rotating shafts 2, lower turntable 3, upper turntable 7, two lower turntables are located jackscrews 8, four adjustment copper sheet 9, pillar 4 and bases 6; Four rotating shafts 2 are fixed on the lower turntable 3, and described rotating shaft 2 is in line in twos, and wherein the straight line that is linked to be of the straight line that is linked to be of two rotating shafts 2 and two other rotating shaft 2 intersects vertically; Upper turntable 7 and lower turntable 3 by described wherein two be connected straight rotating shaft 2 and connect, and can rotate with two rotating shafts 2 of lower turntable 3 around connecting upper turntable 7; Also there are respectively two to be used for adjusting the upward adjustment copper sheet 9 of the center of turntable 7 in the rotating shaft 2 in the connection between turntable 7 and the lower turntable 3; Also be connected with in the rotating shaft 2 in the connection between turntable 7 and the lower turntable 3 for two the upper turntable location jackscrews 1 of turntable on the fixed adjustment 7 with respect to the angle of lower turntable 3; Two rotating shafts 2 that lower turntable 3 does not connect turntable 7 are connected with two pillars 4 respectively, and lower turntable 3 can rotate around two rotating shafts 2 of connecting struts 4.Connect and also be useful on respectively the center of adjusting lower turntable 3 in two rotating shafts 2 of two pillars 4 and lower turntable 3 and adjust copper sheet 9; Connect two lower turntable location jackscrews 8 that also are connected with in the rotating shaft 2 between lower turntable 3 and the pillar 4 for 3 angles of turntable under the fixed adjustment.
Rotating shaft 2 is vertically fixed on the lower turntable 3 by welding.
Two pillars 4 are fixed on the base 6 by pillar fix screw 5.
The present invention adopts pure physical construction, has solved dexterously the difficult problem of miniature four-axle aircraft static test.Of the present invention lightweight, volume is little, rotates lightly, and little to the interference of miniature four-axle aircraft, it is little that aircraft when test overcomes the energy that pivoting friction and rotor inertia consume at this device.The aircraft test result is true, and simulate effect is better.
Description of drawings
Fig. 1 system schematic of the present invention
The constructional drawing of Fig. 2 pillar of the present invention
The constructional drawing of turntable in Fig. 3 the present invention
The constructional drawing of turntable under Fig. 4 the present invention
Among the figure: 1, upper turntable is located jackscrew; 2, rotating shaft; 3, lower turntable; 4, pillar; 5, pillar fix screw; 6, base; 7, upper turntable; 8, lower turntable is located jackscrew; 9, adjust copper sheet; 10, lower turntable shaft hole; 11, pillar fixing screw hole; 12, lower turntable is located top wire hole; 13, upper turntable is located top wire hole; 14, upper turntable shaft hole; 15, the large plane of lower turntable; 16, lower turntable vertical surface.
The specific embodiment
The present invention will be further described in conjunction with Fig. 1-Fig. 4:
Two-freedom minute vehicle test platform, it includes two upper turntable location jackscrews 1, four rotating shafts 2, lower turntable 3, upper turntable 7, two lower turntables are located jackscrews 8, four adjustment copper sheet 9, pillar 4 and bases 6.Fixing aircraft on the upper turntable 7, and can rotating around two rotating shafts 2 between lower turntable 3 and the upper turntable 7, thus realize the rotation of aircraft one degree of freedom.Two rotating shafts 2 that are connected with pillar on the lower turntable 3 are vertical with two rotating shafts 2 on the upper turntable 7, and can rotate by the lower turntable shaft hole 10 on pillar 4, thereby realize the rotation of another degree of freedom of aircraft.Pillar 4 is fixed on the base 6, and base 6 is placed on the horizontal table top, is used for supporting whole device.
Four rotating shafts 2 are vertically fixed on the large plane 15 of lower turntable on the lower turntable 3 in twos by welding.Upper turntable shaft hole 14 on the upper turntable 7 cooperates with two rotating shafts 2 on the lower turntable 3, and can 2 rotate around the shaft.Two upper turntable location jackscrews 1 are installed in the top wire hole 13 of turntable location, are used for the angle between fixing upper turntable 7 and the lower turntable 3.Unclamp turntable location jackscrew 1, aircraft just can freely rotate in this degree of freedom.Also there are respectively two to adjust copper sheet 9 in the connection in the rotating shaft 2 of turntable 7 and lower turntable 3, are used for adjusting the distance between the lower turntable vertical surface 16 on upper turntable 7 and the lower turntable 3, thereby make turntable 7 be positioned at the center of lower turntable 3.In addition two rotating shafts 2 on the lower turntable 3 cooperate with lower turntable shaft hole 10 on two pillars 4 respectively, lower turntable shaft hole 10 rotations that lower turntable 3 can be on pillar 4.Two lower turntable location jackscrews 8 are installed in the top wire hole 12 of lower turntable location, are used for the angle between fixing lower turntable 3 and the base 6.Unclamp lower turntable location jackscrew 8, aircraft just can freely rotate in this degree of freedom.Also there are respectively two to adjust copper sheet 9 in the rotating shaft 2 of connecting struts 4 and lower turntable 3, are used for adjusting the distance between the lower turntable vertical surface 16 on pillar 4 and the lower turntable 3, thereby make lower turntable 3 be positioned at the center of base 6.
Above-mentioned upper turntable 7 materials are carbon fiber, and thickness is about 0.001 meter, and length is about 0.05 meter, and width is about 0.01 meter.The material of rotating shaft 2 is 45 steel, chrome-faced, and diameter is 0.002 meter, length is 0.01 meter.Angle between per two rotating shafts 2 is 90 °, and four rotating shafts 2 are in same plane.Lower turntable 3 materials are carbon fiber, and thickness is about 0.001 meter, and length is about 0.01 meter.
The present invention is simple to operate, and volume is small and exquisite.Can be used for the static flight simulation of miniature four-axle aircraft and be used for flight attitude control research.
Claims (3)
1. two-freedom minute vehicle test platform is characterized in that:
It includes two upper turntable location jackscrews (1), four rotating shafts (2), lower turntable (3), upper turntable (7), two lower turntable location jackscrews (8), four adjustment copper sheet (9), pillar (4) and bases (6); Four rotating shafts (2) are fixed on the lower turntable (3), and described rotating shaft (2) is in line in twos, and wherein the straight line that is linked to be of the straight line that is linked to be of two rotating shafts (2) and two other rotating shaft (2) intersects vertically; Upper turntable (7) and lower turntable (3) by described wherein two be connected straight rotating shaft (2) and connect, and can rotate with two rotating shafts (2) of lower turntable (3) around connecting upper turntable (7); Also there are respectively two to be used for adjusting the upward adjustment copper sheet (9) of the center of turntable (7) in the rotating shaft (2) between turntable in the connection (7) and the lower turntable (3); Also be connected with in the rotating shaft (2) between turntable in the connection (7) and the lower turntable (3) for two the upper turntable location jackscrews (1) of turntable on the fixed adjustment (7) with respect to the angle of lower turntable (3); Two rotating shafts (2) that lower turntable (3) does not connect turntable (7) are connected with two pillars (4) respectively, and lower turntable (3) can rotate around two rotating shafts (2) of connecting struts (4); Connect and also be useful on respectively the center of adjusting lower turntable (3) in two rotating shafts (2) of two pillars (4) and lower turntable (3) and adjust copper sheet (9); Connect two lower turntable location jackscrews (8) that also are connected with in the rotating shaft (2) between lower turntable (3) and the pillar (4) for turntable under the fixed adjustment (3) angle;
Base (6) is placed on the horizontal table top, and two pillars (4) are fixed on the base (6), and two lower turntable shaft holes (10) of the upper rotating shaft (2) of turntable (3) were coaxial under being used on two pillars (4) connected; Rotating shaft (2) can be rotated in lower turntable shaft hole (10).
2. two-freedom minute vehicle test platform according to claim 1, its
Be characterised in that: rotating shaft (2) is vertically fixed on lower turntable (3) by welding
On.
3. two-freedom minute vehicle test platform according to claim 1, its
Be characterised in that: two pillars (4) are fixed on by pillar fix screw (5)
On the base (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012105004565A CN103010483A (en) | 2012-11-29 | 2012-11-29 | Two-DOF (Degrees of Freedom) test platform for micro aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012105004565A CN103010483A (en) | 2012-11-29 | 2012-11-29 | Two-DOF (Degrees of Freedom) test platform for micro aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103010483A true CN103010483A (en) | 2013-04-03 |
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ID=47959707
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012105004565A Pending CN103010483A (en) | 2012-11-29 | 2012-11-29 | Two-DOF (Degrees of Freedom) test platform for micro aerial vehicle |
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| Country | Link |
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| CN (1) | CN103010483A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105620787A (en) * | 2015-12-23 | 2016-06-01 | 浙江大学 | Full-freedom testing platform for micro air vehicle |
| CN106785328A (en) * | 2017-02-08 | 2017-05-31 | 西安天圆光电科技有限公司 | A kind of carbon fibre composite three-axle table |
| CN110641732A (en) * | 2019-09-29 | 2020-01-03 | 蚌埠和能信息科技有限公司 | Two-degree-of-freedom miniature aircraft test platform |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2413266Y (en) * | 2000-02-17 | 2001-01-03 | 大连方舟科贸有限公司 | Multi-purpose horizontal stable platform |
| CN102230801A (en) * | 2011-03-30 | 2011-11-02 | 北京航空航天大学 | Light-type triaxial ISP (inertially stabilized platform) system using aerial remote sensing technology |
| CN202229764U (en) * | 2011-08-02 | 2012-05-23 | 王靖微 | Triaxial rotary table with dynamic stabilizing function |
-
2012
- 2012-11-29 CN CN2012105004565A patent/CN103010483A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2413266Y (en) * | 2000-02-17 | 2001-01-03 | 大连方舟科贸有限公司 | Multi-purpose horizontal stable platform |
| CN102230801A (en) * | 2011-03-30 | 2011-11-02 | 北京航空航天大学 | Light-type triaxial ISP (inertially stabilized platform) system using aerial remote sensing technology |
| CN202229764U (en) * | 2011-08-02 | 2012-05-23 | 王靖微 | Triaxial rotary table with dynamic stabilizing function |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105620787A (en) * | 2015-12-23 | 2016-06-01 | 浙江大学 | Full-freedom testing platform for micro air vehicle |
| CN106785328A (en) * | 2017-02-08 | 2017-05-31 | 西安天圆光电科技有限公司 | A kind of carbon fibre composite three-axle table |
| CN106785328B (en) * | 2017-02-08 | 2023-09-05 | 西安天圆光电科技有限公司 | Carbon fiber composite material triaxial revolving stage |
| CN110641732A (en) * | 2019-09-29 | 2020-01-03 | 蚌埠和能信息科技有限公司 | Two-degree-of-freedom miniature aircraft test platform |
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| C06 | Publication | ||
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| C05 | Deemed withdrawal (patent law before 1993) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20130403 |