CN201592778U - Aircraft capable of tilting and rotating through four rotary wings - Google Patents
Aircraft capable of tilting and rotating through four rotary wings Download PDFInfo
- Publication number
- CN201592778U CN201592778U CN2009203184707U CN200920318470U CN201592778U CN 201592778 U CN201592778 U CN 201592778U CN 2009203184707 U CN2009203184707 U CN 2009203184707U CN 200920318470 U CN200920318470 U CN 200920318470U CN 201592778 U CN201592778 U CN 201592778U
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- power unit
- power pack
- rotating shaft
- rotary wings
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Abstract
The utility model discloses an aircraft capable of tilting and rotating through four rotary wings. The aircraft comprises wings and a plurality of ribbed plates arranged on a main body of the aircraft, wherein a front tilt rotating shaft and a back tilt rotating shaft are mounted in the front and the back reinforcing ribbed plates of the wings, the front tilt rotating shaft and the back tilt rotating shaft are connected with a rotating device and further correlated and synchronized through a connecting rod, a No.1 power unit and a No.2 power unit are respectively mounted at two ends of the front tilt rotating shaft, a No.3 power unit and a No.4 power unit are respectively mounted at two ends of the back tilt rotating shaft, four sets of the rotary wings are respectively mounted on the No.1 power unit, the No.2 power unit, the No.3 power unit and the No.4 power unit, the rotation directions of the each adjacent two rotary wings are reverse, the rotation of the rotary wings of the No.1 power unit and the No.2 power unit are positioned in the same plane, and the rotation of the rotary wings of the No.3 power unit and the No.4 power unit are positioned in the same plane. The device has the advantages of simple and reliable structure, vertical lifting and high-speed cruising through the power layout of the four rotary wings, flexible realization of pitching, rolling, yawing and other functions, fast reaction, small impacts caused by the centre of gravity, high stability and easy realization of fixed point stable hovering.
Description
Technical field
The utility model belongs to the aviation power field of mechanical technique, relates to a kind of four rotor crafts that vert.
Background technology
But tiltrotor aircraft is a kind ofly both can carry out vertical takeoff and landing as helicopter, can realize the aircraft of fixed-wing high-speed flight again, has both advantages concurrently.At present place in operation the bispin rotor aircraft that can vert arranged, as the v-22 osprey of the U.S..But because the bispin rotor aircraft can't direct control pitching balance, influenced greatly by center of gravity, the steerability difficulty is big, and system's diversity is big, complicated in mechanical structure, and involving great expense of device influenced large batch of promoting the use of.
Summary of the invention
The purpose of this utility model provides a kind of four rotor crafts that vert, and having solved existing bispin rotor aircraft can't direct control pitching balance, influenced greatly by center of gravity, and steerability is poor, and system's diversity is big, the problem of complicated in mechanical structure.
The technical scheme that the utility model adopted is, a kind of four rotor crafts that vert, be included in aircraft body and be provided with the floor of wing and some reinforcements, tiliting axis and back tiliting axis before being equipped with in the floor of before and after wing, strengthening, preceding tiliting axis is connected with wheel word with the back tiliting axis, by the connecting rod associated synchronisation, the two ends of preceding tiliting axis are separately installed with the 1# power pack, the 2# power pack, the two ends of back tiliting axis are separately installed with the 3# power pack, the 4# power pack, the 1# power pack, the 2# power pack, the 3# power pack, one cover rotor is installed on the 4# power pack separately, each adjacent rotor hand of rotation is opposite in twos, the 1# power pack, the rotor of 2# power pack is rotated in the same plane, the 3# power pack, the rotor of 4# power pack is rotated in the same plane.
Device of the present utility model, simple and reliable for structure, by the power arrangement of four rotors, but but have the advantage of vertical takeoff and landing high-performance cruise, realize functions such as pitching, lift-over, driftage flexibly, it is little that reaction is influenced by center of gravity fast, stability is high, stable the hovering of realizing easily fixing a point.
Description of drawings
Fig. 1 is the structural representation of the utility model device.
Among the figure, 1.1# power pack, 2.2# power pack, 3.3# power pack, 4.4# power pack, 5. preceding tiliting axis, 6. floor, 7. wing, 8. back tiliting axis.
The specific embodiment
Below in conjunction with the drawings and specific embodiments the utility model is elaborated.
As Fig. 1, the structure of the utility model device is, be included in aircraft body and be provided with wing 7 and some floors 6, tiliting axis 5 and back tiliting axis 8 before in the floor 6 that wing 7 front and back are strengthened, being equipped with, preceding tiliting axis 5 is connected with wheel word with back tiliting axis 8, by the connecting rod associated synchronisation, realize equidirectionally verting synchronously, the two ends of preceding tiliting axis 5 are separately installed with 1# power pack 1,2# power pack 2, the two ends of back tiliting axis 8 are separately installed with 3 # power pack 3,4# power pack 4,1# power pack 1,2 # power pack 2,3# power pack 3, one cover rotor is installed on the 4# power pack 4 separately, each adjacent rotor hand of rotation is opposite in twos, 1# power pack 1, the rotor of 2# power pack 2 is rotated in the same plane, 3# power pack 3, the rotor of 4# power pack 4 is rotated in the same plane.
The principle of work of the utility model device is,
Tiliting axis 5 and back tiliting axis 8 rotate synchronously before the control, make the rotation of four rotors all in same plane, just four power pack thrusts all vertically downward, when rotor upwards verts, aircraft is a helicopter mode, realizes the control of attitude of flight vehicle during helicopter mode by the power of controlling four power pack.Strengthen the power of 3 # power pack 3,4# power pack 4 simultaneously, because back tiliting axis 8 liftings, then aircraft forward; Strengthen the power of 1# power pack 1 and 2# power pack 2 simultaneously, because preceding tiliting axis 5 liftings, then aircraft retreats; Change 1# power pack 1,3# power pack 3 simultaneously, perhaps 2 # power pack 2,4# power pack 4 power then can be realized the skew about aircraft; The change of the Longitudinal Warping distortion of aircraft and reactive torque changes the power of 1# power pack 1,4 # power pack 4 or 2 # power pack 2,3# power pack 3 simultaneously, owing to can realize the driftage (turning to) of aircraft.For example: 1# power pack 1, the relative 2# power pack 2 of 4# power pack 4 power, 3# power pack 3 are big, then can produce deformation, 1# power pack 1 position is higher and 4# power pack 4 relative 3# power pack 3 are higher with respect to 2# power pack 2, at this moment preceding tiliting axis produces the horizontal component of force on 2# power pack 2 directions relatively, back tiliting axis 8 produces the horizontal component of force on 3# power pack 3 directions, just can realize the left-hand rotation of aircraft.
Tiliting axis 5 and back tiliting axis 8 rotate synchronously before the control, make when rotor tilts forward, four power pack thrusts all backward, aircraft obtains speed forward, and at this moment wing begins to produce lift, and the power of balance aircraft gravity is excessive in all producing lift by the body wing by the thrust of pure rotor, attitude of flight vehicle control is the same with the ordinary fixed wing aircraft, by aileron, yaw rudder, elevating rudder finished.
Device of the present utility model, simple and reliable for structure, by the control of the motion direct force on xyz three direction of principal axis, realize functions such as pitching, lift-over, driftage flexibly, it is little that reaction is influenced by center of gravity fast, and stability is high; By the power arrangement of four rotors, the two groups of rotors in front and back link by tiliting axis and vert synchronously with realization in addition, and adjacent rotor is realized easily fixing a point to stablize hovering, but but had the advantage of vertical takeoff and landing high-performance cruise simultaneously in twos on the contrary to offset reactive torque.
Claims (1)
1. four rotor crafts that can vert, be included in aircraft body and be provided with the floor (6) of wing (7) and some reinforcements, it is characterized in that: preceding tiliting axis (5) and back tiliting axis (8) are installed in the floor of strengthening before and after wing (7) (6), preceding tiliting axis (5) is connected with wheel word with back tiliting axis (8), by the connecting rod associated synchronisation, the two ends of preceding tiliting axis (5) are separately installed with 1# power pack (1), 2# power pack (2), the two ends of back tiliting axis (8) are separately installed with 3# power pack (3), 4# power pack (4), 1# power pack (1), 2# power pack (2), 3# power pack (3), one cover rotor is installed on the 4# power pack (4) separately, each adjacent rotor hand of rotation is opposite in twos, 1# power pack (1), the rotor of 2# power pack (2) is rotated in the same plane, 3# power pack (3), the rotor of 4# power pack (4) is rotated in the same plane.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009203184707U CN201592778U (en) | 2009-12-25 | 2009-12-25 | Aircraft capable of tilting and rotating through four rotary wings |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009203184707U CN201592778U (en) | 2009-12-25 | 2009-12-25 | Aircraft capable of tilting and rotating through four rotary wings |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201592778U true CN201592778U (en) | 2010-09-29 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009203184707U Expired - Fee Related CN201592778U (en) | 2009-12-25 | 2009-12-25 | Aircraft capable of tilting and rotating through four rotary wings |
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Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102951290A (en) * | 2012-10-31 | 2013-03-06 | 西安韦德沃德航空科技有限公司 | Non-co-axial multi-rotor aircraft and attitude control method thereof |
| CN103010462A (en) * | 2012-11-09 | 2013-04-03 | 许宏伟 | Low-altitude aircraft |
| CN103466089A (en) * | 2013-09-26 | 2013-12-25 | 许庆松 | Fast-flying helicopter |
| CN103786880A (en) * | 2014-01-17 | 2014-05-14 | 江苏艾锐泰克无人飞行器科技有限公司 | Unmanned aerial vehicle capable of taking off and landing vertically |
| CN105109677A (en) * | 2015-08-28 | 2015-12-02 | 武汉捷特航空科技有限公司 | Composite aircraft composed of fixed wings and multi-rotary wings and control method of composite aircraft |
| CN105129081A (en) * | 2015-08-12 | 2015-12-09 | 江阴市翔诺电子科技有限公司 | Novel multiaxial rotor aircraft and steering control method of the same under hovering state |
| CN105438463A (en) * | 2015-11-30 | 2016-03-30 | 珞石（北京）科技有限公司 | Quad tilt-rotor aircraft |
| CN105539833A (en) * | 2016-01-11 | 2016-05-04 | 成都学尚科技有限公司 | Fixed-wing multi-shaft aircraft |
| CN106132825A (en) * | 2013-12-23 | 2016-11-16 | 李尚泫 | Many rotor flyings body |
| CN106394895A (en) * | 2016-09-23 | 2017-02-15 | 广东天米教育科技有限公司 | Multi-form unmanned aerial vehicle and flight control method thereof |
| CN107074352A (en) * | 2014-09-02 | 2017-08-18 | 瑞格夫·阿米特 | Many sides rotate rotor aircraft |
| CN107089325A (en) * | 2017-04-26 | 2017-08-25 | 优雷特(银川)航空技术有限公司 | A kind of split blade type unmanned plane tilting wing device and aircraft |
| CN107264780A (en) * | 2017-06-27 | 2017-10-20 | 何漠 | Tandem vectored thrust drives aircraft and its design method entirely |
-
2009
- 2009-12-25 CN CN2009203184707U patent/CN201592778U/en not_active Expired - Fee Related
Cited By (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102951290A (en) * | 2012-10-31 | 2013-03-06 | 西安韦德沃德航空科技有限公司 | Non-co-axial multi-rotor aircraft and attitude control method thereof |
| CN103010462A (en) * | 2012-11-09 | 2013-04-03 | 许宏伟 | Low-altitude aircraft |
| CN103466089A (en) * | 2013-09-26 | 2013-12-25 | 许庆松 | Fast-flying helicopter |
| CN106132825B (en) * | 2013-12-23 | 2018-05-11 | 李尚泫 | More rotor flying bodies |
| CN106132825A (en) * | 2013-12-23 | 2016-11-16 | 李尚泫 | Many rotor flyings body |
| CN103786880A (en) * | 2014-01-17 | 2014-05-14 | 江苏艾锐泰克无人飞行器科技有限公司 | Unmanned aerial vehicle capable of taking off and landing vertically |
| CN107074352A (en) * | 2014-09-02 | 2017-08-18 | 瑞格夫·阿米特 | Many sides rotate rotor aircraft |
| CN105129081A (en) * | 2015-08-12 | 2015-12-09 | 江阴市翔诺电子科技有限公司 | Novel multiaxial rotor aircraft and steering control method of the same under hovering state |
| CN105129081B (en) * | 2015-08-12 | 2018-02-23 | 江阴市翔诺电子科技有限公司 | A kind of rotating direction control method under novel multi-shaft rotor craft and its floating state |
| CN105109677A (en) * | 2015-08-28 | 2015-12-02 | 武汉捷特航空科技有限公司 | Composite aircraft composed of fixed wings and multi-rotary wings and control method of composite aircraft |
| CN105109677B (en) * | 2015-08-28 | 2017-04-19 | 武汉捷特航空科技有限公司 | Composite aircraft composed of fixed wings and multi-rotary wings and control method of composite aircraft |
| CN105438463A (en) * | 2015-11-30 | 2016-03-30 | 珞石（北京）科技有限公司 | Quad tilt-rotor aircraft |
| CN105539833A (en) * | 2016-01-11 | 2016-05-04 | 成都学尚科技有限公司 | Fixed-wing multi-shaft aircraft |
| CN106394895A (en) * | 2016-09-23 | 2017-02-15 | 广东天米教育科技有限公司 | Multi-form unmanned aerial vehicle and flight control method thereof |
| CN106394895B (en) * | 2016-09-23 | 2019-05-03 | 广东天米教育科技有限公司 | A kind of polymorphic unmanned plane and its flight control method |
| CN107089325A (en) * | 2017-04-26 | 2017-08-25 | 优雷特(银川)航空技术有限公司 | A kind of split blade type unmanned plane tilting wing device and aircraft |
| CN107264780A (en) * | 2017-06-27 | 2017-10-20 | 何漠 | Tandem vectored thrust drives aircraft and its design method entirely |
| CN107264780B (en) * | 2017-06-27 | 2019-06-28 | 何漠 | Tandem vectored thrust drives aircraft and its design method entirely |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20100929 Termination date: 20121225 |