CN105151273B - A kind of more paddle aircrafts - Google Patents
A kind of more paddle aircrafts Download PDFInfo
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- CN105151273B CN105151273B CN201510721351.6A CN201510721351A CN105151273B CN 105151273 B CN105151273 B CN 105151273B CN 201510721351 A CN201510721351 A CN 201510721351A CN 105151273 B CN105151273 B CN 105151273B
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- wing
- composite wing
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- rear plastic
- front flaps
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Abstract
A kind of more paddle aircrafts, belong to vehicle technology field, including fuselage, left composite wing, right composite wing, empennage and undercarriage.It is furnished with control system and airborne equipment in fuselage.Empennage is located at the afterbody of fuselage, and empennage includes tailplane and vertical tail.Undercarriage uses wheeled construction or sled and wheeled combining structure.Left composite wing is identical with right composite wing structure, they are symmetrically arranged on the left and right sides of fuselage.It are furnished with two, three or four rotors in left composite wing, each rotor is by an engine driving.The fin of left composite wing includes front flaps and the rear plastic that can be deflected around wing axis.All rotors are all located at the lower section of wing axis.More paddle takeoff and landing places are little, can be vertically moved up or down.The lift of generation is larger, safety and stability and maneuverability.
Description
Technical field
A kind of more paddle aircrafts, belong to vehicle technology field, more particularly to a kind of more paddle aircrafts.
Background technology
Traditional taking off and land is needed compared with long runway, it is impossible to which VTOL, also inconvenient Ultra-Low Speed or hovering fly
OK, retrogressing flight can not be realized, relatively short distance landing is also highly difficult.Traditional helicopter energy consumption is big, and efficiency is low, security and
Stability is not high.
The content of the invention
The purpose of the present invention is overcoming the above-mentioned deficiency of traditional aircraft and helicopter, invention is a kind of to facilitate short take-off and landing
Even more paddle aircrafts of the efficient safety and stability of energy VTOL.
A kind of more paddle aircrafts, including fuselage, left composite wing, right composite wing, empennage and undercarriage.Equipped with behaviour in fuselage
Control system and airborne equipment.Left composite wing is identical with right composite wing structure, they are symmetrically arranged on the left and right sides of fuselage.
Empennage is located at the afterbody of fuselage, and empennage includes tailplane and vertical tail.Tailplane plays horizontal stabilizer and elevator
Effect, vertical tail play vertical stabilization and rudder.Undercarriage is using wheeled construction or sled and wheeled combination knot
Structure.
The structure of left composite wing is：Left composite wing includes front flaps, rear plastic, wing axis, outer rotor, inward turning
The wing, outer engine, intrinsic motivation and stent.The rear end of front flaps is connected with wing axis, and front flaps can deflect up and down around wing axis.
The front end of rear plastic is connected with wing axis, and rear plastic can deflect up and down around wing axis.For relative level, front flaps are upward
The maximum angle of deflection is no more than 45 °, and the maximum angle that front flaps deflect down is no more than 30 °；Rear plastic upward deflects
Maximum angle be no more than 45 °, the maximum angle that rear plastic deflects down be no more than 30 °.Interior rotor close to fuselage install and
Outer rotor is installed away from fuselage.The diameter of outer rotor is not more than the diameter of interior rotor.Outer engine and intrinsic motivation be installed on
On the stent that fuselage is all connected with wing axis, outer engine provides power for outer rotor, and intrinsic motivation provides power for interior rotor.The wing
Axis is horizontally disposed.The line of the pivot of the pivot of interior rotor and outer rotor is in the lower section of wing axis.The rotation of outer rotor
The Plane of rotation for turning plane and interior rotor is coplanar.The Plane of rotation of interior rotor slightly forward downward is tilted or is horizontal, interior
The angle of the Plane of rotation of rotor and the forward downward of horizontal plane is not more than 10 °.The rearmost end of the wing tip turning circumference of interior rotor
Beeline between rear plastic is more than 10mm.The chord length of rear plastic is equal to or slightly greater than the radius of turn of interior rotor.
The chord length of front flaps is equal to or slightly greater than the radius of turn of interior rotor.The length of left composite wing be more than interior rotor diameter and
The sum of diameter of outer rotor.
The quantity of rotor and engine in the more paddle aircrafts of the present invention also has six sets and eight sets of two kinds of shapes in addition to four sets
Formula：The first form is：Three rotors and supporting three engines are housed, which is arranged in a linear in left composite wing
The length of left composite wing is more than the sum of diameter of three rotors when the lower section of the wing axis of left composite wing, the form；The right side is multiple
Conjunction wing is identical with the structure of left composite wing, they are symmetrically arranged on the left and right sides of fuselage.Second of form be：It is left compound
Four rotors and supporting four engines are housed, which is arranged in a linear under the wing axis of left composite wing in wing
Just, the length of left composite wing is more than the sum of diameter of four rotors during the form；The knot of right composite wing and left composite wing
Structure is identical, they are symmetrically arranged on the left and right sides of fuselage.
In order to improve mobility, will leave blank among the fixed section of the vertical tail of more paddle aircrafts, in the position of leaving blank
One electric propeller of the vertical arrangement installation in longitudinal direction, wide-angle turns to when so facilitating the hang or low speed.
A kind of operation principle of more paddle aircrafts of the invention is：As by the rear plastic of left composite wing and right composite wing
Rear plastic is all deflected downwards to extreme lower position, by the front flaps of the front flaps of left composite wing and right composite wing all to
Undercarriage is adjusted to extreme higher position and to wheeled state, starts all engines by upper deflecting, drives corresponding rotor respectively
Rotation, the aircraft can realize that advance takes off；Such as by the rear plastic of left composite wing, the rear portion wing of right composite wing
The front flaps of piece, the front flaps of left composite wing and right composite wing all deflect upward into extreme higher position, and the aircraft can
Realization is taken off vertically；The rear plastic of the rear plastic of left composite wing and right composite wing is all such as deflected upward into highest order
Put, the front flaps of the front flaps of left composite wing and right composite wing are all deflected downwards to extreme lower position, the aircraft
It can be achieved to retreat flight.Adjust the rear plastic, the rear plastic of right composite wing, the front portion of left composite wing of left composite wing
The deflection angle of the front flaps of fin and right composite wing and direction can change aerodynamic direction that the aircraft produces
And size, it can also change aerodynamic size and Orientation of the aircraft by adjusting the rotating speed of each rotor.By empennage come
Control pitching and the course of the aircraft.Comparing with traditional aircraft, the landing site of the more paddle aircraft requirements of the present invention is little, and
Can vertical lift.Compared with traditional helicopter, the more paddle aircrafts of the present invention due to the presence of left composite wing and right composite wing,
The lift that the aircraft produces is larger, if running out of steam the longer distance that can also glide, can strive for more times to tie up
Repair equipment or find safe landing point, it is so relatively safer；Due to left composite wing rotor and right composite wing it is corresponding
Rotor turn on the contrary, rotating torque can be offset, flight stability and control is simple；Since all rotors are all under fin
Side, it is preceding to fly or fly that the flow field of fin upper and lower surface is improved during rotor rotational afterwards, increase downwash flow, delay the upper surface of fin
Air-flow separation, improve efficiency, greatly increase lift coefficient, due to the presence of multiple rotors, the air maneuver is flexible.
Brief description of the drawings
Fig. 1 is a kind of left view schematic diagram of more paddle aircrafts of the present invention, and Fig. 2 is the schematic top plan view of Fig. 1；Fig. 3 is to be exaggerated
Left composite wing left view schematic diagram, Fig. 4 is the schematic top plan view of Fig. 3.
In figure, 1- fuselages, the left composite wings of 2-, the right composite wings of 3-, 4- empennages, 5- undercarriages；Belong to left composite wing 2
Component include：21- front flaps, 22- rear plastics, 23- wing axis, the outer rotors of 24-, rotor in 25-, the outer engines of 26-,
27- intrinsic motivations, 28- stents.
Embodiment
The present invention is illustrated in conjunction with attached drawing：A kind of more paddle aircrafts, including fuselage 1, left composite wing 2, the right side
Composite wing 3, empennage 4 and undercarriage 5.It is furnished with control system and airborne equipment in fuselage 1.Left composite wing 2 and right compounding machine
3 structure of the wing is identical, they are symmetrically arranged on the left and right sides of fuselage 1.Empennage 4 is located at the afterbody of fuselage 1, and empennage 4 includes level
Empennage and vertical tail.Tailplane plays horizontal stabilizer and elevator, and vertical tail plays vertical stabilization and direction
The effect of rudder.Undercarriage 5 uses wheeled construction.The structure of left composite wing 2 is：Left composite wing 2 include front flaps 21, after
Portion's fin 22, wing axis 23, outer rotor 24, interior rotor 25, outer engine 26, intrinsic motivation 27 and stent 28.Front flaps 21
Rear end is connected with wing axis 23, and front flaps 21 can be deflected around wing axis about 23.The front end of rear plastic 22 is connected with wing axis 23, after
Portion's fin 22 can be deflected around wing axis about 23.The leading edge of front flaps 21 is perfectly round, and the trailing edge of rear plastic 22 is sharp.Relative level
For face, the maximum angle that front flaps 21 upward deflect is 20 °, and the maximum angle that front flaps 21 deflect down is 15 °；Afterwards
The maximum angle that portion's fin 22 upward deflects is 20 °, and the maximum angle that rear plastic 22 deflects down is 15 °.Interior rotor 25 leans on
Nearly fuselage 1 is installed and outer rotor 24 is installed away from fuselage 1.The diameter of outer rotor 24 is not more than the diameter of interior rotor 25.Start outside
Machine 26 and intrinsic motivation 27 are installed on the stent 28 being all connected with fuselage 1 and wing axis 23, and outer engine 26 carries for outer rotor 24
For power, intrinsic motivation 27 provides power for interior rotor 25.Wing axis 23 is horizontally disposed.The pivot and outer rotor of interior rotor 25
The line of 24 pivot is in the underface of wing axis 23.The Plane of rotation of outer rotor 24 and the Plane of rotation of interior rotor 25 are all
It is horizontal.Beeline between the rearmost end and rear plastic 22 of the wing tip turning circumference of interior rotor 25 is more than
10mm.The chord length of rear plastic 22 is slightly larger than the radius of turn of interior rotor 25.The chord length of front flaps 21 is slightly larger than interior rotor 25
Radius of turn.The length of left composite wing 2 is more than the sum of the diameter of interior rotor 25 and the diameter of outer rotor 24.
The more paddle aircrafts of the present invention are such generation beneficial effects：Such as the rear plastic 22 of left composite wing 2 and the right side are answered
The rear plastic for closing wing 3 is all deflected downwards to extreme lower position, by the front flaps 21 and right composite wing 3 of left composite wing 2
Front flaps all deflect upward into extreme higher position, and undercarriage 5 is adjusted and to wheeled state, starts all engines, point
Corresponding rotor wing rotation is not driven, and the aircraft can realize takeoff；It is such as that the rear plastic 22 of left composite wing 2, the right side is multiple
Rear plastic, the front flaps 21 of left composite wing 2 and the front flaps of right composite wing 3 for closing wing 3 all deflect upward into
Extreme higher position, the aircraft can be realized and taken off vertically.Such as by after the rear plastic 22 of left composite wing 2 and right composite wing 3
Portion's fin all deflects upward into extreme higher position, by the front flaps of the front flaps 21 of left composite wing 2 and right composite wing 3 all
Extreme lower position is deflected downwards to, the aircraft can realize retrogressing flight.Rear plastic 22, the right side for adjusting left composite wing 2 are compound
The deflection angle of the front flaps of the rear plastic of wing 3, the front flaps 21 of left composite wing 2 and right composite wing 3 and side
To aerodynamic direction and the size that the aircraft produces can be changed, it can also change described fly by adjusting the rotating speed of each rotor
Aerodynamic size and Orientation of machine.Pitching and the course of the aircraft are controlled by empennage 4.With traditional aircraft ratio
Compared with the present invention is more, and paddle takeoff and landing place is little, and can be vertically moved up or down.Compared with traditional helicopter, the more paddle aircrafts of the present invention
Due to the presence of left composite wing 2 and right composite wing 3, the lift that the aircraft produces is larger, if running out of steam can also slide
The longer distance of Xiang, can strive for that more times carry out maintenance of equipment or find safe landing point, so relatively safer；Due to a left side
The corresponding rotor of the rotor of composite wing 2 and right composite wing 3 is turned on the contrary, rotating torque can be offset, flight stability and
Control is simple；It is preceding to fly or fly that during rotor rotational fin upper and lower surface is improved afterwards since all rotors are all in the lower section of fin
Flow field, increase downwash flow, delay fin upper surface air-flow separation, improve efficiency, greatly increase lift coefficient, by
It is flexible in the presence of multiple rotors, the air maneuver.The rear plastic 22 of left composite wing 2 and the rear portion of right composite wing 3
Fin can also play the wing flap and aileron of traditional aircraft.Therefore more paddle air maneuvers are flexible.
Claims (5)
- A kind of 1. more paddle aircrafts, it is characterised in that：Including fuselage（10）, left composite wing（2）, right composite wing（3）, empennage （4）And undercarriage（5）；Fuselage（1）It is interior to be furnished with control system and airborne equipment；Left composite wing（2）With right composite wing（3）Knot Structure is identical, they are symmetrically arranged on fuselage（1）The left and right sides；Empennage（4）Positioned at fuselage（1）Afterbody, empennage（4）Including water The horizontal tail wing and vertical tail；Undercarriage（5）Using wheeled construction or sled and wheeled combining structure；Left composite wing（2）Knot Structure is：Left composite wing（2）Including front flaps（21）, rear plastic（22）, wing axis（23）, outer rotor（24）, interior rotor （25）, outer engine（26）, intrinsic motivation（27）And stent（28）；Front flaps（21）Rear end and wing axis（23）It is connected, it is preceding Portion's fin（21）Can be around wing axis（23）Deflection up and down；Rear plastic（22）Front end and wing axis（23）It is connected, rear plastic（22） Can be around wing axis（23）Deflection up and down；Interior rotor（25）Close to fuselage（1）Install and outer rotor（24）Away from fuselage（1）Installation；Outside Rotor（24）Diameter be not more than interior rotor（25）Diameter；Outer engine（26）And intrinsic motivation（27）It is installed on and fuselage （1）With wing axis（23）All connected stents（28）On, outer engine（26）For outer rotor（24）Power, intrinsic motivation are provided（27） For interior rotor（25）Power is provided；Wing axis（23）It is horizontally disposed；Interior rotor（25）Pivot and outer rotor（24）Rotation The line at center is in wing axis（23）Lower section；Outer rotor（24）Plane of rotation and interior rotor（25）Plane of rotation it is coplanar； Interior rotor（25）Plane of rotation slightly forward downward tilt or be horizontal；Interior rotor（25）Wing tip turning circumference most Rear end and rear plastic（22）Between beeline be more than 10mm；Rear plastic（22）Chord length be equal to or slightly greater than interior rotor （25）Radius of turn；Front flaps（21）Chord length be equal to or slightly greater than interior rotor（25）Radius of turn；Left composite wing （2）Length be more than interior rotor（25）Diameter and outer rotor（24）The sum of diameter；If by left composite wing（2）Rear portion Fin（22）With right composite wing（3）Rear plastic be all deflected downwards to extreme lower position, by left composite wing（2）The anterior wing Piece（21）With right composite wing（3）Front flaps all deflect upward into extreme higher position, and by undercarriage（5）Adjust to wheeled shape State, starts all engines, drives corresponding rotor wing rotation respectively, and the aircraft can realize that advance takes off；If By left composite wing（2）Rear plastic（22）, right composite wing（3）Rear plastic, left composite wing（2）Front flaps （21）With right composite wing（3）Front flaps all deflect upward into extreme higher position, the aircraft can be realized and taken off vertically；Such as Fruit is by left composite wing（2）Rear plastic（22）With right composite wing（3）Rear plastic all deflect upward into extreme higher position, By left composite wing（2）Front flaps（21）With right composite wing（3）Front flaps be all deflected downwards to extreme lower position, institute Retrogressing flight can be realized by stating aircraft.
- A kind of 2. more paddle aircrafts according to claim 1, it is characterised in that：Front flaps（21）Leading edge it is perfectly round, rear portion Fin（22）Trailing edge it is sharp；For relative level, front flaps（21）The maximum angle upward deflected is preceding no more than 45 ° Portion's fin（21）The maximum angle deflected down is no more than 30 °；Rear plastic（22）The maximum angle upward deflected is no more than 45 °, rear plastic（22）The maximum angle deflected down is no more than 30 °；Interior rotor（25）Plane of rotation and horizontal plane to The angle of front lower place is not more than 10 °.
- A kind of 3. more paddle aircrafts according to claim 2, it is characterised in that：For relative level, front flaps（21） The maximum angle upward deflected is 20 °, front flaps（21）The maximum angle deflected down is 15 °；Rear plastic（22）Upwards The maximum angle of deflection is 20 °, rear plastic（22）The maximum angle deflected down is 15 °.
- A kind of 4. more paddle aircrafts according to claim 1, it is characterised in that：Interior rotor（25）Pivot and outer rotor （24）The line of pivot be in wing axis（23）Underface.
- A kind of 5. more paddle aircrafts according to claim 1 or 2 or 3 or 4, it is characterised in that：In the fixed section of vertical tail Between leave blank, which is installed with an electric propeller.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510721351.6A CN105151273B (en) | 2015-10-30 | 2015-10-30 | A kind of more paddle aircrafts |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510721351.6A CN105151273B (en) | 2015-10-30 | 2015-10-30 | A kind of more paddle aircrafts |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105151273A CN105151273A (en) | 2015-12-16 |
| CN105151273B true CN105151273B (en) | 2018-05-01 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510721351.6A Active CN105151273B (en) | 2015-10-30 | 2015-10-30 | A kind of more paddle aircrafts |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11358719B2 (en) * | 2017-07-18 | 2022-06-14 | ST Engineering Aerospace Ltd. | Asymmetric aerial vehicle |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4789115A (en) * | 1986-08-29 | 1988-12-06 | Theodore Koutsoupidis | VTOL aircraft |
| JPH05155384A (en) * | 1991-12-04 | 1993-06-22 | Mitsubishi Heavy Ind Ltd | Wing stalling preventive system for airplane |
| US20100148011A1 (en) * | 2008-11-12 | 2010-06-17 | Sanderson Terry M | Telescoping structure and method |
| CN101607600A (en) * | 2008-12-12 | 2009-12-23 | 于江 | Solar-wind hybrid power airplane |
| JP2014065477A (en) * | 2012-09-24 | 2014-04-17 | Takashi Sasaki | Vertical and horizontal takeoff and landing aircraft |
| CN103287569B (en) * | 2013-05-15 | 2015-04-22 | 西北工业大学 | Lifting-pushing type large-scale solar-powered unmanned aerial vehicle capable of taking off and landing in non-runway field and hovering |
| CN204452934U (en) * | 2015-02-05 | 2015-07-08 | 仉军 | The double mode aircraft of rotor, fixed-wing |
| CN205131628U (en) * | 2015-10-30 | 2016-04-06 | 佛山市神风航空科技有限公司 | Many oars aircraft |
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| Publication number | Publication date |
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| CN105151273A (en) | 2015-12-16 |
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Effective date of registration: 20191218 Address after: 313000 1-C, building 1, No. 656, Qixing Road, high tech Zone, Wuxing District, Huzhou City, Zhejiang Province Patentee after: Huzhou xinbeilian Network Technology Co., Ltd Address before: Foshan City, Guangdong province 528500 city streets Gaoming District No. 78 Jiangwan Road, room 402 Fu Wan Patentee before: Shenfeng science and technology of aviation Co., Ltd of Foshan City |
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Effective date of registration: 20200702 Address after: 225400, Taizhou, Jiangsu, Huangqiao province Taixing Industrial Park Road Patentee after: Jiangsu Yuneng Water Conservancy Engineering Co.,Ltd. Address before: 313000 1-C, building 1, No. 656, Qixing Road, high tech Zone, Wuxing District, Huzhou City, Zhejiang Province Patentee before: Huzhou xinbeilian Network Technology Co.,Ltd. |