CN105217024B - A kind of axle aircraft of symmetric form six - Google Patents
A kind of axle aircraft of symmetric form six Download PDFInfo
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- CN105217024B CN105217024B CN201510721355.4A CN201510721355A CN105217024B CN 105217024 B CN105217024 B CN 105217024B CN 201510721355 A CN201510721355 A CN 201510721355A CN 105217024 B CN105217024 B CN 105217024B
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Abstract
A kind of axle aircraft of symmetric form six, category vehicle technology field, including fuselage, left composite wing, right composite wing, support, preceding rotor, rear rotor and undercarriage.It is furnished with control system and airborne equipment in fuselage.Left composite wing is identical with right composite wing structure, and they are symmetrically arranged on the left and right sides of fuselage.Preceding rotor is identical with rear rotor structure, and they are respectively arranged in the rear and front end of fuselage by support.Undercarriage uses sled and wheeled combining structure.Left composite wing is identical with right composite wing structure, and they are symmetrically arranged on the left and right sides of fuselage.Respectively equipped with two rotors in left composite wing and right 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 axle.The axle aircraft landing site of symmetric form six less, can be vertically moved up or down.The lift of generation is larger, safety and stability and maneuverability.
Description
Technical field
A kind of axle aircraft of symmetric form six, category vehicle technology field, more particularly to a kind of six axles aircraft.
Background technology
Energy consumption is big when six traditional axle aircraft cruise, and stability and security are poor, when losing part or all of power
It basically can not save oneself.Traditional aircraft can not be vertically moved up or down and hover.Traditional helicopter energy consumption is big, and efficiency is low, security
It is also not high with stability.
The content of the invention
The purpose of the present invention is the above-mentioned deficiency for overcoming six traditional axle aircraft, aircraft and helicopter, invents a kind of energy
The axle aircraft of symmetric form six of the highly effective and safe of VTOL.
A kind of axle aircraft of symmetric form six, including fuselage, left composite wing, right composite wing, support, preceding rotor, rear rotation
The wing and undercarriage.It is furnished with control system and airborne equipment in fuselage.Left composite wing is identical with right composite wing structure, and they are right
Claim the left and right sides for being installed on fuselage.Preceding rotor is identical with rear rotor structure, and they are respectively arranged in before fuselage by support
Two ends afterwards.Preceding rotor and rear rotor are driven by two motors respectively.Preceding rotor and rear rotor are turned on the contrary, the convenient regulation of rotating speed.
Preceding rotor and rear rotor mainly play pitching and lifting flight attitude control action.Undercarriage uses sled and wheeled combining structure.
The structure of left composite wing is：Left composite wing includes front flaps, rear plastic, wing axle, outer rotor, inward turning
The wing, outer engine and intrinsic motivation.The rear end of front flaps is connected with wing axle, and front flaps can be deflected above and below wing axle.Rear portion
The front end of fin is connected with wing axle, and rear plastic can be deflected above and below wing axle.For relative level, front flaps are upward deflected
Maximum angle be no more than 35 °, the maximum angle that front flaps are deflected down be no more than 20 °；Rear plastic is upward deflected most
Wide-angle is no more than 35 °, and the maximum angle that rear plastic is deflected down is no more than 20 °.Interior rotor is installed and outward turning close to fuselage
The wing is installed away from fuselage.The diameter of outer rotor is not more than the diameter of interior rotor.Outer engine and intrinsic motivation are respectively placed in outward turning
The lower section of the wing and interior rotor is arranged on the support being all connected with fuselage and wing axle, and outer engine provides power for outer rotor, interior
Engine provides power for interior rotor.The steering of interior rotor and the steering of outer rotor are identical with the steering of preceding rotor.Wing axle water
Plain cloth is put.The line of the pivot of the pivot of interior rotor and outer rotor is in the underface of wing axle.The rotation of outer rotor
The Plane of rotation of plane and interior rotor is coplanar.The Plane of rotation of interior rotor is horizontal.When front flaps and rear plastic
When being all deflected downwards to extreme lower position, the wing tip turning circumference of interior rotor foremost with rearmost end respectively with front flaps and after
Beeline between portion's fin is both greater than 10mm.The chord length of front flaps and rear plastic is equal, chord length of rear plastic etc.
In or slightly larger than interior rotor radius of turn.The length of left composite wing be more than interior rotor diameter and outer rotor diameter it
With.
A kind of operation principle of the axle aircraft of symmetric form six of the invention is：Such as the rear plastic of left composite wing and the right side are answered
The rear plastic for closing wing is all deflected downwards to extreme lower position, by the front portion of the front flaps of left composite wing and right composite wing
Fin all deflects upward into extreme higher position, and undercarriage is adjusted to wheeled state, starts all engines and motor, respectively
Corresponding rotor wing rotation is driven, the aircraft can realize advance rolling start；It is such as that the rear plastic of left composite wing, the right side is multiple
The front flaps for closing rear plastic, the front flaps of left composite wing and the right composite wing of wing all deflect upward into highest order
Put, the aircraft can be realized and taken off vertically；Such as by the rear plastic of left composite wing and the rear plastic of right composite wing all
Extreme higher position is deflected upward into, the front flaps of the front flaps of left composite wing and right composite wing are all deflected downwards to most
Lower position, the aircraft can realize retrogressing flight.Adjust rear plastic, the rear portion wing of right composite wing of left composite wing
The deflection angle of the front flaps of piece, the front flaps of left composite wing and right composite wing and direction can change the aircraft
The aerodynamic direction produced and size, the aerodynamic of the aircraft can be also changed by the rotating speed for adjusting each rotor
Size and Orientation.Compare with traditional aircraft, the landing site of the axle aircraft requirements of symmetric form six of the present invention is little, and can be vertical
Lifting, can hover in the air.Compared with traditional helicopter and Multi-axis aircraft, the axle aircraft of symmetric form six of the present invention is due to a left side
The presence of composite wing and right composite wing, the lift that the aircraft is produced is larger, if run out of steam can also glide it is longer
Distance, can strive for more times come maintenance of equipment or find safe landing point, so relatively safely；Due to left compounding machine
All rotors can improve following table on fin all in the lower section of fin during preceding winged or rear winged rotor rotational in the wing and right composite wing
The flow field in face, increases downwash flow, delays the air-flow separation of the upper surface of fin, improves efficiency, greatly increase lift coefficient,
Due to the presence of multiple rotors, the aircraft maneuverability.
Brief description of the drawings
Fig. 1 is a kind of left view schematic diagram of the axle aircraft of symmetric form six of the invention, and Fig. 2 is Fig. 1 schematic top plan view；Fig. 3
It is the left view schematic diagram for the left composite wing being exaggerated, Fig. 4 is Fig. 3 schematic top plan view.
In figure, 1- fuselages, the left composite wings of 2-, the right composite wings of 3-, 4- supports, rotor before 5-, rotor after 6-, 7- rises and falls
Frame；Belonging to the component of left composite wing 2 includes：In 21- front flaps, 22- rear plastics, 23- wing axles, the outer rotors of 24-, 25-
Rotor, the outer engines of 26-, 27- intrinsic motivations.
Embodiment
The present invention is illustrated in conjunction with accompanying drawing：A kind of axle aircraft of symmetric form six, including fuselage 1, a left side are combined
Wing 2, right composite wing 3, support 4, preceding rotor 5, rear rotor 6 and undercarriage 7.Equipped with control system and airborne set in fuselage 1
It is standby.Left composite wing 2 is identical with the right structure of composite wing 3, and they are symmetrically arranged on the left and right sides of fuselage 1.Preceding rotor 5 is with after
The structure of rotor 6 is identical, and they are respectively arranged in the rear and front end of fuselage 1 by support 4.Preceding rotor 5 and rear rotor 6 are respectively by two
Platform motor drives.Preceding rotor 5 and rear rotor 6 are turned on the contrary, the convenient regulation of rotating speed.The Plane of rotation of preceding rotor 5 and rear rotor 6
Plane of rotation is in same level.Preceding rotor 5 and rear rotor 6 mainly play pitching and lifting flight attitude control action.Rise
Fall frame 7 and use sled and wheeled combining structure.The structure of left composite wing 2 is：Left composite wing 2 include front flaps 21, after
Portion's fin 22, wing axle 23, outer rotor 24, interior rotor 25, outer engine 26 and intrinsic motivation 27.The rear end of front flaps 21 and the wing
Axle 23 is connected, and front flaps 21 can be deflected around wing axle about 23.The front end of rear plastic 22 is connected with wing axle 23, rear plastic 22
It can be deflected around wing axle about 23.For relative level, the maximum angle that front flaps 21 are upward deflected is 20 °, front flaps
21 maximum angles deflected down are 15 °；The maximum angle that rear plastic 22 is upward deflected is 20 °, the downward bias of rear plastic 22
The maximum angle turned is 15 °.Interior rotor 25 is installed close to fuselage 1 and outer rotor 24 is installed away from fuselage 1.The diameter of outer rotor 24
Equal to the diameter of interior rotor 25.Outer engine 26 and intrinsic motivation 27 are respectively placed in outer rotor 24 and the lower section of interior rotor 25 is installed
On the support 4 being all connected with fuselage 1 and wing axle 23, outer engine 26 is that outer rotor 24 provides power, and intrinsic motivation 27 is interior
Rotor 25 provides power.The steering of interior rotor 25 and the steering of outer rotor 24 are identical with the steering of preceding rotor 5.The level of wing axle 23
Arrangement.The line of the pivot of interior rotor 25 and the pivot of outer rotor 24 is in the underface of wing axle 23.Outer rotor 24
Plane of rotation and interior rotor 25 Plane of rotation it is coplanar.The Plane of rotation of the Plane of rotation of outer rotor 24 and preceding rotor 5 is also common
Face.The Plane of rotation of interior rotor 25 is horizontal.When front flaps 21 and rear plastic 22 are all deflected downwards to lowest order
When putting, the wing tip turning circumference of interior rotor 25 foremost and rearmost end is respectively between front flaps 21 and rear plastic 22
Beeline is both greater than 10mm.Front flaps 21 are equal with the chord length of rear plastic 22, and the chord length of rear plastic 22 is slightly larger than interior
The radius of turn of rotor 25.The length of left composite wing 2 is more than twice of the diameter of interior rotor 25.
The axle aircraft of symmetric form six of the present invention is such generation beneficial effect：Such as by the rear plastic of left composite wing 2
22 and the rear plastic of right composite wing 3 be all deflected downwards to extreme lower position, the front flaps 21 of left composite wing 2 and the right side are answered
The front flaps for closing wing 3 all deflect upward into appropriate location, and undercarriage 7 is adjusted to wheeled state, start all hairs
Motivation and motor, drive corresponding rotor wing rotation respectively, and the aircraft can realize advance rolling start；Such as by left composite wing
Before 2 rear plastic 22, the rear plastic of right composite wing 3, the front flaps 21 of left composite wing 2 and right composite wing 3
Portion's fin all deflects upward into extreme higher position, and the aircraft can be realized and taken off vertically；Such as by the rear plastic of left composite wing 2
22 and the rear plastic of right composite wing 3 all deflect upward into appropriate location, the front flaps 21 of left composite wing 2 and the right side are answered
The front flaps for closing wing 3 are all deflected downwards to extreme lower position, and the aircraft can realize retrogressing flight.Adjust left composite wing
Before 2 rear plastic 22, the rear plastic of right composite wing 3, the front flaps 21 of left composite wing 2 and right composite wing 3
The deflection angle of portion's fin and direction can change aerodynamic direction and the size that the aircraft is produced, by adjusting each rotation
The rotating speed of the wing can also change aerodynamic size and Orientation of the aircraft.Compare with traditional aircraft, the present invention is symmetrical
The landing site of the axle aircraft requirements of type six less, and can be vertically moved up or down, and can hover in the air.With traditional helicopter and multiaxis
Aircraft compares, and the axle aircraft of symmetric form six of the present invention is due to the presence of left composite wing 2 and right composite wing 3, the flight
The lift that device is produced is larger, if running out of steam the longer distance that can also glide, can strive for that more times carry out maintenance of equipment
Or safe landing point is found, it is so relatively safer；Due to rotor all in left composite wing 2 and right composite wing 3 all in
The lower section of fin, it is preceding to fly or fly that during rotor rotational the flow field of fin upper and lower surface is improved afterwards, increase downwash flow, delay fin
Upper surface air-flow separation, improve efficiency, greatly increase lift coefficient, due to the presence of multiple rotors, the aircraft
Maneuverability.
Claims (5)
1. a kind of axle aircraft of symmetric form six, it is characterised in that：Including fuselage（1）, left composite wing（2）, right composite wing
（3）, support（4）, preceding rotor（5）, rear rotor（6）And undercarriage（7）；Fuselage（1）It is interior to be furnished with control system and airborne equipment；It is left
Composite wing（2）With right composite wing（3）Structure is identical, and they are symmetrically arranged on fuselage（1）The left and right sides；Preceding rotor（5）
With rear rotor（6）Structure is identical, and they pass through support（4）It is respectively arranged in fuselage（1）Rear and front end；Preceding rotor（5）With it is rear
Rotor（6）Driven respectively by two motors；Preceding rotor（5）With rear rotor（6）Turn on the contrary, the convenient regulation of rotating speed；Undercarriage（7）
Using sled and wheeled combining structure；Left composite wing（2）Structure be：Left composite wing（2）Including front flaps（21）, after
Portion's fin（22）, wing axle（23）, outer rotor（24）, interior rotor（25）, outer engine（26）And intrinsic motivation（27）；Front flaps
（21）Rear end and wing axle（23）It is connected, front flaps（21）Can be around wing axle（23）Deflect up and down；Rear plastic（22）Front end
With wing axle（23）It is connected, rear plastic（22）Can be around wing axle（23）Deflect up and down；Interior rotor（25）Close to fuselage（1）Install and it is outer
Rotor（24）Away from fuselage（1）Install；Outer rotor（24）Diameter be not more than interior rotor（25）Diameter；Outer engine（26）With
Intrinsic motivation（27）It is respectively placed in outer rotor（24）With interior rotor（25）Lower section be arranged on and fuselage（1）With wing axle（23）All phases
Support even（4）On, outer engine（26）For outer rotor（24）Power, intrinsic motivation are provided（27）For interior rotor（25）There is provided dynamic
Power；Interior rotor（25）Steering and outer rotor（24）Steering with preceding rotor（5）Steering it is identical；Wing axle（23）Horizontal cloth
Put；Interior rotor（25）Pivot and outer rotor（24）Pivot line be in wing axle（23）Underface；Outward turning
The wing（24）Plane of rotation and interior rotor（25）Plane of rotation it is coplanar；Interior rotor（25）Plane of rotation be horizontal；
Work as front flaps（21）And rear plastic（22）When being all deflected downwards to extreme lower position, interior rotor（25）Wing tip turning circumference
Foremost with rearmost end respectively with front flaps（21）And rear plastic（22）Between beeline be both greater than 10mm；The anterior wing
Piece（21）And rear plastic（22）Chord length it is equal, rear plastic（22）Chord length be equal to or slightly greater than interior rotor（25）Rotation
Radius；Left composite wing（2）Length be more than interior rotor（25）Diameter and outer rotor（24）Diameter sum.
2. the axle aircraft of a kind of symmetric form six according to claim 1, it is characterised in that：Rear plastic（22）Chord length etc.
In interior rotor（25）Radius of turn；Left composite wing（2）Length be more than interior rotor（25）Twice of diameter.
3. the axle aircraft of a kind of symmetric form six according to claim 1, it is characterised in that：It is anterior for relative level
Fin（21）The maximum angle upward deflected is no more than 35 °, front flaps（21）The maximum angle deflected down is no more than 20 °；
Rear plastic（22）The maximum angle upward deflected is no more than 35 °, rear plastic（22）The maximum angle deflected down is no more than
20°。
4. the axle aircraft of a kind of symmetric form six according to claim 3, it is characterised in that：It is anterior for relative level
Fin（21）The maximum angle upward deflected is 20 °, front flaps（21）The maximum angle deflected down is 15 °；Rear plastic
（22）The maximum angle upward deflected is 20 °, rear plastic（22）The maximum angle deflected down is 15 °.
5. the axle aircraft of a kind of symmetric form six according to claim 1 or 2 or 3 or 4, it is characterised in that：Preceding rotor（5）'s
Plane of rotation and rear rotor（6）Plane of rotation be in same level in；Outer rotor（24）Plane of rotation and preceding rotor（5）
Plane of rotation it is coplanar.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510721355.4A CN105217024B (en) | 2015-10-30 | 2015-10-30 | A kind of axle aircraft of symmetric form six |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510721355.4A CN105217024B (en) | 2015-10-30 | 2015-10-30 | A kind of axle aircraft of symmetric form six |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105217024A CN105217024A (en) | 2016-01-06 |
| CN105217024B true CN105217024B (en) | 2017-10-10 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510721355.4A Active CN105217024B (en) | 2015-10-30 | 2015-10-30 | A kind of axle aircraft of symmetric form six |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105217024B (en) |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN205131640U (en) * | 2015-10-30 | 2016-04-06 | 佛山市神风航空科技有限公司 | Six aircraft on symmetry type |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5244167A (en) * | 1991-08-20 | 1993-09-14 | John Turk | Lift augmentation system for aircraft |
| US9889928B2 (en) * | 2009-08-26 | 2018-02-13 | Manuel Salz | Lift, propulsion and stabilising system for vertical take-off and landing aircraft |
| US10625852B2 (en) * | 2014-03-18 | 2020-04-21 | Joby Aero, Inc. | Aerodynamically efficient lightweight vertical take-off and landing aircraft with pivoting rotors and stowing rotor blades |
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2015
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Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN205131640U (en) * | 2015-10-30 | 2016-04-06 | 佛山市神风航空科技有限公司 | Six aircraft on symmetry type |
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| Publication number | Publication date |
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| CN105217024A (en) | 2016-01-06 |
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Effective date of registration: 20190624 Address after: 100039 Building No. 1, 51 Yongding Road, Haidian District, Beijing Patentee after: Beijing Remote Sensing Equipment Institute Address before: 528500 room 402, Fu Wan Jiangwan Road, Hecheng street, Gaoming District, Foshan, Guangdong, China, 78 Patentee before: Shenfeng science and technology of aviation Co., Ltd of Foshan City |
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