CN105217024A - A kind of symmetric form six axle aircraft - Google Patents
A kind of symmetric form six axle aircraft Download PDFInfo
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- CN105217024A CN105217024A CN201510721355.4A CN201510721355A CN105217024A CN 105217024 A CN105217024 A CN 105217024A CN 201510721355 A CN201510721355 A CN 201510721355A CN 105217024 A CN105217024 A CN 105217024A
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Abstract
A kind of symmetric form six axle aircraft, belongs to vehicle technology field, comprises fuselage, left composite wing, right composite wing, support, front rotor, rear rotor and alighting gear.Control system and airborne equipment is furnished with in fuselage.Left composite wing is identical with right composite wing structure, and their symmetries are installed on the left and right sides of fuselage.Front rotor is identical with rear rotor structure, and they are installed on the rear and front end of fuselage respectively by support.Alighting gear adopts sled and wheeled unitized construction.Left composite wing is identical with right composite wing structure, and their symmetries are installed on the left and right sides of fuselage.Respectively be furnished with two rotors in left composite wing and right composite wing, each rotor is by an engine drive.The fin of left composite wing comprises can around the front flaps of wing axle deflection and rear plastic.Described symmetric form six axle aircraft landing site is little, can vertical lift.The lift produced is comparatively large, safety and stability and maneuverability.
Description
Technical field
A kind of symmetric form six axle aircraft, belongs to vehicle technology field, particularly relates to a kind of six axle aircraft.
Background technology
When six traditional axle aircraft cruise, energy consumption is large, stability and safety poor, substantially cannot save oneself when losing part or all of power.Traditional aircraft can not vertical lift and hovering.Traditional helicopter energy consumption is large, and efficiency is low, and safety and stability is not high yet.
Summary of the invention
The object of the invention is the above-mentioned deficiency overcoming traditional six axle aircraft, aircraft and helicopter, invent a kind of symmetric form six axle aircraft of highly effective and safe of energy vertical takeoff and landing.
A kind of symmetric form six axle aircraft, comprises fuselage, left composite wing, right composite wing, support, front rotor, rear rotor and alighting gear.Control system and airborne equipment is furnished with in fuselage.Left composite wing is identical with right composite wing structure, and their symmetries are installed on the left and right sides of fuselage.Front rotor is identical with rear rotor structure, and they are installed on the rear and front end of fuselage respectively by support.Front rotor and rear rotor are driven by two motors respectively.Front rotor and rear rotor turn on the contrary, and rotating speed is convenient to be regulated.Front rotor and rear rotor mainly play pitching and lifting flight attitude control action.Alighting gear adopts sled and wheeled unitized construction.
The structure of left composite wing is: left composite wing comprises front flaps, rear plastic, wing axle, outer rotor, interior rotor, outer driving engine and intrinsic motivation.The rear end of front flaps is connected with wing axle, and front flaps can deflect up and down around wing axle.The front end of rear plastic is connected with wing axle, and rear plastic can deflect up and down around wing axle.Relative level face, the maximum angle that front flaps upward deflects is no more than 35 °, and the maximum angle that front flaps deflects down is no more than 20 °; The maximum angle that rear plastic upward deflects is no more than 35 °, and the maximum angle that rear plastic deflects down is no more than 20 °.Interior rotor near fuselage installation, install away from fuselage by outer rotor.The diameter of outer rotor is not more than the diameter of interior rotor.Outer driving engine and intrinsic motivation are placed in outer rotor and the below of interior rotor respectively and are arranged on the support that is all connected with fuselage and wing axle, and outer driving engine provides power for outer rotor, and intrinsic motivation provides power for interior rotor.Turning to of interior rotor is all identical with turning to of front rotor with turning to of outer rotor.Wing axle horizontal arrangement.The line of the centre of gration of interior rotor and the centre of gration of outer rotor is in immediately below wing axle.The plane of rotation of outer rotor and the plane of rotation of interior rotor coplanar.The plane of rotation of interior rotor is horizontal.When front flaps and rear plastic are all deflected downwards to extreme lower position, the wing tip turning circumference of interior rotor foremost and the shortest distance of rearmost end respectively and between front flaps and rear plastic be all greater than 10mm.The chord length of front flaps and rear plastic is equal, and the chord length of rear plastic is equal to or slightly greater than the radius of rotation of interior rotor.The length of left composite wing is greater than the diameter of interior rotor and the diameter sum of outer rotor.
The principle of work of this invention a kind of symmetric form six axle aircraft is: as the rear plastic of the rear plastic of left composite wing and right composite wing is all deflected downwards to extreme lower position, the front flaps of the front flaps of left composite wing and right composite wing is all deflected upward into extreme higher position, and alighting gear is adjusted to wheeled state, start all driving engines and motor, drive corresponding rotor wing rotation respectively, described aircraft can realize advance rolling start; As the front flaps of the rear plastic of the rear plastic of left composite wing, right composite wing, the front flaps of left composite wing and right composite wing is all deflected upward into extreme higher position, described aircraft can realize taking off vertically; As the rear plastic of the rear plastic of left composite wing and right composite wing is all deflected upward into extreme higher position, the front flaps of the front flaps of left composite wing and right composite wing is all deflected downwards to extreme lower position, described aircraft can realize retreating flight.Adjust the deflection angle of the front flaps of the rear plastic of left composite wing, the rear plastic of right composite wing, the front flaps of left composite wing and right composite wing and direction and can change the aerodynamic direction and size that described aircraft produces, also can be changed aerodynamic size and Orientation of described aircraft by the rotating speed adjusting each rotor.Compare with traditional aircraft, the landing site of symmetric form six axle aircraft requirements of the present invention is little, and energy vertical lift, can aloft hover.Compare with traditional helicopter and Multi-axis aircraft, symmetric form six axle aircraft of the present invention is due to the existence of left composite wing and right composite wing, the lift that described aircraft produces is larger, if run out of steam longer distance of also gliding, more time docking facility can be striven for or find safe landing point, safer like this; Because in left composite wing and right composite wing, all rotors are all in the below of fin, before fly or after can improve the flow field of fin upper and lower surface when flying rotor rotational, increase downwash flow, delay the burbling of the upper surface of fin, raise the efficiency, lift coefficient is increased greatly, due to the existence of multiple rotor, described aircraft maneuverability.
Accompanying drawing explanation
Fig. 1 is that schematic diagram is looked on a left side for a kind of symmetric form six of the present invention axle aircraft, and Fig. 2 is the schematic top plan view of Fig. 1; Fig. 3 is that schematic diagram is looked on a left side for the left composite wing be exaggerated, and Fig. 4 is the schematic top plan view of Fig. 3.
In figure, 1-fuselage, the left composite wing of 2-, the right composite wing of 3-, 4-support, rotor before 5-, rotor after 6-, 7-alighting gear; The component belonging to left composite wing 2 comprises: 21-front flaps, 22-rear plastic, 23-wing axle, the outer rotor of 24-, rotor in 25-, the outer driving engine of 26-, 27-intrinsic motivation.
Detailed description of the invention
Now by reference to the accompanying drawings the present invention is illustrated: a kind of symmetric form six axle aircraft, comprises fuselage 1, left composite wing 2, right composite wing 3, support 4, front rotor 5, rear rotor 6 and alighting gear 7.Control system and airborne equipment is furnished with in fuselage 1.Left composite wing 2 is identical with right composite wing 3 structure, and their symmetries are installed on the left and right sides of fuselage 1.Front rotor 5 is identical with rear rotor 6 structure, and they are installed on the rear and front end of fuselage 1 respectively by support 8.Front rotor 5 and rear rotor 6 are driven by two motors respectively.Front rotor 5 and rear rotor 6 turn on the contrary, and rotating speed is convenient to be regulated.The plane of rotation of front rotor 5 and the plane of rotation of rear rotor 6 are in same level.Front rotor 5 and rear rotor 6 mainly play pitching and lifting flight attitude control action.Alighting gear 7 adopts sled and wheeled unitized construction.The structure of left composite wing 2 is: left composite wing 2 comprises front flaps 21, rear plastic 22, wing axle 23, outer rotor 24, interior rotor 25, outer driving engine 26 and intrinsic motivation 27.The rear end of front flaps 21 is connected with wing axle 23, and front flaps 21 can deflect around wing axle about 23.The front end of rear plastic 22 is connected with wing axle 23, and rear plastic 22 can deflect around wing axle about 23.Relative level face, the maximum angle that front flaps 21 upward deflects is 20 °, and the maximum angle that front flaps 21 deflects down is 15 °; The maximum angle that rear plastic 22 upward deflects is 20 °, and the maximum angle that rear plastic 22 deflects down is 15 °.Interior rotor 25 to be installed and outer rotor 24 is installed away from fuselage 1 near fuselage 1.The diameter of outer rotor 24 equals the diameter of interior rotor 25.Outer driving engine 26 and intrinsic motivation 27 are placed in outer rotor 24 and the below of interior rotor 25 respectively and are arranged on the support 4 that is all connected with fuselage 1 and wing axle 23, and outer driving engine 26 provides power for outer rotor 24, and intrinsic motivation 27 provides power for interior rotor 25.Turning to of interior rotor 25 is all identical with turning to of front rotor 5 with turning to of outer rotor 24.Wing axle 23 horizontal arrangement.The line of the centre of gration of interior rotor 25 and the centre of gration of outer rotor 24 is in immediately below wing axle 23.The plane of rotation of outer rotor 24 and the plane of rotation of interior rotor 25 coplanar.The plane of rotation of outer rotor 24 and the plane of rotation of front rotor 5 also coplanar.The plane of rotation of interior rotor 25 is horizontal.When front flaps 21 and rear plastic 22 are all deflected downwards to extreme lower position, the wing tip turning circumference of interior rotor 25 foremost and the shortest distance of rearmost end respectively and between front flaps 21 and rear plastic 22 be all greater than 10mm.The chord length of front flaps 21 and rear plastic 22 is equal, and the chord length of rear plastic 22 is a bit larger tham the radius of rotation of interior rotor 25.The length of left composite wing 2 is greater than the twice of the diameter of interior rotor 25.
Symmetric form six axle aircraft of the present invention produces beneficial effect like this: as the rear plastic 22 of left composite wing 2 and the rear plastic of right composite wing 3 are all deflected downwards to extreme lower position, the front flaps 21 of left composite wing 2 and the front flaps of right composite wing 3 are all deflected upward into appropriate location, and alighting gear 7 is adjusted to wheeled state, start all driving engines and motor, drive corresponding rotor wing rotation respectively, described aircraft can realize advance rolling start; As the front flaps of the rear plastic of the rear plastic 22 of left composite wing 2, right composite wing 3, the front flaps 21 of left composite wing 2 and right composite wing 3 is all deflected upward into extreme higher position, described aircraft can realize taking off vertically; As the rear plastic 22 of left composite wing 2 and the rear plastic of right composite wing 3 are all deflected upward into appropriate location, the front flaps 21 of left composite wing 2 and the front flaps of right composite wing 3 are all deflected downwards to extreme lower position, and described aircraft can realize retreating flight.Adjust the deflection angle of the front flaps of the rear plastic 22 of left composite wing 2, the rear plastic of right composite wing 3, the front flaps 21 of left composite wing 2 and right composite wing 3 and direction and can change the aerodynamic direction and size that described aircraft produces, also can be changed aerodynamic size and Orientation of described aircraft by the rotating speed adjusting each rotor.Compare with traditional aircraft, the landing site of symmetric form six axle aircraft requirements of the present invention is little, and energy vertical lift, can aloft hover.Compare with traditional helicopter and Multi-axis aircraft, symmetric form six axle aircraft of the present invention is due to the existence of left composite wing 2 and right composite wing 3, the lift that described aircraft produces is larger, if run out of steam longer distance of also gliding, more time docking facility can be striven for or find safe landing point, safer like this; Because rotors all in left composite wing 2 and right composite wing 3 is all in the below of fin, before fly or after can improve the flow field of fin upper and lower surface when flying rotor rotational, increase downwash flow, delay the burbling of the upper surface of fin, raise the efficiency, lift coefficient is increased greatly, due to the existence of multiple rotor, described aircraft maneuverability.
Claims (5)
1. a symmetric form six axle aircraft, is characterized in that: comprise fuselage (1), left composite wing (2), right composite wing (3), support (4), front rotor (5), rear rotor (6) and alighting gear (7); Fuselage is furnished with control system and airborne equipment in (1); Left composite wing (2) is identical with right composite wing (3) structure, and their symmetries are installed on the left and right sides of fuselage (1); Front rotor (5) is identical with rear rotor (6) structure, and they are installed on the rear and front end of fuselage (1) respectively by support (8); Front rotor (5) and rear rotor (6) are driven by two motors respectively; Front rotor (5) and rear rotor (6) turn on the contrary, and rotating speed is convenient to be regulated; Alighting gear (7) adopts sled and wheeled unitized construction; The structure of left composite wing (2) is: left composite wing (2) comprises front flaps (21), rear plastic (22), wing axle (23), outer rotor (24), interior rotor (25), outer driving engine (26) and intrinsic motivation (27); The rear end of front flaps (21) is connected with wing axle (23), and front flaps (21) can deflect up and down around wing axle (23); The front end of rear plastic (22) is connected with wing axle (23), and rear plastic (22) can deflect up and down around wing axle (23); Interior rotor (25) near fuselage (1) installation, install away from fuselage (1) by outer rotor (24); The diameter of outer rotor (24) is not more than the diameter of interior rotor (25); Outer driving engine (26) and intrinsic motivation (27) are placed in outer rotor (24) and the below of interior rotor (25) respectively and are arranged on the support (4) that is all connected with fuselage (1) and wing axle (23), outer driving engine (26) provides power for outer rotor (24), and intrinsic motivation (27) provides power for interior rotor (25); Turning to of interior rotor (25) is all identical with turning to of front rotor (5) with turning to of outer rotor (24); Wing axle (23) horizontal arrangement; The line of the centre of gration of interior rotor (25) and the centre of gration of outer rotor (24) is in immediately below wing axle (23); The plane of rotation of outer rotor (24) and the plane of rotation of interior rotor (25) coplanar; The plane of rotation of interior rotor (25) is horizontal; When front flaps (21) and rear plastic (22) are all deflected downwards to extreme lower position, the wing tip turning circumference of interior rotor (25) foremost and the shortest distance of rearmost end respectively and between front flaps (21) and rear plastic (22) be all greater than 10mm; The chord length of front flaps (21) and rear plastic (22) is equal, and the chord length of rear plastic (22) is equal to or slightly greater than the radius of rotation of interior rotor (25); The length of left composite wing (2) is greater than the diameter of interior rotor (25) and the diameter sum of outer rotor (24).
2. a kind of symmetric form six axle aircraft according to claim 1, is characterized in that: the chord length of rear plastic (22) equals the radius of rotation of interior rotor (25); The length of left composite wing (2) is greater than the twice of the diameter of interior rotor (25).
3. a kind of symmetric form six axle aircraft according to claim 1, it is characterized in that: relative level face, the maximum angle that front flaps (21) upward deflects is no more than 35 °, and the maximum angle that front flaps (21) deflects down is no more than 20 °; The maximum angle that rear plastic (22) upward deflects is no more than 35 °, and the maximum angle that rear plastic (22) deflects down is no more than 20 °.
4. a kind of symmetric form six axle aircraft according to claim 3, it is characterized in that: relative level face, the maximum angle that front flaps (21) upward deflects is 20 °, and the maximum angle that front flaps (21) deflects down is 15 °; The maximum angle that rear plastic (22) upward deflects is 20 °, and the maximum angle that rear plastic (22) deflects down is 15 °.
5. a kind of symmetric form six axle aircraft according to claim 1 or 2 or 3 or 4, is characterized in that: the plane of rotation of front rotor (5) and the plane of rotation of rear rotor (6) are in same level; The plane of rotation of outer rotor (24) and the plane of rotation of front rotor (5) 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 true CN105217024A (en) | 2016-01-06 |
| CN105217024B CN105217024B (en) | 2017-10-10 |
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| 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 |
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| Country | Link |
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| CN (1) | CN105217024B (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5244167A (en) * | 1991-08-20 | 1993-09-14 | John Turk | Lift augmentation system for aircraft |
| US20120280091A1 (en) * | 2009-08-26 | 2012-11-08 | Manuel Munoz Saiz | Lift, propulsion and stabilising system for vertical take-off and landing aircraft |
| WO2015143093A2 (en) * | 2014-03-18 | 2015-09-24 | Joby Aviation, Inc. | Aerodynamically efficient lightweight vertical take-off and landing aircraft with pivoting rotors and stowing rotor blades |
| 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 |
-
2015
- 2015-10-30 CN CN201510721355.4A patent/CN105217024B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5244167A (en) * | 1991-08-20 | 1993-09-14 | John Turk | Lift augmentation system for aircraft |
| US20120280091A1 (en) * | 2009-08-26 | 2012-11-08 | Manuel Munoz Saiz | Lift, propulsion and stabilising system for vertical take-off and landing aircraft |
| WO2015143093A2 (en) * | 2014-03-18 | 2015-09-24 | Joby Aviation, Inc. | Aerodynamically efficient lightweight vertical take-off and landing aircraft with pivoting rotors and stowing rotor blades |
| 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 |
|---|---|
| CN105217024B (en) | 2017-10-10 |
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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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