CN105217026B - A kind of compound aircraft - Google Patents
A kind of compound aircraft Download PDFInfo
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- CN105217026B CN105217026B CN201510721191.5A CN201510721191A CN105217026B CN 105217026 B CN105217026 B CN 105217026B CN 201510721191 A CN201510721191 A CN 201510721191A CN 105217026 B CN105217026 B CN 105217026B
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Abstract
A kind of compound aircraft, category vehicle technology field, including fuselage, left composite wing, right composite wing, compound empennage and undercarriage.It is furnished with control system and airborne equipment in fuselage.Compound empennage is located at the afterbody of fuselage, and compound empennage includes vertical tail, left electric propeller and right electric propeller.Left electric propeller is identical with right electric screw paddle structure, turns on the contrary, being symmetrically arranged in the right and left of vertical tail.Undercarriage uses wheeled construction or 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.It are furnished with two or three rotors in left composite wing, each rotor is by an engine driving.The fin of left composite wing includes fixed front flaps and the rear plastic that can be deflected around wing axle.All rotors are all located at the lower section of wing axle.The compound aircraft landing site is little, can be vertically moved up or down.Caused lift is larger, safety and stability and maneuverability.
Description
Technical field
A kind of compound aircraft, category vehicle technology field, more particularly to a kind of compound aircraft.
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, relatively short distance landing is also highly difficult.Traditional helicopter energy consumption is big, and efficiency is low, and safety and stability is not high.
The content of the invention
The purpose of the present invention is to overcome the above-mentioned deficiency of traditional aircraft and helicopter, and invention is a kind of to facilitate short take-off and landing
The even compound aircraft of the efficient safety and stability of energy VTOL.
A kind of compound aircraft, including fuselage, left composite wing, right composite wing, compound empennage and undercarriage.Fuselage
It is interior to be furnished with control system and airborne equipment.Left composite wing is identical with right composite wing structure, and they are symmetrically arranged on fuselage
The left and right sides.Compound empennage is located at the afterbody of fuselage, and compound empennage includes vertical tail, left electric propeller and right electric screw
Oar.Left electric propeller is identical with right electric screw paddle structure, turns on the contrary, being symmetrically arranged in the right and left of vertical tail.
Left electric propeller includes propeller and motor, and motor is by lithium battery power supply.Vertical tail plays vertical stabilization and rudder
Effect, the effect of left electric propeller and right electric propeller lifting rudder are also used for adjusting flight attitude.Undercarriage is using wheel
Formula structure or 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, intrinsic motivation and support.Front flaps are fixed on the left side of fuselage.Wing axle is horizontally disposed, the left end of wing axle with
Front flaps are connected, and the right-hand member of wing axle is fixed on fuselage, and wing axle is placed at the trailing edge of front flaps.The leading edge of front flaps is high
In the trailing edge of front flaps, the angle of front flaps and horizontal plane is between 8 ° -30 °.The front end of rear plastic is connected with wing axle,
Rear plastic can deflect up and down around wing axle.For relative level, the maximum angle that rear plastic upward deflects is no more than 35 °,
The maximum angle that rear plastic deflects down is no more than 30 °.Interior rotor is installed close to fuselage and outer rotor is installed away from fuselage.Outside
The diameter of rotor is not more than the diameter of interior rotor.Outer engine and intrinsic motivation are arranged on the support being all connected with fuselage and wing axle
On, outer engine provides power for outer rotor, and intrinsic motivation provides power for interior rotor.The pivot of interior rotor and outer rotor
The line of pivot be in the lower section of wing axle, and the line is parallel with wing axle.The Plane of rotation of outer rotor and interior rotor
Plane of rotation is coplanar.The Plane of rotation of interior rotor slightly forward downward tilt or be horizontal, the Plane of rotation of interior rotor with
The angle of the forward downward of horizontal plane is not more than 8 °.Between the rearmost end and rear plastic of the wing tip turning circumference of interior rotor most
Short distance is more than 8mm.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 be equal to or
Slightly larger than the radius of turn of interior rotor.The length of left composite wing is more than the diameter of interior rotor and the diameter sum of outer rotor.
The quantity of rotor and engine in the compound aircraft of the present invention also has six sets of form in addition to four sets：It is left
Three rotors and supporting three engines are housed, three rotors are arranged in a linear in the wing axle of left composite wing in composite wing
Lower section, the length of left composite wing is more than the diameter sum of three rotors during the form；Right composite wing and left composite wing
Structure it is identical, they are symmetrically arranged on the left and right sides of fuselage.
In order to improve mobility, it will leave blank among the canned paragraph of the vertical tail of the compound aircraft, left blank at this
One electronic vertical screw of the vertical arrangement installation in position longitudinal direction, wide-angle turns when so facilitating the aircraft hovering or low speed
To.
A kind of operation principle of compound aircraft of the invention is：Such as by the rear plastic of left composite wing and right compounding machine
The rear plastic of the wing is all deflected downwards to extreme lower position, and undercarriage is adjusted and to wheeled state, starts all engines, point
Not Qu Dong corresponding to rotor wing rotation, the aircraft can realize takeoff；Such as the rear plastic of left composite wing and the right side are answered
The rear plastic for closing wing all deflects upward into extreme higher position, and the aircraft can be realized and taken off vertically.Adjust left composite wing
Rear plastic and right composite wing rear plastic deflection angle and direction can change the aircraft caused by air move
The direction of power and size, the rotating speed by adjusting each rotor can also change aerodynamic size and Orientation of the aircraft.
Pitching and the course of the aircraft are controlled by compound empennage.Compare with traditional aircraft, the compound aircraft of the present invention
It is required that landing site it is little, and can be vertically moved up or down.Compared with traditional helicopter, the compound aircraft of the present invention is multiple due to a left side
Close the presence of wing and right composite wing, lift caused by the aircraft is larger, if run out of steam can also glide it is longer
Distance, it can strive for that more times carry out maintenance of equipment or find safe landing point, it is so relatively safer；Due to left composite wing
Rotor and the corresponding rotor of right composite wing turn on the contrary, rotating torque can be offset, flight stability and control is simple；By
Lower section in all rotors all in fin, the flow field of fin upper and lower surface can be improved during rotor rotational, increase downwash flow, prolong
The air-flow separation of the upper surface of backlimb piece, improves efficiency, greatly increases lift coefficient, due to multiple rotors and compound empennage
In the presence of the aircraft maneuverability.
Brief description of the drawings
Fig. 1 is a kind of left view schematic diagram of compound aircraft of the present invention；Fig. 2 is Fig. 1 schematic top plan view；Fig. 3 is to put
The left view schematic diagram of big left composite wing, 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- vertical tails, the left electric propellers of 5-, the 6- right sides
Electric propeller, 7- undercarriages；Belonging to the component of left composite wing 2 includes：21- front flaps, 22- rear plastics, the 23- wings
Axle, the outer rotors of 24-, rotor in 25-, the outer engines of 26-, 27- intrinsic motivations, 28- supports.
Embodiment
The present invention is illustrated in conjunction with accompanying drawing：A kind of compound aircraft, including fuselage 1, left composite wing
2nd, right composite wing 3, compound empennage and undercarriage 7.It is furnished with control system and airborne equipment in fuselage 1.Left composite wing 2 and the right side
The structure of composite wing 3 is identical, and they are symmetrically arranged on the left and right sides of fuselage 1.Compound empennage is located at the afterbody of fuselage 1, compound
Empennage includes vertical tail 4, left electric propeller 5 and right electric propeller 6.Left electric propeller 5 and right electric propeller 6 knot
Structure is identical, turns on the contrary, being flatly symmetrically arranged in the right and left of vertical tail 4.Left electric propeller 5 include propeller and
Motor, motor is by lithium battery power supply.Vertical tail 4 plays vertical stabilization and rudder, left electric propeller 5 and right electricity
The effect of the dynamic lifting rudder of propeller 6 is also used for adjusting flight attitude.Undercarriage 7 uses wheeled construction.The knot of left composite wing 2
Structure is：Left composite wing 2 includes front flaps 21, rear plastic 22, wing axle 23, outer rotor 24, interior rotor 25, outer engine
26th, intrinsic motivation 27 and support 28.Front flaps 21 are fixed on the left side of fuselage 1.Wing axle 23 is horizontally disposed, the left end of wing axle 23
It is connected with front flaps 21, the right-hand member of wing axle 23 is fixed on the fuselage 1, and wing axle 23 is placed at the trailing edge of front flaps 21.It is anterior
The leading edge of fin 21 is higher than the trailing edge of front flaps 21, and the angle of front flaps 21 and horizontal plane is 23 °.Before rear plastic 22
End is connected with wing axle 23, and rear plastic 22 can deflect around wing axle about 23.For relative level, rear plastic 22 upward deflects
Maximum angle be 25 °, the maximum angle that rear plastic deflects down be 15 °.Interior rotor 25 is installed and outer rotor close to fuselage 1
24 install away from fuselage 1.The diameter of outer rotor 24 is not more than the diameter of interior rotor 25.Outer engine 26 and intrinsic motivation 27 are installed
On the support 28 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 line of the pivot of interior rotor 25 and the pivot of outer rotor 24 be in wing axle 23 just under
Side, and the line is parallel with wing axle 23.The Plane of rotation of outer rotor 24 and the Plane of rotation of interior rotor 25 are coplanar.Interior rotor 25
Plane of rotation is horizontal.Beeline between the rearmost end and rear plastic 22 of the wing tip turning circumference of interior rotor 25
More than 8mm.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 equal to or slightly greater than
The radius of turn of interior rotor 25.The length of left composite wing 2 is more than the diameter of interior rotor 25 and the diameter sum of outer rotor 24.
The compound aircraft of the present invention is such generation beneficial effect：Such as by the He of rear plastic 22 of left composite wing 2
The rear plastic of right composite wing 3 is all deflected downwards to extreme lower position, starts all engines, respectively rotor corresponding to driving
Rotation, the aircraft can realize takeoff；Such as by the rear plastic 22 of left composite wing 2 and the rear portion of right composite wing 3
Fin all deflects upward into extreme higher position, and the aircraft can be realized and taken off vertically.Adjust the rear plastic 22 of left composite wing 2
With the deflection angle of the rear plastic of right composite wing 3 and direction can change aerodynamic direction caused by the aircraft and
Size, the rotating speed by adjusting each rotor can also change aerodynamic size and Orientation of the aircraft.Pass through compound tail
The wing controls the pitching of the aircraft and course.Compare with traditional aircraft, the landing of the compound aircraft requirements of the present invention
Place is little, and can be vertically moved up or down.Compared with traditional helicopter, the compound aircraft of the present invention is due to left composite wing and the right side
The presence of composite wing, lift caused by the aircraft is larger, if running out of steam the longer distance that can also glide, Ke Yizheng
More times are taken to carry out maintenance of equipment or find safe landing point, it is so relatively safer；Rotor and the right side due to left composite wing
The corresponding rotor of composite wing is turned on the contrary, rotating torque can be offset, flight stability and control is simple；Due to all rotors
The flow field of fin upper and lower surface can be improved all in the lower section of fin, during rotor rotational, increase downwash flow, delay the upper of fin
The air-flow separation on surface, improves efficiency, greatly increases lift coefficient, described due to the presence of multiple rotors and compound empennage
Aircraft maneuverability.The rear plastic 22 of left composite wing 2 and the rear plastic of right composite wing 3 can also play traditional fly
The effect of the wing flap and aileron of machine.Therefore the compound aircraft more maneuverability.
Claims (6)
- A kind of 1. compound aircraft, it is characterised in that：Including fuselage（1）, left composite wing（2）, right composite wing（3）, it is multiple Close empennage and undercarriage（7）；Fuselage（1）It is interior to be furnished with control system and airborne equipment；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；Compound empennage is located at fuselage（1）Afterbody, compound tail The wing includes vertical tail（4）, left electric propeller（5）With right electric propeller（6）；Left electric propeller（5）With right electronic spiral shell Revolve oar（6）Structure is identical, turns on the contrary, being flatly symmetrically arranged in vertical tail（4）The right and left；Left electric propeller （5）Including propeller and motor；Vertical tail（4）Play vertical stabilization and rudder, left electric propeller（5）And the right side Electric propeller（6）The effect of lifting rudder is also used for adjusting flight attitude；Undercarriage（7）Using wheeled construction or sled and wheel Formula combining structure；Left composite wing（2）Structure be：Left composite wing（2）Including front flaps（21）, rear plastic（22）、 Wing axle（23）, outer rotor（24）, interior rotor（25）, outer engine（26）, intrinsic motivation（27）And support（28）；Front flaps （21）It is fixed on fuselage（1）Left side；Wing axle（23）It is horizontally disposed, wing axle（23）Left end and front flaps（21）It is connected, the wing Axle（23）Right-hand member be fixed on fuselage（1）On, wing axle（23）It is placed in front flaps（21）Trailing edge at；Front flaps（21）Before Edge is higher than front flaps（21）Trailing edge, front flaps（21）Angle with horizontal plane is between 8 ° -30 °；Rear plastic（22） Front end and wing axle（23）It is connected, rear plastic（22）Can be around wing axle（23）Deflection up and down；For relative level, 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 30 °；Inward turning The wing（25）Close to fuselage（1）Install and outer rotor（24）Away from fuselage（1）Installation；Outer rotor（24）Diameter be not more than interior rotor （25）Diameter；Outer engine（26）And intrinsic motivation（27）It is arranged on and fuselage（1）With wing axle（23）All connected supports （28）On, outer engine（26）For outer rotor（24）Power, intrinsic motivation are provided（27）For interior rotor（25）Power is provided；Inward turning The wing（25）Pivot and outer rotor（24）The line of pivot be in wing axle（23）Lower section, and the line and wing axle （23）It is parallel；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 is tilted or is horizontal；Interior rotor（25）Wing tip turning circumference rearmost end and rear plastic（22）It Between beeline be more than 8mm；Rear plastic（22）Chord length be equal to or slightly greater than interior rotor（25）Radius of turn；The anterior wing Piece（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）Diameter sum；Vertical tail（4）Canned paragraph among leave blank, the position of leaving blank is longitudinally perpendicular Straight arrangement is installed with an electronic vertical screw.
- A kind of 2. compound aircraft according to claim 1, it is characterised in that：Front flaps（21）Leading edge be higher than before Portion's fin（21）Trailing edge, front flaps（21）Angle with horizontal plane is 23 °.
- A kind of 3. compound aircraft according to claim 1, it is characterised in that：For relative level, rear plastic （22）The maximum angle upward deflected is 25 °, rear plastic（22）The maximum angle deflected down is 15 °.
- A kind of 4. compound aircraft according to claim 1, it is characterised in that：Interior rotor（25）Pivot and outer Rotor（24）The line of pivot be in wing axle（23）Underface.
- A kind of 5. compound aircraft according to claim 1 or 2 or 3 or 4, it is characterised in that：Rotor and engine Quantity also has six sets of form in addition to four sets：Three rotors and supporting three engines are housed, this three in left composite wing Individual rotor is arranged in a linear in the lower section of the wing axle of left composite wing, and the length of left composite wing is more than three rotors during the form Diameter sum；Right composite wing is identical with the structure of left composite wing, and they are symmetrically arranged on the left and right sides of fuselage.
- A kind of 6. compound aircraft according to claim 1 or 2 or 3 or 4, it is characterised in that：Interior rotor（25）Rotation The angle for turning the forward downward of plane and horizontal plane is not more than 8 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510721191.5A CN105217026B (en) | 2015-10-30 | 2015-10-30 | A kind of compound aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510721191.5A CN105217026B (en) | 2015-10-30 | 2015-10-30 | A kind of compound aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105217026A CN105217026A (en) | 2016-01-06 |
| CN105217026B true CN105217026B (en) | 2017-12-19 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510721191.5A Active CN105217026B (en) | 2015-10-30 | 2015-10-30 | A kind of compound aircraft |
Country Status (1)
| Country | Link |
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| CN (1) | CN105217026B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SG11201913608YA (en) * | 2017-07-18 | 2020-01-30 | St Eng Aerospace Ltd | Asymmetric aerial vehicle |
| US10144503B1 (en) * | 2018-02-22 | 2018-12-04 | Kitty Hawk Corporation | Fixed wing aircraft with trailing rotors |
| EP3757004B1 (en) * | 2019-06-27 | 2023-03-29 | Volocopter GmbH | Vtol aircraft with wing connecting booms |
| CN115071967B (en) * | 2022-07-14 | 2024-07-23 | 西南交通大学 | Vertical take-off and landing aircraft |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3139244A (en) * | 1961-08-15 | 1964-06-30 | Cooper B Bright | Inflatable vtol aircraft |
| US4789115A (en) * | 1986-08-29 | 1988-12-06 | Theodore Koutsoupidis | VTOL aircraft |
| 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 |
| CN104369863A (en) * | 2014-10-31 | 2015-02-25 | 吴建伟 | Composite vertical take-off/landing aircraft |
| CN205131654U (en) * | 2015-10-30 | 2016-04-06 | 佛山市神风航空科技有限公司 | Compound aircraft |
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2015
- 2015-10-30 CN CN201510721191.5A patent/CN105217026B/en active Active
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| Publication number | Publication date |
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| CN105217026A (en) | 2016-01-06 |
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Effective date of registration: 20191119 Address after: 313000 1-B, building 1, No. 656, Qixing Road, high tech Zone, Wuxing District, Huzhou City, Zhejiang Province Patentee after: Huzhou Qiqi Electromechanical 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-B, building 1, No. 656, Qixing Road, high tech Zone, Wuxing District, Huzhou City, Zhejiang Province Patentee before: Huzhou Qiqi Electromechanical Technology Co.,Ltd. |
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| TR01 | Transfer of patent right |