CN105197234A - Combined aircraft provided with empennage - Google Patents
Combined aircraft provided with empennage Download PDFInfo
- Publication number
- CN105197234A CN105197234A CN201510721341.2A CN201510721341A CN105197234A CN 105197234 A CN105197234 A CN 105197234A CN 201510721341 A CN201510721341 A CN 201510721341A CN 105197234 A CN105197234 A CN 105197234A
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- CN
- China
- Prior art keywords
- wing
- rotor
- empennage
- interior rotor
- rear plastic
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Abstract
The invention discloses a combined aircraft provided with an empennage and belongs to the technical field of aircrafts. The combined aircraft comprises an aircraft body, a left combined wing, a right combined wing, the empennage and a landing gear, wherein a control system and airborne equipment are arranged in the aircraft body; the empennage is located at the tail part of the aircraft body and comprises a horizontal empennage and a vertical empennage; the landing gear adopts a wheel type structure; the left combined wing and the right combined wing have the same structure and are mounted symmetrically on the left side and the right side of the aircraft body; two rotors are arranged in the left combined wing, and each rotor is driven by an engine; vanes of the left combined ring comprise a fixed front vane and a rear vane capable of deflecting around the wing axis, and all the rotors are located below the wing axis. The combined aircraft provided with the empennage requires a small take-off and landing field, takes off and lands vertically, is safe, stable and flexible and produces larger lift force.
Description
Technical field
With a compound type aircraft for empennage, belong to vehicle technology field, particularly relate to a kind of compound type aircraft with empennage.
Background technology
Traditional taking off and land needs comparatively long runway, also inconvenient Ultra-Low Speed flight, and comparatively short take-off and landing is also very difficult.Traditional helicopter energy consumption is large, and efficiency is low, and safety and stability is not high.
Summary of the invention
The object of the invention is the above-mentioned deficiency overcoming traditional aircraft and helicopter, invent a kind of compound type aircraft facilitating the band empennage of the efficient safety and stability of short take-off and landing.
With a compound type aircraft for empennage, comprise fuselage, left composite wing, right composite wing, empennage 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.Empennage is positioned at the afterbody of fuselage, and empennage comprises tailplane and vertical tail.Tailplane comprises leading portion fixed part and back segment moving part, and the back segment of vertical tail can deflection.Tailplane plays horizontal stabilizer and elevating rudder, and vertical tail plays vertical stabilator and yaw rudder.Alighting gear adopts wheeled 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, intrinsic motivation and support.Front flaps is fixed on the left side of fuselage.Wing axle transverse horizontal is arranged, the left end of wing axle is connected with front flaps, and the right-hand member of wing axle is fixed on fuselage, and wing axle is placed in the trailing edge place of front flaps.The leading edge of front flaps is higher than the trailing edge of front flaps, and the angle of front flaps and horizontal surface is between 4 °-15 °.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 rear plastic upward deflects is no more than 20 °, and the maximum angle that rear plastic deflects down is no more than 15 °.Interior rotor near fuselage installation, install away from fuselage by outer rotor.The diameter of outer rotor and the equal diameters of interior rotor.Outer rotor and interior rotor turn on the contrary.Outer driving engine and intrinsic motivation are arranged on the top of outer rotor and interior rotor respectively by support, and outer driving engine is connected with interior rotor with outer rotor respectively with the axle shaft of intrinsic motivation.The line of the centre of gration of interior rotor and the centre of gration of outer rotor is in immediately below wing axle, and this line is parallel with 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 tilts slightly toward front lower place, and the angle of the plane of rotation of interior rotor and the forward downward of horizontal surface is not more than 6 °.When rear plastic deflects down maximum angle, its trailing edge is greater than 12mm to the shortest distance of the plane of rotation of interior rotor.The chord length of rear plastic equals or is slightly smaller than the radius of rotation of interior rotor.The chord length of front flaps is equal to or slightly greater than the radius of rotation of interior rotor.The length of left composite wing is greater than the twice of the diameter of interior rotor.
The principle of work of a kind of compound type aircraft with empennage of this invention is: as the rear plastic of the rear plastic of left composite wing and right composite wing all deflected down, start all driving engines, drive corresponding rotor wing rotation respectively, described aircraft can realize rolling start; As the rear plastic of the rear plastic of left composite wing and right composite wing is all deflected upward into extreme higher position, described aircraft can realize taking off vertically.Adjust the deflection angle of the rear plastic of left composite wing and the rear plastic of 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.Pitching and the course of described aircraft is controlled by empennage.Compare with traditional aircraft, the landing site of the compound type aircraft requirements of band empennage of the present invention is little, and can vertical lift.Compare with traditional helicopter, the compound type aircraft of band empennage 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; Even if the descending speed losing the vertical described aircraft that declines due to power also can not be too fast, relatively safe.Because interior rotor and outer rotor turn on the contrary, rotating torque can be offset, flight stability and control simple; Because all rotors are all in the below of fin, the flow field of fin upper and lower surface during rotor rotational, can be improved, increase downwash flow, delay the burbling of the upper surface of fin, raise the efficiency, lift coefficient is increased greatly.
Accompanying drawing explanation
Fig. 1 is that schematic diagram is looked on a left side for a kind of compound type aircraft with empennage of the present invention, 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-empennage, 41-tailplane, 42-vertical tail, 5-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, 28-support.
Detailed description of the invention
Now by reference to the accompanying drawings the present invention is illustrated: a kind of compound type aircraft with empennage, comprises fuselage 1, left composite wing 2, right composite wing 3, empennage 4 and alighting gear 5.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.Empennage 4 is positioned at the afterbody of fuselage 1, and empennage 4 comprises tailplane 41 and vertical tail 42.Tailplane 41 comprises leading portion fixed part and back segment moving part, and the back segment of vertical tail 42 can deflection.Tailplane 41 plays horizontal stabilizer and elevating rudder, and vertical tail 42 plays vertical stabilator and yaw rudder.Alighting gear 5 adopts wheeled 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, intrinsic motivation 27 and support 28.Front flaps 21 is fixed on the left side of fuselage 1.Wing axle 23 transverse horizontal is arranged, the left end of wing axle 23 is connected with front flaps 21, and the right-hand member of wing axle 23 is fixing on the fuselage 1, and wing axle 23 is placed in the trailing edge place of front flaps 21.The leading edge of front flaps 21 is higher than the trailing edge of front flaps 21, and front flaps 21 is 12 ° with the angle of horizontal surface.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 rear plastic 22 upward deflects is 15 °, and the maximum angle that rear plastic 22 deflects down is 12 °.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 and the equal diameters of interior rotor 25.Outer rotor 24 and interior rotor 25 turn on the contrary.Outer driving engine 26 and intrinsic motivation 27 are arranged on the top of outer rotor 24 and interior rotor 25 respectively by support 28, and outer driving engine 26 is connected with interior rotor 25 with outer rotor 24 respectively with the axle shaft of intrinsic motivation 27.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, and this line is parallel with 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 tilts slightly toward front lower place, and the angle of the interior plane of rotation of rotor 25 and the forward downward of horizontal surface is 4 °.When rear plastic 21 deflects down maximum angle, its trailing edge is greater than 12mm to the shortest distance of the plane of rotation of interior rotor 25.The chord length of rear plastic 21 is slightly smaller than the radius of rotation of interior rotor 25.The chord length of front flaps 21 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.
The compound type aircraft of band empennage 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 all deflected down, start all driving engines, drive corresponding rotor wing rotation respectively, described aircraft can realize rolling start; As the rear plastic of the rear plastic 22 of left composite wing 2 and right compounding machine 3 wing is all deflected upward into extreme higher position, described aircraft can realize taking off vertically.Adjust the deflection angle of the rear plastic 22 of left composite wing 2 and the rear plastic of 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.Pitching and the course of described aircraft is controlled by empennage 4.Compare with traditional aircraft, the landing site of the compound type aircraft requirements of band empennage of the present invention is little, and can vertical lift.Compare with traditional helicopter, the compound type aircraft of band empennage 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; Even if the descending speed losing the vertical described aircraft that declines due to power also can not be too fast, relatively safe.Because interior rotor 25 and outer rotor 24 turn on the contrary, rotating torque can be offset, flight stability and control simple; Because all rotors are all in the below of fin, the flow field of fin upper and lower surface during rotor rotational, can be improved, increase downwash flow, delay the burbling of the upper surface of fin, raise the efficiency, lift coefficient is increased greatly.
Claims (3)
1. the compound type aircraft with empennage, is characterized in that: comprise fuselage (1), left composite wing (2), right composite wing (3), empennage (4) and alighting gear (5); Be furnished with control system in fuselage (1) identical with right composite wing (3) structure with the left composite wing of airborne equipment (2), their symmetries are installed on the left and right sides of fuselage (1); Empennage (4) is positioned at the afterbody of fuselage (1), and empennage (4) comprises tailplane (41) and vertical tail (42); Alighting gear (5) adopts wheeled 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), intrinsic motivation (27) and support (28); Front flaps (21) is fixed on the left side of fuselage (1); Wing axle (23) transverse horizontal is arranged, the left end of wing axle (23) is connected with front flaps (21), and the right-hand member of wing axle (23) is fixed on fuselage (1), and wing axle (23) is placed in the trailing edge place of front flaps (21); The leading edge of front flaps (21) is higher than the trailing edge of front flaps (21), and the angle of front flaps (21) and horizontal surface is between 4 °-15 °; 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); Relative level face, the maximum angle that rear plastic (22) upward deflects is no more than 20 °, and the maximum angle that rear plastic (22) deflects down is no more than 15 °; Interior rotor (25) near fuselage (1) installation, install away from fuselage (1) by outer rotor (24); The diameter of outer rotor (24) and the equal diameters of interior rotor (25); Outer rotor (24) and interior rotor (25) turn on the contrary; Outer driving engine (26) and intrinsic motivation (27) are arranged on the top of outer rotor (24) and interior rotor (25) respectively by support (28), and outer driving engine (26) is connected with interior rotor (25) with outer rotor (24) respectively with the axle shaft of intrinsic motivation (27); 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), and this line is parallel with 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) tilts slightly toward front lower place, and the angle of the plane of rotation of interior rotor (25) and the forward downward of horizontal surface is not more than 6 °; When rear plastic (21) deflects down maximum angle, its trailing edge is greater than 12mm to the shortest distance of the plane of rotation of interior rotor (25); The chord length of rear plastic (21) equals or is slightly smaller than the radius of rotation of interior rotor (25); The chord length of front flaps (21) 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 twice of the diameter of interior rotor (25).
2. a kind of compound type aircraft with empennage according to claim 1, is characterized in that: front flaps (21) is 12 ° with the angle of horizontal surface; Relative level face, the maximum angle that rear plastic (22) upward deflects is 15 °, and the maximum angle that rear plastic (22) deflects down is 12 °.
3. a kind of compound type aircraft with empennage according to claim 1 and 2, is characterized in that: the chord length of rear plastic (21) is slightly smaller than the radius of rotation of interior rotor (25); The chord length of front flaps (21) is a bit larger tham the radius of rotation of interior rotor (25).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510721341.2A CN105197234B (en) | 2015-10-30 | 2015-10-30 | A kind of compound aircraft with empennage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510721341.2A CN105197234B (en) | 2015-10-30 | 2015-10-30 | A kind of compound aircraft with empennage |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105197234A true CN105197234A (en) | 2015-12-30 |
| CN105197234B CN105197234B (en) | 2017-12-01 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510721341.2A Active CN105197234B (en) | 2015-10-30 | 2015-10-30 | A kind of compound aircraft with empennage |
Country Status (1)
| Country | Link |
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| CN (1) | CN105197234B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107985587A (en) * | 2017-11-28 | 2018-05-04 | 深圳华越无人机技术有限公司 | A kind of VTOL fixed-wing unmanned plane |
| CN109987222A (en) * | 2018-01-02 | 2019-07-09 | 上海骄翔智能技术有限公司 | Unmanned plane, powertrain and the method for reducing the air drag in unmanned plane |
| DE102019107593A1 (en) * | 2019-03-25 | 2020-10-01 | LIFT Holding GmbH | Flying device |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR735472A (en) * | 1932-04-06 | 1932-11-09 | Aircraft lifting device | |
| US4789115A (en) * | 1986-08-29 | 1988-12-06 | Theodore Koutsoupidis | VTOL aircraft |
| JP5277342B1 (en) * | 2012-12-11 | 2013-08-28 | 和博 高橋 | Vertical take-off and landing aircraft |
| CN104058093A (en) * | 2014-06-20 | 2014-09-24 | 吴智勇 | Novel tiltable rotor wing vertical take-off and landing plane |
| CN204452934U (en) * | 2015-02-05 | 2015-07-08 | 仉军 | The double mode aircraft of rotor, fixed-wing |
| CN205131655U (en) * | 2015-10-30 | 2016-04-06 | 佛山市神风航空科技有限公司 | Compound aircraft of tape trailer wing |
-
2015
- 2015-10-30 CN CN201510721341.2A patent/CN105197234B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR735472A (en) * | 1932-04-06 | 1932-11-09 | Aircraft lifting device | |
| US4789115A (en) * | 1986-08-29 | 1988-12-06 | Theodore Koutsoupidis | VTOL aircraft |
| JP5277342B1 (en) * | 2012-12-11 | 2013-08-28 | 和博 高橋 | Vertical take-off and landing aircraft |
| CN104058093A (en) * | 2014-06-20 | 2014-09-24 | 吴智勇 | Novel tiltable rotor wing vertical take-off and landing plane |
| CN204452934U (en) * | 2015-02-05 | 2015-07-08 | 仉军 | The double mode aircraft of rotor, fixed-wing |
| CN205131655U (en) * | 2015-10-30 | 2016-04-06 | 佛山市神风航空科技有限公司 | Compound aircraft of tape trailer wing |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107985587A (en) * | 2017-11-28 | 2018-05-04 | 深圳华越无人机技术有限公司 | A kind of VTOL fixed-wing unmanned plane |
| CN107985587B (en) * | 2017-11-28 | 2020-05-19 | 深圳华越无人机技术有限公司 | Vertical take-off and landing fixed wing unmanned aerial vehicle |
| CN109987222A (en) * | 2018-01-02 | 2019-07-09 | 上海骄翔智能技术有限公司 | Unmanned plane, powertrain and the method for reducing the air drag in unmanned plane |
| DE102019107593A1 (en) * | 2019-03-25 | 2020-10-01 | LIFT Holding GmbH | Flying device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105197234B (en) | 2017-12-01 |
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Effective date of registration: 20190605 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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| TR01 | Transfer of patent right |