CN105197234B - A kind of compound aircraft with empennage - Google Patents
A kind of compound aircraft with empennage Download PDFInfo
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- CN105197234B CN105197234B CN201510721341.2A CN201510721341A CN105197234B CN 105197234 B CN105197234 B CN 105197234B CN 201510721341 A CN201510721341 A CN 201510721341A CN 105197234 B CN105197234 B CN 105197234B
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- wing
- rotor
- fuselage
- empennage
- rear plastic
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Abstract
A kind of compound aircraft with empennage, category 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.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 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 with empennage 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 with empennage, category vehicle technology field, more particularly to it is a kind of with the compound of empennage
Aircraft.
Background technology
Traditional to take off and the needs that land are compared with long runway, also inconvenient Ultra-Low Speed flight, relatively short distance landing is also very
It is 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
Efficient safety and stability the compound aircraft with empennage.
A kind of compound aircraft with empennage, including fuselage, left composite wing, right composite wing, empennage 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 machine
The left and right sides of body.Empennage is located at the afterbody of fuselage, and empennage includes tailplane and vertical tail.Tailplane is consolidated including leading portion
Fixed part and back segment movable part, the back segment of vertical tail can deflection.Tailplane plays horizontal stabilizer and elevator
Effect, vertical tail play vertical stabilization and rudder.Undercarriage uses wheeled construction.
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 transverse horizontal arrangement, a left side for wing axle
End is connected with front flaps, and the right-hand member of wing axle is fixed on fuselage, and wing axle is placed at the trailing edge of front flaps.Before front flaps
Edge is higher than the trailing edge of front flaps, and the angle of front flaps and horizontal plane is between 4 ° -15 °.The front end of rear plastic and wing axle
It is connected, 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
20 °, the maximum angle that rear plastic deflects down is no more than 15 °.Interior rotor is installed close to fuselage and outer rotor is pacified away from fuselage
Dress.The diameter of the diameter of outer rotor and interior rotor is equal.Outer rotor and interior rotor turn to opposite.Outer engine and intrinsic motivation lead to
Cross the top that support is separately mounted to outer rotor and interior rotor, the axle shaft of outer engine and intrinsic motivation respectively with outer rotor and
Interior rotor is connected.The line of the pivot of the pivot of interior rotor and outer rotor is in the underface of wing axle, and the line
It is parallel with wing axle.The Plane of rotation of the Plane of rotation of outer rotor and interior rotor is coplanar.The Plane of rotation of interior rotor slightly forward downward
Tilt, the angle of the Plane of rotation of interior rotor and the forward downward of horizontal plane is not more than 6 °.Rear plastic deflects down maximum angular
The beeline of its trailing edge to the Plane of rotation of interior rotor is more than 12mm when spending.The chord length of rear plastic is equal to or slightly less than inward turning
The radius of turn of the wing.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 is more than
Twice of the diameter of interior rotor.
A kind of operation principle of the compound aircraft with empennage of the invention is：Such as by the rear plastic of left composite wing and
The rear plastic of right composite wing all deflects down, and starts all engines, respectively rotor wing rotation corresponding to driving, described to fly
Row device can realize takeoff；Such as the rear plastic of left composite wing and the rear plastic of right composite wing are all deflected upward into
Extreme higher position, the aircraft can be realized and taken off vertically.Adjust the rear plastic of left composite wing and the rear portion of right composite wing
The deflection angle of fin and direction can change aerodynamic direction and size caused by the aircraft, by adjusting each rotor
Rotating speed can also change aerodynamic size and Orientation of the aircraft.The pitching of the aircraft is controlled by empennage
And course.Compare with traditional aircraft, the landing site of the compound aircraft requirements of the invention with empennage is little, and can be vertical
Lifting.Compared with traditional helicopter, the compound aircraft of the invention with empennage is due to left composite wing and right composite wing
Presence, lift caused by the aircraft is larger, if running out of steam the longer distance that can also glide, can strive for more
Time carrys out maintenance of equipment or finds safe landing point, so relatively safer；Even if vertically decline the flight because power loses
The decrease speed of device also will 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 is simple；It can improve fin upper and lower surface because all rotors are all in the lower section of fin, during rotor rotational
Flow field, increase downwash flow, delay fin upper surface air-flow separation, improve efficiency, greatly increase lift coefficient.
Brief description of the drawings
Fig. 1 is a kind of left view schematic diagram of the compound aircraft with empennage of the present invention, and Fig. 2 is Fig. 1 schematic top plan view；
Fig. 3 is the left view schematic diagram for the left composite wing being exaggerated, and 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- empennages, 41- tailplanes, 42- vertical tails,
5- undercarriages；Belonging to the component of left composite wing 2 includes：21- front flaps, 22- rear plastics, 23- wing axles, 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 with empennage, including fuselage 1, a left side
Composite wing 2, right composite wing 3, empennage 4 and undercarriage 5.It is furnished with control system and airborne equipment in fuselage 1.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.Empennage 4 is located at the afterbody of fuselage 1, tail
The wing 4 includes tailplane 41 and vertical tail 42.Tailplane 41 includes leading portion fixed part and back segment movable part, vertical end
The back segment of the wing 42 can deflection.Tailplane 41 plays horizontal stabilizer and elevator, and vertical tail 42 plays vertical peace
Determine the effect of face and rudder.Undercarriage 5 uses wheeled construction.The structure of left composite wing 2 is：Before left composite wing 2 includes
Portion's fin 21, rear plastic 22, wing axle 23, outer rotor 24, interior rotor 25, outer engine 26, intrinsic motivation 27 and support 28.Before
Portion's fin 21 is fixed on the left side of fuselage 1.The transverse horizontal of wing axle 23 arranges that the left end of wing axle 23 is connected with front flaps 21, the wing
The right-hand member of axle 23 is fixed on the fuselage 1, and wing axle 23 is placed at the trailing edge of front flaps 21.The leading edge of front flaps 21 is higher than front portion
The trailing edge of fin 21, the angle of front flaps 21 and horizontal plane is 12 °.The front end of rear plastic 22 is connected with wing axle 23, rear portion
Fin 22 can deflect around wing axle about 23.For relative level, the maximum angle that rear plastic 22 upward deflects is 15 °, after
The maximum angle that portion's fin 22 deflects down is 12 °.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 and the diameter of interior rotor 25 are equal.Outer rotor 24 and interior rotor 25 turn to conversely.Outer engine 26 and interior
Engine 27 is separately mounted to the top of outer rotor 24 and interior rotor 25 by support 28, outer engine 26 and intrinsic motivation 27
Axle shaft is connected with outer rotor 24 and interior rotor 25 respectively.The company of the pivot of interior rotor 25 and the pivot of outer rotor 24
Line is in the underface of wing axle 23, and the line is parallel with wing axle 23.The rotation of the Plane of rotation and interior rotor 25 of outer rotor 24
Co-planar.The Plane of rotation of interior rotor 25 slightly forward downward tilts, the Plane of rotation of interior rotor 25 and horizontal plane to front lower
The angle of side is 4 °.Beeline of its trailing edge to the Plane of rotation of interior rotor 25 when rear plastic 21 deflects down maximum angle
More than 12mm.The chord length of rear plastic 21 is slightly smaller than the radius of turn of interior rotor 25.The chord length of front flaps 21 is slightly larger than inward turning
The radius of turn of the wing 25.The length of left composite wing 2 is more than twice of the diameter of interior rotor 25.
Compound aircraft of the invention with empennage is such generation beneficial effect：Such as by the rear portion of left composite wing 2
The rear plastic of fin 22 and right composite wing 3 all deflects down, and starts all engines, rotor rotation corresponding to driving respectively
Turn, the aircraft can realize takeoff；Such as by the rear plastic 22 of left composite wing 2 and the rear portion wing of the wing of right compounding machine 3
Piece all deflects upward into extreme higher position, and the aircraft can be realized and taken off vertically.Adjust the He of rear plastic 22 of left composite wing 2
The deflection angle of the rear plastic of right composite wing 3 and direction can change aerodynamic direction caused by the aircraft and big
Small, the rotating speed by adjusting each rotor can also change aerodynamic size and Orientation of the aircraft.Controlled by empennage 4
Make pitching and the course of the aircraft.Compare with traditional aircraft, the compound aircraft requirements of the invention with empennage rise
It is little to drop place, and can be vertically moved up or down.Compared with traditional helicopter, the compound aircraft of the invention with empennage is multiple due to a left side
Close the presence of wing 2 and right composite wing 3, lift caused by the aircraft 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；Because power loses
Also will not be too fast even if the decrease speed for vertically declining the aircraft, it is relatively safe.Due to interior rotor 25 and outer rotor 24
Turn on the contrary, rotating torque can be offset, flight stability and control is simple；Because all rotors are all in the lower section of fin, rotor
The flow field of fin upper and lower surface can be improved during rotation, increase downwash flow, delay the air-flow separation of the upper surface of fin, improve effect
Rate, greatly increase lift coefficient.
Claims (3)
- A kind of 1. compound aircraft with empennage, it is characterised in that：Including fuselage（1）, left composite wing（2）, right compounding machine The 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）Answered with the right side Close wing（3）Structure is identical, and they are symmetrically arranged on fuselage（1）The left and right sides；Empennage（4）Positioned at fuselage（1）Afterbody, tail The wing（4）Including tailplane（41）And vertical tail（42）；Undercarriage（5）Using wheeled construction；Left composite wing（2）Structure It is：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） Transverse horizontal arrangement, wing axle（23）Left end and front flaps（21）It is connected, 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）Leading edge be higher than front flaps（21）Trailing edge, it is preceding Portion's fin（21）Angle with horizontal plane is between 4 ° -15 °；Rear plastic（22）Front end and wing axle（23）It is connected, the rear portion wing Piece（22）Can be around wing axle（23）Deflection up and down；For relative level, rear plastic（22）The maximum angle upward deflected does not surpass 20 ° are crossed, rear plastic（22）The maximum angle deflected down is no more than 15 °；Interior rotor（25）Close to fuselage（1）Install and outward turning The wing（24）Away from fuselage（1）Installation；Outer rotor（24）Diameter and interior rotor（25）Diameter it is equal；Outer rotor（24）And inward turning The wing（25）Turn to opposite；Outer engine（26）And intrinsic motivation（27）Pass through support（28）It is separately mounted to outer rotor（24）With it is interior Rotor（25）Top, outer engine（26）And intrinsic motivation（27）Output shaft respectively with outer rotor（24）With interior rotor（25） It is connected；Interior rotor（25）With outer rotor（24）Turn to opposite；Interior rotor（25）Pivot and outer rotor（24）Rotation in The line of the heart is in wing axle（23）Underface, 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 tilt, interior rotor（25）Rotary flat The angle of the forward downward of face and horizontal plane is not more than 6 °；Rear plastic（22 ）Its trailing edge is in when deflecting down maximum angle Rotor（25）The beeline of Plane of rotation be more than 12mm；Rear plastic（22 ）Chord length be equal to or slightly less than in 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）Twice of diameter；For relative level, rear plastic（22）The maximum upward deflected Angle is 15 °, rear plastic（22）The maximum angle deflected down is 12 °；Left composite wing（2）Rear plastic（22）And the right side Composite wing（3）Rear plastic all deflect upward into extreme higher position, the aircraft, which is realized, to take off vertically；Adjust left compounding machine The wing（2）Rear plastic（22）With right composite wing（3）Rear plastic deflection angle and direction change aircraft production Raw aerodynamic direction and size.
- A kind of 2. compound aircraft with empennage according to claim 1, it is characterised in that：Front flaps（21）With water The angle of plane is 12 °.
- A kind of 3. compound aircraft with empennage according to claim 1 or 2, it is characterised in that：Rear plastic（22 ） Chord length slightly smaller than in rotor（25）Radius of turn；Front flaps（21）Chord length be slightly larger than interior rotor（25）Rotation half Footpath.
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 CN105197234A (en) | 2015-12-30 |
| CN105197234B true CN105197234B (en) | 2017-12-01 |
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ID=54945302
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 |
|---|---|
| CN (1) | CN105197234B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN109987222B (en) * | 2018-01-02 | 2022-06-24 | 上海峰飞航空科技有限公司 | Unmanned aerial vehicle, power transmission system and method for reducing air resistance in unmanned aerial vehicle |
| DE102019107593A1 (en) * | 2019-03-25 | 2020-10-01 | LIFT Holding GmbH | Flying device |
Family Cites Families (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 |
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2015
- 2015-10-30 CN CN201510721341.2A patent/CN105197234B/en active Active
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| Publication number | Publication date |
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| CN105197234A (en) | 2015-12-30 |
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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 |