CN106043685B - Double vectors promote paddle rotor/fixed-wing combined type vertically taking off and landing flyer - Google Patents
Double vectors promote paddle rotor/fixed-wing combined type vertically taking off and landing flyer Download PDFInfo
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- CN106043685B CN106043685B CN201610380319.0A CN201610380319A CN106043685B CN 106043685 B CN106043685 B CN 106043685B CN 201610380319 A CN201610380319 A CN 201610380319A CN 106043685 B CN106043685 B CN 106043685B
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- wing
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- type rotor
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/24—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with rotor blades fixed in flight to act as lifting surfaces
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
Abstract
The invention discloses a kind of double vectors to promote paddle rotor/fixed-wing combined type vertically taking off and landing flyer, belongs to aviation aircraft design field.The aircraft promotes paddle, fuselage and empennage to form by special type rotor, wing, vector.During VTOL, prevailing lift is provided by special type rotor, two vectors on empennage promote paddle thrust direction to distinguish horizontal direction from left to right, and it is anti-twisted to balance special type rotor to provide lateral thrust.During by VTOL pattern switch transition to flat winged pattern, two vectors promote paddle 90 degree of horizontal deflection backward, generate forward thrust, lift is gradually provided by wing.There is the present invention landing of taking off vertically to equal winged ability with high speed simultaneously, and can carry out the conversion of both patterns in the air；Level speed, voyage and endurance will compare pure helicopter and improve about 50%, and the job area with bigger and higher work capacity can replace helicopter in the future.
Description
Technical field
The present invention relates to a kind of double vectors to promote paddle rotor/fixed-wing combined type vertically taking off and landing flyer, both have with
The same VTOL of helicopter and hovering ability, but can as fixed wing aircraft high speed cruise flight, belong to aviation
Technical field of aircraft design.
Background technology
The outstanding feature of helicopter is can to do low latitude (from the ground several meters), low speed (since hovering) and head side at present
It, especially can be in the VTOL of small area place to constant maneuvering flight.But there are Speed Obstacles for helicopter, cannot achieve height
Speed flight.
And to make aircraft that can obtain rotor craft distinctive in low-altitude low-speed for combined type vertically taking off and landing flyer layout
Under the conditions of flexible flight and VTOL, hovering, it is rear fly, the excellent properties that side is winged, but also with Fixed Wing AirVehicle
High-altitude, high speed, efficiently, the advantages that combat radius is big.It is this to design the flying quality for not only having merged two kinds of variety classes aircrafts,
Respective flight envelope is improved, but also there is lower signal characteristic value and good high-speed flight survivability.So phase
Compare pure helicopter, it is necessary to invent a kind of novel combined type vertically taking off and landing flyer layout.
Ripe vertically taking off and landing flyer at present, has the following deficiencies：
1, the vertically taking off and landing flyer conversion and control based on tilting rotor technology is complicated.
2, the vertically taking off and landing flyer rotor based on stalling rotor technology is main load component under flat winged pattern, and is revolved
The general aspect ratio of the wing is larger, and the more general fixed aerofoil of overall structure rigidity is low, and flutter is easy to happen when flying speed is very fast
Equal Aeroelastic Problems, are unfavorable for high-speed flight.
Invention content
In order to solve the problems in the existing technology, it is multiple to provide a kind of double vector propulsion paddle rotor/fixed-wings by the present invention
Box-like vertically taking off and landing flyer, the aircraft mainly promote paddle, fuselage and empennage to form by special type rotor, wing, vector.
During VTOL, prevailing lift is provided by special type rotor, two vectors on empennage promote paddle thrust direction horizontal respectively
To from left to right, it is anti-twisted to balance special type rotor to provide lateral thrust.By VTOL pattern switch transition to the mistake of flat winged pattern
Cheng Zhong, two vectors promote paddles 90 degree of horizontal deflection backward, generate forward thrust, aircraft ramp up it is flat winged, lift by
It is gradually provided by wing, special type rotor, which tapers off, to be rotated and be locked in designated position, parallel with fixed-wing, forms double-vane layout.
The advantage of the invention is that：
(1) rapidly vertical and landing takeoff may be implemented, landing site is required relatively low.
(2) the flat of high speed may be implemented to fly, there is larger voyage and endurance.
(3) while there is landing of taking off vertically to equal winged ability with high speed, and both patterns can be carried out in the air
Conversion.
(4) special type rotor is similar to the rotor of pure helicopter, flight efficiency having the same, VTOL flying quality
It is close with pure helicopter with low-speed operations performance, and level speed, voyage will compare pure helicopter with endurance and improve about
50%, there is the job area of bigger and higher work capacity, helicopter can be replaced in the future.
(5) wing of the aircraft and empennage are similar to the wing of conventional fixed-wing aircraft and empennage, which exists
With conventional fixed-wing aircraft flight efficiency having the same when flat winged pattern, flat winged performance is close with conventional fixed-wing aircraft, and
The ability then compared with conventional fixed-wing aircraft with take off vertically landing and low-speed operations is more suitable for field use and low latitude
Low speed operation.
(6) the special type rotor of the aircraft, wing, empennage and vector promote paddle can independent control, and it is mutual
Interference is smaller, and VTOL pattern peace flies pattern can realize stable switch transition in the air, compares tail sitting posture VTOL
Aircraft, tiltrotor, tilting wing formula vertically taking off and landing flyer etc. have higher safety and comfort.
Description of the drawings
Fig. 1 is that double vectors under VTOL pattern promote paddle rotor/fixed-wing combined type vertically taking off and landing flyer.
Fig. 2 is that double vectors under flat winged pattern promote paddle rotor/fixed-wing combined type vertically taking off and landing flyer.
In figure：
1. special type rotor；2. wing；3. vector promotes paddle；4. fuselage；5. empennage.
Specific implementation mode
The present invention is described in detail with reference to the accompanying drawings and examples.
The present invention provides a kind of double vector propulsion paddle rotor/fixed-wing combined type vertically taking off and landing flyer, as shown in Figure 1,
The aircraft includes special type rotor 1, wing 2, vector propulsion paddle 3, fuselage 4 and empennage 5.The special type rotor 1 is located at machine
The top at about 40% length from front to back of body 4, the flat shape of blade is isosceles trapezoid, length of blade and mean width ratio
Wider compared to pure helicopter rotor blade (length-width ratio 15-20) for 6-10, taper ratio about 0.6 selects relative thickness 8%-
12%, upper lower curve is all the front and back symmetrical aerofoil profile of elliptic curve.The wing 2 is located at 4 junction of fuselage below fuselage,
The geometric center of wing 2 is overlapped with the center of special type rotor 1, and the area of wing 2 is 1 rotation status rotor disk area of special type rotor
20%-25%, the aspect ratio about 13-17 of wing 2 select the airfoil with high ratio of lift over drag of relative thickness 10%-15%.The empennage 5
Positioned at 4 tail portion of fuselage, the distance of 5 leading edge root of empennage to 1 center of special type rotor is equal to the radius of special type rotor 1,5 area of empennage
For the 15%-20% of the area of wing 2, aspect ratio is about 5-8, selects the aerofoil profile symmetrical above and below of relative thickness 8%-12%.Institute
It states vector to promote there are two paddles 3, be separately positioned at the rear of the left and right ends of empennage 5, vector promotes paddle 3 can horizontal deflection 90
Degree, in VTOL pattern, two vectors promote the thrust direction of paddle 3 respectively to the left and to the right, VTOL pattern with
During flat winged pattern switch transition, two vectors promote paddle 3 simultaneously to 90 degree of post deflection, and two vectors promote when equalling winged pattern
The direction of paddle 3 backward, generates forward thrust.Special type rotor 1 and vector promote paddle 3 by the dynamical system inside fuselage 4
Driving.
When aircraft vertical takes off, dynamical system drives special type rotor 1 to rotate and provides lift, and aircraft is lifted support in sky
In, also output power to vector promotes paddle 3 to dynamical system simultaneously, by adjusting two vectors propulsion paddles 3 pushing away to the left and to the right
Power size can offset the reaction force under the different rotating speeds of the generation of special type rotor 1, and generate yaw control moment.Such as Fig. 2 institutes
Show, after reaching certain altitude, when aircraft by VTOL pattern switch transition to flat winged mode flight when, vector propulsion paddle 3
Paddle shaft be rotated by 90 ° backward in fuselage plane, generate forward thrust, and increase thrust, be gradually increased level speed, wing
2 provide prevailing lift, are 1 off-load of special type rotor, and 1 rotating speed of special type rotor continuously decreases at this time, can make when level speed increases to
When wing 2 generates enough lift, 1 rotating speed of special type rotor is reduced to zero, stops operating and is locked in and 2 keeping parallelism of wing
Position, whole airplane, which is laid out to put down forward in double-vane, to fly, to realize the steady switching of two kinds of offline mode.It is flat winged-vertical when carrying out
When straight landing switch transition flight, special type rotor 1 unlocks, and rotating speed is gradually increased, and increases upward pulling force, while vector pushes away
It turn 90 degrees and is gradually reduced thrust partially to both sides respectively into paddle 3, the generation of special type rotor 1 can be finally completely counterbalanced by by adjusting thrust
Different rotating speeds under reaction force.Aircraft is transformed into VTOL pattern at this time, and realizes vertical landing.
Claims (1)
1. pair vector promotes paddle rotor/fixed-wing combined type vertically taking off and landing flyer, it is characterised in that：The aircraft is by special type
Rotor, wing, vector promote paddle, fuselage and empennage composition, during VTOL, lift, empennage are provided by special type rotor
On two vectors promote paddle thrust direction distinguish horizontal direction from left to right, it is anti-twisted to balance special type rotor to provide lateral thrust；By
During VTOL pattern switch transition to flat winged pattern, two vectors promote paddles 90 degree of horizontal deflection backward, generate to
Preceding thrust, aircraft, which ramps up to put down, to fly, and lift is gradually provided by wing, and special type rotor, which tapers off, to be rotated and be locked in finger
Positioning is set, parallel with fixed-wing, forms double-vane layout；
The special type rotor is located at top of the fuselage from front to back at 40% length, and the flat shape of blade is isosceles trapezoid,
Length of blade is 6-10 with mean width ratio, and taper ratio 0.6, it is all oval bent to select relative thickness 8%-12%, upper lower curve
The front and back symmetrical aerofoil profile of line；
The wing is located at fuselage junction below fuselage, and the geometric center of wing is overlapped with the center of special type rotor, wing
Area be special type rotor（1）The 20%-25% of rotation status rotor disk area, the aspect ratio 13-17 of wing select relative thickness
The airfoil with high ratio of lift over drag of 10%-15%；
The empennage is located at afterbody, and the distance of empennage leading edge root to special type rotor centers is equal to the radius of special type rotor,
Fin area is 15%-20%, the aspect ratio 5-8 of the area of wing, selects the wing symmetrical above and below of relative thickness 8%-12%
Type；
The vector promotes there are two paddles, is separately positioned at the rear of the left and right ends of empennage, and vector promotes paddle horizontal inclined
It turn 90 degrees, in VTOL pattern, two vectors promote the thrust direction of paddle respectively to the left and to the right, in VTOL mould
Formula is with during flat winged pattern switch transition, and two vectors promote paddle simultaneously to 90 degree of post deflection, two vectors when equalling winged pattern
The direction for promoting paddle backward, generates forward thrust.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610056129 | 2016-01-27 | ||
| CN2016100561293 | 2016-01-27 |
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| Publication Number | Publication Date |
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| CN106043685A CN106043685A (en) | 2016-10-26 |
| CN106043685B true CN106043685B (en) | 2018-09-11 |
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| CN201610380319.0A Active CN106043685B (en) | 2016-01-27 | 2016-06-01 | Double vectors promote paddle rotor/fixed-wing combined type vertically taking off and landing flyer |
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Families Citing this family (15)
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| US10464668B2 (en) | 2015-09-02 | 2019-11-05 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
| KR20180061182A (en) | 2015-09-02 | 2018-06-07 | 제톱테라 잉크. | Ejector and airfoil structure |
| US11001378B2 (en) | 2016-08-08 | 2021-05-11 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
| CN106807095A (en) * | 2017-03-23 | 2017-06-09 | 高桂霞 | A kind of cloudling offline mode signal switching apparatus |
| EP3645854A4 (en) | 2017-06-27 | 2021-03-24 | Jetoptera, Inc. | Configuration for vertical take-off and landing system for aerial vehicles |
| CN108327837A (en) * | 2018-04-28 | 2018-07-27 | 苏州智泉农业科技有限公司 | A kind of self-balancing two-wheeled agricultural vehicle |
| CN109050908A (en) * | 2018-08-24 | 2018-12-21 | 安徽云翼航空技术有限公司 | A kind of composite wing aviation aircraft and its flight control method |
| CN109815528A (en) * | 2018-12-13 | 2019-05-28 | 航天神舟飞行器有限公司 | A method of the aircraft parameters optimization based on large-scale composite wing gas |
| CN109823520A (en) * | 2019-02-26 | 2019-05-31 | 徐桂敏 | Aircraft and flight system |
| CN109911178A (en) * | 2019-03-13 | 2019-06-21 | 南京灵龙旋翼无人机系统研究院有限公司 | A kind of tail-rotor for rotary-wing aircraft and propulsion sharing system and control method |
| EP3757004B1 (en) * | 2019-06-27 | 2023-03-29 | Volocopter GmbH | Vtol aircraft with wing connecting booms |
| CN110481771A (en) * | 2019-09-26 | 2019-11-22 | 成都纵横大鹏无人机科技有限公司 | Can VTOL Fixed Wing AirVehicle and UAV system |
| CN110949662B (en) * | 2019-12-06 | 2023-04-18 | 江西洪都航空工业集团有限责任公司 | Novel concept layout airplane with double-wing configuration |
| CN114954932B (en) * | 2021-09-28 | 2023-09-26 | 熊磊 | Vertical take-off and landing aircraft based on variable-pitch wing technology and double-pitch wing layout |
| CN113753261B (en) * | 2021-11-09 | 2022-02-11 | 中国空气动力研究与发展中心低速空气动力研究所 | Wind tunnel test device and method for combined model of combined conventional rotor wing high-speed helicopter |
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| US7510139B2 (en) * | 2005-11-02 | 2009-03-31 | Walliser Eric W | Rotor wing aircraft having a bypassable radial inflow turbine |
| CN102632992A (en) * | 2012-03-28 | 2012-08-15 | 北京航空航天大学 | Single-power horizontal tractor type high-speed high-mobility helicopter |
| US9120567B2 (en) * | 2012-06-11 | 2015-09-01 | Sikorsky Aircraft Corporation | High speed compound rotary wing aircraft |
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