CN105923154A - Longitudinal column type double-rotor-wing fixed wing combined vertical take-off and landing aircraft - Google Patents
Longitudinal column type double-rotor-wing fixed wing combined vertical take-off and landing aircraft Download PDFInfo
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- CN105923154A CN105923154A CN201610380326.0A CN201610380326A CN105923154A CN 105923154 A CN105923154 A CN 105923154A CN 201610380326 A CN201610380326 A CN 201610380326A CN 105923154 A CN105923154 A CN 105923154A
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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
- B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
-
- 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
- B64C29/02—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded
Abstract
The invention discloses a longitudinal column type double-rotor-wing fixed wing combined vertical take-off and landing aircraft and belongs to the technical field of design of aviation aircrafts. The aircraft is composed of two special-shaped rotor wings, fixed wings, two vector propellers, an aircraft body, a vertical tail wing and horizontal tail wings. The two special-shaped rotor wings are located above the head of the aircraft body and above the vertical tail wing correspondingly. The diameters of the two special-shaped rotor wings are equal. The fixed wings are located between projections of the two special-shaped rotor wings in the horizontal plane. The two vector propellers are located on the rear edges of the fixed wings correspondingly and can deflect upwards or downwards by 20 degrees in the axis direction of the vector propellers. The aircraft has the capability of vertical taking off/landing and high-speed flat flight and can conduct switching to two modes in the air. Compared with conventional helicopters, the flat flight speed, the air range and the endurance of the aircraft are increased by about 50%, and the aircraft has wider operating range and higher operating capability and can replace helicopters in the future.
Description
Technical field
The present invention proposes the new ideas vertically taking off and landing flyer that a kind of lap siding DCB Specimen is compound with fixed-wing, has the vertical of excellence concurrently
Landing and high speed are put down and are flown performance, belong to aviation aircraft design field.
Background technology
Pure helicopter, asymmetric owing to front flying the air-flow of rotor under working environment so that the front maximal rate that flies is by advancing blade
The restriction that comperssibility influence and retreating blade air-flow separate, maximum cruise is generally at about 300km/h；Fixed wing airplane is then
Hovering and low-speed operations cannot be completed.And composite helicopter combines the flight characteristic of helicopter and fixed wing airplane, thus hold concurrently
Both abilities of tool, its application prospect is the broadest, and economic outlook is good.The vertically taking off and landing flyer of external existing maturation, such as
V-22 osprey formula tiltrotor, X-50A based on stall rotor technology " Aeschna melanictera ", combine helicopter and fixed wing airplane
Advantage, has VTOL concurrently and high speed is put down and flown performance.
A kind of new vertical landing new ideas are to be combined with fixed-wing by rotor, and its state of flight is changed by following components
Composition: when taking off, similar to pure helicopter, rotor the lift produced takes off vertically；After arriving certain altitude, gradually
Fly the thrust of propulsion plant before increase, make aircraft obtain certain horizontal velocity, reduce rotor rotating speed simultaneously；Work as level speed
When increasing to make fixed-wing face produce enough lift, rotor rotating speed is reduced to zero, simultaneously rotor and fixed-wing keeping parallelism,
Form class double-vane layout.Current the hybrid helicopter provided of this layout has been successfully realized flight, tentatively achieves VTOL
Flight, high-speed horizontal flight and switch transition flight, have preferable effect.
At present ripe vertically taking off and landing flyer, has a following deficiency:
1, vertically taking off and landing flyer conversion and control based on tilting rotor technology is complicated.
2, vertically taking off and landing flyer rotor based on stall rotor technology flies to be main load parts under pattern flat, and rotor is general
Aspect ratio is relatively big, and the fixing aerofoil that overall structure rigidity is more general is low, is susceptible to the pneumatic bombs such as tremor when flight speed is very fast
Sex chromosome mosaicism, is unfavorable for high-speed flight.
Based on case above, it is necessary to study a kind of novel rotor fixed-wing combined type aircraft, it is possible to overcome disadvantages mentioned above.
Summary of the invention
In order to solve problems of the prior art, the present invention provides a kind of and has that VTOL performance and stable high speed are flat to fly concurrently
The aircraft lap siding DCB Specimen fixed-wing combined type vertically taking off and landing flyer of performance.Described aircraft by two special type rotors,
One fixed-wing, two vectors advance oar, fuselage, vertical tail and tailplane composition.Two special type rotors of aircraft,
Becoming lap siding to be arranged in above head upper and vertical tail, fixed-wing is positioned at waist, and two vectors advance oar one the first from left right
It is positioned at fixed-wing trailing edge, and is arranged symmetrically with relative to fuselage.During aircraft vertical takeoff and landing, two special types
Rotor reversely rotates provides upwards lift counter balance torque simultaneously；After aircraft reach a certain height, vector advances oar to start working,
Producing horizontal thrust, make aircraft produce level speed and be gradually increased, after putting down and flying up to certain speed, special type rotor slows down
Rotating until stopping, being locked to subsequently be parallel to fixed-wing, now special type rotor is changed into fixing aerofoil and provides a small amount of lift,
Fixed-wing provides the prevailing lift of full machine, and vector advances oar to provide horizontal thrust, makes aircraft realize the most flat flying.
It is an advantage of the current invention that:
(1) can realize taking off vertically/landing rapidly, landing site is required relatively low；
(2) at a high speed flat can be realized to fly, when there is bigger voyage and boat；
(3) there is the ability that fly flat with high speed that take off vertically/land simultaneously, and can aloft carry out the conversion of both patterns.
(4) special type rotor is similar to the rotor of pure helicopter, has identical flight efficiency, and VTOL flying quality and low speed fly
Row performance is all close with pure helicopter, and level speed, voyage with will compare during boat pure helicopter improve about 50%, have
Bigger job area and higher performance capacity, can replace helicopter in the future.
(5) fixed-wing of this aircraft is all the most similar to the wing of conventional fixed-wing aircraft and empennage with empennage, has identical work former
Reason, version and pneumatic efficiency so that the flat performance that flies of this aircraft is close with conventional fixed-wing aircraft, and fixes with routine
Wing aircraft is compared, and has the ability of vertical and landing takeoff and low-speed operations, is more suitable for field usage and low-altitude low-speed operation.
(6) the special type rotor of this aircraft, fixed-wing, empennage and vector advance oar independently to control, and between interference less,
The peaceful pattern that flies of VTOL pattern can aloft realize stable switch transition, compares tail sitting posture vertically taking off and landing flyer, verts
Gyroplane, tilting wing formula vertically taking off and landing flyer etc. have higher safety and comfortableness.
(7) use lap siding DCB Specimen ensure that aircraft can VTOL under high load-carrying, and without tail-rotor counter balance torque.
(8) vector is used to advance oar to provide aircraft the flat power that flies so that aircraft is achieved the most flat flying.
(9) vector advances oar to use vector to advance, and can produce thrust simultaneously and control the effect of aspect.
Accompanying drawing explanation
The structural representation of the lap siding DCB Specimen fixed-wing combined type vertically taking off and landing flyer that Fig. 1 provides for the present invention.
In figure:
1. special type rotor；2. fuselage；3. fixed-wing；4. vector advances oar；5. vertical tail；6. tailplane.
Detailed description of the invention
The present invention is described in detail with embodiment below in conjunction with the accompanying drawings.
The present invention provides a kind of lap siding DCB Specimen fixed-wing combined type vertically taking off and landing flyer, has VTOL concurrently and high speed is put down and flown
Performance.As it is shown in figure 1, described aircraft layout includes that two special type rotors 1, fuselage 2,3, two vectors of fixed-wing push away
Enter oar 4, vertical tail 5 and tailplane 6.Described special type rotor 1 has two, lays respectively at the top of the head of fuselage 2
With the top of vertical tail 5, both equal diameters.Fixed-wing 3 is positioned at the middle part of fuselage 2, is positioned at two special type rotors 1
Between the projection of horizontal plane, it is to avoid aerodynamic interference when working with special type rotor 1, i.e. fixed-wing 3 wing root leading edge point is to machine
The distance of one special type rotor 1 center of rotation of body head is equal to the radius of special type rotor 1, and the trailing edge of fixed-wing 3 is to afterbody
The distance of one special type rotor 1 center of rotation is equal to the radius of turn of special type rotor 1.Two blades of described special type rotor 1
Flat shape is isosceles trapezoid, and length of blade is 6-10 with the ratio of mean breadth, compares pure helicopter rotor blade (length and width
Than 15-20) wider, taper ratio about 0.6, symmetrical before and after selecting relative thickness 8%-12%, upper lower curve to be all elliptic curve
Aerofoil profile.Described fixed-wing 3 and fuselage 2 consolidation and the centre position of fuselage 2, the area of fixed-wing 3 is that special type rotor 1 revolves
Turn the 20%-25% of state rotor disk area, the aspect ratio of fixed-wing 3 about 13-17, select the promotion resistance of relative thickness 10%-15%
Compare aerofoil profile.The length of described fuselage 2 is about 1.5 times of special type rotor 1 diameter.Described vertical tail 5 is arranged in fuselage 2 tail
The top in portion, area is about the 10%-15% of fixed-wing 3 area, and tailplane 6 is arranged in the lower section of fuselage 2 afterbody, area
For the 15%-20% of the area of fixed-wing 3, aspect ratio is about 5-8, vertical tail 5 and tailplane 6 and all selects relative thickness
The aerofoil profile symmetrical above and below of 8%-12%.Described vector advance oar 4 have two, lay respectively at the trailing edge of fixed-wing 3, both relative to
Fuselage 2 is arranged symmetrically with, and spacing is 0.8-1 times of the diameter of special type rotor 1, and vector propelling oar 4 axis direction can be up or down
Deflect 20 degree, can produce horizontal thrust and must thrust up or down, both sides the most reversely deflection just can provide rolling
Turning control moment, the thrust controlling both sides is unequal, can produce yawing.
The mode of operation of the aircraft that the present invention provides is divided into VTOL pattern to fly pattern with the most flat, in VTOL pattern,
Two special type rotors 1 work, it is provided that the lift of aircraft and control power, make the aircraft can be with vertical and landing takeoff.Put down and fly mould
During formula, two special type rotor 1 stalls locking is parallel to fixed-wing 3, is changed into fixing aerofoil, now the prevailing lift of aircraft by
Fixed-wing 3 provides, and special type rotor 1 provides a small amount of lift, vertical tail 5 and tailplane 6 to balance the moment of torsion of pitching and driftage,
Vector advances oar 4 high speed rotating to provide horizontal thrust forward, can provide rolling by adjusting thrust direction for aircraft simultaneously
Control moment so that aircraft does the most flat flying.By VTOL patten transformation to flat fly pattern during, first vector
Advancing oar 4 to start to rotate and provide thrust, and be gradually increased rotating speed and thrust makes aircraft level accelerate, fixed-wing 3 starts subsequently
Produce lift, and gradually provide prevailing lift, special type rotor 1 to reduce speed now rotation final stall locking.Pattern is being flown by flat
Being transformed in VTOL mode process, first aircraft down flight, special type rotor 1 unlocks and starts to rotate, and lift is gradually
Increasing, level speed provides whole lift when reducing to zero afterwards, and vector advances oar 4 gradually to slow down and quits work.
Claims (5)
1. lap siding DCB Specimen fixed-wing combined type vertically taking off and landing flyer, including fuselage, fixed-wing, vertical tail and tailplane,
It is characterized in that: also include that two vectors advance oar and two special type rotors；
Two described special type rotors lay respectively at top and the top of vertical tail, both equal diameters of the head of fuselage；Fixing
The wing is at two special type rotors between the projection of horizontal plane, and fixed-wing wing root leading edge point is to one special type rotor wing rotation of fuselage head
The distance at center is equal to the radius of special type rotor, and the trailing edge of fixed-wing is to the distance etc. at one special type rotor wing rotation center of afterbody
Radius of turn in special type rotor；Said two vector advances oar to lay respectively at the trailing edge of fixed-wing, and both are symmetrical relative to fuselage
Arranging, spacing is 0.8-1 times of the diameter of special type rotor, and vector advances oar axis direction can deflect 20 degree up or down.
Lap siding DCB Specimen fixed-wing combined type vertically taking off and landing flyer the most according to claim 1, it is characterised in that: described spy
The flat shape of two blades of type rotor is isosceles trapezoid, and length of blade is 6-10 with the ratio of mean breadth, taper ratio 0.6,
Aerofoil profile symmetrical before and after selecting relative thickness 8%-12%, upper lower curve to be all elliptic curve.
Lap siding DCB Specimen fixed-wing combined type vertically taking off and landing flyer the most according to claim 1, it is characterised in that: described solid
Determining the 20%-25% that area is special type rotor wing rotation state rotor disk area of the wing, the aspect ratio of fixed-wing is 13-17, selects relatively
The airfoil with high ratio of lift over drag of thickness 10%-15%.
Lap siding DCB Specimen fixed-wing combined type vertically taking off and landing flyer the most according to claim 1, it is characterised in that: described machine
1.5 times of a length of special type rotor diameter of body.
Lap siding DCB Specimen fixed-wing combined type vertically taking off and landing flyer the most according to claim 1, it is characterised in that: described vertical
Fin area is the 10%-15% of fixed-wing area, and tailplane area is the 15%-20% of the area of fixed-wing, and aspect ratio is
5-8, vertical tail and tailplane all select the aerofoil profile symmetrical above and below of relative thickness 8%-12%.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610380326.0A CN105923154B (en) | 2016-06-01 | 2016-06-01 | Lap siding DCB Specimen fixed-wing combined type vertically taking off and landing flyer |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610380326.0A CN105923154B (en) | 2016-06-01 | 2016-06-01 | Lap siding DCB Specimen fixed-wing combined type vertically taking off and landing flyer |
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| Publication Number | Publication Date |
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| CN105923154A true CN105923154A (en) | 2016-09-07 |
| CN105923154B CN105923154B (en) | 2019-03-12 |
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| CN201610380326.0A Active CN105923154B (en) | 2016-06-01 | 2016-06-01 | Lap siding DCB Specimen fixed-wing combined type vertically taking off and landing flyer |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108045572A (en) * | 2017-12-03 | 2018-05-18 | 中国直升机设计研究所 | A kind of compound thrust high-speed helicopter of cross-arranging type |
| CN108572655A (en) * | 2018-04-25 | 2018-09-25 | 重庆市亿飞智联科技有限公司 | flight control method and related device |
| CN108845581A (en) * | 2018-06-12 | 2018-11-20 | 中国科学院工程热物理研究所 | The compound multi-modal flight control method of quadrotor drone |
| CN111348183A (en) * | 2018-12-20 | 2020-06-30 | 沃科波特有限公司 | Aircraft with a flight control device |
| WO2020250029A1 (en) | 2019-06-12 | 2020-12-17 | Chong Qing Liang Jiang Aircrraft Design Institute Ltd. | Method and convertible vtol or evtol aircraft for transition from helicopter mode to gyroplane mode and vice versa |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108045572A (en) * | 2017-12-03 | 2018-05-18 | 中国直升机设计研究所 | A kind of compound thrust high-speed helicopter of cross-arranging type |
| CN108572655A (en) * | 2018-04-25 | 2018-09-25 | 重庆市亿飞智联科技有限公司 | flight control method and related device |
| CN108845581A (en) * | 2018-06-12 | 2018-11-20 | 中国科学院工程热物理研究所 | The compound multi-modal flight control method of quadrotor drone |
| CN111348183A (en) * | 2018-12-20 | 2020-06-30 | 沃科波特有限公司 | Aircraft with a flight control device |
| CN111348183B (en) * | 2018-12-20 | 2023-12-05 | 沃科波特有限公司 | Aircraft with a plurality of aircraft body |
| WO2020250029A1 (en) | 2019-06-12 | 2020-12-17 | Chong Qing Liang Jiang Aircrraft Design Institute Ltd. | Method and convertible vtol or evtol aircraft for transition from helicopter mode to gyroplane mode and vice versa |
| WO2020250010A1 (en) | 2019-06-12 | 2020-12-17 | Chong Qing Liang Jiang Aircraft Design Institute Ltd. | Operating method for a convertible uav |
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| Publication number | Publication date |
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| CN105923154B (en) | 2019-03-12 |
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