CN107161322A - One kind becomes sweepback STOL Fixed Wing AirVehicle - Google Patents
One kind becomes sweepback STOL Fixed Wing AirVehicle Download PDFInfo
- Publication number
- CN107161322A CN107161322A CN201710310246.2A CN201710310246A CN107161322A CN 107161322 A CN107161322 A CN 107161322A CN 201710310246 A CN201710310246 A CN 201710310246A CN 107161322 A CN107161322 A CN 107161322A
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- wing
- aircraft
- fuselage
- propeller
- stol
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/04—Arrangement or disposition on aircraft
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Tires In General (AREA)
- Toys (AREA)
Abstract
Become sweepback STOL Fixed Wing AirVehicle the invention discloses one kind, aircraft uses the Shuan Fa Flying-wings of blended wing-body low aspect ratio, respectively there is the corresponding major diameter propeller of an engine driving in fore-body both sides, complete machine most surfaces and the vertical fin of rear side and the control surface of elevon is set to be in high performance airscrew slip-stream, both sides wing synchronously can outwards deploy forward or backward to interior folding；When wing folds back, wing is fitted completely with fuselage, and the overall streamlined aerodynamic configuration in curved surface of aircraft, lifting area is big, reduces flight resistance.When wing is opened, aircraft span is greatly increased, and is greatly improved aircraft cruise economy.Using propeller, wing body lifting body, swing-wing reasonable cooperation, aircraft is possessed STOL, high maneuverability and high cruise economy ability.By optimizing to wing body joint, make wing aircraft under expansion and collapsed state that all there is less flight resistance.
Description
Technical field
The present invention relates to aviation aircraft design field, specifically, it is related to a kind of sweepback STOL fixed-wing that becomes and flies
Row device.
Background technology
Fixed Wing AirVehicle has been limited to need very big high-quality landing site, in order to weaken to landing site according to
Rely, World Developed Countries develop various VUAVs.
Double hair pancake shape aircraft can still keep larger lift coefficient under High Angle of Attack state and be unlikely to stall, institute
Taken off with the relatively High Angle of Attack posture that aircraft can be more than 20 degree, so that shorten the/landing distance that takes off, in-flight can be at 30 degree
Still not stall and controllable above.Even when aircraft thrust-weight ratio is more than 1, aircraft can realize VTOL and overhead suspension
Stop.Two engine spacing of double hair pancake shape aircraft are larger, and major diameter blade causes the most of wetted area of full machine in spiral shell
Revolve in oar slip-stream, when wing deploys, a part for wing is also in propellerslip.Using aircraft as when referring to, left side
Propeller rotate counterclockwise, right side propeller turns clockwise, and is just vortexed direction of rotation on the contrary, subtracting significantly with aircraft wingtips
Small induced drag caused by wingtip vortex.
In the prior art, pancake shape aircraft has less wing load, and the fuselage for adding whole pancake shape is all wrapped up
Propeller produce high speed slip-stream in, aircraft can with High Angle of Attack STOL, aircraft be also blended wing-body in other words
Flying-wing, greatly reduces flight resistance.Aerodynamic control surface on the vertical fin and horizontal tail of aircraft is all in engine prop
In high speed slip-stream, possess very high steerage, it is ensured that still have under the lower-speed state of aircraft handling well.
U.S. X-173 and its military version F-5U disclose a kind of double hair pancake shape Flight Vehicle Design schemes of typical case, this pair hair
The technical scheme that pancake shape aircraft is used is that main body includes two groups of major diameter four-blade propellers of engine driving of two stretchings；
The pancake shape fuselage of approximate trapezoid, the short and small fixed wing that fuselage afterbody stretches out to both sides, twin vertical fin.Its weak point is aircraft
Lift-drag ratio it is relatively low, cruise economy it is poor, the flight envelope of aircraft is narrower.
The content of the invention
In order to avoid the deficiency that prior art is present, the present invention proposes a kind of change sweepback STOL Fixed Wing AirVehicle.
The technical solution adopted for the present invention to solve the technical problems is:Including two propellers, two engines, wing bodies
Connection rotating shaft, fuselage, wing, main landing gear, elevon, vertical fin, using the Shuan Fa Flying-wings of low aspect ratio, two wings position
In fuselage outer side, and can around the synchronous expansion preceding laterally outwardly of wing body connection rotating shaft, or backward, inside fuselage side folds laminating, it is double vertical
Tail is located at rear portion on fuselage and is symmetrically installed, and elevon is arranged on back body and is located at two vertical fin rear portions, propeller and engine
Connection, engine is symmetrically mounted on fore-body two side ends, and both sides propeller is reversely rotated each other, makes fuselage surface and rear side
The control surface of vertical fin and elevon is in propellerslip, and main landing gear is located at fore-body, and afterbody is equipped with tail wheel.
Undercarriage is 3 points of arrangements, and main landing gear makes aircraft be more than 20 degree away from the angle of attack between ground under parked state.
Beneficial effect
Change sweepback STOL Fixed Wing AirVehicle proposed by the present invention, using the Shuan Fa Flying-wings of low aspect ratio；
Respectively there is the corresponding major diameter propeller of an engine driving fore-body both sides, make the vertical fin at complete machine most surfaces and rear portion
It is in the control surface of elevon in high performance airscrew slip-stream, both sides wing synchronously outwards can deploy forward, or inside backward
Fuselage side is folded；When wing folds back, wing is fitted completely with fuselage, and aircraft is integrally in curved surface streamlined pneumatic outer
Shape, lifting area is big, reduces flight resistance.When wing is opened, aircraft span is greatly increased, and makes aircraft cruise economy
It is greatly improved.Using propeller, wing body lifting body, swing-wing reasonable cooperation, make aircraft possess STOL,
High maneuverability and high cruise economy ability.By optimizing to wing body joint, wing is set to be flown under expansion and collapsed state
Device all has less flight resistance.
Become sweepback STOL Fixed Wing AirVehicle and use pancake shape structure fuselage, realize that High Angle of Attack state is taken off landing,
Each rudder face is in propeller high speed slip-stream, aircraft is still had good navigability under the low speed, is greatly shortened and take off
Landing landing airdrome length used, reduces the requirement to landing site, improves aircraft flight flexibility.
Become sweepback STOL Fixed Wing AirVehicle to complete after short takeoff, can fly in high-speed flight and efficiently two kinds of cruise
Switched under row state；After wing deploys, the resistance of aircraft increases small value, but its lift-drag ratio is greatly promoted, and flies
The cruise economy of device is improved, and is made aircraft while possessing flying speed, voyage and endurance, is more applicable for reality
Task needs.
Become sweepback STOL Fixed Wing AirVehicle to fit completely with fuselage before wing expansion, it is ensured that aircraft entirety
Streamline aerodynamic configuration；After wing expansion, fuselage and wing division section still ensure that fuselage is a streamlined lifting body, i.e. wing
The resistance for deploying and packing up two states is varied less.
Brief description of the drawings
Further is made to a kind of sweepback STOL Fixed Wing AirVehicle that becomes of the invention with embodiment below in conjunction with the accompanying drawings
Describe in detail.
Fig. 1 becomes sweepback STOL Fixed Wing AirVehicle wing for the present invention and packs up rear axle mapping entirely.
Fig. 2 a become sweepback STOL Fixed Wing AirVehicle wing for the present invention and pack up rear front view entirely.
Fig. 2 b become sweepback STOL Fixed Wing AirVehicle wing for the present invention and pack up lateral side view entirely.
Fig. 2 c become sweepback STOL Fixed Wing AirVehicle wing for the present invention and pack up rear top view entirely.
Fig. 2 d are Fig. 2 c fuselage A-A transverse sectional views.
Schematic diagram when Fig. 3 becomes the expansion of sweepback STOL Fixed Wing AirVehicle wing for the present invention.
Fig. 4 a are front view when aircraft wing of the present invention is deployed.
Fig. 4 b are side view when aircraft wing of the present invention is deployed.
Top view when Fig. 4 c are aircraft wing expansion of the present invention.
Fig. 4 d are Fig. 4 c fuselage B-B transverse sectional views.
In figure
1. the elevon of 2. engine of propeller, 3. 6. fuselage of wing body connection rotating shaft 4. wing, 5. main landing gear 7.
8. vertical fin
Embodiment
The present embodiment is a kind of change sweepback STOL Fixed Wing AirVehicle.Fuselage portion is pancake shape structure,
It is also lifting body, longitudinal cross-section is conventional aerofoil profile, and relative thickness can reach 30%, so fuselage interior has enough space mountings
Become wing mechanism and mission payload.Larger can also increase of relative thickness streams circular rector, improves and rises in the case of not occurring air-flow separation
Power.When wing-folding, merge in wing back segment embedment fuselage and with fuselage, whole frame aircraft is in pancake shape, aircraft wings are carried
Lotus very little, in addition complete machine be at including control surface in propeller high speed slip-stream, aircraft low speed and STOL superior performance.
In addition, propeller blade direction of rotation and wingtip vortex rotation are in opposite direction, aircraft can be made under wing-folding collapsed state
Induced drag is substantially reduced.When wing deploys, aircraft turns into winged without horizontal tail aircraft, and aspect ratio increase, cruise is economical
Property improve, by dividing the optimization design of section to wing and fuselage, aircraft fuselage is deployed and pack up two kinds of shapes in wing
Possess good aerodynamic configuration under state, aircraft resistance will not be significantly increased.Aircraft is set both to have possessed thin-cake flight
Device STOL ability, possesses cruise economy well again.
Refering to Fig. 1~Fig. 4 d, the present embodiment becomes sweepback STOL Fixed Wing AirVehicle, by two engines 2, two spiral shells
Rotation oar 1, wing body connection rotating shaft 3, fuselage 6, wing 4, main landing gear 5, elevon 7, vertical fin 8 are constituted, using low aspect ratio
Shuan Fa Flying-wings；Wherein two engines 2 are connected with major diameter propeller 1 positioned at the front part sides of fuselage 6, the spacing of engine 2
It is larger, it is ensured that the slip-stream that propeller 1 is produced covering aircraft fuselage surfaces as many as possible, aircraft is passed through under lower-speed state
The slip-stream of propeller high speed produces enough lift, reduces landing ground run distance.The propeller 1 of the front part sides of fuselage 6 is synchronous inverse respectively
Hour hands rotate and turned clockwise, and the screw current and wing tip vortex air flow of both sides are in opposite direction, when greatly reducing flight
Induced drag.Fuselage 6 and wing 4 are connected by wing body connection rotating shaft 3, and wing 4 is driven by hydraulic actuator to be connected around wing body
Spindle turns 3 rotations.Wing 4 has the centre of lift for being fully deployed and packing up aircraft after two states, expansion still in center of gravity
In the range of rear, it is ensured that aircraft is stably and controllable before and after aircraft wing expansion.After wing 4 folds back, the upper surface of wing 4 with
The lower surface laminating of the both sides of fuselage 6, lower surface camber flowing transition on aircraft after folding, it is ensured that wing 4 deploys and collapsed state
Lower aircraft is respectively provided with the flight resistance of very little.Twin vertical fin 8 is located at rear portion on fuselage 6 and is symmetrically installed, and elevon 7 is arranged on machine
Vertical fin rear lateral portion on body 6, the vertical fin 8 at rear portion and the control surface of elevon 7 are in the high speed slip-stream of propeller 1, make aircraft
Still there is good maneuverability under lower-speed state.Elevon 7 is located at the rear portion of two vertical fin 8, when aircraft takeoff or need to face upward
When rising, two rudder faces are upward deflected simultaneously, as elevator；When aircraft needs to roll left, under the rudder face of right side on the rudder face of left side partially
Partially, play aileron, two rudder faces are in propeller high speed slip-stream, make aircraft still pitching and roll appearance under lower-speed state
State is controllable.
Park the stage in ground:Aircraft landing gear uses bikini, and main landing gear 5 is higher, and tail wheel is smaller, in parked state
Under make the angle of attack of the aircraft away from ground be more than 20 degree.
The short takeoff stage：The both sides wing 4 of aircraft, which is folded, closes at the both sides of fuselage 6, and fuselage major part wetted area exists
In the high speed slip-stream that two major diameter propellers 2 are produced, and spiral shell is also at positioned at elevon 7, the vertical fin 8 of aircraft aft
Revolve in the slip-stream of oar 2, it is ensured that aircraft still has good maneuverability under the low speed.It is horizontal that aircraft wing 4 enters fuselage 6 after folding
To section, the tangential downside of back segment embedment fuselage 6 of wing 4, the smooth transition of aircraft upper and lower surface curved surface, aircraft is in wing
Possess less flight resistance after 4 foldings.
Cruising phase:The both sides wing 4 of aircraft is driven by hydraulic actuator, around wing body connection rotating shaft 3 while forward
Maximum angle is deployed into, the span of aircraft is greatly increased, aspect ratio, which increases, causes full machine lift-drag ratio increase；While large area oar
The slip-stream that disk is produced covers a part for wing 4, and therefore pneumatic efficiency gets a promotion, therefore cruise economy is greatly improved.Flight
Device wing 4 is under expansion and collapsed state, and aircraft fuselage 6 still keeps streamlined aerodynamic configuration, so under the deployed condition of wing 4
Flight resistance very little.The propeller of the front part sides of aircraft fuselage 6 synchronous rotate counterclockwise and turns clockwise respectively, both sides
Screw current is in opposite direction with wing tip vortex air flow, reduces induced drag and lift is damaged caused by wing tip vortex air flow
Lose.
Short distance landing phases:The both sides wing 4 of aircraft folds back simultaneously around wing body connection rotating shaft 3, in the back segment of wing 4
The downside of fuselage 6 is embedded in, is fitted with fuselage 6, the lifting body upper and lower surface curved surface of laminating rear wing body composition is seamlessly transitted, as pancake
Shape aircraft.Aircraft is landed with High Angle of Attack posture, and the most of wetted area of aircraft is covered by the high speed slip-stream of propeller 1
Lid, aircraft still has very lift and well manipulation ability under lower-speed state, therefore landing distance of taking off is very short.
Claims (2)
1. one kind becomes sweepback STOL Fixed Wing AirVehicle, it is characterised in that:Including two propellers, two engines, the wings
Body connection rotating shaft, fuselage, wing, main landing gear, elevon, vertical fin, using the Shuan Fa Flying-wings of low aspect ratio, two wings
Positioned at fuselage outer side, and can around the synchronous expansion preceding laterally outwardly of wing body connection rotating shaft, or backward, inside fuselage side folds and fitted, it is double
Vertical fin is located at rear portion on fuselage and is symmetrically installed, and elevon is arranged on back body and is located at two vertical fin rear portions, and propeller is with starting
Machine is connected, and engine is symmetrically mounted on fore-body two side ends, and both sides propeller is reversely rotated each other, makes fuselage surface and rear side
Vertical fin and elevon control surface be in propellerslip in, main landing gear be located at fore-body, afterbody be equipped with tail
Wheel.
2. change sweepback STOL Fixed Wing AirVehicle according to claim 1, it is characterised in that:Undercarriage is 3 cloth
Put, main landing gear makes aircraft be more than 20 degree away from the angle of attack between ground under parked state.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710310246.2A CN107161322A (en) | 2017-05-05 | 2017-05-05 | One kind becomes sweepback STOL Fixed Wing AirVehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710310246.2A CN107161322A (en) | 2017-05-05 | 2017-05-05 | One kind becomes sweepback STOL Fixed Wing AirVehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107161322A true CN107161322A (en) | 2017-09-15 |
Family
ID=59813391
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710310246.2A Pending CN107161322A (en) | 2017-05-05 | 2017-05-05 | One kind becomes sweepback STOL Fixed Wing AirVehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107161322A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110775250A (en) * | 2019-11-19 | 2020-02-11 | 南京航空航天大学 | Variant tilt-rotor aircraft and working method thereof |
| CN113232826A (en) * | 2021-05-07 | 2021-08-10 | 南京航空航天大学 | Vertical take-off and landing aircraft with vertical tail seat and control method thereof |
| CN115027667A (en) * | 2022-07-04 | 2022-09-09 | 哈尔滨工业大学 | Bionic deformable wing unmanned aerial vehicle capable of vertically taking off and landing and flight attitude control method |
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| EP0251890A1 (en) * | 1986-06-27 | 1988-01-07 | Thomson-Brandt Armements | Multiple unfolding wing, and its use in an aircraft missile |
| CN103879556A (en) * | 2014-03-31 | 2014-06-25 | 冯加伟 | Wide flight envelop morphing aircraft |
| CN104648656A (en) * | 2015-02-12 | 2015-05-27 | 厦门大学 | Vertical take-off and landing unmanned plane lift augmentation control device and vertical take-off and landing unmanned plane lift augmentation control method |
| CN204433033U (en) * | 2015-02-12 | 2015-07-01 | 厦门大学 | A kind of VUAV with high lift device |
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2017
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Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3738595A (en) * | 1969-10-14 | 1973-06-12 | J Bouchnik | Delta-wing aircraft |
| EP0251890A1 (en) * | 1986-06-27 | 1988-01-07 | Thomson-Brandt Armements | Multiple unfolding wing, and its use in an aircraft missile |
| CN103879556A (en) * | 2014-03-31 | 2014-06-25 | 冯加伟 | Wide flight envelop morphing aircraft |
| CN104648656A (en) * | 2015-02-12 | 2015-05-27 | 厦门大学 | Vertical take-off and landing unmanned plane lift augmentation control device and vertical take-off and landing unmanned plane lift augmentation control method |
| CN204433033U (en) * | 2015-02-12 | 2015-07-01 | 厦门大学 | A kind of VUAV with high lift device |
Non-Patent Citations (1)
| Title |
|---|
| 官网: "飞行薄饼特异独行 美系F5U战斗机成长史", 《HTTP://WANGYOU.PCGAMES.COM.CN/274/2740089.HTML》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110775250A (en) * | 2019-11-19 | 2020-02-11 | 南京航空航天大学 | Variant tilt-rotor aircraft and working method thereof |
| CN113232826A (en) * | 2021-05-07 | 2021-08-10 | 南京航空航天大学 | Vertical take-off and landing aircraft with vertical tail seat and control method thereof |
| CN115027667A (en) * | 2022-07-04 | 2022-09-09 | 哈尔滨工业大学 | Bionic deformable wing unmanned aerial vehicle capable of vertically taking off and landing and flight attitude control method |
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| PB01 | Publication | ||
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Application publication date: 20170915 |