CN106927021A - Fan wing unmanned plane - Google Patents
Fan wing unmanned plane Download PDFInfo
- Publication number
- CN106927021A CN106927021A CN201710219834.5A CN201710219834A CN106927021A CN 106927021 A CN106927021 A CN 106927021A CN 201710219834 A CN201710219834 A CN 201710219834A CN 106927021 A CN106927021 A CN 106927021A
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- Prior art keywords
- wing
- fan
- cross flow
- unmanned plane
- flow fan
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/36—Structures adapted to reduce effects of aerodynamic or other external heating
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Remote Sensing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The present invention relates to unmanned plane field, a kind of fan wing unmanned plane, the flight efficiency and handling of lifting fan wing unmanned plane are disclosed.The present invention includes wing, cross flow fan and cowling panel, and cross flow fan is arranged on the rear portion of wing and along wing spanwise arrangement；Cowling panel is arranged on the top of cross flow fan, and cowling panel receives servos control, the size of the airflow path for adjusting cross flow fan；Cross flow fan on the left and right both sides wing of unmanned plane uses different motor controls.The present invention is applied to fan wing unmanned plane.
Description
Technical field
The present invention relates to unmanned plane field, more particularly to fan wing unmanned plane.
Background technology
Fan rotor aircraft receives the U.S., Britain, Iran, Israel etc. because of its unique flight theory and flying quality
The concern of the related research institutes of country.Under the subsidy of the mechanisms such as U.S. NASA, Britain SMART, the Imperial of Britain
College, Kingston University, FanWing companies, Syracuse University, the Naval in the U.S.
Postgraduate School, Propulsive Wing companies, the Iran University of Science and of Iran
It is many that the research institutions such as Technology have carried out principle, configuration, aerodynamic characteristic, the structure optimization of fan wing class aircraft etc.
Theoretical and experimental study, and manufactured principle prototype.
Research of the China for fanning wing class aircraft is also at the early-stage, is concentrated mainly on colleges and universities and R＆D institution.For fan
The research of wing class aircraft is in the research such as theory study stage, Niu Zhongguo, Jiang Jiali of Chinese aerodynamic investigation institute mostly
The total arrangement of fan wing machine, and rotor speed, blade drift angle and flying speed are to fanning the shadow of rotor aircraft aerodynamic characteristic
Ring.The Di Nansi of East China University of Science fans the UNSTEADY FLOW and static pressure distribution feelings of thriving type by be have studied with CFD approach
Condition, it was demonstrated that the eccentric vortex that the fan wing 80% lift exists from cross flow fan inside.And Nanjing Aero-Space University, air force
The work of some explorations has also been done in fan rotor aircraft field by engineering university etc., and has made the fan in wing nose placement
Wing unmanned plane is simultaneously successfully taken a flight test, but it is not carried out differential control, and flight efficiency also has huge room for promotion.
Fan rotor aircraft is primarily present problems with present：
1. the total arrangement also imperfection of wing unmanned plane is currently fanned, and unmanned plane pitching poor-performing is susceptible to High Angle of Attack
Stall；
2. the control for fanning the wing cannot be realized differential, it is impossible to complete complicated action, operating efficiency is low；
3. airframe structure is complicated, increased the weight of whole machine；
4. flight efficiency is low, and each kernel texture arrangement is unreasonable.
The content of the invention
The technical problem to be solved in the present invention is：A kind of fan wing unmanned plane, the flight efficiency of lifting fan wing unmanned plane are provided
And handling.
To solve the above problems, the technical solution adopted by the present invention is：Fan wing unmanned plane, including wing, cross flow fan and
Cowling panel；Cross flow fan is arranged on the rear portion of wing and along the cross flow fan in wing spanwise arrangement, and left and right wing using not
Same motor control；Cowling panel is arranged on the top of cross flow fan, and by servos control, cowling panel is used to adjust the gas of cross flow fan
Flow the size of runner.
Further, the end of the wingtip of wing is provided with wingtip end plate.
Further, also including aileron, aileron is located at wing tail end；Aileron receives servos control, for providing pitching and rolling
Torque.
Further, fan wing unmanned plane can integrally divide quinquepartite：Left wing top end plate, left side wing section, middle frame
Partly, the right wing section, right flank top end plate；Wherein：Left side wing section and the right wing section are sequentially distributed from front to back
Be：Front fairing, lithium battery, fan add cowling panel, aileron；What middle frame part was sequentially distributed from front to back is effectively to carry
Lotus, communicator, winged control device, motor, steering wheel.
It is of the invention to have the advantages that：
1st, because overall configuration of the present invention is laid out using flying wing type, cross flow fan is arranged in the rear portion of wing, using wingtip
End plate is opened up to streaming reducing wing, is greatly enhanced the efficiency of cross flow fan work.Because cross flow fan is rearmounted, the liter of aircraft
Moved behind power center, can greatly ensure to fan the pitching stability of wing machine.Because landing is apart from short, using slidingtype landing, the wing
Top end plate can be saved and install additional weight and resistance that undercarriage is brought as supporting surface.The rotation of cross flow fan can band
Carry out substantial amounts of air-flow, and boundary-layer can be adjusted by cowling panel, it is ensured that aircraft can be in not stall under High Angle of Attack.
2nd, because the cross flow fan of two wings of left and right receives different motor controls, control passage is different, by adjusting left and right
Two rotation speed of the fan differences come control rolling with driftage, improve aircraft driving efficiency；
3. main body mechanism is simple.Fan rotor aircraft can cancel horizontal tail, vertical fin completely, simply join simply by adjusting aileron
It is dynamic or differential, pitching and rolling are controlled, reduce the weight and structure complexity of aircraft.
4. flight efficiency is high.Coordinate the moveable cowling panel in cross flow fan top, can adjust the size of runner.Taking off or
When low speed is flat winged, increase runner can obtain larger lift increment to suck more air.And in cruising phase, can reduce
Runner, reduces resistance, has both low-speed performance high, improves flight efficiency.
Brief description of the drawings
Fig. 1 is the integral layout figure that embodiment fans wing machine；
Fig. 2 is tradition fan wing machine flight theory figure；
Fig. 3 is embodiment fan wing machine flight theory figure；
Fig. 4 is GOE-383 aerofoil profile figures；
Fig. 5 is the GOE-383 aerofoil profile figures that rear portion has installed cross flow fan additional；
Fig. 6 is the comparison diagram that original aerofoil profile is distributed with the two-dimensional pressure for installing cross flow fan aerofoil profile additional.
Numbered in figure：DB is wingtip end plate, and 1 is front fairing, and 2 is lithium battery, and 3 add cowling panel for fan, and 301 is crossing current
Fan, 302 is cowling panel, and 4 is aileron, and 5 is payload, and 6 is communicator, and 7 to fly control device, and 8 is brushless electric machine, and 9 are
Steering wheel, JL is left side wing section, and JM is middle frame part, and JR is the right wing section.
Specific embodiment
Embodiment provides a kind of fan wing unmanned plane, as shown in figure 1, the fan wing unmanned plane can integrally divide quinquepartite, i.e.,：
Left wing top end plate DB, left side wing section JL, middle frame part JM, the right wing section JR, right flank top end plate DB；Wherein：
What left side wing section JL and the right wing section JB were sequentially distributed from front to back is：Front fairing 1, lithium battery 2, fan add whole
Stream plate 3, aileron 4；What middle frame part was sequentially distributed from front to back is payload 5, communicator 6, flies control device 7, nothing
Brush motor 8, steering wheel 9.
Cross flow fan 301：Cross flow fan is arranged on the rear portion of wing and along wing spanwise arrangement, using high-strength aluminum alloy
Material, size causes that the flow velocity of wing upper and lower surface is different for the motion of 30mm*290mm cross flow fans 301, and in cross flow fan
301 are internally formed vortex low-pressure area, cause the pressure differential of wing upper and lower surface so that wing obtains lift.Meanwhile, blade is to sky
Air-flow is released in gas effect backward, forms thrust forward.Can be by controlling rotating speed, the blade angle etc. of cross flow fan 301
Factor controls the intensity of vortex low-pressure area, so as to realize the control to fan wing machine lift, thrust.Also, on two wings of left and right
Cross flow fan controlled by different brushless electric machines, control passage is different, can be by adjusting the left and right speed discrepancy of two cross flow fan 301
To control rolling and driftage, so as to improve the driving efficiency of aircraft.
Wingtip end plate DB：The end of the wingtip of wing is arranged on, is opened up to streaming for reducing wing, be greatly enhanced crossing current
The efficiency of fan work.Because landing is apart from short, using slidingtype landing, wingtip end plate DB can save installation as supporting surface
Additional weight and resistance that undercarriage is brought.
Steering wheel 9：Control cowling panel 302, the motion of aileron 4.
Aileron 4：Aileron is located at wing tail end, for providing pitching and rolling moment.
Cowling panel 302：Cowling panel is arranged on the top of cross flow fan, can adjust the size of runner.Taking off or low speed is flat
When flying, increase runner can obtain larger lift increment to suck more air, and now cowling panel 302 is swung back.And in cruise rank
Section, can be leaned forward by cowling panel 302, reduce runner, reduce resistance, flight efficiency be improved, so as to realize the height of aircraft
Fast function.
Lithium battery 2：The energy of whole machine flight is provided.
Payload 5：Increase the function of aircraft, such as photography, investigation, fight capability.
Leading edge radome fairing 1：Reduce air drag.
Brushless electric machine 8：Cross flow fan 301 is driven, transmission is realized.
Tradition fan wing machine and embodiment fan wing airfoil type compare as shown in Figure 2,3, and the cross flow fan 301 of tradition fan wing machine is pacified
Mounted in the fixed wing aircraft leading edge of a wing, and the cross flow fan 301 at the wing rear portion of the fan wing machine of embodiment is fixed alar part and is made
Hollow structure, in bevel phase top airfoil fluting, increases the conveyance capacity of wing, so that preferably guiding air-flow is close to aerofoil stream
It is dynamic.New fan wing machine has also installed mobilizable cowling panel 301 additional on cross flow fan, absorbs and guiding air-flow enters crossing current wind
Fan, and air-flow import and export size can be adjusted by steering wheel, control the aerodynamic characteristic of aircraft such that it is able to obtain bigger taking off
Lift, obtain less resistance in cruising phase.Compare and find out, new fan wing machine is main compared to tradition fan wing airfoil type
With 2 advantages：(1) trailing edge is embedded in by by cross flow fan, can preferably guides air-flow to adhere to, improve lift,
Reduce resistance；(2) increase mobilizable cowling panel, improve and take off and cruising characteristics.
As shown in figure 3, the flight theory of embodiment is：Using the cross flow fan 301 pairs for being placed in wing rear upper surface
Air is accelerated, and is a kind of big load flight between gyroplane and fixed wing aircraft while providing lift and thrust
Device.Air-flow is divided into two parts when flowing through cross flow fan, a part of air-flow flows through from the upper limb of cowling panel 302, after wing
Edge inclined-plane flows out, and upper and lower surface flow velocity is different, produces pressure differential, generating unit decilitre power；Another part air-flow is by cross flow fan 301
Suction is divided into two parts：1. after rotated blade accelerates, flowed out along trailing edge inclined-plane, merge with front portion air-flow and combine, accelerated
Inclined-plane upper surface air flow, 2. along the arc top airfoil reverse flow of wing, one is formd in blade center place to the right
Individual significant low pressure eccentric vortex.Eccentric vortex internally forms low-pressure area so that wing upper and lower surface produces larger pressure differential, so that
Greater part lift is produced, this part lift is the main source for fanning rotor aircraft lift.
The thrust that fan wing unmanned plane is obtained is made up of two parts：When a part of thrust is that blade is rotated, blade promotes air-flow
Discharge backward, according to Newton's third law, air-flow provides propulsive thrust forward for blade, so as to form thrust；Another part
Thrust is provided by eccentric vortex, and because low pressure eccentric vortex is mostly formed at blade interior position to the right, this just have impact on horizontal stroke
The pressure distribution of flow fan horizontal direction, and then produce a thrust forward.
Need to install cross flow fan additional inside wing in view of embodiment, therefore select the aerofoil profile of large thickness ratio as base
Standard, such as the GOE-383 aerofoil profiles shown in Fig. 4, because wing is the tapered wing with angle of sweep, in order to ensure cross flow fan
The normal direction of 301 rotary shafts is consistent with heading, therefore at wing root, cross flow fan should be at wing chord posterior border position, slightly locate in the wing,
Cross flow fan should be at wing chord leading edge locus.Embodiment installs cross flow fan 301 additional with GOE-383 aerofoil profiles, the aerofoil profile maximum gauge
It is 20% chord length.
In order to more specifically obtain installing additional the Aerodynamic parameter of the wing after cross flow fan, here intercept wing open up to
The aerofoil section in stage casing, section are emulated as shown in figure 5, having carried out two-dimentional CFD to aerofoil profile using Fluent softwares, emulation such as result
As shown in Figure 6.Fig. 6 shows the contrast that original aerofoil profile is distributed with the two-dimensional pressure for installing cross flow fan aerofoil profile additional, it can be seen that by
In acceleration of the cross flow fan 301 to aerofoil profile upper surface air so that the upper table surface pressure of its leading edge is less than corresponding original
Aerofoil profile；The low pressure whirlpool that the rotation of cross flow fan 301 is produced also causes the pressure at aerofoil profile upper surface cross flow fan position much smaller than original
Beginning aerofoil profile, so as to considerably increase the lift of wing.From fig. 6, it can be seen that as a length of 0.5m of airfoil chord, in air speed 5m/s,
Under cross flow fan rotating speed 6000rpm, upper surface air-flow highest can accelerate to about 12m/s, and the more original aerofoil profile of lift improves about 45%.
Embodiment shows by test：
1st, the flying wing type layout for using, at the rear portion of wing along spanwise arrangement cross flow fan 301, and using wingtip end plate DB
Opened up to crossing current to reduce wing, be greatly enhanced the efficiency of cross flow fan work.Because cross flow fan 301 is rearmounted, the liter of aircraft
Moved behind power center, can greatly ensure to fan the pitching stability of wing machine.Because landing is apart from short, using slidingtype landing, the wing
Top end plate DB can be saved and be installed additional weight and resistance that undercarriage is brought as supporting surface.The rotation of cross flow fan 301 can
To bring substantial amounts of air-flow, and boundary-layer can be adjusted, it is ensured that aircraft can be in not stall under High Angle of Attack.Wind Tunnel Data
Show, this fan wing machine still has the characteristic of not stall under High Angle of Attack, is coincide with simulation result.
2nd, using outer rotor brushless motor 7 as power set, cross flow fan 301 is driven, realizes efficient driving.Due to adopting
Be laid out with flying wing type, horizontal tail, vertical fin can be cancelled, only linked by aileron or it is differential control lift and rolling, substantially reduce
The weight and complex degree of structure of aircraft.
3rd, control system is designed using anury, and trailing edge both sides are installed aileron and provide pitching and rolling moment simultaneously.
The rear portion of wing along spanwise arrangement cross flow fan 301, and reduced using wingtip end plate DB wing open up to crossing current 301.Fan wing machine
Can also be by the size that controls the rotating speed of fan to control lift and thrust, can also be by adjusting two cross flow fan rotating speeds of left and right
Differ to control rolling and driftage, improve the driving efficiency of aircraft.
4th, coordinate the moveable cowling panel 302 in the top of cross flow fan 301, can adjust the size of runner.Taking off or low speed
When flat winged, increase runner can obtain larger lift increment to suck more air.And in cruising phase, runner can be reduced,
Resistance is reduced, flight efficiency is improved.
It is pointed out that described above simply illustrate some principles of the invention, due to the general of constructed field
It is easy to carry out some modifications on this basis for logical technical staff and changes.Therefore, this specification be not intended to by
The present invention be confined to shown in and described concrete structure and the scope of application in, therefore every corresponding modification for being possible to be utilized with
And equivalent, belong to apllied the scope of the claims of the invention.
Claims (4)
1. wing unmanned plane, including wing, cross flow fan and cowling panel are fanned, it is characterised in that after cross flow fan is arranged on wing
Portion and along the cross flow fan in wing spanwise arrangement, and left and right wing use different motor controls；Cowling panel is arranged on crossing current wind
The top of fan, and by servos control, cowling panel is used for the size of the airflow path for adjusting cross flow fan.
2. it is as claimed in claim 1 to fan wing unmanned plane, it is characterised in that the end of the wingtip of wing is provided with wingtip end
Plate.
3. as claimed in claim 2 to fan wing unmanned plane, it is characterised in that also including aileron, aileron is located at wing tail end；Aileron
By servos control, for providing pitching and rolling moment.
4. it is as claimed in claim 3 to fan wing unmanned plane, it is characterised in that fan wing unmanned plane integrally divides quinquepartite：Left wing's tip
End plate, left side wing section, middle frame part, the right wing section, right flank top end plate；Left side wing section and the right wing
Part be sequentially distributed from front to back be：Front fairing, lithium battery, fan add cowling panel, aileron；Middle frame part by it is preceding extremely
What is be sequentially distributed afterwards is payload, communicator, winged control device, motor, steering wheel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710219834.5A CN106927021A (en) | 2017-04-06 | 2017-04-06 | Fan wing unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710219834.5A CN106927021A (en) | 2017-04-06 | 2017-04-06 | Fan wing unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106927021A true CN106927021A (en) | 2017-07-07 |
Family
ID=59426263
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710219834.5A Pending CN106927021A (en) | 2017-04-06 | 2017-04-06 | Fan wing unmanned plane |
Country Status (1)
| Country | Link |
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| CN (1) | CN106927021A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107826245A (en) * | 2017-11-21 | 2018-03-23 | 南京航空航天大学 | A kind of cross flow fan swing device |
| CN107976120A (en) * | 2017-10-23 | 2018-05-01 | 四川大学 | A kind of rudder piece pop-up and arrangement for deflecting |
| CN109823510A (en) * | 2019-03-06 | 2019-05-31 | 中南大学 | Hypersonic aircraft and its thermal protection structure and coolant circulating system |
| CN114291261A (en) * | 2022-01-20 | 2022-04-08 | 上海工程技术大学 | Double-transverse-flow fan wing of wing aircraft and design method thereof |
| CN114940260A (en) * | 2022-06-20 | 2022-08-26 | 中国航空工业集团公司西安飞机设计研究所 | Fan wing structure and aircraft with same |
| CN116238689A (en) * | 2023-05-12 | 2023-06-09 | 南京航空航天大学 | Perpendicular take-off and landing span medium aircraft based on propulsion wings and control system thereof |
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| US20060266882A1 (en) * | 2005-04-21 | 2006-11-30 | Syracuse University | Cross-flow fan propulsion system |
| US20120111994A1 (en) * | 2010-01-15 | 2012-05-10 | Propulsive Wing, LLC | Cross-flow fan propulsion system |
| CN104401485A (en) * | 2014-10-13 | 2015-03-11 | 南京航空航天大学 | Four-wing unmanned aerial vehicle and control method thereof |
| CN204250356U (en) * | 2014-05-14 | 2015-04-08 | 刘新广 | New fan wing aircraft |
| CN204726671U (en) * | 2015-05-07 | 2015-10-28 | 南京航空航天大学 | A kind of high efficient fan wing |
| CN205076026U (en) * | 2015-09-29 | 2016-03-09 | 刘新广 | Built -in two cross flow fan's fan wing |
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| US20060266882A1 (en) * | 2005-04-21 | 2006-11-30 | Syracuse University | Cross-flow fan propulsion system |
| US20120111994A1 (en) * | 2010-01-15 | 2012-05-10 | Propulsive Wing, LLC | Cross-flow fan propulsion system |
| CN204250356U (en) * | 2014-05-14 | 2015-04-08 | 刘新广 | New fan wing aircraft |
| CN104401485A (en) * | 2014-10-13 | 2015-03-11 | 南京航空航天大学 | Four-wing unmanned aerial vehicle and control method thereof |
| CN204726671U (en) * | 2015-05-07 | 2015-10-28 | 南京航空航天大学 | A kind of high efficient fan wing |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107976120A (en) * | 2017-10-23 | 2018-05-01 | 四川大学 | A kind of rudder piece pop-up and arrangement for deflecting |
| CN107976120B (en) * | 2017-10-23 | 2024-01-19 | 四川大学 | Rudder sheet popup and deflection device |
| CN107826245A (en) * | 2017-11-21 | 2018-03-23 | 南京航空航天大学 | A kind of cross flow fan swing device |
| CN107826245B (en) * | 2017-11-21 | 2023-12-05 | 南京航空航天大学 | Cross-flow fan blade device |
| CN109823510A (en) * | 2019-03-06 | 2019-05-31 | 中南大学 | Hypersonic aircraft and its thermal protection structure and coolant circulating system |
| CN114291261A (en) * | 2022-01-20 | 2022-04-08 | 上海工程技术大学 | Double-transverse-flow fan wing of wing aircraft and design method thereof |
| CN114291261B (en) * | 2022-01-20 | 2023-09-22 | 上海工程技术大学 | Double-cross-flow fan blade of fan-blade aircraft and design method thereof |
| CN114940260A (en) * | 2022-06-20 | 2022-08-26 | 中国航空工业集团公司西安飞机设计研究所 | Fan wing structure and aircraft with same |
| CN116238689A (en) * | 2023-05-12 | 2023-06-09 | 南京航空航天大学 | Perpendicular take-off and landing span medium aircraft based on propulsion wings and control system thereof |
| CN116238689B (en) * | 2023-05-12 | 2023-09-29 | 南京航空航天大学 | Perpendicular take-off and landing span medium aircraft based on propulsion wings and control system thereof |
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Application publication date: 20170707 |
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