CN107813928A - One kind can vert more rotor twin fuselage canard configuration unmanned vehicles - Google Patents
One kind can vert more rotor twin fuselage canard configuration unmanned vehicles Download PDFInfo
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- CN107813928A CN107813928A CN201610816203.7A CN201610816203A CN107813928A CN 107813928 A CN107813928 A CN 107813928A CN 201610816203 A CN201610816203 A CN 201610816203A CN 107813928 A CN107813928 A CN 107813928A
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- canard
- fuselage
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- rudder face
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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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/12—Canard-type aircraft
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Abstract
The present invention relates to a kind of unmanned vehicle of VTOL, the aircraft uses the aerodynamic arrangement of twin fuselage long distance canard, 4 propellers with inclining rotary mechanism that dynamical system is laid out by Y-shaped are formed, and wing uses the variable geometry based on compliant structure, and rudder face uses flexible seamless rudder face structure.The beneficial effects of the present invention are：Using that can vert, more rotor systems realize VTOL, avoid useless dynamical system during flat fly being present and producing " useless weight "；Arrange that dynamical system can avoid the interference in air flow between propeller and fuselage between two fuselages；Twin fuselage can improve body rigidity so as to reduce body weight；Long distance canard can improve the rigidity of full machine lift coefficient, regulation aerodynamic center position, increase body so as to reducing body weight；Using the adaptive wing based on compliant structure so that the wing aerodynamic profile moment is in optimum state；Using flexible seamless rudder face, wing and rudder face are seamlessly connected, so as to reduce interference drag.
Description
Technical field
The present invention relates to airborne vehicle technical field, more particularly to a kind of unmanned vehicle of VTOL, the aircraft is adopted
With the aerodynamic arrangement of twin fuselage long distance canard, the dynamical system of a pair of coaxial double-oar systems and two single propeller compositions, and
Devise the variable geometry based on compliant structure, and flexible seamless rudder face structure, can possess hovering efficiency it is high, can be before high speed
Fly, can VTOL the features such as.
Background technology
Vertically taking off and landing flyer is an important aircraft class.Extensively should although VTOL aircraft obtains already
With, but for a long time, can the new design of VTOL aircraft can not always ensure do not sacrificing voyage, efficiency and work capacity
Under conditions of improve flying speed.With the development of technology, the research on new vertical takeoff and landing vehicle turns into focus again.
In recent years, U.S. Department of Defense's pre research Plan Bureau (DARPA) proposes " VTOL Experimental Aircraft Programme " (X-Plane),
Want to it is creative rotor technology must be combined with fixed-wing technology, develop vertically taking off and landing flyer of new generation.
Compared with current vertically taking off and landing flyer, can vert more rotor systems of this vertically taking off and landing flyer use are realized and hung down
Straight landing；Using twin-fuselage configuration so that there are enough space arrangement coaxial double-oar dynamical systems between fuselage, propeller is avoided
Interference in air flow between dynamical system and fuselage, also cause there are enough space charging appliances in fuselage；Use long distance canard can be with
Full machine lift coefficient is improved, adjusts the position of the pneumatic focus of full machine, while long distance canard and twin fuselage, host wing composition closing are whole
Body, full machine rigidity is improved, so that housing construction weight is mitigated；Avoid dynamical system not busy using tilting rotor mechanism
Put so that dynamical system is all effectively applied under the winged state of VTOL peace；Using based on the adaptive of compliant structure
Wing so that when flight operating mode changes, wing adjusts shape therewith, reaches under the operating mode preferably aerodynamic configuration, obtains more preferable
Lifting resistance characteristic；Using flexible seamless rudder face, connected between rudder face and aerofoil with flexible material, ensure rudder face leading edge and aerofoil it
Between do not have between gap, the border of rudder face and aerofoil without disconnected every reaching that wing and rudder face are seamless to be seamlessly transitted, reduce interference and hinder
The effect of power.Rudder face is driven using memory metal, and flexible material modulus of elasticity is moderate, so that memory metal is enough to drive rudder
Face,.
The content of the invention
Present invention aims at the flying quality for improving vertical take-off and landing unmanned aerial vehicle.
To improve the flying quality of vertical take-off and landing unmanned aerial vehicle, the present invention is achieved through the following technical solutions：One kind is hung down
Straight landing unmanned vehicle, including Y-shaped are laid out can vert more rotor VTOL systems, twin-fuselage configuration, long distance canard, base
Variable geometry, flexible seamless rudder face structure in compliant structure etc..
Y-shaped of the present invention is laid out more rotor power systems that can vert, and, arranges coaxial double-oar close to heading a bit
Propeller, 2 points of afterbody, arrange a pair of single-blades.Propeller, which is all arranged on, to vert in structure, during VTOL, oar disk center
Axis vertical, when putting down winged, oar disk center axis switchs to level.The system has following advantageous feature：(1) control is simple.(2) hang
Stop efficiency high.(3) " useless weight " is small, and " empty weight coefficient " is low.Partial power system is in " idle " state, be effectively increased
Mission payload, extend endurance, voyage.(4) level speed is high.
Twin-fuselage configuration of the present invention, based on following two reasons：(1) the hovering efficiency peace for improving rotor flies to promote
Efficiency：Using twin-fuselage configuration, " rotor system " among VTOL dynamical system can be arranged between two fuselages.Hang down
In the straight landing stage, fuselage, wing will not be formed to rotor air-flow to be stopped, so as to improve hovering efficiency, is put down the winged stage, between fuselage
Unobstructed passage is formd, compared with unit body aircraft installs the aircraft of tilting rotor in fuselage, puts down and flies extreme rotor
Carry out flow path not block, intake efficiency is high, so as to improve flat winged propulsive efficiency.(2) twin-fuselage configuration can improve machine
Body rigidity, so as to mitigate construction weight, improve the voyage and endurance of aircraft.
Long distance canard of the present invention, canard is arranged in fuselage close to the position on head, by canard by two fuselages
It is connected.Canard can increase the rigidity of whole aircraft while pitching moment trim needs are met, improve two twin fuselage
The anti-twisting property of structure, mitigate airframe structure weight；In terms of the arrangement of canard, because canard can produce wake flow, if main frame
The wing is located among the wake flow of canard, the effect of washing will certainly be influenceed by under, reduces efficiency.Therefore, canard uses lower single-blade, main
Wing uses midsetwing, host wing is avoided the downwash flow of canard.Such arrangement can be with wall canard wake flow to host wing
Interfere.
Variable geometry of the present invention based on compliant structure, realized unlike conventional rigid mechanism by kinematic pair complete
Portion moves and function, and realizes the main movement of mechanism and function mainly by the deformation of the flexible member in mechanism, while
The transmission and conversion of motion, power and energy can be realized, effectively realizes the variable camber function of adaptive wing, can be outside aircraft
In the case that portion's flight environment of vehicle, especially flying speed change, change air foil shape, wing shapes, must adapt to fly with more preferable
Requirement to lift-drag ratio.
Flexible seamless rudder face structure of the present invention, refer to connecting using flexible seamless between rudder face and airfoil.Rudder
There is no gap between face and aerofoil surface, rudder face edge is flexibly connected with wing, does not form fracture.Such flexible seamless rudder face
Structure, it can improve pneumatic efficiency when using rudder face, reduce interference drag.In addition, flexible seamless rudder face is driven by memory metal
It is dynamic.
Brief description of the drawings
Fig. 1 schemes (unmanned plane take off vertically top view) for the present invention is a kind of.
Fig. 2 schemes (unmanned plane take off vertically side view) for the present invention is a kind of.
Fig. 3 schemes (the flat winged top view of unmanned plane) for the present invention is a kind of.
Fig. 4 schemes (the flat winged side view of unmanned plane) for the present invention is a kind of.
Fig. 5 schemes (unmanned drive end unit propulsion plant figure) for the present invention is a kind of.
Embodiment
To describe the technology contents of the present invention, construction feature, the objects and the effects in detail, below in conjunction with embodiment
And accompanying drawing is coordinated to be explained in detail.
The design of this patent most critical is, introduces the aerodynamic arrangement of twin fuselage and long distance canard, introduces Y-shaped layout
Can be verted more rotor power systems.
Refer to Fig. 1, Fig. 2 and Fig. 5, a kind of vertical take-off and landing unmanned aerial vehicle, including pitot 1, electron-light cameraing probe 2,
Canard 3, canard deflection rudder 4,5, radar 5, undercarriage 6, left and right fuselage 8,9, flight control computer 10, main propelling screws vert dress
Put 11, coaxial double-oar propeller 12, host wing 13, vertical fin deflection rudder 14, host wing deflection rudder 15, sterm propeller air intake duct 16,
Tail undercarriage 17, afterbody propeller 18, left and right vertical fin 19,20, afterbody promote inclining rotary mechanism 21.
It was found from foregoing description, the present invention is using Y-shaped layout VTOL dynamical system, the cloth of coaxial double-oar propeller 12
Put between heading, two fuselages 8,9, have installation coaxial double-oar thereon, pass through main propelling screws reclining device 11
It is controlled to turn to the angle needed for current flight state, two fuselages 8,9 afterbodys are each provided with afterbody propeller 18, pacified thereon
A tail undercarriage 17 is filled, changes propeller rotational angle also by afterbody inclining rotary mechanism 21, tail inlet is streamlined,
When unmanned vehicle is flat to fly, and the fitting of fuselage streamline, reduce flight resistance.
It was found from foregoing description, the present invention uses twin-fuselage configuration, and pitot 1, electron-light cameraing probe 2 and radar 5 are located at
Fuselage head, flight control computer 10 are located at fuselage interior, and left and right fuselage 8,9 is mainly connected by preposition canard 3 and host wing 13,
The layout of twin fuselage provides enough installing spaces to main propelling screws reclining device 11, under takeoff condition, left and right machine
Body 8,9, host wing 13 will not be formed to rotor air-flow to be stopped, reduces interference drag, under flat winged state, left and right fuselage 8,9
Between form unobstructed passage, compared with unit body aircraft installs the aircraft of tilting rotor in fuselage, put down the winged stage
Rotor carrys out flow path and not blocked, and improves the intake efficiency of coaxial double-oar propeller 12.Dynamical system is equal in the VTOL stage
Lift is provided, in flat fly, equal steering horizontal provides thrust.The flat winged stage does not have useless dynamical system.Flat winged stage power
System provides thrust, host wing and canard and provides lift.This design can improve aircraft empty weight coefficient, improve flight
Efficiency, so as to extend endurance, voyage.
It was found from foregoing description, the present invention is laid out using long distance canard, and canard 3 is arranged in into left and right fuselage 8,9 heads, is led to
Cross canard 3 left and right fuselage 8,9 is connected.Canard 3 can increase whole aircraft while pitching moment trim needs are met
Rigidity, improve two-shipper body structure anti-twisting property, mitigate airframe structure weight；Wake flow can be produced additionally, due to canard 3, if
Host wing 13 is located among the wake flow of canard 3, the effect of washing will certainly be influenceed by under, reduces efficiency.Therefore, canard 3 uses
Lower single-blade, host wing 13 use midsetwing, host wing 13 is avoided the downwash flow of canard.Long distance canard established angle is more than main frame
The wing, under High Angle of Attack operating mode, the stall first of long distance canard, avoid the angle of attack from further expanding and cause host wing stall.In addition, long distance duck
The wing can provide lift, so as to increase full machine lift coefficient.
It was found from foregoing description, the present invention use the variable geometry 13 based on compliant structure, unlike conventional rigid mechanism that
Sample realizes the deformation of wing by kinematic pair, and realizes whole wing mainly by the deformation of the flexible member in wing structure
Deformation, effectively realizes the variable camber function of adaptive wing, can change in aircraft exterior flight environment of vehicle, especially flying speed
In the case of change, change air foil shape, wing shapes, with the more preferable requirement that must adapt to fly to lift-drag ratio.Wherein, it is described submissive
Material selects from the combination including memorial alloy, sma polymer, polypropylene, baroplastics.
It was found from foregoing description, canard of the invention deflection rudder 4,5, vertical fin deflects rudder 14, and host wing deflection rudder 15 uses
Flexible seamless rudder face structure, connected between rudder face and aerofoil using flexible seamless.There is no gap, rudder between rudder face and aerofoil surface
Face edge is flexibly connected with wing, does not form fracture.Such flexible seamless rudder face structure, it can be kept when using rudder face
Smooth aerodynamic configuration, pneumatic efficiency is improved, reduce interference drag.In addition, flexible seamless rudder face is driven by memory metal.
It was found from foregoing description, in takeoff condition, coaxial double-oar propeller 12 is inclined the present invention by main propelling screws
Rotary device 11 turns to the plane parallel with fuselage, and two afterbody propellers 18 promote inclining rotary mechanism 21 by respective afterbody
The plane parallel with fuselage is turned to, the required lift that takes off or hover is provided for unmanned plane, when unmanned plane rises to safety
After level altitude, undercarriage 6 is packed up, then promote inclining rotary mechanism 21 will be coaxial by main propelling screws reclining device 11 and afterbody
Double oar propellers 12 and afterbody propeller 18 rotate to the position vertical with two fuselages, there is provided the thrust that unmanned plane advances, canard 3
The lift needed for unmanned plane during flying is provided with host wing 13, is completed entirely by the flight control computer 10 inside fuselage 8,9
The take-off process of unmanned plane, in flight course, the flexible wing that the present invention uses can be according to suffered by the current flight of unmanned plane
Aerodynamic force, by technologies such as compliant mechanism, memorial alloys, the rational air foil shape for changing wing shapes and wing, come
Lift the aeroperformance of wing, flight control computer 10 control canard 4, the deflection rudder 4 of host wing 13 and left and right empennage 19,20,5,
14th, 15, the rational flight attitude for controlling unmanned plane, pitot 1, radar 5 and the first 2 grade Aerial Electronic Equipment of electron-light cameraing are supplied to nothing
External information needed for man-machine.
Refer to Fig. 1, Fig. 2, Fig. 3, Fig. 4, be that unmanned vehicle state of (or hovering) peace when flying of taking off is shown respectively
It is intended to.
In summary, technical scheme provided by the invention, a kind of vertical take-off and landing unmanned aerial vehicle is allow on land,
Take off vertically in the case of the multiple types of floors such as deck, by twin fuselage and long distance canard configuration, provided for coaxial double-oar dynamical system
While sufficient installing space, avoid interference in air flow, reduce whole machine weight, be also improved full machine lift coefficient, increase body
A variety of advantages such as rigidity；By tilting rotor, mechanism avoids dynamical system from leaving unused so that dynamical system is in unmanned plane VTOL
All effectively applied under the winged state of peace；Using the adaptive wing based on compliant structure and flexible seamless rudder face, gas is kept
While dynamic smooth-shaped so that the aircraft moment is in preferably state of flight；
Embodiments of the invention are the foregoing is only, are not intended to limit the scope of the invention, it is every to utilize this hair
The equal conversion that bright specification and accompanying drawing content are done, or the technical field of correlation is directly or indirectly used in, similarly include
In the scope of patent protection of the present invention.
Claims (6)
- More rotor twin fuselage canard configuration unmanned vehicles 1. one kind can vert, it is characterised in that aircraft is remote using twin fuselage Aerodynamic arrangement away from canard, dynamical system are formed using 4 propellers of Y-shaped layout, and wing is designed using compliant structure, the flap The wing uses seamless flap configurations.
- 2. more rotor twin fuselage canard configuration unmanned vehicles according to claim 1 that vert, it is characterised in that power System layout is laid out using Y-shaped.Body medium position arrangement coaxial double-oar between two fuselages, two afterbodies respectively arrange one Individual propeller.The propeller system is fitted with inclining rotary mechanism, during VTOL, oar disk center axis vertical, puts down when flying, oar Disk center's axis switchs to level.The system has following features：Control is simple；Hovering efficiency is high；" useless weight " small, " empty weight Coefficient " is low；There is no dynamical system to be in " idle " state in flat fly, mission payload can be effectively increased, extend endurance, boat Journey；Level speed is high.
- 3. more rotor twin fuselage canard configuration unmanned vehicles according to claim 1 that vert, it is characterised in that use Twin-fuselage configuration, there are enough spaces to arrange coaxial double-oar system between two fuselages.Meanwhile twin-fuselage configuration can increase The rigidity of body, construction weight is advantageously reduced, increase the span, so as to extend endurance, voyage.
- 4. more rotor twin fuselage canard configuration unmanned vehicles according to claim 1 that vert, it is characterised in that use Long distance canard configuration.Canard is arranged in fuselage close to the position on head, is lower single-blade, canard runs through two fuselages, by two Fuselage is connected.Canard can increase the rigidity of whole aircraft while pitching moment trim needs are met.Long distance canard with Host wing forms enclosed construction so that the anti-twisting property enhancing of housing construction, so as to mitigate airframe structure weight.Host wing Using midsetwing, host wing is set to avoid the downwash flow of canard.
- 5. more rotor twin fuselage canard configuration unmanned vehicles according to claim 1 that vert, it is characterised in that use Variable geometry based on compliant structure.The main movement of mechanism and work(are realized mainly by the deformation of the flexible member in mechanism Can, while the transmission and conversion of motion, power and energy can be also realized, effectively realize the variable camber function of adaptive wing, can be with In the case where aircraft exterior flight environment of vehicle, especially flying speed change, change air foil shape, wing shapes, with more preferable The requirement flown to lift-drag ratio must be adapted to.
- 6. more rotor twin fuselage canard configuration unmanned vehicles according to claim 1 that vert, it is characterised in that use Flexible seamless rudder face structure.There is no gap between rudder face and aerofoil surface, rudder face edge is flexibly connected with wing, do not formed disconnected Split.It can improve pneumatic efficiency when using rudder face, reduce interference drag.In addition, flexible seamless rudder face is driven by memory metal It is dynamic.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201610816203.7A CN107813928A (en) | 2016-09-12 | 2016-09-12 | One kind can vert more rotor twin fuselage canard configuration unmanned vehicles |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201610816203.7A CN107813928A (en) | 2016-09-12 | 2016-09-12 | One kind can vert more rotor twin fuselage canard configuration unmanned vehicles |
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| CN107813928A true CN107813928A (en) | 2018-03-20 |
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| CN201610816203.7A Pending CN107813928A (en) | 2016-09-12 | 2016-09-12 | One kind can vert more rotor twin fuselage canard configuration unmanned vehicles |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108791816A (en) * | 2018-07-16 | 2018-11-13 | 西安君晖航空科技有限公司 | A kind of tilting wing unmanned plane with complex pneumatic rudder face |
| CN109533243A (en) * | 2018-12-06 | 2019-03-29 | 上海交通大学 | Deep-sea unmanned remote-controlled vehicle |
| CN110282114A (en) * | 2019-07-17 | 2019-09-27 | 王颖 | It is a kind of for Reservoir region cruise can VTOL composite wing electric power unmanned plane |
| CN111792027A (en) * | 2020-07-03 | 2020-10-20 | 中国空气动力研究与发展中心 | Aircraft with double-fuselage tandem wing vertical take-off and landing layout |
| CN113039122A (en) * | 2018-09-17 | 2021-06-25 | 乌瓦沃斯控股有限公司 | Method for controlling an aircraft and aircraft (variants) |
| CN113911336A (en) * | 2021-11-29 | 2022-01-11 | 南京航空航天大学 | Double-fuselage type tilt rotorcraft |
| CN114655434A (en) * | 2022-05-25 | 2022-06-24 | 中国空气动力研究与发展中心空天技术研究所 | Automatic angle changing device for tail-pushing motor of vertical take-off and landing composite wing unmanned aerial vehicle |
| CN114872880A (en) * | 2022-06-14 | 2022-08-09 | 南京航空航天大学 | Tilt rotor wing mechanism applying shape memory material, folding structure and aircraft |
| CN114872880B (en) * | 2022-06-14 | 2024-07-16 | 南京航空航天大学 | Tilt rotor mechanism, folding structure and aircraft using shape memory material |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN108791816A (en) * | 2018-07-16 | 2018-11-13 | 西安君晖航空科技有限公司 | A kind of tilting wing unmanned plane with complex pneumatic rudder face |
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| CN109533243A (en) * | 2018-12-06 | 2019-03-29 | 上海交通大学 | Deep-sea unmanned remote-controlled vehicle |
| CN110282114A (en) * | 2019-07-17 | 2019-09-27 | 王颖 | It is a kind of for Reservoir region cruise can VTOL composite wing electric power unmanned plane |
| CN111792027A (en) * | 2020-07-03 | 2020-10-20 | 中国空气动力研究与发展中心 | Aircraft with double-fuselage tandem wing vertical take-off and landing layout |
| CN113911336A (en) * | 2021-11-29 | 2022-01-11 | 南京航空航天大学 | Double-fuselage type tilt rotorcraft |
| CN114655434A (en) * | 2022-05-25 | 2022-06-24 | 中国空气动力研究与发展中心空天技术研究所 | Automatic angle changing device for tail-pushing motor of vertical take-off and landing composite wing unmanned aerial vehicle |
| CN114872880A (en) * | 2022-06-14 | 2022-08-09 | 南京航空航天大学 | Tilt rotor wing mechanism applying shape memory material, folding structure and aircraft |
| CN114872880B (en) * | 2022-06-14 | 2024-07-16 | 南京航空航天大学 | Tilt rotor mechanism, folding structure and aircraft using shape memory material |
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Application publication date: 20180320 |