CN201923320U - Twin-engine vertical take-off and landing fixed-wing unmanned aerial vehicle - Google Patents

Twin-engine vertical take-off and landing fixed-wing unmanned aerial vehicle Download PDF

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Publication number
CN201923320U
CN201923320U CN2011200097278U CN201120009727U CN201923320U CN 201923320 U CN201923320 U CN 201923320U CN 2011200097278 U CN2011200097278 U CN 2011200097278U CN 201120009727 U CN201120009727 U CN 201120009727U CN 201923320 U CN201923320 U CN 201923320U
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CN
China
Prior art keywords
wing
aerial vehicle
unmanned aerial
twin
aircraft
Prior art date
Application number
CN2011200097278U
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Chinese (zh)
Inventor
杨苡
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杨苡
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Priority to CN2011200097278U priority Critical patent/CN201923320U/en
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Publication of CN201923320U publication Critical patent/CN201923320U/en

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Abstract

The utility model relates to a twin-engine vertical take-off and landing fixed-wing unmanned aerial vehicle, which is characterized in that: the whole body adopts a canard pneumatic configuration, and canard winglets are positioned at the front side of a main fuselage; main wings are positioned at the back side of the fuselage, and two engines with propellers are arranged at the tips of the main wings; backward swept H-shaped vertical tails are simultaneously arranged on nacelles of the engines at the wing tips, and take-off and landing pillars are arranged at the tops of the H-shaped vertical tails; and movable rudder surfaces are arranged on the back edges of the H-shaped vertical tails, and elevons are arranged at the outer sides of the back edges of the main wings. The unmanned aerial vehicle can vertically take off and land in a very small space like a helicopter, also can hover over the air to complete special observation and reconnaissance missions, and also can fly as fast as a fixed-wing aircraft. The unmanned aerial vehicle does not need an airport runway normally used by the fixed-wing aircraft, without catapults and parachutes, so the use is convenient, and the cost is lower; and the whole structure is simple and the manufacturing cost is low, and so the unmanned aerial vehicle has obvious cost price advantages compared with the helicopter, a tiltrotor and the like.

Description

Twin-engined vertical takeoff and landing fixed-wing unmanned planes
Technical field
The utility model relate to a kind of can be as the such vertical and landing takeoff of helicopter and hovering flight and can be as the unmanned aerial vehicle of fixed wing aircraft high-performance cruise flight.
Background technology
Its most special-purpose ejector catapult-assisted take-off that needs of taking off of fixed-wing unmanned plane in the past, or need one than long straight takeoff runway rolling start, need special-purpose parachute to cooperate buffer air bag to carry out parachuting in the time of landing mostly, perhaps adopting special-purpose arresting net to reclaim, is exactly to land with sliding race of special-purpose takeoff runway in addition.All these has caused conventional fixed-wing unmanned plane to take off and land need possess more limiting condition, causes it to use alerting ability to reduce, and use cost is higher.Though and vertical takeoff and landing (VTOL) easily of common depopulated helicopter and hovering flight are still because its complex structure, but the main rotor of its feathering and require the tail rotor assembly of displacement to need the movable a lot of manufacture difficulty of precision parts big equally, maintaining technical requirements height, face the cost problem of higher equally, and helicopter is because its principle and structural intrinsic factor cause its flying speed relatively low.
The utility model content
The purpose of this utility model be to provide a kind of can be as the such vertical and landing takeoff of helicopter and hovering flight and can be as the unmanned aerial vehicle of fixed wing aircraft high-performance cruise flight.
To achieve these goals, the technical solution adopted in the utility model is: twin-engined vertical takeoff and landing fixed-wing unmanned planes, it is characterized in that: complete machine adopts canard aerodynamic arrangement, the canard winglet is positioned at the fuselage front side, host wing is positioned at the fuselage rear side, the wing of host wing is installed two driving engines that screw propeller is housed slightly, the H shape vertical tail of sweepback is installed on the wing engine nacelle slightly simultaneously, top at this H shape vertical tail is equipped with the pillar that rises and falls, trailing edge is equipped with movable direction rudder face, and the host wing trailing edge outside is equipped with elevon.This host wing is trapezoidal or rectangle.This screw propeller is a tractor airscrew.
The beneficial effects of the utility model: the beneficial effects of the utility model are that it can be as helicopter at very narrow and small place vertical and landing takeoff, can also hover and finish special observation and reconnaissance mission in the air, can also quick flight as fixed wing aircraft, it does not need fixed wing aircraft airfield runway commonly used, need not ejector and parachute, practical and convenient cost is lower, its complete machine structure is simple, and low cost of manufacture is compared helicopter and tiltrotor etc. and had tangible cost of price advantage.
Description of drawings
Fig. 1 is to Figure 4 shows that the utility model adopts the integral structure scheme drawing of the twin-engined vertical takeoff and landing fixed-wing unmanned planes of canard aerodynamic arrangement.
The scheme drawing of the structure of each operation of components process when Fig. 5 is the up process of aircraft.
The scheme drawing of the structure of each operation of components process when Fig. 6 is the descending process of aircraft.
Fig. 7 is the scheme drawing of the structure of each operation of components process in the aircraft lift-over process to the right.
Fig. 8 is the scheme drawing of the structure of each operation of components process in the aircraft lift-over process to the left.
Fig. 9 is the aircraft scheme drawing of the structure of each operation of components process in the tilting procedure to the right.
Figure 10 is the aircraft scheme drawing of the structure of each operation of components process in the tilting procedure to the left.
The specific embodiment
The utility model proposes a kind of can be as the such vertical and landing takeoff of helicopter and hovering flight and can be as the unmanned aerial vehicle of fixed wing aircraft high-performance cruise flight.Its structure sees also Fig. 1 to shown in Figure 4, and its complete machine adopts canard aerodynamic arrangement, and canard winglet 3 is positioned at fuselage 1 front side, and watch-dog cabin 2 is positioned at the below of two canard winglets, 3 next door fuselage 1, and host wing 4 trapezoidal or rectangle is positioned at the fuselage rear side.The wing of host wing 4 is installed two driving engines that tractor airscrew 5 is housed slightly, the H shape vertical tail 7 of sweepback is installed on the wing engine nacelle 6 slightly simultaneously, top at this H shape vertical tail 7 is equipped with the pillar 10 that rises and falls, and trailing edge is equipped with movable direction rudder face 9.The host wing 4 trailing edges outsides is equipped with elevon 8, and is shared by the mixing mode, plays the effect of lifting rudder face when movable rudder face 9 deflections up or down simultaneously of host wing 4 both sides, for complete machine provides pitch control subsystem moment.As shown in Figure 5 and Figure 6, when the rudder face of both sides upward deflects simultaneously, make whole aircraft obtain nose-up pitching moment under the combined action of this rudder face gas washing stream under the wind stream in when flight and screw propeller, this moment, aircraft can come back upwards, as shown in Figure 5.When the rudder face of both sides deflects down simultaneously, make whole aircraft obtain nose-down pitching moment under the effect of this rudder face gas washing stream under the wind stream in when flight and screw propeller, this moment, aircraft can be bowed downwards.And upwards play aileron during the downward differential deflection of another side on one side when the movable rudder face of host wing both sides, for complete machine provides the lift-over control torque.As shown in Figure 7 and Figure 8.When if left side rudder face downward bias when visual tail direction then right side rudder face upward deflect, the left side rudder face can produce the upper lifting force square under the following gas washing stream combined action of the wind stream in when flight and screw propeller, and the right side rudder face can produce under the following gas washing stream combined action of the wind stream in when flight and screw propeller and press down moment, in the combined action of the moment of this left and right sides different directions lift-over to the right of getting off the plane, as shown in Figure 7.If the left side rudder face upward deflects and right side rudder face when deflecting down when visual tail direction, can produce under the combined action of left side rudder face gas washing stream under the wind stream in when flight and screw propeller and press down moment, and can produce the upper lifting force square under the combined action of right side rudder face gas washing stream under the wind stream in when flight and screw propeller, in the combined action of the moment of this left and right sides different directions lift-over to the left of getting off the plane.As shown in Figure 8.
This H shape vertical tail 7 plays the direction stabilator, the effect of yaw rudder and alighting gear simultaneously.This direction rudder face 9 can only be simultaneously synchronous to same direction deflection, when the four direction rudder 9 of seeing the left and right sides from the aircraft back simultaneously to the right during deflection, complete machine can produce yawing moment to the right under the combined action of the wind stream under screw propeller when gas washing stream and flight, this moment, plane nose can tilt to the right, as shown in Figure 9.When the four direction rudder 9 of seeing the left and right sides from the aircraft back simultaneously to the left during deflection, complete machine can produce yawing moment to the left under the combined action of the wind stream under screw propeller when gas washing stream and flight, and this moment, plane nose can tilt to the left.As shown in figure 10.Aircraft when vertical takeoff and landing since low its control of flying speed main rely under the screw propeller gas washing stream to act on respectively to control produce control torque on the rudder face and finish.When aircraft was in that level is flat at a high speed to fly, because flying speed is fast, the control torque that the combined action of gas washing stream produces on each control rudder face under wind stream the when control of this moment mainly relies on flight and the screw propeller was finished.
The twin-engined vertical takeoff and landing fixed-wing of the utility model unmanned plane four pillars 10 that rise and fall by H T tail 7 tops when taking off support vertical being parked on the ground of whole fuselage.Driving two tractor airscrews, the 5 generations power that draws high vertically upward behind the engine starting takes off vertically whole aircraft, aircraft also can keep perpendicular attitude to hover in the air, this moment, two screw propellers provided lift to complete machine, as long as the lift that two screw propellers produce equals or the own wt that is slightly larger than aircraft just can guarantee that hang is aerial.And thereby the attitude of aircraft control relies on screw propeller to rotate gas washing stream under the brute force that produces to act on and make complete machine produce around fuselage X on the yaw rudder rudder face of the elevon in the host wing trailing edge outside and H shape vertical tail trailing edge; Y; the rotation control torque that Z is three, thus the deflection angles by these control rudder faces of instant and trickle adjustment make complete machine vertical hover or the process of vertical drift motion at a slow speed in keep dynamical equilibrium.
Need do the fast flat engine speed that only need strengthen when flying when the twin-engined vertical takeoff and landing fixed-wing of the utility model unmanned plane makes the vertical acceleration of aircraft control elevating rudder then to adjust attitude by aircraft and become level flight condition, the aircraft of this moment just becomes the fixed wing aircraft of the canard aerodynamic arrangement of a routine fully, aircraft relies on host wing and preposition fixed type canard that lifting flight is provided, and the screw propeller of both sides only provides the power that draws in for aircraft.The yaw rudder of elevon on the aircraft and vertical tail trailing edge provides around fuselage X for complete machine, Y, the rotation control torque that Z is three.
Send out only need put down when vertical takeoff and landing fixed-wing unmanned planes need land and fly to overhead back, the zone of waiting to land and increase engine speed and make complete machine quicken to control then elevating rudder aircraft is come back up to the attitude of climbing vertically upward when the utility model is two, can progressively reduce engine speed this moment and reduce the lift of screw propeller and control each rudder face and decelerating to stable hovering until aircraft, then further slightly inching reduce engine speed and make lift be slightly less than vertical reductions height that aircraft deadweight aircraft just can be at a slow speed until the ground of landing.

Claims (3)

1. twin-engined vertical takeoff and landing fixed-wing unmanned planes, it is characterized in that: complete machine adopts canard aerodynamic arrangement, the canard winglet is positioned at the fuselage front side, host wing is positioned at the fuselage rear side, the wing of host wing is installed two driving engines that screw propeller is housed slightly, and the H shape vertical tail of sweepback is installed on the wing engine nacelle slightly simultaneously, at the top of this H shape vertical tail the pillar that rises and falls is installed, trailing edge is equipped with movable direction rudder face, and the host wing trailing edge outside is equipped with elevon.
2. twin-engined vertical takeoff and landing fixed-wing unmanned plane as claimed in claim 1, it is characterized in that: this host wing is trapezoidal or rectangle.
3. twin-engined vertical takeoff and landing fixed-wing unmanned plane as claimed in claim 1, it is characterized in that: this screw propeller is a tractor airscrew.
CN2011200097278U 2011-01-13 2011-01-13 Twin-engine vertical take-off and landing fixed-wing unmanned aerial vehicle CN201923320U (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN2011200097278U CN201923320U (en) 2011-01-13 2011-01-13 Twin-engine vertical take-off and landing fixed-wing unmanned aerial vehicle

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN2011200097278U CN201923320U (en) 2011-01-13 2011-01-13 Twin-engine vertical take-off and landing fixed-wing unmanned aerial vehicle

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CN201923320U true CN201923320U (en) 2011-08-10

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Cited By (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102514712A (en) * 2011-12-07 2012-06-27 上海大学 Vertical take-off and landing aircraft
CN102849211A (en) * 2012-09-28 2013-01-02 宋新民 Variable power vertical short-distance takeoff landing aircraft with fixed wings
CN102941917A (en) * 2012-10-26 2013-02-27 覃黎 Micro aircraft carrier
CN102991672A (en) * 2012-05-18 2013-03-27 宋新民 Variable power wing vertical short-range taking off and landing aircraft
WO2013056492A1 (en) * 2011-10-17 2013-04-25 Tian Yu Composite aircraft consisting of fixed-wing and electrically driven propellers and having helicopter functions
CN103318410A (en) * 2013-07-05 2013-09-25 西北工业大学 Vertical take-off and landing micro aerial vehicle without control surface
CN103640696A (en) * 2013-12-05 2014-03-19 新誉集团有限公司 Vertical touchdown type unmanned aerial vehicle and control method thereof
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
CN105346715A (en) * 2015-09-29 2016-02-24 上海圣尧智能科技有限公司 Vertical take-off and landing unmanned plane
CN105366049A (en) * 2015-11-24 2016-03-02 中国航空工业集团公司沈阳飞机设计研究所 Vertical takeoff and landing unmanned aerial vehicle
CN105620741A (en) * 2016-02-24 2016-06-01 成都方舟智控科技有限公司 Aircraft and control method thereof
CN105818981A (en) * 2016-04-06 2016-08-03 江富余 Helicopter with rotor, fixed wing and propellers
CN105905295A (en) * 2016-06-14 2016-08-31 临沂高新区翔鸿电子科技有限公司 Vertical take-off and landing fixed wing aircraft
CN106114853A (en) * 2016-08-09 2016-11-16 烟台中飞海装科技有限公司 A kind of push-button aircraft
CN106114854A (en) * 2016-08-09 2016-11-16 烟台中飞海装科技有限公司 A kind of push-button aircraft
CN106275389A (en) * 2016-10-19 2017-01-04 吴瑞霞 A kind of control aircraft pitch, the system turned on one's side, go off course
CN106428548A (en) * 2016-10-12 2017-02-22 曹萍 Vertical take-off and landing unmanned aerial vehicle
CN106516097A (en) * 2016-10-19 2017-03-22 吴瑞霞 Unpiloted aircraft
CN106628115A (en) * 2016-11-25 2017-05-10 烟台南山学院 Four-duct flying-wing type unmanned aerial vehicle
CN107323660A (en) * 2017-06-30 2017-11-07 马鞍山市赛迪智能科技有限公司 A kind of VTOL method of dalta wing unmanned plane
CN108263594A (en) * 2018-01-31 2018-07-10 曹蔚萌 A kind of bladeless fan power vertical take-off and landing drone
US10464668B2 (en) 2015-09-02 2019-11-05 Jetoptera, Inc. Configuration for vertical take-off and landing system for aerial vehicles
CN110758727A (en) * 2019-11-26 2020-02-07 邹雯 Unmanned aerial vehicle with synchronous folding mechanism of multimachine wing
CN111003172A (en) * 2018-10-08 2020-04-14 苏郁夫 Jet type vertical lifting pneumatic system
CN111587208A (en) * 2018-01-03 2020-08-25 株式会社爱隆未来 Flying object and flying method for flying object
US10875658B2 (en) 2015-09-02 2020-12-29 Jetoptera, Inc. Ejector and airfoil configurations

Cited By (33)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013056492A1 (en) * 2011-10-17 2013-04-25 Tian Yu Composite aircraft consisting of fixed-wing and electrically driven propellers and having helicopter functions
CN102514712A (en) * 2011-12-07 2012-06-27 上海大学 Vertical take-off and landing aircraft
CN102991672A (en) * 2012-05-18 2013-03-27 宋新民 Variable power wing vertical short-range taking off and landing aircraft
CN102849211A (en) * 2012-09-28 2013-01-02 宋新民 Variable power vertical short-distance takeoff landing aircraft with fixed wings
CN102941917A (en) * 2012-10-26 2013-02-27 覃黎 Micro aircraft carrier
CN103318410A (en) * 2013-07-05 2013-09-25 西北工业大学 Vertical take-off and landing micro aerial vehicle without control surface
CN103640696B (en) * 2013-12-05 2016-06-08 新誉集团有限公司 Hang down and drop unmanned plane and control method thereof
CN103640696A (en) * 2013-12-05 2014-03-19 新誉集团有限公司 Vertical touchdown type unmanned aerial vehicle and control method thereof
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
CN104648656B (en) * 2015-02-12 2017-02-01 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
US10464668B2 (en) 2015-09-02 2019-11-05 Jetoptera, Inc. Configuration for vertical take-off and landing system for aerial vehicles
US10875658B2 (en) 2015-09-02 2020-12-29 Jetoptera, Inc. Ejector and airfoil configurations
CN105346715A (en) * 2015-09-29 2016-02-24 上海圣尧智能科技有限公司 Vertical take-off and landing unmanned plane
CN105366049A (en) * 2015-11-24 2016-03-02 中国航空工业集团公司沈阳飞机设计研究所 Vertical takeoff and landing unmanned aerial vehicle
CN105620741A (en) * 2016-02-24 2016-06-01 成都方舟智控科技有限公司 Aircraft and control method thereof
CN105818981A (en) * 2016-04-06 2016-08-03 江富余 Helicopter with rotor, fixed wing and propellers
CN105905295A (en) * 2016-06-14 2016-08-31 临沂高新区翔鸿电子科技有限公司 Vertical take-off and landing fixed wing aircraft
CN106114854B (en) * 2016-08-09 2019-06-25 烟台中飞海装科技有限公司 A kind of push-button aircraft
CN106114854A (en) * 2016-08-09 2016-11-16 烟台中飞海装科技有限公司 A kind of push-button aircraft
CN106114853A (en) * 2016-08-09 2016-11-16 烟台中飞海装科技有限公司 A kind of push-button aircraft
CN106114853B (en) * 2016-08-09 2019-05-10 烟台中飞海装科技有限公司 A kind of push-button aircraft
CN106428548A (en) * 2016-10-12 2017-02-22 曹萍 Vertical take-off and landing unmanned aerial vehicle
CN106428548B (en) * 2016-10-12 2019-09-27 曹萍 A kind of vertical take-off and landing unmanned aerial vehicle
CN106516097A (en) * 2016-10-19 2017-03-22 吴瑞霞 Unpiloted aircraft
CN106275389A (en) * 2016-10-19 2017-01-04 吴瑞霞 A kind of control aircraft pitch, the system turned on one's side, go off course
CN106628115A (en) * 2016-11-25 2017-05-10 烟台南山学院 Four-duct flying-wing type unmanned aerial vehicle
CN107323660A (en) * 2017-06-30 2017-11-07 马鞍山市赛迪智能科技有限公司 A kind of VTOL method of dalta wing unmanned plane
CN107323660B (en) * 2017-06-30 2020-01-17 马鞍山市赛迪智能科技有限公司 Vertical take-off and landing method of delta-wing unmanned aerial vehicle
CN111587208A (en) * 2018-01-03 2020-08-25 株式会社爱隆未来 Flying object and flying method for flying object
CN108263594B (en) * 2018-01-31 2019-05-10 曹蔚萌 A kind of bladeless fan power vertical take-off and landing drone
CN108263594A (en) * 2018-01-31 2018-07-10 曹蔚萌 A kind of bladeless fan power vertical take-off and landing drone
CN111003172A (en) * 2018-10-08 2020-04-14 苏郁夫 Jet type vertical lifting pneumatic system
CN110758727A (en) * 2019-11-26 2020-02-07 邹雯 Unmanned aerial vehicle with synchronous folding mechanism of multimachine wing

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Effective date of registration: 20170222

Address after: Xiaoshan District of Hangzhou City, Zhejiang province 310000 Xintang Branch Park South Road No. 3089 show

Patentee after: Hangzhou Xiang Rong Intelligent Technology Co., Ltd.

Address before: 102200 Beijing city Changping District Ming Dynasty Tombs Park No. 19 tailing

Patentee before: Yang Yi

CF01 Termination of patent right due to non-payment of annual fee
CF01 Termination of patent right due to non-payment of annual fee

Granted publication date: 20110810

Termination date: 20180113