CN106864746A - It is a kind of can VTOL the rotor canard configuration aircraft of tailstock formula three - Google Patents

It is a kind of can VTOL the rotor canard configuration aircraft of tailstock formula three Download PDF

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Publication number
CN106864746A
CN106864746A CN201710088828.0A CN201710088828A CN106864746A CN 106864746 A CN106864746 A CN 106864746A CN 201710088828 A CN201710088828 A CN 201710088828A CN 106864746 A CN106864746 A CN 106864746A
Authority
CN
China
Prior art keywords
wing
power set
tail
fuselage
vertical tail
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN201710088828.0A
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Chinese (zh)
Inventor
张子健
卢伟
杨会涛
龚喜盈
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Northwestern Polytechnical University
Xian Aisheng Technology Group Co Ltd
Original Assignee
Northwestern Polytechnical University
Xian Aisheng Technology Group Co Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Northwestern Polytechnical University, Xian Aisheng Technology Group Co Ltd filed Critical Northwestern Polytechnical University
Priority to CN201710088828.0A priority Critical patent/CN106864746A/en
Publication of CN106864746A publication Critical patent/CN106864746A/en
Pending legal-status Critical Current

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Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C29/00Aircraft capable of landing or taking-off vertically
    • B64C29/0008Aircraft capable of landing or taking-off vertically having its flight directional axis horizontal when grounded
    • B64C29/0016Aircraft capable of landing or taking-off vertically having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
    • B64C29/0025Aircraft capable of landing or taking-off vertically having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being fixed relative to the fuselage
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C39/00Aircraft not otherwise provided for
    • B64C39/12Canard-type aircraft
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C2201/00Unmanned aerial vehicles; Equipment therefor
    • B64C2201/02Unmanned aerial vehicles; Equipment therefor characterized by type of aircraft
    • B64C2201/021Airplanes, i.e. having wings and tail planes

Abstract

The invention discloses it is a kind of can VTOL the rotor canard configuration aircraft of tail sitting posture three, it is made up of fuselage, wing, canard, vertical tail and power set, the head of fuselage is provided with canard, and the two sides of tail of fuselage is wing, and vertical tail is provided with below afterbody;Wing tip position and vertical tail wing tip position are respectively arranged with power set, and power set are variable-pitch propeller.Trailing edge is provided with elevon, and vertical tail trailing edge is provided with rudder, and trailing edge of canard is provided with elevator.The wing tip of three rotor canard configuration aircraft, vertical tail wing tip and fuselage tail end collectively form four strong points, and in halted state, four strong points make aircraft vertically upright rest in ground;Aircraft vertical landing fast response time, with good stability during VTOL.Aircraft uses canard configuration, can fly so that fixed-wing mode is flat at a high speed, and the flight time is long, and with good maneuverability and mobility.

Description

It is a kind of can VTOL the rotor canard configuration aircraft of tailstock formula three
Technical field
The present invention relates to a kind of aircraft of VTOL, specifically, be related to it is a kind of can VTOL tail sitting posture three Rotor canard configuration aircraft.
Background technology
Flight Vehicle Design expert and researcher are attempting a kind of flight for being capable of short distance or VTOL of design always Device.To solve, Fixed Wing AirVehicle is limited by landing site and tiltrotor has that flying speed is slow, cruising time is short lacks Fall into, and existing tail sitting posture VTOL fixed-wing unmanned vehicle driving efficiency is low, the problem that wind resistance is poor.
At present in actual applications, unmanned vehicle is generally divided into Fixed Wing AirVehicle and rotor craft two types, Although the characteristics of conventional fixed-wing unmanned vehicle has fast speed, remote voyage and cruise time long, landing distance will High-quality runway is sought, landing is limited by geographical environment, it is impossible to carry out hovering, thus application is restricted;And revolve Wing unmanned vehicle can not limited in complicated narrow and small place VTOL by landing site, but rotor efficiency can not show a candle to The wing of fixed wing aircraft, power consumption is big, and flight resistance is big, thus influence flying speed and cruising time.
With the extensive use of unmanned vehicle, takeoff and landing performance and the duration performance requirement to unmanned vehicle are significantly carried Height, due to can the Fixed Wing AirVehicle of VTOL have the characteristics of Fixed Wing AirVehicle speed is fast, voyage is remote, the cruise time is long concurrently The ability of full landform landing can be carried out in the complexity such as mountain region, jungle, ship deck narrow regions with rotor craft, therefore, can The fixed-wing unmanned vehicle of VTOL has become the focus of research.
It is existing can the fixed-wing unmanned vehicle of VTOL include verting dynamical type and the class of tailstock formula two.Vert dynamical type VTOL fixed-wing unmanned vehicle, makes power realize from level to vertical mutual by tilting rotor or jet engine Conversion, VTOL and hovering are carried out when power direction is changed into vertical by overcoming gravity, by overcoming air when being changed into level Resistance flies before carrying out level.The shortcoming of this VTOL mode is that power inclining rotary mechanism can increase construction weight and complicated journey Degree, reduction reliability.V-22 " osprey " tiltrotor control difficulty such as the U.S. is big, and aircraft accident frequently occurs, and mechanism is multiple Miscellaneous and construction weight is big, reduces its flying quality.
The power direction of tailstock formula VTOL fixed-wing unmanned vehicle is fixed, without power inclining rotary mechanism but existing Tail sitting posture VTOL Fixed Wing AirVehicle there is open defect.Patent CN 204822068U disclose " a kind of tail sitting posture hang down Straight landing aircraft ", the technical scheme that the tailstock vertical takeoff and landing vehicle is used is that its aircraft body includes the main machine body wing Plate, main machine body wing plate is respectively socketed with fuselage wing plate component on two relative sides;The front portion of main machine body wing plate is provided with two electricity Machine, each motor connects a propeller by drive shaft, and the afterbody of main machine body wing plate is connected with two groups of rudder face components.It is not enough Part is VTOL and hovering phase, under propellerslip effect, operating torque is produced by pneumatic control surface deflection, is manipulated Efficiency is low, and wind resistance is poor.
The content of the invention
In order to avoid the deficiency that prior art is present, overcome fixed wing aircraft to be limited by landing site and deposited with heligyro In the defect that flying speed is slow, cruising time is short, the present invention propose it is a kind of can VTOL the rotor canard configuration of tail sitting posture three Aircraft.
The technical solution adopted for the present invention to solve the technical problems is:Including fuselage, wing, canard, vertical tail, dynamic Power apparatus, the head of the fuselage is provided with a pair of canards, and afterbody both sides are wing, are provided with below afterbody vertical Fin, and center line and the fuselage axis of vertical tail be located in same perpendicular;Wing tip position and vertical tail Wing tip position is respectively arranged with power set;Trailing edge is provided with elevon, and vertical tail trailing edge is provided with rudder, duck Wing trailing edge is provided with elevator;The wing tip of the wing, the wing tip of the vertical tail are collectively formed with the tail end of the fuselage Four strong points, in halted state, four strong points make aircraft vertically upright rest in ground;
The power set are three groups, wherein two groups of power set are bending moment propeller, power set are symmetrically mounted on two Side wing tip position, bending moment propeller and the wing tip whirlpool of wing tip reversely rotate, to reduce the induced drag of wing; Another set power set are cyclic pitch propeller, and power set are arranged on vertical tail wing tip position, and power set Rotating shaft is parallel with the axis of fuselage.
Battery or piston-mode motor are installed, battery motor drives power set, or logical in the fuselage Cross the dynamic driving power device of piston-mode motor.
Can VTOL the rotor canard configuration aircraft of tail sitting posture three fly VTOL, hovering and the low-speed operations stage It is, by power set together functioning equalization aircraft gravity, to keep total pulling force constant, by reducing on the wing tip of both sides Revolution speed of propeller/pitch, increases the revolution speed of propeller/pitch on vertical tail, while the propeller oar disk side on vertical tail Propeller reaction torque is offset to deflection, aircraft is faced upward, vice versa;Keep total pulling force constant, increase on the wing of left side Revolution speed of propeller/pitch, reduces the revolution speed of propeller/pitch on the wing of right side, while the propeller oar disk side on vertical tail Propeller reaction torque is offset to deflection, makes aircraft rolling to the right, vice versa;Keep total pulling force constant, by vertical tail On propeller rotation produce reaction torque, make vehicle yaw, vice versa.
Level flight stage is the aerodynamic lift balancing gravity produced by wing and canard, is produced by power set Propulsive force flies before overcoming air drag at a high speed, can be navigated long, oceangoing voyage flight, and the elevator on canard carry out pitch control, machine Aileron on the wing carries out rolling control, and the rudder on vertical tail carries out driftage control.
Beneficial effect
It is proposed by the present invention can VTOL the rotor canard configuration aircraft of tail sitting posture three, by fuselage, wing, canard, Vertical tail and power set are constituted, and the head of fuselage is provided with canard, and the two sides of tail of fuselage is wing, under afterbody Side is provided with vertical tail;Wing tip position and vertical tail wing tip position are respectively arranged with power set, and power set are Variable-pitch propeller.Trailing edge is provided with elevon, and vertical tail trailing edge is provided with rudder, and trailing edge of canard is provided with lifting Rudder.The wing tip of three rotor canard configuration aircraft, vertical tail wing tip and fuselage tail end collectively form four strong points, During halted state, four strong points make aircraft vertically upright rest in ground;Aircraft vertical landing fast response time, hangs down With good stability during straight landing.Aircraft uses canard configuration, can fly so that fixed-wing mode is flat at a high speed, the flight time It is long, and with good maneuverability and mobility.
The present invention can VTOL the rotor canard configuration aircraft of tail sitting posture three use VTOL mode, can be very big Reduce the requirement to landing site in degree.Aircraft adds bending moment propeller using three rotors, response speed faster, with good Maneuverability and wind resistance.Aircraft is flown during horizontal flight in fixed-wing mode, and energy ezpenditure is small, flight Speed is fast, and cruising time is long, and with good stability.
Brief description of the drawings
Below in conjunction with the accompanying drawings with implementation method to the present invention it is a kind of can VTOL the rotor canard configuration of tail sitting posture three fly Row device is described in further detail.
Fig. 1 be the present invention can VTOL the rotor canard configuration Flight Vehicle Structure schematic diagram of tail sitting posture three.
Fig. 2 be the present invention can VTOL the rotor canard configuration aircraft flight state top view of tail sitting posture three.
In figure:
1. power set of 2. wing of fuselage, 3. canard, 4. vertical tail 5.
Specific embodiment
The present embodiment be it is a kind of can VTOL the rotor canard configuration aircraft of tail sitting posture three.
Refering to Fig. 1, Fig. 2, the present embodiment can VTOL the rotor canard configuration aircraft of tail sitting posture three, including flight shape State is in the fuselage 1 of horizontal level, and fuselage 1 is streamlined structure, and a pair of canards 3, duck are symmetrically installed with the head both sides of fuselage 1 The trailing edge of the wing 3 is provided with elevator, and the afterbody of fuselage 1 is provided with a pair of wings 2, and wing is shoulder-wing configuration, with non-negative The upper counterangle, aileron is installed in the trailing edge of wing 2;A vertical tail 4 is provided with below the afterbody of fuselage 1, after vertical tail 4 Edge is provided with rudder.
The wing tip of wing 2, the wing tip of vertical tail 4 collectively form three strong points, or wing 2 wing tip, vertical tail 4 Wing tip and the tail end of fuselage 1 collectively form four strong points, ground state when, three strong points or four strong points make to fly Row device vertically upright rests in ground;By three strong points or this four strong points as aircraft landing fulcrum, nothing Undercarriage need to be additionally installed.
In the present embodiment, the wing tip of wing 2, the wing tip of vertical tail 4 and the tail end of fuselage 1 collectively form four supports Point.
In the present embodiment, power set 5 are three groups, wherein two groups of power set 5 are bending moment propeller, 5 pairs, power set Claim to be arranged on the wing tip position of both sides wing 2, bending moment propeller and the wingtip vortex of wing 2 of the wing tip of wing 2 are reversely rotated, to reduce machine The induced drag of the wing, improves pneumatic efficiency;Another set power set 5 are cyclic pitch propeller, and power set 5 are arranged on vertical Fin wing tip position, and the rotating shaft of power set 5 is parallel with the axis of fuselage 1.
Battery or piston-mode motor are installed, battery motor drives power set 5, or passes through in fuselage 1 The motor-driven driving power device 5 of piston engine.
The present embodiment can VTOL the rotor canard configuration aircraft of tail sitting posture three, the control mode of each state of flight is such as Under:
Stop the stage in ground:The wing tip of wing 2, the wing tip of vertical tail 4 and the tail end of fuselage 1 constitute four strong points, make flight Device rests in ground straight up.
VTOL, hovering and low-speed operations stage:It is, by power set 5 together functioning equalization aircraft gravity, to protect Hold that total pulling force is constant, by reducing the revolution speed of propeller/pitch on the wing tip of both sides wing 2, increase the propeller on vertical tail 4 Rotating speed/pitch, while propeller reaction torque is offset in the propeller oar disk lateral deflection on vertical tail 4, makes aircraft face upward, instead It is as the same;Keep total pulling force constant, increase the revolution speed of propeller/pitch on the wing 2 of left side, reduce the spiral on the wing 2 of right side Oar rotating speed/pitch, while propeller reaction torque is offset in the propeller oar disk lateral deflection on vertical tail 4, makes aircraft to the right Rolling, vice versa;Keep total pulling force constant, by the reaction torque that the propeller rotation on vertical tail 4 is produced, make aircraft Driftage, vice versa.
Level flight stage:It is the aerodynamic lift balancing gravity produced by wing 2 and canard 3, is produced by power set 5 Raw propulsive force flies before overcoming air drag at a high speed, can be navigated long, oceangoing voyage flight, and the elevator on canard 3 carry out pitching control System, the aileron on wing 2 carries out rolling control, and the rudder on vertical tail 4 carries out driftage control.

Claims (2)

1. it is a kind of can VTOL the rotor canard configuration aircraft of tail sitting posture three, it is characterised in that:Including fuselage, wing, duck The wing, vertical tail, power set, the head of the fuselage are provided with a pair of canards, and afterbody both sides are wing, afterbody Lower section be provided with vertical tail, and the center line of vertical tail is located in same perpendicular with fuselage axis;Wing tip Position and vertical tail wing tip position are respectively arranged with power set;Trailing edge is provided with elevon, vertical tail trailing edge Rudder is installed, trailing edge of canard is provided with elevator;The wing tip of the wing, the wing tip of the vertical tail and the fuselage Tail end collectively form four strong points, in halted state, four strong points make aircraft vertically upright rest in ground;
The power set are three groups, wherein two groups of power set are bending moment propeller, power set are symmetrically mounted on both sides machine Thriving tip position, bending moment propeller and the wing tip whirlpool of wing tip reversely rotate, to reduce the induced drag of wing;In addition One group of power set are cyclic pitch propeller, and power set are arranged on vertical tail wing tip position, and power set rotating shaft Axis with fuselage is parallel.
2. it is according to claim 1 can VTOL the rotor canard configuration aircraft of tail sitting posture three, it is characterised in that:Institute State and be provided with fuselage battery or piston-mode motor, battery motor drives power set, or is sent out by piston type Motivation moves driving power device.
CN201710088828.0A 2017-02-20 2017-02-20 It is a kind of can VTOL the rotor canard configuration aircraft of tailstock formula three Pending CN106864746A (en)

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Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108001679A (en) * 2017-11-30 2018-05-08 湖北航天飞行器研究所 Three shrouded propeller power modes can VTOL fixed-wing unmanned vehicle
CN108284950A (en) * 2017-11-30 2018-07-17 湖北航天飞行器研究所 Four shrouded propeller power modes can VTOL fixed-wing unmanned vehicle
CN109606674A (en) * 2018-12-26 2019-04-12 中南大学 Tail sitting posture vertical take-off and landing drone and its control system and control method
CN109649650A (en) * 2018-12-29 2019-04-19 成都纵横大鹏无人机科技有限公司 Canard configuration tailstock formula vertically taking off and landing flyer
CN109795682A (en) * 2018-12-10 2019-05-24 清华大学 A kind of efficient tail sitting posture VTOL Fixed Wing AirVehicle and its 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
CN112722264A (en) * 2021-01-12 2021-04-30 中国人民解放军国防科技大学 Tail sitting type vertical take-off and landing unmanned aerial vehicle
US11001378B2 (en) 2016-08-08 2021-05-11 Jetoptera, Inc. Configuration for vertical take-off and landing system for aerial vehicles
CN113306710A (en) * 2021-07-28 2021-08-27 西安羚控电子科技有限公司 Tube type launching composite wing unmanned aerial vehicle and method for realizing roll action
US11148801B2 (en) 2017-06-27 2021-10-19 Jetoptera, Inc. Configuration for vertical take-off and landing system for aerial vehicles

Citations (3)

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EP1114772A1 (en) * 1999-12-29 2001-07-11 Gkn Westland Helicopters Limited VTOL aircraft with variable wing sweep
CN102133926A (en) * 2011-03-08 2011-07-27 上海大学 Tailstock type vertical take-off and landing unmanned aerial vehicle
CN106184738A (en) * 2016-06-17 2016-12-07 北京航空航天大学 A kind of dismountable tailstock formula VUAV

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1114772A1 (en) * 1999-12-29 2001-07-11 Gkn Westland Helicopters Limited VTOL aircraft with variable wing sweep
CN102133926A (en) * 2011-03-08 2011-07-27 上海大学 Tailstock type vertical take-off and landing unmanned aerial vehicle
CN106184738A (en) * 2016-06-17 2016-12-07 北京航空航天大学 A kind of dismountable tailstock formula VUAV

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
US11001378B2 (en) 2016-08-08 2021-05-11 Jetoptera, Inc. Configuration for vertical take-off and landing system for aerial vehicles
US11148801B2 (en) 2017-06-27 2021-10-19 Jetoptera, Inc. Configuration for vertical take-off and landing system for aerial vehicles
CN108001679A (en) * 2017-11-30 2018-05-08 湖北航天飞行器研究所 Three shrouded propeller power modes can VTOL fixed-wing unmanned vehicle
CN108284950A (en) * 2017-11-30 2018-07-17 湖北航天飞行器研究所 Four shrouded propeller power modes can VTOL fixed-wing unmanned vehicle
CN109795682A (en) * 2018-12-10 2019-05-24 清华大学 A kind of efficient tail sitting posture VTOL Fixed Wing AirVehicle and its control method
CN109606674A (en) * 2018-12-26 2019-04-12 中南大学 Tail sitting posture vertical take-off and landing drone and its control system and control method
CN109649650A (en) * 2018-12-29 2019-04-19 成都纵横大鹏无人机科技有限公司 Canard configuration tailstock formula vertically taking off and landing flyer
CN112722264A (en) * 2021-01-12 2021-04-30 中国人民解放军国防科技大学 Tail sitting type vertical take-off and landing unmanned aerial vehicle
CN113306710A (en) * 2021-07-28 2021-08-27 西安羚控电子科技有限公司 Tube type launching composite wing unmanned aerial vehicle and method for realizing roll action

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