CN105923153A - Fixed-wing aircraft capable of vertically taking off and landing - Google Patents
Fixed-wing aircraft capable of vertically taking off and landing Download PDFInfo
- Publication number
- CN105923153A CN105923153A CN201610337309.9A CN201610337309A CN105923153A CN 105923153 A CN105923153 A CN 105923153A CN 201610337309 A CN201610337309 A CN 201610337309A CN 105923153 A CN105923153 A CN 105923153A
- Authority
- CN
- China
- Prior art keywords
- fixed
- fuselage
- controller
- belt pulley
- motor
- 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
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
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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
- B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
- B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
- B64C29/0033—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft 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 tiltable relative to the fuselage
Abstract
The invention relates to the field of fixed-wing aircrafts, in particular to a fixed-wing aircraft capable of vertically taking off and landing. The fixed-wing aircraft is designed mainly for solving the problem that existing fixed-wing aircrafts have high requirements for take-off and landing sites. The fixed-wing aircraft comprises an aircraft body, a vertical tail wing is fixed to the aircraft body, and a rudder is mounted on the vertical tail wing. Lifting tail wings are mounted on the tail of the aircraft body, and ailerons are mounted on the two sides of the aircraft body. A motor is mounted in each deputy propeller mounting hole in the aircraft body, and deputy propellers are arranged on output shafts of the corresponding motors. A starting and power-generating all-in-one machine is mounted in a main propeller mounting hole through a servo rudder and comprises an engine and a starter. Two overrunning clutches and a main propeller are arranged on a power output shaft of the engine, a gear on an output shaft of the starter is engaged with a gear on the overrunning clutch A, and a belt wheel on the overrunning clutch B is connected with a belt wheel on the starter through a belt. An oil tank and a flying controller are arranged on the aircraft body. The fixed-wing aircraft has the advantages of being capable of vertically taking off and landing or hovering, and having low requirements for take-off and landing sites.
Description
Technical field:
The present invention relates to Fixed Wing AirVehicle field, be specifically related to a kind of can the Fixed Wing AirVehicle of VTOL.
Background technology:
Existing Fixed Wing AirVehicle has outstanding flying power and high-performance cruise, but it is disadvantageous in that inertia is bigger, it is necessary to could lift through longer runway, landing site is required height, rise, fall is slided during running and is easily broken down, malfunction, it is impossible to hovering.
Summary of the invention:
The technical problem to be solved is to provide and a kind of requires low to landing site, flexible operation, it is possible to aloft hover can the Fixed Wing AirVehicle of VTOL.
Above-mentioned purpose is achieved in that it includes fuselage, vertical tail is fixed on the afterbody of fuselage, it is characterized in that: rudder is contained in the rear end of vertical tail by Servo-controller, two lifting empennages are arranged on the afterbody of vertical tail both sides respectively by respective Servo-controller, two ailerons are arranged on the both sides of fuselage respectively by various Servo-controllers, fuselage is provided with four secondary propeller installing holes, a motor is had in each secondary propeller installing hole, described each motor is fixed on fuselage by respective connecting rod respectively, connect on the power output shaft of each motor and have secondary propeller, described secondary propeller be arranged in parallel with fuselage, waist has main screw installing hole, start, power generation all-in-one machine is arranged in main screw installing hole by Servo-controller,
Start, power generation all-in-one machine includes electromotor and starter motor, equipped with main screw on one power output shaft of electromotor, equipped with two freewheel clutches on another power output shaft of electromotor, two freewheel clutches are clutch A and clutch B respectively, equipped with the first gear on starter motor output shaft, freewheel clutch A outer cover is provided with the second gear, the first described gear and the second gear are meshed, freewheel clutch B outer cover is provided with the first belt pulley, first belt pulley is connected fixing with freewheel clutch B, starter motor outer cover is provided with the second belt pulley, second belt pulley is connected fixing with starter motor, first belt pulley and the second belt pulley are connected by belt, starter motor is connected by wire with electricity generating controller, electricity generating controller is connected by wire with accumulator；Described electricity generating controller and accumulator are all located on fuselage, it is connected by wire between accumulator with each motor, being further fixed on fuel tank and flight controller on fuselage, be connected by oil pipe between fuel tank with electromotor, flight controller is connected by wire with each Servo-controller.
The invention have the advantage that owing to main screw is arranged on the engine power output shaft of startup, power generation all-in-one machine, start, power generation all-in-one machine is arranged in main screw installing hole by Servo-controller, so start, power generation all-in-one machine main screw can be driven to vert, when main screw is vertical with fuselage, aircraft is high-speed flight state, between main screw with fuselage parallel time, aircraft can VTOL or hovering, landing site is required low by it, fault, flexible operation it is not susceptible to during landing.
Accompanying drawing illustrates:
Fig. 1 is the high-speed flight status architecture schematic diagram of the present invention；
Fig. 2 is the VTOL status architecture schematic diagram of the present invention；
Fig. 3 is startup, the structural representation of power generation all-in-one machine in the present invention amplified.
Detailed description of the invention:
With reference to Fig. 13, it includes fuselage 1, vertical tail 2 is fixed on the afterbody of fuselage, it is characterized in that: rudder 3 is contained in the rear end of vertical tail by Servo-controller 4, two lifting empennages 5 are arranged on the afterbody of vertical tail both sides respectively by respective Servo-controller, two ailerons 6 are arranged on the both sides of fuselage respectively by various Servo-controllers, fuselage is provided with four secondary propeller installing holes 9, a motor 7 is had in each secondary propeller installing hole, described each motor is fixed on fuselage by respective connecting rod respectively, connect on the power output shaft of each motor and have secondary propeller 8, described secondary propeller be arranged in parallel with fuselage, waist has main screw installing hole 10, start, power generation all-in-one machine 11 is arranged in main screw installing hole by Servo-controller,
nullStart、Power generation all-in-one machine includes electromotor 11 1 and starter motor 11 2，Equipped with main screw 12 on one power output shaft of electromotor，Equipped with two freewheel clutches on another power output shaft of electromotor，Two freewheel clutches are clutch A11 3 and clutch B11 4 respectively，Equipped with the first gear 11 5 on starter motor output shaft，Freewheel clutch A outer cover is provided with the second gear 11 6，The first described gear and the second gear are meshed，Freewheel clutch B outer cover is provided with the first belt pulley 11 7，First belt pulley is connected fixing with freewheel clutch B，Starter motor outer cover is provided with the second belt pulley 11 8，Second belt pulley is connected fixing with starter motor，First belt pulley and the second belt pulley are connected by belt，Starter motor is connected by wire with electricity generating controller 13，Electricity generating controller is connected by wire with accumulator 14；Described electricity generating controller and accumulator are all located on fuselage, it is connected by wire between accumulator with each motor, being further fixed on fuel tank 15 and flight controller 16 on fuselage, be connected by oil pipe between fuel tank with electromotor, flight controller is connected by wire with each Servo-controller.
Claims (1)
- null1. one kind can the Fixed Wing AirVehicle of VTOL，Including fuselage (1)，Vertical tail (2) is fixed on the afterbody of fuselage，It is characterized in that: rudder (3) is contained in the rear end of vertical tail by Servo-controller (4)，Two liftings empennage (5) are arranged on the afterbody of vertical tail both sides respectively by respective Servo-controller，Two ailerons (6) are arranged on the both sides of fuselage respectively by various Servo-controllers，Fuselage is provided with four secondary propeller installing holes (9)，A motor (7) is had in each secondary propeller installing hole，Described each motor is fixed on fuselage by respective connecting rod respectively，Connect on the power output shaft of each motor and have secondary propeller (8)，Described secondary propeller be arranged in parallel with fuselage，Waist has main screw installing hole (10)，Start、Power generation all-in-one machine (11) is arranged in main screw installing hole by Servo-controller，nullStart、Power generation all-in-one machine includes electromotor (11 1) and starter motor (11 2)，Equipped with main screw (12) on one power output shaft of electromotor，Equipped with two freewheel clutches on another power output shaft of electromotor，Two freewheel clutches are clutch A(11 3 respectively) and clutch B(11 4)，Equipped with the first gear (11 5) on starter motor output shaft，Freewheel clutch A outer cover is provided with the second gear (11 6)，The first described gear and the second gear are meshed，Freewheel clutch B outer cover is provided with the first belt pulley (11 7)，First belt pulley is connected fixing with freewheel clutch B，Starter motor outer cover is provided with the second belt pulley (11 8)，Second belt pulley is connected fixing with starter motor，First belt pulley and the second belt pulley are connected by belt，Starter motor is connected by wire with electricity generating controller (13)，Electricity generating controller is connected by wire with accumulator (14)；Described electricity generating controller and accumulator are all located on fuselage, it is connected by wire between accumulator with each motor, being further fixed on fuel tank (15) and flight controller (16) on fuselage, be connected by oil pipe between fuel tank with electromotor, flight controller is connected by wire with each Servo-controller.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610337309.9A CN105923153A (en) | 2016-05-21 | 2016-05-21 | Fixed-wing aircraft capable of vertically taking off and landing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610337309.9A CN105923153A (en) | 2016-05-21 | 2016-05-21 | Fixed-wing aircraft capable of vertically taking off and landing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105923153A true CN105923153A (en) | 2016-09-07 |
Family
ID=56841818
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610337309.9A Pending CN105923153A (en) | 2016-05-21 | 2016-05-21 | Fixed-wing aircraft capable of vertically taking off and landing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105923153A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107244415A (en) * | 2017-05-24 | 2017-10-13 | 彩虹无人机科技有限公司 | The composite power rotor wing unmanned aerial vehicle that a kind of fuselage can vert |
| CN110217391A (en) * | 2019-05-31 | 2019-09-10 | 沈阳迪智科技有限公司 | A kind of oil electric mixed dynamic VTOL sweepforward fixed-wing unmanned plane |
| CN114148517A (en) * | 2021-12-30 | 2022-03-08 | 四川文理学院 | Vertical take-off and landing high-speed unmanned aerial vehicle and control method thereof |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7874513B1 (en) * | 2005-10-18 | 2011-01-25 | Smith Frick A | Apparatus and method for vertical take-off and landing aircraft |
| CN102042147A (en) * | 2009-10-20 | 2011-05-04 | 通用汽车环球科技运作公司 | Torque transmitting mechanism of an internal combustion engine, a vehicle and a method of transmitting torque |
| CN102120489A (en) * | 2011-02-28 | 2011-07-13 | 南昌航空大学 | Tilt ducted unmanned aerial vehicle |
| CN102897317A (en) * | 2011-07-29 | 2013-01-30 | 奥格斯塔韦斯兰股份公司 | Convertiplane |
| CN105480418A (en) * | 2015-12-17 | 2016-04-13 | 北京猎鹰无人机科技有限公司 | Ducted fixed-wing oil-electric hybrid unmanned aircraft |
| CN205770148U (en) * | 2016-05-21 | 2016-12-07 | 辽宁辽飞航空科技有限公司 | A kind of can the Fixed Wing AirVehicle of VTOL |
-
2016
- 2016-05-21 CN CN201610337309.9A patent/CN105923153A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7874513B1 (en) * | 2005-10-18 | 2011-01-25 | Smith Frick A | Apparatus and method for vertical take-off and landing aircraft |
| CN102042147A (en) * | 2009-10-20 | 2011-05-04 | 通用汽车环球科技运作公司 | Torque transmitting mechanism of an internal combustion engine, a vehicle and a method of transmitting torque |
| CN102120489A (en) * | 2011-02-28 | 2011-07-13 | 南昌航空大学 | Tilt ducted unmanned aerial vehicle |
| CN102897317A (en) * | 2011-07-29 | 2013-01-30 | 奥格斯塔韦斯兰股份公司 | Convertiplane |
| CN105480418A (en) * | 2015-12-17 | 2016-04-13 | 北京猎鹰无人机科技有限公司 | Ducted fixed-wing oil-electric hybrid unmanned aircraft |
| CN205770148U (en) * | 2016-05-21 | 2016-12-07 | 辽宁辽飞航空科技有限公司 | A kind of can the Fixed Wing AirVehicle of VTOL |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107244415A (en) * | 2017-05-24 | 2017-10-13 | 彩虹无人机科技有限公司 | The composite power rotor wing unmanned aerial vehicle that a kind of fuselage can vert |
| CN110217391A (en) * | 2019-05-31 | 2019-09-10 | 沈阳迪智科技有限公司 | A kind of oil electric mixed dynamic VTOL sweepforward fixed-wing unmanned plane |
| CN114148517A (en) * | 2021-12-30 | 2022-03-08 | 四川文理学院 | Vertical take-off and landing high-speed unmanned aerial vehicle and control method thereof |
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Application publication date: 20160907 |
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