CN106586001A - Multimode and multi-based unmanned aerial vehicle with tailed flying wing configuration - Google Patents
Multimode and multi-based unmanned aerial vehicle with tailed flying wing configuration Download PDFInfo
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- CN106586001A CN106586001A CN201611079239.8A CN201611079239A CN106586001A CN 106586001 A CN106586001 A CN 106586001A CN 201611079239 A CN201611079239 A CN 201611079239A CN 106586001 A CN106586001 A CN 106586001A
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- unmanned vehicle
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
- B64D27/16—Aircraft characterised by the type or position of power plant of jet type
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/06—Fins
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/08—Stabilising surfaces mounted on, or supported by, wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
- B64D27/04—Aircraft characterised by the type or position of power plant of piston type
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- 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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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/11—Propulsion using internal combustion piston engines
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/12—Propulsion using turbine engines, e.g. turbojets or turbofans
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/13—Propulsion using external fans or propellers
- B64U50/14—Propulsion using external fans or propellers ducted or shrouded
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
Abstract
The invention relates to the technical field of unmanned aerial vehicles, and particularly relates to an unmanned aerial vehicle with a tailed flying wing configuration, which has a plurality of working modes such as vertical take-off and landing/short-distance take-off and landing/conventional take-off and landing/low-speed forward flight/high-speed forward flight and the like and can realize coast-based/vessel-based multi-based configuration. The unmanned aerial vehicle comprises a lifting body type vehicle body of which the longitudinal section is of an airfoil shape, and main airfoils, upper airfoils and end airfoils which are arranged at both sides of the vehicle body and form smooth integration with the vehicle body, and a duct propeller propulsion device and a vertical fin which are arranged at the tail of the vehicle body, wherein the lower end of the vertical fin is fixedly connected with a duct structure of the duct propeller propulsion device arranged at the tail of the vehicle body. According to the invention, the tailed flying wing configuration integrated with jointed wings is adopted, so that the unmanned aerial vehicle has various advantages such as excellent aerodynamic characteristics and high effective load factor of the conventional flying wing configuration, and also effectively overcomes the inherent defects of the conventional flying wing configuration in aspects of stability and operability.
Description
Technical field
The present invention relates to unmanned air vehicle technique field, belongs to the fixed wing airplane design field in aviation aircraft, tool
Body be related to it is a kind of with flying before VTOL/STOL/CTOL/low speed/at a high speed before various operation modes such as fly, can
Bank base/warship Quito base portion administration is realized, the flying wing type unmanned vehicle of connection wing aerodynamic arrangement form is integrated with.
Background technology
At present, possess VTOL/STOL function, can realize that the aircraft of bank base/warship Quito base portion administration is main
Helicopter, the vertically taking off and landing flyer using jet engine thrust steering, tilting rotor/propeller power can be divided into vertically to rise
The several types such as drop aircraft.
Wherein, helicopter due to do not need ground runway and can VTOL, hovering, in front and back side fly etc. it is excellent winged
Row quality, obtains in military and civilian field and extensively applies.But there is advancing blade shock loss when flying before at a high speed in helicopter
With the problems such as retreating blade stall, flight speed is difficult to improve.Additionally, the rotor lift of helicopter needs to put down in flight course
Weight power, this also causes helicopter in whole flight course all the time in high power work state, causes helicopter voyage to have
Limit, cruising time short defect.
Turned to using jet engine thrust and realize being related to Thrust Vectoring Technology by the aircraft of VTOL that this is crucial
Technology, such Thrust Vectoring Technology require that engine exhaust jet pipe has bigger deflection vector relative to conventional vector jet pipe
Angle, and exhaust pipe deflection angle degree can continuously adjustabe and simultaneously meet aircraft STOL, VTOL, during cruise pitching and
Many-sided war skill index such as driftage control and superior cruise performance, its research and development difficulty is larger and cost is high.
Tilting rotor/propeller power vertically taking off and landing flyer realizes pin by angle of rake verting such as rotor/propellers
Regulation to state of flight.Such aircraft not only has the various technological difficulties of fixed wing airplane and helicopter, while also having
There is the technical problem that tiltrotor is exclusive, its structure, aerodynamic force and manipulation technology are more multiple than general fixed wing airplane or helicopter
It is miscellaneous much.Its research and development is related to the tackling key problem of multinomial key technology, and research and development difficulty is big, developing risk is high.
As described above, having put at present actually used, the aircraft of VTOL function and high-performance cruise ability is had concurrently
The vertically taking off and landing flyer for only being turned to using jet engine thrust and tilting rotor/propeller power vertically taking off and landing flyer
Two classes, but its R＆D costs is higher, it is very big to research and develop difficulty.
The content of the invention
It is an object of the invention to provide it is a kind of both with the VTOL ability similar to helicopter, fly with fixed-wing again
The unmanned vehicle of machine high-performance cruise ability, while with good cruising characteristics, and can effectively solving routine Flying-wing
Aircraft Lateral course unstable and a heavy handled difficult problem.
For achieving the above object, the invention provides technical scheme below：
A kind of multimode Duo Jiyou tail Flying-wing unmanned vehicle, including：
Lifting body formula of the vertical section in aerofoil profile (aerofoil profile refers to the longitudinal section shape of classical fixed wing airplane wing)
Fuselage, be arranged on fuselage both sides with fuselage smooth blend formula host wing, upper limb, the end wing, be arranged on the duct spiral shell of afterbody
Rotation oar propulsive unit, vertical fin.The main wing for being arranged on fuselage both sides is slightly located to arrange the end wing, the upper end of described two end wings in the wing
Upper limb by being arranged on body upper is connected with the vertical fin for being arranged on afterbody respectively, the lower end of the vertical fin be arranged at
The duct structure of the shrouded propeller propulsion plant of afterbody is fixedly connected with.
Further, the rear end of described two upper limbs is provided with elevator, for equalling pitch control when flying；
Further, the vertical fin rear end is provided with rudder, for putting down Heading control when flying.
Further, the both sides of the fuselage, be provided with ducted fan, both sides ducted fan direction of rotation before center of gravity
On the contrary；Two ducted fans swing along an axis of pitch (referring to the horizontal axis vertical with fuselage fore-and-aft direction) and arrange.
Further, two ducted fans are respectively fixedly connected with the transverse axis two ends for being built in fuselage installation；It is built in fuselage installation
Servomotor drive endless screw apparatus, endless screw apparatus are meshed with the gear on transverse axis, by the start of servomotor with
The transmission of worm gear device, realizes 360 ° Omnidirectional rotations of the ducted fan system in transaxial plane.
Further, the ducted fan of fuselage both sides is driven respectively by turning to two contrary direct current generators, is led to
Cross electricity regulation and control system and be added on regulation of the realization of the voltage on direct current generator bus for rotation speed of the fan and pulling force；Servomotor and straight
Stream motor is by airborne energy storage device supply of electrical energy.
Further, afterbody is provided with the small sized turbine jet engine vertically installed.
Further, transmission of the turbojet main shaft by clutch, driving bevel gear and driven bevel pinion, drives
The rotor input shaft of dynamic high-speed permanent magnetic electromotor, produced high-frequency alternating current are transformed to corresponding system by electrical energy changer
Unidirectional current, to airborne energy storage device charge.
Further, the heavy oil piston power plant of fuselage interior is horizontally installed to, for driving the culvert of afterbody
Road propeller set；Small sized turbine jet engine adopts same fuel with heavy oil piston power plant.
The method have technical effect that：
A. the You Wei flying wing types aerodynamic arrangement for being integrated with the connection wing is employed, unmanned vehicle is having conventional Flying-wing concurrently
While many advantages, such as aerodynamic characteristic is excellent, efficient loading coefficient is high, effectively overcome conventional Flying-wing in stability and
Existing inherent shortcoming in maneuverability.
B. unmanned vehicle employs the aerodynamic configuration based on the embedded ducted fan hybrid lift mechanism of You Wei Flying-wings
The longitudinal attitude control under VTOL state is realized in design, auxiliary using the jet thrust of small sized turbine jet engine.
Under flat winged state, turbojet output shaft power drive high-speed power generation device, produced electrical power storage is in airborne storage
Energy device, and the use of airborne equipment, ducted fan and mission payload can be provided, realize aircraft platforms energy power system
High efficiency integrated form is arranged.
C. the longitudinal force that unmanned vehicle was both provided using ducted fan and turbojet is realized taking off vertically
And vertical landing, wing and the pressure reduction lift of fuselage offer can be utilized again to obtain higher flight speed in the flat winged stage and move
Power propulsive efficiency, makes unmanned vehicle integrate VTOL and high-performance cruise performance.
D. the ducted fan of fuselage both sides can realize 360 ° of Omnidirectional rotations in transaxial plane, and the pulling force produced by which can be with
Lifting force as the VTOL stage, flat winged stage draw in power or the auxiliary steering force under other state of flights, carry significantly
The mobility and maneuvering performance of high unmanned vehicle.
E. the shrouded propeller for being driven by heavy oil piston power plant as the main thruster flown before low speed under state,
Can be flown before realizing the high speed of unmanned vehicle by combining with the ducted fan of rotation to horizontal level.Two-stage propeller
Combining form so that unmanned vehicle also can change according to the demand of aerial mission while possessing CTOL ability
Forward flight speed, realizes the multi-modal of unmanned vehicle and uses and bank base/warship Quito base portion administration.
Description of the drawings
Fig. 1 is the unmanned vehicle axonometric chart provided by embodiments of the invention；
Fig. 2 is the unmanned vehicle total arrangement diagrammatic side view provided by embodiments of the invention；
Fig. 3 is the unmanned vehicle total arrangement diagrammatic top view provided by embodiments of the invention；
Fig. 4 is the unmanned vehicle ducted fan part energy power system arrangement principle provided by embodiments of the invention
Figure；
Fig. 5 is the ducted fan rotation position definition figure provided by embodiments of the invention；
Fig. 6 is the unmanned vehicle turbojet provided by embodiments of the invention and piston power device part
Energy power system arrangement schematic diagram, the figure is fuselage vertical section sectional view；
Fig. 7 is the three-view diagram of the unmanned vehicle VTOL operation mode provided by embodiments of the invention；
Fig. 8 is the three-view diagram of the unmanned vehicle STOL operation mode provided by embodiments of the invention；
Fig. 9 is the three-view diagram of the unmanned vehicle CTOL operation mode provided by embodiments of the invention；
Figure 10 is the three-view diagram of winged operation mode before the unmanned vehicle low speed provided by embodiments of the invention；
Figure 11 is the three-view diagram of winged operation mode before the unmanned vehicle high speed provided by embodiments of the invention.
Specific embodiment
The present invention is described in detail below in conjunction with accompanying drawing.
Embodiment 1
As shown in Figure 1, 2, 3, a kind of multimode Duo Jiyou tail Flying-wing unmanned vehicle, the aircraft include：Vertical section
Lifting body formula fuselage 1 in aerofoil profile flat shape, the blended wing-body formula host wing 2, upper limb 3 for being arranged on 1 both sides of fuselage, the end wing 4,
It is arranged on shrouded propeller propulsion plant 5, the vertical fin 6 of 1 afterbody of fuselage.The main wing 2 for being arranged on 1 both sides of fuselage is slightly located in the wing
The end wing 4 is set, and the upper part of described two end wings 4 is respectively by being arranged on the upper limb 3 above fuselage 1 and being arranged on 1 tail of fuselage
The vertical fin 6 in portion connects, the duct structure of the lower end of the vertical fin 6 and the shrouded propeller propulsion plant 5 for being arranged at 1 afterbody of fuselage
It is fixedly connected with.
Unmanned vehicle provided by the present invention employs the You Wei flying wing types aerodynamic arrangement for being integrated with the connection wing, lifting body
The design of formula fuselage 1, while aerodynamic drag is substantially reduced, also can produce certain pressure reduction lift when front winged, have
Effect improves the lifting resistance characteristic of full machine.It is pneumatic by the main wing 2, upper limb 3, the end wing 4 and the 6 combined connection wing for being formed of vertical fin
Design, aircraft while conventional flying wing type aerodynamic arrangement intrinsic good cruising characteristics are inherited, effectively solving
Such Aircraft Lateral course unstable and heavy handled is difficult, with preferable maneuverability and stability.
Embodiment 2
Multimode Duo Jiyou tail Flying-wing unmanned vehicle according to an embodiment of the invention provides a kind of efficient
The integrated form energy power system design of rate, as shown in Figure 3.Its feature includes：
Unmanned vehicle employ before 1 front part sides of fuselage, center of gravity arrange ducted fan 9 distribution form, with
The VTOL stage produces direct lifting force.As shown in figure 4,9 direction of rotation of ducted fan of 1 both sides of fuselage is conversely, be connected
In 13 two ends of transverse axis for being built in the installation of fuselage 1.Ducted fan 9 turns to contrary direct current generator 15 by two and is driven simultaneously
Produce pulling force.The servomotor 12 for being built in the installation of fuselage 1 drives the gear 14 on endless screw apparatus 11, with transverse axis 13 mutually to nibble
Close.The direct current generator 15 of servomotor 12 and driving ducted fan 9 is supplied by the airborne energy storage device 17 for being built in the installation of fuselage 1
To electric energy.By the start and the transmission of worm gear device of servomotor 12, achievable ducted fan 9 is in transaxial plane
360 ° of Omnidirectional rotations the locking being capable of achieving on optional position, the rotation position definition of ducted fan are as shown in Figure 5.
As shown in fig. 6, after the center of gravity of unmanned vehicle, a small sized turbine jet is vertically arranged on 1 axis of fuselage
Electromotor 10, in the state of clutch 20 unclamps, turbojet 10 is mainly for generation of jet thrust, High Temperature High Pressure
Combustion gas expand and produce thrust i.e. lifting force straight up in ejector exhaust pipe 18, jet thrust is except with fan pulling force altogether
Outside the same lifting for completing aircraft, it may also be used for the steering force needed for the longitudinal direction pitch attitude control of VTOL stage is provided
Square；In the state of clutch 20 is tightened up, the main shaft 19 of turbojet passes through driving bevel gear 21 and driven bevel pinion
22 transmission, drives the rotor input shaft of high-speed permanent magnetic electromotor 23.Now, the major part residue work(of turbojet 10
Rate is used to drive high-speed engine 23 and produces high-frequency alternating current, and Jing electrical energy changers 24 change backward airborne energy storage device 17
Charge；The afterbody of unmanned vehicle is provided with shrouded propeller propulsion plant 5, propeller is by being built in fuselage 1, be horizontally mounted
Heavy oil piston power plant 25 driven.Small sized turbine jet engine 10 is adopted with heavy oil piston power plant 25
Same fuel.
Embodiment 3
Multimode Duo Jiyou tail Flying-wing unmanned vehicle according to an embodiment of the invention, VTOL Working mould
System mode under state is as shown in Figure 7.Under VTOL operation mode, the heavy oil piston power plant 25 at 1 rear portion of fuselage
" mourning in silence " state of holding.The ducted fan 9 of 1 both sides of fuselage is rotated to vertical position as shown in Figure 4, rotate at a high speed and produce to
On lifting force；The clutch 20 of 19 outfan of turbojet main shaft unclamps, and the combustion gas of High Temperature High Pressure is in ejector exhaust pipe
Thrust i.e. lifting force straight up is expanded and is produced in 18, and ducted fan 9 produces enough lift jointly, to realize vertical side
VTOL under side-jet control.Additionally, the jet thrust produced by turbojet 10 can be additionally used in providing hanging down
Operating torque needed for straight landing stage longitudinal direction pitch attitude control.
Multimode Duo Jiyou tail Flying-wing unmanned vehicle according to an embodiment of the invention, STOL Working mould
System mode under state is as shown in Figure 8.Under STOL operation mode, the clutch of 19 outfan of turbojet main shaft
Device 20 unclamps, and 10 downward jet of turbojet is producing lifting force straight up；The ducted fan 9 of 1 both sides of fuselage
Rotate to centre position as shown in Figure 5, the vertical direction component of fan pulling force is used to provide the lifting force needed for STOL,
Horizontal direction component is used to provide and draws in power along 1 axis direction of fuselage；The heavy oil piston power plant 25 at 1 rear portion of fuselage drives
Dynamic shrouded propeller propulsion plant 5 rotates at a high speed, produces the propulsive force along 1 axis direction of fuselage.It is fast when possessing certain advance
After degree, lift component and machine that the vertical direction jet thrust, ducted fan 9 in the generation of turbojet 10 is provided
Under the collective effect of the pressure reduction lift produced by body 1, wing 2, upper limb 3, the STOL process of unmanned vehicle is completed.
Multimode Duo Jiyou tail Flying-wing unmanned vehicle according to an embodiment of the invention, routinely take off Working mould
System mode under state is as shown in Figure 9.Take off under operation mode conventional, the ducted fan 9 of 1 both sides of fuselage is rotated to such as Fig. 5
Shown vertical position, and keep the heavy oil piston type at " mourning in silence " state, 1 rear portion of fuselage to move together with turbojet 10
Power apparatus 25 drive shrouded propeller device 5 to rotate at a high speed, produce the propulsive force along 1 axis direction of fuselage.It is certain when possessing
After pace, unmanned vehicle has been completed under the pressure reduction lift effect that wing 2, upper limb 3 and fuselage 1 are produced jointly
Fly over journey.System mode under conventional landing operation mode is identical with the conventional operation mode that takes off, can be with root in descent
According to demand starting turbine jet engine 10 and ducted fan 9, to auxiliary landing.
Multimode Duo Jiyou tail Flying-wing unmanned vehicle according to an embodiment of the invention, completes vertical rising
Fly/short takeoff with after certain terrain clearance, carried by the heavy oil piston power plant 25 at 1 rear portion of fuselage first
For propulsive force, flying instrument is made for certain forward flight speed；Then ducted fan 9 is rotated to vertical position as shown in Figure 5
And close in good time；Then clutch 20 is tightened up, most of dump power of turbojet 10 is used to drive to be sent out at a high speed
Motor 23 simultaneously produces high-frequency alternating current, and Jing electrical energy changers 24 convert backward airborne energy storage device 17 and charge.As above
System mode conversion will bring larger loss of lift, directly result in unmanned vehicle flying height and decline and enter underriding shape
State；Along with the increase of air speed, unmanned vehicle is changed into diving attitude, unmanned vehicle using the elevator 7 of 3 rear end of upper limb
Revert to level flight simultaneously flies operation mode into before low speed.The system mode flown before low speed under operation mode is as shown in Figure 10, front to fly
Power is provided by the shrouded propeller device 5 of 1 afterbody of fuselage.
Multimode Duo Jiyou tail Flying-wing unmanned vehicle according to an embodiment of the invention, it is front at a high speed to fly Working mould
System mode under state is as shown in figure 11.Fly under operation mode before at a high speed, the ducted fan 9 of 1 both sides of fuselage is rotated to such as Fig. 5
Shown horizontal level is simultaneously opened in good time, is flown before being provided by the shrouded propeller device 5 of 1 afterbody of ducted fan 9 and fuselage is common
Power.
It is winged before the low speed of unmanned vehicle/front at a high speed to fly under operation mode, by the elevator 7 and vertical fin 6 of 3 rear end of upper limb
The rudder 8 of rear end is respectively completed pitching and yaw attitude control.
Cruise task is completed, when will proceed to vertical landing/short distance landing, before unmanned vehicle should initially enter low speed
Winged operation mode, immediately by the section air door of regulation 1 back heavy oily piston formula power set 25 of fuselage, reduces forward flight speed, and
The turbojet 10 at 1 rear portion of ducted fan 9 and fuselage of 1 both sides of fuselage is started in good time, then further reduces heavy oil
The output of piston power device 25 is until shutdown, completes unmanned vehicle system gravity and rise dynamic balance to system weight from pressure reduction
Load transfer of the power by fan pulling force and jet thrust common equilibrium, realizes the vertical landing/short distance drop of unmanned vehicle then
Fall.
Presently preferred embodiments of the present invention is the foregoing is only, not to limit the present invention, all essences in the present invention
Any modification, equivalent and improvement made within god and principle etc., should be included within the scope of the present invention.
Claims (9)
1. a kind of multimode Duo Jiyou tail Flying-wing unmanned vehicle, it is characterised in that include：
Lifting body formula fuselage (1) of the vertical section in aerofoil profile, be arranged on fuselage (1) both sides with fuselage smooth blend formula host wing
(2), upper limb (3), the end wing (4), are arranged on shrouded propeller propulsion plant (5), the vertical fin (6) of fuselage (1) afterbody；The setting
Main wing (2) in fuselage (1) both sides is slightly located to arrange the end wing (4) in the wing, and the upper end of described two end wings (4) is respectively by being arranged on
Upper limb (3) above fuselage (1) is connected with the vertical fin (6) for being arranged on fuselage (1) afterbody, lower end and the setting of the vertical fin (6)
It is fixedly connected with the duct structure of the shrouded propeller propulsion plant (5) of fuselage (1) afterbody.
2. multimode Duo Jiyou tail Flying-wing unmanned vehicle according to claim 1, it is characterised in that：On described two
The rear end of the wing (3) is provided with elevator (7), for equalling pitch control when flying.
3. multimode Duo Jiyou tail Flying-wing unmanned vehicle according to claim 1, it is characterised in that：The vertical fin
(6) rear end is provided with rudder (8), for putting down Heading control when flying.
4. multimode Duo Jiyou tail Flying-wing unmanned vehicle according to claim 1, it is characterised in that：The fuselage
(1) ducted fan (9) is provided with before both sides, center of gravity, both sides ducted fan direction of rotation is contrary；Two ducted fans (9)
Swing along an axis of pitch and arrange.
5. multimode Duo Jiyou tail Flying-wing unmanned vehicle according to claim 4, it is characterised in that：Two ducted fans
(9) it is respectively fixedly connected with being built in transverse axis (13) two ends that fuselage (1) is installed；It is built in the servomotor (12) that fuselage (1) is installed
Endless screw apparatus (11) are driven, endless screw apparatus (11) are meshed with the gear (14) on transverse axis (13), by servomotor
(12) start and the transmission of worm gear device, realize 360 ° Omnidirectional rotations of ducted fan (9) system in transaxial plane.
6. multimode Duo Jiyou tail Flying-wing unmanned vehicle according to claim 4, it is characterised in that：Fuselage (1) two
The ducted fan (9) of side is driven respectively by turning to two contrary direct current generators (15), adjusts (16) control to add by electricity
Voltage on direct current generator (15) bus realizes the regulation for rotation speed of the fan and pulling force；Servomotor (12) and unidirectional current
Machine (15) is by airborne energy storage device (17) supply of electrical energy.
7. multimode Duo Jiyou tail Flying-wing unmanned vehicle according to claim 1, it is characterised in that：Fuselage (1) tail
Portion is provided with the small sized turbine jet engine (10) vertically installed.
8. multimode Duo Jiyou tail Flying-wing unmanned vehicle according to claim 7, it is characterised in that：Turbojet is sent out
Transmission of the motivation main shaft (19) by clutch (20), driving bevel gear (21) and driven bevel pinion (22), drives high-speed permanent magnetic
The rotor input shaft of electromotor (23), produced high-frequency alternating current are transformed to corresponding system by electrical energy changer (24)
Unidirectional current, charges to airborne energy storage device (17).
9. multimode Duo Jiyou tail Flying-wing unmanned vehicle according to claim 1, it is characterised in that：It is horizontally installed to
The internal heavy oil piston power plant (25) of fuselage (1), for driving the shrouded propeller device (5) of fuselage (1) afterbody；It is little
Type turbojet (10) adopts same fuel with heavy oil piston power plant (25).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611079239.8A CN106586001A (en) | 2016-11-30 | 2016-11-30 | Multimode and multi-based unmanned aerial vehicle with tailed flying wing configuration |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611079239.8A CN106586001A (en) | 2016-11-30 | 2016-11-30 | Multimode and multi-based unmanned aerial vehicle with tailed flying wing configuration |
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| CN106586001A true CN106586001A (en) | 2017-04-26 |
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| CN201611079239.8A Pending CN106586001A (en) | 2016-11-30 | 2016-11-30 | Multimode and multi-based unmanned aerial vehicle with tailed flying wing configuration |
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| CN108045575A (en) * | 2017-12-18 | 2018-05-18 | 刘行伟 | A kind of short takeoff vertical landing aircraft |
| CN108312795A (en) * | 2018-02-05 | 2018-07-24 | 中国船舶科学研究中心（中国船舶重工集团公司第七0二研究所） | Aerial-underwater paleocinetic amphibious aircraft and sailing method can be achieved in one kind |
| CN109466745A (en) * | 2018-12-29 | 2019-03-15 | 河北天启通宇航空器材科技发展有限公司 | A kind of gyroplane tail structure |
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| CN110282123A (en) * | 2019-07-17 | 2019-09-27 | 高峰 | It is a kind of for natural calamity situation inspection can VTOL the electronic unmanned plane of composite wing |
| FR3099138A1 (en) * | 2019-07-23 | 2021-01-29 | Safran Aircraft Engines | Aircraft comprising a blower thruster at the rear of the fuselage and an attachment structure for this thruster |
| CN111532426A (en) * | 2020-04-22 | 2020-08-14 | 中国空气动力研究与发展中心 | Aircraft with V-shaped empennage and multiple rotors in vertical take-off and landing layout |
| EP4023557A4 (en) * | 2020-10-21 | 2022-11-23 | Comac Beijing Aircraft Technology Research Institute | Aircraft propulsion system |
| CN116834966A (en) * | 2021-01-14 | 2023-10-03 | 何春远 | Manufacturing method and application of high-speed aircraft |
| CN114704407A (en) * | 2021-08-10 | 2022-07-05 | 中国电子科技集团公司第三十八研究所 | Multistage turbofan engine |
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