CN107878746A - A kind of VTOL fixed-wing long endurance unmanned aircraft of oil electric mixed dynamic - Google Patents
A kind of VTOL fixed-wing long endurance unmanned aircraft of oil electric mixed dynamic Download PDFInfo
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- CN107878746A CN107878746A CN201710981102.XA CN201710981102A CN107878746A CN 107878746 A CN107878746 A CN 107878746A CN 201710981102 A CN201710981102 A CN 201710981102A CN 107878746 A CN107878746 A CN 107878746A
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- fuselage
- wing
- displacement system
- fuel power
- verting
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/52—Tilting of rotor bodily relative to fuselage
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
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Abstract
The invention discloses a kind of VTOL fixed-wing long endurance unmanned aircraft of oil electric mixed dynamic；Unmanned plane uses three fuselage parallel arrangements, fuselage is possessed more load spaces；Inclining rotary mechanism is combined with the dynamic pitch-changing mechanism of oil can bring higher pneumatic efficiency and bigger lifting capacity.Unmanned plane is taking off, cruise, in descent, first fuel power displacement system and the second fuel power displacement system of verting of verting provides the main vertical lift in VTOL stage, first lift motor, the second lift motor provide the additional vertical lift in VTOL stage, and four dynamical system combinations provide attitude regulation torque needed for pitching and roll.There is stronger thrust and very high pneumatic efficiency using fuel power displacement system of verting, by displacement fully meet VTOL with during level cruise to the Bu Tong pneumatic effect needed for propeller.Finally bring higher pneumatic efficiency and bigger lifting capacity, and longer cruising time.
Description
Technical field
The present invention relates to VTOL fixed-wing unmanned plane field, specifically, is related to a kind of hanging down for oil electric mixed dynamic
Straight landing fixed-wing long endurance unmanned aircraft.
Background technology
With science and technology progress, especially flight control computer technology, the communication technology, electronic technology fast development,
The performance of unmanned vehicle constantly strengthens, species is on the increase, and small volume, cost are low possessed by unmanned vehicle, use dimension
Shield is convenient etc., and advantage is more obvious embodies.So its application demand in national defence and civil area sharply increases.
The definition of VTOL Fixed Wing AirVehicle is:It can take off/land with zero velocity and possess hovering ability, and can be with
Fixed-wing mode horizontal flight.Compared with conventional aircraft, VTOL Fixed Wing AirVehicle has Fixed Wing AirVehicle flight
Speed is fast, voyage is remote, the performance advantage of endurance length, and and can is small in place and spatial domain limited mountain area, jungle and surface ship etc.
Area, complex region complete landing, and therefore, the practical value of VTOL Fixed Wing AirVehicle is increasingly by the extensive of industry
Accreditation.
At present, VTOL Fixed Wing AirVehicle includes vert dynamical type, tailstock formula and the class of composite power formula three.Tailstock formula
Although vertically taking off and landing flyer needs additional mechanism providing additional operation, existing tailstock formula unlike dynamical type VTOL of verting without aircraft
Obvious limitation be present in VTOL Fixed Wing AirVehicle.General tailstock formula vertically taking off and landing flyer only VTOL, if
The difficult extreme case of landing then occurs in system damage.Composite power formula vertically taking off and landing flyer typically has two sets of power to set
Standby, a set of power-equipment is responsible for VTOL, and a set of power-equipment is responsible for horizontal flight.It is disadvantageous in that a set of power of increase
Equipment, add construction weight.Next is limited to current technical reason, is responsible for the power-equipment of VTOL mostly using electronic
Machine, there is serious deficiency in terms of lifting capacity.Dynamical type VTOL Fixed Wing AirVehicle vert by inclining rotary mechanism, it is real
From level to vertical mutual conversion, power overcomes resistance in the horizontal direction during horizontal flight, hangs down for existing rotor or jet engine
Power vertically overcomes gravity when flying nonstop to row.But there is also obvious office for the existing VTOL fixed-wing unmanned plane that verts
Limit.
At the U of patent of invention CN 206125423 " a kind of VTOL fixed-wing unmanned plane with the power set that vert "
In, disclosed power arrangement of verting has the following disadvantages:First, the power side of a fuel engines is added using four motor
Case, wherein the first two motor can vert.The fuel engines of horizontal thrust is provided with, increases inclining rotary mechanism again by the first two electricity
Machine also provides horizontal thrust, declines overall efficiency of energy utilization.Second, VTOL, existing electricity are completed using motor
Mechanical, electrical pool technology is not enough to support heavy－duty landing at all；So that unmanned plane lifting capacity is limited.3rd, can vert preceding two
Individual motor uses constant pitch airscrew, and experiment proves that rotor state and the flat winged state of fixed-wing are complete to the demand of airscrewpiston
Different, pneumatic efficiency degradation can be caused using constant pitch airscrew, so wanting to reach higher pneumatic efficiency, it is necessary to make
Use variable-pitch propeller.
The content of the invention
The load-carrying that occurs in order to avoid the VUAV that verted existing for prior art is less than normal, overall pneumatic efficiency
The problem of relatively low, the present invention propose a kind of VTOL fixed-wing long endurance unmanned aircraft of oil electric mixed dynamic.The unmanned plane is adopted
With three fuselage parallel arrangement modes, fuselage possesses more load spaces；Inclining rotary mechanism is combined with the dynamic pitch-changing mechanism of oil can band
Come higher pneumatic efficiency and bigger lifting capacity.
The technical solution adopted for the present invention to solve the technical problems is:Including the first winglet, host wing, the first machine
Body, the first fuel power vert displacement system, main machine body, pitot, the second fuel power vert displacement system, the second fuselage,
Second winglet, the second lift motor, horizontal tail, the first lift motor, the second vertical fin, the first vertical fin, the main machine body
It is structure as a whole with the first fuselage, the second fuselage, the first fuselage and the second fuselage are respectively positioned at the both sides of main machine body and in
Between the wing connect, laterally be symmetrical parallel layout, three fuselages possess more load spaces, before pitot is fixed on main machine body
End；The trailing edge of the host wing is provided with aileron, and the first winglet, the second winglet are symmetrically mounted on host wing both sides
Hold wingtip position；
First vertical fin is arranged on the first back body portion, and second vertical fin is arranged on the second back body portion, and two
There is rudder to be used for producing unmanned plane yawing on vertical fin；Horizontal tail is installed, in horizontal tail between the first vertical fin and the second vertical fin
There is elevator to be used for producing unmanned plane pitching moment；
Vert displacement system and second fuel power of first fuel power verts displacement system respectively positioned at the
One front fuselage and the second front fuselage, the first lift motor, the second lift motor are arranged on the first fuselage afterbody and
Two fuselage afterbodies；First fuel power displacement system and the second fuel power displacement system of verting of verting provides main vertical lift,
First lift motor and the second lift motor provide additional vertical lift, realize unmanned plane vertical short landing campaign, fire
Displacement system of oily power verting combines with lift electric system, for providing attitude regulation torque needed for pitching and roll.
When taking off, displacement system of verting, which is inclined, to be turn 90 degrees, and vert displacement system, the second fuel oil of the first fuel power moves
Power vert displacement system provide horizontal thrust.
Beneficial effect
A kind of VTOL fixed-wing long endurance unmanned aircraft of oil electric mixed dynamic proposed by the present invention, is put down using three fuselages
Row layout structure, fuselage possess more load spaces；Inclining rotary mechanism is combined with the dynamic pitch-changing mechanism of oil, can be brought higher
Pneumatic efficiency and bigger lifting capacity.Although unmanned plane using fuel power vert displacement system inclining rotary mechanism complexity,
It is that the dynamic displacement power of oil has very strong thrust and very high pneumatic efficiency, can meets that VTOL and level are patrolled completely by displacement
To the different pneumatic effects needed for propeller during boat.Finally bring higher pneumatic efficiency and longer cruising time.
The VTOL fixed-wing long endurance unmanned aircraft of oil electric mixed dynamic of the present invention, can VTOL, STOL,
Or sliding race landing.With flexibility more more preferable than traditional fixed-wing unmanned plane and more excellent than conventional helicopters, multi-rotor aerocraft
Flying quality.
Brief description of the drawings
Chord endurance is fixed to a kind of VTOL of oil electric mixed dynamic of the present invention with embodiment below in conjunction with the accompanying drawings
Unmanned plane is described in further detail.
Fig. 1 is VTOL fixed-wing long endurance unmanned aircraft top view of the present invention.
Fig. 2 is VTOL fixed-wing long endurance unmanned aircraft front view of the present invention.
Fig. 3 is VTOL fixed-wing long endurance unmanned aircraft side view of the present invention.
Fig. 4 is VTOL fixed-wing long endurance unmanned aircraft of the present invention in VTOL view.
Fig. 5 is VTOL fixed-wing long endurance unmanned aircraft axonometric drawing of the present invention.
In figure:
The main frame of displacement the system 5. 1. fuel power of 2. host wing of the first winglet, 3. first fuselage 4. first verts
The fuel power of 6. pitot of body 7. second verts the lift of 8. second fuselage of displacement system, 9. second winglet 10. second
The vertical fin of 13. second vertical fin of motor 11. horizontal tail, 12. first lift motor 14. first
Embodiment
The present embodiment is a kind of VTOL fixed-wing long endurance unmanned aircraft of oil electric mixed dynamic.
Refering to Fig. 1~Fig. 5, the VTOL fixed-wing long endurance unmanned aircraft of the present embodiment oil electric mixed dynamic, by first
Winglet 1, host wing 2, the first fuselage 3, the first fuel power vert displacement system 4, main machine body 5, pitot 6, second fire
Oily power verts displacement system 7, the second fuselage 8, the second winglet 9, the second lift motor 10, horizontal tail 11, the first lift
Motor 12, the second vertical fin 13, the first vertical fin 14 form；Wherein, the fuselage 3 of main machine body 5 and first, the second fuselage 8 are integrated knot
Structure, the first fuselage 3 are connected positioned at the both sides of main machine body 5 by the middle wing respectively with the second fuselage 8, are being laterally symmetrical parallel cloth
Office, the combination of three fuselages possess more load spaces, and pitot 6 is fixed on the leading section of main machine body 5.The trailing edge peace of host wing 2
Equipped with aileron, unmanned plane rolling moment is produced.First winglet 1, the second winglet 9 are symmetrically mounted on the both sides of host wing 2
Hold wingtip position.First vertical fin 14 is arranged on the rearward end of the first fuselage 3, and the second vertical fin 13 is arranged on the rearward end of the second fuselage 8, and two
There is rudder to be used for producing unmanned plane yawing on vertical fin；Horizontal tail 11 is installed between first vertical fin 14 and the second vertical fin 13, put down
There is elevator to be used for producing unmanned plane pitching moment on tail 11.
In the present embodiment, the first fuel power displacement system 4 and second fuel power displacement system 7 of verting of verting is divided
Not An Zhuan the front end of the first fuselage 3 and the front end of the second fuselage 8, the first lift motor 12, the second lift motor 10 are set respectively
Put at the rear portion of the first fuselage 3 and the rear portion of the second fuselage 8.First fuel power displacement system 4 of verting is verted with the second fuel power
Displacement system 7 provides main vertical lift, and the first lift motor 12 and the second lift motor 10 provide additional vertical lift, real
Existing unmanned plane vertical short landing campaign.Displacement system of fuel power verting combines with lift electric system, for providing pitching
With roll needed for attitude regulation torque.When taking off, displacement system of verting, which is inclined, to be turn 90 degrees, and the first fuel power verts displacement
System 4, the second fuel power vert displacement system 7 provide horizontal thrust.
In the present embodiment, main machine body 5, the first fuselage 3, the second fuselage 8, host wing 2, the first winglet 1 and second wing
Sharp winglet 9, and three fuselage arrangement aerodynamic configuration structures of the first vertical fin 14, the second vertical fin 13, horizontal tail 8 composition.Main machine body 5 is
Hollow and thin-walled shell structure, inside arrangement beam and reinforcing frame are divided into airborne equipment cabin and mission payload cabin.Airborne equipment cabin is in machine
Head point is provided with air environment and required battery.Head upper is used for air environment with hatchcover to be dismounted and ties up
Shield.Mission module is located at the postmedian of main machine body 5, is provided with task device；Lower section has hatchcover to be used for task device dismounting maintenance.Main frame
The both sides of body 5 are disposed with fuel oil tank.First fuselage 3 and the second fuselage 8 are hollow and thin-walled shell structure, inside arrangement beam and reinforcement
Frame；Two front fuselage portions are respectively provided with fuel power and verted displacement system, including pitch-changing mechanism and variable-pitch propeller.Piggyback pod is pacified
Equipped with fuel engines and small generator；Middle fuselage provides the energy for power battery cabin for lift motor.First fuselage 3
It is equipment compartment with the back segment of the second fuselage 8, for installing electron speed regulator, lift motor.
Host wing 2 is airfoil with high ratio of lift over drag, inside arrangement rib and girder construction.The fuselage 3 of host wing 2 and first, the second machine
The middle wing that body 8 connects is disposed with fuel oil tank.The both sides aileron location arrangements electronics steering wheel of host wing 2, to control aileron movement.
The VTOL fixed-wing long endurance unmanned aircraft flight course of oil electric mixed dynamic:
During VTOL, the first fuel power fuel power of displacement system 4 and second that verts verts displacement system 7
Main vertical lift is provided, the first lift motor 12, the second lift motor 11 provide the additional vertical liter in VTOL stage
Power, four sets of dynamical system combinations provide attitude regulation torque needed for pitching and roll, complete VTOL process.
In cruising level flight state, the first fuel power fuel power of displacement system 4 and second that verts verts displacement system 7
Incline and turn 90 degrees, there is provided be flat to fly required motive force.Host wing 2 produce lift, elevator, aileron, rudder provide needed for appearance
State Torque-adjusting.
During short distance is slided and runs landing, the first fuel power fuel power of displacement system 4 and second that verts verts displacement
System 7 is verted, and the first fuel power displacement system 4 and second fuel power displacement system 7 of verting of verting is provided and tilted upward
Pulling force, and unmanned plane is obtained horizontal acceleration, unmanned plane, which is slided, to be run, and host wing 2 produces lift, while the first lift motor
12nd, the second lift motor 11 provides additional vertical lift.Four sets of dynamical system combinations provide posture needed for pitching and roll and adjusted
Torque is saved, unmanned plane completes short distance cunning and runs landing under comprehensive function.
Claims (2)
- A kind of 1. VTOL fixed-wing long endurance unmanned aircraft of oil electric mixed dynamic, it is characterised in that:It is small including the first wing tip Vert displacement system, main machine body, pitot, the second fuel power of the wing, host wing, the first fuselage, the first fuel power verts change Away from system, the second fuselage, the second winglet, the second lift motor, horizontal tail, the first lift motor, the second vertical fin, first Vertical fin, the main machine body are structure as a whole with the first fuselage, the second fuselage, and the first fuselage and the second fuselage are located at main machine body respectively Both sides and connected by the middle wing, laterally be symmetrical parallel layout, three fuselages possess more load spaces, and pitot is solid It is scheduled on the leading section of main machine body；The trailing edge of the host wing is provided with aileron, and the first winglet, the second winglet are symmetrically pacified Mounted in host wing two side ends wingtip position；First vertical fin is arranged on the first back body portion, and second vertical fin is arranged on the second back body portion, two vertical fins On have rudder be used for produce unmanned plane yawing；Horizontal tail is installed between the first vertical fin and the second vertical fin, has liter in horizontal tail Drop rudder is used for producing unmanned plane pitching moment；First fuel power displacement system and second fuel power displacement system of verting of verting is located at the first machine respectively Body front end and the second front fuselage, the first lift motor, the second lift motor are arranged on the first fuselage afterbody and the second machine Portion behind；First fuel power displacement system and the second fuel power displacement system of verting of verting provides main vertical lift, and first Lift motor and the second lift motor provide additional vertical lift, realize unmanned plane vertical short landing campaign, fuel oil moves Power displacement system of verting combines with lift electric system, for providing attitude regulation torque needed for pitching and roll.
- 2. the VTOL fixed-wing long endurance unmanned aircraft of oil electric mixed dynamic according to claim 1, it is characterised in that: When taking off, displacement system of verting, which is inclined, to be turn 90 degrees, and vert displacement system, the second fuel power of the first fuel power verts change Horizontal thrust is provided away from system.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710981102.XA CN107878746A (en) | 2017-10-20 | 2017-10-20 | A kind of VTOL fixed-wing long endurance unmanned aircraft of oil electric mixed dynamic |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710981102.XA CN107878746A (en) | 2017-10-20 | 2017-10-20 | A kind of VTOL fixed-wing long endurance unmanned aircraft of oil electric mixed dynamic |
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| CN107878746A true CN107878746A (en) | 2018-04-06 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201710981102.XA Pending CN107878746A (en) | 2017-10-20 | 2017-10-20 | A kind of VTOL fixed-wing long endurance unmanned aircraft of oil electric mixed dynamic |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108910049A (en) * | 2018-05-23 | 2018-11-30 | 深圳智航无人机有限公司 | Unmanned plane and UAV system for logistics transportation |
| CN109857132A (en) * | 2019-03-12 | 2019-06-07 | 辽宁壮龙无人机科技有限公司 | A kind of flight control assemblies and method |
| CN112046764A (en) * | 2020-09-07 | 2020-12-08 | 南京航空航天大学 | Rotary wing vertical take-off and landing hybrid power unmanned aerial vehicle and control method thereof |
| CN114852324A (en) * | 2022-05-19 | 2022-08-05 | 亿维特(南京)航空科技有限公司 | Vertical take-off and landing passenger plane |
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| CN104417750A (en) * | 2013-09-03 | 2015-03-18 | 杨家雄 | Tandem tilt rotor aircraft |
| CN205440869U (en) * | 2016-03-31 | 2016-08-10 | 西安东锐航空科技有限公司 | Fixed chord flight time aircraft of canard configuration of VTOL |
| CN106143898A (en) * | 2016-08-08 | 2016-11-23 | 北京奇正数元科技股份有限公司 | A kind of VTOL tilting rotor fixed wing airplane |
| CN206125423U (en) * | 2016-11-02 | 2017-04-26 | 北京航空航天大学 | VTOL fixed wing uavs with power device verts |
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2017
- 2017-10-20 CN CN201710981102.XA patent/CN107878746A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104417750A (en) * | 2013-09-03 | 2015-03-18 | 杨家雄 | Tandem tilt rotor aircraft |
| CN205440869U (en) * | 2016-03-31 | 2016-08-10 | 西安东锐航空科技有限公司 | Fixed chord flight time aircraft of canard configuration of VTOL |
| CN106143898A (en) * | 2016-08-08 | 2016-11-23 | 北京奇正数元科技股份有限公司 | A kind of VTOL tilting rotor fixed wing airplane |
| CN206125423U (en) * | 2016-11-02 | 2017-04-26 | 北京航空航天大学 | VTOL fixed wing uavs with power device verts |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108910049A (en) * | 2018-05-23 | 2018-11-30 | 深圳智航无人机有限公司 | Unmanned plane and UAV system for logistics transportation |
| CN109857132A (en) * | 2019-03-12 | 2019-06-07 | 辽宁壮龙无人机科技有限公司 | A kind of flight control assemblies and method |
| CN112046764A (en) * | 2020-09-07 | 2020-12-08 | 南京航空航天大学 | Rotary wing vertical take-off and landing hybrid power unmanned aerial vehicle and control method thereof |
| CN112046764B (en) * | 2020-09-07 | 2021-11-05 | 南京航空航天大学 | Rotary wing vertical take-off and landing hybrid power unmanned aerial vehicle and control method thereof |
| CN114852324A (en) * | 2022-05-19 | 2022-08-05 | 亿维特(南京)航空科技有限公司 | Vertical take-off and landing passenger plane |
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Application publication date: 20180406 |