CN207000818U - A kind of VTOL fixed wing aircraft of oil electricity mixing - Google Patents
A kind of VTOL fixed wing aircraft of oil electricity mixing Download PDFInfo
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- CN207000818U CN207000818U CN201720512366.6U CN201720512366U CN207000818U CN 207000818 U CN207000818 U CN 207000818U CN 201720512366 U CN201720512366 U CN 201720512366U CN 207000818 U CN207000818 U CN 207000818U
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Abstract
The utility model discloses a kind of VTOL fixed wing aircraft of oil electricity mixing, including fuselage, it is symmetricly set on the wing of the fuselage both sides and is arranged on the empennage of the fuselage tail end, also include at least two rotor units being arranged on the wing, at least two described rotor units include at least one first rotor unit and at least one second rotor unit, the first rotor unit is included on symmetrically arranged a pair of first rotor assemblies of the fuselage axis, the second rotor unit is included on symmetrically arranged a pair of second rotor assemblies of the fuselage axis, first rotor assemblies and second rotor assemblies are separately positioned on the wing end, first rotor assemblies and second rotor assemblies form the inertia geometrical plane of three fulcrums or four fulcrums using asymmetrical control technology set-up mode.The utility model at least has the advantage that：Structure optimization, dynamical system utilization rate is high, stationarity is good, endurance is strong.
Description
Technical field
Vehicle technology field is the utility model is related to, more particularly to a kind of VTOL fixed-wing of oil electricity mixing flies
Machine.
Background technology
Current tilt rotor aircraft has many types, wherein mainly using fuel engines or motor as driving power
Based on." osprey " in the U.S. uses complete mechanical method at present, and all rotors are all using fuel engines as driving.Due to
Fuel engines response speed is too slow, aircraft balanced can not be met required for the quick lift regulation of rotor, therefore employ change
Away from technology, the quick displacement of angle by adjusting rotor blade is to realize the quick regulation of lift, but this kind of technology causes machine
Tool complicatedization, cost are high, difficult in maintenance, reliability is low.For electric tilting rotor wing aircraft developed in recent years, institute
Some rotors are using motor as driving.By battery powered, the characteristic using motor fast response time, by changing electricity
The lift of each rotor of motivation rotational speed regulation, to meet that the quick lift of the rotor needed for aircraft balanced is adjusted.This system knot
Structure is simple, safe and reliable, but due to the limitation of current battery energy storage, the time of this flight and flight is all very
Short, practical value is very low.
In the market have also been devised a kind of combine more rotors and fixed wing aircraft, by fuel electric generator and motor
The aircraft combined.For this kind of aircraft in VTOL, all rotors all rotate produces lift vertically upward upwards, profit
Keep balancing with motor quick regulation characteristic, fuel engines rotor produces lift, and rotor system is simple in construction.But this kind of aircraft
It is not thoroughly tilt rotor aircraft, when VTOL or hovering, all rotors all work for it, but fly aircraft is flat
When only some rotor wing rotation direction provide power for aircraft.Obviously this kind of aircraft is redundant system, power utilization
Rate is low, and during horizontal flight, part rotor does not provide the power of flight, while adds flight resistance, increases aircraft
Load.
Utility model content
In order to solve the above technical problems, the utility model purpose is to provide a kind of VTOL fixed-wing of oil electricity mixing
Aircraft, with solve the problems, such as it is of the prior art it is complicated, dynamical system utilization rate is low, stationarity is poor, endurance is low.
A kind of VTOL fixed wing aircraft of oil electricity mixing of the present utility model, including fuselage, be symmetricly set on it is described
The wing of fuselage both sides and the empennage for being arranged on the fuselage tail end, in addition at least two rotors being arranged on the wing
Unit, at least two described rotor units include at least one first rotor unit and at least one second rotor unit, institute
Stating the first rotor unit is included on symmetrically arranged a pair of first rotor assemblies of the fuselage axis, the second rotor unit
Including on symmetrically arranged a pair of second rotor assemblies of the fuselage axis, first rotor assemblies can including rotary speed
The motor of regulation and the first rotor for being driven by it rotation, second rotor assemblies include the hair using fixed rotary speed
Motivation and the second rotor for being driven by it rotation, first rotor assemblies and second rotor assemblies are separately positioned on described
Wing end, first rotor assemblies and second rotor assemblies form one using asymmetrical control technology set-up mode
The inertia geometrical plane of three fulcrums or four fulcrums.
Further, the thrust of each motor is adjusted respectively, each described to form multiple variable thrust fulcrums
Engine is using fixed thrust, with the equivalent quantitative thrust fulcrum of formation single-point.
Further, the fixed wing aircraft also includes being used for the power for monitoring the motor and engine operating
Control circuit, the power control circuit include microprocessor, each motor for being coupled with the microprocessor and described
The power unit of engine, to establish the logical relation mathematical modeling between each motor and the rotating speed of the engine.
Further, first rotor assemblies and the second rotor assemblies in the plane parallel to the fuselage axis
Rotate, its rotational angle is 0-90 °.
Further, the fixed wing aircraft includes two rotor units, and one is provided with one of them described wing
The first rotor unit, the second rotor unit is provided with another described wing.
Further, the fixed wing aircraft includes three rotor units, and one is provided with one of them described wing
The first rotor unit and the second rotor unit, above and below the first rotor unit and the second rotor unit
It is arranged in parallel, the first rotor unit or the second rotor unit is provided with another described wing.
Further, the fixed wing aircraft includes four rotor units, and one is respectively respectively arranged with two wings
The first rotor unit and the second rotor unit, above and below the first rotor unit and the second rotor unit
It is arranged in parallel.
Further, the tune for detecting the motor speed is provided between the motor and the microprocessor
Fast device, the speed regulator include FET.
Further, the ratio between the diameter of first rotor and the wing length are 0.1-0.6, second rotor with
The ratio between described wing length is 0.1-0.6.
Further, the material of the fuselage and wing is glass fiber compound material, carbon fibre composite, metal plate material
One or more combinations in material, balsa wood material.
By such scheme, the utility model at least has advantages below：
1st, by being provided with the first rotor assemblies and the second rotor assemblies, including motor and fuel engines, fuel oil hair
Motivation is using fixed rotating speed, in VTOL, mainly by being pushed away caused by high-power fuel engines and its institute's band rotor
Power provides lift, balance control is realized by adjusting motor speed Fast transforms thrust, in flat winged state, mainly by big
Power fuel engines and its provide aircraft speed forward with thrust caused by rotor, it is quick by adjusting motor speed
Conversion thrust realizes the overall gesture stability of aircraft；
2nd, asymmetrical set-up mode is used by the first rotor and second rotor, forms three fulcrums or four
The inertia geometrical plane of point, ensure the stability contorting of aircraft；
3rd, by way of oily electricity mixing, fuel engines and motor are organically used cooperatively, on the one hand utilize electricity
Motivation response range is big, overcomes landing process to the flat adjustment for flying over journey thrust wide variation, on the other hand utilizes
The characteristics of motor response range is greatly and power dynamic range is big realizes the stability contorting of aircraft, strong using fuel engines power
Strength, long-endurance feature realize aircraft length continuation of the journey.
Described above is only the general introduction of technical solutions of the utility model, in order to better understand skill of the present utility model
Art means, and being practiced according to the content of specification, with preferred embodiment of the present utility model and coordinate accompanying drawing detailed below
Describe in detail bright as after.
Brief description of the drawings
Fig. 1 is structural representation of the present utility model；
Fig. 2 is the utility model Fig. 1 mechanic equivalent schematic diagram；
Fig. 3 is another structural representation of the present utility model；
Fig. 4 is the utility model Fig. 3 mechanic equivalent schematic diagram；
Fig. 5 is another structural representation of the present utility model.
In the figures above：1st, fuselage；2nd, wing；3rd, empennage；4th, the first rotor assemblies；5th, the second rotor assemblies.
Embodiment
With reference to the accompanying drawings and examples, specific embodiment of the present utility model is described in further detail.Below
Embodiment is used to illustrate the utility model, but is not limited to the scope of the utility model.
With reference to shown in Fig. 1 to Fig. 5, the utility model discloses a kind of VTOL fixed wing aircraft of oil electricity mixing, bag
Fuselage 1 is included, be symmetricly set on the wing 2 of the both sides of fuselage 1 and is arranged on the empennage 3 of the tail end of fuselage 1.The fuselage 1
Material with wing 2 is glass fiber compound material, one kind or more in carbon fibre composite, Metal plate, balsa wood material
Kind combination, can preferably mitigate weight using these materials, the oil consumption and discharge greatly reduced, reduce operation cost, and
With extremely strong antifatigue and resistance to corrosion, increase the service life.
The VTOL fixed wing aircraft of the oil electricity mixing also includes at least two rotors being arranged on the wing 2
Unit, at least two described rotor units include at least one first rotor unit and at least one second rotor unit.Institute
State a pair of first rotor assemblies 4 that the first rotor unit includes setting on the axisymmetrical of fuselage 1, the second rotor list
Member includes a pair of second rotor assemblies 5 set on the axisymmetrical of fuselage 1.First rotor assemblies 4 include rotation
The adjustable motor of speed and the first rotor for being driven by it rotation, the thrust of each motor is adjusted respectively, with shape
Into multiple variable thrust fulcrums.Second rotor assemblies 5 include using the engine for fixing rotary speed and are driven by it turning
The second dynamic rotor, each engine is fuel engines, and it includes fuel oil engine, using fixed thrust, with equivalent shape
Into the quantitative thrust fulcrum of single-point.By way of oily electricity mixing, fuel engines and motor are organically used cooperatively, a side
Face is big using motor response range, overcomes landing process to the flat adjustment for flying over journey thrust wide variation, another
Aspect is big and the stability contorting of aircraft is realized the characteristics of power dynamic range is big using motor response range, is started using fuel oil
Mechanomotive force is powerful, and long-endurance feature realizes aircraft length continuation of the journey.First rotor assemblies 4 and second rotor assemblies
5 are separately positioned on the end of wing 2, when aircraft vertical takes off, first rotor assemblies 4 and the second rotor assemblies 5
In the rotation with surface parallel to the axis of fuselage 1, taking off vertically to flat fly, the first rotor assemblies 4 and second
The angle that rotor assemblies 5 turn over is 90 °.The diameter of first rotor and the length ratio of wing 2 are 0.1-0.6, described
Second rotor and the length ratio of wing 2 are 0.1-0.6.By being provided with the first rotor assemblies 4 and the second rotor assemblies 5,
It is mainly electronic by adjusting in flat winged state using fixed rotating speed including motor and fuel engines, fuel engines
Machine rotating speed Fast transforms thrust realizes the overall balance control of aircraft, in VTOL, is mainly produced by fuel engines
High-power thrust stabilized flight.
With reference to shown in Fig. 1, the fixed wing aircraft includes two rotor units, is provided with one of them described wing 2
One the first rotor unit, the second rotor unit is provided with another described wing 2.First rotor
4 equivalent formation two variable thrust fulcrums, the second rotor assemblies 5 of the second rotor unit etc. of the first rotor assemblies of unit
Effect forms a quantitative thrust fulcrum.A plane can be determined in geometrically three thrust fulcrums, when a branch of this plane
Point is fixed, the normal vector of the plane can be arbitrarily adjusted by two other fulcrum so as to realize that the balance of aircraft controls.Specifically
Mode is：Two fuel engines of the second rotor unit are using fixed rotary speed, two motor of the first rotor unit
Rotating speed can be needed to adjust according to flight respectively to change thrust size, to adjust the pitching of aircraft, on two axial directions of level
Balance, realize that balance of the aircraft in take-off process controls, ensures that aircraft steadily takes off or landed.With reference to shown in Fig. 2, Fig. 2 is
Fig. 1 mechanic equivalent schematic diagram.
With reference to shown in Fig. 3, the fixed wing aircraft includes three rotor units, is provided with one of them described wing 2
One the first rotor unit and the second rotor unit, the first rotor assemblies 4 and second of the first rotor unit
Second rotor assemblies 5 of rotor unit are combined, two variable thrust fulcrums of equivalent formation.The first rotor unit and described
Be arranged in parallel (the plane and the second of the second rotor unit that the first rotor of the first rotor unit turns over above and below second rotor unit
The plane that rotor turns over is relative to the diameter parallel of fuselage 1), the first rotor list is provided with another described wing 2
Member, the first rotor assemblies 4 of the first rotor unit form two variable thrust fulcrums.Because each rotor assemblies are relative to fuselage 1
Axisymmetrical is set, and the straight line of each equivalent formation of rotor unit on two wings 2 is parallel to each other, four variable thrust fulcrum shapes
The inertia geometrical plane of Cheng Yisi fulcrums.Four motor can need to adjust rotating speed respectively to change thrust size according to flight,
For adjusting course, pitching and rolling on three axis of movements of aircraft.With reference to shown in Fig. 4, the mechanic equivalent that Fig. 4 is Fig. 3 shows
It is intended to.
With reference to shown in Fig. 5, the fixed wing aircraft includes four rotor units, is respectively respectively arranged with two wings 2
One the first rotor unit and the second rotor unit, the first rotor unit and the second rotor unit
Be arrangeding in parallel up and down, (plane and the second rotor of the second rotor unit that the first rotor of the first rotor unit turns over turn over flat
Face is relative to the diameter parallel of fuselage 1).First rotor assemblies 4 of the first rotor unit on two wings 2 and the second rotor unit
Second rotor assemblies 5 are combined respectively, four variable thrust fulcrums of equivalent formation.Because each rotor assemblies are relative to the axle of fuselage 1
Line is symmetrical arranged, and the straight line of each equivalent formation of rotor unit on two wings 2 is parallel to each other, and four variable thrust fulcrums are formed
The inertia geometrical plane of one or four fulcrums.
The fixed wing aircraft also includes being used for the power control circuit for monitoring the motor and engine operating,
The power control circuit includes the dynamic of microprocessor, each motor coupled with the microprocessor and the engine
Power unit, to establish the logical relation mathematical modeling between each motor and the rotating speed of the engine.The motor
The speed regulator for detecting the motor speed is provided between the microprocessor, the speed regulator includes field-effect
Pipe.
Described above is only preferred embodiment of the present utility model, is not limited to the utility model, it is noted that
For those skilled in the art, on the premise of the utility model technical principle is not departed from, can also do
Go out some improvement and modification, these improvement and modification also should be regarded as the scope of protection of the utility model.
Claims (9)
1. a kind of VTOL fixed wing aircraft of oil electricity mixing, including fuselage, the wing for being symmetricly set on the fuselage both sides
With the empennage for being arranged on the fuselage tail end, it is characterised in that：Also include at least two rotor lists being arranged on the wing
Member, at least two described rotor units include at least one first rotor unit and at least one second rotor unit, described
First rotor unit is included on symmetrically arranged a pair of first rotor assemblies of the fuselage axis, the second rotor unit bag
Include on symmetrically arranged a pair of second rotor assemblies of the fuselage axis, it is adjustable that first rotor assemblies include rotary speed
The motor of section and the first rotor for being driven by it rotation, second rotor assemblies include starting using fixed rotary speed
Machine and the second rotor for being driven by it rotation, first rotor assemblies and second rotor assemblies are separately positioned on the machine
Tip extension, first rotor assemblies and second rotor assemblies form one three using asymmetrical control technology set-up mode
The inertia geometrical plane of fulcrum or four fulcrums.
A kind of 2. VTOL fixed wing aircraft of oil electricity mixing according to claim 1, it is characterised in that：The fixation
Wing aircraft also includes being used for the power control circuit for monitoring the motor and engine operating, the power control circuit
Each motor and the power unit of the engine coupled including microprocessor, with the microprocessor.
A kind of 3. VTOL fixed wing aircraft of oil electricity mixing according to claim 1, it is characterised in that：Described first
In the rotation with surface parallel to the fuselage axis, its rotational angle is 0-90 ° for rotor assemblies and the second rotor assemblies of institute.
A kind of 4. VTOL fixed wing aircraft of oil electricity mixing according to claim 1, it is characterised in that：The fixation
Wing aircraft includes two rotor units, and the first rotor unit, another institute are provided with one of them described wing
State and the second rotor unit is provided with wing.
A kind of 5. VTOL fixed wing aircraft of oil electricity mixing according to claim 1, it is characterised in that：The fixation
Wing aircraft includes three rotor units, is provided with one of them described wing described in the first rotor unit and one
Second rotor unit, the first rotor unit and the second rotor unit be arranged in parallel up and down, on another described wing
It is provided with the first rotor unit or the second rotor unit.
A kind of 6. VTOL fixed wing aircraft of oil electricity mixing according to claim 1, it is characterised in that：The fixation
Wing aircraft includes four rotor units, is respectively respectively arranged with described in the first rotor unit and one on two wings
Second rotor unit, the first rotor unit and the second rotor unit be arranged in parallel up and down.
A kind of 7. VTOL fixed wing aircraft of oil electricity mixing according to claim 2, it is characterised in that：It is described electronic
The speed regulator for detecting the motor speed is provided between machine and the microprocessor, the speed regulator includes field-effect
Pipe.
A kind of 8. VTOL fixed wing aircraft of oil electricity mixing according to claim 1, it is characterised in that：Described first
The ratio between the diameter of rotor and the wing length are 0.1-0.6, and the ratio between second rotor and the wing length are 0.1-
0.6。
A kind of 9. VTOL fixed wing aircraft of oil electricity mixing according to claim 1, it is characterised in that：The fuselage
Material with wing is glass fiber compound material, the one or more in carbon fibre composite, Metal plate, balsa wood material
Combination.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720512366.6U CN207000818U (en) | 2017-05-10 | 2017-05-10 | A kind of VTOL fixed wing aircraft of oil electricity mixing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720512366.6U CN207000818U (en) | 2017-05-10 | 2017-05-10 | A kind of VTOL fixed wing aircraft of oil electricity mixing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207000818U true CN207000818U (en) | 2018-02-13 |
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ID=61443204
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720512366.6U Active CN207000818U (en) | 2017-05-10 | 2017-05-10 | A kind of VTOL fixed wing aircraft of oil electricity mixing |
Country Status (1)
| Country | Link |
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| CN (1) | CN207000818U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107128489A (en) * | 2017-05-10 | 2017-09-05 | 优飞科技（苏州）有限公司 | A kind of VTOL fixed wing aircraft of oil electricity mixing |
| WO2020035715A1 (en) * | 2018-08-15 | 2020-02-20 | Gary Anthony Daprato | Aircrafts with controllers and tiltable rotors for attitude-controlled flight |
-
2017
- 2017-05-10 CN CN201720512366.6U patent/CN207000818U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107128489A (en) * | 2017-05-10 | 2017-09-05 | 优飞科技（苏州）有限公司 | A kind of VTOL fixed wing aircraft of oil electricity mixing |
| WO2020035715A1 (en) * | 2018-08-15 | 2020-02-20 | Gary Anthony Daprato | Aircrafts with controllers and tiltable rotors for attitude-controlled flight |
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Legal Events
| Date | Code | Title | Description |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20211111 Address after: Room 102, No. 10, Lane 2500, xiupu Road, Pudong New Area, Shanghai 200120 Patentee after: Shanghai Youqian Intelligent Technology Co., Ltd Address before: 215000 Room 401, building 9, Northwest District, Suzhou nano City, No. 99, Jinjihu Avenue, Suzhou Industrial Park, Jiangsu Province Patentee before: Youfei Technology (Suzhou) Co., Ltd |