CN106672232A - Efficient vertical takeoff and landing aircraft - Google Patents
Efficient vertical takeoff and landing aircraft Download PDFInfo
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- CN106672232A CN106672232A CN201710119002.6A CN201710119002A CN106672232A CN 106672232 A CN106672232 A CN 106672232A CN 201710119002 A CN201710119002 A CN 201710119002A CN 106672232 A CN106672232 A CN 106672232A
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- 238000010276 construction Methods 0.000 claims description 5
- 230000007246 mechanism Effects 0.000 abstract description 14
- 238000006243 chemical reaction Methods 0.000 abstract description 6
- 238000013461 design Methods 0.000 abstract description 3
- 238000012360 testing method Methods 0.000 description 6
- 238000010586 diagram Methods 0.000 description 5
- 238000000034 method Methods 0.000 description 5
- 230000008520 organization Effects 0.000 description 3
- 230000001141 propulsive effect Effects 0.000 description 3
- 241000566150 Pandion haliaetus Species 0.000 description 2
- 238000005452 bending Methods 0.000 description 2
- 230000008901 benefit Effects 0.000 description 2
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- 238000005516 engineering process Methods 0.000 description 2
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- 241000283084 Balaenoptera musculus Species 0.000 description 1
- 230000033228 biological regulation Effects 0.000 description 1
- 230000000052 comparative effect Effects 0.000 description 1
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- 238000011161 development Methods 0.000 description 1
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- 238000005265 energy consumption Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
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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
- B64C27/22—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
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/34—Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- 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
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/52—Tilting of rotor bodily relative to fuselage
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
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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
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C2009/005—Ailerons
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- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
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Abstract
The invention relates to an efficient vertical takeoff and landing aircraft, and discloses an efficient vertical takeoff and landing fixed-wing unmanned aerial vehicle, which comprises a fuselage, a wing, a horizontal tail, a vertical tail, a control surface, a power unit, a tilting mechanism and an undercarriage. The tilting mechanism controls the tilting angle of the wing and the horizontal tail to realize the mutual conversion of a vertical takeoff and landing state and a flat flight state of the aircraft. A propeller power unit is arranged on each of the wing and the horizontal tail, a part of lift at the vertical takeoff and landing stage is provided by the wing propeller power unit, and the tail propeller power unit is responsible for the aircraft pitch balance adjustment; the power device installed on the wing is closed in the flat flight state, and the tail propeller power unit provides forward thrust in order to improve the efficiency of the aircraft in a cruising state. Compared with the existing vertical takeoff and landing fixed-wing unmanned aerial vehicle design scheme, the flight aerodynamic efficiency of the aircraft in the fixed-wing flat flight state is taken into account while the layout is simplified, and reliability and practicability are relatively high.
Description
Technical field
The invention belongs to aviation aircraft design field, more particularly to a kind of efficient multi-purpose, while can reach solid again
Determine the vertical take-off and landing unmanned aerial vehicle of wing cruising flight efficiency.
Background technology
Current most common unmanned vehicle mainly has two kinds of forms of many rotors and fixed-wing, multi-rotor aerocraft construction letter
Single, simple to provide lift by rotor, control response is more sensitive, can accomplish VTOL and spot hover, but such winged
Row device is due to no thrust power, while pneumatic efficiency is low, causes its forward flight speed slow, and wind loading rating is weak, and endurance is poor;
, using the flight layout for passing through extensive checking, pneumatic efficiency is higher, can realize patrolling for long period for fixed-wing unmanned plane
Boat flight and flying speed higher, but such aircraft will reach certain speed during takeoff and landing, to rising
Drop place there are certain requirements, while spot hover and low-speed operations cannot be carried out so that its scope of application receives very big limit
System.
For the advantage of comprehensive both aircraft, exploitation one kind can realize that VTOL and spot hover can be carried out again
The aircraft of prolonged high speed cruise flight, people have carried out extensive trial, wherein enter the practical stage earliest is beautiful
V-22 " osprey " tilt rotor aircraft that state develops, have also appeared a series of rotations of verting such as XV-15, " hawkeye " and V-44 afterwards
The wing verifies type and concept type, and China also once illustrated " blue whale " tilting rotor concept aircraft.
Above aircraft realizes VTOL and high speed fixed-wing two kinds of moulds of cruise mostly by the way of tilting rotor
The conversion of formula, in the VTOL stage, it is functionally similar to lifting airscrew to aircraft propeller, is providing liter vertically upward
The attitude of aircraft is adjusted by feathering while power, 90 degree need to be tilted forward for aircraft is carried in fixed-wing
For thrust power, this causes that such aircraft propeller must is fulfilled for lifting airscrew and fixed-wing propulsion two kinds of characteristics of oar, this
Sample does not simply fail to take into account the blade aerodynamic efficiency under two states, and also results in rotor controlling organization and control method is very multiple
It is miscellaneous, simultaneously because wing does not vert together with propeller, cause VTOL stage wing to produce propeller downwash flow
Interference, reduce further the pneumatic efficiency and control stability of aircraft.Above deficiency result in such aircraft safety
General aircraft is far below with reliability, in actual use Frequent Accidents.
The China Patent Publication No. CN203332392U fixed-wing unmanned planes that can vert propose a kind of tilting wing unmanned plane,
Using tandem wing configurations, before and after fuselage both sides are set two pairs can tilting wing, and spiral is set in the middle part of each wing
Oar propulsive mechanism, the VTOL of aircraft and the conversion of fixed-wing cruise both of which realized by verting for the two pairs of wings,
Afterbody is additionally mounted with vertical fin and horizontal tail.
China Patent Publication No. 205440867U propose can tilting wing aircraft is also adopted by is tandem wing configurations,
Each wing middle part arrangement propeller drive mechanism, rear wing rear propeller sets vertical rudder face.
It is used for the propeller of different flight state from having been put into be can be seen that on widely used aircraft at present, its
Configuration makes a big difference, particularly for providing the helicopter lifting airscrew oar of lift and for providing fixation vertically upward
The high performance airscrew of wing aircraft forward thrust, either all there is significance difference in both from shape size or in mechanical structure
Different, this is that, because the aerodynamic conditions difference of propeller under different flight state is larger, propeller must be from aerodynamic configuration and inside
The pneumatic efficiency that this aerodynamic conditions could remain higher is adapted in structure, and then meets routine use requirement, therefore as same
When to take into account the vertically taking off and landing flyer of VTOL state and high speed fixed-wing cruising condition, it is necessary to consider both state gas
The different influences to aircraft propeller pneumatic efficiency of dynamic condition.As practical V-22 " osprey " tilting rotor of unique input
Aircraft just employs the propeller similar to lifting airscrew to maintain the pneumatic effect under helicopter state (lift mode)
Rate, but the inherent shortcoming that its forward flight speed and voyage will be far below the Fixed Wing AirVehicle of same order is also brought simultaneously.With
Above-mentioned patent be representative prior art in VTOL state and high speed fixed-wing cruising condition also use identical spiral
Oar provides lift and propulsive force, does not consider the difference of propeller pneumatic efficiency under both modes, causes propeller extremely
In inefficient state under few pattern a kind of wherein, it is impossible to the overall effective utilization of aircraft is improved, in particular with flight
The maximization of device, for the continuous improvement of the index requests such as its voyage and flying speed, this influence can be more obvious.
Meanwhile, most schemes use tandem wing in the prior art with above-mentioned patent as representative, preceding to fly over journey
In interference of the preceding wing purling to rear wing and propeller can cause aircraft entirety pneumatic efficiency and control stability under
Drop.
Additionally, the load that tilting wing aircraft wing is born will be more than common Fixed Wing AirVehicle and multi-rotor aerocraft
Will complexity, the pulling force and oscillating load of propeller under plumbness should be born, bear again pneumatic moment of flexure under horizontality,
Moment of torsion and shearing force, and these load are transferred to fuselage by airfoil root tie point, thus airfoil root and fuselage company
The structure type of socket part position directly determines the load-bearing rigidity and intensity of this wing.In prior art with above-mentioned patent as representative
Middle wing uses main girder structure, airfoil root to be connected with fuselage by a pipe, and wing loads are passed by this root pipe
Fuselage is delivered to, due to shape limitation, the sectional area of connecting circular tube will be much smaller than the cross-sectional area at wing wing root, and this is equivalent to machine
Wing structure generates an abrupt change of cross-section at tie point, causes partial structurtes significant stress concentration phenomenon occur, greatly
Reduce the load-carrying efficiency of wing structure.
The content of the invention
Regarding to the issue above, can be while VTOL and the cruise of high speed fixed-wing will it is an object of the invention to provide one kind
Ask, the aircraft of pneumatic efficiency higher can be ensured under the two offline mode again, be laid out compared with existing program simpler
Clean reasonable, pneumatic efficiency and reliability are higher.
Technical purpose of the invention is realized by following any technical scheme.
A kind of VUAV, including fuselage 1, can tilting wing 2, be arranged on wing wing power set 3,
Can be verted tailplane 5 and the empennage power set 6 being arranged on tailplane, it is characterised in that the wing power set 3
There is different rotating speed and/or lift with empennage power set 6.
According to the described VUAV of one of above-mentioned technical proposal, it is characterised in that the wing power set 3
Including low speed lift oar.
According to the described VUAV of one of above-mentioned technical proposal, it is characterised in that the empennage power set 6
Including propelled at high velocity oar.
According to the described VUAV of one of above-mentioned technical proposal, it is characterised in that the low speed lift oar
Blade is packed up into folding after fixed-wing cruising condition in the unmanned plane.
According to the described VUAV of one of above-mentioned technical proposal, it is characterised in that the wing power set 3
Closed after the unmanned plane enters fixed-wing cruising condition.
According to the described VUAV of one of above-mentioned technical proposal, it is characterised in that the unmanned plane also includes
The vertical tail 4 of fuselage is fixed on, the vertical tail can not vert.
According to the described VUAV of one of above-mentioned technical proposal, it is characterised in that the wing is arranged at institute
State body upper.
According to the described VUAV of one of above-mentioned technical proposal, it is characterised in that verting for the wing turns
Axle is disposed in proximity to the position of trailing edge.
According to the described VUAV of one of above-mentioned technical proposal, it is characterised in that the wing 2 or so is put
At least 2 propeller power set using low speed lift oar, the tailplane 5 sets at least 1 and uses propelled at high velocity oar
Propeller power set.
According to the described VUAV of one of above-mentioned technical proposal, it is characterised in that the unmanned plane also includes
Nose-gear 8 and rear undercarriage 9, both of which uses wheeled construction.
In one more specifically technical scheme, the present invention is using a kind of flight of tilting wing in order to achieve the above object
Device, including main machine body, can tilting wing, the tailplane that can vert, aerofoil inclining rotary mechanism, vertical tail and propeller power dress
Put.The propeller power set are separately mounted on wing and tailplane, in aircraft flight mode transition procedure with
Aerofoil verts jointly, wherein wing propeller power set mainly be responsible for provide VTOL state under aircraft lift and portion
Point gesture stability, tailplane propeller power set be mainly responsible under VTOL state aircraft pitch attitude controling power with
And thrust power under preceding winged state.The aerofoil inclining rotary mechanism is responsible between aircraft vertical landing and fixed-wing cruise mode
Transfer process in wing and tailplane relative to fuselage corner adjustment.
In another more specifically technical scheme, the wing propeller power set and tailplane propeller are dynamic
Power apparatus are respectively adopted the propeller of multi-form, and wherein wing propeller power set are used similar to helicopter lifting rotor
Low speed lift oar, provide efficient lift in the aircraft vertical landing stage, the oar after aircraft enters fixed-wing cruising condition
Leaf folds back and packs up to reduce flight resistance;Tailplane propeller power set use propelled at high velocity propeller, in flight
Pneumatic efficiency higher is maintained under device fixed-wing cruise mode, power consumption is reduced, extends the flight time.
In another more specifically technical scheme, the tailplane is converted to complete dynamic flat under fixed cruise mode
Tail, can up and down deflect along tiliting axis in the range of certain angle, while driving tailplane propeller power set jointly inclined
Turn, realize that two-dimensional vector is advanced, so that horizontal tail primary control surface is no longer needed, by empennage inclining rotary mechanism and tailplane primary control surface
Mechanism unites two into one, and simplifies the controlling organization of aircraft, while improve the flat winged state aircraft pitch control of fixed-wing again
Efficiency.Additionally, the vertical tail is no longer linked with horizontal rear wing structure, but it is attached with fuselage respectively, is realized
The separation arrangement of structure, vertical tail is fixed relative to fuselage during patten transformation, is not deflected jointly with horizontal tail, so
Influence of the vertical tail to empennage inclining rotary mechanism is avoided, so that horizontal tail structure is more succinct, horizontal tail structure weight is reduced
Amount.
In another more specifically technical scheme, the wing is arranged in body upper, and wing verts rotating shaft placement
An envelope for extending to two ends wing power set fixing point is being formed at the position of trailing edge, the leading edge of a wing to rotating shaft
The central wing box structure of enclosed, setting vert rotating shaft tie point and fuselage of wing in wing box trailing edge centre position carries out hinge company
Connect, wing box lower surface centre position sets attachment lug and wing actuation mechanism of verting and is attached, by this tie point at two
Wing loads are converted into concentrated force and are transferred to fuselage.Due to wing box structure through left and right wing and unlike girder formula wing that
Sample is limited by pipe connection shape and size, and the cross-sectional area at wing wing root is increased on to greatest extent, reduces the wing
The local stress concentration degree of root so that the integral rigidity and intensity of wing are particularly antitorque, bending resistance is compared to girder
Formula wing is obviously improved, it is to avoid wing occurs that deformation is excessive in flight course, or even the serious of aileron reversal occurs and ask
Topic, improves the safety of structure of aircraft while wing structure weight is mitigated.
In another more specifically technical scheme, the airframe structure is further included with the wheeled of turning function
Landing gear structure, so that flying instrument runs landing function for the sliding of fixed wing aircraft, in the case where power set fail
Landing can be slided, the reliability and security of aircraft is drastically increased.
Using the tiltrotor aircraft of technical solution of the present invention, its remarkable advantage includes:
(1) wing propeller power set and tailplane propeller power set are respectively adopted low speed lift oar and high speed
Propulsion oar, is each responsible for the lift in VTOL stage and the thrust power of fixed-wing cruising phase so that aircraft is in difference
Its flight efficiency is obviously improved than the VTOL Fixed Wing AirVehicle using single form propeller under offline mode, right
This inventor has carried out substantial amounts of proving flight, and comparative result of specifically taking a flight test is reference can be made to specific embodiment 3.
(2) using the stabilator with vector propulsion, while tailplane and vertical tail realize that structure is separated, letter
Empennage controlling organization is changed, has reduced horizontal tail construction weight, while improve the pitching control under aircraft fixed-wing cruise mode
Efficiency processed.
(3) wing mainly carries position using integrally closed central wing box instead of the girder in general wing structure,
Structural bearing efficiency and integral rigidity and intensity are improved, the structure peace of wing is improve while wing structure weight is mitigated
Full property and reliability.
(4) aircraft still can be carried out except that can realize VTOL in the case of partial power failure of apparatus
The rolling start and landing of traditional fixed wing aircraft, further increase safety and reliability.
Brief description of the drawings
Fig. 1 is placement scheme schematic diagram of the aircraft of the invention under VTOL pattern;
Fig. 2 is schematic diagram of the aircraft of the invention under fixed-wing cruise mode;
Fig. 3 is the deflection schematic diagram of flying tail and power set under aircraft fixed-wing cruise mode of the invention;
Fig. 4 is position view of the overall center wing box structure of aircraft of the invention in wing;
Fig. 5 is aircraft wing center of the invention wing box overall structure diagram;
Fig. 6 is that aircraft wing wing root center wing box structure of the invention and main beam structure transversal profile compare figure;
Fig. 7 is the placement scheme schematic diagram after aircraft of the invention increases power set.
Specific embodiment
Below in conjunction with drawings and Examples, the invention will be further described.
Embodiment 1
Fig. 1~3 show the basic structure layout and the method for operation of a kind of new vertical takeoff and landing vehicle of the invention.Should
Aircraft include fuselage 1, the wing 2 on the top of fuselage 1, the propeller power set 3 of the both sides of wing 2 and aileron control rudder face 10,
Vertical tail 4 and vertical fin primary control surface 11 on rear side of back, the verted stabilator 5 of the afterbody of fuselage 1 and installation
Propeller power set 6 on tailplane, fuselage 1 further includes to control the actuation mechanism 7 and can of verting of wing deflection
For the sliding nose-gear 8 and rear undercarriage 9 for running landing.
Propeller power set 3 and wing 2 are relatively fixed, by actuation mechanism 7 of verting in offline mode transfer process
Together deflect, wing power set 3 use the low speed rotor with folder function, its aerodynamic configuration and structure similar to
Helicopter lifting rotor, can so ensure that aircraft possesses pneumatic efficiency higher under VTOL pattern.Work as aircraft
Into after high speed fixed-wing cruise mode, as shown in Fig. 2 propeller power set 3 are stopped to reduce energy ezpenditure, while
Blade is folded back to reduce the air drag of aircraft, and aileron control rudder face 10, vertical fin primary control surface are passed through in flight course
11 and tailplane 5 come the flight attitude that controls and adjust aircraft.
Propeller power set 6 and tailplane 5 are relatively fixed, and both VTOL stages deflect to hangs down with fuselage axis
Straight position, controling power, fixed-wing cruising phase level are controlled by propeller power set 6 for aircraft provides attitude regulation
Empennage 5 drives propeller power set 6 to be deflected up and down along tiliting axis, such as Fig. 3 to be initial position with fuselage axis parallel position
It is shown, while winged propulsive force and pitch control power before being provided for aircraft, to fly pneumatic efficiency, propeller before ensureing aircraft
Power set 6 are using the conventional propelled at high velocity oar of traditional Fixed Wing AirVehicle.
The wheeled construction that nose-gear 8 and rear undercarriage 9 are commonly used using Fixed Wing AirVehicle, possesses sliding race landing function,
Both the ground supports in VTOL stage had been can be used for, it is also possible in the case where partial power fails with fixed-wing offline mode
Gliding landing.
Fig. 4~5 illustrate position and the overall structure form of wing center of the present invention wing box 12, and wing center wing box 12 is entered
One step includes power set jointing 13, wing rotating shaft jointing 14 and inclining rotary mechanism jointing 15, respectively same spiral shell
Rotation oar power set 3, wing vert rotating shaft and wing verts, and actuation mechanism 7 is attached.Wing center wing box 12 is used
Composite or aerolite are integrally manufactured, and local strengthening is carried out at jointing position, wing other aerofoil knots
Structure is attached by way of being glued or mechanically connecting with wing center wing box 12.Fig. 6 special exhibitions wing of the present invention
The transversal profile of wing root, as can be seen from the figure the area in central wing box scheme wing root section 16 is than girder scheme wing root section
17 at least increase by more than 3 times, and the stress water of airfoil root can be effectively reduced when wing twist load and bending load is transmitted
It is flat, reduce the overall deformation of wing.
Implement row 2
As shown in fig. 7, the 4 propeller power set 3 using low speed lift oar that are symmetrically arranged on wing 2,
Be symmetrically arranged two propeller power set 6 using propelled at high velocity oar on tailplane 5, increases relative to embodiment 1
The lift of whole machine, improves its load-carrying ability, while the rotational speed difference that can combine power set propeller further be improved
Flying vehicles control efficiency, wherein difference of the propeller power set 3 under fixed-wing cruise mode according to state of flight can be by
Propeller all folds back and packs up or only pack up two of which, improve adaptability of the aircraft under different flying conditions and
Reliability.
Embodiment 3
Based on technical scheme, inventor is designed into Late Stage Verification and takes a flight test development from the initial scheme of aircraft
Substantial amounts of creative work, during taking a flight test, inventor is had found for VTOL Fixed Wing AirVehicle, using different spiral shells
Rotation oar can be produced to its flight efficiency under different flight state and significantly affected.For further clear and definite this species diversity, invention
People uses the aircraft of technical solution of the present invention, and different propellers are respectively adopted under identical flying condition have been carried out vertically
Landing and fixed-wing are cruised the taking a flight test of both states, and power required during stable state is in aircraft in the case of each
Device minimum throttle is recorded, and record result is as shown in the table:
As can be seen from the above table, can all hung down respectively using the aircraft of low speed lift oar and propelled at high velocity propeller
Straight landing stage and fixed-wing cruising phase keep relatively low accelerator open degree and then maintenance flight efficiency higher, but when both
After aircraft conversion offline mode, it maintains the minimum accelerator open degree of stabilized flight condition to improve rapidly, greatly improves
Energy expenditure rate, reduces the flight efficiency of aircraft, especially with the aircraft of low speed lift oar, in fixed-wing cruise rank
Section blade efficiency significantly declines, while larger paddle size further increases the air drag of aircraft, in order to maintain
The state of flight of stabilization, it is necessary to which all power set are fully open, this causes the energy expenditure rate of aircraft or even is far above
VTOL state, has deviated from by fixed-wing cruise to improve the design original intention of aircraft flight efficiency.Further, since conversion
During throttle mutation, easily cause the unstable of aircraft, generated for the flight safety and reliability of aircraft non-
Normal detrimental effect.Meanwhile, inventor has found during taking a flight test, and is occurred without in aircraft overall resistance and increases considerably and move
In the case that power apparatus have pneumatic efficiency higher, it is only necessary to can just be patrolled for aircraft provides fixed-wing by empennage power set
Thrust power needed for boat so that aircraft energy consumption is reduced to 35% (using the concrete scheme of embodiment 1) in VTOL stage
Hereinafter, therefore, inventor is respectively adopted and gone straight up to using creative mentality of designing in wing power set and empennage power set
Machine rotor lift oar and propelled at high velocity propeller, and close wing power set and by low speed lift oar in fixed-wing cruising phase
Fold back to reduce air drag, so as to the flight efficiency that can make aircraft remain higher under different conditions, from table
As can be seen that during taking a flight test, using the aircraft of technical solution of the present invention, its throttle is able to maintain that relatively reasonable at one
Interval, flight efficiency of the aircraft under each state of flight can be effectively improved, with more preferable practicality.
All embodiments are used for illustrative purposes only above, rather than limitation of the present invention, about the technology of technical field
Personnel, without departing from the spirit and scope of the present invention, can also make various conversion or change, therefore all equivalent
Technical scheme should also belong to scope of the invention and should be limited by each claim.
Claims (10)
1. a kind of VUAV, including fuselage (1), can tilting wing (2), the wing power set that are arranged on wing
(3), can vert tailplane (5) and the empennage power set (6) that are arranged on tailplane, it is characterised in that the wing
Power set (3) and empennage power set (6) are with different rotating speed and/or lift.
2. VUAV according to claim 1, it is characterised in that the wing power set (3) are including low
Fast lift oar.
3. VUAV according to claim 1, it is characterised in that the empennage power set (6) are including height
Speed propulsion oar.
4. VUAV according to claim 2, it is characterised in that the blade of the low speed lift oar is described
Unmanned plane is packed up into folding after fixed-wing cruising condition.
5. VUAV according to claim 1, it is characterised in that the wing power set (3) are described
Unmanned plane is closed after entering fixed-wing cruising condition.
6. VUAV according to claim 1, it is characterised in that the unmanned plane also includes being fixed on fuselage
Vertical tail (4), the vertical tail can not vert.
7. VUAV according to claim 1, it is characterised in that the wing is arranged on the fuselage
Side.
8. VUAV according to claim 7, it is characterised in that the rotating shaft of verting of the wing is arranged at leans on
The position of nearly trailing edge.
9. VUAV according to claim 1, it is characterised in that put at least 2 in wing (2) left and right
Using the propeller power set of low speed lift oar, the tailplane (5) sets at least 1 spiral using propelled at high velocity oar
Oar power set.
10. VUAV according to claim 1, it is characterised in that the unmanned plane also includes nose-gear
(8) and rear undercarriage (9), both of which uses wheeled construction.
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CN201710119002.6A CN106672232A (en) | 2017-03-02 | 2017-03-02 | Efficient vertical takeoff and landing aircraft |
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CN201710119002.6A CN106672232A (en) | 2017-03-02 | 2017-03-02 | Efficient vertical takeoff and landing aircraft |
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Cited By (54)
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