CN206552260U - A kind of efficient vertically taking off and landing flyer - Google Patents
A kind of efficient vertically taking off and landing flyer Download PDFInfo
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- CN206552260U CN206552260U CN201720194703.1U CN201720194703U CN206552260U CN 206552260 U CN206552260 U CN 206552260U CN 201720194703 U CN201720194703 U CN 201720194703U CN 206552260 U CN206552260 U CN 206552260U
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Abstract
The utility model discloses a kind of efficient vertically taking off and landing flyer, it is made up of fuselage, wing, tailplane, vertical tail, control rudder face, power set, inclining rotary mechanism and undercarriage.Inclining rotary mechanism controls the tilt angle of wing and tailplane, realize the phase co-conversion of the winged state of aircraft vertical landing state peace, propeller power set are mounted on wing and tailplane, VTOL stage aircraft major part lift is provided by wing propeller power set, empennage propeller power set are responsible for aircraft pitch balance adjustment, the power set installed on flat winged state lower wing are closed, forward thrust is provided by empennage propeller power set, to improve efficiency of the aircraft under flat winged cruising condition.Compared to existing VTOL fixed-wing unmanned aerial vehicle design scheme, the utility model has taken into account flight pneumatic efficiency of the aircraft under the flat winged state of fixed-wing while simplified topology, and reliability is higher with practicality.
Description
Technical field
The utility model belongs to aviation aircraft design field, more particularly to a kind of efficient multi-purpose, while can reach again
To the vertical take-off and landing unmanned aerial vehicle of fixed-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, wind loading rating is weak, and endurance is poor；
The flight layout that fixed-wing unmanned plane is verified extensively using passing through, pneumatic efficiency is higher, can realize patrolling for long period
Boat flight and higher flying speed, 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 can not be carried out so that its scope of application receives very big limit
System.
In order to integrate the advantage of both aircraft, exploitation one kind can realize VTOL and spot hover and can carry out
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 posture of aircraft is adjusted by feathering while power, need to tilt forward 90 degree in fixed-wing carries for aircraft
For thrust power, this make it that such aircraft propeller must is fulfilled for lifting airscrew and fixed-wing promotes 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 being set in fuselage both sides 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 two pairs of wings,
Afterbody is additionally mounted with vertical fin and horizontal tail.
China Patent Publication No. 205440867U propose can tilting wing aircraft also use tandem wing configurations,
Arrangement propeller drive mechanism in the middle part of each wing, rear wing rear propeller sets vertical rudder face.
It is used for the propeller of different flight state from having been put into 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
It is different, this be due to propeller under different flight state aerodynamic conditions difference it 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.It is used 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 also bring simultaneously its forward flight speed and voyage will far below the Fixed Wing AirVehicle of same order inherent shortcoming.With
Above-mentioned patent also uses identical spiral for the prior art of representative in VTOL state and high speed fixed-wing cruising condition
Oar provides lift and propulsive force, the difference of the pneumatic efficiency of propeller under both modes is not considered, 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, tandem wing is used using above-mentioned patent as the most schemes of the prior art of representative, it is preceding to fly over journey
In interference of the preceding wing purling to rear wing and propeller can cause under the overall pneumatic efficiency of aircraft and control stability
Drop.
In addition, 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, therefore the company of airfoil root and fuselage by airfoil root tie point
The structure type of socket part position directly determines the load-bearing rigidity and intensity of this wing.Using above-mentioned patent as the prior art of representative
Middle wing uses main girder structure, and airfoil root is connected by a pipe with fuselage, 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.
Utility model content
In view of the above-mentioned problems, the purpose of this utility model is to provide, one kind can VTOL and high speed fixed-wing be patrolled simultaneously
Boat is required, can ensure the aircraft of higher pneumatic efficiency under the two offline mode again, is laid out more compared with existing program
Plus it is succinct reasonable, pneumatic efficiency and reliability are higher.
Technical purpose of the present utility model 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.
VUAV according to one of above-mentioned technical proposal, it is characterised in that the wing power set 3
Including low speed lift oar.
VUAV according to one of above-mentioned technical proposal, it is characterised in that the empennage power set 6
Including propelled at high velocity oar.
VUAV according to one of above-mentioned technical proposal, it is characterised in that the low speed lift oar
Blade is folded after the unmanned plane enters fixed-wing cruising condition and packed up.
VUAV according to 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.
VUAV according to 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.
VUAV according to one of above-mentioned technical proposal, it is characterised in that the wing is arranged at institute
State body upper.
VUAV according to 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.
VUAV according to 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 to use propelled at high velocity oar
Propeller power set.
VUAV according to 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 utility model uses a kind of tilting wing in order to achieve the above object
Aircraft, including main machine body, can tilting wing, the tailplane that can vert, aerofoil inclining rotary mechanism, vertical tail and propeller power
Device.The propeller power set are separately mounted on wing and tailplane, in aircraft flight mode transition procedure
Verted jointly with aerofoil, wherein wing propeller power set mainly be responsible for provide VTOL state under aircraft lift and
Part gesture stability, tailplane propeller power set are mainly responsible for aircraft pitch attitude controling power under VTOL state
And thrust power under preceding winged state.The aerofoil inclining rotary mechanism be responsible for aircraft vertical landing and fixed-wing cruise mode it
Between 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 moved
Various forms of propellers are respectively adopted in power apparatus, and wherein wing propeller power set, which are used, is 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, which folds back, to be packed up to reduce flight resistance；Tailplane propeller power set use propelled at high velocity propeller, in flight
Higher pneumatic efficiency 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 be deflected along tiliting axis in the range of certain angle, while driving tailplane propeller power set jointly inclined
Turn, realize that two-dimensional vector is promoted, 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 improving the flat winged state aircraft pitch control of fixed-wing again
Efficiency.In addition, the vertical tail is no longer linked with horizontal rear wing structure, but it is attached, realizes with fuselage respectively
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 formed at the position close to trailing edge, the leading edge of a wing to rotating shaft
The central wing box structure of enclosed, sets vert rotating shaft tie point and fuselage of wing to carry out hinge company in wing box trailing edge centre position
Connect, wing box lower surface centre position sets attachment lug and wing actuation mechanism of verting to be attached, pass through 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 added on to greatest extent, the wing is reduced
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 further comprises 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 solutions of the utility model, its remarkable advantage includes：
(1) low speed lift oar and high speed is respectively adopted in wing propeller power set and tailplane propeller power set
Oar is promoted, the lift in VTOL stage and the thrust power of fixed-wing cruising phase is each responsible for so that aircraft is in difference
Its flight efficiency is right than being obviously improved using the VTOL Fixed Wing AirVehicle of single form propeller under offline mode
This utility model people 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 promoted with vector, while tailplane and vertical tail realize that structure is separated, letter
Empennage controlling organization is changed, has reduced horizontal tail construction weight, while improving 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 improved 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 present utility model under VTOL pattern；
Fig. 2 is schematic diagram of the aircraft of the present utility model under fixed-wing cruise mode；
Fig. 3 is the deflection signal of flying tail and power set under aircraft fixed-wing cruise mode of the present utility model
Figure；
Fig. 4 is position view of the overall central wing box structure of aircraft of the present utility model in wing；
Fig. 5 is the central wing box overall structure diagram of aircraft wing of the present utility model；
Fig. 6 is that the central wing box structure of aircraft wing wing root of the present utility model and main beam structure transversal profile compare figure；
Fig. 7 is the placement scheme schematic diagram after aircraft increase power set of the present utility model.
Embodiment
Below in conjunction with drawings and examples, the utility model is described in further detail.
Embodiment 1
Fig. 1~3 show basic structure layout and the operation side of a kind of new vertical takeoff and landing vehicle of the present utility model
Formula.The aircraft includes fuselage 1, the wing 2 on the top of fuselage 1, the propeller power set 3 and aileron control rudder of the both sides of wing 2
Vertical tail 4 and vertical fin primary control surface 11 on rear side of face 10, back, the afterbody of fuselage 1 vert stabilator 5 and
Propeller power set 6 on tailplane, fuselage 1 further comprises the actuation mechanism 7 of verting for controlling wing deflection
And available for the sliding nose-gear 8 and rear undercarriage 9 for running landing.
Propeller power set 3 and wing 2 are relatively fixed, and pass through 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 are similar to
Helicopter lifting rotor, can so ensure that aircraft possesses higher pneumatic efficiency 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 expenditure, simultaneously
Blade folds back to reduce in the air drag of aircraft, flight course by aileron control rudder face 10, vertical fin primary control surface
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, provides attitude regulation for aircraft by propeller power set 6 and controls controling power, fixed-wing cruising phase level
Empennage 5 with fuselage axis parallel position as initial position, to drive propeller power set 6 to be deflected along above and below tiliting axis, such as Fig. 3
It is shown, while winged propulsive force and pitch control power before being provided for aircraft, to ensure to fly pneumatic efficiency, propeller before 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 it can be used for the ground supports in VTOL stage, can also be 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 the central wing box 12 of the utility model wing, wing center wing box
12 further comprise power set jointing 13, wing rotating shaft jointing 14 and inclining rotary mechanism jointing 15, respectively
Rotating shaft is verted with propeller power set 3, wing and wing actuation mechanism 7 of verting is attached.The central wing box 12 of the wing
Integrally it is manufactured using composite or aerolite, local strengthening, other wings of wing is carried out at jointing position
Face structure is attached by way of being glued or mechanically connecting with the central wing box 12 of wing.This practicality of Fig. 6 special exhibitions
The transversal profile of Novel aerofoil 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 increases by more than 3 times, and airfoil root can be effectively reduced when transmitting wing twist load and bending load
Stress level, reduce wing overall deformation.
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 complete machine, improves its load-carrying ability, while the rotational speed difference that can combine power set propellers further be improved
Flying vehicles control efficiency, wherein propeller power set 3 can be by according to the difference of state of flight under fixed-wing cruise mode
Propeller, which all folds back, packs up or only packs up two of which, improve adaptability of the aircraft under different flying conditions and
Reliability.
Embodiment 3
Based on the technical solution of the utility model, utility model people is designed into Late Stage Verification examination from the initial scheme of aircraft
Fly to have carried out substantial amounts of creative work, during taking a flight test, utility model human hair referring now to VTOL Fixed Wing AirVehicle,
Its flight efficiency under different flight state can be produced and significantly affected using different propellers.In order to further it is clear and definite this
Species diversity, utility model people uses the aircraft of technical solutions of the utility model, is respectively adopted not under identical flying condition
With propeller carried out VTOL and fixed-wing cruises the taking a flight test of both states, and aircraft in the case of each is in
The minimum throttle of required power set is recorded during stable state, and record result is as shown in the table：
As can be seen from the above table, it can all hung down respectively using the aircraft of low speed lift oar and propelled at high velocity propeller
Straight landing stage and the relatively low accelerator open degree of fixed-wing cruising phase holding and then the higher flight efficiency of maintenance, 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
Stable state of flight, 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 be mutated, easily cause the unstable of aircraft, for aircraft flight safety and reliability generate it is non-
Normal detrimental effect.Meanwhile, utility model people has found during taking a flight test, and occurs without and increases considerably in aircraft overall resistance
And in the case that power set have higher pneumatic efficiency, it is only necessary to just it can provide fixation for aircraft by empennage power set
Thrust power needed for wing cruise so that aircraft energy consumption is reduced to 35% (the specific side of use embodiment 1 in VTOL stage
Case) below, therefore, utility model people is distinguished using creative mentality of designing in wing power set and empennage power set
Wing power set and will be low are closed using lifting airscrew lift oar and propelled at high velocity propeller, and in fixed-wing cruising phase
Fast lift oar folds back to reduce air drag, so as to can make aircraft maintain higher flight effect under different conditions
Rate, as can be seen from the table, during taking a flight test, using the aircraft of technical solutions of the utility model, its throttle is able to maintain that
In a relatively reasonable interval, flight efficiency of the aircraft under each state of flight can be effectively improved, with more preferable
Practicality.
All embodiments are only for illustration of the utility model above, rather than to limitation of the present utility model, relevant technology neck
The technical staff in domain, in the case where not departing from spirit and scope of the present utility model, can also make various conversion or change,
Therefore all equivalent technical schemes, which should also belong to category of the present utility model, to be limited by each claim.
Claims (10)
1. a kind of efficient vertically taking off and landing flyer, including fuselage (1), can tilting wing (2), the wing power that is arranged on wing
Device (3), can vert tailplane (5) and the empennage power set (6) that are arranged on tailplane, it is characterised in that described
Wing power set (3) and empennage power set (6) have different rotating speed and/or lift.
2. efficient vertically taking off and landing flyer according to claim 1, it is characterised in that wing power set (3) bag
Include low speed lift oar.
3. efficient vertically taking off and landing flyer according to claim 1, it is characterised in that empennage power set (6) bag
Include propelled at high velocity oar.
4. efficient vertically taking off and landing flyer according to claim 2, it is characterised in that the blade of the low speed lift oar exists
The aircraft, which enters to fold after fixed-wing cruising condition, to be packed up.
5. efficient vertically taking off and landing flyer according to claim 1, it is characterised in that the wing power set (3) exist
The aircraft, which enters after fixed-wing cruising condition, closes.
6. efficient vertically taking off and landing flyer according to claim 1, it is characterised in that the aircraft also includes being fixed on
The vertical tail (4) of fuselage, the vertical tail can not vert.
7. efficient vertically taking off and landing flyer according to claim 1, it is characterised in that the wing is arranged at the fuselage
Top.
8. efficient vertically taking off and landing flyer according to claim 7, it is characterised in that the rotating shaft setting of verting of the wing
In the position close to trailing edge.
9. efficient vertically taking off and landing flyer according to claim 1, it is characterised in that wing (2) left and right put to
Few 2 propeller power set using low speed lift oar, the tailplane (5) sets at least 1 to use propelled at high velocity oar
Propeller power set.
10. efficient vertically taking off and landing flyer according to claim 1, it is characterised in that the aircraft also includes preceding rise
Fall frame (8) and rear undercarriage (9), both of which uses wheeled construction.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201720194703.1U CN206552260U (en) | 2017-03-02 | 2017-03-02 | A kind of efficient vertically taking off and landing flyer |
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