CN106672232A - Efficient vertical takeoff and landing aircraft - Google Patents

Efficient vertical takeoff and landing aircraft Download PDF

Info

Publication number
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
Authority
CN
China
Prior art keywords
wing
aircraft
power set
fixed
propeller
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN201710119002.6A
Other languages
Chinese (zh)
Inventor
胡龙
王博
王一博
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Beijing Tianyu New Super Aviation Technology Co Ltd
Original Assignee
Beijing Tianyu New Super Aviation Technology Co Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Beijing Tianyu New Super Aviation Technology Co Ltd filed Critical Beijing Tianyu New Super Aviation Technology Co Ltd
Priority to CN201710119002.6A priority Critical patent/CN106672232A/en
Publication of CN106672232A publication Critical patent/CN106672232A/en
Pending legal-status Critical Current

Links

Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C27/00Rotorcraft; Rotors peculiar thereto
    • B64C27/22Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
    • B64C27/26Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C25/00Alighting gear
    • B64C25/32Alighting gear characterised by elements which contact the ground or similar surface 
    • B64C25/34Alighting gear characterised by elements which contact the ground or similar surface  wheeled type, e.g. multi-wheeled bogies
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C27/00Rotorcraft; Rotors peculiar thereto
    • B64C27/04Helicopters
    • B64C27/08Helicopters with two or more rotors
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C27/00Rotorcraft; Rotors peculiar thereto
    • B64C27/22Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
    • B64C27/28Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C27/00Rotorcraft; Rotors peculiar thereto
    • B64C27/52Tilting of rotor bodily relative to fuselage
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C3/00Wings
    • B64C3/38Adjustment of complete wings or parts thereof
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C9/00Adjustable control surfaces or members, e.g. rudders
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C9/00Adjustable control surfaces or members, e.g. rudders
    • B64C2009/005Ailerons

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Toys (AREA)

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

A kind of efficient vertically taking off and landing flyer
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.
CN201710119002.6A 2017-03-02 2017-03-02 Efficient vertical takeoff and landing aircraft Pending CN106672232A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201710119002.6A CN106672232A (en) 2017-03-02 2017-03-02 Efficient vertical takeoff and landing aircraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201710119002.6A CN106672232A (en) 2017-03-02 2017-03-02 Efficient vertical takeoff and landing aircraft

Publications (1)

Publication Number Publication Date
CN106672232A true CN106672232A (en) 2017-05-17

Family

ID=58862445

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201710119002.6A Pending CN106672232A (en) 2017-03-02 2017-03-02 Efficient vertical takeoff and landing aircraft

Country Status (1)

Country Link
CN (1) CN106672232A (en)

Cited By (54)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107010218A (en) * 2017-06-01 2017-08-04 北京天宇新超航空科技有限公司 A kind of Flying-wing's vertically taking off and landing flyer
CN107150803A (en) * 2017-06-07 2017-09-12 天津科技大学 Mixed layout unmanned plane and its control method
CN107697279A (en) * 2017-10-16 2018-02-16 江富余 Vert afterbody high-speed helicopter
CN107719659A (en) * 2017-08-28 2018-02-23 南京达索航空科技有限公司 A kind of VTOL fixed-wing formula aircraft
CN107933909A (en) * 2017-12-17 2018-04-20 北京天宇新超航空科技有限公司 A kind of high-speed and high-efficiency tilting wing unmanned vehicle
CN107972848A (en) * 2017-12-06 2018-05-01 北京迪鸥航空科技有限公司 Aircraft redundance force vector controls tail vane
CN108045573A (en) * 2017-12-05 2018-05-18 长沙展朔轩兴信息科技有限公司 Pull in front and others push behind the multi-functional fixed-wing unmanned plane of formula
CN108058811A (en) * 2017-11-30 2018-05-22 易瓦特科技股份公司 The wing tip of adjustable angle applied to unmanned plane
CN108128448A (en) * 2018-01-08 2018-06-08 浙江大学 The coaxial tilting rotor wing unmanned aerial vehicle of double shoe formulas and its control method
CN108146630A (en) * 2017-11-30 2018-06-12 易瓦特科技股份公司 The power rotor structure of adjustable angle applied to unmanned plane
CN108177772A (en) * 2017-11-30 2018-06-19 易瓦特科技股份公司 The rotor airframe structure of adjustable angle applied to unmanned plane
CN108190014A (en) * 2017-11-30 2018-06-22 易瓦特科技股份公司 Wing tip fuselage applied to unmanned plane
CN108196565A (en) * 2018-03-04 2018-06-22 西北工业大学 A kind of novel unmanned plane and its attitude control method being combined based on projection with more rotors
CN108190017A (en) * 2017-11-30 2018-06-22 易瓦特科技股份公司 Rotor fuselage applied to unmanned plane
CN108190015A (en) * 2017-11-30 2018-06-22 易瓦特科技股份公司 The rotor fuselage of adjustable angle applied to unmanned plane
CN108216614A (en) * 2017-11-30 2018-06-29 易瓦特科技股份公司 The power wingtip device of adjustable angle applied to unmanned plane
CN108238232A (en) * 2016-12-27 2018-07-03 韩国科学技术院 Aircraft capable of taking off and landing vertically, flying vertically and horizontally and generating energy in air
CN108394560A (en) * 2018-03-15 2018-08-14 成鑫 A kind of fixed-wing unmanned plane and its landing method
CN108762299A (en) * 2018-05-30 2018-11-06 上海交通大学 A kind of unmanned plane formation method and fleet system
CN108995800A (en) * 2018-09-07 2018-12-14 佛山皖和新能源科技有限公司 A kind of novel rotor wing unmanned aerial vehicle structure
WO2018232787A1 (en) * 2017-06-19 2018-12-27 深圳市龙云创新航空科技有限公司 Vertical take-off and landing fixed-wing unmanned aerial vehicle
CN109094776A (en) * 2018-08-02 2018-12-28 西安君晖航空科技有限公司 The four of a kind of static-stability are verted wing unmanned plane
CN109110121A (en) * 2018-09-07 2019-01-01 佛山皖和新能源科技有限公司 A kind of novel three rotor wing unmanned aerial vehicles structure
CN109110120A (en) * 2018-09-07 2019-01-01 佛山皖和新能源科技有限公司 A kind of three rotor wing unmanned aerial vehicle lift systems
CN109353495A (en) * 2018-11-30 2019-02-19 南京航空航天大学 It is a kind of can VTOL unmanned autogyro
CN109703753A (en) * 2019-02-12 2019-05-03 欧阳军 A kind of new vertical takeoff and landing vehicle
CN109815528A (en) * 2018-12-13 2019-05-28 航天神舟飞行器有限公司 A method of the aircraft parameters optimization based on large-scale composite wing gas
CN110040248A (en) * 2019-04-26 2019-07-23 南京智飞航空科技有限公司 A kind of vertically taking off and landing flyer
CN110104163A (en) * 2019-04-28 2019-08-09 厦门大学 One kind can hang down flying wing type unmanned plane
CN110422328A (en) * 2019-08-26 2019-11-08 南京灵龙旋翼无人机系统研究院有限公司 A kind of tilting rotor wing unmanned aerial vehicle linear power configuration method and structure
CN110775261A (en) * 2019-11-19 2020-02-11 南京航空航天大学 Crossed composite high-speed helicopter and working method thereof
CN110775263A (en) * 2019-10-22 2020-02-11 上海交通大学 Tailstock type sea-air cross-region unmanned aerial vehicle and sea-air flight mode thereof
CN111137446A (en) * 2019-12-26 2020-05-12 中国空气动力研究与发展中心 Pneumatic layout of multi-rotor vertical take-off and landing unmanned aerial vehicle with stalling function
CN111152919A (en) * 2020-01-08 2020-05-15 北京建筑大学 Control method of unmanned aerial vehicle capable of taking off and landing vertically
CN111232195A (en) * 2019-11-05 2020-06-05 西安羚控电子科技有限公司 Carrier-borne heavy oil composite wing unmanned aerial vehicle
CN111409821A (en) * 2020-04-26 2020-07-14 北京航空航天大学合肥创新研究院 Solar unmanned aerial vehicle with tilting wings
CN111591440A (en) * 2020-05-27 2020-08-28 湖南省仙鸟科技有限公司 Sickle wing vertical take-off and landing aircraft
CN111674546A (en) * 2020-06-19 2020-09-18 南京航空航天大学 Rotor wing pneumatic appearance suitable for small and medium-sized unmanned tilt rotor wing aircraft
CN111801272A (en) * 2018-03-05 2020-10-20 特克诺维特有限公司 Thrust steering aircraft
CN112319795A (en) * 2020-11-30 2021-02-05 福州大学 Composite structure aircraft with tiltable rotor wing
CN113148138A (en) * 2021-03-15 2021-07-23 南京航空航天大学 Tailstock type unmanned aerial vehicle and control method
CN113232854A (en) * 2021-05-17 2021-08-10 南京航空航天大学 Distributed unmanned aerial vehicle platform applicable to ballistic launching and launching method
CN113260566A (en) * 2018-12-28 2021-08-13 列奥纳多股份公司 Thrust reverser aircraft and associated control method
JP2021522111A (en) * 2018-05-10 2021-08-30 ジョビー エアロ, インコーポレイテッドJoby Aero, Inc. Electric tilt rotor aircraft
CN113460297A (en) * 2021-07-21 2021-10-01 成都纵横大鹏无人机科技有限公司 Tilting power structure and system and aircraft
CN113753230A (en) * 2021-10-11 2021-12-07 广东汇天航空航天科技有限公司 Aircraft, wing subassembly and hovercar
CN114180048A (en) * 2021-12-29 2022-03-15 天津斑斓航空科技有限公司 Active tilting wing structure and aircraft
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
CN115092390A (en) * 2022-04-22 2022-09-23 中国航空研究院 Overall aerodynamic layout of turboprop vertical take-off and landing fixed-wing aircraft
CN115123535A (en) * 2022-08-11 2022-09-30 北京北航天宇长鹰无人机科技有限公司 Tilt wing unmanned aerial vehicle
US11964755B2 (en) 2017-05-22 2024-04-23 Overair, Inc. Tilt actuator for aircraft
WO2024103279A1 (en) * 2022-11-16 2024-05-23 成都倒立摆科技有限公司 Dual-rotor tilt aircraft and flight control method therefor
WO2024103278A1 (en) * 2022-11-16 2024-05-23 成都倒立摆科技有限公司 Multi-propeller tilting aircraft and flight control method therefor
CN118182828A (en) * 2024-05-14 2024-06-14 珠海市万隆达智能科技有限公司 Fixed wing aircraft capable of taking off and landing vertically

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101041380A (en) * 2006-03-23 2007-09-26 李泽奇 Inclined wing airplane and application thereof
US20100072325A1 (en) * 2008-01-22 2010-03-25 Kenneth William Sambell Forward (Upstream) Folding Rotor for a Vertical or Short Take-Off and Landing (V/STOL) Aircraft
US20110001020A1 (en) * 2009-07-02 2011-01-06 Pavol Forgac Quad tilt rotor aerial vehicle with stoppable rotors
US20160244158A1 (en) * 2013-08-13 2016-08-25 Usa As Represented By The Administrator Of The National Aeronautics And Space Adminstration Vertical take-off and landing vehicle with increased cruise efficiency
CN106428547A (en) * 2015-08-12 2017-02-22 刘十 Perpendicular take-off and landing fixed-wing aircraft with multiple automatic retractable rotors
CN206552260U (en) * 2017-03-02 2017-10-13 北京天宇新超航空科技有限公司 A kind of efficient vertically taking off and landing flyer

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101041380A (en) * 2006-03-23 2007-09-26 李泽奇 Inclined wing airplane and application thereof
US20100072325A1 (en) * 2008-01-22 2010-03-25 Kenneth William Sambell Forward (Upstream) Folding Rotor for a Vertical or Short Take-Off and Landing (V/STOL) Aircraft
US20110001020A1 (en) * 2009-07-02 2011-01-06 Pavol Forgac Quad tilt rotor aerial vehicle with stoppable rotors
US20160244158A1 (en) * 2013-08-13 2016-08-25 Usa As Represented By The Administrator Of The National Aeronautics And Space Adminstration Vertical take-off and landing vehicle with increased cruise efficiency
CN106428547A (en) * 2015-08-12 2017-02-22 刘十 Perpendicular take-off and landing fixed-wing aircraft with multiple automatic retractable rotors
CN206552260U (en) * 2017-03-02 2017-10-13 北京天宇新超航空科技有限公司 A kind of efficient vertically taking off and landing flyer

Cited By (64)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108238232A (en) * 2016-12-27 2018-07-03 韩国科学技术院 Aircraft capable of taking off and landing vertically, flying vertically and horizontally and generating energy in air
US11964755B2 (en) 2017-05-22 2024-04-23 Overair, Inc. Tilt actuator for aircraft
CN107010218A (en) * 2017-06-01 2017-08-04 北京天宇新超航空科技有限公司 A kind of Flying-wing's vertically taking off and landing flyer
CN107150803A (en) * 2017-06-07 2017-09-12 天津科技大学 Mixed layout unmanned plane and its control method
WO2018232787A1 (en) * 2017-06-19 2018-12-27 深圳市龙云创新航空科技有限公司 Vertical take-off and landing fixed-wing unmanned aerial vehicle
CN107719659A (en) * 2017-08-28 2018-02-23 南京达索航空科技有限公司 A kind of VTOL fixed-wing formula aircraft
CN107697279A (en) * 2017-10-16 2018-02-16 江富余 Vert afterbody high-speed helicopter
CN108058811A (en) * 2017-11-30 2018-05-22 易瓦特科技股份公司 The wing tip of adjustable angle applied to unmanned plane
CN108146630A (en) * 2017-11-30 2018-06-12 易瓦特科技股份公司 The power rotor structure of adjustable angle applied to unmanned plane
CN108177772A (en) * 2017-11-30 2018-06-19 易瓦特科技股份公司 The rotor airframe structure of adjustable angle applied to unmanned plane
CN108190014A (en) * 2017-11-30 2018-06-22 易瓦特科技股份公司 Wing tip fuselage applied to unmanned plane
CN108190017A (en) * 2017-11-30 2018-06-22 易瓦特科技股份公司 Rotor fuselage applied to unmanned plane
CN108190015A (en) * 2017-11-30 2018-06-22 易瓦特科技股份公司 The rotor fuselage of adjustable angle applied to unmanned plane
CN108216614A (en) * 2017-11-30 2018-06-29 易瓦特科技股份公司 The power wingtip device of adjustable angle applied to unmanned plane
CN108045573A (en) * 2017-12-05 2018-05-18 长沙展朔轩兴信息科技有限公司 Pull in front and others push behind the multi-functional fixed-wing unmanned plane of formula
CN107972848A (en) * 2017-12-06 2018-05-01 北京迪鸥航空科技有限公司 Aircraft redundance force vector controls tail vane
CN107972848B (en) * 2017-12-06 2024-03-15 北京俪鸥航空科技有限公司 Redundant power vector control tail rudder of aircraft
CN107933909A (en) * 2017-12-17 2018-04-20 北京天宇新超航空科技有限公司 A kind of high-speed and high-efficiency tilting wing unmanned vehicle
CN108128448A (en) * 2018-01-08 2018-06-08 浙江大学 The coaxial tilting rotor wing unmanned aerial vehicle of double shoe formulas and its control method
CN108196565A (en) * 2018-03-04 2018-06-22 西北工业大学 A kind of novel unmanned plane and its attitude control method being combined based on projection with more rotors
CN111801272A (en) * 2018-03-05 2020-10-20 特克诺维特有限公司 Thrust steering aircraft
CN108394560A (en) * 2018-03-15 2018-08-14 成鑫 A kind of fixed-wing unmanned plane and its landing method
JP2021522111A (en) * 2018-05-10 2021-08-30 ジョビー エアロ, インコーポレイテッドJoby Aero, Inc. Electric tilt rotor aircraft
JP7093467B2 (en) 2018-05-10 2022-06-29 ジョビー エアロ,インコーポレイテッド Electric tilt rotor aircraft
CN108762299A (en) * 2018-05-30 2018-11-06 上海交通大学 A kind of unmanned plane formation method and fleet system
CN108762299B (en) * 2018-05-30 2020-04-24 上海交通大学 Unmanned aerial vehicle formation method and formation system
CN109094776A (en) * 2018-08-02 2018-12-28 西安君晖航空科技有限公司 The four of a kind of static-stability are verted wing unmanned plane
CN109110120A (en) * 2018-09-07 2019-01-01 佛山皖和新能源科技有限公司 A kind of three rotor wing unmanned aerial vehicle lift systems
CN109110121A (en) * 2018-09-07 2019-01-01 佛山皖和新能源科技有限公司 A kind of novel three rotor wing unmanned aerial vehicles structure
CN108995800A (en) * 2018-09-07 2018-12-14 佛山皖和新能源科技有限公司 A kind of novel rotor wing unmanned aerial vehicle structure
CN109353495A (en) * 2018-11-30 2019-02-19 南京航空航天大学 It is a kind of can VTOL unmanned autogyro
CN109815528A (en) * 2018-12-13 2019-05-28 航天神舟飞行器有限公司 A method of the aircraft parameters optimization based on large-scale composite wing gas
CN113260566A (en) * 2018-12-28 2021-08-13 列奥纳多股份公司 Thrust reverser aircraft and associated control method
CN109703753A (en) * 2019-02-12 2019-05-03 欧阳军 A kind of new vertical takeoff and landing vehicle
CN110040248A (en) * 2019-04-26 2019-07-23 南京智飞航空科技有限公司 A kind of vertically taking off and landing flyer
CN110104163A (en) * 2019-04-28 2019-08-09 厦门大学 One kind can hang down flying wing type unmanned plane
CN110422328A (en) * 2019-08-26 2019-11-08 南京灵龙旋翼无人机系统研究院有限公司 A kind of tilting rotor wing unmanned aerial vehicle linear power configuration method and structure
CN110775263A (en) * 2019-10-22 2020-02-11 上海交通大学 Tailstock type sea-air cross-region unmanned aerial vehicle and sea-air flight mode thereof
CN110775263B (en) * 2019-10-22 2023-01-31 上海交通大学 Tailstock type air-sea cross-region unmanned aerial vehicle
CN111232195A (en) * 2019-11-05 2020-06-05 西安羚控电子科技有限公司 Carrier-borne heavy oil composite wing unmanned aerial vehicle
CN110775261A (en) * 2019-11-19 2020-02-11 南京航空航天大学 Crossed composite high-speed helicopter and working method thereof
CN111137446A (en) * 2019-12-26 2020-05-12 中国空气动力研究与发展中心 Pneumatic layout of multi-rotor vertical take-off and landing unmanned aerial vehicle with stalling function
CN111152919B (en) * 2020-01-08 2021-06-15 北京建筑大学 Control method of unmanned aerial vehicle capable of taking off and landing vertically
CN111152919A (en) * 2020-01-08 2020-05-15 北京建筑大学 Control method of unmanned aerial vehicle capable of taking off and landing vertically
CN111409821A (en) * 2020-04-26 2020-07-14 北京航空航天大学合肥创新研究院 Solar unmanned aerial vehicle with tilting wings
CN111591440A (en) * 2020-05-27 2020-08-28 湖南省仙鸟科技有限公司 Sickle wing vertical take-off and landing aircraft
CN111674546A (en) * 2020-06-19 2020-09-18 南京航空航天大学 Rotor wing pneumatic appearance suitable for small and medium-sized unmanned tilt rotor wing aircraft
CN112319795A (en) * 2020-11-30 2021-02-05 福州大学 Composite structure aircraft with tiltable rotor wing
CN113148138A (en) * 2021-03-15 2021-07-23 南京航空航天大学 Tailstock type unmanned aerial vehicle and control method
CN113232854A (en) * 2021-05-17 2021-08-10 南京航空航天大学 Distributed unmanned aerial vehicle platform applicable to ballistic launching and launching method
CN113460297A (en) * 2021-07-21 2021-10-01 成都纵横大鹏无人机科技有限公司 Tilting power structure and system and aircraft
CN113753230B (en) * 2021-10-11 2023-08-18 广东汇天航空航天科技有限公司 Aircraft, wing assembly and aerocar
CN113753230A (en) * 2021-10-11 2021-12-07 广东汇天航空航天科技有限公司 Aircraft, wing subassembly and hovercar
CN114180048A (en) * 2021-12-29 2022-03-15 天津斑斓航空科技有限公司 Active tilting wing structure and aircraft
CN114180048B (en) * 2021-12-29 2023-12-29 天津斑斓航空科技有限公司 Active tilting wing structure and aircraft
CN115092390B (en) * 2022-04-22 2024-05-31 中国航空研究院 Vortex paddle vertical take-off and landing fixed wing aircraft
CN115092390A (en) * 2022-04-22 2022-09-23 中国航空研究院 Overall aerodynamic layout of turboprop vertical take-off and landing fixed-wing aircraft
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
CN114852324B (en) * 2022-05-19 2024-09-06 亿维特(南京)航空科技有限公司 Vertical take-off and landing passenger aircraft
CN115123535A (en) * 2022-08-11 2022-09-30 北京北航天宇长鹰无人机科技有限公司 Tilt wing unmanned aerial vehicle
WO2024103278A1 (en) * 2022-11-16 2024-05-23 成都倒立摆科技有限公司 Multi-propeller tilting aircraft and flight control method therefor
WO2024103279A1 (en) * 2022-11-16 2024-05-23 成都倒立摆科技有限公司 Dual-rotor tilt aircraft and flight control method therefor
CN118182828A (en) * 2024-05-14 2024-06-14 珠海市万隆达智能科技有限公司 Fixed wing aircraft capable of taking off and landing vertically
CN118182828B (en) * 2024-05-14 2024-08-13 珠海市万隆达智能科技有限公司 Fixed wing aircraft capable of taking off and landing vertically

Similar Documents

Publication Publication Date Title
CN206552260U (en) A kind of efficient vertically taking off and landing flyer
CN106672232A (en) Efficient vertical takeoff and landing aircraft
CN205440867U (en) But tilting wing aircraft
CN101875399B (en) Tilt rotor aircraft adopting parallel coaxial dual rotors
US11780572B2 (en) VTOL aircraft using fixed forward canted rotors to simulate rigid wing dynamics
CN108382579A (en) A kind of new and effective tilting rotor unmanned vehicle
CN101423117A (en) Tilt-rotor plane operated and propelled by thrust scull and slipstream rudder
IL224219A (en) Personal aircraft
CN106882373A (en) A kind of combined type tilt rotor helicopter
CN106864746A (en) It is a kind of can VTOL the rotor canard configuration aircraft of tailstock formula three
CN207029551U (en) A kind of combined type tilt rotor helicopter
CN106218887A (en) A kind of vertically taking off and landing flyer of distributed-power device layout
CN105083551A (en) Tilt rotary-wing aircraft and control method thereof
CN112224400B (en) Novel tilt rotor aircraft and working method thereof
CN110901890A (en) High-speed rotor craft with rotor capable of being designed in classification mode
CN106915459A (en) A kind of hybrid tilting rotor wing unmanned aerial vehicle
CN108394556A (en) A kind of efficient tilting rotor wing unmanned aerial vehicle
CN107140208A (en) STOL top load multiaxis fans wing unmanned plane
CN113371190A (en) Combined type high-speed helicopter based on conventional rotor wing configuration
CN112027073A (en) Combined type tilting wing longitudinal rotation double-rotor aircraft
RU2521121C1 (en) Heavy-duty multirotor convertible rotorcraft
CN106828920A (en) It is a kind of can VTOL tailstock formula tailless configuration aircraft
CN110282127A (en) A kind of tailstock formula unmanned plane
CN205837190U (en) Thrust type tilt rotor aircraft
CN204871605U (en) Gyroplane can vert

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
WD01 Invention patent application deemed withdrawn after publication

Application publication date: 20170517

WD01 Invention patent application deemed withdrawn after publication