CN110127046A - A kind of new vertical landing aircraft and its control method - Google Patents
A kind of new vertical landing aircraft and its control method Download PDFInfo
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- CN110127046A CN110127046A CN201910391527.4A CN201910391527A CN110127046A CN 110127046 A CN110127046 A CN 110127046A CN 201910391527 A CN201910391527 A CN 201910391527A CN 110127046 A CN110127046 A CN 110127046A
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- 238000000034 method Methods 0.000 title claims abstract description 10
- 230000001105 regulatory effect Effects 0.000 claims description 12
- 230000007423 decrease Effects 0.000 claims description 6
- 230000001276 controlling effect Effects 0.000 claims description 4
- 229910003460 diamond Inorganic materials 0.000 claims description 2
- 239000010432 diamond Substances 0.000 claims description 2
- 230000008450 motivation Effects 0.000 claims description 2
- 230000001737 promoting effect Effects 0.000 claims description 2
- 238000005265 energy consumption Methods 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 5
- 230000001141 propulsive effect Effects 0.000 description 4
- 238000009966 trimming Methods 0.000 description 3
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 2
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
Abstract
The invention discloses a kind of new vertical landing aircraft and its control methods, including fuselage, it further include the rotary shaft that the back is set, wing on the rotary shaft is set, it is wherein equipped in rotary shaft for controlling wing rotation or fixed retaining mechanism, it is respectively symmetrically equipped with one on the both ends of wing and has the bi-directional engine that forward and reverse promotes driving capability, when the bi-directional engine of wing two sides difference forward and reverse promotes, wing is rotated by axis of rotary shaft, when the bi-directional engine forward direction of wing two sides promotes, the wing mechanism that is locked locks and keeps the state vertical with the fuselage.The invention has the advantages that smaller volume may be implemented under same take-off weight, easy to carry, due to not having to change the aerodynamic arrangement of aircraft, faster, flying distance is big for cruising speed, and energy consumption is small, is conducive to extend the hang time.
Description
Technical field
The present invention relates to a kind of aircraft technical fields, more particularly, to a kind of technology of hybrid VTOL aircraft.
Background technique
There are mainly three types of type of airplane common at present: more rotary wind types, fixed-wing formula, or on traditional fixed wing aircraft
Install the hybrid of more rotor landing modules additional.Manned aircraft or aircraft is also using these three mode landings mostly.
It is limited to the setting on airport, for the convenience for improving aircraft utilization, the demand of VTOL is for using aircraft
A kind of main demand has been increasingly becomed, and for the aircraft of existing three kinds of aerofoil profile modes, respectively there are advantage and disadvantage: 1, right
For fixed wing aircraft, although its speed of a ship or plane is fast, voyage is remote, also small, the support in too busy to get away place is influenced by weather, more
It is easy to be limited by the mode of taking off, is unable to satisfy the requirement of VTOL；2, requirement of more gyroplanes to place is low, can be with
Landing whenever and wherever possible, can hovering, more flexibly, but level speed, payload, voyage and adaptive capacity to environment all compare and have
Limit, and to increase the ability of this several respect, the volume of aircraft can become very surprising again, directly influence the property of this type airplane
Valence than with the convenience that uses；3, hybrid type combines more rotors and fixed-wing, i.e., rotor is mounted on fixed-wing,
Play multi-rotor aerocraft VTOL and advantage that fixed-wing quickly cruises simultaneously, but there is also be difficult to avoid that take-off weight
Limited problem, it is often more important that in cruise, aerodynamic arrangement, which meets with, to be destroyed, and causes flight resistance to increase, cruising ability reduces
Deng.
Summary of the invention
It may be implemented to switch between fixed-wing and rotor the object of the present invention is to provide one kind, be small in size, cruise
The complete new vertical landing aircraft of aerodynamic arrangement.
It is a further object of the present invention to provide a kind of convenient new vertical landing aircraft control methods of manipulation.
The technical solution of the invention is as follows: a kind of new vertical landing aircraft, including fuselage, further includes being arranged described
The rotary shaft of back, the wing of setting on the rotary shaft are wherein equipped with for controlling wing rotation or fixing in rotary shaft
Retaining mechanism, on the both ends of wing respectively symmetrically be equipped with one have forward and reverse promote the two-way of driving capability start
Machine, when the bi-directional engine of wing two sides difference forward and reverse promotes, wing is rotated by axis of rotary shaft, when wing two sides
Bi-directional engine forward direction when promoting, the wing mechanism that is locked locks and keeps the state vertical with the fuselage.
Wing is arranged on the rotary shaft, when the bi-directional engine direction of propulsion when wing two sides is opposite, wing can be made to revolve
Turn, generate lift vertically upward, when reducing the output power of bi-directional engine of side reverse propulsion, due to wing two sides
Propulsive force it is not reciprocity, aircraft can be made to generate forward speed, when the bi-directional engine deboost of side reverse propulsion is
When zero, wing rotate to it is vertical with fuselage when, by the fixed wing of retaining mechanism, then restart the bi-directional engine of side simultaneously
It is adjusted to positive propulsion, aircraft can switch to straight line cruising condition from spiral bank position at this time, to realize that rotor takes off and consolidates
Determine wing cruise, the aerodynamic quality of entire fuselage does not have any change, and wing area is more much larger than common rotor, in peer
Under product, the take-off weight of acquisition is bigger, takes off flexibly, since fuselage is without additional structure, aerodynamic arrangement and cruise drag and fixation
Wing aircraft is consistent, and speed when cruise is higher.
The vertical cross-section of the wing is in tabular or aerofoil profile.Different lift effects can be realized when taking off and cruising
Fruit.
The two sides of the wing can pass through the rotation axial adjustment horizontal incidence angle respectively.It can be adjusted respectively when wing rotates
The aerodynamic arrangement of whole two sides improves lift and trimming moment, improves the reliability of manipulation.
The wing includes covering and is arranged in covering for adjusting the regulating mechanism of wing windward side shape.It can
To adjust separately the aerodynamic arrangement of two sides wing when wing rotates, lift and trimming moment are improved.
The regulating mechanism includes the longitudinal rod being arranged along the wing length direction, is arranged in parallel on longitudinal rod
Several groups adjust connection rod set, wherein each adjusting connection rod set includes the transverse link being fixed on longitudinal rod, first
Link in rhomb form group, third link in rhomb form group, is respectively sleeved on transverse link and can transversely connecting rod slide the second link in rhomb form group
Dynamic the first sliding block and the second sliding block, the symmetrical end of two of the first link in rhomb form group are hingedly connected the covering of upper and lower, separately
Two symmetrical ends are hingedly connected one end and the first sliding block of transverse link, the symmetrical end difference of two of the second link in rhomb form group
Be articulated and connected the covering of the wing upper and lower, and another two symmetrically holds and is hingedly connected the first sliding block and the second sliding block, third
The symmetrical end of two of link in rhomb form group is hingedly connected the covering of the wing upper and lower, and another two is symmetrically held and is respectively articulated with
Connect the other end of the second sliding block and transverse link.It, can be with when transversely connecting rod slides back and forth for the first sliding block and the second sliding block
The upper-lower height of three groups of link in rhomb form groups is adjusted separately, so as to adjust the spacing between wing upper and lower covering, to realize machine
The adjusting of wing windward side shape, to adapt to adjustment of the fixed-wing with rotor state difference to surface state windward.
The short limb rotated with the rotary shaft is equipped in the rotary shaft below the wing, when the wing and machine
When body is vertically fixed, short limb is parallel with the fuselage to be fixed.Short limb can be rotated with rotary shaft, can be mentioned in the VTOL stage
For additional lift, and the lifting moment for balancing wing two sides.
Another technical solution of the invention is: a kind of control method of new vertical landing aircraft, including following step
Rapid: 1. take off vertically the stage: the bi-directional engine difference forward and reverse of control wing two sides promotes, and turns wing around rotary shaft
Dynamic, aircraft vertical takes off；2., cruising phase: the bi-directional engine of wing side reverse propulsion gradually decreases output power, wing
The positive bi-directional engine promoted of the other side keeps output power constant, and helically formula rises aircraft, to the double of reverse propulsion
When being reduced to zero to engine power, adjustment wing is vertical with fuselage, by the fixed wing of retaining mechanism, restarts the double of shutdown
To engine and be changed to positive propulsion, adjust two sides motor power size, make aircraft along the tangential direction of helix fly out into
Enter cruising condition；3., the vertical landing stage: retaining mechanism discharge wing, gradually decrease wing side forward direction propulsion two-way hair
Motivation output power after power to be output is down to zero, restarts and is changed to reverse propulsion, rotates wing around rotary shaft.
The thrust of forward and reverse is provided by the bi-directional engine of two sides, so that wing rotation is generated lift, for taking off
And landing keeps the propulsive force of wing two sides not reciprocity, generates forward speed, aircraft can by reducing the thrust of reverse propulsion
With spiral escalation, when wing is fixed and two sides bi-directional engine is made to be positive promote, aircraft can be from vrille
Tangential direction changes into cruise, it is only necessary to change the thrust direction of wing two sides engine, can realize fixed-wing and rotation
The switching of wing state, manipulation is simple, easy to use, and flight control is easy reliable.
Further include the steps that adjusting wing horizontal incidence angle, wherein adjusting rotary shaft two sides in the vertical and landing takeoff stage
The wing angle of attack on the contrary, in cruising phase, when wing is vertical with fuselage, the wing angle of attack for adjusting rotary shaft two sides is identical.?
VTOL and cruising phase adjust separately the angle of attack direction of wing two sides, balance the torque of wing two sides more, and manipulation more may be used
It leans on.
Further include the steps that adjusting wing cover shape, wherein in the vertical and landing takeoff stage, by wing cover
Regulating mechanism make the wing windward side of rotary shaft two sides on the contrary, in cruising phase, made by the regulating mechanism in wing cover
The wing windward side of rotary shaft two sides is identical.In VTOL and cruising phase, the angle of attack direction of wing two sides is adjusted separately, is made
The torque of wing two sides more balances, and manipulates more reliable.
The invention has the advantages that smaller volume may be implemented under same take-off weight, and it is easy to carry, due to not changing
Become the aerodynamic arrangement of aircraft, faster, flying distance is big for cruising speed, and energy consumption is small, is conducive to extend the hang time.
Detailed description of the invention
Attached drawing 1 is the structural schematic diagram of the embodiment of the present invention 1；
Attached drawing 2 is another angled arrangement schematic diagram of the embodiment of the present invention 1；
State of flight figure when attached drawing 3 is 1 VTOL of the embodiment of the present invention；
State of flight figure when attached drawing 4 is 1 cruising condition of the embodiment of the present invention；
Another state of flight figure when attached drawing 5 is 1 cruising condition of the embodiment of the present invention；
Attached drawing 6 is the wing inside top structural schematic diagram of the embodiment of the present invention 1；
Attached drawing 7 be in Fig. 6 A-A to structural schematic diagram；
Attached drawing 8 is the structural schematic diagram of the embodiment of the present invention 2；
1, fuselage, 2, wing, 3, rotary shaft, 4, bi-directional engine, 5, bi-directional engine, 6, covering, 7, longitudinal rod, 8,
Transverse link, the 9, first link in rhomb form group, the 10, second link in rhomb form group, 11, third link in rhomb form group, the 12, first sliding block, 13,
Second sliding block, 14, short limb.
Specific embodiment
Embodiment 1:
Refering to fig. 1-2, a kind of new vertical landing aircraft, including fuselage 1, setting on the fuselage 1 the rotary shaft 3 in portion, set
The wing 2 in rotary shaft 3 is set, is wherein equipped in rotary shaft 3 for controlling the rotation of wing 2 or fixed retaining mechanism, in machine
It is symmetrically arranged with two on the both ends of the wing 2 and has bi-directional engine 4 and bi-directional engine 5 that forward and reverse promotes driving capability,
When the positive propulsion of the bi-directional engine 4 of 2 two sides of wing, 5 reversed reverse propulsion of bi-directional engine, wing 2 is axis with rotary shaft 3
Rotation, when the bi-directional engine 4 and 5 of 2 two sides of wing is positive promote, the mechanism that is locked of wing 2 is locked and is kept and machine
The vertical state of body 1.
Wing 2 is arranged in rotary shaft 3, when the direction of propulsion of bi-directional engine 4 and 5 when 2 two sides of wing is opposite, can make
Wing 2 rotates, and generates lift vertically upward, when reducing the output power of bi-directional engine 5 of side reverse propulsion, due to
The propulsive force of 2 two sides of wing is not reciprocity, aircraft can be made to generate forward speed, when the bi-directional engine 5 of side reverse propulsion
When deboost is zero, when the rotation of wing 2 is extremely vertical with fuselage 1, by the fixed wing 2 of retaining mechanism, then side is restarted
Bi-directional engine 5 and be adjusted to positive propulsion, aircraft can switch to straight line cruising condition from spiral bank position at this time, thus real
Existing rotor takes off to cruise with fixed-wing, and the aerodynamic quality of entire fuselage does not have any change, and wing area is than common rotor
Much larger, under equal volume, the take-off weight of acquisition is bigger, takes off flexibly, since fuselage is without additional structure, aerodynamic arrangement and
Cruise drag is consistent with fixed wing aircraft, and speed when cruise is higher.
The vertical cross-section of wing 2 is in tabular or aerofoil profile.The two sides of wing 2 can be met by 3 adjustment level of rotary shaft respectively
Angle.Wing 2 includes covering 6 and is arranged in covering 6 for adjusting the regulating mechanism of 2 windward side shape of wing.It can be in wing 2
The aerodynamic arrangement of two sides is adjusted separately when rotation, is improved lift and trimming moment, is improved the reliability of manipulation.
If regulating mechanism includes the longitudinal rod 7 being arranged along 2 length direction of wing, is arranged in parallel on longitudinal rod 7
Dry group adjusts connection rod set, wherein each adjusting connection rod set includes the transverse link being fixed on longitudinal rod 78, the first water chestnut
Shape connection rod set 9, third link in rhomb form group 11, is respectively sleeved on transverse link 8 and can transversely connect second link in rhomb form group 10
The first sliding block 12 and the second sliding block 13 that bar 8 slides, the symmetrical end of two of the first link in rhomb form group 9 are hingedly connected wing 2
The covering 6 of upper and lower, another two symmetrically hold the one end for being hingedly connected transverse link 8 and the first sliding block 12, and the second diamond shape connects
Two of bar group 10 symmetrical ends are hingedly connected the covering 6 of 2 upper and lower of wing, and another two, which is symmetrically held, is hingedly connected the
One sliding block 12 and the second sliding block 13, the symmetrical end of two of third link in rhomb form group 11 are hingedly connected the illiteracy of 2 upper and lower of wing
Skin 6, another two symmetrically hold the other end for being hingedly connected the second sliding block 13 and transverse link 8.When the first sliding block 12 and second
Sliding block 13 can adjust separately the upper-lower height of three groups of link in rhomb form groups, so as to adjust wing when transversely connecting rod 8 slides back and forth
Spacing between 2 upper and lower coverings 6, so that the adjusting of 2 windward side shape of wing is realized, to adapt to fixed-wing and rotor state
Adjustment of the difference to surface state windward.
Refering to Fig. 3-5, the control method of the new vertical landing aircraft of the embodiment of the present invention 1, comprising the following steps:
1. taking off vertically the stage: the bi-directional engine 4 of control 2 two sides of wing is positive to be promoted, 5 reverse push of bi-directional engine
Into rotating wing 2 around rotary shaft 3, aircraft vertical takes off；
2., cruising phase: the bi-directional engine 5 of 2 side reverse propulsion of wing gradually decreases output power, the wing other side
The positive bi-directional engine 4 promoted keep output power constant, helically formula rises aircraft, and two-way to reverse propulsion is started
When 5 power of machine is reduced to zero, adjustment wing 2 is vertical with fuselage 1, by the fixed wing 2 of retaining mechanism, restarts the two-way of shutdown
Engine 5 is simultaneously changed to positive propulsion, adjusts two sides motor power size, and aircraft is made to fly out entrance along the tangential direction of helix
Cruising condition；
3., the vertical landing stage: retaining mechanism discharges wing 2, gradually decreases two-way starting for 2 side forward direction of wing propulsion
The output power of machine 5 after power to be output is down to zero, restarts and is changed to reverse propulsion, rotates wing 2 around rotary shaft 3.
The thrust of forward and reverse is provided by the bi-directional engine of two sides, so that the rotation of wing 2 is generated lift, for taking off
And landing keeps the propulsive force of wing two sides not reciprocity, generates forward speed, aircraft can by reducing the thrust of reverse propulsion
With spiral escalation, when wing 2 is fixed and two sides bi-directional engine is made to be positive promote, aircraft can be from vrille
Tangential direction changes into cruise, it is only necessary to change the thrust direction of wing two sides engine, can realize fixed-wing and rotation
The switching of wing state, manipulation is simple, easy to use, and flight control is easy reliable.
In addition, further including the steps that adjusting 2 horizontal incidence angle of wing, wherein adjusting rotation in the vertical and landing takeoff stage
2 angle of attack of wing of 3 two sides of axis, when wing 2 is vertical with fuselage 1, adjusts the wing 2 of 3 two sides of rotary shaft on the contrary, in cruising phase
The angle of attack is identical.In VTOL and cruising phase, the angle of attack direction of wing two sides is adjusted separately, keeps the torque of wing two sides more flat
Weighing apparatus manipulates more reliable.
Further include the steps that 6 shape of covering for adjusting wing 2, wherein passing through wing 2 in the vertical and landing takeoff stage
Regulating mechanism in covering 6 makes 2 windward side of wing of 3 two sides of rotary shaft on the contrary, in cruising phase, by the covering 6 of wing 2
Regulating mechanism keep 2 windward side of wing of 3 two sides of rotary shaft identical.In VTOL and cruising phase, wing two is adjusted separately
The angle of attack direction of side, balances the torque of wing two sides more, manipulates more reliable.
The aircraft of the present embodiment can be manned aircraft, be also possible to unmanned plane.
Embodiment 2:
Refering to Fig. 7, for another new vertical landing aircraft of the present invention, the rotation including fuselage 1, setting portion on the fuselage 1
Axis 3, the wing 2 being arranged in rotary shaft 3 and short limb 14, wherein short limb 14 is arranged below wing 2 and can be 3 turn with rotary shaft
It is dynamic.It is equipped in rotary shaft 3 for controlling wing 2 and the rotation of short limb 14 or fixed retaining mechanism, it is symmetrical on the both ends of wing 2
If there are two the bi-directional engine 4 and bi-directional engine 5 that have forward and reverse propulsion driving capability, when pair of 2 two sides of wing
It is promoted to engine 4 is positive, when 5 reversed reverse propulsion of bi-directional engine, wing 2 is that axis rotates with rotary shaft 3, when 2 liang of wing
When the bi-directional engine 4 and 5 of side is positive promote, the mechanism that is locked of wing 2 locks and keeps the state vertical with fuselage 1,
Short limb 14 keeps the state parallel with fuselage 1 at this time.Other technical characteristics are same as Example 1, should not repeat herein.
Claims (9)
1. a kind of new vertical landing aircraft, including fuselage, it is characterised in that: further include the rotation that the back is arranged in
Axis, the wing of setting on the rotary shaft, are wherein equipped with for controlling wing rotation or fixed retaining mechanism, in machine in rotary shaft
It is respectively symmetrically equipped with one on the both ends of the wing and has the bi-directional engine that forward and reverse promotes driving capability, when wing two sides
Bi-directional engine distinguish forward and reverse promote when, wing using rotary shaft be axis rotation, when wing two sides bi-directional engine just
To when promoting, the wing mechanism that is locked locks and keeps the state vertical with the fuselage.
2. a kind of new vertical landing aircraft according to claim 1, it is characterised in that: the vertical cross-section of the wing is in
Tabular or aerofoil profile.
3. a kind of new vertical landing aircraft according to claim 2, it is characterised in that: the two sides of the wing can be distinguished
Pass through the rotation axial adjustment horizontal incidence angle.
4. a kind of new vertical landing aircraft according to claim 1 or 2 or 3, it is characterised in that: the wing includes covering
Skin and it is arranged in covering for adjusting the regulating mechanism of wing windward side shape.
5. a kind of new vertical landing aircraft according to claim 4, it is characterised in that: the regulating mechanism includes along institute
The longitudinal rod for stating the setting of wing length direction, the several groups being arranged in parallel on longitudinal rod adjust connection rod set, wherein each
Adjusting connection rod set includes the transverse link being fixed on longitudinal rod, the first link in rhomb form group, the second link in rhomb form group, the
Three Diamond connection rod set, be respectively sleeved on transverse link and can transversely rod slide the first sliding block and the second sliding block, first
The symmetrical end of two of link in rhomb form group is hingedly connected the covering of upper and lower, and another two symmetrically holds and is hingedly connected transverse direction
One end of connecting rod and the first sliding block, the symmetrical end of two of the second link in rhomb form group are hingedly connected the wing upper and lower
Covering, another two, which is symmetrically held, is hingedly connected the first sliding block and the second sliding block, the symmetrical end point of two of third link in rhomb form group
Be not articulated and connected the covering of the wing upper and lower, and another two, which is symmetrically held, is hingedly connected the second sliding block and transverse link
The other end.
6. a kind of new vertical landing aircraft according to claim 4, it is characterised in that: described in below the wing
Rotary shaft is equipped with the short limb rotated with the rotary shaft, when the wing is vertical with fuselage fixed, short limb and the fuselage
It is parallel fixed.
7. a kind of control method of new vertical landing aircraft as described in claim 1, it is characterised in that: including following step
Rapid: 1. take off vertically the stage: the bi-directional engine difference forward and reverse of control wing two sides promotes, and turns wing around rotary shaft
Dynamic, aircraft vertical takes off；2., cruising phase: the bi-directional engine of wing side reverse propulsion gradually decreases output power, wing
The positive bi-directional engine promoted of the other side keeps output power constant, and helically formula rises aircraft, to the double of reverse propulsion
When being reduced to zero to engine power, adjustment wing is vertical with fuselage, by the fixed wing of retaining mechanism, restarts the double of shutdown
To engine and be changed to positive propulsion, adjust two sides motor power size, make aircraft along the tangential direction of helix fly out into
Enter cruising condition；3., the vertical landing stage: retaining mechanism discharge wing, gradually decrease wing side forward direction propulsion two-way hair
Motivation output power after power to be output is down to zero, restarts and is changed to reverse propulsion, rotates wing around rotary shaft.
8. a kind of control method of new vertical landing aircraft according to claim 7, it is characterised in that: further include adjustment
The step of wing horizontal incidence angle, wherein adjusting the wing angle of attack of rotary shaft two sides on the contrary, patrolling in the vertical and landing takeoff stage
In the boat stage, when wing is vertical with fuselage, the wing angle of attack for adjusting rotary shaft two sides is identical.
9. a kind of control method of new vertical landing aircraft according to claim 7 or 8, it is characterised in that: further include
The step of adjusting wing cover shape, wherein making to revolve by the regulating mechanism in wing cover in the vertical and landing takeoff stage
The wing windward side of shaft two sides makes the machine of rotary shaft two sides by the regulating mechanism in wing cover on the contrary, in cruising phase
Wing windward side is identical.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910391527.4A CN110127046A (en) | 2019-05-10 | 2019-05-10 | A kind of new vertical landing aircraft and its control method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910391527.4A CN110127046A (en) | 2019-05-10 | 2019-05-10 | A kind of new vertical landing aircraft and its control method |
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| Publication Number | Publication Date |
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| CN110127046A true CN110127046A (en) | 2019-08-16 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201910391527.4A Pending CN110127046A (en) | 2019-05-10 | 2019-05-10 | A kind of new vertical landing aircraft and its control method |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2011162173A (en) * | 2010-02-13 | 2011-08-25 | Am Creation:Kk | Vertical takeoff and landing airplane |
| CN104085532A (en) * | 2014-07-01 | 2014-10-08 | 北京航空航天大学 | Layout scheme and control method of tilt rotor transport aircraft |
| CN104176235A (en) * | 2013-05-23 | 2014-12-03 | 中国直升机设计研究所 | Rotatable wing of rotor craft |
| WO2016109003A2 (en) * | 2014-12-19 | 2016-07-07 | Sikorsky Aircraft Corporation | Delta fuselage for vertical take-off and landing (vtol) aircraft |
| CN108284943A (en) * | 2018-03-14 | 2018-07-17 | 北京航空航天大学 | A kind of mechanism that bent for trailing edge flexibility |
| CN209956222U (en) * | 2019-05-10 | 2020-01-17 | 广州中国科学院工业技术研究院 | Novel vertical take-off and landing aircraft |
-
2019
- 2019-05-10 CN CN201910391527.4A patent/CN110127046A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2011162173A (en) * | 2010-02-13 | 2011-08-25 | Am Creation:Kk | Vertical takeoff and landing airplane |
| CN104176235A (en) * | 2013-05-23 | 2014-12-03 | 中国直升机设计研究所 | Rotatable wing of rotor craft |
| CN104085532A (en) * | 2014-07-01 | 2014-10-08 | 北京航空航天大学 | Layout scheme and control method of tilt rotor transport aircraft |
| WO2016109003A2 (en) * | 2014-12-19 | 2016-07-07 | Sikorsky Aircraft Corporation | Delta fuselage for vertical take-off and landing (vtol) aircraft |
| CN108284943A (en) * | 2018-03-14 | 2018-07-17 | 北京航空航天大学 | A kind of mechanism that bent for trailing edge flexibility |
| CN209956222U (en) * | 2019-05-10 | 2020-01-17 | 广州中国科学院工业技术研究院 | Novel vertical take-off and landing aircraft |
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