CN108394546A - It is complete to deform the Fixed Wing AirVehicle that hung down - Google Patents
It is complete to deform the Fixed Wing AirVehicle that hung down Download PDFInfo
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- CN108394546A CN108394546A CN201810273990.4A CN201810273990A CN108394546A CN 108394546 A CN108394546 A CN 108394546A CN 201810273990 A CN201810273990 A CN 201810273990A CN 108394546 A CN108394546 A CN 108394546A
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- hung down
- rotor
- airvehicle
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- 239000007787 solid Substances 0.000 claims description 4
- 230000001154 acute effect Effects 0.000 claims description 3
- 238000005516 engineering process Methods 0.000 abstract description 6
- 238000003860 storage Methods 0.000 abstract description 3
- 238000000034 method Methods 0.000 description 3
- 208000035473 Communicable disease Diseases 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000009194 climbing Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 208000015181 infectious disease Diseases 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000013507 mapping Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
The Fixed Wing AirVehicle that hung down is deformed entirely the present invention provides a kind of, is related to vehicle technology field, solves the larger and not portable technical problem of existing unmanned plane during flying device occupied space.The full Fixed Wing AirVehicle that hung down that deforms includes fuselage, fixed-wing and rotor, and fixed-wing is rotatablely connected with fuselage, and rotor is arranged on fixed-wing or fuselage；When full deformation hung down Fixed Wing AirVehicle be in the grounding state when, fixed-wing can be turned to the spanwise position parallel with the length direction of fuselage and deform Fixed Wing AirVehicle occupied space in the horizontal direction of having hung down entirely to reduce, and/or fuselage can be folded to reduce and deform Fixed Wing AirVehicle occupied space in the horizontal direction of having hung down entirely in the vertical direction.The storage space that the present invention is used to reduce needed for unmanned plane during flying device increases its portability.
Description
Technical field
The present invention relates to vehicle technology fields, and the Fixed Wing AirVehicle that hung down is deformed entirely more particularly, to a kind of.
Background technology
Aircraft (flight vehicle) is the instrument to fly in endoatmosphere or exoatmosphere space (space).Flight
Device is divided into 3 classes：Aircraft, spacecraft, rocket and guided missile.
And with the development of economy, this aircraft of UAV is increasingly popularized, UAV referred to as " nobody
Machine ", english abbreviation are " UAV ", are the not manned aircrafts manipulated using radio robot and the presetting apparatus provided for oneself,
Or it fully or is intermittently automatically operated by car-mounted computer.
Compared with manned aircraft, unmanned plane is often more suitable for the task of those too " slow-witted, dirty or dangerous ".Nobody
Machine press application field, can be divided into it is military with it is civilian.Military aspect, unmanned plane are divided into reconnaissance plane and target drone.Civilian aspect, unmanned plane
+ sector application, which is unmanned plane, really just have been needed；At present take photo by plane, agricultural, plant protection, miniature self-timer, express transportation, disaster relief,
Observe wild animal, monitoring infectious disease, mapping, news report, electric inspection process, the disaster relief, movies-making, manufacture romance etc. field
Application, greatly expanded the purposes of unmanned plane itself, developed country is also in actively extension sector application and development unmanned plane
Technology.
Applicants have discovered that at least there is following technical problem in the prior art：Existing unmanned plane during flying device occupied space compared with
It is big and inconvenient to carry.
Invention content
Hung down Fixed Wing AirVehicle the purpose of the present invention is to provide full deformation, with solve it is existing in the prior art nobody
The larger and not portable technical problem of machine aircraft occupied space.Optimization technique side in many technical solutions provided by the invention
Many technique effects elaboration as detailed below that case can be generated.
To achieve the above object, the present invention provides following technical schemes：
Full deformation provided by the invention has been hung down Fixed Wing AirVehicle, including fuselage, fixed-wing and rotor, wherein：It is described solid
Determine the wing to be rotatablely connected with the fuselage, the rotor is arranged on the fixed-wing or the fuselage；When the full deformation is hung down
Fixed Wing AirVehicle is played when being in grounding state, the fixed-wing can be turned to the length of the spanwise and the fuselage
The parallel position in direction has been hung down Fixed Wing AirVehicle occupied space in the horizontal direction with reducing the full deformation, and/or,
The fuselage can be folded to reduce the full deformation and hang down Fixed Wing AirVehicle institute in the horizontal direction in the vertical direction
The space occupied.
Further, the fuselage includes head section and endpiece；It is rotatablely connected between the head section and the endpiece, when described complete
Deformation has hung down Fixed Wing AirVehicle when being in state of flight, and the head section is equal with the axis of the endpiece in the longitudinal direction
Row；When it is described it is full deformation hung down Fixed Wing AirVehicle be in the grounding state when, the head section can rotate down be folded to it is described
The lower surface of endpiece fits together.
Further, the length of the head section is equal to the length of the endpiece.
Further, the fixed-wing includes the first fixed-wing and the second fixed-wing, first fixed-wing and described second
Fixed-wing is rotatablely connected with the head section and the endpiece respectively, when the full deformation has hung down Fixed Wing AirVehicle in grounding shape
When state, the spanwise of first fixed-wing and second fixed-wing can turn to and the head section and the endpiece respectively
Length direction it is parallel.
Further, when the spanwise of first fixed-wing turns to parallel with the head section, described first fixes
The both ends of the wing be within the head section both ends or with head section both ends flush；The spanwise of second fixed-wing
When turning to parallel with the length direction of the endpiece, the both ends of second fixed-wing be within the head section both ends or
Person and endpiece both ends flush.
Further, the rotor is mounted on the both ends of the spanwise of first fixed-wing and second fixed-wing.
Further, the full Fixed Wing AirVehicle that hung down that deforms further includes at least two motors, and the motor is respectively institute
The rotor stated on the first fixed-wing and second fixed-wing provides power.
Further, the axis phase of the rotation axis and the length direction of the head section of the rotor on first fixed-wing
Parallel, the rotation axis of the rotor on second fixed-wing and the upper surface of the endpiece are perpendicular.
Further, the head section includes end and middle part, is driven between the end and the middle part by deforming
Device is connected, first fixed-wing and end rotation connection and the rotation of the rotor on first fixed-wing
Axis is parallel with the axis of the length direction of the end, the rotation of the rotor under state of flight on second fixed-wing
Axis is in the state with horizontal plane, when the deformation driving device drives end and drives the institute on first fixed-wing
When stating the rotation axis of rotor and turning to parallel with the rotation axis of the rotor on the second fixed-wing, the full deformation has been hung down fixation
Rotor aircraft is in jacking condition；When the end drive the rotation axis of the rotor on first fixed-wing turn to
When the angle of the rotation axis of the rotor on second fixed-wing is acute angle, right angle or obtuse angle, the full deformation has been hung down fixed-wing
Aircraft is in flat winged state.
Further, the full fixed-wing both ends lower surface for deforming the Fixed Wing AirVehicle that hung down is equipped with retractable fall
Ground support device.
Beneficial effects of the present invention are：Existing aircraft fixed-wing is symmetrical and fixed about the central axes in fuselage length direction
The spanwise of the wing and the length direction of fuselage are perpendicular, and with fuselage relative motion cannot occur for fixed-wing, so aircraft
More space is occupied under grounding state and is not easy to carry；And the fixed-wing of the present invention can be turned to spanwise
It is integrally occupied can be folded to reduce the full deformation Fixed Wing AirVehicle that hung down for parallel and fuselage with the length direction of fuselage
Space, the storage and carrying after so that aircraft is grounded are more convenient.
Description of the drawings
In order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, to embodiment or will show below
There is attached drawing needed in technology description to be briefly described, it should be apparent that, the accompanying drawings in the following description is only this
Some embodiments of invention for those of ordinary skill in the art without creative efforts, can be with
Obtain other attached drawings according to these attached drawings.
Fig. 1, which is that the present invention is complete, deforms side view of the Fixed Wing AirVehicle under jacking condition that hung down；
Fig. 2, which is that the present invention is complete, deforms front view of the Fixed Wing AirVehicle under jacking condition that hung down；
Fig. 3, which is that the present invention is complete, deforms vertical view of the Fixed Wing AirVehicle under jacking condition that hung down；
Fig. 4 is that full deformation of the invention has hung down Fixed Wing AirVehicle in the flat side view flown under state；
Fig. 5 is that full deformation of the invention has hung down Fixed Wing AirVehicle in the flat front view flown under state；
Fig. 6 is that full deformation of the invention has hung down Fixed Wing AirVehicle in the flat vertical view flown under state；
Fig. 7 is the full schematic diagram for deforming the Fixed Wing AirVehicle fixed-wing rotation process that hung down of the invention；
Fig. 8 is the vertical view of the fixed-wing span of the present invention and fuselage length direction parastate；
Fig. 9 is that the full Fixed Wing AirVehicle that hung down that deforms of the invention adds the vertical view of folded state on the basis of Fig. 7.
11, head section in figure；111, end；112, middle part；12, endpiece；21, the first fixed-wing；22, the second fixed-wing；
3, rotor；4, driving device is deformed.
Specific implementation mode
To make the object, technical solutions and advantages of the present invention clearer, technical scheme of the present invention will be carried out below
Detailed description.Obviously, described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.Base
Embodiment in the present invention, those of ordinary skill in the art are obtained all without making creative work
Other embodiment belongs to the range that the present invention is protected.
As shown in Figure 1 to 9, hung down Fixed Wing AirVehicle the present invention provides a kind of full deformation, including fuselage, fixed-wing and
Rotor 3, wherein：Fixed-wing is rotatablely connected with fuselage, and rotor 3 is arranged on fixed-wing or fuselage；Fixation of having hung down is deformed when complete
When rotor aircraft is in grounding state, fixed-wing can be turned to the spanwise position parallel with the length direction of fuselage to subtract
Small full deformation has been hung down Fixed Wing AirVehicle occupied space in the horizontal direction, and/or, fuselage can in the vertical direction by
It folds and deforms Fixed Wing AirVehicle occupied space in the horizontal direction of having hung down entirely to reduce.
Due to existing aircraft fixed-wing about the central axes in fuselage length direction symmetrical and fixed-wing spanwise
It is perpendicular with the length direction of fuselage, so aircraft occupies more space under grounding state and is not easy to carry；
And fixed-wing is set as being rotatablely connected with fuselage in the present invention, in this way when the full Fixed Wing AirVehicle that hung down that deforms is in grounding state
When, fixed-wing can be turned to that spanwise is parallel with the length direction of fuselage, both consistent with the length direction of fuselage, in this way
It has been reduced by the full memory space for deforming and having hung down needed for Fixed Wing AirVehicle, has also been allowed to more portable；And after fixed-wing is rotated,
The length of fuselage is still longer, and such form takes up space or comparison is more, therefore, becomes full when will further be in grounding state
The hung down fuselage of Fixed Wing AirVehicle of shape is designed as folding, has hung down occupied by Fixed Wing AirVehicle entirety to reduce full deformation
Space, make its storage space smaller that is more portable, using.
Optionally embodiment, fuselage include head section 11 and endpiece 12；It is rotatablely connected between head section 11 and endpiece 12,
When full deformation hung down Fixed Wing AirVehicle be in state of flight when, head section 11 is equal with the axis of endpiece 12 in the longitudinal direction
Row；When full deformation hung down Fixed Wing AirVehicle be in the grounding state when, head section 11 can rotate down be folded to under endpiece 12
Surface fits together.
In order to facilitate storing and carrying, the form that fuselage is arranged to fold is got up to reduce its length, fuselage exists
The folding of its width direction is more difficult, therefore fuselage is divided into head section 11 and endpiece 12 two from length direction in the present embodiment
Point, the rotation connection of this two parts, head section 11 is parallel with the axis of endpiece 12 in the longitudinal direction, and head section 11 can be downward
It turns folding to the lower surface of endpiece 12 and fits together, the length of such fuselage is just opposite to be reduced, to reduce full deformation
The memory space to have hung down needed for Fixed Wing AirVehicle, it is also more portable.
Optionally embodiment, the length of head section 11 are equal to the length of endpiece 12.
Head section 11 is rotated down to be folded to and is bonded with the lower surface of endpiece 12, length and 12 equal length of endpiece
Words, the fuselage after folding in this way is most compact most space-saving, further reduces full deformation and has hung down needed for Fixed Wing AirVehicle
Memory space, it is also more portable.
Optionally embodiment, fixed-wing include the first fixed-wing 21 and the second fixed-wing 22, the first fixed-wing 21
It is rotatablely connected respectively with head section 11 and endpiece 12 with the second fixed-wing 22, when full deformation has hung down Fixed Wing AirVehicle in grounding shape
When state, the spanwise of the first fixed-wing 21 and the second fixed-wing 22 can turn to the length side with head section 11 and endpiece 12 respectively
To parallel.
Double fixed-wings can provide the lift of bigger for fuselage, and be unlikely to generate excessive resistance；And first is fixed
Double fixed-wings with head section 11 and the rotation connection of endpiece 12 rather than are all disposed within head section 11 by the wing 21 and the second fixed-wing 22 respectively
Or it is all disposed within endpiece 12, such construction is the first fixed-wing 21 and the generation of the second fixed-wing 22 after capable of avoiding rotation
Conflict (can first fold fuselage and rotate fixed-wing respectively again), has hung down needed for Fixed Wing AirVehicle to further reduce full deformation
Memory space create convenience；
The rotary course of first fixed-wing and the second fixed-wing is shown in Fig. 7：The rotation direction at the first fixed-wing both ends is by arrow A
It is marked with B, the rotation direction at the second fixed-wing both ends is marked by arrow C and D.
When the spanwise of optionally embodiment, the first fixed-wing 21 turns to parallel with head section 11, first
The both ends of fixed-wing 21 be within 11 both ends of head section or with 11 both ends flush of head section；The spanwise of second fixed-wing 22
When turning to parallel with the length direction of endpiece 12, the both ends of the second fixed-wing 22 are within 11 both ends of head section or and tail
12 both ends flushes of section.
When fuselage is folded, and the spanwise of the first fixed-wing 21 and the spanwise of the second fixed-wing 22 turn to and
When the length direction of fuselage is consistent, the span of the first fixed-wing 21 and the span of the second fixed-wing 22 are no more than head section 11 respectively
With the length of endpiece 12, such airframe structure is most compact, and Fixed Wing AirVehicle institute of having hung down is deformed entirely to further reduce
The memory space needed, it is also more portable.
Optionally embodiment, rotor 3 are mounted on the spanwise of the first fixed-wing 21 and the second fixed-wing 22
Both ends.
Rotor 3 may be mounted on fuselage or fixed-wing, and in the present embodiment, rotor 3 is mounted on the first fixed-wing 21
With the both ends of the spanwise of the second fixed-wing 22, four rotors 3 can either provide enough lift, such distribution to fuselage
Mode can also preferably keep the balance of fuselage, while also avoiding rotor 3 on fuselage and being brought when fixed-wing rotation
Conflict.
Optionally embodiment, the full Fixed Wing AirVehicle that hung down that deforms further includes at least two motors, motor difference
Power is provided for the rotor 3 on the first fixed-wing 21 and the second fixed-wing 22.
First fixed-wing 21 and the second fixed-wing 22 provide power using independent motor for rotor 3 respectively, increase in this way
Add safety, and the two motors are located at the upper surface of fuselage and are all overhead type, i.e. motor side is connected with fuselage side
It connects, the other side is hanging, in this way when with fuselage relative rotation occurs for the first fixed-wing 21 and the second fixed-wing 22, is not interfered with
It is rotated；And the hanging place in the other side of motor is provided with the limiting device that can be opened and pack up, and can ensure in this way when first is solid
The spanwise for determining the wing 21 and the second fixed-wing 22 turns to double fixed-wing quilts when the state consistent with the length direction of fuselage
Locking can't disorderly be put.
Optionally embodiment, the rotation axis of the rotor 3 on the first fixed-wing 21 and the length direction of head section 11
Axis is parallel, and the rotation axis of the rotor 3 on the second fixed-wing 22 and the upper surface of endpiece 12 are perpendicular.On first fixed-wing 21
Rotor 3 be set as parallel with the axis of the length direction of head section 11, rotor 3 can provide flat winged for aircraft when rotating when
Power；And the rotation axis of the rotor 3 on the second fixed-wing 22 is set as perpendicular with the upper surface of endpiece 12, then 3 turns of rotor
The power of lifting can be provided when dynamic for aircraft, and the rotor 3 on the rotor 3 and the second fixed-wing 22 on the first fixed-wing 21
Independent operating cooperates again, and aircraft can be made to fly to switch between the state of lifting flat：When on the first fixed-wing 21
When rotor 3 on rotor 3 and the second fixed-wing 22 works at the same time, aircraft is in flat winged state, when only the second fixed-wing 22
On rotor 3 work when, aircraft is in jacking condition.
Optionally embodiment, head section 11 include end 111 and middle part 112, end 111 and middle part 112 it
Between be connected by deforming driving device 4, the first fixed-wing 21 is rotatablely connected with end 111 and the rotor on the first fixed-wing 21
3 rotation axis is parallel with the axis of the length direction of end 111, and the rotor 3 under state of flight on the second fixed-wing 22 turns
Moving axis is in the state with horizontal plane, when deformation driving device 4 drives end 111 and drives the rotation on the first fixed-wing 21
It is complete to deform the Fixed Wing AirVehicle that hung down when the rotation axis of the wing 3 turns to parallel with the rotation axis of rotor 3 on the second fixed-wing 22
In jacking condition；When end 111 drive the first fixed-wing 21 on rotor 3 rotation axis turn to on the second fixed-wing 22
The angle of rotation axis of rotor 3 when being acute angle, right angle or obtuse angle, the full deformation Fixed Wing AirVehicle that hung down is in put down and flies state.
Only the rotor 3 at 22 both ends of the second fixed-wing is the power brought or relatively limited of climbing of aircraft, therefore,
Consideration verts the rotor 3 at 21 both ends of the first fixed-wing to increase the power of aircraft climb, on the propeller set of rotor 3
It installs additional and verts or wrench device can increase the complexity of entire fuselage, reduce its overall security, therefore in end 111 and centre
Deformation driving device 4 is provided between portion 112, deformation driving device 4 can be by changing between head section 11 and 12 upper surface of endpiece
Angle, 22 relative position of the second fixed-wing to drive the first fixed-wing 21 being connect with head section 11 and be connect with endpiece 12 occur
Variation, to make the folder between 3 rotation axis of rotor in the rotation axis and the second fixed-wing 22 of the rotor 3 on the first fixed-wing 21
Angle changes, and to drive fuselage to switch between flat winged form and lifting form, is not necessarily to the propeller set in rotor 3 in this way
Upper installation is verted or wrench device.
Deformation driving device 4 in the present invention is steering engine, and steering engine is to realize the most common device being most easy to get of frame deflection；
Deformation driving device 4 is arranged between head section 11 and endpiece 12, the center of gravity of such fuselage only can front fuselage and rear end it
Between move, the balance of fuselage totality will not be impacted.
Optionally embodiment, the full fixed-wing both ends lower surface for deforming the Fixed Wing AirVehicle that hung down is equipped with can folding and unfolding
Floor-type support device.
In order to increase stability when fuselage is temporarily parked in ground, being provided in the lower surface at fixed-wing both ends can folding and unfolding
Floor-type support device, the device landing when open, state of flight or the grounding state when can pack up reduce space.
The above description is merely a specific embodiment, but scope of protection of the present invention is not limited thereto, any
Those familiar with the art in the technical scope disclosed by the present invention, can easily think of the change or the replacement, and should all contain
Lid is within protection scope of the present invention.Therefore, protection scope of the present invention should be based on the protection scope of the described claims.
Claims (10)
- The Fixed Wing AirVehicle 1. a kind of full deformation has been hung down, which is characterized in that including fuselage, fixed-wing and rotor, wherein：It is described solid Determine the wing to be rotatablely connected with the fuselage, the rotor is arranged on the fixed-wing or the fuselage；When the full deformation is hung down Fixed Wing AirVehicle is played when being in grounding state, the fixed-wing can be turned to the length of the spanwise and the fuselage The parallel position in direction has been hung down Fixed Wing AirVehicle occupied space in the horizontal direction with reducing the full deformation, and/or, The fuselage can be folded to reduce the full deformation and hang down Fixed Wing AirVehicle institute in the horizontal direction in the vertical direction The space occupied.
- 2. full deformation according to claim 1 has been hung down Fixed Wing AirVehicle, which is characterized in that the fuselage include head section with Endpiece；It is rotatablely connected between the head section and the endpiece, when the full Fixed Wing AirVehicle that hung down that deforms is in state of flight When, the axis of the head section and the endpiece in the longitudinal direction is parallel；At Fixed Wing AirVehicle has been hung down in the full deformation When the state of grounding, the head section can be rotated down to be folded to and be fit together with the lower surface of the endpiece.
- The Fixed Wing AirVehicle 3. full deformation according to claim 2 has been hung down, which is characterized in that the length of the head section is equal to The length of the endpiece.
- The Fixed Wing AirVehicle 4. full deformation according to claim 2 has been hung down, which is characterized in that the fixed-wing includes first Fixed-wing and the second fixed-wing, first fixed-wing and second fixed-wing are rotated with the head section and the endpiece respectively Connection, when it is described it is full deformation hung down Fixed Wing AirVehicle be in the grounding state when, first fixed-wing and it is described second fixation The spanwise of the wing can turn to parallel with the length direction of the head section and the endpiece respectively.
- The Fixed Wing AirVehicle 5. full deformation according to claim 4 has been hung down, which is characterized in that the wing of first fixed-wing Exhibition direction is when turning to parallel with the head section, the both ends of first fixed-wing be within the head section both ends or with Head section both ends flush；The spanwise of second fixed-wing turns to parallel with the length direction of the endpiece When, the both ends of second fixed-wing be within the head section both ends or with endpiece both ends flush.
- The Fixed Wing AirVehicle 6. full deformation according to claim 4 has been hung down, which is characterized in that the rotor is mounted on described The both ends of the spanwise of first fixed-wing and second fixed-wing.
- 7. full deformation according to claim 6 has been hung down Fixed Wing AirVehicle, which is characterized in that described complete to deform fixation of having hung down Rotor aircraft further includes at least two motors, and the motor is respectively the institute on first fixed-wing and second fixed-wing It states rotor and power is provided.
- The Fixed Wing AirVehicle 8. full deformation according to claim 7 has been hung down, which is characterized in that on first fixed-wing The rotation axis of the rotor is parallel with the axis of the length direction of the head section, the rotor on second fixed-wing Rotation axis and the upper surface of the endpiece are perpendicular.
- 9. full deformation according to claim 8 has been hung down Fixed Wing AirVehicle, which is characterized in that the head section include end with Middle part is connected between the end and the middle part by deforming driving device, first fixed-wing and the end The rotation axis of portion's rotation connection and the rotor on first fixed-wing is equal with the axis of the length direction of the end It goes, the rotation axis of the rotor under state of flight on second fixed-wing is in the state with horizontal plane, when described Deformation driving device drives end and the rotation axis of the rotor on first fixed-wing is driven to turn to and fixed with second When the rotation axis of the rotor on the wing is parallel, the full Fixed Wing AirVehicle that hung down that deforms is in jacking condition；When the end Portion drives the rotation axis of the rotor on first fixed-wing to turn to the rotation with the rotor on the second fixed-wing When the angle of axis is acute angle, right angle or obtuse angle, the full deformation has hung down Fixed Wing AirVehicle in flat winged state.
- The Fixed Wing AirVehicle 10. full deformation according to claim 1 has been hung down, which is characterized in that the full deformation has been hung down solid The fixed-wing both ends lower surface for determining rotor aircraft is equipped with retractable floor-type support device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810273990.4A CN108394546A (en) | 2018-03-29 | 2018-03-29 | It is complete to deform the Fixed Wing AirVehicle that hung down |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810273990.4A CN108394546A (en) | 2018-03-29 | 2018-03-29 | It is complete to deform the Fixed Wing AirVehicle that hung down |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108394546A true CN108394546A (en) | 2018-08-14 |
Family
ID=63099180
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810273990.4A Pending CN108394546A (en) | 2018-03-29 | 2018-03-29 | It is complete to deform the Fixed Wing AirVehicle that hung down |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108394546A (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20120248259A1 (en) * | 2011-03-24 | 2012-10-04 | Mark Allan Page | Long endurance vertical takeoff and landing aircraft |
| CN105775122A (en) * | 2016-03-03 | 2016-07-20 | 刘博� | Tilt rotor type aircraft |
| CN106428548A (en) * | 2016-10-12 | 2017-02-22 | 曹萍 | Vertical take-off and landing unmanned aerial vehicle |
-
2018
- 2018-03-29 CN CN201810273990.4A patent/CN108394546A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20120248259A1 (en) * | 2011-03-24 | 2012-10-04 | Mark Allan Page | Long endurance vertical takeoff and landing aircraft |
| CN105775122A (en) * | 2016-03-03 | 2016-07-20 | 刘博� | Tilt rotor type aircraft |
| CN106428548A (en) * | 2016-10-12 | 2017-02-22 | 曹萍 | Vertical take-off and landing unmanned aerial vehicle |
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Application publication date: 20180814 |