CN207917144U - One kind is verted wing helicopter - Google Patents
One kind is verted wing helicopter Download PDFInfo
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- CN207917144U CN207917144U CN201820008512.6U CN201820008512U CN207917144U CN 207917144 U CN207917144 U CN 207917144U CN 201820008512 U CN201820008512 U CN 201820008512U CN 207917144 U CN207917144 U CN 207917144U
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- wing
- fuselage
- drive paddle
- rotary shaft
- type drive
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Abstract
The utility model is related to vehicle technology fields, more particularly to one kind is verted wing helicopter, including fuselage, preceding wing drive paddle assembly, rear type drive paddle component, the first rotary shaft and the second rotary shaft, preceding wing drive paddle assembly is connected by the first rotary shaft with fuselage, and it can vert around the first rotary shaft, type drive paddle component is connected by the second rotary shaft with fuselage afterwards, and can be verted around the second rotary shaft；Preceding wing drive paddle assembly include be symmetricly set on fuselage both sides preceding wing and preceding type drive paddle component, the wing root of preceding wing be connected with the first rotary shaft, the wing tip of preceding wing is connected with preceding type drive paddle component, and preceding type drive paddle component and rear type drive paddle component form triangle.Under the different state of flight of the wing helicopter that verts, preceding wing drive paddle assembly and rear type drive paddle component have different tilt angles, can promote dynamic efficiency and the safety of helicopter, realize the effect for improving the speed of a ship or plane and extending flyer miles.
Description
Technical field
The utility model is related to vehicle technology field, more particularly to one kind is verted wing helicopter.
Background technology
Helicopter (helicopter) is also known as " gyroplane ", is one of important type of aircraft, can be run on no airport
Landing under the conditions of road, and can spot hover and horizontal flight in the air, have great using flexible, be widely used in rescuing
Help, fire-fighting, commander, transport, aerial work etc..
Current helicopter both domestic and external is based on single rotor formula helicopter.Single rotor formula helicopter is architectural limitation, cruise
Speed is usually no more than 300 kilometers/hour, and ultimate run is no more than 1000 kilometers, and performance can not show a candle to fixed wing aircraft.The whole world
Active service unique vertical landing transporter V-22 fishing hawk helicopters, maximum flying speed is up to 509 kilometers, flying speed, height
Modern helicopters are all greatly exceeded, but its control system is extremely complex, safety is not high, always can not be at due to often falling machine
For mainstream helicopter.
In view of current helicopter in the speed of a ship or plane, voyage and the defect of safety, need to research and develop a kind of speed of a ship or plane, voyage is more than
Single rotor formula helicopter at present, while again safe and reliable product.
Utility model content
For the above problem of the prior art, verts wing helicopter, pass through the purpose of this utility model is to provide one kind
Completely new structure design keeps the big voyage of high speed and the conflicting defect of safe VTOL to solve existing helicopter.
To solve the above-mentioned problems, the utility model provides one kind and verts wing helicopter, including fuselage, preceding wing drive
Paddle assembly, rear type drive paddle component, the first rotary shaft and the second rotary shaft,
First rotary shaft is arranged in the front of the fuselage, and the first rotary shaft is parallel with the horizontal axis of the fuselage, institute
Wing drive paddle assembly is connected by first rotary shaft with the fuselage before stating, and can be inclined around first rotary shaft
Turn, second rotary shaft is arranged in the tail portion of the fuselage, and the second rotary shaft is parallel with the horizontal axis of the fuselage, dynamic after described
Power paddle component is connected by second rotary shaft with the fuselage, and can be verted around second rotary shaft；
The preceding wing drive paddle assembly includes the preceding wing for being symmetricly set on the fuselage both sides and preceding type drive paddle group
Part, the wing root of the preceding wing are connected with first rotary shaft, and the wing tip of preceding wing is connected with the preceding type drive paddle component, institute
Type drive paddle component forms triangle with the rear type drive paddle component before stating.
Preferably, the preceding type drive paddle component includes preceding type drive paddle, first accommodates shell and the first driver, and described first
It accommodates shell with the wing tip of the preceding wing to be connected, in described first accommodates shell, first drives for the first driver setting
The shaft of dynamic device stretches out described first and accommodates shell, and is connect with the preceding type drive paddle, and first driver is for driving institute
Type drive paddle rotation before stating.
Preferably, type drive paddle component includes rear type drive paddle, second accommodates shell and the second driver after described, and described second
It accommodating shell and rotates axis connection with described second, the second driver setting is in described second accommodates shell, and described second
The shaft of driver stretches out described second and accommodates shell, and is connect with the rear type drive paddle, and second driver is for driving
Type drive paddle rotation after described.
Preferably, when the wing helicopter that verts is in level flight condition, the shaft of first driver and described
The shaft of second driver is parallel with the longitudinal axis of the fuselage, when the wing helicopter that verts is in VTOL state, institute
Axis oriented normal of the shaft of the shaft and second driver of stating the first driver with the fuselage.
Preferably, the axial line of the shaft of first driver is parallel with the aerofoil of preceding wing.
Further, the wing helicopter that verts further includes rear wing components, and the rear wing components are symmetrically positioned in described
The rear portion of fuselage, the rear wing components include rear wing and rudder face, and the wing root of the rear wing is connected with the fuselage, rear machine
The wing tip of the wing is connected with the rudder face, and the rudder face is vertical with the horizontal axis of the fuselage, the aerofoil and the machine of the rear wing
The horizontal axis of body is parallel.
Preferably, the tail portion of the fuselage has opening, and the opening is with the side horizontally and vertically of the vertical fuselage
To through the tail portion of the fuselage.
Preferably, second rotary shaft is located in the opening, and the both ends of the second rotary shaft are separately connected the opening
Two side, it is described after type drive paddle component can be rotated in the opening around second rotary shaft.
Preferably, the rear wing components are symmetrically distributed in the both sides of the opening.
Further, the wing helicopter that verts further includes undercarriage and a pair of of aileron, and the undercarriage is arranged described
The lower part of fuselage, the aileron are symmetricly set on the both sides of the fuselage, and positioned at the lower section of the preceding wing.
Due to above-mentioned technical proposal, the utility model has the advantages that：
(1) preceding wing drive paddle assembly is connect by the first rotary shaft with fuselage by the utility model, in fuselage afterbody
Rear type drive paddle component is added, and rear type drive paddle component is connected with fuselage by the second rotary shaft, preceding wing drive paddle assembly
It can vert around the first rotary shaft, rear type drive paddle component can vert around the second rotary shaft, to drive helicopter horizontal flight
Or VTOL.Since preceding type drive paddle component and rear type drive paddle component constitute stable triangular support so that helicopter hangs down
Straight landing is safer, simultaneously because preceding type drive paddle axis is parallel with the aerofoil of preceding wing so that VTOL dynamic efficiency is most
Bigization.
(2) under the different state of flight of helicopter, pass through the preceding wing drive paddle assembly of control and rear type drive paddle component
Tilt angle, the dynamic efficiency of helicopter can be promoted.When the wing helicopter that verts is in level flight condition, the first driving
The shaft of device and the shaft of the second driver are all parallel with the longitudinal axis of fuselage, and preceding type drive paddle and rear type drive paddle provide for fuselage jointly
Forward propulsive force, meanwhile, the aerofoil of the aerofoil of preceding wing and rear wing is all parallel with the longitudinal axis of fuselage, and aerofoil is greatly reduced
The air drag born can promote flying speed and extend flyer miles.When verting, wing helicopter is in VTOL state
When, for the shaft of the shaft of the first driver and the second driver with the axis oriented normal of fuselage, preceding type drive paddle and rear type drive paddle are total
It is all the propulsive force of fuselage offer upwardly or downwardly, meanwhile, the aerofoil of preceding wing and the axis oriented normal of fuselage can substantially subtract
The air drag that wing is born before during few landing, improves landing dynamic efficiency and safety.
(3) the utility model only needs the tilt angle for controlling preceding wing drive paddle assembly and rear type drive paddle component can be real
The effect for now promoting the speed of a ship or plane and shipping kilometre has control simple, maneuverable excellent compared to existing fishing hawk helicopter
Gesture.
Description of the drawings
It, below will be to institute in embodiment or description of the prior art in order to illustrate more clearly of the technical solution of the utility model
Attached drawing to be used is needed to be briefly described.It should be evident that the accompanying drawings in the following description is only some of the utility model
Embodiment for those of ordinary skill in the art without creative efforts, can also be attached according to these
Figure obtains other attached drawings.
Fig. 1 is structural schematic diagram of the wing helicopter under flat winged state that vert that the utility model embodiment provides；
Fig. 2 is structural schematic diagram of the wing helicopter under flat winged state that vert that the utility model embodiment provides；
Fig. 3 is structural schematic diagram of the wing helicopter under VTOL state that vert that the utility model embodiment provides；
Fig. 4 is structural schematic diagram of the wing helicopter under VTOL state that vert that the utility model embodiment provides.
In figure：1- fuselages, wing before 2-, type drive paddle component before 3-, type drive paddle component after 4-, the first rotary shafts of 5-, 6-
Two rotary shafts, wing components after 7-, 8- undercarriages, 9- openings, the 10- longitudinal axis, 11- horizontal axis, 12- ailerons, type drive paddle before 31-, 32-
First accommodates shell, the first drivers of 33-, type drive paddle after 41-, and 42- second accommodates shell, the second drivers of 43-, machine after 71-
The wing, 72- rudder faces.
Specific implementation mode
In order to make those skilled in the art more fully understand the utility model, below in conjunction with the utility model reality
The attached drawing in example is applied, the technical scheme in the utility model embodiment is clearly and completely described, it is clear that described
Embodiment is only the embodiment of the utility model part, instead of all the embodiments.Based on the reality in the utility model
Example is applied, every other embodiment obtained by those of ordinary skill in the art without making creative efforts is all answered
When the range for belonging to the utility model protection.
It should be noted that the specification and claims of the utility model and term " first " in attached drawing, "
Two " etc. be for distinguishing similar object, without being used to describe specific sequence or precedence.It should be appreciated that using in this way
Data can be interchanged in the appropriate case, so that the embodiments of the present invention described herein can be in addition to scheming herein
Sequence other than those of showing or describe is implemented.In addition, term " comprising " and " having " and their any deformation, it is intended that
In cover it is non-exclusive include, for example, containing the process of series of steps or unit, method, system, product or equipment need not
Those of be limited to clearly to list step or unit, but may include not listing clearly or for these processes, method,
The intrinsic other steps of product or equipment or unit.
Existing aircraft mostly uses greatly the mode of tilting rotor to realize that VTOL and high speed fixed-wing are cruised two kinds
The conversion of pattern, aircraft propeller are functionally similar to lifting airscrew the VTOL stage, are providing vertically upward
The posture of aircraft is adjusted by feathering while lift, when high speed fixed-wing cruises, propeller needs forward
It verts 90 degree and provides thrust power for aircraft, this makes such aircraft propeller must satisfy lifting airscrew and fixation
The wing promotes two kinds of characteristics of paddle, does not simply fail to take into account the blade aerodynamic efficiency under two states in this way, and also cause rotor control
Mechanism and control method are sufficiently complex, simultaneously because wing does not vert together with propeller, cause VTOL stage wing
Interference is generated to propeller downwash flow, further reduced the pneumatic efficiency and control stability of aircraft.It results in above
Aircraft safety and reliability are relatively low, in actual use Frequent Accidents.
For above-mentioned present situation, vert wing helicopter the present embodiment provides one kind, the type drive paddle group after fuselage afterbody is added
Rear type drive paddle component is connected by the second rotary shaft with fuselage, preceding wing drive paddle assembly is passed through the first rotary shaft by part
It is connect with fuselage, preceding wing drive paddle assembly can be rotated around the first rotary shaft, and rear type drive paddle component can be around the second rotation
Shaft rotation is dynamic, and preceding wing drive paddle assembly includes preceding wing and preceding type drive paddle component, as a result, preceding type drive paddle component and rear type drive paddle
Component constitutes stable triangular support, can be with the horizontal flight of smooth drive helicopter or VTOL.Type drive paddle component afterwards
The propulsive force of helicopter flight or landing can be increased by being arranged, and promote dynamic efficiency, be conducive to improve the speed of a ship or plane and extended voyage；Due to
Preceding wing verts together with preceding type drive paddle component so that VTOL stage wing not will produce propeller downwash flow dry
It disturbs, improves the pneumatic efficiency and control stability of aircraft.
Fig. 1-4 shows topology layout and the method for operation of the wing helicopter that verts of the utility model.In general, it goes straight up to
Machine has the longitudinal axis, horizontal axis and vertical axis, and the front end of helicopter is machine nose, rear end is tail, is known as by the axis of machine nose to tail
" longitudinal axis ", is connected by machine both wings and the axis for running through center of gravity is known as " horizontal axis ", from top to bottom and through the axis of center of gravity, referred to as
" vertical axis ".In figure, 10 be the longitudinal axis of the wing helicopter that verts, and 11 be the horizontal axis of the wing helicopter that verts.
Referring to Fig. 1-4, the wing helicopter provided in this embodiment that verts includes fuselage 1, preceding wing drive paddle assembly, moves afterwards
Power paddle component 4, the first rotary shaft 5 and the second rotary shaft 6, first rotary shaft 5 are arranged in the front of the fuselage 1, and first
Rotary shaft 5 is parallel with the horizontal axis of the fuselage, and the preceding wing drive paddle assembly passes through first rotary shaft 5 and the machine
Body 1 is connected, and can vert around first rotary shaft 5, and second rotary shaft 6 is arranged in the tail portion of the fuselage 1, and second
Rotary shaft 6 is parallel with the horizontal axis of the fuselage, and the rear type drive paddle component 4 passes through second rotary shaft 6 and 1 phase of the fuselage
Even, it and can vert around second rotary shaft 6；The preceding wing drive paddle assembly includes being symmetricly set on the fuselage two
The preceding wing 2 of side and preceding type drive paddle component 3, the wing root of the preceding wing 2 are connected with first rotary shaft 4, the wing of preceding wing 2
Sharp to be connected with the preceding type drive paddle component 3, the preceding type drive paddle component 3 forms triangle with the rear type drive paddle component 4.Due to
First rotary shaft 5 penetrates fuselage 1, and for the helicopter structure compared with Xi Le Aircraft Companies of U.S. X-18, fuselage profile is complete, whole
Intensity will not be weakened.The diameter of first rotary shaft 5 can be as small as possible in the case where meeting strength demand, and wing is rigid before making
Bearing well can be with passing power paddle lift, to increase cargo hold sectional area in fuselage under VTOL state.
Preceding type drive paddle component 3 and preceding wing are relatively fixed, in offline mode transfer process together by the first rotary shaft
Deflection.The preceding type drive paddle component 3 includes that preceding type drive paddle 31, first accommodates shell 32 and the first driver 33, and described first holds
Shell 32 of receiving is connected with the wing tip of the preceding wing 2, and first driver 33 is arranged in described first accommodates shell 32, the
The shaft of one driver 33 stretches out described first and accommodates shell 32, and is connect with the preceding type drive paddle 31, first driver
33 for driving the preceding type drive paddle 31 to rotate.For the force efficiency that flies before guarantee helicopter, tradition may be used in preceding type drive paddle
The common propelled at high velocity paddle of Fixed Wing AirVehicle.
In offline mode transfer process, wing drive paddle assembly is around the second rotary shaft one before rear type drive paddle component cooperation
With deflection.Type drive paddle component 4 includes that rear type drive paddle 41, second accommodates shell 42 and the second driver 43 after described, and described second
It accommodates shell 42 to connect with second rotary shaft 6, the setting of the second driver 43 is in described second accommodates shell 42, institute
The shaft for stating the second driver 43 stretches out the second receiving shell 42, and is connect with the rear type drive paddle 41, and described second drives
Dynamic device 43 is for driving the rear type drive paddle 41 to rotate.
Under different flight state, the preceding wing drive paddle assembly and rear type drive paddle component of the wing helicopter that verts have not
Same mated condition.When the wing helicopter that verts is in level flight condition, the shaft of first driver 33 and institute
The shaft for stating the second driver 43 is parallel with the longitudinal axis of the fuselage 1, at this point, preceding type drive paddle and rear type drive paddle are to go straight up to jointly
Machine provides forward propulsive force, and function is equivalent to fixed-wing and promotes paddle, the aerofoil of the aerofoil of preceding wing and rear wing all with machine
The longitudinal axis of body is parallel, and the air drag that aerofoil is born is greatly reduced, and can promote flying speed and extend flyer miles.Work as institute
When stating the wing helicopter that verts and being in VTOL state, preceding wing drive paddle assembly is rotated by 90 ° on the first axial rotary, after
Type drive paddle component is rotated down 90 ° around the second rotary shaft so that the shaft of first driver 33 and second driver
Axis oriented normal of 43 shaft with the fuselage 1, at this point, preceding type drive paddle is in body upper, rear type drive paddle is under fuselage
Side, preceding type drive paddle and rear type drive paddle provide propulsive force upward or downward for helicopter jointly, and function is equivalent to helicopter rotation
The wing improves the stability of fuselage entirety, while preceding wing is with preceding since preceding type drive paddle and rear type drive paddle form triangular support
Type drive paddle verts together, avoids wing and generates interference to preceding type drive paddle downwash flow, further improves the safety of helicopter
Property, while improving the dynamic efficiency of VTOL.
As a preferred embodiment, the axial line of the shaft of first driver 33 and the preceding wing 2
Aerofoil is parallel.No matter winged state or VTOL state, the aerofoil of the axial line of the shaft of first driver and preceding wing are put down
All it is parallel, the utilization rate of dynamic efficiency can be improved in this way, more particularly to makes VTOL dynamic efficiency maximize.
Specifically, the tail portion of the fuselage has an opening 9, the opening 9 with the vertical fuselage horizontally and vertically
The tail portion of the fuselage is run through in direction.Second rotary shaft 6 is located in the opening 9, and the both ends of the second rotary shaft 6 connect respectively
The two side of the opening is connect, the rear type drive paddle component 4 can rotate in the opening 9 around second rotary shaft 6.
The wing helicopter provided in this embodiment that verts further includes rear wing components 7, undercarriage and a pair of of aileron.Machine after described
Wing component 7 is symmetrically positioned in the both sides of the opening 9, and the rear wing components 7 include rear wing 71 and rudder face 72, the rear wing
71 wing root is connected with the fuselage 1, and the wing tip of rear wing 71 is connected with the rudder face 72, the rudder face 72 and the fuselage 1
Horizontal axis it is vertical, it is described after wing 71 aerofoil it is parallel with the horizontal axis of the fuselage 1.The undercarriage 8 is arranged in the fuselage
Lower part, undercarriage includes nose-gear and rear undercarriage, and it is normal that Fixed Wing AirVehicle may be used in nose-gear and rear undercarriage
Wheeled construction.The aileron 12 is symmetricly set on the both sides of the fuselage, and positioned at the lower section of the preceding wing 2, aileron
12 are fixed on fuselage and can not vert, and the design of aileron 12 can increase the flat winged state lift of helicopter.
The above-mentioned preceding wing for being arranged on fuselage both sides and preceding type drive paddle component vert around the first rotary shaft, machine before both sides
The action of verting of the wing can synchronize or asynchronous.Figures 1 and 2 show that structure of the wing helicopter under flat winged state of verting is shown
It is intended to, puts down under winged state, the aerofoil of preceding wing is parallel with the longitudinal axis of fuselage, and the first driver of type drive paddle action turns before driving
The shaft for the second driver that type drive paddle acts after axis and driving is parallel with the longitudinal axis of the fuselage；When VTOL, preceding machine
The wing rotates clockwise 90 ° around first rotating shaft, and rear type drive paddle component rotates clockwise 90 ° around the second shaft, makes the first driver
Shaft and the shaft of the second driver with the axis oriented normal of fuselage, the structure of the wing helicopter under VTOL state of verting
Shown in Fig. 3 and Fig. 4.
Due to above-mentioned technical proposal, the utility model has the advantages that：
(1) preceding wing drive paddle assembly is connect by the first rotary shaft with fuselage by the utility model, in fuselage afterbody
Rear type drive paddle component is added, and rear type drive paddle component is connected with fuselage by the second rotary shaft, preceding wing drive paddle assembly
It can vert around the first rotary shaft, rear type drive paddle component can vert around the second rotary shaft, to drive helicopter horizontal flight
Or VTOL.Since preceding type drive paddle component and rear type drive paddle component constitute stable triangular support so that helicopter hangs down
Straight landing is safer, simultaneously because preceding type drive paddle axis is parallel with the aerofoil of preceding wing so that VTOL dynamic efficiency is most
Bigization.
(2) under the different state of flight of helicopter, pass through the preceding wing drive paddle assembly of control and rear type drive paddle component
Tilt angle, the dynamic efficiency of helicopter can be promoted.When the wing helicopter that verts is in level flight condition, the first driving
The shaft of device and the shaft of the second driver are all parallel with the longitudinal axis of fuselage, and preceding type drive paddle and rear type drive paddle provide for fuselage jointly
Forward propulsive force, meanwhile, the aerofoil of the aerofoil of preceding wing and rear wing is all parallel with the longitudinal axis of fuselage, and aerofoil is greatly reduced
The air drag born can promote flying speed and extend flyer miles.When verting, wing helicopter is in VTOL state
When, for the shaft of the shaft of the first driver and the second driver with the axis oriented normal of fuselage, preceding type drive paddle and rear type drive paddle are total
It is all the propulsive force of fuselage offer upwardly or downwardly, meanwhile, the aerofoil of preceding wing and the axis oriented normal of fuselage can substantially subtract
The air drag that wing is born before during few landing, improves landing dynamic efficiency and safety.
(3) the utility model only needs the tilt angle for controlling preceding wing drive paddle assembly and rear type drive paddle component can be real
The effect for now promoting the speed of a ship or plane and shipping kilometre has control simple, maneuverable excellent compared to existing fishing hawk helicopter
Gesture.
Each technical characteristic of above example can be combined arbitrarily, to keep description succinct, not to above-described embodiment
In each technical characteristic it is all possible combination be all described, as long as however, the combination of these technical characteristics be not present lance
Shield is all considered to be the range of this specification record.
Above example only expresses the several embodiments of the utility model, the description thereof is more specific and detailed, but simultaneously
Cannot the limitation to utility model patent range therefore be interpreted as.It should be pointed out that for the ordinary skill people of this field
For member, without departing from the concept of the premise utility, various modifications and improvements can be made, these belong to this reality
With novel protection domain.Therefore, the protection domain of the utility model patent should be determined by the appended claims.
Claims (10)
- The wing helicopter 1. one kind is verted, which is characterized in that including fuselage (1), preceding wing drive paddle assembly, rear type drive paddle component (4), the first rotary shaft (5) and the second rotary shaft (6),In the front of the fuselage (1), the first rotary shaft (5) and the horizontal axis of the fuselage are flat for first rotary shaft (5) setting Row, the preceding wing drive paddle assembly are connected by first rotary shaft (5) with the fuselage (1), and can be around described First rotary shaft (5) is verted, and second rotary shaft (6) is arranged in the tail portion of the fuselage (1), the second rotary shaft (6) and institute The horizontal axis for stating fuselage is parallel, and the rear type drive paddle component (4) is connected by second rotary shaft (6) with the fuselage (1), and It can vert around second rotary shaft (6)；The preceding wing drive paddle assembly includes the preceding wing (2) for being symmetricly set on the fuselage both sides and preceding type drive paddle component (3), the wing root of the preceding wing (2) is connected with first rotary shaft (5), wing tip and the preceding type drive paddle of preceding wing (2) Component (3) is connected, and the preceding type drive paddle component (3) forms triangle with the rear type drive paddle component (4).
- 2. the wing helicopter according to claim 1 that verts, which is characterized in that the preceding type drive paddle component (3) includes preceding dynamic Power paddle (31), first accommodate shell (32) and the first driver (33), and described first accommodates shell (32) and the preceding wing (2) Wing tip be connected, in described first accommodates shell (32), the first driver (33) turns for first driver (33) setting Axis stretches out described first and accommodates shell (32), and is connect with the preceding type drive paddle (31), and first driver (33) is for driving Dynamic preceding type drive paddle (31) rotation.
- 3. the wing helicopter according to claim 2 that verts, which is characterized in that moved after type drive paddle component (4) includes after described Power paddle (41), second accommodate shell (42) and the second driver (43), and described second accommodates shell (42) rotates with described second Axis (6) connects, and second driver (43) is arranged in described second accommodates shell (42), second driver (43) Shaft stretches out described second and accommodates shell (42), and is connect with the rear type drive paddle (41), and second driver (43) is used for Drive rear type drive paddle (41) rotation.
- 4. the wing helicopter according to claim 3 that verts, which is characterized in that the wing helicopter that verts is in horizontal flight When state, the shaft of first driver (33) and the shaft of second driver (43) are vertical with the fuselage (1) Axis is parallel, when the wing helicopter that verts is in VTOL state, the shaft and described second of first driver (33) Axis oriented normal of the shaft of driver (43) with the fuselage (1).
- 5. the wing helicopter according to claim 2 that verts, which is characterized in that the axis of the shaft of first driver (33) Heart line is parallel with the preceding aerofoil of wing (2).
- 6. the wing helicopter according to claim 1 that verts, which is characterized in that further include rear wing components (7), the rear machine Wing component (7) is symmetrically positioned in the rear portion of the fuselage (1), it is described after wing components (7) include rear wing (71) and rudder face (72), The wing root of wing (71) is connected with the fuselage (1) after described, and the wing tip of rear wing (71) is connected with the rudder face (72), described Rudder face (72) is vertical with the horizontal axis of the fuselage (1), and the aerofoil of the rear wing (71) is parallel with the horizontal axis of the fuselage (1).
- 7. the wing helicopter according to claim 6 that verts, which is characterized in that the tail portion of the fuselage has opening (9), institute State the tail portion that opening (9) runs through the fuselage with the direction horizontally and vertically of the vertical fuselage.
- 8. the wing helicopter according to claim 7 that verts, which is characterized in that second rotary shaft (6) is located at described open In mouthful (9), the both ends of the second rotary shaft (6) are separately connected the two side of the opening, it is described after type drive paddle component (4) can be It is rotated around second rotary shaft (6) in the opening (9).
- 9. the wing helicopter according to claim 7 that verts, which is characterized in that wing components (7) are symmetrically distributed in after described The both sides of the opening (9).
- 10. the wing helicopter according to claim 1 that verts, which is characterized in that further include undercarriage (8) and a pair of of aileron (12), the undercarriage (8) is arranged in the lower part of the fuselage, and the aileron (12) is symmetricly set on the both sides of the fuselage, And positioned at the lower section of the preceding wing (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820008512.6U CN207917144U (en) | 2018-01-03 | 2018-01-03 | One kind is verted wing helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820008512.6U CN207917144U (en) | 2018-01-03 | 2018-01-03 | One kind is verted wing helicopter |
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| Publication Number | Publication Date |
|---|---|
| CN207917144U true CN207917144U (en) | 2018-09-28 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820008512.6U Active CN207917144U (en) | 2018-01-03 | 2018-01-03 | One kind is verted wing helicopter |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110329492A (en) * | 2019-06-25 | 2019-10-15 | 李海刚 | Unmanned plane |
| CN111605708A (en) * | 2019-02-25 | 2020-09-01 | 飞巧科技有限公司 | Deflection wing aircraft |
-
2018
- 2018-01-03 CN CN201820008512.6U patent/CN207917144U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111605708A (en) * | 2019-02-25 | 2020-09-01 | 飞巧科技有限公司 | Deflection wing aircraft |
| CN110329492A (en) * | 2019-06-25 | 2019-10-15 | 李海刚 | Unmanned plane |
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Effective date of registration: 20220217 Address after: 310051 No. 1760, Jiangling Road, Hangzhou, Zhejiang, Binjiang District Patentee after: ZHEJIANG GEELY HOLDING GROUP Co.,Ltd. Address before: 200000 Fengjing town Industrial Park, Jinshan District, Shanghai Patentee before: SHANGHAI MAPLE AUTOMOBILE Co.,Ltd. Patentee before: Zhejiang Geely Holding Group Co., Ltd |