CN107264779A - A kind of method that utilization fin wing adjustment sheet aircraft navigates by water posture - Google Patents
A kind of method that utilization fin wing adjustment sheet aircraft navigates by water posture Download PDFInfo
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- CN107264779A CN107264779A CN201710484967.5A CN201710484967A CN107264779A CN 107264779 A CN107264779 A CN 107264779A CN 201710484967 A CN201710484967 A CN 201710484967A CN 107264779 A CN107264779 A CN 107264779A
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- fin wing
- sheet
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- wing
- fuselage
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/04—Adjustable control surfaces or members, e.g. rudders with compound dependent movements
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Abstract
The invention discloses the method that a kind of utilization fin wing adjustment sheet aircraft navigates by water posture, belong to technical field of aerospace.The large area sheet fin wing is installed on the sheet fuselage of sheet aircraft, change the relative motion state of the fin wing and air-flow by rotating the fin wing, according to the aerodynamic structure of the fin wing, air-flow acts power on the fin wing, the power or torque that the active force is produced are put on after sheet fuselage, can control the navigation posture of airborne vehicle.>=2, the fin wing can be located at sheet fuselage back in pairs to the depth-width ratio and length-width ratio of sheet fuselage, change the airflow direction formation torque being applied to it and sheet fuselage is produced deflection；Also sheet afterbody can be located at, and produces sheet fuselage and is horizontally diverted；Sheet belly is may also be arranged in pairs in, and sheet fuselage is produced vertical deflection.There is effectively to safeguard sheet fuselage characteristic, coordinated flight mechanism, vehicle reliability and adaptability is improved, can extensively should be in manned or unmanned airborne vehicle etc..
Description
Technical field
The present invention relates to the method that a kind of utilization fin wing adjustment sheet aircraft navigates by water posture, belong to aeronautical technology neck
Domain.
Background technology
Man-carrying aircraft can be divided into fixed-wing and the major class of rotary wings two, and fixed-wing is common in Horizontal Take-off and Landing airborne vehicle（As sprayed
Gas formula passenger plane）, and rotary wings are common in VTOL airborne vehicle（Such as helicopter）.The technical merit just reached at present is come
Say, Fixed-Wing can be easy to operate with high-speed flight, but need to rely on runway landing.Rotary wing aircraft can vertically rise
Drop, is not required to rely on runway landing, strong adaptability, but mechanism is lacked of proper care, and manipulation is complicated, and flying speed is slow, and fuel efficiency is low.
New vertical landing airborne vehicle can solve VTOL and meet horizontal flight two again after using sheet fuselage
The contradiction planted offline mode and produced, by as the new developing direction of VTOL airborne vehicle.But, the special knot of sheet fuselage
Structure brings the problem of some are new to the gesture stability of airborne vehicle again, is mainly shown as：（1）Laminar character.Sheet fuselage it is special
Structural requirement controlling organization is likewise supplied with the characteristic of sheet.（2）Control moment is big.Relative to existing airborne vehicle, sheet fuselage
Special construction improve stability of the sheet machine airborne vehicle in both direction in length and breadth, it is therefore desirable to pitching moment and yaw forces
Square is bigger.（3）Compatibility.Attitude coutrol mechanism needs equally to be capable of two kinds of flight operating modes of compatible VTOL and horizontal flight
It is required that.（4）Harmony.Sheet machine airborne vehicle has the advantages that inherent flight mechanism is coordinated, and attitude coutrol mechanism can only show this
A little advantages, it is impossible to spoiling the harmony property.（5）Balance.Sheet machine airborne vehicle uses rotor VTOL, it is necessary to hovering phase again
Possess balance ability, and horizontal flight is then required without this.Therefore need to design an effectively reliable provisional moment of torsion
Balance control mechanism.（6）Reliability.Sheet machine airborne vehicle has decoupled the flight requirement of mutual restriction, with simple and reliable excellent
Point, attitude coutrol mechanism can only show these advantages, it is impossible to destroy.（7）Intuitive.Sheet machine Aircraft requirements gesture stability machine
Structure is simple and easy to do, control effect is intuitively easy to get.（8）Accuracy.The sensing of sheet machine Aircraft requirements attitude coutrol mechanism is clear and definite,
It can be precisely controlled.
The content of the invention
The technical problem to be solved in the present invention is to overcome the relatively low flight attitude control brought of sheet aircraft speed
The problem of middle low flow velocity air force is not enough and sheet fuselage bring the problems such as control moment increases to the gesture stability of airborne vehicle,
A kind of method that utilization fin wing adjustment sheet aircraft navigates by water posture is proposed, sheet fuselage air dynamic characteristics is not being destroyed
On the premise of realize effective control of sheet aircraft state.
In order to solve the above technical problems, the present invention proposes a kind of utilization fin wing adjustment sheet aircraft navigation posture
Method, the airborne vehicle using the sheet fuselage of depth-width ratio and length-width ratio >=2 installs one as object on the sheet fuselage of airborne vehicle
Individual or multiple large area sheet fin wings, the relative motion state for changing the fin wing and air-flow by rotating the fin wing acts power or logical
The assembled state generation torque for changing the fin wing is crossed, the power or torque that the fin wing is produced is put on sheet fuselage, control airborne vehicle
Navigate by water posture.The installation number of the fin wing is determined according to actual needs.Preferably, the depth-width ratio and length-width ratio of the sheet fuselage
It is 3-10.
The fin wing has fin wing axle, and the fin wing can be using fin wing axle as axis rotation, so as to obtain aircraft attitude adjustment needs
Auxiliary torque, power-assisted sheet aircraft navigate by water posture adjustment.The rotation of the fin wing can be provided by independent power, such as ad hoc
Manipulate motor etc., can also manpower driving in case the need of fault forced landing.
The fin wing can be closed flat forms one with sheet fuselage, can be using conventional jack（Structure）Realize, such as cut with scissors
Connect foldable structure etc..
The fin wing is large area laminated structure, and enough air are produced in low-speed operations using the large area aerofoil of the fin wing
Power, controls the navigation posture of airborne vehicle.The specific area of the fin wing is specifically determined according to actual needs, is met in low-speed operations
Enough air forces can be produced and the navigation posture of airborne vehicle is adjusted.
The fin wing can before and after use or use in pairs up and down in pairs, front and rear try one's best in pairs when using spaces out, i.e.,
Spaced out as far as possible in the range of fuselage, with specific reference to determination is actually needed, to produce the boat of enough Torque Control airborne vehicles
Row posture.
Installation site of the fin wing on sheet fuselage is unrestricted, may be disposed at the head, back, abdomen of sheet fuselage
Portion, afterbody, waist, the fin wing mainly adjust sheet aircraft pitch attitude when being located at belly or waist, the fin wing is located at head
Or sheet aircraft horizontal deflection posture is mainly adjusted during afterbody, the fin wing mainly adjusts sheet aircraft when being located at back
Device transverse translation posture.For other airborne vehicles, the position limitation factor of the sheet fin wing is installed on sheet fuselage to be lacked
It is many.
The fin wing uses large area rigidity thin-wall construction, and fin wing curve is streamlined, to reduce the gas of section as far as possible
Flow resistance power.Fin wing surface is generally continuous level, or using the pneumatic curved surface of aircraft wing, so that the air-flow for flowing through its surface is protected
Continuous flowing is held, air force adjustment demand is met.
Its aerofoil is not in a plane together with sheet fuselage during fin wing work of the present invention for pitch control, but with
The plane of sheet fuselage intersects vertically；When the fin wing for pitch control does not work, air-flow can be complied with naturally lower anti-or straight
Receive to close and enter sheet fuselage plane, to reduce its harmful effect to airborne vehicle as far as possible.
The present invention is needed by installing the large area sheet fin wing on the sheet fuselage of sheet airborne vehicle when airborne vehicle is navigated by water
During adjustment navigation posture, allow the fin wing to be rotated around fin wing axle, change the relative motion state of the fin wing and air-flow and produce enough
Active force, or enough torque is produced by the assembled state for changing the fin wing, the active force puts on sheet fuselage, overcomes sheet
The problem of low flow velocity air force is not enough in the relatively low flight attitude control brought of aircraft speed and sheet fuselage are to boat
The gesture stability of pocket brings the problems such as control moment increases, and realizes the control that posture is navigated by water to airborne vehicle.
Compared with prior art, the present invention can effectively overcome the relatively low flight attitude brought of sheet aircraft speed
The problem of low flow velocity air force is not enough in control and sheet fuselage bring control moment increase etc. to the gesture stability of airborne vehicle
Problem, realizes the smooth conversions of two kinds of mode of operations of VTOL and horizontal flight and effectively compatible, with can effectively safeguard piece
The advantages of shape fuselage characteristic, coordinated flight mechanism, raising vehicle reliability and adaptability, it can be widely applied to man-carrying aircraft
Or the field such as unmanned plane.
Brief description of the drawings
Fig. 1 is the sheet aircraft schematic diagram using the inventive method embodiment 1.
Fig. 2 is the sheet aircraft schematic diagram using the inventive method embodiment 2.
Fig. 3 is the sheet aircraft schematic diagram using the inventive method embodiment 3.
Fig. 4 is the sheet aircraft schematic diagram using the inventive method embodiment 4.
In figure：1- sheet aircrafts, the 2- fin wings, 2-1- anterior dorsal fins, 2-2- posterior dorsals, 2-3- tail fins, 2-4- abdomeinal fins,
3- fin wing axles, 3-1- anterior dorsal fin axles, 3-2- posterior dorsal axles, 3-3- tail fin shafts, 3-4- abdomeinal fin axles, 4- perforates, 5- propellers, 6- rotations
The wing.
Embodiment
The embodiment to the present invention is further described in detail below in conjunction with the accompanying drawings, unreceipted skill in embodiment
Art or product are prior art or can be by buying the conventional products obtained.
Embodiment 1：The method that navigation is controlled using the fin wing referring to Fig. 1, this sheet airborne vehicle, using depth-width ratio as 10, length and width
Airborne vehicle than the sheet fuselage for 3 is object, and the large area sheet fin wing 2 is installed on the sheet fuselage 1 of airborne vehicle, by turning
The dynamic fin wing changes it and the relative motion state of air-flow acts power or produces torque by the assembled state for changing the fin wing, makes
The power or torque that the fin wing is produced put on sheet fuselage, control the navigation posture of airborne vehicle.The fin wing 2 has fin wing axle 3, and the fin wing 2 can
It is axis rotation with fin wing axle 3, it is rotated by supporting power（Motor）There is provided, can also manpower driving in case fault forced landing it
Need.The fin wing 2 is large area laminated structure, and enough air forces are produced in low-speed operations using the large area aerofoil of the fin wing 2, is controlled
The navigation posture of airborne vehicle processed.The fin wing 2 has two, located at belly, front-back staggered, reversed dip, uses in pairs, pull open as far as possible away from
From and be separately positioned on the front-end and back-end of sheet belly, to produce enough torque, main adjustment sheet aircraft
Device pitch attitude, so as to control the navigation posture of airborne vehicle.The fin wing 2 can be closed flat and sheet machine using conventional extendible structure
Figure is integral.For pitch control the fin wing 2 location mid-shaft be provided with fin wing axle 3, during work its aerofoil not with sheet fuselage 1
It is in a plane together, but is intersected vertically with the plane of sheet fuselage 1；, can when the fin wing for pitch control does not work
To comply with, air-flow is naturally lower instead or directly to be folded into sheet fuselage plane.The fin wing 2 uses large area rigidity thin-wall construction, the fin wing
Contour line is streamlined.The surface of the fin wing 2 is continuous level, using the pneumatic curved surface of aircraft wing.
Sheet aircraft is used after sheet fuselage, and fuselage VTOL pattern and horizontal flight are solved well
Compatibling problem under two kinds of mode of operations of pattern, but the difficult contradiction of pitching manipulation is also brought to a certain extent, and fin
The use of the wing, increases the pitching moment of airborne vehicle, it is possible thereby to which it is difficult to solve sheet aircraft pitching manipulation well
The problem of.The fin wing 2 can be rotated with fin wing axle 3 for axle center, allow the fin wing 2 to avoid blocking windstream, downwash flow and ascending air,
The requirement of compatible road driving, three kinds of operating modes of VTOL and horizontal flight.The dislocation of the fin wing 2 of front and back position is arranged, reversely inclined
Tiltedly, pitching moment can significantly be increased.The fin wing 2 can be locked by manual or automatic control rotation or locking, former and later two fin wings 2
Complete Synchronization is rotated backward to obtain maximum pitching moment afterwards, can also rotate to complete various vernier controls respectively.The fin wing 2 is adopted
With large area structure, pitching moment is further increased.
The present invention is exaggerated control moment using the fin wing, cleverly position and the mutual cooperation of large area, it is ensured that boat
Pocket can apply certain control by manipulating the rotation fin wing, adjust landing attitude, improve in unpowered emergency landing
The security and success rate of unpowered forced landing.When operating former and later two fin wings to tilt in the same direction, airborne vehicle can be achieved in hovering shape
Movable control under state.Under floating state, rotor produces downwash flow；When the current skeg wing turns forward together, sheet
Aircraft is moved rearwards by；Currently, the skeg wing is with when retreating, and sheet aircraft is moved forward.In sheet fuselage
During airborne vehicle horizontal flight, the fin wing can carry out HeiFin to fuselage, reach the effect being precisely controlled.
Embodiment 2：The method that navigation is controlled using the fin wing referring to Fig. 2, this sheet airborne vehicle, using depth-width ratio as 3, length-width ratio
Airborne vehicle for 8 sheet fuselage is object, and large area sheet is installed in the afterbody vertical level of the sheet fuselage 1 of airborne vehicle
The fin wing 2, the relative motion state for changing itself and air-flow by rotating the fin wing 2 acts power, puts on the power that the fin wing is produced
Sheet fuselage, controls the navigation posture of airborne vehicle.The fin wing 2 has a fin wing axle 3, the fin wing 2 can with fin wing axle 3 for axle center left-right rotation,
It is rotated by supporting power（Motor）There is provided, can also manpower driving in case need of fault forced landing, main adjustment sheet fuselage navigates
Pocket horizontal attitude.The fin wing 2 is large area laminated structure, using the large area aerofoil of the fin wing 2, in the flight of sheet aircraft
It is middle to produce enough air forces, driftage control ability during sheet aircraft horizontal flight is increased, control airborne vehicle
Posture is navigated by water, the difficult contradiction of sheet aircraft driftage control is solved.The fin wing 2 is rotated with fin wing axle 3 for axle center, Ke Yirang
The fin wing 2 avoids blocking windstream, downwash flow and rises air-flow, meets the compatible road driving of sheet aircraft, vertically rises
The requirement of drop and three kinds of operating modes of horizontal flight.There is installation propeller 5 in perforate 4, hole on the fin wing 2, propeller 5 and the fin wing 2 can be made
Collaboration rotation changes direction of propulsion.The fin wing 2 is large area rigidity plate, to increase the stability of aircraft attitude adjustment and expand inclined
Torque.The fin wing 2 uses large area rigidity thin-wall construction, and its contour line is streamlined, surface is continuous level, using the aircraft wing
The pneumatic curved surface of type.
Embodiment 3：The method that navigation is controlled using the fin wing referring to Fig. 3, this sheet airborne vehicle, using depth-width ratio as 5, length-width ratio
Airborne vehicle for 10 sheet fuselage is object, at the back of the sheet fuselage 1 of airborne vehicle and afterbody with sheet fuselage same
The Plane Installation large area sheet fin wing, the relative motion state for changing itself and air-flow by rotating the fin wing acts power, makes fin
The power that the wing is produced puts on sheet fuselage, controls the navigation posture of airborne vehicle.The back of sheet fuselage 1 is provided with two panels fin in pairs
The wing, i.e. anterior dorsal fin 2-1 and posterior dorsal 2-2, the two dorsal fin wings have an anterior dorsal fin axle 3-1 and posterior dorsal axle 3-2, dorsal fin can using fin wing axle as
Axle center left-right rotation, they are symmetrically set in the same plane of airborne vehicle rotorshaft both sides, main adjustment sheet aircraft
Transverse translation posture；The afterbody of sheet fuselage 1 is provided with a piece of fin wing, i.e. tail fin 2-3, main adjustment sheet aircraft
Horizontal attitude；Each fin wing common combination formation fin wing group, and the work that cooperates, navigation posture needed for adjustment airborne vehicle.Each fin
The wing is large area laminated structure, and using the large area aerofoil of the fin wing, enough air are in-flight produced in sheet aircraft
Power, and enough torque is produced by the assembled state for changing the fin wing, when greatly increasing sheet aircraft horizontal flight
Driftage control ability, control the navigation posture of airborne vehicle, solve the difficult contradiction of sheet aircraft driftage control.Each fin
The wing is rotated by axle center of its axle, and it is rotated by supporting power（Motor）There is provided, can also manpower driving in case the need of fault forced landing,
The fin wing can be allowed to avoid blocking windstream, downwash flow and rise air-flow, the compatible road driving of sheet aircraft is met, hang down
The requirement of three kinds of operating modes of straight landing and horizontal flight.Have on the tail fin 2-3 of the afterbody of sheet fuselage 1 in perforate 4, hole and spiral shell is installed
Oar 5 is revolved, propeller 5 can be made to cooperate with rotation to change direction of propulsion with the fin wing.The fin wing is large area rigidity plate, to increase airborne vehicle
The stability of pose adjustment simultaneously expands deflection torque.Each fin wing use large area rigidity thin-wall construction, its contour line for it is streamlined,
Surface is continuous level, using the pneumatic curved surface of aircraft wing.
Embodiment 4：The method that navigation is controlled using the fin wing referring to Fig. 4, this sheet airborne vehicle, using depth-width ratio as 4, length-width ratio
Airborne vehicle for 9 sheet fuselage is object, and large area sheet is installed in the back of the sheet fuselage 1 of airborne vehicle, afterbody and belly
The shape fin wing, the relative motion state for changing itself and air-flow by rotating the fin wing acts power, puts on the power that the fin wing is produced
Sheet fuselage, controls the navigation posture of airborne vehicle.The back of sheet fuselage 1 is in pairs provided with the two panels fin wing, i.e. anterior dorsal fin 2-1 with after
Dorsal fin 2-2, the two dorsal fin wings have anterior dorsal fin axle 3-1 and posterior dorsal axle 3-2, and dorsal fin can be using fin wing axle as axle center left-right rotation, they
It is symmetrically set in the same plane of airborne vehicle rotorshaft both sides, assists mainly in the horizontal shifting posture of adjustment airborne vehicle；Sheet machine
The afterbody of body 1 is provided with a piece of fin wing, i.e. tail fin 2-3, and tail fin 2-3 has tail fin shaft 3-3, and tail fin assists mainly in the water of adjustment airborne vehicle
Flat posture；The belly of sheet fuselage 1 is provided with the two panels fin wing, i.e. abdomeinal fin 2-4, and abdomeinal fin 2-4 has an abdomeinal fin axle 3-4, abdomeinal fin located at belly,
Front-back staggered, reversed dip, use in pairs, space out and be separately positioned on the front-end and back-end of sheet belly as far as possible,
To produce enough torque, the pitch attitude of adjustment sheet aircraft is assisted mainly in；Each fin wing common combination formation fin wing
Group, and the work that cooperates, navigation posture needed for adjustment airborne vehicle.Each fin wing is large area laminated structure, utilizes the fin wing
Large area aerofoil, in-flight produces enough air forces, and produce by the assembled state for changing the fin wing in sheet aircraft
Raw enough torque, greatly increases driftage control ability during sheet aircraft horizontal flight, controls the navigation of airborne vehicle
Posture, solves the difficult contradiction of sheet aircraft driftage control.Each fin wing is rotated by axle center of its axle, and it is rotated by supporting
Power（Motor）There is provided, can also manpower driving in case the need of fault forced landing.Can allow the fin wing avoid blocking windstream, under wash
Air-flow and liter air-flow, meet the compatible road driving of sheet aircraft, the requirement of three kinds of operating modes of VTOL and horizontal flight.
There is installation propeller 5 in perforate 4, hole on the tail fin 2-3 of the afterbody of sheet fuselage 1, propeller 5 can be made to cooperate with rotation with the fin wing
Turn to change direction of propulsion.The fin wing is large area rigidity plate, to increase the stability of aircraft attitude adjustment and expand deflection torque.
Each fin wing uses large area rigidity thin-wall construction, and its contour line is streamlined, surface is continuous level, using the gas of aircraft wing
Moving surface.
The technology contents of the present invention are described above in conjunction with accompanying drawing, but protection scope of the present invention be not limited to it is described
In content, the knowledge that one skilled in the relevant art possesses, the premise of present inventive concept can also not departed from
Under the technology contents of the present invention are made a variety of changes, within the spirit and principles of the invention, any modification for being made, etc.
With replacement, improvement etc., it should be included in the scope of the protection.
Claims (10)
1. a kind of method that utilization fin wing adjustment sheet aircraft navigates by water posture, it is characterised in that：With depth-width ratio and length and width
Airborne vehicle than sheet fuselage >=2 is object, and one or more large area sheets are installed on the sheet fuselage of airborne vehicle
The fin wing, the relative motion state for changing the fin wing and air-flow by rotating the fin wing acts power or the combination shape by changing the fin wing
State produces torque, power or torque that the fin wing is produced is put on sheet fuselage, controls the navigation posture of airborne vehicle.
2. the method that utilization fin wing adjustment sheet aircraft according to claim 1 navigates by water posture, it is characterised in that：
Preferably, the depth-width ratio and length-width ratio of the sheet fuselage are 3-10.
3. the method that utilization fin wing adjustment sheet aircraft according to claim 1 navigates by water posture, it is characterised in that：
The fin wing has fin wing axle, and the fin wing can be using fin wing axle as axis rotation.
4. the method that the utilization fin wing adjustment sheet aircraft according to claim 1 or 3 navigates by water posture, its feature exists
In：The fin wing can be closed flat forms one with sheet fuselage.
5. the method that the utilization fin wing adjustment sheet aircraft according to claim 1 or 3 navigates by water posture, its feature exists
In：The fin wing is large area laminated structure, and enough air forces are produced in low-speed operations using the large area aerofoil of the fin wing,
Control the navigation posture of airborne vehicle.
6. the method that the utilization fin wing adjustment sheet aircraft according to claim 1 or 3 navigates by water posture, its feature exists
In：The fin wing can before and after use or use in pairs up and down in pairs, front and rear try one's best in pairs when using spaces out, to produce foot
The navigation posture of enough Torque Control airborne vehicles.
7. the method that utilization fin wing adjustment sheet aircraft according to claim 1 navigates by water posture, it is characterised in that：
Installation site of the fin wing on sheet fuselage is unrestricted, may be disposed at the head of sheet fuselage, back, belly, afterbody,
Waist, the fin wing mainly adjusts sheet aircraft pitch attitude when being located at belly or waist, when the fin wing is located at head or afterbody
Main adjustment sheet aircraft horizontal deflection posture, the fin wing mainly adjusts sheet aircraft when being located at back laterally flat
Move posture.
8. the method that the utilization fin wing adjustment sheet aircraft according to claim 1 or 3 navigates by water posture, its feature exists
In：The fin wing uses large area rigidity thin-wall construction, and fin wing curve is streamlined.
9. the method that the utilization fin wing adjustment sheet aircraft according to claim 1 or 3 navigates by water posture, its feature exists
In：The fin wing surface is generally continuous level, or using the pneumatic curved surface of aircraft wing.
10. the method that the sheet airborne vehicle according to claim 1 or 7 controls navigation by the fin wing, it is characterised in that：For
Its aerofoil is not in a plane together with sheet fuselage during the fin wing work of pitch control, but vertical with the plane of sheet fuselage
It is intersecting；When the fin wing for pitch control does not work, air-flow can be complied with and descend anti-or directly folded into sheet fuselage naturally
Plane.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710484967.5A CN107264779A (en) | 2017-06-23 | 2017-06-23 | A kind of method that utilization fin wing adjustment sheet aircraft navigates by water posture |
| PCT/CN2018/090417 WO2018224033A1 (en) | 2017-06-09 | 2018-06-08 | Aircraft with imitation beetle elytron wings |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710484967.5A CN107264779A (en) | 2017-06-23 | 2017-06-23 | A kind of method that utilization fin wing adjustment sheet aircraft navigates by water posture |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107264779A true CN107264779A (en) | 2017-10-20 |
Family
ID=60068752
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710484967.5A Pending CN107264779A (en) | 2017-06-09 | 2017-06-23 | A kind of method that utilization fin wing adjustment sheet aircraft navigates by water posture |
Country Status (1)
| Country | Link |
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| CN (1) | CN107264779A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109956024A (en) * | 2017-12-25 | 2019-07-02 | 内蒙古宝亮信息技术股份有限公司 | A kind of aircraft |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB393976A (en) * | 1931-12-16 | 1933-06-16 | Cierva Juan De La | Improvements in and relating to aircraft having freely rotative wings |
| CN105473443A (en) * | 2013-08-12 | 2016-04-06 | 第一装置有限公司 | Convertiplane with new aerodynamic and technical solutions which make the aircraft safe and usable |
| CN205469797U (en) * | 2016-01-12 | 2016-08-17 | 许正科 | Intelligent flying robot of fish shape |
| CN105984584A (en) * | 2015-03-04 | 2016-10-05 | 刘新广 | Arrow-type airplane |
| CN205931235U (en) * | 2016-08-10 | 2017-02-08 | 上海牧羽航空科技有限公司 | Amphibious aircraft with automatic balance fin |
-
2017
- 2017-06-23 CN CN201710484967.5A patent/CN107264779A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB393976A (en) * | 1931-12-16 | 1933-06-16 | Cierva Juan De La | Improvements in and relating to aircraft having freely rotative wings |
| CN105473443A (en) * | 2013-08-12 | 2016-04-06 | 第一装置有限公司 | Convertiplane with new aerodynamic and technical solutions which make the aircraft safe and usable |
| CN105984584A (en) * | 2015-03-04 | 2016-10-05 | 刘新广 | Arrow-type airplane |
| CN205469797U (en) * | 2016-01-12 | 2016-08-17 | 许正科 | Intelligent flying robot of fish shape |
| CN205931235U (en) * | 2016-08-10 | 2017-02-08 | 上海牧羽航空科技有限公司 | Amphibious aircraft with automatic balance fin |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109956024A (en) * | 2017-12-25 | 2019-07-02 | 内蒙古宝亮信息技术股份有限公司 | A kind of aircraft |
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