CN107323650A - Movable wing aircraft - Google Patents
Movable wing aircraft Download PDFInfo
- Publication number
- CN107323650A CN107323650A CN201610290506.XA CN201610290506A CN107323650A CN 107323650 A CN107323650 A CN 107323650A CN 201610290506 A CN201610290506 A CN 201610290506A CN 107323650 A CN107323650 A CN 107323650A
- Authority
- CN
- China
- Prior art keywords
- wing
- port
- starboard
- aileron
- fuselage
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
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
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/58—Wings provided with fences or spoilers
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C2009/005—Ailerons
Abstract
The present invention relates to a kind of movable wing aircraft, being respectively arranged on the left side and the right side on port wing and starboard wing, port wing, starboard wing for fuselage is respectively and fixedly provided with engine, provided with undercarriage behind nose-gear, left back undercarriage, the right side below fuselage, it is characterised in that：Provided with flap rotation axis and wing drive mechanism, port wing is inner, starboard wing the inner is arranged on flap rotation axis, flap rotation axis is vertically arranged with fuselage datum line, wing drive mechanism, which can drive port wing, starboard wing by flap rotation axis and be fixed on port wing, the engine synchronization on starboard wing, to be rotated, that is, is adjusted port wing, starboard wing and be fixed on the angle of port wing, the engine on starboard wing and horizontal direction；Flap rotation axis and port wing, starboard wing are located at the both sides of the top, the lower section of fuselage or fuselage of fuselage.
Description
Technical field
The present invention relates to a kind of movable wing aircraft.
Background technology
Fixed wing aircraft is the important component of modern transportation instrument, fixed wing aircraft fuselage
Be respectively arranged on the left side and the right side to be equipped with port wing and starboard wing, port wing, starboard wing and start
Machine, power is provided for aircraft.Fixed wing aircraft, which exists, to be disadvantageous in that, one is to take off to need
Runway is wanted, required airport floor space is big；Two be that takeoff and landing require very high to driving technology,
And the Effects of Density that aircraft landing is taken off landing by airport is very big.
The content of the invention
The present invention goal of the invention be to provide a kind of movable wing aircraft, be not required to takeoff runway, can
Realize VTOL.
Realize the object of the invention technical scheme：
A kind of movable wing aircraft, fuselage is respectively arranged on the left side and the right side port wing and starboard wing, left machine
Be respectively and fixedly provided with engine on the wing, starboard wing, below fuselage provided with nose-gear, left back undercarriage,
Undercarriage behind the right side, it is characterised in that：Provided with flap rotation axis and wing drive mechanism, in port wing
End, starboard wing the inner are arranged on flap rotation axis, and flap rotation axis is vertical with fuselage datum line to be set
Put, wing drive mechanism can drive port wing, starboard wing by flap rotation axis and be fixed on left machine
Engine synchronization rotation on the wing, starboard wing, that is, adjust port wing, starboard wing and be fixed on left machine
The angle of engine and horizontal direction on the wing, starboard wing；Flap rotation axis and port wing, right machine
The wing is located at the both sides of the top, the lower section of fuselage or fuselage of fuselage.
Wing drive mechanism can drive port wing, starboard wing and be fixed on the hair of port wing, starboard wing
Motivation is adjusted to vertical direction from horizontal direction, you can regulation port wing, starboard wing and horizontal direction
Angle changes in 0 degree to 90 degree, when described port wing, starboard wing are in 0 degree of position, left
Engine and horizontal direction parallel on wing, starboard wing, described port wing, starboard wing are in 90
When spending position, engine and horizontal direction on port wing, starboard wing are in 90 degree.
The left and right sides of fuselage is additionally provided with left undercarriage aileron, right landing gear aileron, left undercarriage pair
The wing, right landing gear aileron respectively be located at port wing, the lower section of starboard wing, left undercarriage aileron outer end,
Right landing gear aileron outer end be respectively arranged below with left back undercarriage, it is right after undercarriage.
Left water conservancy diversion direction is respectively articulated with above left undercarriage aileron outer end, right landing gear aileron outer end
The wing, the right water conservancy diversion direction wing, the angle of the left water conservancy diversion direction wing, the right water conservancy diversion direction wing and vertical direction can
Adjust.
When aircraft is in state of flight, the front port between the left water conservancy diversion direction wing, the right water conservancy diversion direction wing
Width is more than rear port width.
Landing aileron is provided between port wing and starboard wing, landing aileron is installed on flap rotation axis
On, landing aileron rotates independently of port wing, starboard wing.
Flap rotation axis is located at the both sides of the top, the lower section of fuselage or fuselage of fuselage.
1,2 or many engine is equipped with port wing, starboard wing, engine is jet
Engine or airscrew engine.
The device have the advantages that：
Port wing of the present invention is inner, starboard wing the inner is arranged on flap rotation axis, flap rotation axis
It is vertically arranged with fuselage, wing drive mechanism can drive port wing, starboard wing by flap rotation axis
Rotation, that is, adjust the angle of port wing, starboard wing and horizontal direction；Wing drive mechanism of the present invention
Port wing, starboard wing can be driven to be rotated in 0 degree to 90 degree, you can regulation port wing, right machine
The wing changes with horizontal direction angle in 0 degree to 90 degree.When taking off, regulation port wing, right machine
The wing is in 90 degree with horizontal direction, correspondingly, with the engine and level on port wing, starboard wing
Direction in 90 degree, i.e. engine power drive direction from horizontally advance direction be adjusted to vertically to
Upper direction, similar helicopter realizes taking off vertically for aircraft, is not required to runway；Aircraft is by the shape that takes off
During state to cruising condition, the angle of port wing, starboard wing and horizontal direction is progressively adjusted, by
90 degree are progressively adjusted to 0 degree, when adjusting to 0 degree, in cruising condition, are now fixed with common
Wing aircraft is identical.Similarly, during aircraft landing, engine speed is reduced, is slowed down, reach rule
Determine after height, progressively adjust port wing, starboard wing and horizontal direction angle, until in 90 degree,
Realize vertical landing.The present invention can also make common fixed wing aircraft and use, normally taken off by runway,
Landing.
The left and right sides of fuselage of the present invention is additionally provided with left undercarriage aileron, right landing gear aileron, from left to right
Fall frame aileron, right landing gear aileron and be located at port wing, the lower section of starboard wing, left undercarriage pair respectively
Wing outer end, right landing gear aileron outer end be respectively arranged below with left back undercarriage, it is right after undercarriage；
Left undercarriage aileron that the present invention is set up, that right landing gear aileron substantially broadens existing aircraft is left back
Spacing behind undercarriage, the right side between undercarriage, further enhancing aircraft vertical and takes off when landing
Stationarity.
A left side is respectively articulated with above the left undercarriage aileron outer end of the present invention, right landing gear aileron outer end to lead
Flow the direction wing, the right water conservancy diversion direction wing, the left water conservancy diversion direction wing, the right water conservancy diversion direction wing and vertical direction
Angle is adjustable.Existing flap all designs the taper in host wing wing, and body of disembarking is too remote, this
Invention at the 1/3 of host wing equivalent to flap is set, with more preferably water conservancy diversion effect；Aircraft
During in state of flight, the front port between the left water conservancy diversion direction wing of the invention, the right water conservancy diversion direction wing is wide
Degree is more than rear port width, and the air-flow that aircraft is above come in when moving ahead from the water conservancy diversion direction wing is compressed,
High flow rate air-flow is produced, the vacuum pneumatic produced to airplane tail group in high-speed flight is made up,
Reduce vacuum pneumatic.
Landing aileron is provided between port wing and starboard wing of the present invention, landing aileron is installed on wing rotation
In rotating shaft, landing aileron rotates independently of port wing, starboard wing, that is, adjusts landing aileron and level
The angle in direction.In aircraft vertical takeoff and landing, coordinate with undercarriage aileron, can be further
Ensure the stationarity of fuselage.
Brief description of the drawings
Fig. 1 is front view when port wing of the present invention, starboard wing and horizontal direction are in 0 degree；
Fig. 2 is right view when port wing of the present invention, starboard wing and horizontal direction are in 0 degree；
Fig. 3 is front view when port wing of the present invention, starboard wing and horizontal direction are in 90 degree；
Fig. 4 is right view when port wing of the present invention, starboard wing and horizontal direction are in 90 degree；
Fig. 5 is undercarriage aileron of the present invention, the top view of water conservancy diversion direction alar part.
Embodiment
As Figure 1-Figure 4, fuselage 8 is respectively arranged on the left side and the right side port wing 11 and right machine
Engine 2 is respectively and fixedly provided with the wing 1, port wing 11, starboard wing 1, the lower section of fuselage 8 is risen provided with preceding
Fall undercarriage 9 (bikini undercarriage) behind frame 10, left back undercarriage 99, the right side, this is existing
Technology.Port wing 11 is inner, starboard wing 1 is inner is arranged on flap rotation axis 4, wing rotation
Rotating shaft 4 is vertically arranged with fuselage, and wing drive mechanism can drive left machine by flap rotation axis 4
The wing 11, starboard wing 1 and port wing 11, the synchronous rotary of engine 2 on starboard wing 1 are fixed on,
Adjust port wing 11, starboard wing 1 and the angle of horizontal direction, wing drive mechanism, wing
Rotary shaft 4 is arranged in mounting bracket 3.Flap rotation axis can be located at top, the fuselage of fuselage
Lower section or fuselage both sides, in the present embodiment, flap rotation axis 4 is located at the top of fuselage 8.
1,2 or many engine is equipped with port wing 11, right machine, engine is sent out for jet
In motivation or airscrew engine, the present embodiment, 1 spray is equipped with port wing 11, right machine
Gas engine.
Wing drive mechanism can drive port wing 11, starboard wing 1 and be fixed on port wing 11, the right side
Engine 2 on wing 1 is adjusted to vertical direction from horizontal direction, you can regulation port wing 11,
Starboard wing 1 changes with horizontal direction angle in 0 degree to 90 degree, as shown in Figure 1 and Figure 2, institute
When saying that port wing 11, starboard wing 1 are in 0 degree of position, the hair on port wing 11, starboard wing 1
Motivation 2 and horizontal direction parallel, as shown in Figure 3, Figure 4, described port wing 11, starboard wing 1
During in 90 degree of positions, engine 2 and horizontal direction on port wing 11, starboard wing 1 are in 90
Degree.Landing aileron 6 is provided between port wing 11 and starboard wing 1, landing aileron 6 is installed on wing
In rotary shaft 4, landing aileron 6 rotates independently of port wing 11, starboard wing 1.A left side for fuselage 8
Right both sides are additionally provided with left undercarriage aileron 55, right landing gear aileron 5, left undercarriage aileron 55, the right side
Undercarriage aileron 5 is located at port wing 11, the lower section of starboard wing 1, left undercarriage aileron 55 respectively
Outer end, the outer end of right landing gear aileron 5 be respectively arranged below with left back undercarriage 99, it is right after undercarriage
9.The left outer end of undercarriage aileron 55, right landing gear aileron 5 are respectively articulated with left water conservancy diversion above outer end
The direction wing 7, the right water conservancy diversion direction wing 77, the left water conservancy diversion direction wing 7, the right water conservancy diversion direction wing 77 with it is vertical
The angle in direction is adjustable.As shown in figure 5, when aircraft is in state of flight, the left water conservancy diversion direction wing 7,
Front port width between the right water conservancy diversion direction wing 77 is more than rear port width.
When taking off, regulation port wing 11, starboard wing 1 are in 90 degree with horizontal direction, correspondingly,
It is in 90 degree, i.e. engine 2 with the engine 2 on port wing 11, starboard wing 1 and horizontal direction
Power drive direction be adjusted to direction straight up by horizontally advancing direction, similar helicopter is real
Taking off vertically for existing aircraft, is not required to runway；Aircraft during takeoff condition to cruising condition, by
Step section port wing 11, starboard wing 1 and the angle of horizontal direction, are progressively adjusted to 0 by 90 degree
Degree is now identical with common fixed wing aircraft in cruising condition when adjusting to 0 degree.Similarly,
During aircraft landing, the rotating speed of engine 2 is reduced, is slowed down, reached after specified altitude, progressively adjust
Port wing 11, starboard wing 1 and horizontal direction angle are saved, until in 90 degree, realizing vertical landing.
The present invention can also make common fixed wing aircraft and use, and normally taken off, landed by runway.
Left undercarriage aileron 55, the right landing gear aileron 5 that the present invention is set up substantially broaden existing
Spacing behind the left back undercarriage 99 of aircraft, the right side between undercarriage 9, further enhancing aircraft vertical
The stationarity taken off when landing.When aircraft is in state of flight, the left water conservancy diversion direction wing 77 of the invention,
Front port width between the right water conservancy diversion direction wing 7 is more than rear port width, from water conservancy diversion when aircraft moves ahead
The air-flow that the direction wing is above come in is compressed, and produces high flow rate air-flow, and airplane tail group is flown in high speed
The vacuum pneumatic produced during row, is made up, and reduces vacuum pneumatic.The He of port wing 11 of the present invention
Landing aileron 6 is provided between starboard wing 1, landing aileron 6 rotates independently of port wing, starboard wing,
I.e. separately adjustable landing aileron 6 and the angle of horizontal direction.In aircraft vertical takeoff and landing,
Coordinate with undercarriage aileron, the stationarity of fuselage can be further ensured that.
Claims (7)
1. a kind of movable wing aircraft, fuselage is respectively arranged on the left side and the right side port wing and starboard wing,
Be respectively and fixedly provided with engine on port wing, starboard wing, below fuselage provided with nose-gear, left back rise and fall
Undercarriage behind frame, the right side, it is characterised in that：Provided with flap rotation axis and wing drive mechanism, left machine
The wing is inner, starboard wing the inner is arranged on flap rotation axis, and flap rotation axis hangs down with fuselage datum line
Straight to set, wing drive mechanism can drive port wing, starboard wing by flap rotation axis and be fixed on
Engine synchronization rotation on port wing, starboard wing, that is, adjust port wing, starboard wing and be fixed on
The angle of engine and horizontal direction on port wing, starboard wing；Flap rotation axis and port wing,
Starboard wing is located at the both sides of the top, the lower section of fuselage or fuselage of fuselage.
2. movable wing aircraft according to claim 1, it is characterised in that：Wing driving machine
Structure can drive port wing, starboard wing and be fixed on port wing, starboard wing engine from horizontal direction
It is adjusted to vertical direction, you can regulation port wing, starboard wing and horizontal direction angle are at 0 degree to 90
Change in degree, when described port wing, starboard wing are in 0 degree of position, on port wing, starboard wing
Engine and horizontal direction parallel, when described port wing, starboard wing are in 90 degree of positions, left machine
Engine and horizontal direction on the wing, starboard wing are in 90 degree.
3. movable wing aircraft according to claim 2, it is characterised in that：The left and right of fuselage
Both sides are additionally provided with left undercarriage aileron, right landing gear aileron, left undercarriage aileron, right landing gear pair
The wing is located at port wing, the lower section of starboard wing, left undercarriage aileron outer end, right landing gear aileron respectively
Outer end be respectively arranged below with left back undercarriage, it is right after undercarriage.
4. movable wing aircraft according to claim 3, it is characterised in that：Left undercarriage pair
The left water conservancy diversion direction wing, right water conservancy diversion direction are respectively articulated with above wing outer end, right landing gear aileron outer end
The wing, the angle of the left water conservancy diversion direction wing, the right water conservancy diversion direction wing and vertical direction is adjustable.
5. movable wing aircraft according to claim 4, it is characterised in that：Aircraft, which is in, to fly
During row state, the front port width between the left water conservancy diversion direction wing, the right water conservancy diversion direction wing is more than rear port
Width.
6. the movable wing aircraft according to claim 1 to 5 any one, it is characterised in that：
Landing aileron is provided between port wing and starboard wing, landing aileron is installed on flap rotation axis, risen
Aileron is dropped to rotate independently of port wing, starboard wing.
7. the movable wing aircraft according to claim 1 to 5 any one, it is characterised in that：
1,2 or many engine is equipped with port wing, starboard wing, engine starts for jet
Machine or airscrew engine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610290506.XA CN107323650A (en) | 2016-04-29 | 2016-04-29 | Movable wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610290506.XA CN107323650A (en) | 2016-04-29 | 2016-04-29 | Movable wing aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107323650A true CN107323650A (en) | 2017-11-07 |
Family
ID=60193014
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610290506.XA Pending CN107323650A (en) | 2016-04-29 | 2016-04-29 | Movable wing aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107323650A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2156133Y (en) * | 1993-02-10 | 1994-02-16 | 颜定国 | Simple propeller civil airplane |
| CN101875399A (en) * | 2009-10-30 | 2010-11-03 | 北京航空航天大学 | Tilt rotor aircraft adopting parallel coaxial dual rotors |
| CN104743112A (en) * | 2015-04-24 | 2015-07-01 | 南昌航空大学 | Novel tilt wing aircraft |
| CN104925254A (en) * | 2015-06-24 | 2015-09-23 | 吴畏 | Vertical take-off and landing aircraft |
| CN205131630U (en) * | 2015-11-02 | 2016-04-06 | 佛山市神风航空科技有限公司 | Double -oar vertical lift aircraft |
-
2016
- 2016-04-29 CN CN201610290506.XA patent/CN107323650A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2156133Y (en) * | 1993-02-10 | 1994-02-16 | 颜定国 | Simple propeller civil airplane |
| CN101875399A (en) * | 2009-10-30 | 2010-11-03 | 北京航空航天大学 | Tilt rotor aircraft adopting parallel coaxial dual rotors |
| CN104743112A (en) * | 2015-04-24 | 2015-07-01 | 南昌航空大学 | Novel tilt wing aircraft |
| CN104925254A (en) * | 2015-06-24 | 2015-09-23 | 吴畏 | Vertical take-off and landing aircraft |
| CN205131630U (en) * | 2015-11-02 | 2016-04-06 | 佛山市神风航空科技有限公司 | Double -oar vertical lift aircraft |
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