CN109250091A - A kind of flap aircraft - Google Patents
A kind of flap aircraft Download PDFInfo
- Publication number
- CN109250091A CN109250091A CN201811274265.5A CN201811274265A CN109250091A CN 109250091 A CN109250091 A CN 109250091A CN 201811274265 A CN201811274265 A CN 201811274265A CN 109250091 A CN109250091 A CN 109250091A
- Authority
- CN
- China
- Prior art keywords
- wing
- fuselage
- propeller
- motor
- aircraft
- 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.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/34—Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies
- B64C25/36—Arrangements or adaptations of wheels, tyres or axles in general
-
- 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
- B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/385—Variable incidence wings
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Toys (AREA)
Abstract
A kind of flap aircraft, belong to aviation field, including fuselage, empennage, wing, small propeller, motor, battery, rotary shaft, controller, wheel, engine and cockpit, the fuselage interior is equipped with cockpit, engine, battery, the controller of driver, and the propeller is placed in front of wing.The rotary shaft is connected with propeller.So wing, in conjunction with undercarriage, in ground run, the wheel on wing provides power.The tail vane and conventional tail vane are different, and structure is two big propellers in left and right and downward vertical fin composition.Flap aircraft of the invention in conjunction with traditional fixed-wing, when small propeller level, provides upward power, realizes vertical lift using propeller.When small propeller and wing vertical, the wind for flowing through wing can be accelerated, to bring bigger lift to wing.And the undercarriage in conjunction with wing, aircraft can be allowed in ground running.
Description
Technical field
A kind of flap aircraft belongs to aviation field more particularly to a kind of aircraft.
Background technique
With the development of science and technology, aviation field is also rapidly developed, various types of aircraft emerge one after another, quilt
It is widely used in various fields.But at present, there are some problems, such as fixed wing aircraft in the aircraft of aviation field mostly
The advantages of cruise duration is long although having, safety and stability, it needs runway when takeoff and landing, cannot be outside airport
Place landing, this also results in the at high cost and inconvenient of it.And gyroplane, helicopter and multi-rotor unmanned aerial vehicle etc. fly
Row device, in addition to helicopter and gyroplane be able to achieve it is manned other than, multi-rotor unmanned aerial vehicle is had got long long way to go at manned aspect, this
It is determined by the speciality of own, length when its continuation of the journey of the limitation of the technology of battery, motor and propeller, when being not appropriate for long
Between carry people to fly, some small-scale work can only be acted on, such as take photo by plane, cruise, purpose monitoring etc..And helicopter and rotor
Although machine can be manned, it cannot promote on the market, wherein the high height of the cost of helicopter, structure is complicated, and manipulates multiple
Miscellaneous, it is obviously not suitable for promoting.And although gyroplane also can be manned, its takeoff and landing still needs the race of certain distance
Road.
Summary of the invention
The present invention program is vertically moved up or down to invent one kind and do not need runway for deficiency existing for above scheme,
Ground also walking flap aircraft.
A kind of flap aircraft, including fuselage, empennage, wing, small propeller, motor, battery, rotary shaft, controller, wheel
Son, engine and cockpit.
The fuselage interior is equipped with cockpit, engine, battery and the controller of driver.The battery is placed in fuselage
Portion, with all electrical connection of motor.The controller is placed in fuselage interior, is connected with all motors and battery, controls motor
Work.The cockpit is placed in fore-body.
The wing is placed in fuselage two sides；Wing and fuselage connecting place are that activity connects structure, and the bascule is by being placed in machine
Engine inside body is connected, and wing is rotated around fuselage.The rotary shaft has two, is respectively placed in the right and left wing
Front is maintained a certain distance with wing, and length and wing are connected with length with wing: a motor is equipped with inside wing,
It is connected with rotary shaft, which is rotated.
Preferably, the wing and the connection structure of fuselage are similar with loose-leaf structure, and inside passes through gear and engine phase
Even.Work as engine start, can be by control stick, control wing rotation.
In the rotary shaft of the wing nose, multiple motors are installed；The stator same direction of motor itself is fixed on rotation
In shaft, rotor is connected with small propeller；So that small propeller is placed in front of wing.When rotary shaft rotation, small propeller
Also it changes in direction.The end of the wing is equipped with wheel, which is connected directly with motor, motor and battery and control
Device is connected；Angle between the wheel and wing is between 120 ° ~ 150 °.So that wing be rotated down gathering to minimum angles it
Afterwards, wheel can be perpendicular to the ground.
Preferably, the wing also has aileron, controls the yawing rotation of aircraft.
The empennage is placed in afterbody, different with conventional empennage, it is by two big propellers in left and right and vertical fin group
At engine of the power of big propeller in fuselage, vertical fin is controlled by the controller in fuselage.The direction of the vertical fin to
Under, there is a carrying roller in end.
The front fuselage installs a big propeller, and it is winged which, which is directly connected with the engine in fuselage,
Row device provides pulling force.
A groove can also be opened vertically in front fuselage, the rotational structure that groove width matches is installed in slot, the rotation knot
Structure one end is connected with fuselage, and the other end connects motor, and motor connects a big propeller, so that before big propeller is placed in fuselage
Side；Forward pulling force is provided for aircraft；The rotational structure is connected with the engine of fuselage interior, so that itself is able to rotate, from
And big propeller is enabled to change position, it is placed in above front fuselage, upward pulling force is provided for aircraft.
Flap aircraft of the invention using propeller with traditional fixed-wing in conjunction with, when small propeller is horizontal, provide to
On power, realize vertical lift.When small propeller and wing vertical, pulling force is provided, and can accelerate to flow through the wind of wing, to give
Wing brings bigger lift.And wing can rotate, itself also has wheel, by wing in conjunction with undercarriage, so that aircraft
It, can be by wheel in ground run at ground.
Detailed description of the invention
Fig. 1 is flap aircraft schematic diagram；Fig. 2 is the schematic diagram after flap aircraft wing collapses.
In figure, 1- fuselage, 2- tail vane, 3- wing, 4- small propeller, 5- rotary shaft, 6- wheel.
Specific embodiment
The present invention is illustrated now in conjunction with attached drawing, a kind of flap aircraft, including fuselage 1, empennage 2, wing 3,
Small propeller 4, motor, battery, rotary shaft 5, controller, wheel 6, engine and cockpit.
Cockpit, engine, battery and the controller of driver are installed inside the fuselage 1.The battery is placed in fuselage 1
Inside, with all electrical connection of motor.The controller is placed in inside fuselage 1, is connected with all motors and battery, and motor is controlled
Work.The cockpit is placed in 1 front of fuselage.
The wing 3 is placed in 1 two sides of fuselage, V-shaped distribution；Wing 3 and 1 connecting place of fuselage are that activity connects structure, the activity
Structure enables wing 3 to rotate by a certain angle around fuselage 1 by being connected with the engine being placed in inside fuselage 1.The wing 3
Connection structure with fuselage 1 is specially the axis line location piece axis of setting in fuselage 1, and left and right sides wing 3 is existed by connecting rod
It is connected at the axis of the axis line location of fuselage 1, and is connected herein by gear set with engine, wing 3 is rotated.Fuselage
1 slots according to the slewing area of the connecting rod width of wing 3 and wing 3, and wing 3 is rotated down, angle 45 ° ~ 75 ° it
Between.The rotary shaft 5 has two, is respectively placed in 3 front of the right and left wing, maintains a certain distance with wing 3, length and machine
The wing 3 is connected with length with wing 3: being equipped with a motor inside wing 3, is connected with rotary shaft 5, which is revolved
Turn.The wing 3 also has aileron, controls the yawing rotation of aircraft.Aileron is controlled by the controller in fuselage 1.
The end of the wing 3 is equipped with wheel, which is connected directly with motor, motor and battery and controller phase
Even；Angle between the wheel and wing 3 is between 120 ° ~ 150 °.So that wing 3 be rotated down gathering to minimum angles it
Afterwards, wheel can be perpendicular to the ground.This two wheels are as driving wheel, after the wing 3 of aircraft collapses downwards, by machine
The wing 3 is used as undercarriage, and wheel is self-powered, enables aircraft in ground run.
In the rotary shaft 5 of 3 front end of wing, multiple motors are installed；The stator of motor itself is fixed in the same direction
In rotary shaft 5, rotor is connected with small propeller 4；So that small propeller 4 is placed in 3 front of wing.It is small when rotary shaft 5 rotates
Propeller 4 also rotates with it.The direction of small propeller 4 be broadly divided into plane where and small propeller vertical with wing 34 with
Wing 3 is parallel.When small propeller 4 is vertical with wing 3, pulling force can be provided, and can accelerate to flow through the wind of wing 3, to improve
Lift.When 4 place plane of small propeller and horizontal wing 3, pulling force vertically upward can be provided, realizes vertical lift.It is described
The rotation angle of rotary shaft 5 is 90 °, so that the angle between small propeller 4 and wing 3 is converted between 0 ° and 90 °.
The empennage 2 is placed in 1 tail portion of fuselage, different with conventional empennage, it is by two big propellers in left and right and vertical fin
Composition, engine of the power of big propeller in fuselage 1, vertical fin are controlled by the controller in fuselage 1.The side of the vertical fin
To downward, there is a carrying roller in end.The effect of this carrying roller is: when aircraft is in ground running, can and 3 liang of wing
The wheel of end bears the weight of aircraft together, and keeps balance.And 3 front of left and right big propeller and wing of empennage 2
Small propeller 4 combines, and can provide pulling force, realizes vertical lift.Moreover, the two big propellers can also pass through rotational speed difference reality
The gesture stability of existing aircraft.
Claims (8)
1. a kind of flap aircraft, including fuselage (1), empennage (2), wing (3), small propeller (4), motor, battery, rotary shaft
(5), controller, wheel (6), engine and cockpit, it is characterised in that: the wing (3) is placed in fuselage (1) two sides；Wing (3)
It is that activity connects structure with fuselage (1) connecting place, which is connected by being placed in the internal engine of fuselage (1), so that wing
(3) it can be rotated around fuselage (1)；The rotary shaft (5) has two, is respectively placed in front of the right and left wing (3), with wing (3)
It maintains a certain distance, length and wing (3) are connected with length with wing (3): being equipped with a motor inside wing (3), with
Rotary shaft (5) is connected, so that the rotary shaft (5) can rotate；In the rotary shaft (5) of wing (3) front end, multiple electricity are installed
Machine；The stator same direction of motor itself is fixed on rotary shaft (5), and rotor is connected with small propeller (4)；So that small propeller
(4) it is placed in front of wing (3)；The end of the wing (3) is equipped with wheel (6), which is connected directly with motor, motor
It is connected with battery and controller；Angle between the wheel (6) and wing (3) is between 120 ° ~ 150 °, so that wing (3)
It is rotated down after gathering to minimum angles, wheel (6) can be perpendicular to the ground；The empennage (2) is placed in fuselage (1) tail portion, and
Conventional empennage (2) is different, it is made of two big propellers (4) in left and right and vertical fin, and the power of big propeller (4) comes from machine
Engine in body (1), vertical fin are controlled by the controller in fuselage (1)；The direction of the vertical fin is downward, and there is a load-bearing in end
Wheel；The battery is placed in fuselage (1) inside, with all electrical connection of motor；The controller is placed in fuselage (1) inside, with institute
There is motor to be connected with battery, controls the work of motor；The cockpit is placed in fuselage (1) front.
2. a kind of flap aircraft according to claim 1, it is characterised in that: install one big in fuselage (1) front end
Propeller, the big propeller are directly connected with the engine in fuselage (1), provide pulling force for aircraft.
3. a kind of flap aircraft according to claim 1, it is characterised in that: one can also be opened vertically in fuselage (1) front end
Road slot is installed on the rotational structure that groove width matches in slot, which is connected with fuselage (1), other end connection
Motor, motor connect a big propeller, so that big propeller is placed in front of fuselage (1)；Forward pulling force is provided for aircraft；
The rotational structure engine internal with fuselage (1) is connected, so that itself is able to rotate, so that big propeller can change position
It sets, is placed in above fuselage (1) front end, upward pulling force is provided for aircraft.
4. a kind of flap aircraft according to claim 1, it is characterised in that: the connection of the wing (3) and fuselage (1)
Structure is the axis line location piece axis of setting in fuselage (1), and left and right sides wing (3) passes through connecting rod in the axle center of fuselage (1)
Axis at line is connected, and is connected herein by gear set with engine, so that wing (3) can rotate；Fuselage (1) is according to wing
(3) slewing area of connecting rod width and wing (3) fluting, wing (3) are mainly rotated down, angle 45 ° ~ 75 ° it
Between.
5. a kind of flap aircraft according to claim 1, it is characterised in that: the rotation angle of the rotary shaft (5) is
90 °, so that the angle between small propeller (4) and wing (3) is converted between 0 ° and 90 °.
6. a kind of flap aircraft according to claim 1 or 2, it is characterised in that: the small propeller (4) uses two
Vane propeller.
7. a kind of flap aircraft according to claim 1 or 2, it is characterised in that: the wing (3) also has aileron,
Power-assisted is provided for the aerial steering of aircraft.
8. a kind of flap aircraft according to claim 1 or 2, it is characterised in that: the cockpit can also be lifted on fuselage
(1) lower section.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811274265.5A CN109250091A (en) | 2018-10-30 | 2018-10-30 | A kind of flap aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811274265.5A CN109250091A (en) | 2018-10-30 | 2018-10-30 | A kind of flap aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109250091A true CN109250091A (en) | 2019-01-22 |
Family
ID=65042889
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811274265.5A Withdrawn CN109250091A (en) | 2018-10-30 | 2018-10-30 | A kind of flap aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109250091A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112078789A (en) * | 2019-06-14 | 2020-12-15 | 陶德泉 | Hypersonic aircraft |
| CN114084344A (en) * | 2021-08-23 | 2022-02-25 | 上海新云彩航空科技有限责任公司 | Multi-shaft rotor aircraft with power wheel type undercarriage |
-
2018
- 2018-10-30 CN CN201811274265.5A patent/CN109250091A/en not_active Withdrawn
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112078789A (en) * | 2019-06-14 | 2020-12-15 | 陶德泉 | Hypersonic aircraft |
| CN112078789B (en) * | 2019-06-14 | 2024-04-09 | 陶德泉 | Hypersonic aircraft |
| CN114084344A (en) * | 2021-08-23 | 2022-02-25 | 上海新云彩航空科技有限责任公司 | Multi-shaft rotor aircraft with power wheel type undercarriage |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WW01 | Invention patent application withdrawn after publication | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20190122 |