CN109250083A - Fixed-wing and more rotor integral type aircrafts - Google Patents
Fixed-wing and more rotor integral type aircrafts Download PDFInfo
- Publication number
- CN109250083A CN109250083A CN201811274484.3A CN201811274484A CN109250083A CN 109250083 A CN109250083 A CN 109250083A CN 201811274484 A CN201811274484 A CN 201811274484A CN 109250083 A CN109250083 A CN 109250083A
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- CN
- China
- Prior art keywords
- wing
- propeller
- fixed
- rotor
- fixed part
- 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
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
-
- 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
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/52—Tilting of rotor bodily relative to fuselage
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
The invention discloses fixed-wings and more rotor integral type aircrafts, including fuselage, wing, empennage, propeller, undercarriage；The propeller is equipped with multiple, and it is fixed on the two sides of the wing, rotor fixed part is provided at the top of the wing, the both ends of the rotor fixed part are in groove-like, the pedestal of the propeller is placed in the groove of rotor fixed part end, and it is hinged with the groove inner wall of the rotor fixed part, device of rotation driving is arranged close to the end of the propeller in the rotor fixed part, swing rod is fixedly connected on the device of rotation driving, the other end articulated linkage of the swing rod, the other end of the connecting rod and the pedestal of the propeller are hinged；The fuselage interior is equipped with cockpit, and control panel is equipped in the cockpit, and processor is arranged in the control panel.Taking off without relying on long runway in the present invention, and horizontal flight speed is fast.
Description
Technical field
The present invention relates to vehicle technology fields, more particularly to fixed-wing and more rotor integral type aircrafts.
Background technique
There are fixed-wing and more rotors in the common aircraft of aviation field, wherein fixed-wing is pushed by engine, and engine drives
The raw horizontal thrust for being parallel to fuselage axis of movable property, allows fixed-wing high-speed flight in the sky.But since engine cannot produce
The raw lift perpendicular to fuselage axis, so fixed-wing can only obtain lift by the relative motion between fixed-wing and air,
To overcome the gravity of fixed-wing.However, there is two disadvantages for fixed-wing in the prior art: first, it is needed when taking off longer
Runway so that fixed-wing is obtained enough horizontal velocities so that fixed-wing obtains enough lift and takes off；Second, fixed-wing
It needs to keep enough flying speeds that could obtain enough lift to overcome the gravity of itself after take off.
More rotors make the propeller of more rotors around own axes rotation by engine, when more rotors pass through propeller rotation with
Air generates relative motion and obtains lift.Since the lift that more rotors generate directly transfers generation by engine driving propeller certainly,
Therefore more rotors take off without relying on compared with long runway.But since mainly lift, the multi-rotor unmanned aerial vehicle that more rotors provide obtain
The horizontal thrust for being parallel to fuselage axis obtained is smaller, so horizontal flight speed is slower.
Also, existing aircraft does not solve the problems of above-mentioned.
Therefore, one kind is developed without relying on long runway, and the fireballing aircraft of horizontal flight, is those skilled in the art
The problem of urgent need to resolve.
Summary of the invention
In view of this, being not necessarily to rely on long runway the present invention provides one kind, without being always maintained at enough flight after taking off
Speed, and the fast fixed-wing of horizontal flight fast speed and more rotor integral type aircrafts.
To achieve the goals above, the present invention adopts the following technical scheme:
Fixed-wing and more rotor integral type aircrafts, including fuselage, wing, empennage, propeller, undercarriage；The wing is fixed on
The two sides of the fuselage, the empennage are fixed on the tail portion of the fuselage, and the propeller is equipped with multiple, and are fixed on the machine
The two sides of the wing, the undercarriage are fixed on the pedestal of the fuselage；Rotor fixed part, the rotation are provided at the top of the wing
The both ends of wing fixed part are in groove-like, and the pedestal of the propeller is placed in the groove of rotor fixed part end, and with institute
The groove inner wall for stating rotor fixed part is hinged, and the rotor fixed part is filled close to the end of propeller setting rotate driving
Set, be fixedly connected with swing rod on the device of rotation driving, the other end articulated linkage of the swing rod, the other end of the connecting rod with
The pedestal of the propeller is hinged, the spiral by bottom internal and device of rotation driving inside be equipped with motor；It is described
Fuselage interior is equipped with cockpit, and control panel is equipped in the cockpit, and processor, the processor is arranged in the control panel
It is electrically connected with the control panel, the processor is electrically connected with the motor, device of rotation driving.
For above content, multiple propellers of connection in the present invention on fixed-wing, when taking off, propeller be can rotate
Increase the lift taken off, be vertically moved up or down aircraft, aircraft is made to take off when taking off without that can realize compared with long runway,
When carrying out normal flight after aircraft lift-off, propeller-driven aircraft flight can make the speed of flight lower, device of rotation driving
It will drive the swing of swing rod, swing rod drives link motion, and then rotates propeller in groove, when the inclination of propeller
When angle is identical as the tilt angle of wing, propeller can stop operating, and aircraft is made to fly by fixed-wing, improve flight
Speed.
Preferably, propelling screws are arranged in the head position of the fuselage.It can be improved under the action of propelling screws
The speed of aircraft flight forward.
Preferably, the propeller is uniformly arranged in the two sides of the wing, and the radian at the top of the rotor fixed part
It is identical as the radian of the wing.When propeller is not run, aircraft flies by wing, rotor fixed part radian and wing
Radian is identical, and aircraft can be made only stability when airfoil flight to be leaned on not influenced by wing tip portion rotor fixed part.
Preferably, telescopic rod is arranged in the top of the propeller mount, and the telescopic rod is slidably connected with the pedestal.Fly
Machine flight stability rear screw shaft can stop operating, and be tilted a certain angle, and make angle phase of the tilt angle of propeller with wing
Together, and at this time the pars contractilis of propeller is retracted to the inside of pedestal, reduces influence of the height to aircraft flight of propeller, into
And the fixed wing of aircraft is made to can be used alone or be used in conjunction with spiral.
Preferably, retractable driving device, the retractable driving device and the chassis interior are set in the telescopic rod
Motor electrical connection, and be electrically connected with the processor.Retractable driving device can drive telescopic rod to carry out flexible fortune in chassis interior
It is dynamic.
Preferably, the groove of rotor fixed part end is in " U " font.One side opening of propeller rotation, open side
It can be convenient propeller to be rotated in groove, propeller and inside grooves avoided to generate collision.
Preferably, the device of rotation driving is fixed on the inside grooves on the inner wall of the wing side.This
Push-and-pull of the connecting rod to propeller is convenient in the setting of sample, and propeller is made to be easier to rotate in inside grooves.
Beneficial effects of the present invention:
(1) aircraft in the present invention is fixed-wing, more rotor integral type aircrafts, and multiple propellers are total during taking off
Same-action allows aircraft to take off vertically, without compared with long runway；(2) aircraft propeller in flight course can tilt to
The identical position of taper, propeller stop operating only through fixed airfoil flight, can make aircraft rapid flight.
Detailed description of the invention
In order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, to embodiment or will show below
There is attached drawing needed in technical description to be briefly described, it should be apparent that, the accompanying drawings in the following description is only this
The embodiment of invention for those of ordinary skill in the art without creative efforts, can also basis
The attached drawing of offer obtains other attached drawings.
Fig. 1 attached drawing is the overall structure diagram of aircraft provided by the invention.
Fig. 2 attached drawing is the attachment structure schematic diagram of propeller provided by the invention and device of rotation driving.
Wherein, in figure,
1- fuselage；11- cockpit；2- wing；3- empennage；4- propeller；41- pedestal；42- pars contractilis；5- rotor fixed part；
51- device of rotation driving；52- swing rod；53- connecting rod；6- undercarriage；7- propelling screws.
Specific embodiment
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation description, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts every other
Embodiment shall fall within the protection scope of the present invention.
As shown in Figs. 1-2, the embodiment of the invention discloses fixed-wings and more rotor integral type aircrafts, including fuselage 1, wing
2, empennage 3, propeller 4, undercarriage 6；Wing 2 is fixed on the two sides of fuselage 1, and empennage 3 is fixed on the tail portion of fuselage 1, propeller 4
Equipped with two sides that are multiple, and being fixed on wing 2, undercarriage 6 is fixed on the bottom of fuselage 1；It is solid that the top of wing 2 is provided with rotor
Determine portion 5, the both ends of rotor fixed part 5 are in groove-like, and the pedestal of propeller 4 is placed in the groove of 5 end of rotor fixed part, and with
The groove inner wall of rotor fixed part 5 is hinged, and device of rotation driving 51 is arranged close to the end of propeller 4 in rotor fixed part 5, turns
Swing rod 52, the other end articulated linkage 53 of swing rod 52, the other end and propeller 4 of connecting rod 53 are fixedly connected in dynamic driving device 51
Pedestal 41 it is hinged, be equipped with motor inside the bottom inner seat 41 and device of rotation driving 51 of propeller 4；It is set inside fuselage 1
There is cockpit 11, control panel is equipped in cockpit 11, processor is arranged in control panel, and processor is electrically connected with control panel,
Processor is electrically connected with motor, device of rotation driving 51.
For above content, the control panel in the present invention in cockpit 11, which can control, to be taken off, and 4 turns of propeller
Dynamic, the operation of wing 2 and 4 free switching of propeller makes aircraft that can both fly by multiple propellers 4, can also be only
It is flown by fixed wing 2.When only needing wing 2 to carry out flight, propeller 4 can be tilted to and rotor fixed part 5
The identical angle in end, makes propeller 4 stop operating, and carries out the speed that the flight of aircraft can be improved in flight using wing 2, into
And realize the mutual conversion of aircraft fixed wing 2 and propeller 4.
As shown in Figure 1, propelling screws 7 are arranged in the head position of middle fuselage 1 of the present invention.Propelling screws 7 can be winged
Machine provides forward power and lift.
Further, propeller 4 is uniformly arranged in the two sides of wing 2, and the radian and wing 2 at 5 top of rotor fixed part
Radian it is identical.Propeller 4 is equipped with two rows, and the rotation direction of two rows of propellers 4 is on the contrary, propeller 4 is solid with rotor after tilting
The tilt angle for determining 5 end of portion is identical, and identical as the tilt angle of wing 2, can reduce propeller 4 and rotor fixed part 5
Influence to wing 2 reduces the influence to aircraft flight speed.
Further, telescopic rod 42 is arranged in the top of 4 pedestal 41 of propeller, and telescopic rod 42 is slidably connected with pedestal 41.
Further, retractable driving device is set in telescopic rod 42, the motor electricity inside retractable driving device and pedestal 41
Connection, and be electrically connected with processor.Retractable driving device moves under the control of a processor, drives telescopic rod 42 into pedestal 41
Portion is shunk, and the blade of propeller 4 is made to be close to rotor fixed part, is reduced propeller 4 to the influence in 2 flight course of wing, is made to fly
Machine steadily can quickly fly.
Further, the groove of 5 end of rotor fixed part is in " U " font.
Further, device of rotation driving 51 is fixed on inside grooves on the inner wall of 2 side of wing.Rotate driving dress
51 middle positions for being placed in inside grooves are set, connecting rod 52 can be made more accurately to drive the pedestal 41 of propeller 4, make propeller 4
What is rotated is more accurate.
The course of work:
Control panel in cockpit 11 is electrically connected with processor, and motor is arranged in the inside of control panel, is control panel and place
It manages device and electric energy is provided, driver operates control panel, and then controls the operation of aircraft, when aircraft has needed aircraft, spiral shell
Motor inside rotation 4 pedestal 41 of paddle is that propeller 4 provides power, and propeller 4 rotates, the motor and processor inside propeller 4
Electrical connection, processor can control the rotation or stopping of propeller 4, can take off when aircraft goes up to the air without runway；Fuselage 1 simultaneously
The propelling screws 7 of front end, or the flight of aircraft provides the power and lift that advance, and processor equally can control
The rotation of propelling screws 4；After aircraft flight is steady, in order to improve the flying speed of aircraft, propeller 4 can be closed only
It is flown using wing 2, manipulates control panel, processor can control the rotation of device of rotation driving 51, device of rotation driving 51
It will drive the swing of swing rod 52, swing rod 52 drives the movement of connecting rod 53, and connecting rod 53 pushes the pedestal 41 of propeller 4, makes propeller 4
Inclination, finally makes the tilt angle of propeller 4 identical as the tilt angle of 5 end of rotor fixed part, then processor can control
Propeller 4 stops operating, and when propeller 4 is not after rotation, processor controls retractable driving device movement, retractable driving device meeting
Internal contraction of the telescopic rod 42 to pedestal 41 is driven, the height of 4 blade of propeller is reduced, so that blade is close to rotor fixed part 5, makes
Aircraft only passes through wing 2 and flies；When aircraft needs to decline, propeller 4 is made to restore original position under the control of a processor
It sets, and is rotated, and then make aircraft can be with vertical landing.
Each embodiment in this specification is described in a progressive manner, the highlights of each of the examples are with other
The difference of embodiment, the same or similar parts in each embodiment may refer to each other.
The foregoing description of the disclosed embodiments enables those skilled in the art to implement or use the present invention.
Various modifications to these embodiments will be readily apparent to those skilled in the art, as defined herein
General Principle can be realized in other embodiments without departing from the spirit or scope of the present invention.Therefore, of the invention
It is not intended to be limited to the embodiments shown herein, and is to fit to and the principles and novel features disclosed herein phase one
The widest scope of cause.
Claims (7)
1. fixed-wing and more rotor integral type aircrafts, which is characterized in that including fuselage (1), wing (2), empennage (3), propeller
(4), undercarriage (6)；The wing (2) is fixed on the two sides of the fuselage (1), and the empennage (3) is fixed on the fuselage (1)
Tail portion, the propeller (4) is equipped with multiple, and is fixed on the two sides of the wing (2), the undercarriage (6) is fixed on institute
State the bottom of fuselage (1)；
It is provided with rotor fixed part (5) at the top of the wing (2), the both ends of the rotor fixed part (5) are in groove-like, described
The pedestal (41) of propeller (4) is placed in the groove of rotor fixed part (5) end, and with the rotor fixed part (5)
Groove inner wall is hinged, and device of rotation driving (51) are arranged close to the end of the propeller (4) in the rotor fixed part (5),
Swing rod (52) are connected on the device of rotation driving (51), the other end articulated linkage (53) of the swing rod (52), the connecting rod
(53) hingedly, the pedestal (41) of the propeller (4) is internal and rotates for the pedestal (41) of the other end and the propeller (4)
Motor is equipped with inside driving device (51)；
Cockpit (11) are equipped with inside the fuselage (1), are equipped with control panel in the cockpit (11), in the control panel
Processor is arranged in portion, and the processor is electrically connected with the control panel, the processor and the motor, device of rotation driving
(51) it is electrically connected.
2. fixed-wing according to claim 1 and more rotor integral type aircrafts, which is characterized in that the fuselage (1)
Propelling screws (7) are arranged in head position.
3. fixed-wing according to claim 1 and more rotor integral type aircrafts, which is characterized in that the propeller (4)
It uniformly arranges in the two sides of the wing (2), and the radian of the radian at the top of the rotor fixed part (5) and the wing (2)
It is identical.
4. fixed-wing according to claim 3 and more rotor integral type aircrafts, which is characterized in that the propeller (4)
Telescopic rod (42) are arranged in the top of pedestal (41), and the telescopic rod (42) is slidably connected with the pedestal (41).
5. fixed-wing according to claim 4 and more rotor integral type aircrafts, which is characterized in that the telescopic rod (42)
Interior setting retractable driving device, the internal motor of the retractable driving device and the pedestal (41) are electrically connected, and with the place
Manage device electrical connection.
6. fixed-wing according to claim 1 and more rotor integral type aircrafts, which is characterized in that the rotor fixed part
(5) groove of end is in " U " font.
7. fixed-wing according to claim 6 and more rotor integral type aircrafts, which is characterized in that the rotate driving dress
It sets (51) and is fixed on the inside grooves on the inner wall of the wing (2) side.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811274484.3A CN109250083A (en) | 2018-10-30 | 2018-10-30 | Fixed-wing and more rotor integral type aircrafts |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811274484.3A CN109250083A (en) | 2018-10-30 | 2018-10-30 | Fixed-wing and more rotor integral type aircrafts |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109250083A true CN109250083A (en) | 2019-01-22 |
Family
ID=65042892
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811274484.3A Withdrawn CN109250083A (en) | 2018-10-30 | 2018-10-30 | Fixed-wing and more rotor integral type aircrafts |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109250083A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111498102A (en) * | 2020-04-20 | 2020-08-07 | 飞的科技有限公司 | Aircraft with a flight control device |
-
2018
- 2018-10-30 CN CN201811274484.3A patent/CN109250083A/en not_active Withdrawn
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111498102A (en) * | 2020-04-20 | 2020-08-07 | 飞的科技有限公司 | Aircraft with a flight control device |
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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 |
Application publication date: 20190122 |
|
| WW01 | Invention patent application withdrawn after publication |