CN109263922A - A kind of rotatable aircraft of motor - Google Patents
A kind of rotatable aircraft of motor Download PDFInfo
- Publication number
- CN109263922A CN109263922A CN201811274167.1A CN201811274167A CN109263922A CN 109263922 A CN109263922 A CN 109263922A CN 201811274167 A CN201811274167 A CN 201811274167A CN 109263922 A CN109263922 A CN 109263922A
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- CN
- China
- Prior art keywords
- motor
- wing
- fuselage
- propeller
- aircraft
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- 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
- 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
- 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)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Toys (AREA)
Abstract
A kind of rotatable aircraft of motor, belongs to vehicle technology field, and in particular to a kind of rotatable aircraft of motor, including fuselage, wing, empennage, motor, propeller, bearing rod, fixed link and undercarriage；Wherein the fuselage interior is equipped with engine；The wing one is divided into the identical fin of the same function of two sizes, and two fins are symmetrically distributed on the fuselage；The empennage is in the tail portion of the fuselage；The motor is respectively distributed on wing there are four having altogether in symmetric figure, and the propeller is made of the identical fin of size, is respectively distributed on the motor；The bearing rod is divided into four connection wings and motor；The fixed link is connected and fixed wing；The undercarriage is mounted in wing lower part.The present invention can not only promote flight safety coefficient and the long period can maintain state of flight, can also carry out VTOL in any open area.
Description
Technical field
The present invention relates to vehicle technology field, more particularly to a kind of rotatable aircraft of motor.
Background technique
Traditional aircraft can be divided into fixed wing aircraft, helicopter and multi-rotor aerocraft.Wherein, fixed wing aircraft flies
Speed is fast, and mobility is high, and flying radius is big, and security performance coefficient is high, but due to the limitation of itself, wants to the condition taken off
Ask harsh, taking off for fixed wing aircraft must have sufficiently long runway.Helicopter can construct complexity with VTOL,
And it is larger for the culture of helicopter pilot consuming, height is required to the driving technology of driver, cannot be widely popularized.In recent years
Come, the development of multi-rotor unmanned aerial vehicle, so that aviation aircraft has other developing direction, it is not necessarily to runway, can be directly vertical
Lifting.But multi-rotor unmanned aerial vehicle because battery technology restriction, cause its can not flying for long time, and the flight of horizontal direction
Speed teaches fixed wing aircraft slower.
Therefore it provides a kind of novel aircraft, can allow aircraft that can take off vertically, flight safety coefficient is improved,
The problem of improving a kind of rotatable aircraft cruising ability of motor, being those skilled in the art's urgent need to resolve.
Summary of the invention
In view of this, flight safety coefficient can not only be promoted the present invention provides a kind of rotatable aircraft of motor
And the long period state of flight can be maintained, VTOL can also be carried out in any open area, due to a kind of motor
Rotatable aircraft does not need runway so saving the landing time, is coping with a kind of any required rotatable flight of motor
It can be improved efficiency to greatest extent when the task of device, each task is completed in guarantee in the shortest time.
To achieve the goals above, the present invention adopts the following technical scheme:
A kind of rotatable aircraft of motor, including fuselage, wing, empennage, motor, propeller, bearing rod, fixed link and rise and fall
Frame；Wherein the fuselage interior is equipped with engine；The wing one is divided into the identical fin of the same function of two sizes, and two
Fin is symmetrically distributed on the fuselage；The empennage is in the tail portion of the fuselage；There are four be distributed the motor respectively altogether
It is in symmetric figure on wing, the propeller is made of the identical fin of size, is respectively distributed on the motor；The bearing
Bar is divided into four connection wings and motor；The fixed link is connected and fixed wing；The undercarriage is mounted in wing lower part.
The present invention can not only promote flight safety coefficient and the long period can maintain state of flight, can be in office
Open area of anticipating carries out VTOL, since a kind of rotatable aircraft of motor does not need runway so when saving landing
Between, it can improve efficiency, guarantee to greatest extent in a kind of task of any required rotatable aircraft of motor of reply
Each task is completed in the shortest time.
Preferably, in a kind of above-mentioned rotatable aircraft of motor, the bearing rod can change in the horizontal direction
Become motor angle.
Preferably, in a kind of above-mentioned rotatable aircraft of motor, the diameter that the propeller is greater than the motor is long
Degree, enables the propeller by the motor maximizing the benefits, to enable the wing is the fastest to obtain lift, protects
Demonstrate,prove the high efficiency and stability of flight takeoff phase.
Preferably, in a kind of above-mentioned rotatable aircraft of motor, the wing is provided with part flow arrangement, so that a kind of
The rotatable aircraft air flowing of motor is quicker.
The present invention can not only promote flight safety coefficient and the long period can maintain state of flight, can be in office
Open area of anticipating carries out VTOL, since a kind of rotatable aircraft of motor does not need runway so when saving landing
Between, it can improve efficiency, guarantee to greatest extent in a kind of task of any required rotatable aircraft of motor of reply
Each task is completed in the shortest time.
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 structural schematic diagram of the invention.
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.
The embodiment of the invention discloses a kind of rotatable aircraft of motor, can not only be promoted flight safety coefficient and
Long period state of flight can be maintained, VTOL can also be carried out in any open area, since a kind of motor can revolve
The aircraft turned does not need runway so saving the landing time, in a kind of any required rotatable aircraft of motor of reply
It can be improved efficiency to greatest extent when task, each task is completed in guarantee in the shortest time.
A kind of rotatable aircraft of motor, including it is fuselage 1, wing 2, empennage 3, motor 4, propeller 5, bearing rod 6, solid
Fixed pole 7 and undercarriage 8；Engine is wherein housed inside the fuselage 1；The wing 2 is divided into the same function of two sizes
Identical fin, two fins are symmetrically distributed on the fuselage 1；The empennage 3 is in the tail portion of the fuselage 1；The motor 4
It is respectively distributed to there are four altogether in symmetric figure on wing 2, the propeller 5 is made of the identical fin of size, is distributed respectively
On the motor 4；The bearing rod 6 divides for four connection wings 2 and motor 4；The fixed link 7 is connected and fixed wing；Institute
Undercarriage 8 is stated mounted in 2 lower part of wing.
In order to further optimize the above technical scheme, in a kind of above-mentioned rotatable aircraft of motor, the axis
4 angle of motor can be changed in the horizontal direction by holding bar 6.
In order to further optimize the above technical scheme, it is preferred that described in a kind of above-mentioned rotatable aircraft of motor
Propeller 5 is greater than twice of diameter length of the motor 4, enables the propeller 5 by 4 maximizing the benefits of motor, from
And enable the wing 2 is the fastest to obtain lift, the high efficiency and stability of guarantee flight takeoff phase.
A kind of specific working mode of the rotatable aircraft of motor is:
Engine in takeoff opportunity body 1 is that motor 4 provides energy, the propeller 5 of fuselage 1 can be allowed to take the lead in work by motor 4
Make to go up to the air after the power to take off vertically is provided, 4 direction of motor is controlled by control bearing rod 6 in lift-off certain altitude.
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 (3)
1. a kind of rotatable aircraft of motor, which is characterized in that including fuselage (1), wing (2), empennage (3), motor (4),
Propeller (5), bearing rod (6), fixed link (7) and undercarriage (8)；Engine wherein is housed inside the fuselage (1)；The machine
The wing (2) one is divided into the identical fin of the same function of two sizes, and two fins are symmetrically distributed on the fuselage (1)；It is described
Tail portion of the empennage (3) in the fuselage (1)；The motor (4) is respectively distributed on wing (2) there are four having altogether in symmetric figure,
The propeller (5) is made of the identical fin of size, is respectively distributed on the motor (4)；The bearing rod (6) is divided into four
A connection wing (2) and motor (4)；The fixed link (7) is connected and fixed wing；The undercarriage (8) is mounted under wing (2)
Portion.
2. the rotatable aircraft of a kind of motor according to claim 1, it is characterised in that: the bearing rod (6)
Motor (4) angle can be changed in the horizontal direction.
3. the rotatable aircraft of a kind of motor according to claim 1 or 2, it is characterised in that: the propeller (5) is big
In twice of diameter length of the motor (4), make the propeller (5) can be by the motor (4) maximizing the benefits, to make
The wing (2) the fastest can obtain lift, guarantee the high efficiency and stability of flight takeoff phase.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811274167.1A CN109263922A (en) | 2018-10-30 | 2018-10-30 | A kind of rotatable aircraft of motor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811274167.1A CN109263922A (en) | 2018-10-30 | 2018-10-30 | A kind of rotatable aircraft of motor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109263922A true CN109263922A (en) | 2019-01-25 |
Family
ID=65194055
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811274167.1A Withdrawn CN109263922A (en) | 2018-10-30 | 2018-10-30 | A kind of rotatable aircraft of motor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109263922A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111268089A (en) * | 2019-11-22 | 2020-06-12 | 湖北航天飞行器研究所 | Double-fuselage vertical take-off and landing fixed wing unmanned aerial vehicle structure |
| CN111332465A (en) * | 2019-12-09 | 2020-06-26 | 湖北航天飞行器研究所 | Propeller and ducted fan combined type tilt rotor unmanned aerial vehicle and flight mode |
-
2018
- 2018-10-30 CN CN201811274167.1A patent/CN109263922A/en not_active Withdrawn
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111268089A (en) * | 2019-11-22 | 2020-06-12 | 湖北航天飞行器研究所 | Double-fuselage vertical take-off and landing fixed wing unmanned aerial vehicle structure |
| CN111268089B (en) * | 2019-11-22 | 2021-12-07 | 湖北航天飞行器研究所 | Double-fuselage vertical take-off and landing fixed wing unmanned aerial vehicle structure |
| CN111332465A (en) * | 2019-12-09 | 2020-06-26 | 湖北航天飞行器研究所 | Propeller and ducted fan combined type tilt rotor unmanned aerial vehicle and flight mode |
| CN111332465B (en) * | 2019-12-09 | 2022-01-21 | 湖北航天飞行器研究所 | Propeller and ducted fan combined type tilt rotor unmanned aerial vehicle and flight mode |
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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: 20190125 |