CN109398691A - A kind of vertically taking off and landing flyer becoming flying angle - Google Patents
A kind of vertically taking off and landing flyer becoming flying angle Download PDFInfo
- Publication number
- CN109398691A CN109398691A CN201811635363.7A CN201811635363A CN109398691A CN 109398691 A CN109398691 A CN 109398691A CN 201811635363 A CN201811635363 A CN 201811635363A CN 109398691 A CN109398691 A CN 109398691A
- Authority
- CN
- China
- Prior art keywords
- wing
- motor
- propeller
- landing
- flying angle
- 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.)
- Withdrawn
Links
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
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/385—Variable incidence wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
Abstract
The present invention relates to a kind of vertically taking off and landing flyer for becoming flying angle, including including: preceding wing (1), wing (2) afterwards, preceding wing aileron (3), wing aileron (4) afterwards, fuselage (5), left front propeller one (6), left front propeller two (7), right front propeller one (8), right front propeller two (9), left back propeller one (10), left back propeller two (11), right rear screw shaft one (12), the right left front motor one (14) of rear screw shaft two (13), the left front right front motor one (16) of motor two (15), right front motor two (17), left back motor one (18), left back motor two (19), motor one (20) behind the right side, motor two (21) behind the right side, landing support frame (22).It is characterized in that, the preceding wing (1) propeller that wing (2) both ends are installed afterwards had not only been used as VTOL power, but also as horizontal flight direction power.The present invention can complete the aircraft of VTOL by becoming flying angle, thus allow aircraft can VTOL do not limited by place, and long endurance high-efficiency homework can be carried out, in addition from mechanical structure and it is practical manipulate it is more simple and convenient.
Description
Technical field
The present invention relates to vehicle technology field, specially a kind of vertically taking off and landing flyer for becoming flying angle.
Background technique
Traditional vertically taking off and landing flyer can both have been accomplished although the advantages of having merged fixed-wing and more rotors as more rotations
The same VTOL of the wing and spot hover, while again can the high-performance cruise as fixed-wing.But often conventional vertical landing flies
Row device needs more complicated flying power switching mechanism mostly.Such as increase the bar that hung down at fixed-wing wing both ends, hung down bar
Motor and rotor are installed in both ends, are equivalent to by fixed-wing in conjunction with more rotors, although taking its advantage, from taking off vertically and hang down
Land vertically fall on horizontal flight stateful switchover process it is relatively complicated, while biggish energy can be consumed, reduce cruising ability；Furthermore
By taking tilted propeller aircraft as an example, propeller is increased into inclining rotary mechanism, by change spiral propeller angle complete vertical lift with
The mode of horizontal flight.But due to increasing inclining rotary mechanism, aircraft own wt is increased, and structure is complicated.VTOL and water
Switching between the state of flat flight, the system that a set of complexity is also required in terms of manipulation are completed.How to simplify VTOL to fly
The mechanical structure of row device, so that the energy consumption that aircraft converts in flight and descent is reduced, while again convenient for manipulating,
It is the significant problem for needing to solve.
Summary of the invention
It is an object of the invention to a kind of aircraft that propose new construction, to complete by becoming flying angle VTOL.
Allow aircraft can VTOL do not limited by place, and long endurance high-efficiency homework can be carried out.And not equivalent to city
The design feature of most vertically taking off and landing flyer, it is only necessary to by from the change of flight angle of attack, it can reach conversion and hang down
The state of straight landing and horizontal flight.It is more simple and convenient from mechanical structure, with practical manipulation.
The technical solution of the invention is as follows:
The present invention provides a kind of vertically taking off and landing flyer for becoming flying angle, including fuselage, and is located at the fuselage rear and front end
Preceding wing and rear wing.
The preceding wing and rear wing include dynamical system motor, the propeller of integral body.Before motor is fixed on wing
Edge.
Landing support frame is respectively installed at the preceding wing and rear wing both ends, prevents aircraft during landing due to landing
Angle is excessive to injure propeller.
Respectively there are one group of rudder face in the preceding wing and rear wing two sides, and aircraft is controlled in aircraft level flight condition
Posture.
Preferably, the fuselage and preceding wing, rear wing are structure as a whole；
Preferably, the motor spacing is identical is set to preceding wing and rear leading edge of a wing position；
Preferably, the bottom of the fuselage is ellipse, reduces resistance under state of flight, while being also convenient for angle during landing
Transformation.
Compared with prior art, the beneficial effects of the present invention are:
1. adjusting the angle of the perpendicular or parallel ground level of propeller by the angle of attack of change of flight device itself, propeller has been subtracted
The switching of mechanism itself reaches the state turn for only needing a set of dynamical system that VTOL and horizontal high-speed flight can be completed.
2. solving the problems, such as that aircraft is big from high-altitude vertical landing process conversion energy loss, pass through turning for fuselage angle
Become, is landed using propeller under flat winged state, greatly speed up the high-altitude landing time, greatly reduce energy loss, improve indirectly
The cruising ability of aircraft.
3. since structure simply eliminates vertical starting power switching mechanism in same rank aircraft, to reduce fuselage
Weight greatly improves lifting capacity and cruising ability.
4. Design of Propeller is fixed on front and back leading edge of a wing two sides, since front and back wing can generate liter under flat winged state
Power, required horizontal drag force Relative vertical landing lift is smaller, to reduce the loss of kinetic energy under flat winged state again.
Detailed description of the invention
Fig. 1 is overall structure of the present invention；
Fig. 2 is side schematic view of the present invention in vertical flight；
Fig. 3 is top view of the present invention in vertical flight；
Side schematic view when Fig. 4 is flight horizontally forward of the invention；
Top view when Fig. 5 is flight horizontally forward of the invention；
Fig. 6 is landing state of the present invention downside schematic diagram
Wherein left front one 7- of propeller of wing aileron 5- fuselage 6- after wing aileron 4- before wing 3- after wing 2- before 1-
The left back left back propeller two of one 11- of propeller of right two 10- of front propeller of left front right one 9- of front propeller of two 8- of propeller
Right one 17- of front motor of left front two 16- of motor of left front one 15- of motor of right two 14- of rear screw shaft of right one 13- of rear screw shaft of 12-
Two 22- of motor plays descending branch after one 21- of motor is right after right left back two 20- of motor of left back one 19- of motor of two 18- of front motor is right
Support.
Specific embodiment
To be easy to understand the technical means, the creative features, the aims and the efficiencies achieved by the present invention, below with reference to
Attached drawing does further specific descriptions.
Landing flight course of the present invention, including following technical step:
(1) under the stationary state of ground, start propeller on the wing of front and back, propeller generates biggish drawing on wing preceding first
Power, propeller generates lesser pulling force on rear wing 2, and front fuselage can generate upward power at this time, before aircraft is adjusted to
When wing vertical is with ground afterwards, aircraft machine is in a kind of VTOL offline mode.Wing propeller increases pulling force after at this time, when
When propeller resultant force is greater than the weight of fuselage on the wing of front and back, it is achieved that and takes off vertically.
(2) when aircraft reaches ideal flying height, by adjusting preceding wing 1 and the motor pulling force on rear wing 2,
The change of flight angle of attack makes the front and back wing angle of attack, and when being gradually converted into parallel to ground, propeller generates horizontal pull.Aircraft to
Preceding flight is equal to pulling structure before traditional fixed-wing at this time.Wing-borne whole machine weight, front and back propeller is as horizontal pull
Power (Fig. 4).Under level flight condition, by wing aileron (3) before both ends, wing aileron (4) realizes that aircraft is each afterwards
The adjusting of kind direction posture.
(3) when aircraft lands, aircraft machine is in flat winged state at this time, by the pulling force of 2 motor of wing after reducing, this
Fragment position gradually slides behind opportunity, when make front and back electrical axis about vertically with ground when, the perpendicular state of flight of aircraft (figure
3) it is gradually reduced at this point, reducing motor pulling force fuselage by control, wing support frame (22) rear first contacts ground, due to fuselage
Lower end is that ellipse continues to reduce motor output valve, fuselage gradually stable landing.Become flying angle vertical landing to realize
Journey.
Claims (7)
1. it is a kind of become flying angle vertically taking off and landing flyer include: preceding wing (1), rear wing (2), preceding wing aileron (3), after
Spiral before wing aileron (4), fuselage (5), left front propeller one (6), left front propeller two (7), right front propeller one (8), the right side
Paddle two (9), left back propeller one (10), left back propeller two (11), right rear screw shaft one (12), right rear screw shaft two (13) are left
It is the right front motor one (16) of front motor one (14), left front motor two (15), right front motor two (17), left back motor one (18), left back
Motor two (19), it is right after motor one (20), it is right after motor two (21), landing support frame (22).
2. a kind of vertically taking off and landing flyer for becoming flying angle according to claim 1, it is characterised in that: the preceding wing
(1) parallel with rear wing (2) to be fixed on fuselage (5) rear and front end.
3. a kind of vertically taking off and landing flyer for becoming flying angle according to claim 1, it is characterised in that: the left front spiral
Paddle one (6), left front propeller two (7), right front propeller one (8), right front propeller two (9), left front motor one (14), left front electricity
The right front motor one (16) of machine two (15), right front motor two (17) are installed on preceding wing (1) leading edge locus.
4. a kind of vertically taking off and landing flyer for becoming flying angle according to claim 1, it is characterised in that: the left back spiral
The right rear screw shaft one (12) of paddle one (10), left back propeller two (11), right rear screw shaft two (13), left back motor one (18), a left side
Afterwards motor two (19), it is right after motor one (20), it is right after motor two (21), be installed on rear wing (2) leading edge locus.
5. a kind of vertically taking off and landing flyer for becoming flying angle according to claim 1, which is characterized in that the wing rudder face
Installation and preceding wing (1) and rear wing (2) wing outer end two sides.
6. a kind of vertically taking off and landing flyer for becoming flying angle according to claim 1, which is characterized in that the preceding wing
(1) propeller of wing (2) both ends installation had not only been used as VTOL power afterwards, but also as horizontal flight direction power.
7. a kind of vertically taking off and landing flyer for becoming flying angle according to claim 1, which is characterized in that the landing support
Frame (22) is installed on preceding wing (1) wing (2) two sides afterwards.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811635363.7A CN109398691A (en) | 2018-12-29 | 2018-12-29 | A kind of vertically taking off and landing flyer becoming flying angle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811635363.7A CN109398691A (en) | 2018-12-29 | 2018-12-29 | A kind of vertically taking off and landing flyer becoming flying angle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109398691A true CN109398691A (en) | 2019-03-01 |
Family
ID=65462653
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811635363.7A Withdrawn CN109398691A (en) | 2018-12-29 | 2018-12-29 | A kind of vertically taking off and landing flyer becoming flying angle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109398691A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111017205A (en) * | 2019-12-24 | 2020-04-17 | 中国航空工业集团公司西安飞机设计研究所 | Vertical take-off and landing conveyor |
| CN111846226A (en) * | 2020-07-28 | 2020-10-30 | 北京京东乾石科技有限公司 | Unmanned aerial vehicle and control method thereof |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105000179A (en) * | 2014-12-05 | 2015-10-28 | 上海交通大学 | Tiltrotor mixed multi-state aircraft |
| CN205440867U (en) * | 2015-12-30 | 2016-08-10 | 崔浩 | But tilting wing aircraft |
| CN106428550A (en) * | 2016-11-04 | 2017-02-22 | 山东萌萌哒航空科技有限公司 | Tilting type unmanned plane and flight control method thereof |
| CN107176297A (en) * | 2017-06-20 | 2017-09-19 | 北京迪鸥航空科技有限公司 | A kind of aircraft |
| CN107600403A (en) * | 2017-08-21 | 2018-01-19 | 西北工业大学 | A kind of trapezoidal layout tandem tilting wing aircraft and its inclining rotary mechanism |
| US20180086447A1 (en) * | 2016-09-08 | 2018-03-29 | Hop Flyt Inc | Aircraft having independently variable incidence channel wings with independently variable incidence channel canards |
| CN108791818A (en) * | 2018-07-16 | 2018-11-13 | 西安君晖航空科技有限公司 | A kind of novel tilting wing unmanned plane with variable-pitch propeller |
-
2018
- 2018-12-29 CN CN201811635363.7A patent/CN109398691A/en not_active Withdrawn
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105000179A (en) * | 2014-12-05 | 2015-10-28 | 上海交通大学 | Tiltrotor mixed multi-state aircraft |
| CN205440867U (en) * | 2015-12-30 | 2016-08-10 | 崔浩 | But tilting wing aircraft |
| US20180086447A1 (en) * | 2016-09-08 | 2018-03-29 | Hop Flyt Inc | Aircraft having independently variable incidence channel wings with independently variable incidence channel canards |
| CN106428550A (en) * | 2016-11-04 | 2017-02-22 | 山东萌萌哒航空科技有限公司 | Tilting type unmanned plane and flight control method thereof |
| CN107176297A (en) * | 2017-06-20 | 2017-09-19 | 北京迪鸥航空科技有限公司 | A kind of aircraft |
| CN107600403A (en) * | 2017-08-21 | 2018-01-19 | 西北工业大学 | A kind of trapezoidal layout tandem tilting wing aircraft and its inclining rotary mechanism |
| CN108791818A (en) * | 2018-07-16 | 2018-11-13 | 西安君晖航空科技有限公司 | A kind of novel tilting wing unmanned plane with variable-pitch propeller |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111017205A (en) * | 2019-12-24 | 2020-04-17 | 中国航空工业集团公司西安飞机设计研究所 | Vertical take-off and landing conveyor |
| CN111846226A (en) * | 2020-07-28 | 2020-10-30 | 北京京东乾石科技有限公司 | Unmanned aerial vehicle and control method thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106043685B (en) | Double vectors promote paddle rotor/fixed-wing combined type vertically taking off and landing flyer | |
| CN106585976B (en) | A kind of long endurance aircraft layout of tilting rotor/lift fan high speed | |
| CN103693194B (en) | One can be verted quadrotor | |
| WO2017016096A1 (en) | Novel vertical take-off and landing aircraft and control method therefor | |
| CN103287576A (en) | Tailless layout single tail seat type vertical take-off and landing aircraft | |
| WO2016184358A1 (en) | Fixed structure type vertical take-off and landing aircraft based on dual flying control systems and control method therefor | |
| CN204674831U (en) | Many fan arms aircraft | |
| CN103587683A (en) | Small-sized aircraft with tiltable rotor wings | |
| WO2013056492A1 (en) | Composite aircraft consisting of fixed-wing and electrically driven propellers and having helicopter functions | |
| CN106628162A (en) | Composite unmanned aerial vehicle | |
| CN101879945A (en) | Electric tilting rotor wing unmanned aerial vehicle | |
| CN203638093U (en) | Tiltable four-rotor aircraft | |
| CN204197290U (en) | A kind of novel tiltrotor aircraft | |
| CN112937849A (en) | Vertical take-off and landing aircraft with combined layout of tilting type propeller and fixed propeller | |
| CN105346715A (en) | Vertical take-off and landing unmanned plane | |
| CN106043684B (en) | A kind of connectible combined type aircraft of rotor wing | |
| CN105923154B (en) | Lap siding DCB Specimen fixed-wing combined type vertically taking off and landing flyer | |
| CN109398691A (en) | A kind of vertically taking off and landing flyer becoming flying angle | |
| CN206327567U (en) | A kind of compound unmanned vehicle | |
| CN103754360A (en) | Similar flying saucer type rotaplane | |
| CN206187340U (en) | Aircraft | |
| CN110228587A (en) | Pitch-varying system and unmanned aerial vehicle | |
| CN108382578A (en) | A kind of mixed at high speed layout vertically taking off and landing flyer | |
| CN103171758A (en) | Lift-rising method of flying wing type airplane | |
| CN112896499A (en) | Vertical take-off and landing aircraft with combined layout of tilting duct and fixed propeller |
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: 20190301 |