CN206511122U - A kind of VTOL Fixed Wing AirVehicle - Google Patents
A kind of VTOL Fixed Wing AirVehicle Download PDFInfo
- Publication number
- CN206511122U CN206511122U CN201720130129.3U CN201720130129U CN206511122U CN 206511122 U CN206511122 U CN 206511122U CN 201720130129 U CN201720130129 U CN 201720130129U CN 206511122 U CN206511122 U CN 206511122U
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- Prior art keywords
- wing
- rotor
- vertical fin
- vertical
- fuselage
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Classifications
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- 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
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The utility model is related to aircraft field, disclose a kind of VTOL Fixed Wing AirVehicle, including fuselage, the wing symmetrical with respect to fuselage, and it is vertical with wing line, it is provided with rotor on the vertical fin symmetrical with respect to fuselage, wing and vertical fin, and the rotor at least on vertical fin is independently rotated.The utility model has the advantage of fixed-wing and helicopter flight device concurrently, both VTOL can be realized, reduce the requirement to place, the larger lifting while its speed, voyage and lifting capacity have been got back, in addition, the inclination that the utility model passes through integral body carries out the switching of offline mode, has that technical difficulty is low, simple in construction, stability is good and simple operation and other advantages compared to tiltrotor aircraft.
Description
Technical field
The utility model is related to aircraft field, more particularly, to a kind of Fixed Wing AirVehicle.
Background technology
Common standard aircraft is divided into Fixed Wing AirVehicle and the major class of helicopter flight device two, wherein Fixed Wing AirVehicle
With speed is fast, voyage is remote, load-carrying is big, efficiency high, but compared to landing site is required for helicopter flight device it is high, it is necessary to
Suitable plane track；Conversely, helicopter flight device can realize VTOL, the requirement to landing site is low, but goes straight up to
Machine aircraft also has the shortcomings that flying speed is slow, voyage is short.Based on this, also there is a kind of tilting rotor flight in the prior art
Device, its rotor is set when taking off according to the rotor structure of helicopter flight device, realizes the vertical landing of aircraft, awing
Rotor rotational, is set, tiltrotor aircraft has merged fixed-wing and helicopter according to the rotor structure of Fixed Wing AirVehicle
Feature, has the advantages that VTOL, speed are fast, voyage is remote, load-carrying is big, however also have simultaneously technical difficulty it is high, complicated,
The defects such as stability is poor, control and complex operation.
Utility model content
In order to overcome the deficiencies in the prior art, the utility model provides a kind of VTOL Fixed Wing AirVehicle.
The utility model solves the technical scheme that its technical problem used：
A kind of VTOL Fixed Wing AirVehicle, including fuselage, the wing symmetrical with respect to fuselage, and connect with wing
Line is vertical, the vertical fin symmetrical with respect to fuselage, and wing is with being provided with rotor on vertical fin, and the rotor at least on vertical fin is independent
Rotate.
As the further improved procedure of such scheme, the flight step of aircraft includes vertical takeoff stage, rank of taking off
Cruising phase, cruising phase rear body before the cruise of section rear-inclined flight before adjusting stage, cruise after the adjusting stage is inclined
The vertical drop stage before landing preceding adjusting stage and landing after the adjusting stage.
As the further improved procedure of such scheme, in takeoff phase and landing phases, fuselage divides vertically with rotor
Cloth.
As the further improved procedure of such scheme, before cruise in the adjusting stage, the rotor on vertical fin is not with
Same rotational speed.
It is synchronized positioned at wing and rotor on vertical fin in cruising phase as the further improved procedure of such scheme
Rotating speed.
It is used as the further improved procedure of such scheme, including the undercarriage located at wing Yu vertical fin lower end.
It is used as the further improved procedure of such scheme, including the aileron on wing, and the side on vertical fin
To rudder.
As the further improved procedure of such scheme, the length for being shorter in length than wing of vertical fin, the rotor on vertical fin is set
The middle part of correspondence wing is located in the rotor on the end of correspondence vertical fin, wing.
The beneficial effects of the utility model are：
The utility model has the advantage of fixed-wing and helicopter flight device concurrently, can both realize VTOL, reduces to field
The requirement on ground, the larger lifting while its speed, voyage and lifting capacity have been got back, in addition, the utility model passes through entirety
The inclination of fuselage carries out the switching of offline mode, has technical difficulty low, simple in construction, stably compared to tiltrotor aircraft
Property good and simple operation and other advantages.
Brief description of the drawings
The utility model is further illustrated with reference to the accompanying drawings and examples.
Fig. 1 is the schematic perspective view of the utility model one embodiment；
Fig. 2 is the front view of the utility model one embodiment；
Fig. 3 is the top view of the utility model one embodiment；
Fig. 4 is the flight path figure of the utility model aircraft.
Embodiment
The technique effect of design of the present utility model, concrete structure and generation is carried out below with reference to embodiment and accompanying drawing
Clear, complete description, to be completely understood by the purpose of this utility model, scheme and effect.It should be noted that not conflicting
In the case of, the feature in embodiment and embodiment in the application can be mutually combined.
It should be noted that unless otherwise specified, be referred to as " fixing " when a certain feature, " connection " in another feature,
It can directly fix, be connected in another feature, can also indirectly fix, be connected in another feature.In addition, this
The description such as upper and lower, left and right used in utility model is only the phase relative to each part of the utility model in accompanying drawing
For mutual position relationship.
In addition, unless otherwise defined, the technology of all of technologies and scientific terms used here by the article and the art
The implication that personnel are generally understood that is identical.Term used in the description is intended merely to describe specific embodiment herein, without
It is to limit the present invention.Term as used herein " and/or " include the arbitrary of one or more related Listed Items
Combination.
Referring to figs. 1 to Fig. 3, the schematic perspective view, front view and vertical view of the utility model one embodiment are respectively illustrated
Figure, as illustrated, aircraft includes fuselage 100, wing 210, aileron 220, vertical fin 310, rudder 320, rotor 410, motor
420th, undercarriage 500 and steering wheel 600.
Specifically, wing 210 is symmetrical with respect to fuselage 100, the same relative fuselage 100 of vertical fin 310 is symmetrical, and its
Line is vertical with the line of wing 210, i.e., fuselage 100, wing 210 and vertical fin 310 as shown in Figure 1, Figure 2 shown in form cross knot
Structure.The length of vertical fin 310 is preferably shorter than the length of wing 210, the bigger wing 210 of wing body area mainly for generation of lift,
Vertical fin 310 is then mainly used in realizing the pose adjustment of fuselage.
Rotor 410 is driven by motor 420, one end connection rotor 410 of motor 420, other end connection in the present embodiment
Undercarriage 500, more specifically motor 420 are fixed on wing 210 or vertical fin 310, and rotor 410 is located at wing 210 or hung down
The upper end of tail 310, undercarriage 500 is located at the lower end of wing 210 or vertical fin 310（As shown in Figure 3）, fuselage 100 and motor 420
It is preferred to use streamlined structure, to reduce air drag.
As a kind of preferred embodiment of rotor distributing position, the rotor 410 on vertical fin 310 is located at correspondence vertical fin 310
End, the rotor 410 on wing 210 is located at the middle part of correspondence wing 210.
Rotor 410 in the present embodiment on vertical fin 310 can be independent rotation, as between the rotor 410 on wing 210
Independent rotation whether is needed, can be adjusted according to the actual requirements.
Aileron 220 is on wing 210, and rudder 320 is on vertical fin 310, and aileron 220 is with rudder 320 corresponding
Steering wheel 600 driving lower swing, to adjust the heading of aircraft.
Reference picture 4, shows the flight path figure of the utility model aircraft, as illustrated, the flight step of aircraft
Cruise rank before the cruise flown including vertical takeoff stage, takeoff phase rear-inclined before adjusting stage, cruise after the adjusting stage
Section, the vertical drop stage before the inclined landing of cruising phase rear body before adjusting stage and landing after the adjusting stage, below
Each stage is specifically described：
First, the vertical takeoff stage
Before takeoff phase, aircraft being placed on and take off in plane vertically by undercarriage, fuselage divides vertically with rotor
Cloth.With the driving of motor, rotor provides the lift of vertical direction, so as to drive aircraft vertical with the rotor mode of cross four
Take off.
2nd, the adjusting stage before cruising
After taking off, rotor on vertical fin is with different rotational speeds, because the lift that rotor is provided at two is different, therefore
Fuselage is gradually tilted towards the less side vertical fin of lift, and now wing has an angle for being less than 90 degree with horizontal plane（Meet
Angle）, the angle of attack is larger when initial, and lift coefficient is smaller, and wing can only produce certain lift.With further flying for aircraft
OK, fuselage posture is more tilted, and the angle of attack diminishes close to critical value, and the lift that wing is produced is stepped up.
3rd, cruising phase
When the flying speed of aircraft reaches a certain setting value, while when keeping certain angle of attack, aircraft is by cross
Four rotor modes switch to fixed-wing offline mode, and now wing is rotated at the same speed with the rotor on vertical fin, while aileron and direction
Rudder starts control aircraft, it is preferred that fuselage in cruising phase and rotor are along horizontal distribution.
4th, the adjusting stage before landing
When aircraft prepares to land, aircraft is set to be in the heeling condition risen by aileron, the angle of attack is incrementally increased,
Until aircraft is in vertical climb mode.
5th, the vertical drop stage
After aircraft is in the state vertically climbed, aileron is stopped with rudder, by controlling rotor rotating speed
Mode operates aircraft, and aircraft is hung down from fixed-wing pattern switching into the rotor mode of cross four with the rotor mode of cross four
Land vertically.
The utility model has the advantage of fixed-wing and helicopter flight device concurrently, can both realize VTOL, reduces to field
The requirement on ground, the larger lifting while its speed, voyage and lifting capacity have been got back, in addition, the utility model passes through entirety
The inclination of fuselage carries out the switching of offline mode, has technical difficulty low, simple in construction, stably compared to tiltrotor aircraft
Property good and simple operation and other advantages.
Above is preferable implementation of the present utility model is illustrated, but the invention is not limited to the reality
Example is applied, those skilled in the art can also make a variety of equivalent variations on the premise of without prejudice to the utility model spirit
Or replace, these equivalent deformations or replacement are all contained in the application claim limited range.
Claims (8)
1. a kind of VTOL Fixed Wing AirVehicle, it is characterised in that including fuselage, the symmetrical machine of relatively described fuselage
The wing, and, relatively described fuselage symmetrical vertical fin vertical with the wing line, the wing on the vertical fin with being all provided with
The rotor being equipped with rotor, and at least described vertical fin is independently rotated.
2. VTOL Fixed Wing AirVehicle according to claim 1, it is characterised in that the flight step of the aircraft
Cruise rank before the cruise flown including vertical takeoff stage, takeoff phase rear-inclined before adjusting stage, cruise after the adjusting stage
Section, the vertical drop stage before the inclined landing of cruising phase rear body before adjusting stage and landing after the adjusting stage.
3. VTOL Fixed Wing AirVehicle according to claim 2, it is characterised in that in the takeoff phase and landing
In stage, the fuselage is distributed vertically with rotor.
4. VTOL Fixed Wing AirVehicle according to claim 2, it is characterised in that the adjusting stage before the cruise
In, the rotor on the vertical fin is with different rotational speeds.
5. VTOL Fixed Wing AirVehicle according to claim 2, it is characterised in that in the cruising phase, position
Rotated at the same speed with the rotor on vertical fin in the wing.
6. VTOL Fixed Wing AirVehicle according to any one of claim 1 to 3, it is characterised in that including located at
The wing and the undercarriage of the vertical fin lower end.
7. VTOL Fixed Wing AirVehicle according to any one of claim 1 to 3, it is characterised in that including located at
Aileron on the wing, and the rudder on the vertical fin.
8. VTOL Fixed Wing AirVehicle according to any one of claim 1 to 3, it is characterised in that the vertical fin
The length for being shorter in length than the wing, the rotor on the vertical fin is located on the end of correspondence vertical fin, the wing
The rotor is located at the middle part of correspondence wing.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720130129.3U CN206511122U (en) | 2017-02-13 | 2017-02-13 | A kind of VTOL Fixed Wing AirVehicle |
| PCT/CN2017/079204 WO2018145355A1 (en) | 2017-02-13 | 2017-04-01 | Vertical take-off and landing aircraft having fixed wings |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720130129.3U CN206511122U (en) | 2017-02-13 | 2017-02-13 | A kind of VTOL Fixed Wing AirVehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206511122U true CN206511122U (en) | 2017-09-22 |
Family
ID=59867587
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720130129.3U Active CN206511122U (en) | 2017-02-13 | 2017-02-13 | A kind of VTOL Fixed Wing AirVehicle |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN206511122U (en) |
| WO (1) | WO2018145355A1 (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108284950A (en) * | 2017-11-30 | 2018-07-17 | 湖北航天飞行器研究所 | Four shrouded propeller power modes can VTOL fixed-wing unmanned vehicle |
| CN108583869A (en) * | 2018-06-15 | 2018-09-28 | 西安航空学院 | A kind of X-shaped swept-back wing unmanned plane |
| CN109159890A (en) * | 2018-10-29 | 2019-01-08 | 拓攻（南京）机器人有限公司 | A kind of single rotor vertically taking off and landing flyer |
| CN110356553A (en) * | 2019-08-29 | 2019-10-22 | 吕福瑞 | A kind of wheel rotor aircraft |
| CN110562433A (en) * | 2019-09-16 | 2019-12-13 | 北京理工大学珠海学院 | X wing unmanned aerial vehicle |
| CN110683030A (en) * | 2019-10-25 | 2020-01-14 | 中国航空工业集团公司西安飞行自动控制研究所 | Unmanned aerial vehicle capable of taking off and landing vertically |
| CN111566008A (en) * | 2017-12-12 | 2020-08-21 | 卡梅伦·斯潘塞 | Variable geometry vertical take-off and landing (VTOL) aircraft system |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5516060A (en) * | 1993-03-29 | 1996-05-14 | Mcdonnell; William R. | Vertical take off and landing and horizontal flight aircraft |
| SG188691A1 (en) * | 2011-09-27 | 2013-04-30 | Singapore Tech Aerospace Ltd | An unmanned aerial vehicle |
| CN105329441B (en) * | 2015-11-30 | 2018-07-10 | 保定维特瑞交通设施工程有限责任公司 | A kind of four axis all-wing aircraft aircraft of combined type |
| CN106143898B (en) * | 2016-08-08 | 2018-07-10 | 北京奇正数元科技股份有限公司 | A kind of VTOL tilting rotor fixed wing aircraft |
-
2017
- 2017-02-13 CN CN201720130129.3U patent/CN206511122U/en active Active
- 2017-04-01 WO PCT/CN2017/079204 patent/WO2018145355A1/en active Application Filing
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108284950A (en) * | 2017-11-30 | 2018-07-17 | 湖北航天飞行器研究所 | Four shrouded propeller power modes can VTOL fixed-wing unmanned vehicle |
| CN111566008A (en) * | 2017-12-12 | 2020-08-21 | 卡梅伦·斯潘塞 | Variable geometry vertical take-off and landing (VTOL) aircraft system |
| CN108583869A (en) * | 2018-06-15 | 2018-09-28 | 西安航空学院 | A kind of X-shaped swept-back wing unmanned plane |
| CN108583869B (en) * | 2018-06-15 | 2024-03-29 | 西安航空学院 | X-shaped sweepback wing unmanned aerial vehicle |
| CN109159890A (en) * | 2018-10-29 | 2019-01-08 | 拓攻（南京）机器人有限公司 | A kind of single rotor vertically taking off and landing flyer |
| CN109159890B (en) * | 2018-10-29 | 2023-06-09 | 南京拓兴智控科技有限公司 | Single rotor vertical take-off and landing aircraft |
| CN110356553A (en) * | 2019-08-29 | 2019-10-22 | 吕福瑞 | A kind of wheel rotor aircraft |
| CN110356553B (en) * | 2019-08-29 | 2023-06-20 | 吕福瑞 | Full rotor craft |
| CN110562433A (en) * | 2019-09-16 | 2019-12-13 | 北京理工大学珠海学院 | X wing unmanned aerial vehicle |
| CN110683030A (en) * | 2019-10-25 | 2020-01-14 | 中国航空工业集团公司西安飞行自动控制研究所 | Unmanned aerial vehicle capable of taking off and landing vertically |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2018145355A1 (en) | 2018-08-16 |
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