CN206417197U - A kind of tandem wing vertically mixes landing aircraft - Google Patents
A kind of tandem wing vertically mixes landing aircraft Download PDFInfo
- Publication number
- CN206417197U CN206417197U CN201720065927.2U CN201720065927U CN206417197U CN 206417197 U CN206417197 U CN 206417197U CN 201720065927 U CN201720065927 U CN 201720065927U CN 206417197 U CN206417197 U CN 206417197U
- Authority
- CN
- China
- Prior art keywords
- wing
- fuselage
- fixed
- landing aircraft
- tandem
- 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.)
- Expired - Fee Related
Links
Landscapes
- Toys (AREA)
Abstract
Landing aircraft is vertically mixed the utility model discloses a kind of tandem wing, including fuselage, also include the preceding fixed wing and rear fixed wing being arranged on fuselage, fuselage both sides are respectively arranged with connection carbon pipe, the end of wing and the end connection of rear fixed wing are fixed before each connection carbon Guan Junyu, propeller aircraft is provided with each connection carbon pipe, wing rudder is provided with rear fixed wing, is arranged on the vertical fin on fuselage and is provided with vertical fin rudder.The utility model makes the ability that fixed-wing unmanned plane is provided with VTOL, and preceding drawing motor changes the dynamic engine of oil into, need to only refuel just can be inexpensive in a short time execution task repeatedly, and the longer speed of a ship or plane of continuing a journey is higher.
Description
Technical field
The utility model is related to unmanned air vehicle technique field, is more particularly to a kind of tandem wing and vertically mixes landing aircraft.
Background technology
Technical grade unmanned plane is broadly divided into two kinds of multi-rotor unmanned aerial vehicles or fixed-wing unmanned plane on the market at present, but at present this
Two kinds of unmanned planes are while intrinsic advantage is possessed also because it is developed self structure defect and function has certain limitation.It is right
For fixed-wing unmanned plane, although it is had a smooth flight, landform landing, energy hovering flight, but the same energy of its consumption are not limited and is stayed
Short between space-time, load is small, and flying speed is low.For fixed wing aircraft, most of fixed-wings have certain want to take-off venue
Ask, such as need special device catapult-assisted take-off, or one has the smooth takeoff runway rolling start of certain length to obtain required rise
Fly initial velocity.Buffer usually using parachute, buffer air bag, arresting net when it lands or have the smooth takeoff runway of certain length
It is sliding to run landing.But when many times performing task, our aircraft does not have such takeoff condition, or need to pay
Cost is larger.
Utility model content
The purpose of this utility model is to be vertically to mix there is provided a kind of tandem wing in view of the above-mentioned problems existing in the prior art
Close drop aircraft, the problem of solution steady landing of landform and the long endurance of high speed are difficult to take into account.
Above-mentioned purpose of the present utility model is achieved through the following technical solutions：
A kind of tandem wing vertically mixes landing aircraft, including fuselage, in addition to the preceding fixed wing being arranged on fuselage
With rear fixed wing, the end of wing is fixed with after in fuselage both sides before being respectively arranged with connection carbon pipe, each connection carbon Guan Junyu
Propeller aircraft is provided with the end connection of fixed wing, each connection carbon pipe, wing side is provided with rear fixed wing
To rudder, it is arranged on the vertical fin on fuselage and is provided with vertical fin rudder.
Horizontal level of the horizontal level of fixed wing higher than preceding fixed wing after as described above.
Connection carbon pipe as described above is fixed by rotor motor fixed support with several rotor motors, each rotor electricity
Machine is connected with propeller aircraft.
2 rotor motors are provided with each connection carbon pipe as described above.
Each rotor motor as described above is located at same level, and each propeller aircraft is located at same level.
The head of fuselage as described above draws motor before being provided with, preceding drawing motor is connected with preceding drawing propeller.
Fuselage bottom as described above is provided with undercarriage, and undercarriage bottom is provided with roller or boat form floating drum.
By connecting branch between the end and connection carbon pipe of the end of fixed wing and rear fixed wing before as described above
Support seat connection.
Be provided with the vertical fin rudder steering wheel for driving vertical fin rudder to overturn on vertical fin as described above, it is described after
The wing rudder steering wheel for driving wing rudder to overturn is provided with fixed wing.
The utility model compared with prior art, with advantages below：
1st, the utility model makes the ability that fixed-wing unmanned plane is provided with VTOL, compared with other like products, the party
Method is simple in construction, and manufacturing cost is low, is easy to production and assembly and maintenance, and lower to manipulation request, and reliability is high, and this mode rises
Drop flight is not also limited the contoured article entrained by the task storehouse of fuselage, and two pairs of high speed wing lift are big, load big, lure simultaneously
Lead resistance small.
2nd, folding undercarriage can be improved to, windage is smaller.It is preceding to draw motor to change the dynamic engine of oil into, it need to only refuel just
Execution task repeatedly that can be inexpensive in a short time, and the longer speed of a ship or plane of continuing a journey is higher.When carrying ejection type landing, in maximum journey
Security is improved on degree relatively reliable.
Brief description of the drawings
Fig. 1 is dimensional structure diagram of the present utility model；
Fig. 2 is overlooking the structure diagram of the present utility model；
Fig. 3 is side structure schematic view of the present utility model；
Fig. 4 is forward sight structural representation of the present utility model；
In figure：1- fuselages；Motor is drawn before 2-；Propeller is drawn before 3-；Wing is fixed before 4-；5- rotor motors；6- rotor spiral shells
Revolve oar；7- connection carbon pipes；Wing is fixed after 8-；9- wing rudders；10- undercarriages；11- vertical fins；12- vertical fin rudders；13-
Vertical fin rudder steering wheel；14- wing rudder steering wheels；15- hatch doors；16- rotor motor fixed supports；17- connecting support seats.
Embodiment
The technical scheme in the utility model embodiment is clearly and completely described below in conjunction with accompanying drawing, it is clear that institute
The embodiment of description is only a part of embodiment of the utility model, rather than whole embodiments.Based in the utility model
Embodiment, the every other embodiment that those of ordinary skill in the art are obtained under the premise of creative work is not made,
Belong to the scope of the utility model protection.
As shown in figure 1, a kind of tandem wing vertically mixes landing aircraft, including fuselage 1, in addition to set on the fuselage 1
Preceding fixed wing 4 and rear fixed wing 8, the both sides of fuselage 1 are respectively arranged with connection carbon pipe 7, each connection carbon pipe 7 with it is preceding solid
Determine to be provided with propeller aircraft 6 on the end of wing 4 and the end connection of rear fixed wing 8, each connection carbon pipe 7, it is rear solid
Determine to be provided with wing rudder 9 on wing 8, set and be provided with vertical fin rudder 12 on vertical fin 11 on the fuselage 1.
Horizontal level of the horizontal level higher than preceding fixed wing 4 of wing 8 is fixed afterwards.
Connection carbon pipe 7 is fixed by rotor motor fixed support 16 with several rotor motors 5, and each rotor motor 5 is equal
It is connected with propeller aircraft 6.
2 rotor motors 5 are provided with each connection carbon pipe 7.
Each rotor motor 5 is located at same level, and each propeller aircraft 6 is located at same level.
The head of fuselage 1 draws motor 2 before being provided with, preceding drawing motor 2 is connected with preceding drawing propeller 3.
The bottom of fuselage 1 is provided with undercarriage 10, and the bottom of undercarriage 10 is provided with roller or boat form floating drum.
Connected between the end and connection carbon pipe 7 of the end of preceding fixed wing 4 and rear fixed wing 8 by connecting support seat 17
Connect.
The vertical fin rudder steering wheel 13 for driving vertical fin rudder 12 to overturn, described rear fixation are provided with vertical fin 11
The wing rudder steering wheel 14 for driving wing rudder 9 to overturn is provided with wing 8.
Takeoff phase：
The utility model is placed on any landform on the ground, if the water surface, the roller on undercarriage 10 can change boat form into
Floating drum, shifts four throttles of rotor motor 5 onto 60% to 80%, and it is liftoff rapidly that aircraft obtains the power that takes off vertically, when aircraft reaches
Draw motor 2 to start oil supply before certain limit safe altitude and be switched to fixed-wing offline mode by four rotor VTOL, when
The utility model speed reaches certain forward flight speed, and the lift balance enough of preceding fixed wing 4 and the afterwards fixed offer of wing 8 is certainly
During body gravity, four rotor motors 5 enter dormancy holding state, and fixed-wing Pattern completion is switched with regard to this four rotor.
Cruising phase：
Complete after takeoff maneuver, flying power is provided by preceding drawing motor 2, the rotation control of wing rudder 9 is mushed
And decline, the rotation control of vertical fin rudder 12 is to the left or steering to the right is so as to change course.This stage is fixed with common
Wing aircraft is as good as.
Landing phases：
When the utility model completes aerial mission, reach that four rotor motors 5 are reawaked when specifying landing place overhead
Intervention, while rotor motor 5 is refueled, preceding drawing motor 2 subtract oil until close, it is of the present utility model balance with lift successively by
The control adapter of four rotors, flying height is adjusted as common four rotor wing unmanned aerial vehicle, until landing, dropping action is completed with regard to this.
Stable VTOL is realized in order to simplify structure, four rotor motors 5 are generally aligned in the same plane, and four rotor spiral shells
Rotation oar 6 is generally aligned in the same plane, and the distance of four axle center of rotor motor 5 to the overall center of gravity of utility model is equal.
In order to which eddy current effect when reducing fixed-wing mode flight makes flight more steady, induction is reduced while lifting lift
Resistance, preceding fixed wing 4 and rear fixed wing 8 are arranged in Different Plane, wing rudder is housed on rear fixed wing 8, after
The fixed place plane of wing 8 is higher than the preceding fixed place plane of wing 4.
In order to perform take photo by plane, monitor, the task such as survey and draw when the head task that is hung hang storehouse and will not be kept off by undercarriage 10
Firmly sight, undercarriage 10 uses double-span undercarriage（It can be replaced with Sledge type undercarriage）.
For precise positioning and control course, the utility model can be using double GPS Differential positionings.
In order to reduce flight resistance, undercarriage 10 is foldable to be collected in the ventral of fuselage 1.
The preceding number of times for drawing motor 2 to change the dynamic engine of oil into extend continuation of the journey and perform task in a short time.
Ejection type parachute can be carried in fuselage 1, emergency landing, drop are carried out to meet uncontrollable factor in the task of execution
Low dangerous reduction property loss.
Specific embodiment described herein is only to the utility model spirit explanation for example.The utility model institute
Category those skilled in the art can make various modifications or supplement or using similar to described specific embodiment
Mode substitute, but without departing from spirit of the present utility model or surmount scope defined in appended claims.
Claims (9)
1. a kind of tandem wing vertically mixes landing aircraft, including fuselage（1）, it is characterised in that also including being arranged on fuselage（1）
On preceding fixed wing（4）With rear fixed wing（8）, fuselage（1）Both sides are respectively arranged with connection carbon pipe（7）, each connect carbon
Pipe（7）With preceding fixed wing（4）End and rear fixed wing（8）End connection, each connection carbon pipe（7）On be respectively provided with
There is propeller aircraft（6）, wing is fixed afterwards（8）On be provided with wing rudder（9）, it is arranged on fuselage（1）On vertical fin（11）
On be provided with vertical fin rudder（12）.
2. a kind of tandem wing according to claim 1 vertically mixes landing aircraft, it is characterised in that described rear fixation
Wing（8）Horizontal level higher than preceding fixed wing（4）Horizontal level.
3. a kind of tandem wing according to claim 1 vertically mixes landing aircraft, it is characterised in that described connection carbon
Pipe（7）Pass through rotor motor fixed support（16）With several rotor motors（5）It is fixed, each rotor motor（5）And rotor
Propeller（6）Connection.
4. a kind of tandem wing according to claim 3 vertically mixes landing aircraft, it is characterised in that described each connects
Connect carbon pipe（7）On be provided with 2 rotor motors（5）.
5. a kind of tandem wing according to claim 3 vertically mixes landing aircraft, it is characterised in that each described rotation
Wing motor（5）Positioned at same level, each propeller aircraft（6）Positioned at same level.
6. a kind of tandem wing according to claim 1 vertically mixes landing aircraft, it is characterised in that described fuselage
（1）Head be provided with before draw motor（2）, preceding drawing motor（2）With preceding drawing propeller（3）Connection.
7. a kind of tandem wing according to claim 1 vertically mixes landing aircraft, it is characterised in that described fuselage
（1）Bottom is provided with undercarriage（10）, undercarriage（10）Bottom is provided with roller or boat form floating drum.
8. a kind of tandem wing according to claim 1 vertically mixes landing aircraft, it is characterised in that described preceding fixation
Wing（4）End and rear fixed wing（8）End with being connected carbon pipe（7）Between pass through connecting support seat（17）Connection.
9. a kind of tandem wing according to claim 1 vertically mixes landing aircraft, it is characterised in that described vertical fin
（11）On be provided with for driving vertical fin rudder（12）The vertical fin rudder steering wheel of upset（13）, described rear fixed wing
（8）On be provided with for driving wing rudder（9）The wing rudder steering wheel of upset（14）.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720065927.2U CN206417197U (en) | 2017-01-19 | 2017-01-19 | A kind of tandem wing vertically mixes landing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720065927.2U CN206417197U (en) | 2017-01-19 | 2017-01-19 | A kind of tandem wing vertically mixes landing aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206417197U true CN206417197U (en) | 2017-08-18 |
Family
ID=59572067
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720065927.2U Expired - Fee Related CN206417197U (en) | 2017-01-19 | 2017-01-19 | A kind of tandem wing vertically mixes landing aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206417197U (en) |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107571994A (en) * | 2017-10-14 | 2018-01-12 | 上海歌尔泰克机器人有限公司 | A kind of aircraft |
| CN107985584A (en) * | 2017-12-06 | 2018-05-04 | 邹家勇 | Multi-functional flight equipment |
| CN108016615A (en) * | 2017-12-06 | 2018-05-11 | 邹家勇 | There is the fire-fighting equipment of Combined extinguishing |
| CN108031048A (en) * | 2017-12-06 | 2018-05-15 | 邹家勇 | The fire-fighting equipment of crash resistance enhancing based on unmanned plane |
| CN108053715A (en) * | 2017-12-06 | 2018-05-18 | 邹家勇 | Fire-fighting equipment based on unmanned plane |
| CN108357687A (en) * | 2018-04-10 | 2018-08-03 | 浙江海洋大学 | One kind hanging quadrotor based on bat is bionical |
| CN108382578A (en) * | 2018-04-09 | 2018-08-10 | 北京航空航天大学 | A kind of mixed at high speed layout vertically taking off and landing flyer |
| CN109263951A (en) * | 2018-10-30 | 2019-01-25 | 佛山市神风航空科技有限公司 | A kind of aircraft of Novel vertical lift |
| CN109747822A (en) * | 2017-11-06 | 2019-05-14 | 南京福尔摩斯智能科技有限公司 | Implicitly hung down fixed-wing unmanned plane |
| EP3628593A1 (en) | 2018-09-28 | 2020-04-01 | Airbus Helicopters | Multirotor aircraft with hybrid or electric engine with optimised energy consumption |
| WO2020256571A1 (en) * | 2019-06-20 | 2020-12-24 | Eledia El Arby | Foldable tandem wing aircraft |
-
2017
- 2017-01-19 CN CN201720065927.2U patent/CN206417197U/en not_active Expired - Fee Related
Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107571994A (en) * | 2017-10-14 | 2018-01-12 | 上海歌尔泰克机器人有限公司 | A kind of aircraft |
| CN109747822A (en) * | 2017-11-06 | 2019-05-14 | 南京福尔摩斯智能科技有限公司 | Implicitly hung down fixed-wing unmanned plane |
| CN108053715A (en) * | 2017-12-06 | 2018-05-18 | 邹家勇 | Fire-fighting equipment based on unmanned plane |
| CN108016615A (en) * | 2017-12-06 | 2018-05-11 | 邹家勇 | There is the fire-fighting equipment of Combined extinguishing |
| CN107985584A (en) * | 2017-12-06 | 2018-05-04 | 邹家勇 | Multi-functional flight equipment |
| CN108031048A (en) * | 2017-12-06 | 2018-05-15 | 邹家勇 | The fire-fighting equipment of crash resistance enhancing based on unmanned plane |
| CN108382578A (en) * | 2018-04-09 | 2018-08-10 | 北京航空航天大学 | A kind of mixed at high speed layout vertically taking off and landing flyer |
| CN108382578B (en) * | 2018-04-09 | 2024-03-29 | 北京航空航天大学 | High-speed hybrid layout vertical take-off and landing aircraft |
| CN108357687B (en) * | 2018-04-10 | 2023-05-26 | 浙江海洋大学 | Four rotor crafts can hang based on bat is bionical |
| CN108357687A (en) * | 2018-04-10 | 2018-08-03 | 浙江海洋大学 | One kind hanging quadrotor based on bat is bionical |
| EP3628593A1 (en) | 2018-09-28 | 2020-04-01 | Airbus Helicopters | Multirotor aircraft with hybrid or electric engine with optimised energy consumption |
| CN110963053A (en) * | 2018-09-28 | 2020-04-07 | 空客直升机 | Electric or hybrid multi-rotor aircraft with optimized energy consumption |
| US11066161B2 (en) | 2018-09-28 | 2021-07-20 | Airbus Helicopters | Electrically or hybrid powered multirotor aircraft with optimized energy consumption |
| FR3086641A1 (en) * | 2018-09-28 | 2020-04-03 | Airbus Helicopters | MULTIROTOR AIRCRAFT WITH ELECTRIC OR HYBRID MOTORIZATION WITH OPTIMIZED ENERGY CONSUMPTION |
| CN109263951B (en) * | 2018-10-30 | 2021-11-26 | 佛山市神风航空科技有限公司 | Novel vertical lift's aircraft |
| CN109263951A (en) * | 2018-10-30 | 2019-01-25 | 佛山市神风航空科技有限公司 | A kind of aircraft of Novel vertical lift |
| WO2020256571A1 (en) * | 2019-06-20 | 2020-12-24 | Eledia El Arby | Foldable tandem wing aircraft |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN206417197U (en) | A kind of tandem wing vertically mixes landing aircraft | |
| CN103144769B (en) | Pneumatic layout of vertical taking-off and landing aircraft with tilted duct | |
| CN101875399B (en) | Tilt rotor aircraft adopting parallel coaxial dual rotors | |
| CN106741820A (en) | A kind of VTOL fixed-wing unmanned vehicle | |
| CN105711832B (en) | One kind is verted the long endurance combined type aircraft of three rotors | |
| CN106428548A (en) | Vertical take-off and landing unmanned aerial vehicle | |
| CN204750564U (en) | Three rotor VTOL unmanned aerial vehicle on Y type | |
| CN103979104B (en) | One can variant X-type wing vertical landing minute vehicle | |
| CN207078311U (en) | A kind of dynamic four rotor wing unmanned aerial vehicle fuselage folding systems at a high speed of folding combined type oil | |
| CN203005747U (en) | Tilt rotor aircraft | |
| CN105480416A (en) | Unmanned aerial vehicle with tilted rotors | |
| CN107416200A (en) | A kind of electronic compound rotor aircraft | |
| CN106927036A (en) | A kind of dynamic four rotor wing unmanned aerial vehicles at a high speed of folding combined type oil | |
| CN206125421U (en) | VTOL unmanned vehicles | |
| CN106628162A (en) | Composite unmanned aerial vehicle | |
| CN206141828U (en) | Unmanned rotation rotor helicopter | |
| CN106477033A (en) | High speed hybrid multi-rotor aerocraft | |
| CN107140179A (en) | A kind of tailstock formula tandem chord endurance aerodynamic configuration of aircraft | |
| RU2547155C1 (en) | Multi-rotor unmanned electroconvertible aircraft | |
| CN205738073U (en) | A kind of helicopter of VTOL horizontal flight | |
| CN105460215A (en) | Fixed-wing air vehicle achieving vertical or short-distance take-off and landing | |
| CN105270625A (en) | Multi-purpose vertical take-off and landing unmanned aerial vehicle | |
| CN109533319A (en) | A kind of tilting rotor unmanned vehicle structural system with the overlap joint wing | |
| CN206750143U (en) | A kind of electronic compound rotor aircraft | |
| CN206327567U (en) | A kind of compound unmanned vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170818 Termination date: 20200119 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |