CN205440869U - Fixed chord flight time aircraft of canard configuration of VTOL - Google Patents
Fixed chord flight time aircraft of canard configuration of VTOL Download PDFInfo
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- CN205440869U CN205440869U CN201620268632.0U CN201620268632U CN205440869U CN 205440869 U CN205440869 U CN 205440869U CN 201620268632 U CN201620268632 U CN 201620268632U CN 205440869 U CN205440869 U CN 205440869U
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Abstract
The utility model provides a fixed chord flight time aircraft of canard configuration of VTOL, characterized by, be horizontal position's left fuselage, right fuselage and middle fuselage including the state of flight, left side fuselage, right fuselage and middle fuselage level are parallel, left fuselage, right fuselage and middle fuselage are connected to the duck wing, set up the head position at left fuselage, right fuselage and middle fuselage, the afterbody of middle fuselage is provided with an engine, respectively installs two even numbers distributed engine directly over left fuselage, right fuselage, and the below of going up of left fuselage and right afterbody is provided with a vertical tail the pivot of middle afterbody engine distribute along the X axis of fuselage, the engine pivot distributes along the Y axis of fuselage directly over left side fuselage and the right fuselage. The utility model discloses an aircraft attitude control power is adjusted through the control engine rotational speed in whole flight envelope.
Description
Technical field
This utility model relates to a kind of aircraft, and the canard configuration particularly relating to a kind of VTOL fixes aircraft when chord is navigated.
Background technology
The fixed wing airplane having VTOL ability need not special airport and runway, eliminate the airport construction expense of costliness, without bird dispelling, also can be in landing under bad weather condition, reduce use cost, but also it is remote to have voyage, the conventional helicopters such as payload is high do not have the advantage that.So, VTOL Fixed Wing AirVehicle becomes a popular direction of aviation aircraft development.
Existing vertically taking off and landing flyer mostly uses single shaft, twin shaft, or three axles etc. control very difficult VTOL topology layout form, during not only VTOL pattern, stability and reliability are all difficult to ensure that, and owing to its mode used can cause the structure of aircraft to be different from generally conventional fixed wing airplane, excessively complicated, badly influence the aerodynamic arrangement under fixed-wing pattern, thus have a strong impact on the flight quality put down when flying.Another one aspect, existing VTOL aircraft major part is limited due to the design of its structure, has no idea to use the biggest span, thus cannot increase effective wing area, its flight efficiency cannot be improved, and voyage is compared with tradition fixed wing airplane or differs greatly.
Utility model content
This utility model purpose is to provide the canard configuration of a kind of VTOL and fixes aircraft when chord is navigated, and it is characterized in that, is the left fuselage of horizontal level, right fuselage and middle frame including state of flight, described left fuselage, right fuselage and middle frame horizontal parallel；Canard, connects left fuselage, right fuselage and middle frame, is arranged on left fuselage, right fuselage and the head position of middle frame；The afterbody of described middle frame is provided with an electromotor, two distributed electromotors of even number are respectively installed directly over left fuselage, right fuselage, the upper and lower of left fuselage and right afterbody is provided with a vertical tail, described middle frame rear engine rotating shaft along fuselage X-axis line be distributed；Described left fuselage and right fuselage surface engine shaft along fuselage Y-axis line be distributed.
It is right that described canard is provided with 1.
The rear portion of described left fuselage and right fuselage is each provided with wing, and wing extends to middle frame and connects as one with middle frame.
This utility model has the advantages that
This utility model uses ripe gyroplane model layout form and does not affect conventional fixed-wing aircraft layout structure, make its existing vertically taking off and landing flyer simple in construction of ratio, control difficulty low, there is more preferable VTOL performance and hovering performance, and there is faster flight speed and farther voyage.
This utility model is by design, not only achieve layout similar with the most mature and stable existing X-type four-axle aircraft under VTOL pattern and control mode, and retain the tradition distribution form of fixed wing airplane, effective wing area and overall structure reliably under pattern to the full extent flat flying.So it is reasonable to have distribution form compared with other vertically taking off and landing flyer, simple in construction, control mode mature and reliable, fly more stable, the advantages such as voyage is farther, and load-carrying is bigger.
Accompanying drawing explanation
Accompanying drawing described herein is used for providing being further appreciated by of the present utility model, constitutes the part of the application, is not intended that improper restriction of the present utility model, in the accompanying drawings:
The structural representation of aircraft when the canard configuration of the VTOL that Fig. 1 provides for this utility model embodiment fixes chord boat.
Detailed description of the invention
Describing this utility model in detail below in conjunction with accompanying drawing and specific embodiment, at this, illustrative examples of the present utility model and explanation are used for explaining this utility model, but are not intended as restriction of the present utility model.
With reference to Fig. 1, the aircraft when canard configuration of a kind of VTOL fixes chord boat, is the left fuselage 2 of horizontal level, right fuselage 3 and middle frame 1 including state of flight, described left fuselage 2, right fuselage 3 and middle frame 1 horizontal parallel；Canard 4, connects left fuselage 2, right fuselage 3 and middle frame 1, is arranged on left fuselage 2, right fuselage 3 and the head position of middle frame 1；The afterbody of described middle frame 1 is provided with an electromotor 5, two distributed electromotors of even number are respectively installed directly over left fuselage 2, right fuselage 3, the upper and lower of left fuselage and right afterbody is provided with a vertical tail 5, described middle frame 1 rear engine 5 rotating shaft along fuselage X-axis line be distributed；Described left fuselage 2 and right fuselage 3 surface engine shaft along fuselage Y-axis line be distributed.
It is right that described canard 4 is provided with 1.
The rear portion of described left fuselage 2 and right fuselage 3 is each provided with wing, and wing extends to middle frame 1 and connects as one with middle frame 1.
Aircraft manufacturing technology power of the present utility model is adjusted by control engine speed in whole flight envelope.After taking off vertically, carry out horizontal flight by flying thrust before afterbody electromotor provides in starting.Canard configuration is owing to for controlling the rudder face of pitching before center of gravity, all producing positive lift force at all flight conditions, having higher pneumatic efficiency.
The technical scheme provided this utility model embodiment above is described in detail, principle and the embodiment of this utility model embodiment are set forth by specific embodiment used herein, and the explanation of above example is only applicable to the principle helping to understand this utility model embodiment；Simultaneously for one of ordinary skill in the art, according to this utility model embodiment, all will change in detailed description of the invention and range of application, in sum, this specification content should not be construed as restriction of the present utility model.
Claims (3)
1. the aircraft when canard configuration of VTOL fixes chord boat, is characterized in that, be the left fuselage of horizontal level, right fuselage and middle frame including state of flight, described left fuselage, right fuselage and middle frame horizontal parallel；Canard, connects left fuselage, right fuselage and middle frame, is arranged on left fuselage, right fuselage and the head position of middle frame；The afterbody of described middle frame is provided with an electromotor, two distributed electromotors of even number are respectively installed directly over left fuselage, right fuselage, the upper and lower of left fuselage and right afterbody is provided with a vertical tail, described middle frame rear engine rotating shaft along fuselage X-axis line be distributed；Described left fuselage and right fuselage surface engine shaft along fuselage Y-axis line be distributed.
The aircraft when canard configuration of a kind of VTOL the most according to claim 1 fixes chord boat, is characterized in that, it is right that described canard is provided with 1.
The aircraft when canard configuration of a kind of VTOL the most according to claim 1 fixes chord boat, is characterized in that, the rear portion of described left fuselage and right fuselage is each provided with wing, and wing extends to middle frame and connects as one with middle frame.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620268632.0U CN205440869U (en) | 2016-03-31 | 2016-03-31 | Fixed chord flight time aircraft of canard configuration of VTOL |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620268632.0U CN205440869U (en) | 2016-03-31 | 2016-03-31 | Fixed chord flight time aircraft of canard configuration of VTOL |
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| CN205440869U true CN205440869U (en) | 2016-08-10 |
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| CN201620268632.0U Active CN205440869U (en) | 2016-03-31 | 2016-03-31 | Fixed chord flight time aircraft of canard configuration of VTOL |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106828913A (en) * | 2017-01-09 | 2017-06-13 | 北京猎鹰无人机科技有限公司 | A kind of VUAV |
| 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 |
| CN107878746A (en) * | 2017-10-20 | 2018-04-06 | 西北工业大学 | A kind of VTOL fixed-wing long endurance unmanned aircraft of oil electric mixed dynamic |
| CN108190016A (en) * | 2017-11-30 | 2018-06-22 | 易瓦特科技股份公司 | Power rotor structure applied to unmanned plane |
| CN108216615A (en) * | 2017-11-30 | 2018-06-29 | 易瓦特科技股份公司 | Wing tip rotor applied to unmanned plane |
| CN108216611A (en) * | 2017-11-30 | 2018-06-29 | 易瓦特科技股份公司 | Rotor structure applied to unmanned plane |
| CN108216612A (en) * | 2017-11-30 | 2018-06-29 | 易瓦特科技股份公司 | Unmanned plane |
| WO2019007433A1 (en) * | 2017-07-06 | 2019-01-10 | Yu Tian | Hybrid vtol fixed-wing drone having wing-tip propellers |
| CN109398705A (en) * | 2018-03-15 | 2019-03-01 | 吴大卫 | A kind of airfreighter |
| CN110562435A (en) * | 2019-09-30 | 2019-12-13 | 复旦大学 | Bionic bird-scaring unmanned aerial vehicle capable of rising and falling vertically |
| EP3628593A1 (en) | 2018-09-28 | 2020-04-01 | Airbus Helicopters | Multirotor aircraft with hybrid or electric engine with optimised energy consumption |
| CN115402509A (en) * | 2022-11-01 | 2022-11-29 | 上海飞机制造有限公司 | Vertical take-off and landing aircraft |
-
2016
- 2016-03-31 CN CN201620268632.0U patent/CN205440869U/en active Active
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106828913A (en) * | 2017-01-09 | 2017-06-13 | 北京猎鹰无人机科技有限公司 | A kind of VUAV |
| WO2019007433A1 (en) * | 2017-07-06 | 2019-01-10 | Yu Tian | Hybrid vtol fixed-wing drone having wing-tip propellers |
| 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 |
| CN107878746A (en) * | 2017-10-20 | 2018-04-06 | 西北工业大学 | A kind of VTOL fixed-wing long endurance unmanned aircraft of oil electric mixed dynamic |
| CN108216612A (en) * | 2017-11-30 | 2018-06-29 | 易瓦特科技股份公司 | Unmanned plane |
| CN108216611A (en) * | 2017-11-30 | 2018-06-29 | 易瓦特科技股份公司 | Rotor structure applied to unmanned plane |
| CN108216615A (en) * | 2017-11-30 | 2018-06-29 | 易瓦特科技股份公司 | Wing tip rotor applied to unmanned plane |
| CN108190016A (en) * | 2017-11-30 | 2018-06-22 | 易瓦特科技股份公司 | Power rotor structure applied to unmanned plane |
| CN109398705A (en) * | 2018-03-15 | 2019-03-01 | 吴大卫 | A kind of airfreighter |
| EP3628593A1 (en) | 2018-09-28 | 2020-04-01 | Airbus Helicopters | Multirotor aircraft with hybrid or electric engine with optimised energy consumption |
| FR3086641A1 (en) * | 2018-09-28 | 2020-04-03 | Airbus Helicopters | MULTIROTOR AIRCRAFT WITH ELECTRIC OR HYBRID MOTORIZATION WITH OPTIMIZED 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 |
| CN110562435A (en) * | 2019-09-30 | 2019-12-13 | 复旦大学 | Bionic bird-scaring unmanned aerial vehicle capable of rising and falling vertically |
| CN115402509A (en) * | 2022-11-01 | 2022-11-29 | 上海飞机制造有限公司 | Vertical take-off and landing aircraft |
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