CN202754143U - Rotating engine vertical take-off and landing aircraft - Google Patents
Rotating engine vertical take-off and landing aircraft Download PDFInfo
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- CN202754143U CN202754143U CN 201220363597 CN201220363597U CN202754143U CN 202754143 U CN202754143 U CN 202754143U CN 201220363597 CN201220363597 CN 201220363597 CN 201220363597 U CN201220363597 U CN 201220363597U CN 202754143 U CN202754143 U CN 202754143U
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Abstract
The utility model discloses a rotating engine vertical take-off and landing aircraft which aims at solving technical problems of complex take-off and landing technologies and higher cost of existing vertical take-off and landing aircrafts at different levels. The rotating engine vertical take-off and landing aircraft comprises parallelly-connected double fuselages, a wing and an empennage, the parallelly-connected double fuselages are connected into a whole through the wing, and two engines are serially mounted between the parallel-connected double fuselages horizontally and can rotate around fuselage butting shafts along with mounting frames respectively to enable an injection port of the engines to change directions. The rotating engine vertical take-off and landing aircraft has the advantages that the dynamical structure of the aircraft is designed more rationally by uniquely arranging the two engines; vertical take-off and landing flying direction changing and the like are realized by adjusting jet direction of the engines and lifting force generated by the wing and matching of elevators and the like; and the rotating engine vertical take-off and landing aircraft can be a manned or unmanned aircraft which is simple in control, integrally formed and usable in the army, navy and air force, is especially suitable for carrier carrying, can be used as a bomber, early warning aircraft and air tanker, and can carry missile armament to become a ground attack plane and fighter.
Description
Technical field:
The utility model relates to a kind of vertical take-off and landing aircraft (VTOL aircraft), relates in particular to a kind of rotary engine vertical take-off and landing aircraft (VTOL aircraft).Belong to field of aerospace technology.
Background technology:
The vertical takeoff and landing technology of normal arrangement aircraft has three kinds at present, and a kind of is that engine nozzle turns to vertical takeoff and landing such as Britain's Harrier and Russian refined gram aircraft; A kind of is to adopt power fan such as U.S. F35 aircraft; Also having a kind of is that tilting rotor is such as U.S. V22 osprey aircraft.Front two kinds of vertical takeoff and landing technology are more complicated all, and cost is larger.V22 osprey vertical take-off and landing aircraft (VTOL aircraft) is at wing tip two turbo oar engines to be installed, and makes by tilting rotor that aircraft has similar cyclogyro performance when taking off and land, and when normal flight, it has similar common propeller aeroplane performance.
Summary of the invention:
The utility model is in order to solve present vertical take-off and landing aircraft (VTOL aircraft) in the landing technology more complicated that exists in varying degrees, and the technical matters that required cost is higher provides a kind of a kind of vertically taking off and landing flyer that adopts the rotary engine technical design.Its concrete technical scheme is: a kind of rotary engine vertical take-off and landing aircraft (VTOL aircraft), and it comprises twin fuselage in parallel, wing and empennage, described twin fuselage in parallel are connected as a single entity by wing; Tandem is installed between the described twin fuselage in parallel before and after two driving engines; Described two driving engines can rotate around the fuselage abutment shaft with erecting frame respectively, make the injection orifice of driving engine change direction thereupon.
Characteristics of the present utility model and beneficial effect: by the unique layout to two driving engines, make the dynamic structure design of aircraft more reasonable; Jet direction by adjusting driving engine and the lift that produces with wing and elevating rudder etc. cooperate, and realize vertical takeoff and landing, change of flight direction etc.; Make the utility model become a type and control simply, reliable and stable have people/unmanned vehicle, and land, sea and air all can be used.Especially be fit to carrier-borne.Can be used as bomber, early warning plane, tanker aircraft.Also the portability missile armament becomes ground attack aircraft and fighter plane.
Description of drawings:
Fig. 1 the utility model structural representation
Fig. 2 the utility model vertical takeoff and landing schematic diagram
Fig. 3 the utility model change of flight direction schematic diagram
The specific embodiment:
Referring to Fig. 1, the rotary engine vertical take-off and landing aircraft (VTOL aircraft), it comprises twin fuselage 1 in parallel, wing 2 and empennage 3, described twin fuselage 1 in parallel are connected as a single entity by wing 2; Two driving engines 6,7 front and back tandems are installed between the described twin fuselage in parallel 1; Described two driving engines 6,7 can rotate around fuselage abutment shaft 4,5 with erecting frame 8,9 respectively, make the injection orifice 10 of driving engine change direction thereupon.Wherein:
Front and back are installed in two driving engines 6,7 in the middle of two fuselages, for fear of the mutual interference of jet flow phase, adopt up and down arranged in dislocation.
At described wing two ends jet apparatus 12 is installed.
Referring to Fig. 1, engine rotation forward (exist upwards stagger angle) during normal flight, injection orifice 10 backwards, aircraft becomes the normal arrangement aircraft, is subject to engine thrust and advances.
Referring to Fig. 2, Fig. 3, during landing engine rotation upwards, injection orifice 10 produces downward thrust down, makes aircraft be subject to power upwards and takes off;
Injection orifice 10 by two driving engines in front and back towards change, regulate the thrust size and Orientation, make aircraft produce the motion of vertical and fore-and-aft direction.
Landing and when hovering Aircraft Lateral to jet apparatus 12 controls of control by being installed in wing wing tip place, the left and right sides.
Take off change normal flight over to after, the attitude of aircraft and movement in vertical direction then produce aerodynamic force by wing and 11 controls of elevating rudder 3 ailerons are finished.Aircraft is by two rotary engines and wing, control air maneuver and the balance of front and back tandem.The placement scheme of this uniqueness is better than the scheme at 2 driving engines of wing tip installation of V22 osprey aircraft, makes the aircraft balance in pitch more unsophisticated.
The utility model can become a type to be controlled simply, and reliable and stable have people/unmanned vehicle, and land, sea and air all can be used.Especially be fit to carrier-borne.Can be used as bomber, early warning plane, tanker aircraft.Also the portability missile armament becomes ground attack aircraft and fighter plane.
Claims (3)
1. rotary engine vertical take-off and landing aircraft (VTOL aircraft), it comprises twin fuselage in parallel (1), wing (2) and empennage (3), described twin fuselage in parallel (1) are connected as a single entity by wing (2); It is characterized in that: tandem is installed between the described twin fuselage in parallel (1) before and after two driving engines (6,7); Described two driving engines (6,7) can rotate around fuselage abutment shaft (4,5) with erecting frame (8,9) respectively, make the injection orifice (10) of driving engine change direction thereupon.
2. rotary engine vertical take-off and landing aircraft (VTOL aircraft) according to claim 1 is characterized in that: arranged in dislocation about two driving engines (6,7) that tandem is installed before and after between described twin fuselage in parallel (1) adopt.
3. rotary engine vertical take-off and landing aircraft (VTOL aircraft) according to claim 1 is characterized in that: at described wing two ends jet apparatus (12) is installed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220363597 CN202754143U (en) | 2012-07-26 | 2012-07-26 | Rotating engine vertical take-off and landing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220363597 CN202754143U (en) | 2012-07-26 | 2012-07-26 | Rotating engine vertical take-off and landing aircraft |
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| Publication Number | Publication Date |
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| CN202754143U true CN202754143U (en) | 2013-02-27 |
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| CN 201220363597 Expired - Fee Related CN202754143U (en) | 2012-07-26 | 2012-07-26 | Rotating engine vertical take-off and landing aircraft |
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Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103158871A (en) * | 2013-03-07 | 2013-06-19 | 杨义华 | Vertical take-off and landing jet aircraft |
| CN103612752A (en) * | 2013-03-07 | 2014-03-05 | 杨义华 | Vertical take-off technology of vertical take-off and landing jet plane |
| CN103612753A (en) * | 2013-03-07 | 2014-03-05 | 杨义华 | Landing method of vertical take-off and landing jet plane |
| CN105000193A (en) * | 2015-06-23 | 2015-10-28 | 中国航空工业集团公司西安飞机设计研究所 | Follow-up radome bracket and follow-up radar with same as well as aircraft |
| CN105292502A (en) * | 2015-11-17 | 2016-02-03 | 匡仲平 | Landing fuel loading system capable of increasing journey continuation distance of vertical take-off and landing fixed wing aircraft |
| CN105966612A (en) * | 2016-05-27 | 2016-09-28 | 东北师范大学 | Posture-changeable unmanned aerial vehicle capable of achieving vertical takeoff and landing |
| CN106644352A (en) * | 2016-09-23 | 2017-05-10 | 北京航空航天大学 | Double-fuselage double-wing layout aircraft wind tunnel testing method |
| CN106898236A (en) * | 2017-03-19 | 2017-06-27 | 佛山市三水区希望火炬教育科技有限公司 | A kind of floating-island type aircraft carrier it is special be vertically moved up or down large-scale early warning plane model |
| CN107444633A (en) * | 2017-08-04 | 2017-12-08 | 杨爱迪 | Structure changes VTOL invisbile plane |
| CN107521686A (en) * | 2017-03-31 | 2017-12-29 | 杨爱迪 | It is a kind of can VTOL structure changes aircraft |
| CN107813928A (en) * | 2016-09-12 | 2018-03-20 | 北京航空航天大学 | One kind can vert more rotor twin fuselage canard configuration unmanned vehicles |
| CN109878702A (en) * | 2017-12-06 | 2019-06-14 | 林瑤章 | Thrust vector control device |
| CN110194268A (en) * | 2019-06-13 | 2019-09-03 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of unmanned plane miniature gas turbine hybrid power apparatus of oil and electricity |
| CN110294104A (en) * | 2019-07-02 | 2019-10-01 | 刘璐 | It is a kind of can VTOL the stealthy Fixed Wing AirVehicle of high speed |
| CN113335517A (en) * | 2021-08-09 | 2021-09-03 | 中国空气动力研究与发展中心空天技术研究所 | Double-fuselage tandem rotor wing composite wing aircraft layout |
| CN113911336A (en) * | 2021-11-29 | 2022-01-11 | 南京航空航天大学 | Double-fuselage type tilt rotorcraft |
-
2012
- 2012-07-26 CN CN 201220363597 patent/CN202754143U/en not_active Expired - Fee Related
Cited By (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103612752A (en) * | 2013-03-07 | 2014-03-05 | 杨义华 | Vertical take-off technology of vertical take-off and landing jet plane |
| CN103612753A (en) * | 2013-03-07 | 2014-03-05 | 杨义华 | Landing method of vertical take-off and landing jet plane |
| CN103158871B (en) * | 2013-03-07 | 2015-07-29 | 杨义华 | A kind of jet plane of vertical takeoff and landing |
| CN103158871A (en) * | 2013-03-07 | 2013-06-19 | 杨义华 | Vertical take-off and landing jet aircraft |
| CN105000193A (en) * | 2015-06-23 | 2015-10-28 | 中国航空工业集团公司西安飞机设计研究所 | Follow-up radome bracket and follow-up radar with same as well as aircraft |
| CN105292502A (en) * | 2015-11-17 | 2016-02-03 | 匡仲平 | Landing fuel loading system capable of increasing journey continuation distance of vertical take-off and landing fixed wing aircraft |
| CN105966612A (en) * | 2016-05-27 | 2016-09-28 | 东北师范大学 | Posture-changeable unmanned aerial vehicle capable of achieving vertical takeoff and landing |
| CN107813928A (en) * | 2016-09-12 | 2018-03-20 | 北京航空航天大学 | One kind can vert more rotor twin fuselage canard configuration unmanned vehicles |
| CN106644352B (en) * | 2016-09-23 | 2019-03-29 | 北京航空航天大学 | A kind of wind tunnel test methods of twin fuselage two-shipper wing layout aircraft |
| CN106644352A (en) * | 2016-09-23 | 2017-05-10 | 北京航空航天大学 | Double-fuselage double-wing layout aircraft wind tunnel testing method |
| CN106898236A (en) * | 2017-03-19 | 2017-06-27 | 佛山市三水区希望火炬教育科技有限公司 | A kind of floating-island type aircraft carrier it is special be vertically moved up or down large-scale early warning plane model |
| CN107521686A (en) * | 2017-03-31 | 2017-12-29 | 杨爱迪 | It is a kind of can VTOL structure changes aircraft |
| CN107444633A (en) * | 2017-08-04 | 2017-12-08 | 杨爱迪 | Structure changes VTOL invisbile plane |
| CN109878702A (en) * | 2017-12-06 | 2019-06-14 | 林瑤章 | Thrust vector control device |
| CN110194268A (en) * | 2019-06-13 | 2019-09-03 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of unmanned plane miniature gas turbine hybrid power apparatus of oil and electricity |
| CN110294104A (en) * | 2019-07-02 | 2019-10-01 | 刘璐 | It is a kind of can VTOL the stealthy Fixed Wing AirVehicle of high speed |
| CN113335517A (en) * | 2021-08-09 | 2021-09-03 | 中国空气动力研究与发展中心空天技术研究所 | Double-fuselage tandem rotor wing composite wing aircraft layout |
| CN113911336A (en) * | 2021-11-29 | 2022-01-11 | 南京航空航天大学 | Double-fuselage type tilt rotorcraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20130227 Termination date: 20130726 |