CN103963959B - Based on Moving technology can floating type folded wing lifting body aircraft - Google Patents
Based on Moving technology can floating type folded wing lifting body aircraft Download PDFInfo
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- CN103963959B CN103963959B CN201410199232.4A CN201410199232A CN103963959B CN 103963959 B CN103963959 B CN 103963959B CN 201410199232 A CN201410199232 A CN 201410199232A CN 103963959 B CN103963959 B CN 103963959B
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Abstract
The present invention relates to a kind of aviation aircraft, particularly one can floating type lifting body aircraft.Based on Moving technology can floating type folded wing lifting body aircraft, its technical scheme is, it comprises: lifting body fuselage (1), two the front wings (41) be connected with described lifting body fuselage (1), wing (42) adopts blended wing-body formula tandem wing layout after two, and described aircraft also comprises: Moving mechanism (2), vectored thrust mechanism (3) and wing rotary folding mechanism (4); The invention solves the takeoff and landing performance of Fixed Wing AirVehicle and the problem of multi-pose airworthiness, and achieve Fixed Wing AirVehicle vertical/short take-off and landing (STOL), thrust vectoring and the function that can fly in small space.
Description
Technical field
The present invention relates to a kind of aviation aircraft, particularly one can floating type lifting body aircraft.
Background technology
At present at world's aviation field, aircraft is mainly divided into two kinds: Fixed Wing AirVehicle and rotor craft.Due to the layout that this two kinds of aircraft self are single and fixing, it still has significant limitation in all fields.Conventional Fixed Wing AirVehicle needs sliding race landing, landing mode exists significant limitation, and has strict requirement to strip quality (length, width, hardness, planeness, material, Level Of Maintenance etc.).Although rotor craft can reduce the requirement to strip quality, its flying method makes its flying speed lower, and voyage is short, and capacity weight is low.Therefore, vertical/short take-off and landing (STOL) Fixed Wing AirVehicle arises at the historic moment, but the wing dimension of this kind of aircraft is comparatively large, aloft needs during hovering to take larger space, cannot in small space hovering flight.Although another kind of tiltrotor aircraft can realize vertical takeoff and landing and high-performance cruise simultaneously, but also there is critical defect simultaneously, the V-22 " osprey " of such as U.S. army, ensureing its driving engine being positioned at high-power, the large load of wing tip and screw propeller synchronous axial system, manipulation with control is quite difficult.In order to overcome the defect in these " qualities ", " osprey " has to take many complexity, unconventional technical measures, thus the weight of full machine, performance and productive costs are all affected.In addition can the Fixed Wing AirVehicle of vertical/short take-off and landing (STOL) taking off, to cruise etc. different attitude flight time its aeroperformance be different, the irregular conversion of aerodynamic center and centroid distance makes the stability of aircraft decline, and makes it can not take into account the aerial mission of different attitude.Therefore the takeoff and landing performance and the multi-pose airworthiness that how effectively to improve Fixed Wing AirVehicle become problem demanding prompt solution.
Summary of the invention
The object of the invention is: for solving the takeoff and landing performance of Fixed Wing AirVehicle and the problem of multi-pose airworthiness, realize Fixed Wing AirVehicle vertical/short take-off and landing (STOL), thrust vectoring and the function that can fly in small space, propose a kind of based on Moving technology can floating type folded wing lifting body aircraft.
Technical scheme of the present invention is: based on Moving technology can floating type folded wing lifting body aircraft, it comprises: lifting body fuselage, two the front wings be connected with lifting body fuselage, wing adopts blended wing-body formula tandem wing layout after two, and aircraft also comprises: Moving mechanism, vectored thrust mechanism and wing rotary folding mechanism;
Moving mechanism is arranged on lifting body fuselage interior, and it comprises: mass and slideway; Mass embeds in slideway, and moves along lifting body fuselage axis direction;
Vectored thrust mechanism comprises: lift fan, upper hatch door, lower hatch door and vectored thrust driving engine; Lifting body forebody is provided with vertical lift fan air flue, and lift fan is installed in lift fan air flue, and is provided with hatch door at the admission port place of lift fan air flue, is provided with lower hatch door at the air extractor duct place of lift fan air flue; Vectored thrust driving engine quantity has two, and symmetrical is arranged on lifting body afterbody both sides, and the vector spout of vectored thrust driving engine exposes outside lifting body fuselage, and rotates for axle with the S. A. perpendicular to lifting body fuselage axis; Vectored thrust driving engine is provided with two inlet channels, is respectively: sidepiece inlet channel and back inlet channel;
Wing rotary folding mechanism comprises: front wing apparatus for turning and rear wing apparatus for turning; Front wing apparatus for turning drives two front wing horizontal revolving motion, and after rear wing apparatus for turning drives two, wing turns down motion up and down.
The invention has the beneficial effects as follows: (1) the present invention vertical takeoff and landing, hovering and low speed can cruise, and can meet the requirement of various state of flight to stability of aircraft;
(2) fuselage interior of the present invention in aircraft front end installs lift fan, jointly forms bikini power arrangement, for aircraft provides stable lift with rear portion vectored thrust device.Described vectored thrust mechanism, without external screw propeller, enables aircraft among a small circle, realize vertically/short take-off and landing (STOL), and can realize aerial low speed cruise and hover and aerial efficient vector motor-driven;
(3) the Moving mechanism in the present invention can change centroid position under different flight state, for aircraft promotes airworthiness and stability, makes flying instrument for multi-pose flight performance;
(4) wing machine rotary folding system in the present invention is by wing by the system folding under different demand of fold mechanism, thus can reduce the storage space of aircraft, convenient transport and throwing in, and aircraft can be made to cruise in small space cruise.
Accompanying drawing explanation
Fig. 1 is axonometric drawing of the present invention;
Fig. 2 is the arrangement structure schematic diagram of vectored thrust mechanism in the present invention;
Fig. 3 is structural representation of the present invention;
Fig. 4 is structural representation when front wing is collecting state in the present invention;
Fig. 5 be in the present invention after wing open-collecting state time structural representation;
Wherein: 1-lifting body fuselage, 2-Moving mechanism, 3-vectored thrust mechanism, 4-wing rotary folding mechanism, 21-mass, 22-slideway, 31-lift fan, 32-top hatch door slideway, 33-lift fan top hatch door, 34-lift fan air flue admission port, 35-lift fan air flue, 36-lift fan air flue air extractor duct, 37-lift fan bottom hatch door, 38-back inlet channel, 39-sidepiece inlet channel, 310-vectored thrust driving engine, 311-vectored thrust driving engine vector spout, 312-vector nozzle outlet rotary axle, wing before 41-, wing after 42-.
Detailed description of the invention:
See accompanying drawing 1,3, based on Moving technology can floating type folded wing lifting body aircraft, it comprises: lifting body fuselage 1, after two that are connected with lifting body fuselage 1 41, two, front wings, wing 42 adopts blended wing-body formula tandem wing layout, and aircraft also comprises: Moving mechanism 2, vectored thrust mechanism 3 and wing rotary folding mechanism 4;
The fuselage of lifting body fuselage 1 for providing lift for aircraft is overall during a kind of flight, can reduce wing area by actv. like this, and make aircraft still have superior aerial cruising ability;
After two 41, two, front wings, wing 42 adopts blended wing-body formula tandem wing layout to be: front wing 41, wing 42 share the aerodynamic arrangement of lift before and after apportion between two jointly; This layout can make the span of wing reduce, and makes aircraft more flexibly small and exquisite;
It is inner that Moving mechanism 2 is arranged on lifting body fuselage 1, and it comprises: mass 21 and slideway 22; Mass 21 embeds in slideway 22, and moves along lifting body fuselage 1 axis direction;
See accompanying drawing 2, the power that vectored thrust mechanism 3 provides the power of vertically/short take-off and landing (STOL) motor-driven with vector when flying for aircraft, it comprises: lift fan 31, upper hatch door 33, lower hatch door 37 and vectored thrust driving engine 310; Lifting body fuselage 1 front portion is provided with vertical lift fan air flue 35, and lift fan 31 is installed in lift fan air flue 35, and is provided with hatch door 33 at admission port 34 place of lift fan air flue 35, is provided with lower hatch door 36 at air extractor duct 37 place of lift fan air flue 35; Vectored thrust driving engine 310 quantity has two, and symmetrical is arranged on lifting body fuselage 1 two sides of tail, and the vector spout 311 of vectored thrust driving engine 310 exposes outside lifting body fuselage 1, and with the S. A. 312 perpendicular to lifting body fuselage 1 axis for axle rotation; Vectored thrust driving engine 310 is provided with two inlet channels, is respectively: sidepiece inlet channel 39 and back inlet channel 38; Before and after totally three driving engines form bikini power arrangement, be the thrust of aircraft when providing vertically/short take-off and landing (STOL) and cruise, lift fan 31 can produce downward thrust F
1, vectored thrust driving engine 310 can produce the thrust F along vector spout direction
2.Regulated the heart position of aircraft by the movement of Moving mechanism 2 Mass Control block 21, better can distribute the thrust proportioning of lift fan 31 and vector engine 310, thus realize vertical/short take-off and landing (STOL) or hovering and Ultra-Low Speed and cruise;
See accompanying drawing 4,5, wing rotary folding mechanism 4 comprises: front wing apparatus for turning and rear wing apparatus for turning; Front wing apparatus for turning drives two front wing 41 horizontal revolving motion, and after rear wing apparatus for turning drives two, wing about 42 turns down motion; Front wing 41 rotates for S. A. with A, B point, folds in lifting body fuselage 1 bottom; Rear wing 42 rotates in vertical guide, and rotation angle range is 0 ° ~ 165 °.After rear wing 42 rotates 165 °, overlap is covered in lifting body fuselage 1 top; Front wing 41 is identical with said process principle to the process of deployed condition by folded state with rear wing 42, and motion process is contrary.
Mass 21 in such scheme can be driven by electric pushrod, also can be driven by motor-leading screw.
Front wing apparatus for turning in such scheme can be two steering wheels, and two steering wheels respectively wing 41 front with two are connected; Also can be
Rear wing apparatus for turning in such scheme can comprise: adapter shaft, nut and motor-leading screw; S. A. and the nut of adapter shaft and rear wing 42 are connected, and nut sleeve is connected on leading screw.
Preferably, can be tandem wing V tail aerodynamic arrangement by the Flight Vehicle Design described in such scheme, the vertical direction area of conter of V tail provides Lateral static stability for aircraft, removes fixed fin, wetted area is reduced, reduce resistance.
The present invention has 4 kinds of state of flights, takes off, to hover or Ultra-Low Speed cruises, normals cruise, lands.Under different flight state, the working process of each system phase interworking is as shown in the table.
Claims (6)
1. based on Moving technology can floating type folded wing lifting body aircraft, it comprises: lifting body fuselage (1), two the front wings (41) be connected with described lifting body fuselage (1), wing (42) adopts blended wing-body formula tandem wing layout after two, it is characterized in that, described aircraft also comprises: Moving mechanism (2), vectored thrust mechanism (3) and wing rotary folding mechanism (4);
It is inner that described Moving mechanism (2) is arranged on described lifting body fuselage (1), and it comprises: mass (21) and slideway (22); Described mass (21) embeds in slideway (22), and moves along described lifting body fuselage (1) axis direction;
Described vectored thrust mechanism (3) comprising: lift fan (31), upper hatch door (33), lower hatch door (37) and vectored thrust driving engine (310); Described lifting body fuselage (1) front portion is provided with vertical lift fan air flue (35), described lift fan (31) is installed in described lift fan air flue (35), and be provided with described upper hatch door (33) at admission port (34) place of described lift fan air flue (35), be provided with described lower hatch door (37) at air extractor duct (36) place of described lift fan air flue (35); Described vectored thrust driving engine (310) quantity has two, symmetrical is arranged on described lifting body fuselage (1) two sides of tail, the vector spout (311) of described vectored thrust driving engine (310) exposes described lifting body fuselage (1) outward, and with the S. A. (312) perpendicular to described lifting body fuselage (1) axis for axle rotation; Described vectored thrust driving engine (310) is provided with two inlet channels, is respectively: sidepiece inlet channel (39) and back inlet channel (38);
Described wing rotary folding mechanism (4) comprising: front wing apparatus for turning and rear wing apparatus for turning; Described front wing apparatus for turning drives two described front wing (41) horizontal revolving motion, and after described rear wing apparatus for turning drives described two, wing (42) turns down motion up and down.
2. as claimed in claim 1 based on Moving technology can floating type folded wing lifting body aircraft, it is characterized in that, described mass (21) is driven by electric pushrod.
3. as claimed in claim 1 based on Moving technology can floating type folded wing lifting body aircraft, it is characterized in that, described mass (21) is driven by motor-leading screw.
4. as described in claim 1 or 2 or 3 based on Moving technology can floating type folded wing lifting body aircraft, it is characterized in that, described front wing apparatus for turning is two steering wheels, and two described steering wheels are connected with described two described front wings (41) respectively.
5. as described in claim 1 or 2 or 3 based on Moving technology can floating type folded wing lifting body aircraft, it is characterized in that, described rear wing apparatus for turning comprises: adapter shaft, nut and motor-leading screw; S. A. and the described nut of described adapter shaft and described rear wing (42) are connected, and described nut sleeve is connected on leading screw.
6. as described in claim 1 or 2 or 3 based on Moving technology can floating type folded wing lifting body aircraft, it is characterized in that, described aircraft adopts tandem wing V tail aerodynamic arrangement.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410199232.4A CN103963959B (en) | 2014-05-12 | 2014-05-12 | Based on Moving technology can floating type folded wing lifting body aircraft |
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| CN201410199232.4A CN103963959B (en) | 2014-05-12 | 2014-05-12 | Based on Moving technology can floating type folded wing lifting body aircraft |
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| CN103963959B true CN103963959B (en) | 2015-12-30 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104443362A (en) * | 2014-11-03 | 2015-03-25 | 陕西飞机工业（集团）有限公司 | Gravity-center-operated small-sized unmanned aerial vehicle |
| CN105045273B (en) * | 2015-08-12 | 2017-12-22 | 中国运载火箭技术研究院 | A kind of binary channels Moving aircraft |
| CN105539807A (en) * | 2016-01-15 | 2016-05-04 | 杨汉波 | Deformable airplane with front-rear double propeller and front-rear double wing |
| CN109071033B (en) * | 2016-03-11 | 2022-12-06 | 杰托普特拉股份有限公司 | Configuration of a vertical takeoff and landing system for a flying vehicle |
| CN106249748B (en) * | 2016-08-29 | 2020-04-24 | 联想(北京)有限公司 | Equipment form control method and controlled motion equipment |
| US10822101B2 (en) * | 2017-07-21 | 2020-11-03 | General Electric Company | Vertical takeoff and landing aircraft having a forward thrust propulsor |
| CN107554776B (en) * | 2017-08-17 | 2021-03-19 | 丁刘胜 | Duct wing section unmanned aerial vehicle |
| CN108177771B (en) * | 2018-01-08 | 2023-09-26 | 南京航空航天大学 | Variable mass distribution rotary-fixed wing composite aircraft |
| CN113320693A (en) * | 2021-08-04 | 2021-08-31 | 中国空气动力研究与发展中心空天技术研究所 | Novel retractable tandem rotor wing composite wing aircraft layout |
| CN115258107B (en) * | 2022-07-21 | 2023-11-21 | 江苏科技大学 | Folding T-shaped wing for wing body fusion underwater glider and working method thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US5209428A (en) * | 1990-05-07 | 1993-05-11 | Lockheed Corporation | Propulsion system for a vertical and short takeoff and landing aircraft |
| US5405105A (en) * | 1993-05-28 | 1995-04-11 | Hudson Valley V/Stol Aircraft, Inc. | Tilt wing VTOL aircraft |
| US20090121073A1 (en) * | 2006-04-03 | 2009-05-14 | The Boeing Company | Aircraft having a jet engine, an adjustable aft nozzle, and an electric vertical fan |
| CN103231805B (en) * | 2013-05-21 | 2015-09-16 | 吉林大学 | Culvert type flap machine |
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