CN103963959A - Hovering type folding wing lifting body aircraft based on variable centroid technology - Google Patents
Hovering type folding wing lifting body aircraft based on variable centroid technology Download PDFInfo
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- CN103963959A CN103963959A CN201410199232.4A CN201410199232A CN103963959A CN 103963959 A CN103963959 A CN 103963959A CN 201410199232 A CN201410199232 A CN 201410199232A CN 103963959 A CN103963959 A CN 103963959A
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Abstract
The invention relates to an aviation aircraft, and in particular relates to a hovering type folding wing lifting body aircraft based on a variable centroid technology. According to the technical scheme, the hovering type folding wing lifting body aircraft based on the variable centroid technology comprises a lifting body airframe (1), a variable centroid mechanism (2), a vectored thrust mechanism (3) and a wing rotation folding mechanism (4), wherein two front wings (41) and two rear wings (42) which are connected with the lifting body airframe (1) are in a wing combination type serial wing layout. By adopting the hovering type folding wing lifting body aircraft based on the variable centroid technology, the problems of take-off and landing performances and multi-attitude flight performance of a fixed wing aircraft are solved, and the functions of vertical/short-distance take-off and landing, thrust vectoring and small-space flight of the fixed wing aircraft are realized.
Description
Technical field
The present invention relates to a kind of aviation aircraft, particularly a kind of can floating type lifting body aircraft.
Background technology
At world's aviation field, aircraft is mainly divided into two kinds: Fixed Wing AirVehicle and rotor craft at present.Due to these two kinds of layouts that aircraft self is single and fixing, it still has significant limitation in all fields.Conventional Fixed Wing AirVehicle need to be slided race landing, has significant limitation, and runway quality (length, width, hardness, planeness, material, Level Of Maintenance etc.) is had to strict requirement in landing mode.Although rotor craft can reduce the requirement to runway 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 size of this class aircraft is larger, while hovering, need to take larger space aloft, cannot be in small space hovering flight.Although another kind of tiltrotor aircraft can be realized vertical takeoff and landing and high-performance cruise simultaneously, but also there is critical defect simultaneously, the V-22 of U.S. army " osprey " for example, guaranteeing that its driving engine and screw propeller high-power, large load that is positioned at wing tip synchronously rotates, is quite difficult handling with controlling.In order to overcome the defect in these " qualities ", " osprey " has to take many complexity, unconventional technical measures, thereby weight, performance and the productive costs of full machine are all affected.In addition Fixed Wing AirVehicle that can vertical/short take-off and landing (STOL) its aeroperformance when different attitudes flights such as taking off, cruise is different, the irregular conversion of aerodynamic center and centroid distance makes the stability decreases of aircraft, makes it can not take into account the aerial mission of different attitudes.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, after two front wings that are connected with lifting body fuselage, two, wing adopts wing body fusion type tandem wing layout, 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, at the air extractor duct place of lift fan air flue, is provided with lower hatch door; Vectored thrust driving engine quantity has two, the symmetrical lifting body afterbody both sides that are arranged on, and the vector spout of vectored thrust driving engine exposes outside lifting body fuselage, and the S. A. of take perpendicular to lifting body fuselage axis is axle rotation; 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 wings to horizontally rotate 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 can vertical takeoff and landing, hovering and low speed cruise, and can meet the requirement of various state of flights to stability of aircraft;
(2) the present invention installs lift fan in the fuselage interior of aircraft front end, jointly forms bikini power arrangement, for aircraft provides stable lift with rear portion vectored thrust device.Described vectored thrust mechanism, without external screw propeller, makes aircraft can 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 can be by wing by fold mechanism folding system under different demands, thereby reduces the storage space of aircraft, convenient transportation and throwing in, and can make aircraft cruise and cruise in small space.
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 structural representation during open-collecting state of wing;
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-.
The specific embodiment:
Referring to accompanying drawing 1,3, based on Moving technology can floating type folded wing lifting body aircraft, it comprises: lifting body fuselage 1, after be connected with lifting body fuselage 1 two front wings 41, two, wing 42 adopts wing body fusion type tandem wing layouts, and aircraft also comprises: Moving mechanism 2, vectored thrust mechanism 3 and wing rotary folding mechanism 4;
Lifting body fuselage 1 can provide for aircraft integral body the fuselage of lift during for a kind of flight, can reduce wing area by actv. like this, and make aircraft still have superior aerial cruising ability;
After two front wings 41, two, wing 42 adopts wing body fusion type tandem wing layouts to be: front wing 41, wing 42 are between two before and after apportion and the aerodynamic arrangement that jointly shares lift; This layout can make the span of wing reduce, and makes aircraft smaller and more exquisite flexibly;
Moving mechanism 2 is arranged on lifting body fuselage 1 inside, and it comprises: mass 21 and slideway 22; Mass 21 embeds in slideway 22, and moves along lifting body fuselage 1 axis direction;
Referring to accompanying drawing 2, the motor-driven power of vector when vectored thrust mechanism 3 provides the power of vertically/short take-off and landing (STOL) and flies 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 places of lift fan air flue 35, at air extractor duct 37 places of lift fan air flue 35, is provided with lower hatch door 36; Vectored thrust driving engine 310 quantity have two, symmetrical lifting body fuselage 1 two sides of tail that is arranged on, and the vector spout 311 of vectored thrust driving engine 310 exposes outside lifting body fuselage 1, and take and rotate for axle perpendicular to the S. A. 312 of lifting body fuselage 1 axis; Vectored thrust driving engine 310 is provided with two inlet channels, is respectively: sidepiece inlet channel 39 and back inlet channel 38; Totally three driving engines in front and back form bikini power arrangement, the thrust when vertically/short take-off and landing (STOL) being provided and cruising for aircraft, and lift fan 31 can produce downward thrust F
1, vectored thrust driving engine 310 can produce along the thrust F of vector spout direction
2.The movement of controlling mass 21 by Moving mechanism 2 regulates the heart position of aircraft, and the thrust proportioning that can better distribute lift fan 31 and vector engine 310 is cruised thereby realize vertical/short take-off and landing (STOL) or hovering and Ultra-Low Speed;
Referring to 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 wings 41 to horizontally rotate motion, and after rear wing apparatus for turning drives two, wing 42 turns down motion up and down; Front wing 41 be take A, B point as S. A. rotates, and folds in lifting body fuselage 1 bottom; Rear wing 42 rotates in vertical guide, and rotation angle range is 0 °～165 °.Overlapping pasting on lifting body fuselage 1 top after rear wing 42 rotates 165 °; 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 are connected with two front wings 41 respectively; Also can be
Rear wing apparatus for turning in such scheme can comprise: adapter shaft, nut and motor-leading screw; Adapter shaft is connected with S. A. and the nut of rear wing 42, 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, and wetted area is reduced, and reduces resistance.
The present invention has 4 kinds of state of flights, takes off, hovering or Ultra-Low Speed cruise, normal cruise, land.Under different flight state, the working process of each system phase interworking is as shown in the table.
Claims (6)
- Based on Moving technology can floating type folded wing lifting body aircraft, it comprises: lifting body fuselage (1), after two the front wings (41) that are connected with described lifting body fuselage (1), two, wing (42) adopts wing body fusion type tandem wing layout, it is characterized in that, described aircraft also comprises: Moving mechanism (2), vectored thrust mechanism (3) and wing rotary folding mechanism (4);Described Moving mechanism (2) is arranged on described lifting body fuselage (1) inside, 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 locate to be provided with described upper hatch door (33) at the admission port (34) of described lift fan air flue (35), at the air extractor duct (37) of described lift fan air flue (35), locate to be provided with described lower hatch door (36); Described vectored thrust driving engine (310) quantity has two, symmetrical described lifting body fuselage (1) two sides of tail that is arranged on, the vector spout (311) of described vectored thrust driving engine (310) exposes outside described lifting body fuselage (1), and to take perpendicular to the S. A. (312) of described lifting body fuselage (1) axis be 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 wings (41) to horizontally rotate motion, and after described rear wing apparatus for turning drives described two, wing (42) turns down motion up and down.
- 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.
- 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.
- 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.
- 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; Described adapter shaft is connected with S. A. and the described nut of described rear wing (42), and described nut sleeve is connected on leading screw.
- 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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| 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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| CN103963959A true CN103963959A (en) | 2014-08-06 |
| CN103963959B CN103963959B (en) | 2015-12-30 |
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Cited By (10)
| 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 |
| CN105045273A (en) * | 2015-08-12 | 2015-11-11 | 中国运载火箭技术研究院 | Dual-channel variable-centroid aircraft |
| CN105539807A (en) * | 2016-01-15 | 2016-05-04 | 杨汉波 | Deformable airplane with front-rear double propeller and front-rear double wing |
| CN106249748A (en) * | 2016-08-29 | 2016-12-21 | 联想(北京)有限公司 | A kind of equipment configuration control method and controlled motion equipment |
| CN107554776A (en) * | 2017-08-17 | 2018-01-09 | 丁刘胜 | Duct aerofoil profile unmanned plane |
| CN108177771A (en) * | 2018-01-08 | 2018-06-19 | 南京航空航天大学 | Wing composite aircraft is determined in variable mass distribution rotation |
| CN109071033A (en) * | 2016-03-11 | 2018-12-21 | 杰托普特拉股份有限公司 | The construction of vertical and landing takeoff system for the flight vehicles |
| CN109279001A (en) * | 2017-07-21 | 2019-01-29 | 通用电气公司 | The aircraft of vertical takeoff and landing |
| 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 |
| CN115258107A (en) * | 2022-07-21 | 2022-11-01 | 江苏科技大学 | Folding T-shaped wing with wing body integrated with underwater glider and working method of folding T-shaped wing |
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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 |
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Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN105045273A (en) * | 2015-08-12 | 2015-11-11 | 中国运载火箭技术研究院 | Dual-channel variable-centroid aircraft |
| 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 |
| CN109071033A (en) * | 2016-03-11 | 2018-12-21 | 杰托普特拉股份有限公司 | The construction of vertical and landing takeoff system for the flight vehicles |
| CN106249748A (en) * | 2016-08-29 | 2016-12-21 | 联想(北京)有限公司 | A kind of equipment configuration control method and controlled motion equipment |
| CN109279001A (en) * | 2017-07-21 | 2019-01-29 | 通用电气公司 | The aircraft of vertical takeoff and landing |
| CN107554776A (en) * | 2017-08-17 | 2018-01-09 | 丁刘胜 | Duct aerofoil profile unmanned plane |
| CN108177771A (en) * | 2018-01-08 | 2018-06-19 | 南京航空航天大学 | Wing composite aircraft is determined in variable mass distribution rotation |
| 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 |
| CN115258107A (en) * | 2022-07-21 | 2022-11-01 | 江苏科技大学 | Folding T-shaped wing with wing body integrated with underwater glider and working method of folding T-shaped wing |
| 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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| CN103963959B (en) | 2015-12-30 |
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