CN1384019A - Airplane with multi-point deflecting wings - Google Patents
Airplane with multi-point deflecting wings Download PDFInfo
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- CN1384019A CN1384019A CN 01115590 CN01115590A CN1384019A CN 1384019 A CN1384019 A CN 1384019A CN 01115590 CN01115590 CN 01115590 CN 01115590 A CN01115590 A CN 01115590A CN 1384019 A CN1384019 A CN 1384019A
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Abstract
The present invention is improved deflecting-wing airplane. It has multiple-rotation point deflecting-wing configuration and this makes the airplane possess excellent mobility, graet flight range, great cruise speed, large load capacity, high balance capacity and stability and good operating performance. It has high air self-saving capacity and high safety owing to its single-engine flight capacity and wing divorcing technology. In addition, the present invention provides one way for the improvement of helicopter and other rotor crafts.
Description
The present invention relates to a kind of airplane with multi-point deflecting wings, the national uses aviation field.
The tilt-wing aircraft of success use is through development for many years by the U.S. in the world at present.It also is at present unique in the world practical VM-22 " osprey " deflector vane transport plane that drops into.But pass through the analysis of using with to relevant picture, data, this type aircraft also exists many defectives and deficiency at present.Especially realizing that rotor is transformed into the upright position by level attitude, or its balanced capacity is relatively poor and be not easy to handle when being transformed into level attitude by the upright position.Exist in addition that rotor driving engine axis of deflection moment of torsion is big, fixed-wing is less, low-speed operations or when hovering motor-driven poor performance and this machine rotor when flat flying increase because of the flight resistance that diameter causes greatly, the consumption of fuel height, a series of deficiencies and defective such as no single-shot balance and flight performance and the flight safety coefficient that causes are lower.
The present invention is exactly for solving a kind of airplane with multi-point deflecting wings that above-mentioned deficiency provides.
Realize embodiment of the present invention be this " airplane with multi-point deflecting wings " flight with take off, ascending, descending, turn to etc. and all to have many different with existing tilt-wing aircraft, compare with existing tilt-wing aircraft, it has technical advantages such as the fixed-wing of bikini tilt wing layout, main deflection wing hanger bracket, afterbody lateral misalignment rotor craft action-oriented, lengthening of brand-new design and single-engine flight ability.Its flight theory is to utilize that actv. cooperatively interacts between master, tail deflector vane, compound type vertical tail, efficiently, the finishing the taking off of aircraft, ascending, descending, hover and long-distance flight of high maneuverability.And can finish the multiple aerial mission that other machine is difficult for finishing in the larger context.And as the single-engine flight ability, higher low, the bigger outstanding advantages such as load capacity of safety factor, consumption of fuel.
This airplane with multi-point deflecting wings changes swinging strut by fuselage, fixed wing, two main deflection wing, U type lateral misalignment, and coaxial pair of oar rotor of rotating, tailplane, vertical tail seven parts are formed.
This airplane with multi-point deflecting wings body (1) afterbody is an open type U type, and the waist both sides are equipped with fixed wing (2) wing below and are provided with to be provided with in the secondary hanger bracket of main deflection wing engine suspension support (3) (4) support and also are provided with the secondary suspension holdfast of roof jack (7) outside wing on S. A. (5) (6) wing and give establishing in quick-fried broken string (8) line shaped charge is housed.Main deflection rotor driving engine (9) connects by S. A. (5) (6) and the secondary suspension holdfast of main suspension holdfast (3) (4).Main deflection rotor driving engine (9) afterbody is provided with little suspension ring (10) and connects by axle (11) and roof jack (7).Be equipped with on driving engine (9) axle be provided with in power-transfer clutch (12) main deflection rotor (13) the fuselage U-shaped afterbody U-shaped lateral misalignment change swinging strut (14) support (14) bottom be consolidated with horizontal rotating shaft (15) laterally rotating shaft (15) be inserted in the tail cavity, bearing (16) is housed in the rotating shaft (15) laterally worm gear (17) worm gear is housed starts in the rotating shaft top by worm screw (18).The U-shaped lateral misalignment changes and the two coaxial rotor driving engine of oar (19) driving engines (19) of rotating to be housed in the support to change swinging strut (14) by axle (20) and U-shaped lateral misalignment and connect, and opposite coaxial rotor (21) (22) driving engine (19) of two secondary rotation directions is housed on driving engine (19) axle semicircle worm gear (a 23) worm gear (23) vertically is housed is started by the worm screw that is located at U-shaped support inner bottom part (24).The afterbody both sides are equipped with tailplane (25) tailplane end vertical tail (26) are housed.
Wheel (27) driving compartment (28) fuel filler pipe (29) wing strut bar (30)
Fig. 1 is the front elevation scheme drawing of airplane with multi-point deflecting wings
Fig. 2 is the birds-eye view scheme drawing of airplane with multi-point deflecting wings
Fig. 3 is the lateral plan scheme drawing of airplane with multi-point deflecting wings
Dotted line is the coaxial rotor swing position signals of the two oars of rotating in the scheme drawing
The present invention is further illustrated below in conjunction with view
When airplane with multi-point deflecting wings after the two coaxial rotors of oar (21) (22) of two main deflection rotors (13) and rotating all are horizontal and start shooting, under their combined action, aircraft can be realized vertical lift, after aircraft is raised to certain altitude, at this moment after can starting roof jack (7) at the same time or separately and starting worm screw (24), can make two main deflection wings (13) or coaxial pair of oar rotor of rotating (21) (22) rotate to the upright position and produce thrust at the same time or separately, aircraft is flown forward by level attitude.When vertical ascending, descending of aircraft and low-speed operations, also can start worm screw (18) rotation worm gear (17) and make horizontal rotating shaft (15) carry out horizontal swinging, realize the high maneuvering flight of this machine.After aircraft enters higher speed flight, fixed wing (2) has produced enough lift, at this moment also can close two main deflection rotor driving engines (9) and make the main deflection rotor rotate to level attitude by roof jack (7), and open power-transfer clutch (12) and rotor (13) and driving engine are thrown off and become free rotor, so promptly having reduced flight resistance also provides certain lift for aircraft.The thrust of aircraft this moment under this state of flight is provided by the two coaxial rotors of oar (21) (22) of rotating.Turn to maneuvering performance then by fixed wing, vertical tail, tailplane provide jointly.
This machine also can utilize above-mentioned principle to carry out the taking off of the sliding race of various ways, short distance, ultrashort distance, ascending, descending and flight.In case the explosive in this aircraft et out of order also can detonate broken string (8) immediately makes the part wing break away from body, reduces aircraft weight, be the aircraft creation certain condition of escaping danger.
Enforcement of the present invention improves energy first mate degree every technical performance and the range of use and the purposes of deflector vane class aircraft, improve such aircraft and occupant's safety factor, can effectively increase aircraft range, reduce consumption of fuel, increase load, and can significantly improve the balanced capacity and the stability of this type of aircraft.This invention simultaneously is also for the further improvement development of deflector vane class aircraft with an effective engineering selection and approach are provided.
Claims (1)
- One, a kind of airplane with multi-point deflecting wings is by fuselage, fixed wing, two main deflection wing, U type lateral misalignment rotor swinging strut, the two coaxial rotors of oar of rotating, tailplane, and vertical tail 7 parts are formed, and it is characterized in that:The afterbody of 1 airplane with multi-point deflecting wings is an open type U type.Two at 2 airplane with multi-point deflecting wings middle part is equipped with fixed wing (2) fixed wing below and is provided with to be provided with in the secondary suspension holdfast of main deflection rotor engine suspension support (3) (4) support and also is provided with the secondary suspension holdfast of roof jack (7) outside wing on S. A. (5) (6) wing and is provided with in default quick-fried broken string (8) line shaped charge is housedThe main deflection rotor driving engine (9) of 3 airplane with multi-point deflecting wings connects by S. A. (5) (6) and the secondary suspension holdfast of suspension holdfast (3) (4), and main deflection rotor driving engine afterbody is provided with little suspension ring (10) and connects by axle (11) and roof jack (7).Power-transfer clutch (12) main deflection rotor (13) is housed on the engine shaft.Be provided with U type lateral misalignment commentaries on classics swinging strut (14) support (14) bottom in the 4 airplane with multi-point deflecting wings U-shaped afterbodys and be consolidated with horizontal rotating shaft (15), laterally rotating shaft (15) is inserted in the tail cavity.Bearing (16) is housed in the rotating shaft (15) laterally to be equipped with worm gear (17) worm gear and to be driven by worm screw (18) in the rotating shaft top.The rotating pair coaxial rotor driving engine of oar (19) driving engines (19) are housed in the U type lateral misalignment commentaries on classics swinging strut (14) of 5 airplane with multi-point deflecting wings pass through spool (20) and U-shaped lateral misalignment commentaries on classics swinging strut (a 14) connection, opposite coaxial rotor (21) (22) driving engine of two secondary rotation directions is housed on driving engine (19) axle semicircle worm gear (a 23) worm gear (23) vertically is housed by worm screw (24) startup that is located at U-shaped lateral misalignment commentaries on classics swinging strut inner bottom part.The two sides of tail of 6 airplane with multi-point deflecting wings is provided with tailplane (25).Vertical tail (26) is equipped with at the two ends of the tailplane of 7 airplane with multi-point deflecting wings.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 01115590 CN1384019A (en) | 2001-05-08 | 2001-05-08 | Airplane with multi-point deflecting wings |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 01115590 CN1384019A (en) | 2001-05-08 | 2001-05-08 | Airplane with multi-point deflecting wings |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN1384019A true CN1384019A (en) | 2002-12-11 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 01115590 Pending CN1384019A (en) | 2001-05-08 | 2001-05-08 | Airplane with multi-point deflecting wings |
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| Country | Link |
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| CN (1) | CN1384019A (en) |
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2007014531A1 (en) * | 2005-08-02 | 2007-02-08 | Peizhou Han | A vtol aircraft with tilt front rotors |
| CN102161381A (en) * | 2010-03-26 | 2011-08-24 | 北京航空航天大学 | Short takeoff and landing (STOL) small aircraft based on tilting power system |
| CN102417035A (en) * | 2011-09-17 | 2012-04-18 | 陈仁多 | Coaxial helicopter capable of controlling flying speed change completely by buttons |
| CN102442426A (en) * | 2011-10-03 | 2012-05-09 | 陈仁多 | Improved coaxial helicopter |
| CN103318408A (en) * | 2013-06-28 | 2013-09-25 | 李宏生 | Helicopter with main propeller leaning forward |
| CN103434642A (en) * | 2013-08-20 | 2013-12-11 | 朱幕松 | Linked double-wing and double-rotor-wing vertical lifting aircraft |
| CN103935512A (en) * | 2014-05-12 | 2014-07-23 | 马轶 | High endurable multi-rotor craft |
| CN104015923A (en) * | 2014-06-25 | 2014-09-03 | 杨雅茹 | Helicopter with adjustable empennage attitude |
| CN104554733A (en) * | 2013-10-14 | 2015-04-29 | 姜文睿 | Jet engine capable of flexibly changing angle of jet engine body relative to airframe |
| CN105346719A (en) * | 2015-11-18 | 2016-02-24 | 何春旺 | Perpendicular take-off and landing aircraft |
| CN105620743A (en) * | 2016-02-22 | 2016-06-01 | 南京航空航天大学 | Tilting mechanism for tilting three-rotor aircraft |
| CN106143895A (en) * | 2016-07-13 | 2016-11-23 | 中国人民解放军国防科学技术大学 | Thrust type tilt rotor aircraft |
| CN107521684A (en) * | 2017-08-29 | 2017-12-29 | 北京电子工程总体研究所 | One kind is verted three rotor crafts |
| CN108725773A (en) * | 2018-08-06 | 2018-11-02 | 云呈通信息科技（上海）有限公司 | A kind of unmanned transporter |
| CN111498100A (en) * | 2020-05-15 | 2020-08-07 | 中国民航大学 | Thrust vector tilting three-rotor unmanned aerial vehicle and control method thereof |
-
2001
- 2001-05-08 CN CN 01115590 patent/CN1384019A/en active Pending
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2007014531A1 (en) * | 2005-08-02 | 2007-02-08 | Peizhou Han | A vtol aircraft with tilt front rotors |
| CN102161381A (en) * | 2010-03-26 | 2011-08-24 | 北京航空航天大学 | Short takeoff and landing (STOL) small aircraft based on tilting power system |
| CN102417035A (en) * | 2011-09-17 | 2012-04-18 | 陈仁多 | Coaxial helicopter capable of controlling flying speed change completely by buttons |
| CN102442426A (en) * | 2011-10-03 | 2012-05-09 | 陈仁多 | Improved coaxial helicopter |
| CN103318408A (en) * | 2013-06-28 | 2013-09-25 | 李宏生 | Helicopter with main propeller leaning forward |
| CN103434642A (en) * | 2013-08-20 | 2013-12-11 | 朱幕松 | Linked double-wing and double-rotor-wing vertical lifting aircraft |
| CN104554733A (en) * | 2013-10-14 | 2015-04-29 | 姜文睿 | Jet engine capable of flexibly changing angle of jet engine body relative to airframe |
| CN103935512A (en) * | 2014-05-12 | 2014-07-23 | 马轶 | High endurable multi-rotor craft |
| CN104015923A (en) * | 2014-06-25 | 2014-09-03 | 杨雅茹 | Helicopter with adjustable empennage attitude |
| CN105346719A (en) * | 2015-11-18 | 2016-02-24 | 何春旺 | Perpendicular take-off and landing aircraft |
| CN105620743A (en) * | 2016-02-22 | 2016-06-01 | 南京航空航天大学 | Tilting mechanism for tilting three-rotor aircraft |
| CN106143895A (en) * | 2016-07-13 | 2016-11-23 | 中国人民解放军国防科学技术大学 | Thrust type tilt rotor aircraft |
| CN106143895B (en) * | 2016-07-13 | 2018-08-14 | 中国人民解放军国防科学技术大学 | Thrust type tilt rotor aircraft |
| CN107521684A (en) * | 2017-08-29 | 2017-12-29 | 北京电子工程总体研究所 | One kind is verted three rotor crafts |
| CN108725773A (en) * | 2018-08-06 | 2018-11-02 | 云呈通信息科技（上海）有限公司 | A kind of unmanned transporter |
| CN111498100A (en) * | 2020-05-15 | 2020-08-07 | 中国民航大学 | Thrust vector tilting three-rotor unmanned aerial vehicle and control method thereof |
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