CN105857579A - Propeller airplane - Google Patents

Propeller airplane Download PDF

Info

Publication number
CN105857579A
CN105857579A CN201610312234.9A CN201610312234A CN105857579A CN 105857579 A CN105857579 A CN 105857579A CN 201610312234 A CN201610312234 A CN 201610312234A CN 105857579 A CN105857579 A CN 105857579A
Authority
CN
China
Prior art keywords
described
wing
propeller aeroplane
arranged
tailplane
Prior art date
Application number
CN201610312234.9A
Other languages
Chinese (zh)
Inventor
曲浩
张健
王斌
Original Assignee
中国航空工业集团公司西安飞机设计研究所
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by 中国航空工业集团公司西安飞机设计研究所 filed Critical 中国航空工业集团公司西安飞机设计研究所
Priority to CN201610312234.9A priority Critical patent/CN105857579A/en
Publication of CN105857579A publication Critical patent/CN105857579A/en

Links

Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C11/00Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/46Arrangements of or constructional features peculiar to multiple propellers
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64DEQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLYING SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D29/00Power-plant nacelles, fairings, or cowlings
    • B64D29/02Power-plant nacelles, fairings, or cowlings associated with wings

Abstract

The invention discloses a propeller airplane. The propeller airplane comprises wings, a body, two nacelles and an empennage; the two nacelles are arranged on the wings, one of the nacelles is arranged on the wing on one side of the body, the other nacelle is arranged on the wing on the other side of the body, and the two nacelles are arranged on the upper surfaces of the wings; the empennage is provided with a horizontal tail and two vertical tails, and the two vertical tails are arranged at two ends of the horizontal tail respectively. Due to arrangement of the two vertical tails, high aerodynamic efficiency can be achieved by taking full advantage of acceleration action of propeller slipstream. In addition, the propeller airplane is high in structural bearing strength and light in weight.

Description

A kind of propeller aeroplane

Technical field

The present invention relates to technical field of aerospace, particularly relate to a kind of propeller aeroplane.

Background technology

Aircraft is provided power by one or more propulsion units, and described propulsion unit includes being contained in nacelle Whirlpool spray or turbo oar engine, each propulsion unit is connected in aircraft by hanger, and described nacelle is arranged on On wing.Although aero propulsion device early has been enter into jet age, but turboprop is at low subsonics Have that pulling force is big, propulsive efficiency is high, the feature of good economy performance during speed flight so that it is at aircraft circles especially It is that transporter field still has critical role.Engine nacelle, as the critical component of aircraft, is layout research One of key content.

The propeller aeroplane screw tension coefficient using wing hanging layout is big, and slip-stream is strong, typically results in liter Power and resistance increase, and horizontal tail flow field also can be produced by pitching moment acute variation when horizontal tail is flow through in slip-stream Considerable influence, makes aircraft stability and maneuverability produce great changes, jeopardizes flight safety time serious.

Thus, it is desirable to have a kind of technical scheme overcomes or at least to alleviate at least one of prior art above-mentioned Defect.

Summary of the invention

It is an object of the invention to provide a kind of propeller aeroplane overcome or at least alleviate prior art extremely A few drawbacks described above.

For achieving the above object, the present invention provides a kind of propeller aeroplane, and described propeller aeroplane includes machine The wing, fuselage, two nacelles and empennage, two nacelles are arranged on described wing, described in one of them Nacelle is arranged on the side being positioned at fuselage of described wing, and another described nacelle is arranged on described wing It is positioned at the opposite side of fuselage, and two described nacelles are arranged on described upper surface of the airfoil, and described empennage sets Being equipped with tailplane and two vertical tails, a described vertical tail is arranged on described tailplane One end, another described vertical tail is arranged on the other end of described tailplane.

Preferably, described wing span is between 19 to 29m.

Preferably, described aspect ratio is between 6 to 14.

Preferably, point chord length is between 1.0 meters to 1.5 meters.

Preferably, root chord length between 3.6 meters to 4.1m, wing root established angle between 2 ° to 5 °, Wing tip established angle is between 0 ° to 2 °.

Preferably, the wing upper counterangle between 1 ° to 4 °, leading edge sweep between 5 ° to 10 °, Trailing edge sweepforward angle is between 1 ° to 7 °.

Preferably, described tailplane trailing edge is provided with elevator, the side of being equipped with on each described vertical tail To rudder.

Preferably, area is wing area the 15% to 28% of described tailplane, before tailplane root string The edge distance away from main wing trailing edge is 1.3 to 2.0 times of main wing root chord length, and the distance away from level reference is 0.4 to 0.7 times of tailplane root chord length.

Preferably, area is wing area the 15% to 21% of each described vertical tail, vertical tail The root string leading edge distance away from trailing edge is 1.3 to 2.0 times of wing root chord length, and vertical tail is arranged on On horizontal tail wing tip.

Screw in the present invention uses twin-finned layout, and the acceleration that can make full use of propellerslip is made With, pneumatic efficiency is high.Structure-bearing characteristic is good, lightweight.

Accompanying drawing explanation

Fig. 1 is the structural representation of propeller aeroplane according to an embodiment of the invention.

Reference

1 Wing 4 Empennage 2 Fuselage 5 Tailplane 3 Nacelle 6 Vertical tail

Detailed description of the invention

Clearer, below in conjunction with the present invention for the purpose making the present invention implement, technical scheme and advantage Accompanying drawing in embodiment, is further described in more detail the technical scheme in the embodiment of the present invention.Attached In figure, the most same or similar label represents same or similar element or has same or like The element of function.Described embodiment is a part of embodiment of the present invention rather than whole enforcement Example.The embodiment described below with reference to accompanying drawing is exemplary, it is intended to be used for explaining the present invention, and It is not considered as limiting the invention.Based on the embodiment in the present invention, those of ordinary skill in the art The every other embodiment obtained under not making creative work premise, broadly falls into present invention protection Scope.Below in conjunction with the accompanying drawings embodiments of the invention are described in detail.

In describing the invention, it is to be understood that term " " center ", " longitudinally ", " horizontal stroke To ", "front", "rear", "left", "right", " vertically ", " level ", " push up ", " end " " interior ", the orientation of the instruction such as " outward " or position relationship are based on shown in the drawings Orientation or position relationship, be for only for ease of the description present invention and simplify description rather than instruction or hint The device of indication or element must have specific orientation, with specific azimuth configuration and operation, the most not It is understood that as limiting the scope of the invention.

Fig. 1 is the structural representation of propeller aeroplane according to an embodiment of the invention.

Propeller aeroplane as shown in Figure 1 includes wing 1,2, two nacelles 3 of fuselage and empennage 4, Two nacelles 3 are arranged on wing 1, and what one of them nacelle 3 was arranged on wing 1 is positioned at the one of fuselage Side, another nacelle 3 is arranged on the opposite side being positioned at fuselage of wing 1, and two nacelles 3 are arranged on machine Wing upper surface (the wing top position in Fig. 1), empennage 4 is provided with tailplane 5 and two and hangs down Fin 6, a vertical tail 6 is arranged on one end of tailplane 5, and another vertical tail 6 is arranged The other end at tailplane 5.

Nacelle is arranged on above wing, including install screw propeller hub, can be by air flow helical turbine The air inlet leading portion that paddle motor compressor guides;For the stage casing around engine core machine;Encase jet pipe Rear, landing gear compartment.

Nacelle bottom is landing gear compartment, and blade tip overhead has sufficiently high gap, the air-flow of jet pipe ejection Having little to no effect aircraft flap, nacelle meets aerodynamics continuity, reduces stone or rubble is inhaled Enter.

Advantageously, the span of wing 6 is between 19 to 29m.

Advantageously, in propeller aeroplane, aspect ratio is between 6 to 14.This high aspect ratio wing Induced drag can be reduced, improve maximum lift-drag ratio, obtain good voyage performance.

Advantageously, in propeller aeroplane, point chord length is between 1.0 meters to 1.5 meters.

Advantageously, in propeller aeroplane, root chord length between 3.6 meters to 4.1m, wing root established angle Between 2 ° to 5 °, wing tip established angle is between 0 ° to 2 °.

Advantageously, in propeller aeroplane, the wing upper counterangle between 1 ° to 4 °, leading edge sweep Between 5 ° to 10 °, trailing edge sweepforward angle is between 1 ° to 7 °.

Advantageously, in propeller aeroplane, tailplane trailing edge is provided with elevator, each vertical tail On be equipped with rudder.

Advantageously, in propeller aeroplane, area is wing area the 15% to 28% of tailplane, Away from main wing trailing edge 1.3 to 2.0 times that distance is main wing root chord length of tailplane root string leading edge, away from level The distance of datum level is 0.4 to 0.7 times of tailplane root chord length.

Advantageously, in propeller aeroplane, the area of each vertical tail be wing area 15% to 21%, the root string leading edge of vertical tail away from trailing edge distance is wing root chord length 1.3 to 2.0 Times, vertical tail is arranged on horizontal tail wing tip.

In one embodiment, wing span is 25m, and aspect ratio is 9.0, point chord length 1.320m, root Chord length 3.960m, wing root established angle 3.5 °, wing tip established angle 0.5 °, 2.5 ° of the wing upper counterangle, Leading edge sweep 8 °, trailing edge sweepforward angle 4 °.The area of tailplane is the 23% of wing area, level The tail wing root chord leading edge distance away from main wing trailing edge is 1.4 times of main wing root chord length, away from level reference Distance is 0.6 times of tailplane root chord length.Twin-finned area is the 17% of wing area, hangs down Away from main wing trailing edge 1.7 times that distance is main wing root chord length of fin root string leading edge, vertical tail is installed On horizontal tail wing tip.

Propeller aeroplane in this embodiment have passed through CFD and calculates and wind tunnel test, has higher longitudinal direction And Lateral-directional static stability.It is high that propellerslip increases considerably twin vertical fin pneumatic efficiency.The lowest, knot Structure load characteristic is good, lightweight, integral rigidity characteristic is good.

Last it is noted that above example is only in order to illustrate technical scheme, rather than right It limits.Although the present invention being described in detail with reference to previous embodiment, the common skill of this area Art personnel it is understood that the technical scheme described in foregoing embodiments still can be modified by it, Or wherein portion of techniques feature is carried out equivalent;And these amendments or replacement, do not make corresponding The essence of technical scheme departs from the spirit and scope of various embodiments of the present invention technical scheme.

Claims (9)

1. a propeller aeroplane, described propeller aeroplane include wing (1), fuselage (2), two short Cabin (3) and empennage (4), it is characterised in that two nacelles (3) are arranged at described wing (1) On, one of them described nacelle (3) is arranged on the side being positioned at fuselage of described wing (1), another Described nacelle (3) is arranged on the opposite side being positioned at fuselage of described wing (1), and two described nacelles (3) It is arranged on described upper surface of the airfoil, described empennage (4) is provided with tailplane (5) and two vertical Empennage (6), a described vertical tail (6) is arranged on one end of described tailplane (5), another Individual described vertical tail (6) is arranged on the other end of described tailplane (5).
2. propeller aeroplane as claimed in claim 1, it is characterised in that the wing of described wing (6) Exhibition is between 19 to 29m.
3. propeller aeroplane as claimed in claim 2, it is characterised in that at described propeller aeroplane In, aspect ratio is between 6 to 14.
4. propeller aeroplane as claimed in claim 3, it is characterised in that at described propeller aeroplane In, point chord length is between 1.0 meters to 1.5 meters.
5. propeller aeroplane as claimed in claim 4, it is characterised in that at described propeller aeroplane In, root chord length between 3.6 meters to 4.1m, wing root established angle between 2 ° to 5 °, wing tip established angle Between 0 ° to 2 °.
6. propeller aeroplane as claimed in claim 5, it is characterised in that at described propeller aeroplane In, the wing upper counterangle between 1 ° to 4 °, leading edge sweep between 5 ° to 10 °, trailing edge sweepforward Angle is between 1 ° to 7 °.
7. propeller aeroplane as claimed in claim 6, it is characterised in that at described propeller aeroplane In, described tailplane trailing edge is provided with elevator, and each described vertical tail is equipped with rudder.
8. propeller aeroplane as claimed in claim 7, it is characterised in that at described propeller aeroplane In, area is wing area the 15% to 28% of described tailplane, tailplane root string leading edge is away from main wing The distance of trailing edge is 1.3 to 2.0 times of main wing root chord length, and the distance away from level reference is tailplane 0.4 to 0.7 times of root chord length.
9. propeller aeroplane as claimed in claim 7, it is characterised in that in described propeller aeroplane, Area is wing area the 15% to 21% of each described vertical tail, the root string leading edge of vertical tail is away from machine The distance of wing trailing edge is 1.3 to 2.0 times of wing root chord length, and vertical tail is arranged on horizontal tail wing tip.
CN201610312234.9A 2016-05-12 2016-05-12 Propeller airplane CN105857579A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201610312234.9A CN105857579A (en) 2016-05-12 2016-05-12 Propeller airplane

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201610312234.9A CN105857579A (en) 2016-05-12 2016-05-12 Propeller airplane

Publications (1)

Publication Number Publication Date
CN105857579A true CN105857579A (en) 2016-08-17

Family

ID=56630864

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201610312234.9A CN105857579A (en) 2016-05-12 2016-05-12 Propeller airplane

Country Status (1)

Country Link
CN (1) CN105857579A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107697269A (en) * 2017-09-30 2018-02-16 中国航空工业集团公司西安飞机设计研究所 A kind of propeller aeroplane

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2010003698A1 (en) * 2008-07-11 2010-01-14 Airbus Operations Gmbh Aircraft with at least two propeller drives arranged at a distance from one another in the span width direction of the wings
CN101927825A (en) * 2008-09-05 2010-12-29 龙川 Single aircraft
CN104290906A (en) * 2014-11-04 2015-01-21 中国人民解放军国防科学技术大学 Vertical take-off and landing aircraft
CN104973234A (en) * 2015-06-02 2015-10-14 龙川 Aircraft using distributed electric ducted fan flap lift-rising system

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2010003698A1 (en) * 2008-07-11 2010-01-14 Airbus Operations Gmbh Aircraft with at least two propeller drives arranged at a distance from one another in the span width direction of the wings
CN101927825A (en) * 2008-09-05 2010-12-29 龙川 Single aircraft
CN104290906A (en) * 2014-11-04 2015-01-21 中国人民解放军国防科学技术大学 Vertical take-off and landing aircraft
CN104973234A (en) * 2015-06-02 2015-10-14 龙川 Aircraft using distributed electric ducted fan flap lift-rising system

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107697269A (en) * 2017-09-30 2018-02-16 中国航空工业集团公司西安飞机设计研究所 A kind of propeller aeroplane

Similar Documents

Publication Publication Date Title
EP2878538B1 (en) An aircraft
US9346537B2 (en) Winglet system
Seifert A review of the Magnus effect in aeronautics
CN105173061B (en) Plane in supersonic speed plane layout
US20190233089A1 (en) Split Blended Winglet
US7861967B2 (en) Aircraft with integrated lift and propulsion system
US5082204A (en) All wing aircraft
US6923403B1 (en) Tailed flying wing aircraft
US4519746A (en) Airfoil blade
RU2531537C2 (en) Aircraft with lambda-like wing configuration
CN101559832B (en) Fast hybrid helicopter with large range
CN206012959U (en) A kind of how culvert vertical take-off and landing unmanned machine
EP0716978B1 (en) Large dimension aircraft
US3179354A (en) Convertiplane and apparatus thereof
CN101875399B (en) Tilt rotor aircraft adopting parallel coaxial dual rotors
US4828204A (en) Supersonic airplane
US6578798B1 (en) Airlifting surface division
US9440740B2 (en) Oblique blended wing body aircraft
US5242132A (en) Multi-hulled aircraft/boat
US3625459A (en) Airfoil design
CN102282070B (en) Horizontal stabilising surface of an aircraft
US7802754B2 (en) Tilt outboard wing for tilt rotor aircraft
US7980515B2 (en) Aircraft wing modification and related methods
CN103144769B (en) Pneumatic layout of vertical taking-off and landing aircraft with tilted duct
US5681014A (en) Torsional twist airfoil control means

Legal Events

Date Code Title Description
C06 Publication
PB01 Publication
C10 Entry into substantive examination
SE01 Entry into force of request for substantive examination
RJ01 Rejection of invention patent application after publication
RJ01 Rejection of invention patent application after publication

Application publication date: 20160817