WO2021019487A1 - Fuselage d'un aéronef de transport léger - Google Patents

Fuselage d'un aéronef de transport léger Download PDF

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Publication number
WO2021019487A1
WO2021019487A1 PCT/IB2020/057200 IB2020057200W WO2021019487A1 WO 2021019487 A1 WO2021019487 A1 WO 2021019487A1 IB 2020057200 W IB2020057200 W IB 2020057200W WO 2021019487 A1 WO2021019487 A1 WO 2021019487A1
Authority
WO
WIPO (PCT)
Prior art keywords
radii
arcs
cross
section
aircraft
Prior art date
Application number
PCT/IB2020/057200
Other languages
German (de)
English (en)
Inventor
Alexandr N. KORNEEV
Viktor K. SOLOVYOV
Original Assignee
Research And Enginnering Company Llc (Nik)
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 Research And Enginnering Company Llc (Nik) filed Critical Research And Enginnering Company Llc (Nik)
Priority to EP20760542.9A priority Critical patent/EP3924249A1/fr
Publication of WO2021019487A1 publication Critical patent/WO2021019487A1/fr

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/0009—Aerodynamic aspects
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/061—Frames
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/068—Fuselage sections
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
    • B64C1/1407—Doors; surrounding frames
    • B64C1/1415—Cargo doors, e.g. incorporating ramps
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C2001/0045—Fuselages characterised by special shapes

Definitions

  • the present invention relates to the field of aircraft construction, namely to the type of fuselage of transport aircraft.
  • Aircraft fuselages of various cross-sectional shapes are currently known.
  • the size and shape of the fuselage cross-section are determined by the intended use of the aircraft.
  • the shape of the fuselage cross-section of an aircraft varies from round to rectangular to an intermediate oval shape with different ratios of the main dimensions of width and height.
  • the shape of the fuselage cross-section of transport aircraft is determined by the largest dimensions of the transported goods.
  • the dimensions of the transported freight, which are decisive for the transport, are becoming increasingly important, especially for light aircraft / small aircraft.
  • An aircraft is known (Al Kowaljow "Das L-410 UVP-Flugzeug", Verlag “Transport” 1988) with a fuselage consisting of a strength association, which includes reinforced and normal frames, longitudinal stiffeners (stringers) and a smooth load-bearing outer skin. Frames and longitudinal stiffeners form a framework. The load-bearing outer skin is connected to the framework. The fuselage cross-section has a rectangular shape, the rectangle having rounded corners. The ratio of the car width to the car height is 1.15.
  • the cargo version of the aircraft is equipped with a large cargo hatch in the rear of the fuselage. The cargo hatch is designed for loading the cargo to be transported. No pivoting loading ramps or cargo hatches are provided in the aircraft.
  • the fuselage of the aircraft is short and has a rectangular cross-sectional shape with rounded corners. Such a shape of the fuselage cross-section enables even large self-propelled machines of the vehicle type "Jeep" to be accommodated therein.
  • the fuselage has poor flow. This creates additional aerodynamic resistance.
  • the aircraft is equipped with a flat folding ramp. The ramp enables large vehicles to be loaded using their own propulsion power.
  • a fuselage of an aircraft is known (RU 2481236, B64C 1/00).
  • the fuselage comprises a front, a middle and a rear part.
  • the cross-sectional shape of the central part of the fuselage is flattened and consists of four circular arc sections connected one behind the other.
  • the radius of curvature of the arcs that correspond to the top and bottom of the fuselage is greater than the radius of curvature of the arcs that correspond to the sides of the fuselage.
  • the flattened shape of the fuselage helps to increase the usable volume and offers additional space for accommodating passengers and cargo in the aircraft cabin.
  • this fuselage shape ensures better aerodynamics compared to the conventional cylindrical cross-section.
  • An oval shape of the fuselage cross-section, which is only formed by two radii, is not, however, optimized for a specifically specified payload. This is particularly relevant with regard to light short-haul transport aircraft.
  • the aircraft which is closest to the present invention has a fuselage with a non-circular cross-section. Its shape is formed by four circular sections on the top, bottom and both sides. These four sections are executed by three radii.
  • a downwardly pivotable loading ramp is arranged in the rear part of the fuselage.
  • the proposed fuselage arrangement makes it relatively easy to convert the aircraft from a passenger version to a cargo version and back.
  • the proposed hull arrangement enables large containers to be loaded through a cargo hatch in the rear part of the hull.
  • the shortcoming of this technical solution consists in the impossibility of obtaining an optimal fuselage cross-section by creating four circular segments that are executed by three radii.
  • the object of the present invention is to expand the functionality and efficiency of a light transport aircraft that is designed for use on short routes.
  • the technical effect to be achieved through the application of the invention is to enable loading and unloading as well as the transport of various loads with the maximum possible dimensions for this aircraft class. At the same time, maximum rigidity and strength of the fuselage and good aerodynamic properties of the aircraft are achieved.
  • the shaping according to the invention of the aircraft fuselage in a front, rear and, in particular, central part is achieved by the shaping according to the invention of the aircraft fuselage in a front, rear and, in particular, central part.
  • the front part has a shape that tapers towards the fuselage nose which is favorable to the flow.
  • the central part has an elliptical-cylindrical shape with a constant cross section along the longitudinal axis of the aircraft.
  • the rear part has a convergent, aerodynamically favorable shape that tapers towards the end of the fuselage.
  • a width of the middle part is greater than a height of the middle part.
  • the outline of the cross section of the middle part is formed by a connection of at least eight arcs. These are designed with at least five radii.
  • the outline has arcs on its top and bottom, the two sides and connecting arcs between the top and bottom and the sides.
  • the centers of the radii of the arches, the top and bottom lie on a vertical axis of symmetry of the cross section of the central part.
  • the centers of the radii of the lateral arcs are shifted in relation to the axis of symmetry of the aircraft.
  • the radii of the connecting arcs of the top and the sides are larger than the radii of the connecting arcs of the bottom and the sides.
  • the centers of the radii of the connecting arches of the upper The te and the sides are arranged horizontally at a smaller distance from one another than the centers of the radii of the connecting arcs of the underside and the sides.
  • a cargo flap system is mounted in the opening of the loading hatch, comprising a downwardly pivotable loading ramp, lateral outwardly pivotable flaps and an upwardly pivotable central flap.
  • the outline of the cross section of the middle part is designed with a ratio of the total width to the total height of 1.33.
  • the outline of the cross section of the central part is formed by arcs with the following relative radii in relation to the height of the central part: arcs of the top - 1.07H, arcs of the underside - 3.11 H, arcs of the sides - 0.91 H , upper connecting arcs - 0.38H and lower connecting arcs - 0.24H.
  • the center points of the radii of the arcs of the sides are arranged as the corresponding arcs in relation to the vertical axis of symmetry of the cross section of the central part on the respective opposite side of the axis of symmetry.
  • the cargo flap system is mounted in the opening of the loading hatch and, when closed, forms the strength association of the rear part (3) with the surrounding structures of the construction.
  • the claimed aircraft fuselage (FIG. 1) has a front part 1, a middle part 2 and a rear part 3.
  • the front part 1 has a shape that is favorable for flow and tapers along the longitudinal axis of the aircraft towards the nose of the fuselage.
  • the central part 2 is designed in the form of an elliptical cylinder with a constant cross section along the longitudinal axis of the aircraft.
  • the rear part 3 has a convergent shape which is favorable in terms of flow technology and which tapers towards the end of the fuselage along the longitudinal axis of the aircraft.
  • the middle part 2 of the fuselage in the form of an elliptical cylinder has a complex cross-sectional shape with a horizontal alignment of the major axis of the ellipse.
  • the fuselage cross-section has a ratio of the overall dimensions of the width B to the height H of 1, 33 executed.
  • the shape of the fuselage cross-section is carried out by means of a geometric construction using arches with different radii R1 -R5. This cross-sectional shape best meets the requirement of minimizing the cross-sectional area, while at the same time storing and transporting large cargo including self-propelled wheeled vehicles and good aerodynamic flow conditions.
  • the optimized shape of the fuselage cross-section of the middle part 2 according to the invention is formed by the construction of arches with several radii R1-R5, including: an arch of the upper side with a radius R1, an arch of the upper side with a radius R5, arcs of the sides with radii R3, upper connecting arcs with radii R2 and lower connecting arcs with radii R4.
  • This shape of the fuselage cross-section offers the following advantages compared to the round shape with an equivalent area: Increase in width by 9% and decrease in height by 16%.
  • Fig. 3 shows the relationship between the proposed and a round hull shape with the same cross-sectional area. It shows that the proposed cross-section has a filling in the lower half of the cross-section.
  • the increase in the width of the cross-section of the fuselage in its lower part enables air cargo containers such as 2AK-0.7 and LD3-45 or self-propelled vehicles such as UAZ "Patriot” etc. to be freely positioned.
  • the existing aircraft generally have a relative fuselage cross-section of around 10% in relation to the ratio of the largest fuselage cross-sectional area to the wing area.
  • the fuselages of the existing aircraft are compact, which can be traced back to the endeavor to find a reasonable compromise between the aerodynamic resistance of the aircraft fuselage, its weight and its capacity. Comparable fuselage cross-sectional dimensions of the central part of other aircraft in relation to the cross-section of the invention are shown in FIG.
  • the existing aircraft of the types An-28, An-38, L-410, Short SC.7, Do-228, Twin Otter, Y-12F (China) with a take-off weight of up to 8600 kg are manufactured according to the conventional aerodynamic scheme.
  • the fuselages of these aircraft are rectangular in shape with rounded corners.
  • the aircraft cabins of these aircraft can contain two to three seats in a row, either according to a seating configuration "1 + 1" or according to a seating configuration "1 + 2".
  • Characteristic features of the invention include a specific shape of the cross section. The size of the cross-section with this shape considerably exceeds all known closest technical solutions.
  • the cabin width according to the proposed technical solution corresponds to the maximum cabin width of the widest solution of the L-410 to date ( 1.92m) by 36%.
  • the cabin height exceeds the maximum cabin height of the so far highest solution of the Y-12F (1.84m) by 10%.
  • the proposed invention enables five seats to be accommodated in a row in the passenger version according to a seat configuration "2 + 3" (FIG. 5).
  • a system of cargo flaps 4, 5, 6 (FIG. 6) is provided for carrying out loading and unloading work in the tapering rear part of the fuselage 3.
  • the system has a downwardly pivotable loading ramp 4, lateral outwardly pivotable flaps 5 and a narrow central flap 6.
  • the loading ramp 4 is used for loading, unloading and storing goods to be transported.
  • the lateral leaf-shaped flaps 5 (FIG.
  • the loading ramp 4 forms an extension of the loading area on which the payload can be placed.
  • the cargo flap system of the cargo hold offers various possibilities to use the flaps 5, 6 and the loading ramp 4 in different configurations. At the same time, all the flaps 5, 6 and the loading ramp 4 are only opened on the ground during the loading and unloading work.
  • the maximum efficiency can be achieved with the invention in relation to light transport aircraft if the total area of the transported one-piece cargo takes up a considerable area of the cargo hold of the aircraft.
  • the proposed shape of the fuselage cross-section of the central part 2 enables the width of the cargo floor to be increased significantly. As a result, the overall length of the aircraft can in turn be reduced by maintaining the permissible center of gravity range.
  • the proposed system of cargo flaps 4, 5, 6 and the methods for opening them make it possible to carry out loading and unloading work using loading-optimized technology and systems in the convergent rear part of the fuselage.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Body Structure For Vehicles (AREA)

Abstract

Le but de la présente invention est d'améliorer la fonctionnalité et l'efficacité d'un aéronef léger conçu pour être utilisé sur des voies de petits courriers. L'effet technique devant être atteint au moyen de cette invention est de permettre le chargement et le déchargement et le transport de marchandises différentes présentant des dimensions maximales possibles pour cette classe d'aéronefs. En même temps, la rigidité et la résistance maximales du fuselage et de bonnes propriétés aérodynamiques de l'aéronef sont obtenues.
PCT/IB2020/057200 2019-08-01 2020-07-30 Fuselage d'un aéronef de transport léger WO2021019487A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP20760542.9A EP3924249A1 (fr) 2019-08-01 2020-07-30 Fuselage d'un aéronef de transport léger

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
RU2019124498 2019-08-01
RU2019124498 2019-08-01

Publications (1)

Publication Number Publication Date
WO2021019487A1 true WO2021019487A1 (fr) 2021-02-04

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/IB2020/057200 WO2021019487A1 (fr) 2019-08-01 2020-07-30 Fuselage d'un aéronef de transport léger

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EP (1) EP3924249A1 (fr)
CN (1) CN213008694U (fr)
WO (1) WO2021019487A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113139235B (zh) * 2021-04-22 2022-10-28 贵州天义电器有限责任公司 一种飞机曲面配电装置的设计方法

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB560580A (en) * 1942-11-13 1944-04-11 Laurence Rachard Morphew Improvements in or relating to the construction of streamlined panel structures
DE1217213B (de) * 1964-05-08 1966-05-18 Dornier Werke Gmbh Heckladepforte fuer Transportflugzeuge
RU2148534C1 (ru) 1996-05-14 2000-05-10 АО Авиационный научно-технический комплекс им.А.Н.Туполева Самолет (варианты)
US20030062451A1 (en) * 2001-10-02 2003-04-03 Sankrithi Mithra M.K.V. Cargo loading means for short body airplanes
US20120068014A1 (en) * 2010-09-16 2012-03-22 Airbus Operations Gmbh Segment of a fuselage of an aircraft
RU2481236C2 (ru) 2006-12-26 2013-05-10 Эрбюс Фюзеляж летательного аппарата

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB560580A (en) * 1942-11-13 1944-04-11 Laurence Rachard Morphew Improvements in or relating to the construction of streamlined panel structures
DE1217213B (de) * 1964-05-08 1966-05-18 Dornier Werke Gmbh Heckladepforte fuer Transportflugzeuge
RU2148534C1 (ru) 1996-05-14 2000-05-10 АО Авиационный научно-технический комплекс им.А.Н.Туполева Самолет (варианты)
US20030062451A1 (en) * 2001-10-02 2003-04-03 Sankrithi Mithra M.K.V. Cargo loading means for short body airplanes
RU2481236C2 (ru) 2006-12-26 2013-05-10 Эрбюс Фюзеляж летательного аппарата
US20120068014A1 (en) * 2010-09-16 2012-03-22 Airbus Operations Gmbh Segment of a fuselage of an aircraft

Non-Patent Citations (3)

* Cited by examiner, † Cited by third party
Title
"PZL M28 Skytruck", 24 July 1993 (1993-07-24), XP002800873, Retrieved from the Internet <URL:https://en.wikipedia.org/wiki/PZL_M28_Skytruck> [retrieved on 20201029] *
"PZL-Mielec reveals 30-seater Skytruck stretch", 10 September 1997 (1997-09-10), XP002800874, Retrieved from the Internet <URL:https://www.flightglobal.com/pzl-mielec-reveals-30-seater-skytruck-stretch/11562.article> [retrieved on 20201029] *
A.I. KOWALJOW: "Das L-410 UVP-Flugzeug", 1988, VERLAG ''TRANSPORT

Also Published As

Publication number Publication date
CN213008694U (zh) 2021-04-20
EP3924249A1 (fr) 2021-12-22

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