Search Images Maps Play YouTube News Gmail Drive More »
Sign in
Screen reader users: click this link for accessible mode. Accessible mode has the same essential features but works better with your reader.


  1. Advanced Patent Search
Publication numberUS3405893 A
Publication typeGrant
Publication dateOct 15, 1968
Filing dateOct 13, 1966
Priority dateOct 15, 1965
Also published asDE1481622A1
Publication numberUS 3405893 A, US 3405893A, US-A-3405893, US3405893 A, US3405893A
InventorsClaude Flamand, Michel Lazareff, Fernand Rajau
Original AssigneeNord Aviat Soc Nationale De Co
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Large capacity fuselage and corresponding aerodyne
US 3405893 A
Abstract  available in
Previous page
Next page
Claims  available in
Description  (OCR text may contain errors)

Oct. 15, 1968 c. FLAMAND ETAL 3,405,893

LARGE CAPACITY FUSELAGE AND CORRESPONDING AERODYNE Filed Oct. 13, 1966 5 Sheets-Sheet l V w SEES Oct. 15,1968 A A D ETAL 3,405,893


0d. 15, 1968 c, FLAMAND ETAL 3,405,893

LARGE CAPACITY FUSELAGE AND CORRESPONDING AERODYNE Filed 001;. 13, 1966 3 Sheets-Sheet 5 Section] Sec rion.5

United States Patent 3,405,893 LARGE CAPACITY FUSELAGE AND CORRESPONDING AERODYNE Claude Flamand, Chatenay, Michel Lazaretf, Paris, and

Fernand Rajau, Sevres, France, assignors to Nord- Aviation Societe Nationale de Constructions Aeronautiques, Paris, France, a joint-stock company of France Filed Oct. 13, 1966, Ser. No. 586,553 Claims priority, applicatignzFrance, Oct. 15, 1965,

35, 3 6 Claims. (Cl. 244-119) ABSTRACT OF THE DISCLOSURE A large capacity fuselage for an aerodyne comprising hollow longitudinal lobes forming side by side compartments having fiat faces adjacent each other forming a common connecting wall in a vertical plane, with an outer envelope surrounding the lobes to form the outer surface of the fuselage.

The present invention relates to a large capacity fuselage, adapted to any form of aerodyne, passenger, freight or mixed.

It also relates to all aerodynes provided with a fuselage such as defined hereinbelow.

The problems arising from the increase in air traffic and the need to increase the useful transportable volume, whether it be the number of passengers or space for freight, are well known.

The solutions to these problems which are now known consist either of lengthening a classical type fuselage or in superposing such fuselages to form an assembly of several decks.

But the difficulties inherent in both these solutions are essentially due, in the first solution to the difiieulty of centering the apparatus, as well as the tunnel effect caused by a too long fuselage, increasing the difficulties of movement, whilst the second solution requires openings at different levels, or means of access between decks, such as lifts, stairs and the like, which reduce the space available and increase structural masses. Furthermore, by increasing the longitudinal surface, both solutions increase lateral wind hold.

The present invention has none of the above-mentioned drawbacks.

Its object is to supply in a simple manner, a fuselage having several lobes such that:

Each lobe is served by an independent passageway and has its own exits;

The lobes intercommunicate by simple openings;

One or more lobes may be used exclusively for passenger or freight transport;

Lateral wind hold is reduced;

The fuselage shape is suitable for pressurization and of simple, light construction, and furthermore has a large underdeck area where vast cargo-compartments may be installed.

With these ends in view, the large capacity fuselage according to the invention is essentially characterized by the fact that it consists of an association of hollow longitudinal members or lobes, forming as many compartments disposed side by side in a same horizontal plane, and rigidly secured to one another so that the said members enable a compact fuselage to be formed.

According to a special form of embodiment the fuselage comprises two adjacent lobes or compartments.

According to other characteristics:

The hollow members or lobes of the fuselage are connected in pairs by a central girder which may include openings adapted to provide intercommunication of the compartments;

An outer strong, airtight envelope entirely surrounds the assembly of 'lobes or longitudinal members which form the fuselage;

The spaces between the outer envelope and the fuse lage lobes permits the connecting members, piping, cables etc., with which the aerodyne is equipped to be passed through them.

The invention also relates to any areodyne equipped with a fuselage according to the invention.

Thus, and according to other characteristics of these said aerodynes equipped with said fuselage, and which will be explained in greater detail in the following text.

In a first version:

The lower portion of the fuselage is provided with a series of retractable plates disposed symmetrically with respect to the central girder or girders which interconnect the lobes, these said plates constituting cargo-compartments which are easily accessible from the ground;

The propulsion unit as well as the horizonal and vertical tail units are disposed in a known manner on the rear portion of the fuselage, these three members being connected to a triangular frame or structure rigidly secured to the central girder.

And according to a second variant:

The wings unit is in a raised position resting on the pressurized lobes without passing through them, and thereby procuring advantages such that on the one hand the fiat-fuselage-high wing interaction improves the hypersustentation and leads, for a given approach speed, to a reduction in the surface of the wings, and on the other hand, the fatigue resistance of the fuselage structure is increased because the only openings formed are those necessitated by the landing gear bays.

Owing to the landing gear being in a low position, it is short and therefore light and further leads only to slight interaction between the said landing gear and the flaps.

Other advantages and characteristics of the present invention will be brought out from the description which follows with reference to the attached drawings, in which have been shown as an example, two preferred forms of large capacity aerodynes, equipped with a fuselage hav ing two horizontally disposed lobes or adjacent compartments.

FIGURE 1 shows diagrammatically in perspective and partial cross-section, a section of the fuselage according to the invention, the said fuselage being that utilized in the two preferred forms of embodiment of the invention.

FIGURES 2, 3 and 4 show the low winged aerodyne according to a first form of embodiment, respectively in profile, from the front and from above.

FIGURES 5 and 6 to 8 respectively show longitudinal and transversal cross section according to lines 66, 7-7 and 8-8 of FIGURE 5 of the high wing aerodyne according to a second form of preferred embodiment.

FIGURE 9 shows diagrammatically and according to a longitudinal horizontal cross-section of the fuselage of FIGURE 1 a possible mixed freight, passenger embodiment.

FIGURE 10 shows a front view of the aerodyne according to the second form of embodiment.

Referring to FIGURE 1, a section of fuselage 1 is shown including two lobes consisting of the symmetrical jackets 2 and 3 of cylindrical form, of about 3.50 m. diameter for instance, the said jacket constituting the inner pressure-tight partitions of the two compartments of fuselage l. The two lobes or jackets 2 and 3 are moreover rigidly secured and disposed symmetrically with respect to a central girder 4 on which they interconnect.

An outer envelope 5 of oval form and made of a strong metal surrounds lobes 2 and 3 and is tangential to them on the lateral surfaces whilst a space 16 at its upper portion is left free between the arc of the longest radius of the outer envelope, of about 7.5 m. for example, and the upper surfaces of lobes 2 and 3.

The same outer casing 5 is also tangential to the lower portion of lobes 2 and 3. A common deck 6 for both lobes 2 and 3 defines the usable volume whilst an air-tight partition 7 defines the pressurized volume In.

Classical frames 8 help to provide resistance and rigid-- ity of the fuselage assembly.

Such a bi-lobed disposition provides, by its geometrical configuration. numerous advantages, and amongst others:

A great ability to resist internal pressure, a free space at the upper portion through which channels, cables and other connections 9 can be passed, and which are also easy to visit through trap doors 10 of easy access;

A space under the deck for the installation of vast luggage bays easily accessible from the ground;

Useful width of compartments permitting, for example,

two rows of five seats 13 each, which would, for example allow two hundred and fifty places in twenty five rows, and a free passage between rows by means of openings 14; Furthermore, this same bi-lobed disposition permits the construction;

(1) Of an aerodyne such as it is shown in FIGURES 2, 3 and 4 where it is visible that the portion 112 of fuselage 1 prolonging the pressurized portion 1a, may receive the propulsion units lb [a, b, c, d] supplied with air by lateral intakes 1b.; and 1b. the horizontal lb and vertical 1/1 tail fins, members lb lb 112 being rigidly secured to a triangular frame 25 shown in FIG. 2 which is rigidly connected to central girder 4 with girder 4 extending into tail portion lb This device also allows positioning of retractable plates 12 for luggage 17 to be integrated in the fuselage whereby the said central girder 4 is not interrupted and also housing of fiying surface 11 which may be a single unit.

Grouping of propulsion units in this present version makes it possible to obtain reduction of aerodynamic drag owing to the filling of the base by jets of air, good introduction of thrust stresses onto the central girder 4, lessening of the lengths of piping and cables, leading to a substantial saving in weight and easy maintainance as the propulsion assembly constitutes a single engine chamber easily, accessible from the ground. It is furthermore evident, in this disposition, that passengers may embark very quickly and easily, especially by the integrated access stairs disposed at the ends of the bays.

(2) An aerodyne such as shown in FIGURES 5, 6, 7, 8 and 10, where it is seen that the flying surface 18 is positioned high on the lobes without passing through them, landing gears 19 and 20 are short andcompletely housed in lower bays 21 and 22 under the deck after retraction. This first disposition also permits of the lateraliy accessible compartments 23 being equipped with the usual handling apparatus and provides the additional advantages already described.

It is furthermore easy to see, from the diagrammatic representation of the loading plan, given as an example in 4 FIGURE 9, that seats 13 and freight 24 may occupy the whole and/or any proportion of the available space inside fuselage 1.

In particular, the fuselage may include a number of horizontally disposed lobes or compartments in excess of two, the version of the aerodyne may be of any type, a hospital aircraft, or other, and the aerodyne may be of any type, for example S.T.O.L (short take-off and landing aircraft) or V.T.O.L. (vertical takeoff and landing air craft).

We claim:

1. A large capacity fuselage for an aerodyne comprising a plurality of hollow longitudinal lobes each forming a compartment and being disposed side by side so that at least a pair of said lobes are on the same horizontal plane;

said pair of lobes each having a fiat face with their flat faces adjacent each other determining a common connecting vertical plane wall;

an outer envelope at least partially tangential to said lobes, partially tangentially supported on said lobes, and surrounding said lobes to form the outer surface of the fuselage;

said common connecting vertical plane wall forming a center girder of the fuselage having its upper and lower longitudinal edges spaced from said outer envelope.

2. A fuselage in accordance with claim 1 further characterized by said pair of said lobes having horizontal partiiions disposed in their lower portions and within said lobes to form a deck for each of said compartments formed within said lobes.

3. A fuselage for an aerodyne in accordance with claim 1 further characterized by said fuselage having a flying surface extending therefrom and attached thereto.

4. A fuselage for an aerodyne in accordance with claim 3 further characterized by said flying surface being a high flying surface comprising wings placed on and supported by said lobes without passing through them.

5. A fuselage for an aerodyne in accordance with claim 3 further characterized by said flying surface comprising wings extending from the lower portion of the fuselage.

6. A fuselage for an aerodyne in accordance with claim 3 further characterized by a triangular frame rigidly secured to said center girder at the rear of the fuselage and having a propelling group and horizontal and vertical tail units attached thereto.

References Cited UNITED STATES PATENTS 2,147,654 2/1939 Knight 244--1l7 X 2,162,227 6/1939 Page 244-119 2,236,482 3/1941 Lindel 244-419 2,967,034 1/1961 Eyre 244ll9 2,958,480 11/1960 Saulnier 2441l7 X MILTON BUCHLER, Primary Examiner.

T. W. BUCKMAN, Assistant Examiner.

Patent Citations
Cited PatentFiling datePublication dateApplicantTitle
US2147654 *Jun 26, 1936Feb 21, 1939Knight Herbert MAirship
US2162227 *Jan 13, 1938Jun 13, 1939Curtiss Wright CorpPressure fuselage
US2236482 *Sep 8, 1939Mar 25, 1941Messerschmitt Boelkow BlohmAirplane cabin
US2958480 *Jun 22, 1954Nov 1, 1960Raymond SaulnierAircraft with low aspect-ratio wing
US2967034 *Jun 16, 1958Jan 3, 1961Rolls RoyceDelta-wing aircraft construction
Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US4674712 *Jan 22, 1985Jun 23, 1987The Boeing CompanyDouble-lobe fuselage composite airplane
US5086996 *Jul 9, 1990Feb 11, 1992Airbus IndustrieHigh-capacity fuselage for aircraft
US5088661 *Apr 11, 1990Feb 18, 1992The Boeing CompanyAircraft
US5992797 *Sep 18, 1998Nov 30, 1999The Boeing CompanyDual upper deck airplane
US6047923 *Jan 13, 1995Apr 11, 2000Trimbach Turbine, Ltd.Aircraft having multiple fuselages
US6394392Oct 18, 2000May 28, 2002Trimbach Turbine, Ltd.Aircraft having multiple fuselages
US6834833 *Oct 2, 2001Dec 28, 2004The Boeing CompanyTwin aisle small airplane
US7191982 *Jun 2, 2005Mar 20, 2007Airbus FranceFloor for aircraft
US7252267 *Oct 17, 2003Aug 7, 2007The Boeing CompanyAircraft archway architecture
US7293739Dec 14, 2005Nov 13, 2007The Boeing CompanyAircraft archway
US7331545Dec 14, 2005Feb 19, 2008The Boeing CompanyAircraft archway
US7380752Apr 28, 2005Jun 3, 2008The Boeing CompanyAircraft interior architecture
US7395989 *Dec 20, 2005Jul 8, 2008AirbusAircraft fuselage and corresponding aircraft
US7448574Feb 15, 2008Nov 11, 2008The Boeing CompanyAircraft archway architecture
US7455263Apr 22, 2005Nov 25, 2008The Boeing CompanyAirplane interior systems
US7469860Jun 14, 2007Dec 30, 2008The Boeing CompanyAircraft archway architecture
US7475850 *Jun 3, 2005Jan 13, 2009Airbus FranceCockpit floor for aircraft
US7516919Oct 1, 2007Apr 14, 2009The Boeing CompanyAircraft archway architecture
US7618005 *Apr 25, 2007Nov 17, 2009Samuel Barran TafoyaStealth bomber, transporter, air-to-air fueling tanker, and space plane
US8025253Jul 8, 2005Sep 27, 2011Airbus Deutschland GmbhCommercial aircraft with a main deck and a lower deck
US8240607Jun 28, 2006Aug 14, 2012Airbus Operations GmbhAircraft-fuselage assembly concept
US8490921May 30, 2007Jul 23, 2013Airbus Operations GmbhLine system arrangement in an aircraft or spacecraft having a fuselage
US8534605Jun 5, 2007Sep 17, 2013Airbus Operations GmbhAircraft fuselage structure and method for producing it
US8608109Nov 10, 2011Dec 17, 2013The Boeing CompanyPayload use of wing to body volume in an elliptical fuselage
US8651421Jun 5, 2007Feb 18, 2014Airbus Operations GmbhAircraft fuselage structure and method for its production
US8695922 *Jun 6, 2007Apr 15, 2014Airbus Operations GmbhAircraft fuselage structure and method for its production
US9359085Dec 21, 2012Jun 7, 2016Airbus Operations S.L.Aircraft with fuselage-mounted engines and an internal shield
US9611039Apr 28, 2014Apr 4, 2017Airbus Operations (S.A.S.)Aircraft including a passenger cabin extending around a space defined outside the cabin and inside the aircraft
US9637234 *Dec 23, 2013May 2, 2017Airbus Opeations (Sas)Airplane with a fuselage having side outgrowth delimiting storage spaces
US20040129836 *Sep 10, 2003Jul 8, 2004The Boeing CompanyLiquid hydrogen fueled aircraft
US20050082430 *Oct 17, 2003Apr 21, 2005Young David A.Aircraft archway architecture
US20050211841 *Apr 28, 2005Sep 29, 2005The Boeing CompanyAircraft interior architecture
US20060006283 *Jun 3, 2005Jan 12, 2006Airbus FranceCockpit floor for aircraft
US20060091259 *Dec 14, 2005May 4, 2006The Boeing CompanyAircraft archway
US20060102787 *Dec 14, 2005May 18, 2006Young David AAircraft archway
US20060214057 *Dec 20, 2005Sep 28, 2006AirbusAircraft fuselage and corresponding aircraft
US20060226288 *Jun 2, 2005Oct 12, 2006Airbus FranceFloor for aircraft
US20060237585 *Apr 22, 2005Oct 26, 2006The Boeing CompanyAirplane interior systems
US20070241234 *Jun 14, 2007Oct 18, 2007Young David AAircraft archway architecture
US20070272798 *Mar 3, 2005Nov 29, 2007Karklin, Andrey MikhailovichAircraft Fuselage
US20080105783 *Nov 3, 2006May 8, 2008Cessna Aircraft CompanyFuselage design for sonic boom suppression of supersonic aircraft
US20080128551 *Feb 15, 2008Jun 5, 2008The Boeing CompanyAircraft archway architecture
US20080210815 *Oct 1, 2007Sep 4, 2008Young David AAircraft archway architecture
US20080251641 *Jul 8, 2005Oct 16, 2008Airbus Deutschland GmbhCommercial Aircraft With a Main Deck and a Lower Deck
US20090152399 *May 30, 2007Jun 18, 2009Airbus Deutschland GmbhLine system arrangement in an aircraft or spacecraft having a fuselage
US20090314891 *Jun 5, 2007Dec 24, 2009Cord HaackAircraft Fuselage Structure and Method for its Production
US20090321569 *Jun 6, 2007Dec 31, 2009Thorsten SchroeerAircraft fuselage structure and method for its production
US20100012773 *Jul 16, 2008Jan 21, 2010Im SunstarAircrft Structure
US20100025531 *Jun 28, 2006Feb 4, 2010Airbus Deutschland GmbhAircraft-fuselage assembly concept
US20100181426 *Jun 5, 2007Jul 22, 2010Cord HaackAircraft Fuselage Structure and Method for Producing it
US20140175218 *Dec 23, 2013Jun 26, 2014Airbus Operations (Sas)Airplane with a fuselage having side outgrowth delimiting storage spaces
CN101472794BJun 28, 2006Mar 13, 2013空中客车德国运营有限责任公司Aerial vehicle airframe segment, aerial vehicle airframe and method for producing aerial vehicle airframe
CN103158854A *Dec 11, 2012Jun 19, 2013空中客车运营简化股份公司Aircraft nose structure
CN103158854B *Dec 11, 2012Oct 26, 2016空中客车运营简化股份公司飞机机头结构
DE102005023886A1 *May 24, 2005Dec 7, 2006Airbus Deutschland GmbhAircraft fuselage section has accessible first internal tube, accessible second internal tube and external tube whereby first internal tube and second internal tube are enclosed by external tube
EP0408432A1 *Jul 6, 1990Jan 16, 1991Airbus IndustrieHigh capacity aircraft fuselage
EP0899189B2Jul 17, 1998Oct 21, 2009The Boeing CompanyMovable tension tie and locking mechanism
EP2610164A1 *Dec 28, 2011Jul 3, 2013Airbus Operations S.L.Aircraft with fuselage-mounted engines and an internal shield
WO1997030893A1Feb 23, 1996Aug 28, 1997Trimbach Turbine, Ltd.Aircraft having multiple fuselages
WO2007057288A1 *Oct 27, 2006May 24, 2007Airbus FranceLanding gear casing provided with a box structure
WO2007138082A1 *May 30, 2007Dec 6, 2007Airbus Deutschland GmbhLine system arrangement in an aircraft or spacecraft having a fuselage
WO2008000286A1 *Jun 28, 2006Jan 3, 2008Airbus Deutschland GmbhAircraft-fuselage assembly concept
U.S. Classification244/119, 244/54
International ClassificationB64D11/00, B64C1/00, B64C39/00
Cooperative ClassificationY02T50/46, B64C2700/6295, B64C1/00, B64C39/00, B64C2001/0036, B64D11/00
European ClassificationB64D11/00, B64C39/00, B64C1/00