DE319462C - Airplane with closed cabin - Google Patents

Airplane with closed cabin

Info

Publication number
DE319462C
DE319462C DE1919319462D DE319462DA DE319462C DE 319462 C DE319462 C DE 319462C DE 1919319462 D DE1919319462 D DE 1919319462D DE 319462D A DE319462D A DE 319462DA DE 319462 C DE319462 C DE 319462C
Authority
DE
Germany
Prior art keywords
airplane
spar
closed cabin
opening
fuselage
Prior art date
Legal status (The legal status 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 status listed.)
Expired
Application number
DE1919319462D
Other languages
German (de)
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Flugzeug Werke Deutsch GmbH
Original Assignee
Flugzeug Werke Deutsch GmbH
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 Flugzeug Werke Deutsch GmbH filed Critical Flugzeug Werke Deutsch GmbH
Application granted granted Critical
Publication of DE319462C publication Critical patent/DE319462C/en
Expired legal-status Critical Current

Links

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
    • B64C1/14—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
    • 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
    • B64C1/1423—Passenger doors
    • 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
    • B64C2001/0054—Fuselage structures substantially made from particular materials
    • B64C2001/0063—Fuselage structures substantially made from particular materials from wood

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Body Structure For Vehicles (AREA)
  • Toys (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Fittings On The Vehicle Exterior For Carrying Loads, And Devices For Holding Or Mounting Articles (AREA)

Description

Flugzeug mit geschloAsener Fahrzelle. Es ist schon vorgeschlagen worden, bei geschlossenen Flugzeugrümpfen die Einsteigöffnung an der Seite anzubringen. Diese Anordnung bietet aber meist Schwierigkeiten wegen der geringen Bauhöhe des Rumpfes, da zur Schaffung einer genügend hohen Öffnung mindestens einer der oberen Längsholme durch die Einsteigöffnung unterbrochen werden muß. Bei richtiger Durchbildung des Flugzeugrumpfes besteht aber dennoch die -Iöglichkeit, die Einsteigöffnung seitlich anzubringen, ohne daß dieFestigkeit derRumpfkonstruktion irgendwelche Einbuße erleidet. Es ist nur nötig, im Bereiche der Einsteigöffnung die Beanspruchungen des entsprechenden oberen Längsholmes abzufangen und unter der Einsteigöffnung hindurchzuleiten,wie (-las in der Zeichnung in einer beispielsweisen Ausführungsform schematisch veranschaulicht ist. a. und b sind die Längsholme des Flugzeugrumpfes und d sind die Querspanten; lt ist die seitlich liegende Einsteigöffnung, die nach der allseitig geschlossenen Fahrzelle i führt. Im Bereiche dieser Einsteigöffnung h führen von dem Holm a Streben g, g' nach dem Sohlenschenkel k der Einsteigöffnung h und dem unteren Längsholm b, die beide zu einem hochkantigen Träger verbunden sind. Zwischen beiden Streben b g', die sich zu beiden Seiten der Einsteigöffnung h befinden, können ebenfalls besondere Versteifungen in Form von Diagonalstreben oder auch versteifende Verkleidungen, etwa in Form von Sperrholzplatten, vorgesehen werden, so daß nun eine Versteifung zustande kommt, die die Schwächung der Rumpfkonstruktion im Bereiche der Einsteigöffnung h wieder ausgleicht.Airplane with closed cabin. It has already been proposed to attach the entry opening on the side when the fuselage is closed. However, this arrangement usually presents difficulties because of the low overall height of the fuselage, since at least one of the upper longitudinal spars must be interrupted by the access opening in order to create a sufficiently high opening. If the aircraft fuselage is properly formed, however, there is still the possibility of attaching the access opening laterally without the strength of the fuselage construction being impaired in any way. It is only necessary to absorb the stresses on the corresponding upper longitudinal spar in the area of the boarding opening and to guide it through under the boarding opening, as is schematically illustrated in the drawing in an exemplary embodiment. A. And b are the longitudinal spars of the aircraft fuselage and d are the Transverse ribs; lt is the entry opening on the side, which leads to the fully enclosed car i. In the area of this entry opening h, struts g, g 'lead from the spar a to the sole leg k of the entry opening h and the lower longitudinal strut b, both of which lead to one Between the two struts b g ', which are located on both sides of the access opening h, special stiffeners in the form of diagonal struts or stiffening cladding, for example in the form of plywood panels, can be provided so that stiffening is now achieved comes that the weakening of the hull structure in the areas of the Access opening h compensates again.

Claims (1)

PATENT-ANSpRUCH: Flugzeug mit geschlossener Fahrzelle, dadurch gekennzeichnet, daß die seitliche Einsteigöffnung über den oberen Rumpfholm (a) hinausgeführt ist und die durch dessen Unterbrechung bedingte Schwächung aufgehoben wird durch Streben (g, g'), die vom oberen Rumpfholm (ä) nach dein unteren Holm (b) und dem mit diesem verstrebten Sohlenschenkel (h) niedergeführt sind.PATENT CLAIM: Airplane with closed cabin, characterized that the side entry opening is led out over the upper fuselage spar (a) and the weakening caused by its interruption is lifted by striving (g, g '), those from the upper trunk spar (ä) to your lower spar (b) and the one with this braced sole legs (h) are lowered.
DE1919319462D 1919-04-04 1919-04-04 Airplane with closed cabin Expired DE319462C (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE319462T 1919-04-04
DE320941T 1919-06-01

Publications (1)

Publication Number Publication Date
DE319462C true DE319462C (en) 1920-03-09

Family

ID=6151962

Family Applications (2)

Application Number Title Priority Date Filing Date
DE1919319462D Expired DE319462C (en) 1919-04-04 1919-04-04 Airplane with closed cabin
DE1919320941D Expired DE320941C (en) 1919-04-04 1919-06-01 Airplane with closed cabin

Family Applications After (1)

Application Number Title Priority Date Filing Date
DE1919320941D Expired DE320941C (en) 1919-04-04 1919-06-01 Airplane with closed cabin

Country Status (3)

Country Link
DE (2) DE319462C (en)
FR (1) FR512314A (en)
GB (2) GB144257A (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102006016755B3 (en) 2006-04-10 2007-11-29 Airbus Deutschland Gmbh Fuselage section for aircraft, has fuselage skeleton that is fixed to outer skin construction at door opening, so that ribs in fuselage skeleton divides door opening into multiple opening

Also Published As

Publication number Publication date
GB141347A (en) 1921-06-30
GB144257A (en) 1921-07-06
FR512314A (en) 1921-01-20
DE320941C (en) 1920-05-19

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