GB204687A - - Google Patents

Info

Publication number
GB204687A
GB204687A GB21681/23A GB2168123A GB204687A GB 204687 A GB204687 A GB 204687A GB 21681/23 A GB21681/23 A GB 21681/23A GB 2168123 A GB2168123 A GB 2168123A GB 204687 A GB204687 A GB 204687A
Authority
GB
United Kingdom
Prior art keywords
fuselage
points
parts
secured
plane
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
GB21681/23A
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.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Publication of GB204687A publication Critical patent/GB204687A/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
    • B64C1/26—Attaching the wing or tail units or stabilising surfaces
    • 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
    • C—CHEMISTRY; METALLURGY
    • C09—DYES; PAINTS; POLISHES; NATURAL RESINS; ADHESIVES; COMPOSITIONS NOT OTHERWISE PROVIDED FOR; APPLICATIONS OF MATERIALS NOT OTHERWISE PROVIDED FOR
    • C09C—TREATMENT OF INORGANIC MATERIALS, OTHER THAN FIBROUS FILLERS, TO ENHANCE THEIR PIGMENTING OR FILLING PROPERTIES ; PREPARATION OF CARBON BLACK  ; PREPARATION OF INORGANIC MATERIALS WHICH ARE NO SINGLE CHEMICAL COMPOUNDS AND WHICH ARE MAINLY USED AS PIGMENTS OR FILLERS
    • C09C1/00—Treatment of specific inorganic materials other than fibrous fillers; Preparation of carbon black
    • C—CHEMISTRY; METALLURGY
    • C09—DYES; PAINTS; POLISHES; NATURAL RESINS; ADHESIVES; COMPOSITIONS NOT OTHERWISE PROVIDED FOR; APPLICATIONS OF MATERIALS NOT OTHERWISE PROVIDED FOR
    • C09D—COATING COMPOSITIONS, e.g. PAINTS, VARNISHES OR LACQUERS; FILLING PASTES; CHEMICAL PAINT OR INK REMOVERS; INKS; CORRECTING FLUIDS; WOODSTAINS; PASTES OR SOLIDS FOR COLOURING OR PRINTING; USE OF MATERIALS THEREFOR
    • C09D5/00—Coating compositions, e.g. paints, varnishes or lacquers, characterised by their physical nature or the effects produced; Filling pastes
    • C09D5/08—Anti-corrosive paints
    • C09D5/10—Anti-corrosive paints containing metal dust

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Organic Chemistry (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Materials Engineering (AREA)
  • Wood Science & Technology (AREA)
  • Body Structure For Vehicles (AREA)
  • Superstructure Of Vehicle (AREA)
  • Component Parts Of Construction Machinery (AREA)
  • Adjustment And Processing Of Grains (AREA)

Abstract

204,687. Junkers, H. Oct. 2, 1922, [Convention date]. Planes connecting to machine; fuselages; land wheels.-Large free spaces with lateral openings are formed in aeroplane fuselages and the bracing thus dispensed with is replaced by strongly constructed strutwork connecting the fuselage to the supporting surface so as to resist bending, shear, and torsional forces. The Figure shows an aeroplane having a. triangular longitudinal girder 10 along its base, and its front and rear portions resistant to torsion, points 5 on the front portion being connected by sets of tripod struts 7 to the central section 3 of the supporting-plane which is connected at the points 6 to the rear portion of the fuselage by triangular frames 8. One side 11 of the fuselage is continuous but the other has a door 12 with a beam 13 at its upper edge which can be secured when the door is shut to take compression or tension forces and serve as an additional member of the structure. The main undercarriage struts 16 may be secured at the points 5. Modifications are described in which the front and rear parts of the fuselage are hinged together at the base and connected to an upper plane at their upper parts by rigid strut work or fins having pivotal connections to one or other of the plane or fuselage parts. Or extensions on one of the fuselage parts may be connected to the other by struts extending in longitudinal vertical planes, and a supporting surface is secured to the structure at at least three points. Rigid joints may be substituted for true hinged joints. Multiplane constructions may be employed, and a biplane may be obtained by mounting a lower supporting-surface on the floor of the body.
GB21681/23A 1922-10-02 1923-08-27 Expired GB204687A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE204687T 1922-10-02

Publications (1)

Publication Number Publication Date
GB204687A true GB204687A (en) 1924-07-03

Family

ID=31893076

Family Applications (1)

Application Number Title Priority Date Filing Date
GB21681/23A Expired GB204687A (en) 1922-10-02 1923-08-27

Country Status (4)

Country Link
US (1) US1605036A (en)
FR (1) FR569926A (en)
GB (1) GB204687A (en)
NL (1) NL25049C (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11254413B2 (en) * 2019-10-14 2022-02-22 The Boeing Company Spatially staggered jury strut system

Also Published As

Publication number Publication date
US1605036A (en) 1926-11-02
NL25049C (en)
FR569926A (en) 1924-04-19

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