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US1605036A - Flying machine - Google Patents

Flying machine Download PDF

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Publication number
US1605036A
US1605036A US665133A US66513323A US1605036A US 1605036 A US1605036 A US 1605036A US 665133 A US665133 A US 665133A US 66513323 A US66513323 A US 66513323A US 1605036 A US1605036 A US 1605036A
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US
United States
Prior art keywords
hull
wing
strut
rigid
bracings
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 - Lifetime
Application number
US665133A
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English (en)
Inventor
Junkers Hugo
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
Application granted granted Critical
Publication of US1605036A publication Critical patent/US1605036A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • 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
    • 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

Definitions

  • My invention refers to flying machines and its particular object is to provide means whereby more room is made available for useful loads without unduly interfering with the mechanical strength of the hull of the machine.
  • he present invention is designed to provide for especially large free spaces within the hull in combination with lateral openings by utilizing the struts connecting the hull with the wing, such struts being reinforced correspondingly, as well as that portion of the wing vwhich adjoins the hull, for bracing this latter.
  • essential parts of the usual supporting and bracing structure of the hull adjacent the wing can be dispensed with.
  • the hull of an aeroplane having 'its win disposed high above and serving for bracing the .hull can have aspace for the useful ,load which is open on top and at the sides, the rigid system thus resenting gaps which allow entering the liull from the sides.
  • My invention further includes particular features. embodied in the win Vand the braces formin part thereof an which are utilized for bracing the hullin such manner that the combination of these 65 parts furnishes the necessary rigidity.
  • Fig. 2 is a similar. view of an aeroplane having the hull and wing disposed after the manner of a double joint.
  • Fig. 3 is a perspective diagrammatic, view of a machine embodying the constructive features disclosed in Fig. 2.
  • Fig. 4 is a 'diagrammatic section of an aeroplane of a similar kind in which the strut bracing serves for stiiening the hull.
  • Fig. 5 is a perspective diagrammatic view of a machine embodying the constructive features disclosed in Fig. 4.
  • Figs. 6 and 7 are diagrammatic sections of two further modifications.
  • Fig. 1 of the drawings 1 is the front portion and 2 the rear portion of the hull which are united below the wing 3 by means of the joint 4, further joints 5 and 6 being formed between these parts of the hull and the wing.
  • the members 7 and 8 bridging the span between the hull and the wing may either be fins or strut bracings having rigid bases at the hull or at the wing or at both these parts.
  • the forward end of the bracing is rigidly fixed to the rigid front portion of the wing
  • the. three parts 1, 2, 3 form in the vertical longitudinal plane a statically defined three-joint system which, in spite of the large opening in the hull, is capable of taking up all the forces acting in this plane, which originate from loads, from the air resistance yacting on the wing and rudders and from the motor.
  • the hull is not made in two separate parts, but has front and rear portions are directly connected with one another by a bottom portion 9. From a practical standpoint this arrangement is simpler, inasmuch as the assembling and handling of the body is simpliied. rlhe conditions of resistivity are not materially changed, because, in conseuence of the static'over-denition resulting from the bottom portion 9 which does not altogether act like a joint, no fundamental dis lacement of forces takes place.
  • the bottom 10 of the hull which is triangular in cross-section only one side wall 1l is uninterrupted, while the cover is interruptbesides ed by a large opening, the other side wall by a triangular indenture designed for the door 12.
  • the two forward strut bracings 7 which are rigid in all directions, are formed each of three struts arranged in pyramids having their bases on the wing, wh1le their points 5 form a rigid joint axis near the hull.
  • the joint axes formed by the ends 5-5 and 6 6, respectively, of the struts connect the forward and rear portions of the hull with the middle wing portion, all of which are safe against torsional stresses, in a manner which renders also the structure resulting from their combination safe against torsional stresses.
  • the door 12 has a top-beam 13 adapted to be rigidly connected with the side wall b y means of fixation not shown in the drawing, the closed door thus forming a continuation of the hull structure and transmitting tensile and compressive forces.
  • the elastic changes of form of the hull quite especially those occasioned by forces arising from lateral steering, are lessened, while at the bottom the hull can vbe handled after the wing has been completely dismounted.
  • the middle portion 3 of the wing is permanently connected to the hull, onl the lateral wing portions 14, l5 being arranged to be removed forl transport.
  • the carriage In order to safeguard the hull against heavy tensile stresses, the carriage is so designed that the forces transmitted through 1t are directly transferred onto the joints connecting the wing and the hull. end the carria e struts 16 carrying the load extend from t e wheel axle 17 directly to the joints 5 of the strut bracings 7.
  • the links 18 which are merely placed under minor stresses and the struts 19 serving to support the middle portion of the axle are ⁇ connected with other parts of the hull structure.
  • the wing 3 is either merely provided with the necessary means of connection in at least three points, for instance by adding a transverse trianle of struts 21, or it can be utilized foir urther bracing the hull more especially against torsional stresses, by arranging further strut bracings.
  • the joints above mentioned can be designed after the manner of rigid bracings, such as used in framework asse'mbla e points, as is the case for instance at 9 1n s shown in Fig. 6, the new type of aeroplane above described can also be provided with several wings, for instance by arranging a lower bearing plane 25 below the bottom of the hull.
  • Flying machine comprising a lhull and a wing placed across and ata distance from said hull, aside wall of said hull h aving a large indentation, and a ⁇ strut bracing connecting saidy hull and said wing and forming a rigid connection of the parts of the hull structure which are interrupted by said indentation.
  • Flying machine comprising a* hull, a side wall of said hull having a large indentation open on to a wing and a strut bracing connecting t e middle portion of said wing with the front portion and with the rear portion of said hull, while leaving the middle portion of said hull practically unobstruc d.
  • Flying machine comprising a hull, a side wall of said hull having a large indentation open on top, a wing and a strut bracing connecting the middle portion of said wingA with the front portion and with the rear portion of said hull, while leaving the middle portion of said hull practically unobstructed, said front and reark portions and said strut bracing constituting a rigid threejoint structure.
  • An aeroplane comprising a hull, a side wall of said hull having a large indentation open on top,and a wing, the front and rear portions of said hull being formed rigid against torsional stresses, and a front and a rear system ol" strut 'bracings connecting said wing to said hull and arranged to form a member rigid against torsional stresses.
  • An aeroplane comprising a hull, a side wall of said hull having a large indentation open on top; and a wing, the front and rear portions of said hull being formed rigid against torsional stresses and a pair of strut bracings which are arranged in a transverse joint axle and connect each portion with said wing.
  • An aeroplane comprising a hull, a side wall of said hull having ⁇ a large indentation open on top, and a wing, the front and rear portion of said hull having triangular cross section and being formed rigid against'. tor-i sional stresses, and a front and a rear system of strut bracings connecting said wing to said hull and arranged to form a member rigid against torsional stresses.
  • An aeroplane comprising a hull and a wing, the front and rear portions of said hull being Jformed rigid against torsional stresses and being connected at least in one point, two strut bracings rigid in all direc'- tionsconnecting the wing with one of said portions and two strut bracings rigid in the longitudinal direction connecting with the other portion.
  • An aeroplane comprising a hull and a wing, the frontandrear portions of said hull being formed .rigid against torsional stresses and being connected at least in one said wing point, two strut bracings rigid in all directions connecting the wing with one of said portions and two strut bracings rigid in the longitudinal direction connecting said wing with the other portion, said forward strut bracings being rigidly fixed by their bases to the wing, their points being linked to the front portion of the hull, while the rear strut bracings have their bases rigidly connected to the rear portion of the hull, their points being linked to said Wing.
  • Flying machine comprising a hull and .a wing placed across and at a distance from portion and with the rear portion of said hull while leaving the middle portion of said 11u11 practically unobstructed, 'a carriage below said hull and struts connecting said carriage with the strut bracings connecting the hull with the middle portion of said wing.
  • Flying machine comprising a hull, a wing and a strut bracing connecting the middle portion of said wing with the front portion and with the rear portion of said hull while leaving the middle portion ot said hull practically unobstructed, a carriage below said hull and struts connecting said carriageJ with the strut bracings connecting the middle portion of said wing with said hull.

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)
  • Adjustment And Processing Of Grains (AREA)
  • Body Structure For Vehicles (AREA)
  • Superstructure Of Vehicle (AREA)
  • Component Parts Of Construction Machinery (AREA)
US665133A 1922-10-02 1923-09-27 Flying machine Expired - Lifetime US1605036A (en)

Applications Claiming Priority (1)

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

Publications (1)

Publication Number Publication Date
US1605036A true US1605036A (en) 1926-11-02

Family

ID=31893076

Family Applications (1)

Application Number Title Priority Date Filing Date
US665133A Expired - Lifetime US1605036A (en) 1922-10-02 1923-09-27 Flying machine

Country Status (4)

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

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3808651A1 (fr) * 2019-10-14 2021-04-21 The Boeing Company Système de contrefiche spatialement en quinconce

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3808651A1 (fr) * 2019-10-14 2021-04-21 The Boeing Company Système de contrefiche spatialement en quinconce
US11254413B2 (en) 2019-10-14 2022-02-22 The Boeing Company Spatially staggered jury strut system

Also Published As

Publication number Publication date
NL25049C (fr)
FR569926A (fr) 1924-04-19
GB204687A (fr) 1924-07-03

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