DE392511C - Bracing for aircraft - Google Patents
Bracing for aircraftInfo
- Publication number
- DE392511C DE392511C DEL56507D DEL0056507D DE392511C DE 392511 C DE392511 C DE 392511C DE L56507 D DEL56507 D DE L56507D DE L0056507 D DEL0056507 D DE L0056507D DE 392511 C DE392511 C DE 392511C
- Authority
- DE
- Germany
- Prior art keywords
- bracing
- aircraft
- eye
- lamellas
- achieve
- 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
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/18—Spars; Ribs; Stringers
-
- D—TEXTILES; PAPER
- D07—ROPES; CABLES OTHER THAN ELECTRIC
- D07B—ROPES OR CABLES IN GENERAL
- D07B5/00—Making ropes or cables from special materials or of particular form
- D07B5/005—Making ropes or cables from special materials or of particular form characterised by their outer shape or surface properties
-
- D—TEXTILES; PAPER
- D07—ROPES; CABLES OTHER THAN ELECTRIC
- D07B—ROPES OR CABLES IN GENERAL
- D07B1/00—Constructional features of ropes or cables
- D07B1/06—Ropes or cables built-up from metal wires, e.g. of section wires around a hemp core
- D07B1/0693—Ropes or cables built-up from metal wires, e.g. of section wires around a hemp core having a strand configuration
-
- D—TEXTILES; PAPER
- D07—ROPES; CABLES OTHER THAN ELECTRIC
- D07B—ROPES OR CABLES IN GENERAL
- D07B2201/00—Ropes or cables
- D07B2201/20—Rope or cable components
- D07B2201/2001—Wires or filaments
- D07B2201/2002—Wires or filaments characterised by their cross-sectional shape
- D07B2201/2003—Wires or filaments characterised by their cross-sectional shape flat
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Joining Of Building Structures In Genera (AREA)
Description
Verspannung für Luftfahrzeuge. Die Erfindung betrifft eine Verspannung für Luftfahrzeuge, Wasserfahrzeuge, Wasserflugzeuge usw. zum Ersatz der bisher üblichen Wanten oder Verspannungen aus Metall- oder Stahlkabeln,, diel sich beim Gebrauch verlängern, häufigen Brüchen ausgesetzt sind und durch Spleißen miteinander verbunden werden mußten.Bracing for aircraft. The invention relates to a bracing for aircraft, watercraft, seaplanes, etc. to replace the previously common Shrouds or braces made of metal or steel cables, which change during use elongate, subject to frequent breaks and bonded together by splicing had to be.
Die Verspannung nach der Erfindung besteht im wesentlichen, aus einer Reihe von auf- oder nebeneinandergelegtenMetallblättern oder Lamellen, die einfach ohne Verbindung miteinander in beliebiger Richtung mit nach außen abnehmender Breite nebeneinandergelegt sind. Die äußeren verbreiterten Enden tragen ein Loch oder Öhr. in welches die anzuschließende Achse oder Welle hineinpaßt. Um den aerodynamischen Wirkungsgrad zu verbessern und ein windschnittiges Profil zu erzielen, kann das Lamellenbündel verleimt oder mit irgendeiner Umhüllung aus beliebigem Stoff versehen sein, um ein glattes Profil zu erzielen.The bracing according to the invention consists essentially of one Series of stacked or juxtaposed metal sheets or lamellas that simply without connection to each other in any direction with an outwardly decreasing width are placed next to each other. The outer widened ends have a hole or an eye. into which the axis or shaft to be connected fits. To the aerodynamic Improving efficiency and achieving a streamlined profile can do that Laminated bundles glued or with any covering from any Fabric should be provided to achieve a smooth profile.
Die Erfindung ist-in der Zeichnung in mehreren Ausführungsformen dargestellt. Die Abb. i zeigt einen Querschnitt durch eine Verspannung aus neben- bzw. aufeinandergelegten Metallamellen a, deren Breite von den mittleren Lamellen aus abnimmt.The invention is shown in several embodiments in the drawing. Fig. I shows a cross-section through a bracing made of juxtaposed or superimposed Metal slats a, the width of which decreases from the central slats.
In Abb. 2 sind die Lamellen a anders, nämlich, senkrecht zur Anbringung nach Abb. i sorgesehen.In Fig. 2 the slats a are different, namely, perpendicular to the attachment as shown in Fig. i.
Zur Erzielung eines windschnittigen Profiles nimmt die Breite der Lamellen nach außen ab, auch kann das die Lamellen a enthaltende Bündel verleimt, verkittet, gestrichen usw. werden, wodurch man auf der. Oberfläche eine glatte Umhüllung b aus beliebigem Stoff schafft.To achieve a streamlined profile, the width of the Lamellas outwards, the bundle containing the lamellas a can also be glued, cemented, painted, etc. Surface a smooth envelope b creates from any material.
Der Anschluß einer so zusammengesetzten, ohne Verspleißung hergestellten Verspannung erfolgt nach den Abb. 3 und d.. Die Enden der Lamellen a sind bei c zu breiten Köpfen mit öhr oder Loch d verbreitert, durch welches die anzuschließende Achse d hindurchgeht. Der Widerstand oder die Beanspruchung jedes Loches oder Auges d ist gleich dem Widerstand oder der Beanspruchung der entsprechenden Metallamelle.The connection of a so assembled, produced without splicing Bracing takes place according to Fig. 3 and d .. The ends of the lamellas a are at c widened to wide heads with an eye or hole d through which the to be connected Axis d passes through. The resistance or stress of each hole or eye d is equal to the resistance or stress of the corresponding metal lamella.
Claims (3)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DEL56507D DE392511C (en) | 1922-10-01 | 1922-10-01 | Bracing for aircraft |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DEL56507D DE392511C (en) | 1922-10-01 | 1922-10-01 | Bracing for aircraft |
Publications (1)
Publication Number | Publication Date |
---|---|
DE392511C true DE392511C (en) | 1924-03-26 |
Family
ID=7277819
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
DEL56507D Expired DE392511C (en) | 1922-10-01 | 1922-10-01 | Bracing for aircraft |
Country Status (1)
Country | Link |
---|---|
DE (1) | DE392511C (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2019175388A3 (en) * | 2018-03-15 | 2019-10-24 | Future Fibres, LLC | Multi-strand composite fiber tensioning cable |
-
1922
- 1922-10-01 DE DEL56507D patent/DE392511C/en not_active Expired
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2019175388A3 (en) * | 2018-03-15 | 2019-10-24 | Future Fibres, LLC | Multi-strand composite fiber tensioning cable |
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