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Month in the Patent Office

Month in the Patent Office 5 0 AIRCRAFT ENGINEERING February, 1931 A Selection of the More Important Aircraft and Engine Specifications Published Recently 335,603 . Cantilever Wings. Chorlton, 336,761 . Aeroplanes. Gérin, J., 59, Rue are riveted to bulkheads 3 having flanged A. E . L., 55, Lower Belgrave Street, and Haig, apertures 5 ; intermediate bulkheads may also Chevalier, Levallois-Perret, Seine, France. R. A. de H., 7, St. James's Street, both in Sept. 26, 1929, No. 29173. [Class 4] . London. June 27, 1929, No. 19759. [Class 4.] Fuselages: framework: planes, construction Planes, construction of.—In aeroplanes having of.—Lifting surfaces and fuselages of aeroplanes cantilever wings, the wing-tip is stayed against are built up from juxtaposed box elements torsional stresses by securing a stiff cross-rib secured on spars, each box element being B to the cantilever spar A at the point where composed of a number of metal sheets flanged th e spar commences to taper and by providing inwards at the edges and assembled by riveting be provided. Arrangements involving sets of a diagonal spar C connecting the outer tip of juxtaposed flanged edges which form internal three and four spars are illustrated. th e tapering extension A4 to the after portion stiffening-ribs whilst leaving th e external surface smooth. The spars are constitute d by elements, each of which presents a cross section of con­ stan t external dimensions and the relative spac­ ing apart of which is constant for several types of the cross-rib B. In one arrangement, in which the spar A is stayed against torsion by pyramidal bracings A1 and struts A2, the after portion of the rib B is braced against drag stresses by a strut F and drag-wire G. An aileron may be hinged to th e spar C, which may the n be connected to th e rib B at a point nearer t o the spar, enabling the aileron to be included in the wing tip ; the strut F is, in this case, also attache d to rib B at a point coinciding with the end of spar C. According to further modifica­ tions the spar C may form the leading edge of th e aileron and be hinged to the ends of the wing-tip ribs or alternatively these ribs may extend to the rear of spar C to carry the aileron hinges. 336,649 . Single Spar Wings. Messer- schmitt, W., 118A, Haunstctterstrasse, Augs­ burg, Germany. July 15, 1929, No. 21692. [Class 4.]. Planes, construction of.—An aircraft wing ha s a single spar H arranged at or near the neutral axis E of a hollow torsion resisting of machine whilst the length, the thickness and th e material are variable according to the stresses to be supported. The boxes are provided with apertures for the passage of the box constituted by the wing nose or leading spars, the dimensions and spacing apart of edge portion and a stressed metal covering a. these apertures corresponding to those of the The torsion body may be bounded by a wall b spars. Fig. 1 shows wings built up from box which is not capable of taking any substantial elements 1 threaded on tubular spars 2, the amoun t of the bending stresses, or may extend boxes 1 having apertures formed in ribs 3, to the trailing edge. The spar may be so dis­ Figs. 2 and 3, flanged at 5 to slide on the posed that it is subjected to bending stresses tube s 2. The boxes are secured at the outer only ; the neutral axis E of the torsion body ends of the planes by locknuts screwed to is then situated in the spar. Alternatively sleeves or rods on the ends of the spars. One th e spar may be placed a sufficient distance in element 2a of the box 1 is adapted for the front of, or behind, the neutral axis E to attachmen t of bracing struts. In a modifica­ enable it to take a proportion of the torsional tion the tubes 2 are arranged one at the leading stresses. edge and two near to the maximum thickness of th e wing section. Fig. 5 illustrates a fuselage built in three parts from box elements 1 havin g a These abstracts of complete specifications of Patents recently tubula r spars which are composed of elements 2, published are specially compiled, by permission of H.M. Stationery Office, from abridgements appearing in the Patent Journal. Printed 2a arranged to suit the contours of th e fuselage, copies of the full specifications can be obtained from the Patent these being connected together by reinforced Office, 25, Southampton Buildings, London, W.C.2, price one shilling each. intermediate boxes 1b, Fig. 6. The inwardly Except where otherwise stated, the specification is unaccompanied flanged covering elements forming the boxes by drawings if none is reproduced. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Aircraft Engineering and Aerospace Technology Emerald Publishing

Month in the Patent Office

Aircraft Engineering and Aerospace Technology , Volume 3 (2): 1 – Feb 1, 1931
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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb029372
Publisher site
See Article on Publisher Site

Abstract

5 0 AIRCRAFT ENGINEERING February, 1931 A Selection of the More Important Aircraft and Engine Specifications Published Recently 335,603 . Cantilever Wings. Chorlton, 336,761 . Aeroplanes. Gérin, J., 59, Rue are riveted to bulkheads 3 having flanged A. E . L., 55, Lower Belgrave Street, and Haig, apertures 5 ; intermediate bulkheads may also Chevalier, Levallois-Perret, Seine, France. R. A. de H., 7, St. James's Street, both in Sept. 26, 1929, No. 29173. [Class 4] . London. June 27, 1929, No. 19759. [Class 4.] Fuselages: framework: planes, construction Planes, construction of.—In aeroplanes having of.—Lifting surfaces and fuselages of aeroplanes cantilever wings, the wing-tip is stayed against are built up from juxtaposed box elements torsional stresses by securing a stiff cross-rib secured on spars, each box element being B to the cantilever spar A at the point where composed of a number of metal sheets flanged th e spar commences to taper and by providing inwards at the edges and assembled by riveting be provided. Arrangements involving sets of a diagonal spar C connecting the outer tip of juxtaposed flanged edges which form internal three and four spars are illustrated. th e tapering extension A4 to the after portion stiffening-ribs whilst leaving th e external surface smooth. The spars are constitute d by elements, each of which presents a cross section of con­ stan t external dimensions and the relative spac­ ing apart of which is constant for several types of the cross-rib B. In one arrangement, in which the spar A is stayed against torsion by pyramidal bracings A1 and struts A2, the after portion of the rib B is braced against drag stresses by a strut F and drag-wire G. An aileron may be hinged to th e spar C, which may the n be connected to th e rib B at a point nearer t o the spar, enabling the aileron to be included in the wing tip ; the strut F is, in this case, also attache d to rib B at a point coinciding with the end of spar C. According to further modifica­ tions the spar C may form the leading edge of th e aileron and be hinged to the ends of the wing-tip ribs or alternatively these ribs may extend to the rear of spar C to carry the aileron hinges. 336,649 . Single Spar Wings. Messer- schmitt, W., 118A, Haunstctterstrasse, Augs­ burg, Germany. July 15, 1929, No. 21692. [Class 4.]. Planes, construction of.—An aircraft wing ha s a single spar H arranged at or near the neutral axis E of a hollow torsion resisting of machine whilst the length, the thickness and th e material are variable according to the stresses to be supported. The boxes are provided with apertures for the passage of the box constituted by the wing nose or leading spars, the dimensions and spacing apart of edge portion and a stressed metal covering a. these apertures corresponding to those of the The torsion body may be bounded by a wall b spars. Fig. 1 shows wings built up from box which is not capable of taking any substantial elements 1 threaded on tubular spars 2, the amoun t of the bending stresses, or may extend boxes 1 having apertures formed in ribs 3, to the trailing edge. The spar may be so dis­ Figs. 2 and 3, flanged at 5 to slide on the posed that it is subjected to bending stresses tube s 2. The boxes are secured at the outer only ; the neutral axis E of the torsion body ends of the planes by locknuts screwed to is then situated in the spar. Alternatively sleeves or rods on the ends of the spars. One th e spar may be placed a sufficient distance in element 2a of the box 1 is adapted for the front of, or behind, the neutral axis E to attachmen t of bracing struts. In a modifica­ enable it to take a proportion of the torsional tion the tubes 2 are arranged one at the leading stresses. edge and two near to the maximum thickness of th e wing section. Fig. 5 illustrates a fuselage built in three parts from box elements 1 havin g a These abstracts of complete specifications of Patents recently tubula r spars which are composed of elements 2, published are specially compiled, by permission of H.M. Stationery Office, from abridgements appearing in the Patent Journal. Printed 2a arranged to suit the contours of th e fuselage, copies of the full specifications can be obtained from the Patent these being connected together by reinforced Office, 25, Southampton Buildings, London, W.C.2, price one shilling each. intermediate boxes 1b, Fig. 6. The inwardly Except where otherwise stated, the specification is unaccompanied flanged covering elements forming the boxes by drawings if none is reproduced.

Journal

Aircraft Engineering and Aerospace Technology – Emerald Publishing

Published: Feb 1, 1931

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