Get 20M+ Full-Text Papers For Less Than $1.50/day. Start a 14-Day Trial for You or Your Team.

Learn More →

Month in the Patent Office

Month in the Patent Office The blades of an airscrew or spars and similar hollow structural parts of aircraft are formed of two shell sections of wood lamin joined together with a moistureresisting adhesive, each shell section forming in the case of a blade substantially one face of the blade and being made by assembling very thin wood lamin between shaped dies, which dies may be heated as well as pressed together. The wood lamin is preferable less than one millimetre in thickness and the lamin may be assembled so that parts which take higher stresses are more highly compressed. The lamin 9 are treated with a resin and pressed between the dies, 7, 8 which have tubes 10 for conveying a heating medium. After pressing, the parts may be clamped together while the shell member is setting, and finally the free edges 11 are cut away. If desired, the shelllike members 2, 3 may be strengthened by inner longitudinal ribs 22 and the parts are subsequently united by gluing at the leading and trailing edges. For the purpose of securing the blade root within a cylindrical socket, it may have an inner stiffening tube 15 and an outer hardwood sleeve 17 to which a metal sleeve 16 is attached. Alternatively, the hardwood sleeve and metal sleeve are both placed inside and outer clamping sleeves are employed. The shell members 2, 3 may be enclosed in a metal sheeting 23, 24, the edges of which are joined by welding or by interlocking the edges 25. The leading edge may be formed by a separate member 30 dovetailed as at 34 into the outer shells, and such member may be formed with a rubber tip 37 or be wholly of rubber. The resistance to bending stresses may be increased by loading the blade tip either by adding weight or using material of high density. The wood lamin may be interleaved with lamin of other suitable pliable material such as fabric or metal gauze. 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 11 (6): 2 – Jun 1, 1939

Loading next page...
 
/lp/emerald-publishing/month-in-the-patent-office-xnkvb0ZI7N
Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb030507
Publisher site
See Article on Publisher Site

Abstract

The blades of an airscrew or spars and similar hollow structural parts of aircraft are formed of two shell sections of wood lamin joined together with a moistureresisting adhesive, each shell section forming in the case of a blade substantially one face of the blade and being made by assembling very thin wood lamin between shaped dies, which dies may be heated as well as pressed together. The wood lamin is preferable less than one millimetre in thickness and the lamin may be assembled so that parts which take higher stresses are more highly compressed. The lamin 9 are treated with a resin and pressed between the dies, 7, 8 which have tubes 10 for conveying a heating medium. After pressing, the parts may be clamped together while the shell member is setting, and finally the free edges 11 are cut away. If desired, the shelllike members 2, 3 may be strengthened by inner longitudinal ribs 22 and the parts are subsequently united by gluing at the leading and trailing edges. For the purpose of securing the blade root within a cylindrical socket, it may have an inner stiffening tube 15 and an outer hardwood sleeve 17 to which a metal sleeve 16 is attached. Alternatively, the hardwood sleeve and metal sleeve are both placed inside and outer clamping sleeves are employed. The shell members 2, 3 may be enclosed in a metal sheeting 23, 24, the edges of which are joined by welding or by interlocking the edges 25. The leading edge may be formed by a separate member 30 dovetailed as at 34 into the outer shells, and such member may be formed with a rubber tip 37 or be wholly of rubber. The resistance to bending stresses may be increased by loading the blade tip either by adding weight or using material of high density. The wood lamin may be interleaved with lamin of other suitable pliable material such as fabric or metal gauze.

Journal

Aircraft Engineering and Aerospace TechnologyEmerald Publishing

Published: Jun 1, 1939

There are no references for this article.