First published: N/A
Standard: £9 + VAT
An IStructE account gives you access to a world of knowledge. Create a profile to receive details of our unique range of resources, events and training.
Added to basket
This paper deals very broadly with aspects of structural design of the Concorde aircraft rather than dealing in depth with specific details. It opens with consideration of operational conditions peculiar to a supersonic transport aircraft and in particular the influence of sustained periods at elevated temperatures on the choice of material and structural forms. A description is then given of the form and method of manufacture of the primary structure of the aircraft.
N.F. Harpur, M.A. Taunton and T.W. Coombe
In order to simplify the calculation of the ultimate bending capacity of rectangular, solid, or hollow, reinforced concrete beams subjected to bending and torsion the authors introduce approximate expressions connecting the angle of crack in the vertical face with the ratio of the bending moment to the torsion moment. Using these expressions design equations are derived and it is shown that the results obtained using these equations are in close agreement with experimental results.
D.R. Fairbairn and S.R. Davies
Mr. E. H. BATEMAN, introducing the paper for discussion, gave a brief synopsis of the paper illustrating his remarks by blackboard sketches. He drew particular attention to the new method of analysis for multistorey frames by remainder-distribution, which he
claimed had special advantages in connection with the determination of stresses due to wind forces; in this connection he mentioned the Fifth Report of the Wind Bracing Sub-committee of the American Society of Civil Engineers (Proceedings, March, 1936) in which were recorded the times required to solve a particular problem by the methods hitherto available, namely, the moment-distribution method of Professor Hardy Cross and Dr. Goldberg’s adaptation of the slope deflection system.