Hostname: page-component-cd9895bd7-hc48f Total loading time: 0 Render date: 2024-12-28T23:11:31.384Z Has data issue: false hasContentIssue false
  • English
  • Français

Structural Weight Estimations for Novel Configurations*

Published online by Cambridge University Press:  04 July 2016

M. E. Burt
M. E. Burt*
Affiliation:
Structures Department, Royal Aircraft Establishment, Farnborough
Get access Rights & Permissions [Opens in a new window]

Summary

The aims of structure weight estimation are discussed and a review is given of its development in this country during the past fifty years from the simplest of formulae to quite detailed methods. The limitations of formulae derived only from statistical analysis of actual aircraft structures are noted. For aircraft of novel configuration it is essential for the weight of the basic load-carrying structure to be estimated by methods which are based upon the actual design and stressing procedures. The principles of “optimum” or “minimum-weight” structural design are a valuable feature of such methods and are briefly described. Statistical analysis, however, is still important for estimating the substantial weight of the joints, cutouts, transparencies and other features which transform a theoretical optimum structure into a complete and practical one. The problems of several aeroplane and missile configurations of current interest are discussed, and also the extent to which detailed design work is necessary to provide reliable structure weight estimates for such projects.

Type
Research Article
Information
The Aeronautical Journal , Volume 66 , Issue 613 , January 1962 , pp. 15 - 30
Copyright
Copyright © Royal Aeronautical Society 1962

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

Footnotes

*

The 1228th Lecture given to the Society—on 9th May 1961

References

1.Bairstow, L. and Melvill jones, B. (1912). Experiments on Models of Aeroplane Wings. R. & M. 60. March 1912.Google Scholar
2.Farren, W. S. (1929). Monoplane or Biplane. Journal of the Royal Aeronautical Society. July 1929.Google Scholar
3.Liptrot, R. N. (1934). Handbook of Aeronautics, Vol.1. Sir Isaac Pitman & Sons Ltd. 1934.Google Scholar
4.Roxbee Cox, H. (1935). A Note on Wing Structure Weight. R.A.E. Report No. B.A.I 187, A.R.C.1713. March 1935. (Unpublished.)Google Scholar
5.Barnwell, F. S. (1936). Some Notes on Aircraft Possibilities. Journal of the Royal Aeronautical Society. March 1936.CrossRefGoogle Scholar
6.Tye, W. and Montagnon, P. E. (1941). The Estimation of Wing Structure Weight. R. & M. 2080. October 1941.Google Scholar
7.Staff of S.M.E. Dept. (1942). Data for Weight Estima tion. Unpublished Ministry of Aviation Report. June 1942.Google Scholar
8.Burt, M. E. (1952). Effects of Design Speed and Normal Acceleration on Aircraft Structure Weight. A.R.C. Tech nical Report No. C.P.490, 1960.Google Scholar
9.Pugsley, A. G., Tye, W. and Allwright, H. J. (1940). The Structural and Aerodynamic Effects of Wing Thick ness and Fuselage Size Variation. R. & M. 2377. Jan. 1940.Google Scholar
10.Grinsted, F. (1948). Prediction of Wing Structure Weight. Unpublished Ministry of Aviation Report. January 1948.Google Scholar
11.Grinsted, F. (1948). Simple Formulae for Predicting the Weights of Wing, Fuselage and Tail Unit Structures. Unpublished Ministry of Aviation Report. May 1948.Google Scholar
12.Ripley, E. L. (1951). A Method of Wing Weight Predic tion. Unpublished Ministry of Aviation Report. May 1951.Google Scholar
13.Burt, M. E. (1955). Weight Prediction for Wings of Box Construction. Unpublished M.o.A. Report. August 1955.Google Scholar
14.Ripley, E. L. (1950). A Method of Fuselage Structure Weight Prediction. Unpublished M.o.A. Report. Nov. 1950.Google Scholar
15.Burt, M. E. and Phillips, J. (1952). Prediction of Fuselage and Hull Structure Weight. Unpublished Ministry of Aviation Report. April 1952.Google Scholar
16.Ripley, E. L. (1950). A Simple Method of Tail Unit Structure Weight Prediction. Unpublished Ministry of Aviation Report. November 1950.Google Scholar
17.Pavelin, R. A. (1958). Tail Unit Weight Prediction. Unpublished Vickers-Armstrongs (Aircraft) Ltd. Report. June 1958.Google Scholar
18.Burt, M. E. and Ripley, E. L. (1950). Prediction of Undercarriage Weights. Unpublished Ministry of Aviation Report. June 1950.Google Scholar
19.Phillips, J. (1956). A Method of Undercarriage Weight Prediction. Unpublished M.o.A. Report. March 1956.Google Scholar
20.Kuhn, P. (1956). Stresses in Aircraft and Shell Structures. McGraw Hill Book Co. Inc. 1956.Google Scholar
21.Peterson, J. P. and Card, M. F. (1960). Investigation of the Buckling Strength of Corrugated Webs in Shear. N.A.S.A. T.N. D-424. June 1960.Google Scholar
22.Peterson, J. P. (1957). Weight Strength Studies of Struc tures Representative of Fuselage Construction. N.A.C.A. T.N.4114. October 1957.Google Scholar
23.Legg, K. L. C. (1954). Integral Construction—A Survey and an Experiment. Journal of the Royal Aeronautical Society. July 1954.CrossRefGoogle Scholar
24.Supersonic Transport Aircraft—Symposium. Journal of the Royal Aeronautical Society. February 1961.Google Scholar
25.Argyris, J. H. and Dunne, P. C. (1952). Handbook of Aeronautics No. 1. Structural Principles and Data, Part 2, Structural Analysis. Sir Isaac Pitman & Sons Ltd. 1952.Google Scholar
26.Shanley, F. R. (1960). Weight-Strength Analysis of Aircraft Structures. Dover Publications Inc. New York. 1960.Google Scholar
27.Gerard, G. (1956). Minimum Weight Analysis of Com pression Structures. New York University Press. 1956.Google Scholar
28.Farrar, D. J. (1949). The Design of Compression Struc tures for Minimum Weight. Journal of the Royal Aeronautical Society. November 1949.Google Scholar
29.Catchpole, E. J. (1954). The Optimum Design of Com pression Surfaces Having Unfianged Integral Stiffeners. Journal of the Royal Aeronautical Society. Nov. 1954.Google Scholar
30.Heath, W. G. (1960). Sandwich Construction. Aircraft Engineering, July and August 1960.Google Scholar
31.Houghton, D. S. and Chan, A. S. L. (1957). The Design of a Multi-Cell Box in Pure Bending for Minimum Weight. College of Aeronautics Note. No. 74. Nov. 1957.Google Scholar
32.Schuette, E. M. and Mcculloch, J. C. (1947). Charts for the Minimum Weight Design of Multi-Web Wings in Bending. N.A.C.A. T.N.1323. June 1947.Google Scholar
33.Gerard, G. (1957). Handbook of Structural Stability Part 4. Failure of Plates and Composite Elements. N.A.C.A. T.N.3784. August 1957.Google Scholar
34.Rosen, B. W. (1956). Analysis of the Ultimate Strength and Optimum Proportions of Multi-Web Wing Structures. N.A.C.A. T.N.3633. March 1956.Google Scholar
35.Needham, R. A. (1956). The Ultimate Strength of Multi- Web Box Beams in Pure Bending. Journal of Aeronautical Sciences. Nov. 1955. (Also comments by R. A. PRIDE, NOV. 1956).Google Scholar
36.Johnson, A. E. (1954). Bending Tests on Box Beams Having Solid and Open Construction Webs. N.A.C.A. T.N.3231. August 1954.Google Scholar
37.Fraser, A. F. (1956). Experimental Investigation of the Strength of Multi-Web Beams with Corrugated Webs. N.A.C.A. T.N.3801. October 1956.Google Scholar
38.Dow, N. F., Lewtn, L. R. and Troutman, J. L. (1954). Elastic Buckling Under Combined Stresses of Flat Plates with Integral Waffle-like Stiffening. N.A.C.A. T.N.3059. January 1954.Google Scholar