Hostname: page-component-cb9f654ff-plnhv Total loading time: 0.001 Render date: 2025-08-25T09:07:24.587Z Has data issue: false hasContentIssue false
  • English
  • Français

The Present Status of Aircraft Stability Problems in the Aeroelastic Domain

Published online by Cambridge University Press:  04 July 2016

A. S. Taylor
A. S. Taylor*
Affiliation:
Royal Aircraft Establishment
Get access Rights & Permissions [Opens in a new window]

Extract

In his classic paper, The Expanding Domain of Aeroelasticity, Collar indicated how various types of problems (involving at least two of the three kinds of force—aerodynamic, elastic and inertial), which had hitherto been dealt with in their own “watertight compartments,” were tending to coalesce into a single subject which might be defined as “the dynamics of a deformable aeroplane.” The title of the subject, as Collar pointed out, at once suggests (to the mathematician at least) the formal solution of the problems which it comprises.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 63 , Issue 580 , April 1959 , pp. 227 - 238
Copyright
Copyright © Royal Aeronautical Society 1959

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.)

Article purchase

Temporarily unavailable

References

1.Collar, A. R. (1946). The Expanding Domain of Aeroelasticity. Journal of the Royal Aeronautical Society, Vol. 50, August 1946.CrossRefGoogle Scholar
2.Taylor, A. S. Methods of Investigating the Effects of Aeroelasticity on the Stability and Control of Aircraft: A Review of the Present Situation. Unpublished M.O.S. Report.Google Scholar
3.Goland, M., Luke, Y. L. and Kahn, E. A. (1947). Prediction of Wing Loads due to Gusts Including Aeroelastic Effects. United States Air Force Technical Report No. 5706, July 1947. (M.O.S. P.33067.)Google Scholar
4.Houbolt, J. C. and Kordes, E. E. (1952). Gust Response Analysis of an Airplane Including Wing Bending Flexibility. N.A.C.A. T.N. 2763, August 1952.Google Scholar
5.Yeh, G. C. K. and Johann, Martinek (1953). Effects of Wing Twist on the Response of an Aeroplane Encountering a Sharp Edged Gust. Journal of the Aeronautical Sciences, Vol. 20, No. 12, December 1953.Google Scholar
6.Taylor, A. S. and James, K. W. Aeroelastic Effects on the Stability and Control of Aircraft Designed to Operate at Mach Numbers up to 2-5. Unpublished M.O.S. Report.Google Scholar
7.Mclaughlin, M. D. (1954). A Theoretical Investigation of the Short-Period Dynamic Longitudinal Stability of Airplane Configurations having elastic wings of 0° to 60° Sweepback. N.A.C.A. T.N. 3251, December 1954.Google Scholar
8.Cole, H. A., Brown, S. C. and Holleman, E. C. (1954). Experimental and Predicted Longitudinal Response Characteristics of a Large Flexible 35° Swept-Wing Airplane at an Altitude of 35,000 ft. N.A.C.A. Research Memo RM A54H09, N.A.C.A./T.I.L. 5103, November 1954.Google Scholar
9.Cole, H. A., Brown, S. C. and Holleman, E. C. (1955). The Effects of Flexibility on the Longitudinal and Lateral- Directional Response of a Large Airplane. N.A.C.A. Research Memo RM A55D14, N.A.C.A./T.I.L. 5093, May 1955.Google Scholar
10.Klawans, B. B. and Johnson, H. I. (1956). Some Effects of Fuselage Flexibility on Longitudinal Stability and Control. N.A.C.A. T.N. 3543, April 1956.Google Scholar
11.Brown, S. C. and Holleman, E. C. (1956). Experimental and Predicted Lateral-Directional Dynamic-Response Characteristics of a Large Flexible 35° Swept-Wing Airplane at an Altitude of 35,000 ft. N.A.C.A. T.N. 3874, December 1956.Google Scholar
12.Hitch, H. (1956). The Expanded Domain of Aeroelasticity. Vickers-Armstrongs (Aircraft) Ltd. Report VTO/M/487, ARC 18,975, November 1956.Google Scholar
13.Dobson, A. M. (1956). The Response of the Wing and Engines of the Viscount 700 Series to a Vertical Gust Vickers-Armstrongs (Aircraft) Ltd. Report VTO/700/108, ARC 18,974, June 1956.Google Scholar
14.Payne, B. W. (1956). Response of the Type 1000 to Suddenly Applied Elevator. Vickers-Armstrongs (Aircraft) Ltd. Report VTO/1000/30, ARC 18,976, 2nd Issue, December 1956.Google Scholar
15.A. V., Roe and Co. Ltd., Report No. Aero/730/91 (408), January 1957. Unpublished.Google Scholar
16.Bryant, L. W. and Gates, S. B. (1937). Nomenclature for Stability Coefficients. ARC, R. & M. No. 1801, October 1937.Google Scholar
17.Neumark, S. (1943). The Disturbed Longitudinal Motion of an Uncontrolled Aircraft and of an Aircraft with Automatic Control. ARC, R. & M. No. 2078, January 1943.Google Scholar
18.Neumark, S. (1952). Analysis of Short-Period Longitudinal Oscillations of an Aircraft: Interpretation of Flight Tests. ARC, R. & M. No. 2940, September 1952.Google Scholar
19.Gates, S. B. and Lyon, H. M. (1944). A Continuation of Longitudinal Stability and Control Analysis. Part I: General Theory. ARC, R. &M. No. 2027, February 1944.Google Scholar
20.Cole, H. A., Brown, S. C. and Holleman, E. C. (1957) The Effects of Flexibility on the Longitudinal Dynamic Response of the B.47 Airplane. Institute of the Aeronautical Sciences, Preprint No. 678, January 1957.Google Scholar
21.Harper, R. P. Jr. (1955). Flight Evaluations of Various Longitudinal Handling Qualities in a Variable Stability Jet Fighter. Wright Air Development Center Technical Report 55-299, July 1955. (M.O.S. P.57724.)Google Scholar
22.Neumark, S.(1956). Operational Formulae for Response Calculations. ARC, R. & M. No. 3075, June 1956.Google Scholar