Hostname: page-component-84b7d79bbc-4hvwz Total loading time: 0 Render date: 2024-07-31T13:34:09.268Z Has data issue: false hasContentIssue false
  • English
  • Français

Some thoughts on mathematical models for flight dynamics

Published online by Cambridge University Press:  04 July 2016

H. H. B. M. Thomas
H. H. B. M. Thomas*
Affiliation:
Aeronautical Engineering
Get access Rights & Permissions [Opens in a new window]

Summary

The objective of the present paper is to examine how the mathematical modelling of the overall aircraft system, in order to calculate its flight dynamics, has had to change to meet the requirements set by the type of problem posed. Some of these requirements reflect an increasing complexity in the aerodynamic design of the aeroplane. Others, a desire to improve the accuracy of the solutions to new and sometimes old problems.

In addition the basic difficulties raised by the fact that, strictly speaking, the aerodynamic forces and moments depend on the past as well as the present history of the motion.

A comparison is made of the aerodynamic formulations constructed from the character of the dynamics with those deduced, on the basis of a number of assumptions, from an analysis, which starts by considering the true nature of the aerodynamic forces and moments. In mathematical terms this is expressed by describing them as functionals of all the state variables.

Type
Research Article
Information
The Aeronautical Journal , Volume 88 , Issue 875 , May 1984 , pp. 169 - 178
Copyright
Copyright © Royal Aeronautical Society 1984 

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.)

References

1. Hopkin, H. R. A scheme of notation and nomenclature for aircraft dynamics and associated aerodynamics. ARC R&M 3562 (parts 1 to 5), 1966.Google Scholar
2. Etkin, B. Dynamics of Flight. Published by J. Wiley and Sons, Ltd. 1958, 1st Edition.Google Scholar
3. Bryan, G. H. and Williams, W. E. The longitudinal stability of aerial gliders. Proc Roy Soc, London Series A, 1904. 73.Google Scholar
4. Bryan, G. H. Stability in aviation. Macmillan & Co, 1911.Google Scholar
5. Thomas, H. H. B. M. Introduction to the aerodynamics of flight dynamics.(Aerodynamic inputs for problems in aircraft dynamics). VKI Lecture Series 99 (1977).Google Scholar
6. Cowley, W. L. and Glauert, H. Effect of the lag of the downwash on the longitudinal stability of an aeroplane and on the rotary derivative Mq ARC R&M 718, 1921.Google Scholar
7. Tobak, M. On the use of the indicial function concept in the analysisofunsteady motions of wings and wing-tail combinations. NACA Report 1188, 1954.Google Scholar
8. Hancock, G. J. Dynamic effect of controls. AGARD/VKI Special Course on aerodynamic characteristics of control, 1983.Google Scholar
9. Garner, H. C. The application of subsonic theoretical aerodynamics to active controls. RAE Rept No TR81060, 1981.Google Scholar
10. Neumark, S. Results of step-by-step calculation of the recovery of the Typhoon from a terminal velocity dive. RAE Rept Aero 1903, ARC 7422, 1944.Google Scholar
11. Thomas, H. H. B. M. A study of the longitudinal behaviour of an aircraft at near-stall and port-stall conditions. AGARD CP 17, 1966.Google Scholar
12. Phillips, W. H. Effect of steady rolling on longitudinal and directional stability. NACA TN1627, 1948.Google Scholar
13. Pinsker, W. J. G. Charts of peak amplitude in incidence and sideslip in rolling manoeuvres due to inertia cross-coupling. ARC R&M 3293, 1962.Google Scholar
14. Thomas, H. H. B. M. and Price, P. A contribution to the theory of aircraft response in rolling manoeuvres including inertia cross- coupling effects. ARC R&M 3349, 1964.Google Scholar
15. Thomas, H. H. B. M. and Edwards, , Geraldine. Mathematical models of aircraft dynamics for extreme flight conditions AGARD, CP No 235, 1978.Google Scholar
16. Bihrle, W. Jr, Hultberg, R. S. and Mulcay, W. Rotary balance data for a typical single-engine, low-wing general aviation design for an angle-of-attack range of 30° to 90°. NASA CR 2972, 1978.Google Scholar
17. Pantason, P. and Dickens, W. Rotary balance data for a single engine trainer design for an angle-of-attack range of 8° to 90°. NASA CR 3099, 1979.Google Scholar
18. Tobak, M. and Schiff, L. W. On the formulation of the aerodynamic characteristics in aircraft dynamics. VKI Lecture Series No 80, (Aircraft Stability and control), 1975, (also see references listed therein).Google Scholar
19. Thomas, H. H. B. M. A brief introduction to aircraft dynamics . VKI Lecture Series No 80, (Aircraft Stability and control), 1975.Google Scholar
20. Neihouse, A. L., Klinar, W. J. and Scher, S. H. Status of spin research for recent airplane designs. NASA TR R-57, 1960.Google Scholar