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FCS design for structural couplingstability

Published online by Cambridge University Press:  04 July 2016

B. D. Caldwell
B. D. Caldwell*
Affiliation:
British Aerospace Defence (Military Aircraft)Warton Aerodrome, Preston, Lanes, UK
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Abstract

ACT embodying FBW and digital computing is nowimplemented routinely in almost all classes ofaircraft, and is often essential in achievingperformance requirements. However, careful design,thorough understanding, and attention to detail arenecessary if the benefits of ACT are to be realisedand attention must be focused appropriately amongthe issues to be resolved to ensure that developmentproceeds efficiently and overall costs areminimised. This paper introduces structural couplingas one of the important “details” of FCS design, andshows how the “state-of-the-art” has developed atBAe Warton in order to help achieve the performancespecification for a modern weapons system, whilemaintaining a balanced and efficient FCS designeffort.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 100 , Issue 1000 , December 1996 , pp. 506 - 519
Copyright
Copyright © Royal Aeronautical Society 1996 

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References

1. Weymeyer, W.K. and Sporing, R.W. An industry survey on aeroelastic control system instabilities in aerospace vehicles, IAS Paper No 62-47, January 1962.Google Scholar
2. Hofmann, L.G. and Kezer, A. Simplified analysis of flexible booster FCS, MIT E-1210, June 1962.Google Scholar
3. Royal Aircraft Establishment Notes on some problems of high speed aircraft programmes, TM IAP 649, March 1957.Google Scholar
4. Felt, L.R., Huttsell, L.J., Noll, T.E. and Cooley, D.E. Aeroservoe- lastic encounters, J Aircr, July 1979, 16, (7), article 78-1289.Google Scholar
5. Norris, G. Amraam block placed on Lockheed F-16s, Flight International, 20 October 1993.Google Scholar
6. Kehoe, M.W., Laurie, E.J. and Bjarke, L.J. An inflight interaction of the X-29A canard and FCS, AIAA-90-1240-CP, 1990.Google Scholar
7. Thompson, M.O. At The Edge of Space — The X-15 Flight Programme, Airlife, 1990.Google Scholar
8. Evans, G.J. and Beele, B.J. Auto aeroelastic mode coupling, a comparison of predicted and actual characteristics, AGARD FMP S&C, September 1968.Google Scholar
9. Taylor, R., Pratt, R.W. and Caldwell, B.D. The effect of actuator non-linearities on ASE, J Guid Contr Dynam, March 1996, 19, (2).Google Scholar
10.FCS — Design Installation and Test of Piloted Aircraft, General Specification For, MIL-F-9490D.Google Scholar
11. Tretter, S.A. Discrete-Time Signal Processing, John Wiley and Sons, 1976.Google Scholar
12. Taylor, R., Pratt, R.W. and Caldwell, B.D. The effects of sampled signals on the FCS of an agile combat aircraft with a flexible structure, In: proceedings of the AIAA/ASME/IEEE/AISE/AIChE/ISA/SCS American Control Conference (Seattle WA) Vol 1, AIAA, Washington DC, 1995.Google Scholar
13. Nanson, K.M. and Ramsey, R.B. The development and use of inflight analysis at BAe Warton, AGARD FVIP Meeting, Lisbon, Paper 18, September 1996.Google Scholar
14. Young, P. and Patton, R. Comparison of test signals for aircraft frequency domain identification, J Guid Contr Dynam, 1988, 13, (3).Google Scholar
15. PRIESTLY Spectral Analysis and Time Series, Vol 1, Academic, 1981.Google Scholar
16. Taylor, R., Pratt, R.W. and Caldwell, B.D. An alternative approach to aeroservoelastic design and clearance, In: IEE proceedings control theory and applications, 143, (1).Google Scholar
17. Heeg, J., McGowan, A., Crawley, E. and Lin, C. The piezoelectric response tailoring investigation, In: proceedings of RAeS International Forum on Aeroelasticity and Structural Dynamics Vol 1, June 1995.Google Scholar
18. Felton, R.D. Controller Design Methodologies for Rigid Body and Structural Mode Control of an Agile Combat Aircraft, PhD thesis in preparation, Lancaster University, 1996.Google Scholar
19. Forsching, H.W. Unsteady aerodynamic forces on an oscillating wing at high incidences and flow separation, AGARD CP 483, Paper 7, April 1990.Google Scholar
20. Becker, J. Aeroservoelastic stability of aircraft at high incidence, 68th AGARD Fluid Dynamics Panel Specialist Meeting, May 1991.Google Scholar
21. Pilkington, D.J. and Wood, N.J. Unsteady aerodynamic effects of trailing edge controls on delta wings, Aeronaut J, March 1995, 99, (983), pp 99–108.Google Scholar