Affiliation:
1. National Aerospace Laboratories (CSIR)
2. Indian Institute of Technology
Abstract
A full order model of an aeroelastic aircraft has too many parameters to yield satisfactory estimates. In this paper, using simulated data, rigid body and aeroelastic derivatives are estimated in longitudinal axis for single elastic mode. The proposed approach uses an integrated model structure. It emphasizes the use of estimation techniques that have the capability to accurately determine modal characteristics in those flight test situations where the measured data is dominated by elastic effects. Output error method in time domain is applied to the simulated flight data to identify the aircraft derivatives.
Publisher
Trans Tech Publications, Ltd.
Reference14 articles.
1. R E Maine and K W Iliff. Identification of Dynamic System Application to Aircraft,. Agard AG-300, pt I, (1992).
2. S H Zerweckh, A H Von Flotow and J E Murray. Flight Testing of Highly Flexible Aircraft,. Journal of Aircraft, vol 27, 1990, p.342.
3. Waszak, M.R., and Schmidt, D.K., Flight Dynamics of Aeroelastic Vehicle, Journal of Aircraft, Vol. 25, No. 6, 1988, pp.563-571.
4. Ghosh, A.K., and Raisinghani, S.C., Parameter Estimates of an Aeroelastic Aircraft as Affected by Model Simplifications, Journal of Aircraft, Vol. 31, No. 2, March-April 1994, pp.174-180.
5. Jatinder Singh, Basappa and Rohit Kumar., Identification of Aeroelastic Quasi-Steady Effects Through Flex Factor,. Journal of Aerospace Sciences & Technologies Vol. 60, No. 4, Sep (2008).
Cited by
4 articles.
订阅此论文施引文献
订阅此论文施引文献，注册后可以免费订阅5篇论文的施引文献，订阅后可以查看论文全部施引文献