Ariel Drachinsky

DOI Number: N/A

Conference number: IFASD-2017-057

This paper presents a computational and experimental study of the nonlinear aeroelastic response of a missile containing softening and hysteresis in the actuator of its fin. The aim of the work was to study the effect of the nonlinearity and the hysteresis on the dynamic stability of the configuration, and on the type of the obtained instability, mainly focusing on the question whether the oscillations would converge to a limit cycle oscillation (LCO) or diverge. The mathematical model is based on the Increased Order Model (IOM) method, implemented by the DYNRESP software, for the nonlinear solution. The structural model is a modal model calibrated vs GVT tests, and the aerodynamic model is based on an unsteady panel model. The nonlinearity is based on static measurements of the actuator stiffness, and is modeled in the study as an external non-linear feedback loop for the main linear block. The effect of the nonlinearity and softening and hysteresis on the onset velocity is studied along with the effect of the amplitude of initial conditions and an initial static angle of attack. Finally, some of the trends obtained in the simulations are shown in wind tunnel test results.

Read the full paper here

In Categories: 1. IFASD 2017, 1.Events, Dynamic loads
Email
Print
LinkedIn
The paper above was part of  proceedings of a CEAS event and as such the author has signed a publication agreement to have their paper published in the repository. In the case this paper is found somewhere else CEAS always links to the other source.  CEAS takes great care in making the correct content available to the reader. If any mistakes are found  in the listings please contact us directly at papers@aerospacerepository.org and we will correct the listing promptly.  CEAS cannot be held liable either for mistakes in editorial or technical aspects, nor for omissions, nor for the correctness of the content. In particular, CEAS does not guarantee completeness or correctness of information contained in external websites which can be accessed via links from CEAS’s websites. Despite accurate research on the content of such linked external websites, CEAS cannot be held liable for their content. Only the content providers of such external sites are liable for their content. Should you notice any mistake in technical or editorial aspects of the CEAS site, please do not hesitate to inform us.