Abstract
Study of Aeroservoelastic (ASE) interactions is of prime importance in modern aircrafts employing autonomous flight control systems. The complex nature of unsteady aerodynamic forces can induce adverse ASE coupling effects leading to mission failure. This study discusses the ASE analysis of Reusable Launch Vehicle Technology Demonstrator Hypersonic Experiment (RLV-TD HEX01) of the Indian Space Research Organisation (ISRO). Pertinent modeling philosophy adopted for various subsystems, analysis methodology, validations, and simulations carried out to establish closed loop stability of RLV-TD system is discussed in detail. The results of the study clearly indicate the absence of adverse modal coupling in the presence of unsteady aerodynamic and control forces. The existence of adequate closed loop dam** for critical structural modes is established through simulations to ensure adverse interaction free environment in the experimental flight.
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Acknowledgements
The authors would like to acknowledge the contributions of Shri. M. V. Dhekane (Former Director, IISU, ISRO) for comprehensive reviews of the RLV-TD Hex Mission ASE analysis. Authors express their gratitude to RLV-TD digital auto pilot design team of CLD division CGSE entity for the various inputs received for ASE analysis. We also acknowledge the contributions of Shri. S. Balakrishnan, GSLV, VSSC during the early developmental phase of ASE analysis.
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Jayan, M., Ashok Gandhi, P., Daniel, S., Neetha, R. (2021). Aeroservoelastic Analysis of RLV-TD HEX01 Mission. In: Dutta, S., Inan, E., Dwivedy, S.K. (eds) Advances in Structural Vibration. Lecture Notes in Mechanical Engineering. Springer, Singapore. https://doi.org/10.1007/978-981-15-5862-7_29
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DOI: https://doi.org/10.1007/978-981-15-5862-7_29
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