• Fracture mechanics
• Finite element analysis
• Design
• Pylon

The Brobdingnagian increase in the global space Industry as the result of the entry by multiple private giant corporates into the commercial space domain and the massive technological advancements in the field of small and nanosatellites opens up a market where the small satellites no longer need to be carried as piggybacks and with compromised launch timings. Air launch mechanisms are expected to be the key players in this sector considering the quantum of work demonstrated in recent years. The thesis work tries to address the issue of designing and optimization of the multiple options available for air launch mechanism concentrating on using existing aeroplanes modified to act as a carrier for the launchers. A compilation of theoretical works available on this technology and modern engineering tools are used to develop a preliminary design of the pylon for air launch concept. A conceptual design of the pylon integrating the launcher and aircraft is designed using classical methods, different Structural, Aerodynamic, Modal analysis are done to validate the design and are iterated for better performance. A basic fracture mechanics estimation is also done both theoretically and using simulation tools. The thesis aims at providing a path for the technical aspects for air launch mechanisms serving both academic and commercial purposes and deduces a preliminary design for the pylon connecting the launch vehicle and carrier aircraft to analyse different mechanical properties.