Numerical multidisciplinary optimization of aircraft with flight dynamic stability constraints

Abstract

Classical approach to conceptual and preliminary design in aerospace sciences reaches limits. To go further and achieve better, competitive results’ use of optimization methods becomes mandatory. The trend is clearly visible in professional software for simulations equipped with optimization tools, which was not standard just decade ago. Many examples of multidisciplinary optimization were shown, especially with coupled aerodynamics and structure analyses, but only few of them consider dynamic stability effects in the conceptual and preliminary design. The article shows successful example of multidisciplinary design and optimization of Vertical Takeoff and Landing aircraft, which includes coupling of aerodynamics, mass analyses and innovative approach of constraints from flight dynamic stability. Presented optimization framework revealed potential for more efficient conceptual and preliminary design with the result of known dynamic stability characteristics of the aircraft. Obtaining the dynamic stability characteristics is not common on the early stages of the design yet crucial for the aircraft flight performance.

Multidisciplinary analysis and structural optimization for the aeroelastic sizing of a UAV wing using open-source code integration

“…The design and optimization of UAVs are crucial to ensuring their safety, reliability and effectiveness. This requires a thorough understanding of both the aerodynamics and structural aspects of UAVs, as well as their interaction (Mieloszyk, 2021). Advances in computational modeling, analysis and optimization have enabled the development of UAVs with enhanced capabilities, such as longer flight endurance and greater payloads (Goetzendorf-Grabowski et al, 2021).…”

Designing aerodynamic devices for UAV – lessons learned

“…The resulting optimum design has good performance and guarantees excellent aircraft handling characteristics imposed by the flight dynamic stability constraints defined by the flight regulations (EASA CS23, 2018) and norms (MIL-F-8785C, 1980). Development of the optimization framework is presented in Mieloszyk and Goetzendorf-Grabowski, 2017; another example of usage for aircraft design is presented in Mieloszyk, 2020. The outcome is an advanced preliminary design, which has to be followed by a detailed design to reach the manufacturing stage of the aircraft.…”