Abstract—Foldable mechanisms provide many advantages to the aero vehicles. Especially, low storage volume of the vehicles is the main advantage to use these mechanisms while the vehicle is out of flight. In-flight situation, these
mechanisms must also be activated and deployed. Deployment in a right time, from the folded to deployed position, is critical for flight health of these vehicles. Therefore, engineers make analysis and several tests on prototypes to optimize the deployment time and to design a valid mechanism. In this study, a missile foldable wing mechanism is examined, working principles and key components of the mechanism for deployment process are explained, and optimization studies on mechanical parameters of these components are completed by Design of Experiment (DOE) method. As a result of this study;
parameters of the mechanism components affecting deployment time are determined and a novel foldable missile wing mechanism are designed.
Index Terms—Mechanism, aerospace, optimization, design.
Zafer Külünk is with Roketsan Missiles Industry, Ankara, Turkey (e-mail:
zkulunk@roketsan.com.tr).
Murat Şahin is with the Control Systems Design Department, Ankara, Turkey
[PDF]
Cite: Zafer Külünk and Murat Şahin, "Optimization of Mechanical Design Parameters for
Missile Foldable Wing Mechanism by Using Design of
Experiment Method," International Journal of Modeling and Optimization vol. 9, no. 2, pp. 108-112, 2019.
