Abstract

This paper details a quantitative investigation into a cost-effective, three degree-of-freedom test rig to determine aircraft static and dynamic stability derivatives. The technique used a specifically designed three degree-of-freedom gimbaled mechanism to connect an actively controlled model to a vertical support strut. The support strut was also mounted on a six-component piezoelectric balance to obtain aerodynamic force and moment data simultaneously with the model motion. With only minor modifications to the overall setup, a comprehensive set of static and dynamic stability derivatives were obtained which showed reasonable to good agreement with other, independently obtained, data.

Full Text
Published version (Free)

Talk to us

Join us for a 30 min session where you can share your feedback and ask us any queries you have

Schedule a call