| Article ID | Journal | Published Year | Pages | File Type |
|---|---|---|---|---|
| 8058267 | Aerospace Science and Technology | 2018 | 10 Pages |
Abstract
This paper presents a unified framework for addressing the stability analysis of the hovering condition for a multirotor vehicle. By linearization about a trim condition, a decoupled model made of four dynamic modes is derived. A set of stability derivatives is obtained and the effect on natural dynamic stability of design parameters such as arm dihedral and rotor tilt angles is analyzed. A numerical test case is finally discussed in support of the proposed approach.
Related Topics
Physical Sciences and Engineering
Engineering
Aerospace Engineering
Authors
Emanuele L. de Angelis,