Simulator Development for Transition Flight Dynamics of a VTOL MAV
نویسندگان
چکیده
منابع مشابه
Transition Flight of Quad Tilt Wing Vtol Uav
The QTW VTOL UAV, which features tandem tilt wings with propellers mounted at the mid-span of each wing, is one of the most promising UAV configurations, having both VTOL capability and high cruise performance. A six-degree-of-freedom dynamic simulation model covering the full range of the QTW flight envelope was developed and a flight control system including a transition schedule and a stabil...
متن کاملAutonomous Flight of a Samara MAV
Conventionally Micro/Nano scaled hovering flight presents a myriad of challenges and unique design opportunities. The culmination of microelectronics and state of the art measuring devices has enabled the creation of a Micro-air-vehicle (MAV 1 ) resembling one of nature’s most efficient fliers, the seed of the Maple tree. The planform design of the VTOL mechanical samara is based on previous wo...
متن کاملSky/ground modeling for autonomous MAV flight
Recently, we have implemented a computervision based horizon-tracking algorithm for flight stability and autonomy in Micro Air Vehicles (MAVs) [1]. Occasionally, this algorithm fails in scenarios where the underlying Gaussian assumption for the sky and ground appearances is not appropriate. Therefore, in this paper, we present a general statistical image modeling framework which we use to build...
متن کاملDynamic System Identification, and Control for a cost effective open-source VTOL MAV
This paper describes dynamic system identification, and full control of a cost-effective vertical take-off and landing (VTOL) multi-rotor micro-aerial vehicle (MAV) — DJI Matrice 100. The dynamics of the vehicle and autopilot controllers are identified using only a built-in IMU and utilized to design a subsequent model predictive controller (MPC). Experimental results for the control performanc...
متن کاملImproved Mathematical Model for Helicopters Flight Dynamics Applications
The purpose of this paper is concerned with the mathematical model development issues, necessary for a better prediction of dynamic responses of articulated rotor helicopters. The methodology is laid out based on mathematical model development for an articulated rotor helicopters, using the theories of aeroelastisity, finite element and the time domain compressible unsteady aerodynamics. The he...
متن کاملذخیره در منابع من
با ذخیره ی این منبع در منابع من، دسترسی به آن را برای استفاده های بعدی آسان تر کنید
ژورنال
عنوان ژورنال: International Journal of Micro Air Vehicles
سال: 2010
ISSN: 1756-8293,1756-8307
DOI: 10.1260/1756-8293.2.2.69