Spincopter Wing Design and Flight Control

被引：8

作者：

Orsag, Matko ^{[1
]}

Cesic, Josip ^{[1
]}

Haus, Tomislav ^{[1
]}

Bogdan, Stjepan ^{[1
]}

机构：

[1] Univ Zagreb, Fac Elect Engn & Comp, Lab Robot & Intelligent Control Syst, Zagreb 10000, Croatia

来源：

JOURNAL OF INTELLIGENT & ROBOTIC SYSTEMS | 2013年 / 70卷 / 1-4期

关键词：

UAV; Rotorcraft; Control; Aerodynamics; MICRO-AIR VEHICLES; INSECT FLIGHT; SEEDS; AERODYNAMICS; SAMARA;

D O I：

10.1007/s10846-012-9725-2

中图分类号：

TP18 [人工智能理论];

学科分类号：

081104 ; 0812 ; 0835 ; 1405 ;

摘要：

This paper presents dynamical properties of an unmanned aerial vehicle (UAV), called spincopter. The vehicle structure is based on two wings that are forced in rotation (spinning) by propulsion system formed of two propellers. Based on devised dynamical model, that reveals inherent stability of the vehicle, composition of control algorithms for vertical and horizontal movement is proposed. Due to the specific configuration of the propulsion system, movement in horizontal direction is produced by pulsations in rotational speed of propulsion motors. An analysis of influence that such a configuration has on the vehicle dynamics is given. Finally, design recommendations for rotational wings are elaborated, based on extensive simulations of spincopter by using X-PlaneA (R) software package.

引用

页码：165 / 179

页数：15

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