Analysis of Flight and Ground Motion of a Fixed-wing UAV during Landing Phase
This paper presents the analysis of the automatic landing guidance and control law for a small UAV under the condition of atmospheric disturbance including crosswind. The automatic landing control system consists of guidance and control laws for approach-flare in the airfield and ground steering after touchdown. The guidance and control law for approach and flare generates guidance commands for the specified landing patterns and control commands to track the desired altitude, velocity and heading angle. The braking and steering control not only stabilizes the aircraft’s ground run motion under the crosswind condition, but also tracks the centerline of the runway. The landing gear effect is added into the aircraft in six degrees of freedom rigid body model to watch the whole tracking performance and the continuous simulation including approach, flare, touchdown, steering and braking in the presence of crosswind.
automatic landing landing gear model guidance steering control
Ji Tae Kim Boo Min Kim Byoung Soo Kim
School of Aerospace Engineering Gyeongsang National University, Jinju, Korea Department of Aerospace Engineering,Gyeongsang National University, Jinju, Korea
国际会议
2011年亚太航空航天技术学术会议(APISAT 2011)
澳大利亚
英文
1-14
2011-02-28（万方平台首次上网日期，不代表论文的发表时间）