• 主题
高级搜索  >
历史搜索 清空历史
首页> 外文会议>International powered lift conference (IPLC 2008) >Development of a VTOL Mini UAV for Multi-Tasking Missions
【24h】

Development of a VTOL Mini UAV for Multi-Tasking Missions

机译：开发用于多任务任务的VTOL微型无人机

获取原文
获取原文并翻译 | 示例
页面导航
  • 摘要
  • 著录项
  • 相似文献
  • 相关主题

摘要

Recent developments in the field of Mini-UAVs lead to successful designs in both hovering rotorcraft and forward flight fixed wing aircraft. However, a polyvalent MAV capable of stable hovering and fast forward flight in windy conditions is still expected. A promising candidate for such versatile missions consists of a tilt-body coaxial tail-sitter configuration. That concept is studied in this paper both from the flight mechanics and control points of view. Developments are based on an existing prototype called VERTIGO which is capable of transition flights. It consists in a tail sitter fixed-wing mini-UAV equipped with a contra-rotating pair of propellers in tractor configuration.rnA wind tunnel campaign was carried out to extract experimental results from the VERTIGO aerodynamic characteristics. A 6-component sting balance was fitted in the powered model enabling excursion in angles of attack and sideslip angles up to 90°. Thus, a detailed understanding of the transition mechanism could be obtained. Hot wire measurements were done on a smaller contra-rotating propulsion system so as to obtain a clearer picture of the flow behind the propeller. An analytical model including propwash effects was derived from experimental results.rnThe analytical model was used to compute stability modes for specific flight conditions. This allowed an appropriate design of the autopilot capable of stabilization and control over the whole flight envelope. A gain sequencing technique was chosen to ensure stability while minimizing control loop execution time. A MATLAB-based flight simulator including an analytical model for the propeller slipstream has been developed in order to test the validity of airborne control loops.rnMany flight tests were performed with the VERTIGO prototype in different environments (indoor, outdoor with wind ...) and with various degrees of autonomy (attitude control, position control, automatic navigation). Simulation results will be presented in the present paper including hover flight, forward flight and transitions.
机译：小型无人飞行器领域的最新发展导致了旋翼飞机和前向飞行固定翼飞机的成功设计。然而，仍然期望能够在大风条件下稳定地盘旋和快速向前飞行的多价MAV。这种多功能任务的有前途的候选者包括倾斜机体的同轴尾翼配置。本文从飞行力学和控制角度对这一概念进行了研究。该开发基于名为VERTIGO的现有原型，该原型具有过渡飞行能力。它由尾桨固定翼mini-UAV组成，该无人机在拖拉机配置中装有一对反向旋转的螺旋桨。进行了风洞运动以从VERTIGO空气动力学特性中提取实验结果。动力模型中装有6组件的ing秤，可实现迎角和最大90°的侧滑角偏移。因此，可以获得对过渡机制的详细理解。热线测量是在较小的反向旋转推进系统上进行的，以便更清楚地了解螺旋桨后面的流动情况。从实验结果中得出了包括洗药效果的分析模型。该分析模型用于计算特定飞行条件下的稳定模式。这样就可以对自动驾驶仪进行适当的设计，使其能够稳定和控制整个飞行包线。选择一种增益排序技术以确保稳定性，同时最大程度地减少控制循环的执行时间。为了测试机载控制环的有效性，已经开发出了基于MATLAB的飞行模拟器，其中包括用于螺旋桨滑流的分析模型.rn许多飞行试验都是使用VERTIGO原型在不同环境（室内，室外有风...）下进行的并具有不同程度的自主权（姿态控制，位置控制，自动导航）。仿真结果将在本文中介绍，包括悬停飞行，向前飞行和过渡。

著录项

相似文献

  • 外文文献
  • 中文文献
  • 专利
获取原文

客服邮箱：kefu@zhangqiaokeyan.com

京公网安备：11010802029741号 ICP备案号：京ICP备15016152号-6 六维联合信息科技 (北京) 有限公司©版权所有

  • 客服微信

  • 服务号