...
  • 主题
高级搜索  >
历史搜索 清空历史
首页> 外文期刊>Mathematical Problems in Engineering >Trajectory Optimization for a Cruising Unmanned Aerial Vehicle Attacking a Target at Back Slope While Subjected to a Wind Gradient
【24h】

Trajectory Optimization for a Cruising Unmanned Aerial Vehicle Attacking a Target at Back Slope While Subjected to a Wind Gradient

机译：风力梯度对巡航后坡目标的巡航无人机的航迹优化

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

The trajectory of a tubular launched cruising unmanned aerial vehicle is optimized using the modified direct collocation method for attacking a target at back slope under a wind gradient. A mathematical model of the cruising unmanned aerial vehicle is established based on its operational and motion features under a wind gradient to optimize the trajectory. The motion characteristics of "altitude adjustment" and "suicide attack" are taken into full account under the combat circumstance of back slope time key targets. By introducing a discrete time function, the trajectory optimization is converted into a nonlinear programming problem and the SNPOT software is applied to solve for the optimal trajectory of the missile under different wind loads. The simulation results show that, for optimized trajectories, the average attack time decreased by up to 29.1% and the energy consumption is reduced by up to 25.9% under specified wind gradient conditions. A, omega(dire), and W-max have an influence on the flight trajectories of cruising unmanned aerial vehicle. This verifies that the application of modified direct collocation method is reasonable and feasible in an effort to achieve more efficient missile trajectories.
机译：使用改进的直接配置方法优化了管状巡航巡航无人机的轨迹，以在风梯度下攻击后坡目标。基于风速梯度下的运行和运动特征，建立了巡航无人机的数学模型，以优化航迹。在后坡时间关键目标的战斗情况下，充分考虑了“海拔调整”和“自杀攻击”的运动特征。通过引入离散时间函数，将轨迹优化转化为非线性规划问题，并应用SNPOT软件求解导弹在不同风荷载下的最优轨迹。仿真结果表明，在优化的航迹下，在特定的风梯度条件下，平均攻击​​时间最多可减少29.1％，能耗最多可减少25.9％。 A，ω（dire）和W-max对巡航的无人机的飞行轨迹有影响。这证明了改进的直接配置方法的应用是合理和可行的，以实现更有效的导弹弹道。

著录项

  • 来源
    《Mathematical Problems in Engineering》 |2015年第12期|635395.1-635395.14|共14页
  • 作者

    Jiang Tieying; Li Jie; Li Bing; Huang Kewei; Yang Chengwei; Jiang Yimeng;

  • 作者单位

    Beijing Inst Technol, Sch Mech Engn, Beijing 100081, Peoples R China;

    Beijing Inst Technol, Sch Mech Engn, Beijing 100081, Peoples R China;

    Beijing Inst Technol, Sch Mech Engn, Beijing 100081, Peoples R China;

    Beijing Inst Technol, Sch Mech Engn, Beijing 100081, Peoples R China;

    Beijing Inst Technol, Sch Mech Engn, Beijing 100081, Peoples R China;

    China Acad Launch Vehicle Technol, Beijing 100076, Peoples R China;

  • 收录信息
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

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