• 主题
高级搜索  >
历史搜索 清空历史
首页> 外文会议>International Conference on Mechanical Engineering and Mechanics vol.2; 20051026-28; Nanjing(CN) >New Method for Calculating the Vulnerability of Aircraft to a Fragment of Missile
【24h】

New Method for Calculating the Vulnerability of Aircraft to a Fragment of Missile

机译：计算飞机易碎性的新方法

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

At present, when computing the vulnerability of an aircraft to a single fragment of missile, the assumptions are usually made that the threat travels along a parallel and straight trajectory and no ricochet occurs. This paper proposes a new calculation method for considering the effects of ricochet on the aircraft vulnerability assessment. In this method, the JTCG/ME penetration equations are adopted to calculate the actual path and the change of state-of-motion of fragment. Using 'shotline scanning method', the vulnerable area corresponding to each shotline is calculated and thus the vulnerable area and kill probability of the aircraft are obtained. In the example, comparison of the vulnerability for the 26 standard threat aspects using the proposed method and the commonly used method shows the effectiveness and feasibility of the new method. Analysis shows that, (1) the proposed new method provides a realistic and effective aircraft vulnerability assessment, (2) when the ricochet of fragment is considered, the computed aircraft vulnerability will increase compared with the case which does not consider the ricochet, and the increment is relative and sensitive to the threat aspect, and (3) in the aircraft combat survivability or vulnerability assessment, the fragment ricochet should not be ignored.
机译：目前，在计算飞机对单个导弹碎片的脆弱性时，通常会假设威胁沿着平行且笔直的轨迹行进，而不会发生跳弹。本文提出了一种新的计算方法来考虑跳弹对飞机脆弱性评估的影响。在这种方法中，采用JTCG / ME渗透方程来计算实际路径和碎片运动状态的变化。使用“炮弹线扫描方法”，计算与每个炮弹线相对应的易受伤害区域，从而获得飞机的易受伤害区域和致死概率。在示例中，使用所提出的方法和常用方法对26个标准威胁方面的漏洞进行了比较，显示了该新方法的有效性和可行性。分析表明，（1）所提出的新方法提供了切实有效的航空器脆弱性评估，（2）当考虑碎片弹跳时，与不考虑弹跳的情况相比，计算出的航空器脆弱性将增加，并且增量相对于威胁方面是相对敏感的，并且（3）在飞机战斗的生存能力或脆弱性评估中​​，不应忽略碎片弹跳。

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