• 主题
高级搜索  >
历史搜索 清空历史
首页> 外文会议>AIAA Guidance, Navigation and Control Conference Pt.1, Aug 1-3, 1994, Scottsdale, AZ >NEW GUIDANCE LAW FOR A MISSILE WITH VARYING VELOCITY
【24h】

NEW GUIDANCE LAW FOR A MISSILE WITH VARYING VELOCITY

机译：速度变化的导弹的新指导法

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

A new guidance law for a missile with varying velocity is presented. First, the basic guidance equations to compute the missile acceleration command and time-to-go are derived. These equations are available whenever we can predict the intercept point in some way. Taking into account a missile thrust, we obtain the guidance law during boost phase. On the other hand, the guidance law after thrust cutoff is derived by considering an air drag. Three forms of guidance laws are proposed for each phase. One of them, which is called the analytical guidance law, gives the theoretical guidance acceleration commands to guide a missile on the collision course. Though this guidance law is meaningful from the mathematical viewpoint, the guidance equations are too complicated to perform the computation in real time. Thus, we present the approximate guidance law in order to reduce the computation time. This guidance law is useful when it is implemented on a powerful guidance computer on the ground or on the parent aircraft. Next, the approximate guidance law is transformed into the convenient form to realize it on an existing homing missile. Since the obtained form is similar to a conventional augmented proportional navigation, we call it the modified augmented proportional navigation. The guidance laws presented as well as a conventional proportional navigation and an augmented proportional navigation are applied to a simple model of a short range air-to-air missile. Some simulations are performed and then the inner launch envelopes are generated. The simulation results show that the guidance laws presented can intercept the target using far smaller acceleration requirement than prepared for the conventional navigations. When the missile velocity varies significantly, the performance of the conventional navigations are seriously influenced. The inner launch envelopes show that the guidance laws presented provide an overall performance improvement over the conventional navigations. Especially, the modified augmented proportional navigation is useful and attractive from the realistic viewpoint.
机译：提出了一种新型的变速导弹制导律。首先，推导了用于计算导弹加速度指令和飞行时间的基本制导方程。只要我们可以以某种方式预测截距点，这些方程式就可用。考虑到导弹的推力，我们获得了助推阶段的制导律。另一方面，推力截止后的制导律是通过考虑空气阻力得出的。针对每个阶段，提出了三种形式的指导法。其中之一被称为分析制导律，它给出了理论制导加速命令，以在碰撞过程中引导导弹。尽管从数学的观点来看该指导律是有意义的，但是指导方程太复杂而无法实时执行计算。因此，我们提出了近似指导律，以减少计算时间。当在地面或母机上功能强大的制导计算机上实施该制导律时，它很有用。接下来，将近似制导律转换为方便的形式，以在现有的寻的导弹上实现它。由于获得的形式类似于常规的增强比例导航，因此我们将其称为改进的增强比例导航。提出的制导律以及常规比例导航和增强比例导航被应用于短程空空导弹的简单模型。执行一些模拟，然后生成内部发射包络线。仿真结果表明，所提出的制导律可以使用比常规导航所准备的要小得多的加速度要求来拦截目标。当导弹速度变化很大时，常规导航的性能会受到严重影响。内部发射信封表明，与常规导航相比，所提供的制导律提供了整体性能的改进。特别地，从现实的观点来看，改进的增强比例导航是有用的并且具有吸引力。

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