反临近空间高超声速目标拦截弹中末制导交接班窗口

在视线旋转坐标系下建立拦截弹与目标的相对运动方程,分析采用纯比例导引律捕获高超声速目标的充分条件,并推导出在交接班处的最优拦截几何,即零控拦截流型。定性分析了拦截弹速度、高度、导引头特性以及末制导捕获条件等在中末制导交接班时所受到的限制,在此基础上定义了中末制导交接班窗口的概念,并介绍了交接班捕获窗口的影响因素、用途、特性以及计算步骤。以纯比例导引律拦截高速目标为例,定量描述了交接班捕获窗口和零控交接班区域,并通过数字仿真实验验证了交接班捕获窗口的合理性。

真比例导引反高速目标拦截能力分析

针对反高速目标拦截作战过程中拦截弹中末制导交接班时刻状态约束设置的问题,分析了真比例导引制导律的拦截能力。首先,通过分析末制导阶段拦截弹和目标的相对运动关系,推导得到了成功拦截目标的充分必要条件以及目标速度前置角需要满足的约束范围;其次,在中末制导交接班不满足拦截条件的情况下,针对拦截高速非机动目标作战情形,通过分析拦截弹速度前置角和目标速度前置角的变化关系,给出了真比例导引静态捕获区(static capture region,SCR)的定义以及构成;然后,针对拦截高速机动目标作战情形,结合目标速度前置角约束范围得到了真比例导引动态捕获区(dynamic capture region,DCR)的定义以及构成;最后开展了3种情形下的数字仿真,验证了真比例导引拦截能力分析的合理性和有效性。

真比例导引律的解析解研究

描述比例导引律的模型都是非线性微分方程组,不易求解,常规求解方法是线性化。对真比例导引律进行了详细推导,并和纯比例导引律进行了比较和分析,通过坐标变换和引入相对运动的单位角动量,获得了解析的捕获域和截获时间。研究结果表明,真比例导引律的捕获域受到导航比的限制,纯比例导引律的捕获域在一定条件下不受导航比限制。

Capturability of 3D RTPN guidance law against true-arbitrarily maneuvering target with maneuverability limitation

The capturability of the Three-Dimensional(3D)Realistic True Proportional Navigation(RTPN)guidance law is thoroughly analyzed.The true-arbitrarily maneuvering target is considered,which maneuvers along an arbitrary direction in 3D space with an arbitrary but upperbounded acceleration.The whole nonlinear relative kinematics between the interceptor and target is taken into account.First,the upper-bound of commanded acceleration of 3D RTPN is deduced,using a novel Lyapunov-like approach.Second,the reasonable selection range of navigation gain of3D RTPN is analyzed,when the maneuver limitation of interceptor is considered.After that,a more realistic definition of capture is adopted,i.e.,the relative range is smaller than an acceptable miss-distance while the approaching speed is larger than a required impact speed.Unlike previous researches which present Two-Dimensional(2D)capture regions,the inequality analysis technique is utilized to obtain the 3D capture region,where the three coordinates are the closing speed,transversal relative speed,and relative range.The obtained capture region could be taken as a sufficient-but-unnecessary condition of capture.The new theoretical findings are all given in explicit expressions and are more general than previous results.

Capurability analysis for arbitrarily high-speed maneuvering targets

The capturability of an arbitrarily maneuvering target featuring speed superiority over an interceptor is analyzed for Augmented Pure Proportional Navigation(APPN)and RetroAugmented Proportional Navigation(RAPN)guidance.This paper focuses on intercepting arbitrary maneuvers to study more general interception problems.A comparative analysis of the capture region between head-on interception related to APPN and head-pursuit interception related to RAPN is proposed.The results indicate that RAPN performs better than APPN in capturability.It is concluded that increasing the target velocity,which increases the velocity ratio,significantly weakens the capturability of the interceptor,and the average acceleration and relative distance affect the location of the capture region but not its size.The analysis is based on prior knowledge of the target maneuver,which inevitably leads to deviations from actual maneuvers in practical engagement,so a deviation analysis is implemented.The effective capture region shrinks as the absolute value of acceleration deviation increases,and the RAPN has a better deviation fault tolerance compared with the APPN.The results reveal that a larger relative distance can weaken the deviation fault tolerance,and the target velocity has opposite effects on head-on and head-pursuit interception.

New Result on Interception of Stationary Targets at Arbitrary Time-Varying Speed

This paper develops a novel approach and some main results on the varying-speed missile guided by pure proportional navigation(PPN)against a stationary target in the planar interception problem.The missile kinematic equation is established in the arc-length domain based on the differential geometry theory,which eliminates the influence of time-varying missile speed.Then,the closed-form solutions of line-of-sight(LOS)rate,leading angle,closing speed,and curvature command are derived in the arc-length domain.The performance of the varyingspeed missile is analyzed,including the maximum relative distance,maximum curvature command,accurate path-to-go,and curvature increment.Additionally,the capture region is obtained considering the missile maneuvering acceleration limit.These new theoretical results could be extended to improve the performance of existing guidance laws designed under the constant-speed assumption.