协同拦截：两弹一目标打击策略

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"AAM Two-on-one Cooperative Interception with Controllable Impact Time Difference" 这篇研究论文探讨了两枚空对空导弹（AAM）合作拦截一个目标并能控制撞击时间差的问题。在空战防御和攻击中，这样的合作拦截策略能够提高打击效率，减少敌方规避的可能性，同时优化导弹资源的使用。首先，文章建立了序列合作拦截的模型。在这个模型中，两枚导弹协同工作，共同对付一个目标，而不是各自独立行动。这种协同拦截策略旨在最大化拦截的成功率，并通过精确控制导弹的撞击时间差来提高战术效果。接着，论文基于理想的比例导航（IPG）理论，提出了两种序列合作制导律。第一种方法是通过调整导航常数来实现合作，这允许导弹根据目标动态和环境条件调整飞行轨迹。第二种方法则是在导弹上增加一个协调加速度分量，这种协调加速度使得两枚导弹可以同时调整速度和方向，从而实现预定的撞击时间差。在理论分析的基础上，论文进行了数值模拟，以验证所提出的序列合作制导律的有效性。数值模拟的结果表明，通过应用协调加速度，不仅可以实现两枚导弹到达目标的时间差可控，而且可以降低达到目标所需时间的方差，这意味着导弹的攻击精度和时间同步性得到了显著提升。关键词：合作拦截；撞击时间差；空对空导弹；序列合作这篇论文的研究成果对于现代空战策略设计、导弹系统优化以及防御系统开发具有重要的理论与实践价值。通过深入理解并应用这些理论，军事研究人员和工程师可以设计出更高效、更灵活的拦截系统，增强空中战斗能力。

AAM Two-on-one Cooperative Interception with Controllable Impact Time

Difference

Jiaqiang Zhang, Xiaolong Liang

, Zhenqing Shi, Shenghou Li

National Key Laboratory of Air Traffic Collision Prevention

Air Force Engineering University

Xi’an, China

afeu_lxl@163.com

Abstract—Two air-to-air missiles (AAM) cooperative

interception one target with controllable impact time

difference was investigated. The sequential cooperative

interception engagement was modeled first. Then, based on the

ideal proportional navigation (IPG), two sequential

cooperative guidance laws were proposed, one by changing the

navigation constant, while the other by adding a coordination

acceleration component. Finally, numerical simulations were

presented to illustrate the effectiveness of the proposed

sequential cooperative guidance law. It is shown that the time-

to-go variance can be cooperatively decreasing and the

expected impact time difference can be achieved by adding the

proposed coordination acceleration component.

Keywords- cooperative interception; impact time difference;

air-to-air missile; sequential cooperative guidance law

I. INTRODUCTION

Throughout the ages, warfare, wherever it may be, in the

sky, on the ground, or at the sea, cooperation is the centre,

the cooperation tactics determines whom the victory of the

war belongs to. And cooperation in interceptor missile

engagements can be used to create a favorable relative

geometry, which can improve performance and reduce

control effort. Specifically, cooperation in missile guidance

engagements can be used to saturate the target’s defenses

(e.g., using a salvo attack), limit the target’s evasive

possibilities (e.g., by controlling the relative geometry), and

even lure the target into a trap at some scenarios. It can also

be used to improve observability, by generating different

view angles near interception[1-3].

There are potentially two possible modes of cooperation

in guidance: 1) implicit cooperation, in which there is some

coordination parameter between the vehicles; and 2) explicit

cooperation, in which the guidance law explicitly optimizes

some team performance criteria.

Most studies dealing with cooperation interception

problem are formulated for the case of multimissiles trying

to capture a single target simultaneously. Such studies were

conducted over the years to deal with geometrical constraints,

mostly with the constraint of a terminal interception angle.

Whether stationary target or maneuvering target, the

approach to deal with these kinds of problems includes the

traditional guidance laws, such as proportional navigation

(PN)[4-8], and modern missile guidance law, such as the

optimal guidance law[9-10], sliding mode guidance law[11],

differential game guidance law[12] and model predictive

control[13].

Simultaneously attacking is excellent for puncturing the

missile defense system of the warship or ground base. But

for maneuvering fighter target, that’s another story. Any of

the Chaff, Infrared Decoy, Electronic Jamming and the

escaping maneuvering of the fighter can lead the missile

attack failure. If the multimissiles arrival simultaneously,

they may fail simultaneously. It is a wise strategy for the

multimissiles to arrival sequentially with scheming time

difference, when the pilot burst out of the first missile, the

second missile is bombing in front of him.

To the best of our knowledge, none of the

aforementioned cooperation guidance laws in the open

literature enable imposing a controllable impact time

difference between the missiles. This paper fills this gap by

presenting cooperative guidance laws based on the ideal

proportional navigation (IPG), which explicitly enable

imposing a controllable and adjustable impact time

difference between the missiles.

The remainder of this paper is organized as follows: the

sequential cooperative interception engagement is presented

first, and to gain controllable impact time difference, two

cooperative guidance laws based on the ideal proportional

navigation are developed in Sec. III. A performance analysis

of the proposed algorithm is presented in Sec. IV, followed

by concluding remarks.

II. P

ROBLEM FORMULATION

The planar engagement of the two air-to-air missiles

cooperative interception one target with controllable time

difference of arrival is

considered. Its schematic view is

given in Fig. 1. We assume that after the 1th missile

‘impact’ the target, the target will go on flying until the 2th

missile hit it. Variables associated with the 1th and 2th

missile and the target are denoted by additional subscripts 1,

2, and T, respectively. The speed, normal acceleration, and

flight-path angles are denoted by V, a, and Ȗ, respectively;

the range between each missile and the target is denoted as

. The angle between the ith missile-to-target line of sight

(LOS

) and the Cartesian inertial reference frame X axis is Ȝ

;

and the angle between the LOS

and speed vector of missile i

and the target are denoted by ș

and ș

. The acceleration

commands normal to velocity for the missile and the target

are described by a

and a

, respectively.

2286

2018 IEEE/CSAA Guidance, Navi

ation and Control Conference

ust 10-12, 2018 Xiamen, China

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