Introduction G laws for short-range tactical missiles have become a well-researched topic over the past 35 years with publications of analytical treatment and implementation of missile guidance going back to the 1940's Thus, much of the guidance development available in the literature predates that which is known as modern control theory These early concepts, now commonly referred to as classical guidance, have been used from that time to the present to command missiles during their homing phases of flight to target impact To the extent that assumptions of comparable relative velocity and certain conditions on relative bearing between the pursuer and target were valid, the classical guidance techniques remained adequate However, evidence is evolving which suggests that the performance of present weapon systems may be seriously degraded in engagements against targets with predicted characteristics of the 1990's and beyond and in the battlefield environments of that time frame It has been established that the guidance laws currently in wide use may not be adequate in defeating those threats Thus, it is projected that fundamental advances in the application of control systems theory is required to enhance the guidance effectiveness of future missile weapon systems Additionally, missile air frame and propulsion systems also may require advances appropriate to defeat predicted targets In particular, air defense and air-to-air weapons currently undergoing research and development utilizing classical guidance technology may be seriously hampered in the combat scenarios envisioned In evaluating the extensive literature on guidance laws applicable to short-range missiles, the lack of a suitable survey became apparent Although excellent reviews of related topics such as optimal control' and sensitivity methods had appeared while those fields were relatively young, the missile guidance literature was found to be highly decentralized and fragmented This may be attributed, in part, to the fact that literature for guidance laws was usually classified for security purposes These works were rarely published beyond internal industrial reports, and though not made public they became reference documentation for missile designers spanning a period of over 35 years With classical techniques implemented even in today's highly sophisticated systems, the literature gave credence to a widely accepted definition of classical terminal homing and defined its extensions into the modern era It was observed that guidance laws typically fit within the following five categories, the first three of which are the well-known classical techniques: lineof-sight (LOS), pursuit, proportional navigation guidance

Guidance Laws for Short-Range Tactical Missiles

Impact Angle Constrained Integrated Guidance and Control for Maneuvering Target Interception

The problem of intercepting a maneuvering target at a prespecified impact angle is posed in nonlinear zero-sum differential games framework. A feedback form solution is proposed by extending state-dependent Riccati equation method to nonlinear zero-sum differential games. An analytic solution is obtained for the state-dependent Riccati equation corresponding to the impact-angle-constrained guidance problem. The impact-angle-constrained guidance law is derived using the states line-of-sight rate and projected terminal impact angle error. Local asymptotic stability conditions for the closed-loop system corresponding to these states are studied. Time-to-go estimation is not explicitly required to derive and implement the proposed guidance law. Performance of the proposed guidance law is validated using two-dimensional simulation of the relative nonlinear kinematics as well as a thrust-driven realistic interceptor model.

Nonlinear Differential Games-Based Impact-Angle-Constrained Guidance Law

This paper examines the problem of guiding a missile to a target using minimal energy. First, an optimal controller is developed for a missile that has arbitrary control over its acceleration vector. Next, an optimal controller is sought for a missile that has a directional control constraint, which is intended to model the actual constraint present in aerodynamically controlled missiles. The optimal guidance law is shown to have a very convenient form that is directly related to the optimal guidance law without the control constraint. Simulation results are conducted to completely characterize the new guidance law.

Minimum Energy Guidance for Aerodynamically Controlled Missiles

This paper aims to examine the potential of using the emerging deep reinforcement learning techniques in missile guidance applications. To this end, a Markovian decision process that enables the ap...

https://arc.aiaa.org/doi/pdf/10.2514/1.I010970

Computational Missile Guidance: A Deep Reinforcement Learning Approach

On nonzero miss distance.

the height between the model-release point and the water surface. The accelerations were measured by strain-gage type accelerometers, and the records were traced on an oscilloscope and photographed. The two accelerometers used were a ±100 g Kyowa accelerometer with a natural frequency of 2000 cps and a ±200 g accelerometer with a natural frequency of 3000 cps. Both were damped to 65% of critical damping. A Kyowa amplifier was used which had a carrier frequency of 20,000 cps.

A. G. Rawling

Papers

On nonzero miss distance.

Prediction of terminal variables in homing

Nonlinear proportional navigation and the minimum time-to-turn