Impact Angle Control Guidance Synthesis for Evasive Maneuver against Intercept Missile

Abstract

This paper proposes a synthesis of new guidance law to generate an evasive maneuver against enemy's missile interception while considering its impact angle, acceleration, and field-of-view constraints. The first component of the synthesis is a new function of repulsive Artificial Potential Field to generate the evasive maneuver as a real-time dynamic obstacle avoidance. The terminal impact angle and terminal acceleration constraints compliance are based on Time-to-Go Polynomial Guidance as the second component. The last component is the Logarithmic Barrier Function to satisfy the field-of-view limitation constraint by compensating the excessive total acceleration command. These three components are synthesized into a new guidance law, which involves three design parameter gains. Parameter study and numerical simulations are delivered to demonstrate the performance of the proposed repulsive function and guidance law. Finally, the guidance law simulations effectively achieve the zero terminal miss distance, while satisfying an evasive maneuver against intercept missile, considering impact angle, acceleration, and field-of-view limitation constraints simultaneously.

A hierarchical reinforcement learning method for missile evasion and guidance

“…Finally, this paper compares the proposed hierarchical PPO guidance method with traditional guidance methods based on 6 . A guidance synthesis was designed for this combat scenario in 6 .…”

“…Finally, this paper compares the proposed hierarchical PPO guidance method with traditional guidance methods based on 6 . A guidance synthesis was designed for this combat scenario in 6 . The acceleration command of the missile consists of three parts: an artificial potential field(APF), polynomial guidance function, and logarithmic barrier function(LBF).…”

“…However, most weapons used in CIWSs are cannons, which are quite different from a homing guidance missile. Yogaswara et al 6 studied the evasion strategy of attack missiles against the interceptor missiles of an integrated air defense system. The attack missile needs to avoid interception of the interceptor missiles and eventually guide to the target.…”

“…The attack missile needs to avoid interception of the interceptor missiles and eventually guide to the target. A synthesis guidance law is proposed in 6 , which uses an artificial potential field function, time-to-go polynomial guidance law, and logarithmic barrier function to solve the evasion command, impact angle and acceleration constraints, and field-of-view (FOV) constraints. The proposed synthesis guidance law has good performance, however, there are many parameters involved, which make it difficult to choose the optimal value.…”