Guidance Laws Against Defended Aerial Targets

The three body engagement scenario is considered where an aerial missile, homing onto a target aircraft, encounters a defender missile launched by the aircraft. A given set of defender missile guidance laws, namely, proportional navigation and line-of-sight guidance are considered and analysis is carried out for proportional navigation and pure pursuit attacking missile strategies. Analytic capture zones and lateral accelerations ratios for the four resulting scenarios are derived. Closed form expression for attacking missile initial position and launch angles are derived for a successful evasion from the defender. Extensive numerical simulations are carried out which comply with the analytical flndings. Nomenclature vt; vd; vm Target, defender, and missile speeds, respectively ∞t; ∞d; ∞m Target, defender, and missile headings, respectively ∞t0; ∞d0; ∞m0 Target, defender, and missile initial headings, respectively _ ∞t; _ ∞d; _ ∞m Target, defender, and missile turning rates, respectively Rd; Rm; Rdm Target-defender, target-missile, and defender-missile closing ranges, respectively Rd0; Rm0; Rdm0 Target-defender, target-missile, and defender-missile initial closing ranges, respectively _ Rd; _ Rm; _ Rdm Target-defender, target-missile, and defender-missile closing range rates, respectively vcdm; vcm Defender-missile and target-missile closing speeds, respectively vcdm0; vcm0 Defender-missile and target-missile initial closing speeds, respectively ‚d; ‚m; ‚dm