Differential Game Guidance Law for Interceptor Missiles with a Time-varying Lateral Acceleration Limit
نویسندگان
چکیده
منابع مشابه
Bounded Differential Game Guidance Law for Interceptor Missiles with Aero Fins and Reaction Jets
A differential game guidance law for an endoatmospheric interceptor missile steered by aero fins and reaction jets is developed in this paper with bounded controls. For a low-altitude endoatmospheric interceptor, the propellant of the reaction-jet control system (RCS) is restricted by the missile configuration. Considering propellant limits, the effect of the RCS thrust on homing performance is...
متن کاملDifferential Game Based Guidance Law for High Angle of Attack Missiles
Differential Game Based Guidance Law for High Angle of Attack Missiles By P. K. Menon and G.B. Chatterji Optimal Synthesis 450 San Antonio Road, Suite 53 Palo Alto, CA 94303 Abstract A nonlinear differential game theoretic intercept guidance law for short range missiles is derived. Differential geometric transformations are used to convert the nonlinear missile and the target models into a conv...
متن کاملDifferential Game Based Guidance Law for High Angle of Attack Missiles By
Differential Game Based Guidance Law for High Angle of Attack Missiles By P. K. Menon and G.B. Chatterji Optimal Synthesis 450 San Antonio Road, Suite 53 Palo Alto, CA 94303 Abstract A nonlinear differential game theoretic intercept guidance law for short range missiles is derived. Differential geometric transformations are used to convert the nonlinear missile and the target models into a conv...
متن کاملTime-to-go Polynomial Guidance with Impact Angle Constraint for Missiles of Time-Varying Velocity
In this paper, a Time-to-go Polynomial Guidance (TPG) law satisfying impact angle constraints for missiles of time-varying velocity against stationary target is investigated. The guidance law assumes the magnitude of guidance commands as a polynomial function of time-to-go with two unknown coefficients. The coefficients are determined to satisfy the two terminal constraints, which are the termi...
متن کاملEvolutionary Guidance for Multiple Missiles
A new approach to guiding a swarm of missiles using an on-line evolutionary algorithm to optimise the flight paths is introduced. The missiles are flown via intermediate points which are adjusted dynamically by the evolutionary algorithm, then towards the point of impact with the target, thus altering the trajectory shape. Evolutionary algorithms are robust global optimisation techniques and ar...
متن کاملذخیره در منابع من
با ذخیره ی این منبع در منابع من، دسترسی به آن را برای استفاده های بعدی آسان تر کنید
ژورنال
عنوان ژورنال: TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
سال: 2011
ISSN: 0549-3811
DOI: 10.2322/tjsass.54.189