A look angle rate should be considered as a significant constraint for maintaining seeker lock-on condition throughout the engagement because a strapdown imaging infrared (IIR) seeker with an uncooled microbolometer detector might produce blurred target images and fail to track the target when a certain large look angle rate is generated. For preventing such motion blurring effects of strapdown IIR seekers in practical engagement scenarios, this paper extends the previously developed two-dimensional homing guidance law to the three-dimensional guidance law, which can intercept moving targets as well as limit the magnitude of the look angle rate within a given maximum rate. To evaluate the characteristics and interception conditions of the suggested three-dimensional guidance, an analytic switching time solution of the guidance law is also newly derived based on the closed-form solutions in the two-dimensional linearized kinematics. Nonlinear simulations with an ideal missile model and a more realistic missile including lag systems are carried out to confirm the guidance performance of the proposed law.
A look angle rate should be considered as a significant constraint for maintaining seeker lock-on condition throughout the engagement because a strapdown imaging infrared (IIR) seeker with an uncooled microbolometer detector might produce blurred target images and fail to track the target when a certain large look angle rate is generated. For preventing such motion blurring effects of strapdown IIR seekers in practical engagement scenarios, this paper extends the previously developed two-dimensional homing guidance law to the three-dimensional guidance law, which can intercept moving targets as well as limit the magnitude of the look angle rate within a given maximum rate. To evaluate the characteristics and interception conditions of the suggested three-dimensional guidance, an analytic switching time solution of the guidance law is also newly derived based on the closed-form solutions in the two-dimensional linearized kinematics. Nonlinear simulations with an ideal missile model and a more realistic missile including lag systems are carried out to confirm the guidance performance of the proposed law.