The terminal impact-angle-control guidance problem of a homing missile with a physical constraint on seeker's field of view (FOV) limit is considered. The problem is formulated as an infinite horizon non-linear regulator problem with a state constraint, and solved using an extension of the State Dependent Riccati Equation (SDRE) method: first a baseline SDRE controller is designed without taking into account the state constraint, and then a SDRE regulator is designed augmenting the cost functional to take into account the state constraint and the base-line performance. In our design, the state weighting matrix Q is chosen to be a function of time-to-go to include the distance information between the missile and target, and the input weighting matrix R is designed to be a function of the distance of the constrained state to the allowable boundary. Numerical simulations are carried out for different impact angles and seeker's FOV limits, the results of which verify the effectiveness of the proposed guidance approach.
SDRE based impact angle control guidance law considering seeker's field-of-view limit
01.08.2016
695460 byte
Aufsatz (Konferenz)
Elektronische Ressource
Englisch
A Two-Phased Guidance Law for Impact Angle Control with Seeker’s Field-of-View Limit
DOAJ | 2018
|Guidance law switching logic considering the seeker's field-of-view limits
Online Contents | 2009
|Time-Varying Biased Proportional Guidance with Seeker’s Field-of-View Limit
DOAJ | 2016
|Guidance law to control impact time constraining the seeker’s field of view?
Emerald Group Publishing | 2018
|