The invention discloses an
aerospace vehicle combined navigation
robust filtering method based on a launching
inertia coordinate
system, belonging to the technical field of air vehicle combined navigation. The
aerospace vehicle combined navigation
robust filtering method comprises the following steps of performing inertial navigation
algorithm arrangement by taking the launching
inertia coordinate
system as a reference coordinate
system, and constructing a position, speed and posture calculation model of an air vehicle under the launching
inertia coordinate system; on the basis of the position, speed and posture calculation model, constructing an equation of
navigation system error states including a basic navigation
parameter error and an inertia
instrument error, and obtaining a posture
linear measurement equation through a conversion module according to original
star sensor measurement information; and finally estimating and correcting all state values in the constructed state equation by the
robust filtering method. According to the
aerospace vehicle combined navigation robust filtering method disclosed by the invention, the influence, caused by a geophysical field, on the
navigation system of the air vehicle can be effectively reduced; furthermore, under a condition that the
navigation system model of the air vehicle is inaccurate, a filter can work stably; therefore, the precision of a combined navigation system is improved.