Maneuvering target relative navigation method based on extended observer and auxiliary information estimation

The invention discloses a maneuvering target relative navigation method based on an extended observer and auxiliary information estimation. The maneuvering target relative navigation method comprisesthe following steps: step 1, establishing an orbital dynamics state equation and an observation equation of two satellites; 2, calculating the acceleration of the target aircraft caused by the tethered towing force according to the tethered acting force between the control aircraft and the target aircraft; 3, establishing an expansion observer by taking the relative acceleration of the two satellites as an increased state quantity; and 4, solving the expansion observer to realize accurate estimation of the relative position speed of the two satellites under the condition that the maneuvering acceleration of the target aircraft is unknown. On the premise that measurement information of tracking and pointing equipment does not need to be added, accurate estimation of the position speed of the maneuvering target is a