The use of spacecraft opto-electronic devices for preliminary orbit determination of near-earth objects

We consider the problem of predetermining the orbit of a space object (eg space debris) using the equipment installed on board the spacecraft in Earth orbit. The necessary initial data can be obtained from devices in the system of navigation and orientation of most of todays spacecraft - the receiver global positioning system (GLONASS, GPS) and the star sensor. A model of the system is developed and used to obtain estimates of the achievable accuracy prior determination of the orbital parameters of the object in achievable accuracy of source data.