Аннотация:During deep space missions, dynamical operations (orbit and attitude correction manoeuvres, landing in target areas, etc.) planning and realization require spacecraft position fast determination. Due to the objective difficulties of interplanetary communication, it is interesting to solve this problem using data from onboard sensors (in particular, optical ones). What is more, most ’’transportable" of these devices give out ’’angular" (or quaternion) representation of reper objects positions instead of rectangular coordinates or at least distances. Thus, one faces the problem of determination of spacecraft state vector (in a rectangular coordinate system) from data in ’’angular" coordinates in measurement devices coordinate systems. We suggest to determine the spacecraft state vector at the required time as a solution to the problem of minimizing the quadratic cost that determines the difference between the ’’simulated" measurements (i.e., those that would have been made on the ’’simulated" trajectory generated by a current state vector approximation) from the real ones (i.e., those that were obtained from on-board sensors). To find a solution, we use a software implementation of the Levenberg-Marquardt method and a prototype of a software package that allows one to configure spacecraft sensors set and the measurement series parameters.