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One of the main objectives of the mission for the study of small bodies in the solar system is the design of a ballistic trajectory flight of the spacecraft to the small bodies. The challenge is to construct the trajectory of spacecraft motion, ensuring the implementation of the objectives specific space mission.

These trajectories should be technically realizable objects of modern production space industry.

Present work is devoted the design of the spacecraft flight trajectory to small asteroids.

The software package Matlab and storage and processing of navigation data SPICE was studied.

Program calculating the pulse value has been created on basis of solving the problem of Lambert and subsequent refinement of that decision.

Optimal flight was found from Earth to asteroids QN266 and AP10.

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