Control problems in contingency during flight of a space vehicle with low thrust engine

An approximate method of online analysis of contingency during the flight of a space vehicle with low thrust engine and nuclear power unit to asteroids is proposed. The properties of dependence of the vehicle mass near the target on the flight characteristics and parameters of the space vehicle are used. Examples of the choice of a new variant of the expedition to several asteroids of the Main belt in the case of a contingent change in the power of the energy unit are given.