Abstract
Summary The necessity of creating an adaptive system for the improvement of piloting characteristics of a transport space aircraft is substantiated. On the base of stability condition, a specific synthesis of laws for correcting coefficients in damping, stability and controllability circuits is carried out. The laws derived assume different versions of practical realization. The technique of choosing the preferable variant, according to the criteria combination, taking into account, parallel with dynamic indices, weight, realiability and so on is discussed.
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