Abstract
The paper touches the general problem of predictive bounded final state control of dynamic systems, which is typical in many applications, especially in aerospace area. Two closely interrelated aspects of this problem are under consideration, namely, maximizing the manoeuvring capabilities of a space vehicle and reducing the computational load when finding the final state control function in repetitive corrections over a trajectory. The suggested control strategy addresses the both aspects. The main idea consists in replacing the hard differential eigenvalue problem to be solved within a limited time in a correction session by the algorithm that solves initial-value problems with average control over the flight time and makes decisions based on a predicted miss. The equality of manoeuvrability margins is provided in the maximal remaining part of trajectory. The computer simulation of the reduced targeting problem of a low-lift re-entry vehicle shows feasibility and effectiveness of the proposed strategy.