Vol 56, No 5 (2017)

This paper is devoted to synthesizing the asymptotically stable arbitrary programmed motion for a rigid body with a cavity entirely filled with viscous fluid. To solve this problem, we synthesize an active program control applied to the system and a stabilizing feedback control. The control is synthesized as an exact analytical solution in the class of continuous functions. The problem is solved based on Lyapunov’s second method for stability analysis by using Lyapunov functions with sign-constant derivatives.

This paper addresses the problem of the robust stabilization of a nonlinear multivariable time-invariant plant on a semi-infinite discrete time interval under arbitrary nonmeasurable bounded additive disturbances. A guaranteed value of the quality criterion is given by the functional representing the weighted sum of the limiting norms of the control vectors and output variables. To generate control actions, a controller containing a linear generalized inverse model and discrete-time integrators is introduced into the feedback loop. Sufficient conditions for the robust stability of the control system, as well as the conditions for the ultimate boundedness of all its signals (dissipativity conditions), are formulated. A corresponding simulation example is presented.

The problem of optimizing complex systems under incomplete information when there are several criteria for the system’s efficiency (optimization goals) is considered. The properties of different types of the convolution of these criteria, as well as the method of successive concessions for formalizing the concept of the solution of multicriteria (MC) problems with uncertainty, are analyzed. We show that there is a difference between the solutions obtained with different convolutions and method modifications. The advantages of the inverse logical convolution are demonstrated.

Modified Lagrangian bounds are proposed for the generalized assignment problem. The approach is based on a double decomposable structure of the formulation. A family of greedy heuristics is considered to get Lagrangian based feasible solutions. Numerical results for problem instances with number of agents close to number of tasks are provided.

A method is proposed for determining motion parameters of an aerial object using a passive optoelectronic system when an aircraft (AC) performs a special maneuver. The method is based on measuring the azimuth and elevation of the aerial object, as well as the AC’s own coordinates at three path points: two measurements on the straight-and-level segment and one measurement after the maneuver. The method does not violate the tactical situation and makes it possible to maintain optical contact with the object during the maneuver. The method is modeled. The accuracy characteristics are estimated. The validation procedure for determining an aerial object’s motion parameters is proposed.

Algorithms to make an aircraft aware of overrunning a runway on landing and alert it are proposed. These algorithms use a predictive model based on the minimization of the generalized work functional, a detailed description of the affecting factors, and the control scenario in the final phase of the approach to landing and on landing refined in real time.

An algorithm for the rapid construction of the orbital coordinate system (OCS) used in the control system of the manned and cargo spacecraft Soyuz MS and Progress MS is considered. The algorithm is used to speed up the current determination of the state vector value using the satellite navigation equipment immediately after the spacecraft is placed into the Earth’s artificial satellite orbit and the launch vehicle is separated. The proposed algorithm is based on an a priori knowledge of the launch vehicle’s attitude parameters at the time of separation and on the angular velocity (AV) measurements available on board after the start of the strapdown inertial navigation system (SINS). The efficiency of the rapid orbital attitude control algorithm is confirmed by the results of the mathematical modeling and flight development tests.