synthesis of trajectory control of aircraft, method of pathing control, conditional geographical coordinate system, inverse problem dynamics method, restriction of control function

Аuthors

Alesov M. B.

Company "Ramenskoye Design Company", 2, Guriev str., Ramenskoye, Moscow Region, 140103, Russia

e-mail: mbalesov@spb.rpkb.ru

Abstract

In the paper the problem of synthesis aircraft pathing movement control with direct guidance to the target navigation point (TNP) on the sphere is considered. To describe the movement of the aircraft, two models are used: in the original geographical and conditional (polar one relative to the TNP) coordinate systems, while formulas for recalculating the state variables of the control object in different models are presented. The control synthesis is carried out by the inverse dynamics problem method, in which a reference description of the difference between the current angular position of the aircraft and the required direction is selected. To account for the limitation of the control value (roll angle), the nonlinear "saturation" link and its smooth approximations are used. The paper provides the final formulas for calculating the control function for two standard aerial operations: the aircraft guidance to the target point by heading angle (directional guidance) and by path angle (course guidance). In addition, the issues of converting the primary flight and navigation data provided by the aircraft's onboard equipment into output parameters for control are considered. Modelling the guidance of the aircraft on the TNP using numerical  integration of the equations of aircraft motion, taking into account the wind action and synthesized control was performed. Graphical dependences of the parameters of the direction, control function, and trajectories of the aircraft are presented to illustrate the availability of the proposed algorithms and identity of the two problem statements. Based on the Picard’s method the solution of the motion equation, formulas for evaluating the maneuverability are obtained and recommendations for selecting control parameters are given. It is noted the problem statement in conditional coordinates has "natural" geometric interpretation when selecting control parameters and evaluating the trajectory structure. The proposed algorithms can be applied as part of on-board flight navigation support systems and trajectory control of aircraft at significant aircraft speeds and long distances to TNP.

Keywords:

: synthesis of trajectory control of aircraft, method of pathing control, conditional geographical coordinate system, inverse problem dynamics method, restriction of control function

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