APPROACH TO SOLVING THE TERMINAL CONTROL PROBLEM ON CONDITION OF IMPRECISE MEASURING OF STATE VECTOR
Науковий журнал «Радіоелектроніка, інформатика, управління»
Переглянути архів Інформація| Поле | Співвідношення | |
| ##plugins.schemas.marc.fields.042.name## |
dc |
|
| ##plugins.schemas.marc.fields.245.name## |
APPROACH TO SOLVING THE TERMINAL CONTROL PROBLEM ON CONDITION OF IMPRECISE MEASURING OF STATE VECTOR |
|
| ##plugins.schemas.marc.fields.720.name## |
Khatsko, N. E.; Narional Technical University «Kharkiv Polytechnic Institute», Kharkiv, Ukraine |
|
| ##plugins.schemas.marc.fields.653.name## |
control system, strapdown inertial navigation system, the measurement the error of the state vector measurement, dynamical disturbance, the accuracy of the terminal management. |
|
| ##plugins.schemas.marc.fields.520.name## |
The article considers the problem of terminal control of an aircraft using the data from the strapdown inertial navigation system, specifically the case when the aircraft is moved to a specific spatial position having the required vector of terminal velocity. Builded program model for not altered motion of aircraft. Developed software for aircraft control, based on current state-vector taken from inertial navigation system. Method of analysis of aircraft positioning accuracy in the final location of a closed-loop control system that is based on the information taken from inertial sensors that have a deliberately known level of errors. Deduced formulas for estimation of aircraft final position taking into account accelerometer errors. On the base of a simplified model the analysis of the accuracy of the state vector bringing to a given endpoint is performed, depending on the input information level of the perturbation and inaccuracy of input information. Conducted experiments demonstrate dependency of software accuracy on accuracy of terminal control problem solution. The following recommendations were obtained after performing analysis of accuracy of a close-loop system functioning:<br />– With time, the impact of errors from inertial navigation system decreases; – To reduce impact of dynamic altered motion onto the finale state, we should decrease coefficient of gain transfer function;<br />– When choosing a variable parameter in the law of Synthesis method of leading point persecution, you should be guided with the following<br />considerations: if the information-measuring system provides the coordinates and velocity of the object with high accuracy, the selected<br />parameter of the forecast should be minimal. When using low-accuracy sensors, the value of forecast parameter should be increased. |
|
| ##plugins.schemas.marc.fields.260.name## |
Zaporizhzhya National Technical University 2016-04-15 00:00:00 |
|
| ##plugins.schemas.marc.fields.856.name## |
application/pdf http://ric.zntu.edu.ua/article/view/66671 |
|
| ##plugins.schemas.marc.fields.786.name## |
Radio Electronics, Computer Science, Control; No 1 (2016): Radio Electronics, Computer Science, Control |
|
| ##plugins.schemas.marc.fields.546.name## |
ru |
|
| ##plugins.schemas.marc.fields.540.name## |
Copyright (c) 2016 N. E. Khatsko |
|