METHOD FOR CONTROL BY PITCH AND YAW

A Method for controlling an aircraft (A) by pitch and yaw includes rotation of the A with respect to the longitudinal axis, formation of a control signal proportional to the deflection of the A from the support trajectory, its agreeing to the kinematical parameters of rotation of the A; that for one...

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Bibliographische Detailangaben
Hauptverfasser:	KOSOVENKO YEVHEN VIKTOROVYCH, NEMCHYN OLEKSANDR FEDOROVYCH, KOROBOV VITALII ILLICH, SEMENOV LEONID ANTONOVYCH, DOTSENKO BORYS IVANOVYCH, KUZMIN VIACHESLAV PAVLOVYCH, YAKOVLIEV VITALII VASYLIOVYCH, YAKOVENKO PETRO OLEKSIIOVYCH, KOROSTELIOV OLEH PETROVYCH
Format:	Patent
Sprache:	eng
Schlagworte:	AIMING BLASTING HEATING LIGHTING MECHANICAL ENGINEERING WEAPON SIGHTS WEAPONS
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Beschreibung
Zusammenfassung:	A Method for controlling an aircraft (A) by pitch and yaw includes rotation of the A with respect to the longitudinal axis, formation of a control signal proportional to the deflection of the A from the support trajectory, its agreeing to the kinematical parameters of rotation of the A; that for one uses information on the angular velocity of rotation and the current value of the heel angle, this comes from the sensor of linear transversal overloading; control is processed by means of reversing steer drives in such a way that the control signals proportional to the coordinates of disagreement tend to zero.