This thesis examines the control deficiencies in a Bank-to-Turne (BTT) cruise missile due to specific impairments at its control surfaces, during the intermediate phase of its mission. For the study of flight control configuration, a linearized mathematical model is developed which simulates the dynamic response of the missile circular airframe. In the development, a classical design and analysis is performed using both longitudinal and lateral channels for the circular airframe. For each channel the control surfaces are split into independence components and the corresponding continuous open loop uncoupled autopilots are analyzed in terms of their transient response. Specific kinds of impairments are then examined and analyzed and,investigated and the robustness of the complete system is analyzed. Keywords: Autopilot; Yaw; Pitch(Motion), Coupled; Split up; Reconfiguration.
Investigation of Bank-to-Turn Missiles
1986
221 pages
Report
No indication
English
Missile Trajectories & Reentry Dynamics , Missile Tracking Systems , Control surfaces , Banking , Flight maneuvers , Pitch(Motion) , Roll , Yaw , Malfunctions , Airframes , Automatic pilots , Circular , Control , Control systems , Cruise missiles , Deficiencies , Dynamic response , Flight control systems , Guided missiles , Linearity , Mathematical models , Response , Transients , Turning flight , Bank to turn missiles , Impairment
Bank-to-Turn Missiles and Autopilot Design
NTIS | 1990
|Design of Autopilots for Bank-To-Turn Missiles
NTIS | 1989
|'Bank-to-turn steering' for highly maneuverable missiles
AIAA | 1973
|Adaptive sliding mode control for bank-to-turn missiles
Tema Archive | 2009
|Flight Control Design Issues in Bank-to-Turn Missiles
NTIS | 1990
|