Flight vehicle attitude control system design method and device

A flight vehicle attitude control system design method performed by a flight vehicle attitude control system design device including at least one processor, an input device, and a display unit, the flight vehicle attitude control system design method comprising:

• receiving, by the input device of the flight vehicle attitude control system design device, an nth system natural frequency and an nth system damping coefficient representing dynamic characteristics of a flight vehicle with respect to an nth time;
• using the nth system natural frequency and the nth system damping coefficient received by the input device, calculating, by a gain calculator of the flight vehicle attitude control system design device, an nth proportional gain and an nth derivative gain;
• using the calculated nth proportional gain and the calculated nth derivative gain, calculating, by a margin calculator, an nt gain margin and an nth phase margin;
• generating, by a grid generator, an nth gain-phase margin grid from a relationship between the calculated nth proportional gain and the calculated nth derivative gain and a relationship between the calculated nth gain margin and the calculated nth phase margin;
• and
• outputting, by the processor, for display on a display unit, the generated nth gain-phase margin grid on a control gain design region having a gain margin as one of a horizontal coordinate axis and a vertical coordinate axis and a phase margin as the other one of the horizontal coordinate axis and the vertical coordinate axis.