| 摘要 |
An inertial control system for providing vertical velocity and vertical position information for an aircraft is described. Vertical velocity is determined as a function of vertical acceleration of the aircraft and a correction signal. The vertical acceleration correction signal is derived from a function of the barometric altitude and an altitude error signal. The altitude error signal is derived from the difference between the inertially determined vertical position and the barometric altitude. The vertical acceleration correction signal is derived from the altitude error signal and its integral multiplied by variable values which are a function of the time differentiation of the barometric altitude. Vertical position of the aircraft is determined as a function of the derived vertical velocity corrected by a vertical velocity correction signal. |
