| 摘要 |
A fluidic control system which automatically schedules and controls power developed by an aircraft during landing approach operation. Fluidic signals are generated in relation to sensed aircraft flight parameters, and these signals are combined in a preselected manner which includes integration of one of the signals by a series feedback capacitance fluidic integrator, to produce a single input signal indicative of a desired rate of fuel flow to schedule aircraft power to the desired level. The single input signal is temperature compensated, then discretely selectively modified in relation to ambient conditions by selectively varying the impedance of fluidic resistive networks to alter the gain of a fluidic amplifier driven by the single input signal. An error signal is then generated and amplified to produce a power output signal which drives a fuel control servo actuator in proportion to the error signal when the latter is small, and drives the servo in a digital manner when the error is large.
|
