| 摘要 |
PURPOSE: An automatic recovery control system for aircraft stall is provided to automatically create stall recovery commands using state information of an aircraft, thereby reducing the burden of a pilot and achieving stable recovery. CONSTITUTION: An automatic recovery control system for aircraft stall comprises a pitch rate input retardation filter(20), a gain amplifier(30), a stall position selector(40), a stall recovery command limiter(50), and a transient response preventing device(60). The pitch rate input retardation filter receives pitch rates and delays a signal in order to compensate the stall recovery property caused by phase delay. The stall position selector receives the stall recovery commands from the gain amplifier and determines the position of an aircraft in order to automatically select an upright or inverted stall. The stall recovery command limiter receives the signals from the stall position selector and limits the maximum and minimum values of the stall recovery commands. The transient response preventing device switches the output signals of the stall recovery command limiter to horizontal tail plane command signals based on the comparison between the absolute value and the set value of the pitch rate input to the retardation filter.
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