| 摘要 |
2063823 9115827 PCTABS00007 A pitch guidance system for an aircraft utilizes inertially derived pitch information to provide the pilot with information defining the optimum pitch angle for maximum climb during a wind shear condition. The system utilizes a pitch reference modulator (22) that receives a stall warning discrete from a stall warning system to reduce the commanded pitch angle upon the occurrence of a stall warning to reduce the possibility of stalling the aircraft during degraded performance conditions such as tail winds and engine-out conditions. The system utilizes inertially derived pitch information rather than air mass derived angle of attack information to avoid transients in the angle of attack vane signal, and the commanded pitch angle is biased as a function of altitude (70) and vertical speed (58) to optimize the pitch angle for different altitudes and descent rates.
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