초록 ▼

A pitch limit symbol is generated at an aircraft attitude indicator which provides a pilot with display of a stall warning angle of attack margin which is referenced to an airplane symbol on the primary attitude indicator. The position of the pitch limit symbol relative to the aircraft symbol is a f

A pitch limit symbol is generated at an aircraft attitude indicator which provides a pilot with display of a stall warning angle of attack margin which is referenced to an airplane symbol on the primary attitude indicator. The position of the pitch limit symbol relative to the aircraft symbol is a function of the difference in angle of attack between the current angle of attack at the aircraft, and a predetermined angle of attack at which the onset of stall warning occurs. Additional information is provided on the attitude indicator by a flight path angle symbol. The pitch limit symbol together with the flight path angle symbol provides the pilot with information to achieve a positive rate of climb during a pitch up maneuver while adjusting the pitch attitude of the aircraft to avoid a stall situation. The position of the pitch limit symbol may be compensated by various means to decrease the distance between the aircraft symbol and the pitch limit symbol. This is a continuation of application Ser. No. 119,694 filed Nov. 12, 1987 now abandoned, which is a continuation of application Ser. No. 800,057 filed Nov. 20, 1985 now abandoned.

대표청구항 ▼

In an aircraft information display apparatus including an attitude display indicator having (i) a first aircraft symbol and a second horizon symbol, which are positioned at relative locations to each other to indicate an aircraft flight attitude, and (ii) a third symbol, apparatus for displaying an

In an aircraft information display apparatus including an attitude display indicator having (i) a first aircraft symbol and a second horizon symbol, which are positioned at relative locations to each other to indicate an aircraft flight attitude, and (ii) a third symbol, apparatus for displaying an aircraft stall warning margin comprising: a. sensor means for measuring a current angle of attack of the aircraft, and for providing a first output thereof; b. computing means for storing an angle of attack at which a stall warning of the aircraft occurs, and for calculating, in response to the first output, an angle of attack difference between the current angle of attack and the stall warning angle of attack; c. control means for positioning the third symbol above the first aircraft symbol so that a displayed distance between the third symbol and the first aircraft symbol, which is representative of the stall warning margin, is a function of the angle of attack difference; and d. the computing means operating in a manner to reduce the angle of attack difference by a selected amount when an airspeed rate of the aircraft is negative and a pitch attitude of the aircraft exceeds a predetermined pitch attitude, so that the displayed difference between the third symbol and the first airplane symbol is reduced by an amount which represents a safety margin.