Rotation,climbout,and go-around control system

Abstract

Abstract We call out system an RGA system which is an abbreviation for ''''ROTATION-GO-AROUND''''. Data concerning pitch, angle of attack, longitudinal acceleration, elevator position, and flap position are used by the RGA computer to compute the take-off and goaround vertical steering signal presented to a pitch steering display to show the pilot the necessary corrective measures to approach and/or hold a computed pitch attitude. Selection of RGA mode: (a) AC-CL, (accelerated climb); (b) MAX (maximum climb angle), and (c) EWO (Emergency War Order Operation) must be manually programmed by the pilot for a take-off. No manual programming is required for the go-around. The RGA Interface Unit processes the analog flap signals into discrete voltage steps, averages and cross-monitors the left and right angle of attack signals, and provides RGA vertical steering cross-monitoring in a dual system (for pilot and co-pilot). The RGA Control Unit provides the means by which the pilot selects the desired takeoff climb operation and the approach speed deviation display. The control unit uses the flight director RGA mode voltage, a weighton-wheels discrete signal, and the momentary voltage from the control wheel go-around switch to generate the necessary RGA system logic. Angle of attack and flap position data are combined for presentation of normalized angle of attack by the angle-ofattack indicator. The angle-of-attack indicator also provides an auxiliary approach-angle-of-attack deviation output for presentation on the FAST-SLOW display. When selected, this signal indicates to the pilot what corrective measures are required to hold the optimum approach angle-of-attack, and hence, the appropriate approach speed regardless of aircraft weight or configuration.

Inventors

• 👤 Edward S Gwathmey
• 👤 John M Embree

Bibliographic Details