Abstract: A mission computer (10) stores a nominal route plan which includes information indicative of the precise arrival time at specific navigation positions, e.g., waypoints, and the planned fuel consumption during travel to the specified waypoints. The mission computer (10) provides a time and fuel display system (15) with the route plan information. The time and fuel display system (15) generates a display (200) which indicates the total distance to be traveled during the mission (202), a distance traveled indicator (212) to reflect the progress of the aircraft along the mission, and a time bar (205) and a fuel bar (207) the height of which with respect to the indicator (212) are indicative of the percentage that the current time and fuel values are over or under the planned values for the current waypoint. The distance traveled indicator (212) is labeled with a waypoint designation (215) which is indicative of the designation of the waypoint towards which the aircraft is currently flying.

Abstract: In a dual station sidearm control system, a pilot control station provides pilot control signals in response to pilot activation of a pilot sidearm controller (210) and a co-pilot station provides co-pilot control signals in response to co-pilot activation of a co-pilot sidearm controller (211). The pilot control signals and the co-pilot control signals are combined (220) to provide dual station control signals for controlling aircraft attitude in the yaw, pitch, roll and lift attitude axes. A priority detector function (222) is responsive to pilot control signals in one of the attitude axes for reducing the priority of co-pilot control signals with respect to pilot control signals in the one attitude axis as the magnitude of pilot control signals increases in the one attitude axis.

Abstract: An integrated time/limit exceedance cue system including a plurality of dedicated subsystem sensors, a processing unit, and a graphics generating/processing unit that is operative to generate an event dependent, time varying visual cue indicative of the exceedance of an established normal operating limit of a specific aircraft subsystem and operation thereof in a time critical exceedance condition. The time varying visual cue provides a relative indication of the elapsed time of operation of the specific subsystem in the time critical exceedance condition. The time varying visual cue is a symbolic image in the form of an outline, having a predetermined length, that defines a void region. The void region is proportionately opaqued or "filled in" in correspondence with the elapsed time of operation of the specific subsystem in the time critical exceedance condition.

Abstract: Pilot workload is reduced in a helicopter having a force-type, multi-axis sidearm control stick by providing a displacement-type control stick for collective blade pitch control. Either stick may be used by the pilot. When the force-type stick is employed, a trim system causes the displacement-stick to track a collective position command signal which is provided to the blade actuators. Changeover of control to the displacement-type control stick is accomplished either with a switch, or by moving the collective-type control stick. The signals associated with each control stick are alternately faded in and out to assure a smooth transition when collective control is switched over from one to the other.