Rockwell Collins, Inc.

John P Perich

Thomas M Scanlon

Juan M Segal

Samuel E Ferdon

Cornelis Van Der Linden

John W Roltgen

Andrew R Markofski

Jason K Dahlstrom

Brandon J Burnett

Ajay Karthik Ganesan

Dale E McPherson

Charles Steffen

Autonomous systems increase the robustness and safety of current aircraft and to support simplified vehicle, reduced crew, and single pilot operations. The autonomous systems aid air crews in their handling of non-normal, high workload, aircraft upset scenarios. The upset scenarios include the recovery from attitudes outside of the normal operating envelope that even the most robust automatic flight control systems currently in service today do not support.

Multi-axis upset recovery system

A flight display is described. The flight display includes a display screen, a physical network interface, and multiple processors. The flight display interfaces with the flight deck by way of the physical network interface. The display screen displays images representative of avionics data in response to signals generated by one or more of the processors. The processors also generate command signals causing an actuator of the aircraft to control a flight control surface or a throttle. In this regard, the one or more of the processors perform various automatic flight control system (AFCS) functions. A system is further described including multiple of the flight displays. By hosting the AFCS functions across processors of the multiple flight displays, a level of command integrity may be reached. Furthermore, backups flight displays are available to be reconfigured to perform the AFCS functions.

Embedded display automatic flight controls distributed architecture

A system for an airborne platform includes a sensing device, an automatic throttling system, and a processing circuit. The sensing device is configured to measure a current airspeed of an aircraft. The processing circuit is configured to receive a control input comprising a current airspeed value, an airspeed reference value, a maximum adder threshold, and a minimum adder threshold. The processing circuit is further configured to calculate an airspeed error value based on the control input. The processing circuit is further configured to determine a programmed error value based on the calculated airspeed error value. The processing circuit is further configured to calculate an adder value by applying an integration function to the determined programmed error value and to determine a dynamic airspeed reference value based on the calculated adder value. The processing circuit is further configured to transmit the dynamic airspeed reference value to the automatic throttling system.

Systems and methods of airspeed control with dynamic asymmetric airspeed reference

A flight controller includes an altitude capture controller, an altitude profile predictor, and an alert generator. The altitude capture controller receives a first current altitude, a target altitude, and at least one energy state parameter; generates a flight control command, a first expected altitude, and a first predicted altitude. The altitude profile predictor generates a second predicted altitude. The alert generator calculates an expected altitude deviation by comparing a second current altitude of the platform to the first expected altitude; calculates a predicted altitude deviation by comparing the first predicted altitude to the second predicted altitude; and outputs an alert responsive to at least one of (i) an expected altitude threshold function indicating the expected altitude deviation exceeds an expected altitude deviation threshold or (ii) a predicted altitude threshold function indicating the predicted altitude deviation exceeds a predicted altitude deviation threshold.

Systems and methods for altitude capture performance monitor

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John P Perich