Rockwell Collins, Inc.

Thomas M Scanlon

John P Perich

Samuel E Ferdon

Juan M Segal

Douglas A Bell

John W Roltgen

Bradley R Mickelson

Andrew R Markofski

Cornelis Van Der Linden

Stephen W Howard

Jason K Dahlstrom

Ajay Karthik Ganesan

Charles Steffen

Stephen M Kleckner

Brandon J Burnett

Jason M Vanderhorn

Dale E McPherson

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

Present novel and non-trivial systems and methods for validating single-channel tactical flight data in a multi-channel architecture are disclosed. Three single-channel monitors are disclosed along with a fourth, external monitor that is accessible to the multiple channels. A system could be comprised of a navigation data source, two or more communications channels, and an external display unit ('DU'), where each channel may be comprised of a flight management system ('FMS'), a DU, and a flight director (&#x201c;FD&#x201d;) system. In addition to the FMS performing two standard functions of calculating a lateral deviation (&#x201c;LDEV&#x201d;) and a roll command (&#x201c;Roll Cmd&#x201d;), a second LDEV/Roll Command calculator and a Roll Command Calculator are employed in DU and FD of same channel, respectively, to determine data validity. In addition, the FD and the symbologies of LDEV and Roll Cmd generated by the DU are also employed in the determination of data validity.

Tactical flight data validating systems and methods for a multi-channel topological architecture

Growing community of inventors

Cedar Rapids, IA, United States of America

Thomas M Scanlon