Abstract: An aircraft includes a processor, an airframe, a pitch attitude flight control surface coupled with the airframe, a nose wheel coupled with the airframe, main wheels coupled with the airframe, and a brake system coupled with the main wheels. The processor is programmed to determine that the aircraft has entered a braking segment of a landing phase of a flight of the aircraft while the aircraft is on a ground surface and to command the pitch attitude flight control surface with a nose up command during the braking segment in response to determining that the aircraft has entered the braking segment. The nose up command causes the pitch attitude flight control surface to generate a downforce that increases traction between the main wheels and the ground surface due to a weight shift from the nose wheel to the main wheels and directly due to the downforce on the main wheels.

Abstract: An aircraft includes a processor, an airframe, a pitch attitude flight control surface coupled with the airframe, a nose wheel coupled with the airframe, main wheels coupled with the airframe, and a brake system coupled with the main wheels. The processor is programmed to determine that the aircraft has entered a braking segment of a landing phase of a flight of the aircraft while the aircraft is on a ground surface and to command the pitch attitude flight control surface with a nose up command during the braking segment in response to determining that the aircraft has entered the braking segment. The nose up command causes the pitch attitude flight control surface to generate a downforce that increases traction between the main wheels and the ground surface due to a weight shift from the nose wheel to the main wheels and directly due to the downforce on the main wheels.

Abstract: Avionics systems, controllers, and aircraft are provided. An avionics system includes a display unit and a controller, and an aircraft includes the avionics system. The display unit is configured to present an image. The controller is communicatively coupled with the display unit and is configured to control the display unit to present the image in a takeoff mode and in a flight mode of the controller. The controller is further configured to receive signals indicating an aircraft attitude, a target attitude, and an aircraft flight path, to generate a marker in the image in the takeoff mode based on an attitude difference between the aircraft attitude and the target attitude, to generate the marker in the image in the flight mode based on the aircraft flight path, and to generate a signal that causes the display unit to present the image.

Abstract: Avionics systems, controllers, and aircraft are provided. An avionics system includes a display unit and a controller, and an aircraft includes the avionics system. The display unit is configured to present an image. The controller is communicatively coupled with the display unit and is configured to control the display unit to present the image in a takeoff mode and in a flight mode of the controller. The controller is further configured to receive signals indicating an aircraft attitude, a target attitude, and an aircraft flight path, to generate a marker in the image in the takeoff mode based on an attitude difference between the aircraft attitude and the target attitude, to generate the marker in the image in the flight mode based on the aircraft flight path, and to generate a signal that causes the display unit to present the image.

Abstract: The disclosed embodiments relate to a cockpit augmented vision unit (CAVU) is provided that includes a video signal feed, a housing configured to house a display, and an attachment mechanism coupled to the housing that is configured to secure the housing and the display to an oxygen mask. The video signal feed can be communicatively coupled to at least one source of a video signal, and the display can be coupled to the video signal feed. The display is configured to display the video signal.

Abstract: Flight guidance panels and vehicle guidance panels are provided. A flight guidance panel for an aircraft includes a hardware knob, a display proximate the hardware knob, and a controller. The controller is configured for: altering an automation state of the aircraft; receiving a target of a flight parameter for the aircraft to achieve when the automation state is active; and generating a functional panel associated with the flight parameter and the hardware knob based on a configuration of the flight guidance panel.

Abstract: Aircraft, control-by-wire systems, and controllers are provided. The aircraft includes a flight control surface and a control-by-wire system. The control-by-wire system includes an input device and a controller. The input device is configured to control the flight control surface. The controller is communicatively coupled with the input device and configured to automatically offset a neutral force position of the input device based on a deviation of the aircraft from a reference condition while the aircraft is operated in a manual flight mode.

Abstract: Aircraft, control-by-wire systems, and controllers are provided. The aircraft includes a flight control surface and a control-by-wire system. The control-by-wire system includes an input device and a controller. The input device is configured to control the flight control surface. The controller is communicatively coupled with the input device and configured to automatically offset a neutral force position of the input device based on a deviation of the aircraft from a reference condition while the aircraft is operated in a manual flight mode.