A system and a method for improving a stall margin of an aircraft during a climb phase of flight are disclosed. In one embodiment, the method comprises using data indicative of a phase of flight of the aircraft and data indicative of an angle-of-attack, and automatically commanding a deployment of leading edge slats movably attached to wings of the aircraft when the following conditions are true: the aircraft is in a climb phase of flight; and the angle-of-attack equals or exceeds a predefined deployment angle-of-attack threshold value.

A system for in-flight stabilization including a plurality if flight components mechanically coupled to an aircraft. The system further comprises a sensor mechanically coupled to the aircraft, wherein the sensor is configured to detect a failure datum of the flight component. The system comprises a vehicle controller communicatively connected to the sensor and is configured to receive the failure datum of a flight component of the aircraft from the sensor, generate a mitigating response to be performed by at least a flight component of the plurality of flight components, and initiate the at least a flight component of the plurality of flight components. Initiating the flight component of the plurality of flight components further includes performing the mitigating response.

A system for in-flight stabilization including a plurality if flight components mechanically coupled to an aircraft. The system further comprises a sensor mechanically coupled to the aircraft, wherein the sensor is configured to detect a failure datum of the flight component. The system comprises a vehicle controller communicatively connected to the sensor and is configured to receive the failure datum of a flight component of the aircraft from the sensor, generate a mitigating response to be performed by at least a flight component of the plurality of flight components, and initiate the at least a flight component of the plurality of flight components. Initiating the flight component of the plurality of flight components further includes performing the mitigating response.

Provided is a vibration control system for a compound helicopter with a rotor and a fixed wing. The fixed wing includes a movable flap that is mounted on a rear edge of the fixed wing. The vibration control system periodically moves the movable flap so as to periodically change lift of the fixed wing such that vibration aerodynamically generated by the fixed wing is in anti-phase with vibration caused by rotation of the rotor.

Disclosed are methods, systems, and non-transitory computer-readable medium for supersonic flight entry/exit management. For instance, the method may include determining whether a transition between supersonic and subsonic flight is approaching; and in response to determining the transition between subsonic and supersonic flight is approaching, performing a supersonic flight entry/exit process. The supersonic flight entry/exit process may include: obtaining center of gravity (CG) information for the vehicle, drag information for the vehicle, and a planned trajectory of the vehicle (trajectory data); performing an analysis of the trajectory data to determine whether the planned trajectory is safe and consistent; based on a result of the analysis, adjusting the planned trajectory or confirming the planned trajectory of the vehicle; and based on the adjusted planned trajectory or the confirmed planned trajectory of the vehicle, generating actuator instructions to execute the adjusted planned trajectory or the confirmed planned trajectory.

Disclosed are methods, systems, and non-transitory computer-readable medium for supersonic flight entry/exit management. For instance, the method may include determining whether a transition between supersonic and subsonic flight is approaching; and in response to determining the transition between subsonic and supersonic flight is approaching, performing a supersonic flight entry/exit process. The supersonic flight entry/exit process may include: obtaining center of gravity (CG) information for the vehicle, drag information for the vehicle, and a planned trajectory of the vehicle (trajectory data); performing an analysis of the trajectory data to determine whether the planned trajectory is safe and consistent; based on a result of the analysis, adjusting the planned trajectory or confirming the planned trajectory of the vehicle; and based on the adjusted planned trajectory or the confirmed planned trajectory of the vehicle, generating actuator instructions to execute the adjusted planned trajectory or the confirmed planned trajectory.

A method including propelling a vehicle disposed in a medium. The vehicle includes a body, a propulsion mechanism connected to the body, and a direction control system. The vehicle is subject to advection caused by movement of the medium. The method also includes commanding the vehicle to perform a navigation course comprising a closed course-over-ground. The method also includes periodically adjusting navigation of the vehicle along the closed course-over-ground such that a course-through-the-medium turn-rate is varied in a manner that causes a course-over-ground turn-rate of the vehicle to be held constant, thereby minimizing the impact of medium advection on vehicle speed over ground.

Systems and methods according to embodiments of the present technology vary engine throttle and flight control surfaces (such as high-lift devices, which can include flaps and/or slats) during takeoff, climb, approach, and/or landing of a supersonic aircraft to reduce noise. A representative computing device automatically controls thrust output of the propulsion system according to a schedule of thrust output, such that the thrust output remains below levels at which the jet exhaust becomes supersonic, and such that noise is reduced to comply with noise regulations or other limitations. The computing device also automatically controls the position and configuration of flight control surfaces to compensate for the reduced thrust and to maintain an appropriate climb and/or descent rate.

Systems and methods according to embodiments of the present technology vary engine throttle and flight control surfaces (such as high-lift devices, which can include flaps and/or slats) during takeoff, climb, approach, and/or landing of a supersonic aircraft to reduce noise. A representative computing device automatically controls thrust output of the propulsion system according to a schedule of thrust output, such that the thrust output remains below levels at which the jet exhaust becomes supersonic, and such that noise is reduced to comply with noise regulations or other limitations. The computing device also automatically controls the position and configuration of flight control surfaces to compensate for the reduced thrust and to maintain an appropriate climb and/or descent rate.

A system for in-flight stabilization including a plurality of flight components mechanically coupled to an aircraft, wherein the plurality of flight components includes a first flight component and a second flight component opposing the first flight component. The system further comprises a sensor mechanically coupled to the aircraft, wherein the sensor is configured to detect a failure event of a first flight component. The system comprises a vehicle controller communicatively connected to the sensor and is configured to receive the failure datum of the first flight component from the sensor, initiate an automatic response as a function of the failure datum. Initiating the automatic response further includes determining an autorotation inducement action for the second flight component to perform and commanding the second flight component to perform the autorotation inducement action.