Abstract: A method, apparatus, and system for adjusting an operational flight envelope for an aircraft. An airspeed of the aircraft is received from a sensor system in the aircraft. An amount of change in the airspeed of the aircraft is determined. A current ceiling of the operational flight envelope for the aircraft is adjusted based on the amount of change in the airspeed of the aircraft.

Abstract: Integrated slat chine apparatus and methods are described. An example method comprises moving a slat relative to an airfoil between a stowed position and a deployed position. The slat is coupled to the airfoil. The slat is located adjacent a lateral surface of a chine. The chine is coupled to the airfoil. The slat is to expose the lateral surface of the chine when the slat is in the deployed position and to cover the lateral surface of the chine when the slat is in the stowed position.

Abstract: A method, apparatus, and system for adjusting an operational flight envelope for an aircraft. An airspeed of the aircraft is received from a sensor system in the aircraft. An amount of change in the airspeed of the aircraft is determined. A current ceiling of the operational flight envelope for the aircraft is adjusted based on the amount of change in the airspeed of the aircraft.

Abstract: Integrated slat chine apparatus and methods are described. An example method comprises moving a slat relative to an airfoil between a stowed position and a deployed position. The slat is coupled to the airfoil. The slat is located adjacent a lateral surface of a chine. The chine is coupled to the airfoil. The slat is to expose the lateral surface of the chine when the slat is in the deployed position and to cover the lateral surface of the chine when the slat is in the stowed position.

Abstract: Integrated slat chine apparatus and methods are described. An example apparatus includes a chine and a slat. The chine is coupled to an airfoil. The chine includes a lateral surface. The slat is located adjacent the lateral surface of the chine and coupled to the airfoil. The slat is movable relative to the airfoil between a stowed position and a deployed position. The slat is to expose the lateral surface of the chine when the slat is in the deployed position and to cover the lateral surface of the chine when the slat is in the stowed position.

Abstract: Integrated slat chine apparatus and methods are described. An example apparatus includes a chine and a slat. The chine is coupled to an airfoil. The chine includes a lateral surface. The slat is located adjacent the lateral surface of the chine and coupled to the airfoil. The slat is movable relative to the airfoil between a stowed position and a deployed position. The slat is to expose the lateral surface of the chine when the slat is in the deployed position and to cover the lateral surface of the chine when the slat is in the stowed position.

Abstract: An aircraft stall protection system and method include calculating a first angle of attack and a second angle of attack based on aircraft configuration and environmental conditions, the first angle of attack being greater than the second angle of attack. The system and method limit the actual aircraft angle of attack to the first angle of attack for a predetermined period of time and thereafter the system and method limit the actual aircraft angle of attack to the second angle of attack. The system and method allow the aircraft operator or pilot to extract maximum performance from the aircraft for any given set of flight conditions, without the risk of stalling or remaining in a high drag state for a prolonged period of time. This system and method are suitable for use in conjunction with a stall warning system.

Abstract: An aircraft stall protection system and method include calculating a first angle of attack and a second angle of attack based on aircraft configuration and environmental conditions, the first angle of attack being greater than the second angle of attack. The system and method limit the actual aircraft angle of attack to the first angle of attack for a predetermined period of time and thereafter the system and method limit the actual aircraft angle of attack to the second angle of attack. The system and method allow the aircraft operator or pilot to extract maximum performance from the aircraft for any given set of flight conditions, without the risk of stalling or remaining in a high drag state for a prolonged period of time. This system and method are suitable for use in conjunction with a stall warning system.