Abstract: A system and method for estimating a plurality of airspeed parameters of an aircraft is disclosed. The system comprises one or more processors and a memory coupled to the processor. The memory storing data comprises a database and program code that, when executed by the one or more processors, causes the system to receive a plurality of operating parameters that each represent an operating condition of the aircraft. The system is further caused to determine a stability-axis drag coefficient based on the plurality of operating parameters. The stability-axis drag coefficient quantifies a stability-axis drag of the aircraft created during high speed conditions. The system is caused to determine a body-axis lift coefficient based on the plurality of operating parameters, which corresponds to a lift of the aircraft created along a vertical body-axis. The system is also caused to determine a dynamic pressure, which is used to estimate the airspeed parameters.

Abstract: A system and method for estimating a plurality of airspeed parameters of an aircraft is disclosed. The system comprises one or more processors and a memory coupled to the processor. The memory storing data comprises a database and program code that, when executed by the one or more processors, causes the system to receive a plurality of operating parameters that each represent an operating condition of the aircraft. The system is further caused to determine a stability-axis drag coefficient based on the plurality of operating parameters. The stability-axis drag coefficient quantifies a stability-axis drag of the aircraft created during high speed conditions. The system is caused to determine a body-axis lift coefficient based on the plurality of operating parameters, which corresponds to a lift of the aircraft created along a vertical body-axis. The system is also caused to determine a dynamic pressure, which is used to estimate the airspeed parameters.

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.