Abstract: An example method for in-flight determination of a gross weight of an aircraft includes causing an aircraft to perform a first flight operation defined by a first airspeed that is substantially constant and a descent rate that is substantially constant, determining the first airspeed and a first thrust that caused the aircraft to perform the first flight operation, the first thrust being substantially constant during the first flight operation, causing the aircraft to perform a second flight operation defined by a second airspeed that is substantially constant and a descent rate that is substantially constant, determining the second airspeed and a second thrust that caused the aircraft to perform the second flight operation, the second thrust being substantially constant during the second flight operation, and using the first thrust, the second thrust, the first airspeed, and the second airspeed to determine the gross weight of the aircraft.

Abstract: An example method for in-flight determination of a gross weight of an aircraft includes causing an aircraft to perform a first flight operation defined by a first airspeed that is substantially constant and a descent rate that is substantially constant, determining the first airspeed and a first thrust that caused the aircraft to perform the first flight operation, the first thrust being substantially constant during the first flight operation, causing the aircraft to perform a second flight operation defined by a second airspeed that is substantially constant and a descent rate that is substantially constant, determining the second airspeed and a second thrust that caused the aircraft to perform the second flight operation, the second thrust being substantially constant during the second flight operation, and using the first thrust, the second thrust, the first airspeed, and the second airspeed to determine the gross weight of the aircraft.

Abstract: A method for improving inflight fuel efficiency of an aircraft includes sensing aircraft fuel weight in the aircraft fuel tanks and reading the fuel weight by a flight management system during aircraft flight; calculating a current center of gravity position from the fuel weight; calculating an aircraft longitudinal trim drag factor from the current center of gravity; and adjusting a fuel burn prediction utilizing the longitudinal trim drag factor. A system for improving aircraft inflight fuel efficiency includes a flight management system programmed to calculate a current center of gravity position from a current aircraft fuel weight, calculate a longitudinal trim drag factor from the current center of gravity, adjust a fuel burn prediction, and display in the flight deck an adjusted fuel burn prediction for each leg of aircraft flight, which is used to adjust aircraft performance automatically by the flight control system or by the pilot.

Abstract: A method includes receiving, at a flight management system of an aircraft, a required time of arrival (RTA) of the aircraft at a first location. The method includes receiving, at the flight management system, an input indicating an RTA index value. The method further includes modifying a speed of the aircraft based on the RTA and the RTA index value. The speed is determined by the flight management system as part of a flight plan of the aircraft.

Abstract: A system using automatic dependent surveillance-broadcast (ADS-B) data and traffic alert and collision avoidance system (TCAS) data for determining navigation solutions for a vehicle is provided. The system has a communal position system (CPS) with a CPS sensor located in the vehicle. The CPS sensor receives ADS-B data and TCAS data from each of one or more proximate vehicles. The system further has a computer system coupled to the CPS. The computer system is configured to perform the steps of: checking the ADS-B data and the TCAS data for data reasonableness; performing data synchronization of the ADS-B data and the TCAS data; and computing a CPS position and a position accuracy based on the ADS-B data and the TCAS data. The navigation solutions include an alternate navigation solution, an independent navigation solution, and a complementary navigation solution.

Abstract: Systems and methods providing improved flight guidance are described. In some implementations, performance data from a plurality of completed flight segments of an aircraft are recorded and used to generate and/or update a regression model between one or more input parameters and one or more output parameters. Flight profile data for a current flight segment of the aircraft is estimated using the regression model and compared to flight profile data predicted based on pre-programmed performance data. The estimated and predicted flight profile data are compared to determine if a difference between the two exceeds a predetermined amount and flight guidance for a current flight segment is generated based on the estimated flight profile data if the difference exceeds the predetermined amount.

Abstract: A system using automatic dependent surveillance-broadcast (ADS-B) data and traffic alert and collision avoidance system (TCAS) data for determining navigation solutions for a vehicle is provided. The system has a communal position system (CPS) with a CPS sensor located in the vehicle. The CPS sensor receives ADS-B data and TCAS data from each of one or more proximate vehicles. The system further has a computer system coupled to the CPS. The computer system is configured to perform the steps of: checking the ADS-B data and the TCAS data for data reasonableness; performing data synchronization of the ADS-B data and the TCAS data; and computing a CPS position and a position accuracy based on the ADS-B data and the TCAS data. The navigation solutions include an alternate navigation solution, an independent navigation solution, and a complementary navigation solution.

Abstract: A method includes receiving, at a flight management system of an aircraft, a required time of arrival (RTA) of the aircraft at a first location. The method includes receiving, at the flight management system, an input indicating an RTA index value. The method further includes modifying a speed of the aircraft based on the RTA and the RTA index value. The speed is determined by the flight management system as part of a flight plan of the aircraft.