초록 ▼

An onboard portion of the system is located on an aircraft for monitoring a plurality of flight parameters and detecting a predetermined exceedence indicative of a potential problem. With regard to flight data, predetermined exceedences could include abnormal attitude, control surface actuator failu

An onboard portion of the system is located on an aircraft for monitoring a plurality of flight parameters and detecting a predetermined exceedence indicative of a potential problem. With regard to flight data, predetermined exceedences could include abnormal attitude, control surface actuator failure, low hydraulic fluid pressure, low fuel, near stall speed, excessive engine RPM, engine failure, cabin pressure loss, and so forth. With regard to voice data, predetermined exceedences could include excessive decibel levels, excessive static, overly long periods of silence, and other audible conditions indicative of cockpit intrusion. Flight data representative of the flight parameters is transmitted via RF signals upon the detection of the predetermined exceedence. A remote portion of the system receives the transmitted RF signals carrying the flight data and records the flight data for analysis.

대표청구항 ▼

An onboard portion of the system is located on an aircraft for monitoring a plurality of flight parameters and detecting a predetermined exceedence indicative of a potential problem. With regard to flight data, predetermined exceedences could include abnormal attitude, control surface actuator failu

An onboard portion of the system is located on an aircraft for monitoring a plurality of flight parameters and detecting a predetermined exceedence indicative of a potential problem. With regard to flight data, predetermined exceedences could include abnormal attitude, control surface actuator failure, low hydraulic fluid pressure, low fuel, near stall speed, excessive engine RPM, engine failure, cabin pressure loss, and so forth. With regard to voice data, predetermined exceedences could include excessive decibel levels, excessive static, overly long periods of silence, and other audible conditions indicative of cockpit intrusion. Flight data representative of the flight parameters is transmitted via RF signals upon the detection of the predetermined exceedence. A remote portion of the system receives the transmitted RF signals carrying the flight data and records the flight data for analysis. etworks.5. A flight control system according to claim 1, wherein the plurality of predictive neural networks are trained based on a set of trim data.6. A flight control system according to claim 1, wherein at least one of the upstream processing elements converts dimensional aircraft state parameters into nondimensional aircraft state parameters selected from the group consisting of inflow ratio, advance ratio, thrust coefficient, torque coefficient, rotor hub roll rate, and rotor hub pitch rate.7. A flight control system according to claim 6, wherein at least one of the upstream processing elements comprises an estimating neural network.8. A flight control system according to claim 7, wherein the estimating neural network comprises an estimated rotor torque coefficient neural network and an estimated rotor thrust coefficient neural network.9. A flight control system according to claim 1, wherein at least some of the plurality of predictive neural networks comprise predictive neural networks selected from the group consisting of an inflow ratio prediction neural network, a rotor thrust coefficient prediction neural network, a rotor torque coefficient prediction neural network, and an engine torque prediction neural network.10. A method of determining tactile cueing for a flight control input apparatus, comprising: receiving observed parameters relating to the flight envelope of an aircraft including observed parameters relating to an aircraft state; converting at least some observed parameters relating to an aircraft state into nondimensional aircraft state parameters; predicting flight envelope limiting parameters based on the observed parameters and nondimensional aircraft state parameters; determining the most limiting flight envelope limiting parameter; and determining a tactile cueing position for the flight control input apparatus based on the most limiting parameter. 11. The method according to claim 10, wherein the step of receiving observed parameters further comprises receiving aircraft state parameters selected from the group consisting of roll rate, pitch rate, rotor tip mach number, rotor rotational speed, collective pitch, and cyclic pitch.12. The method according to claim 10, wherein the step of receiving observed parameters further comprises receiving observed parameters relating to engine state parameters selected from the group consisting of turbine gas temperature, engine transmission torque, and gas generator speed.13. The method according to claim 10, wherein the step of receiving observed parameters further comprises receiving observed parameters relating to environmental parameters selected from the group consisting of ambient temperature and air density.14. The method according to claim 10, wherein the step of receiving observed parameters further comprises receiving observed parameters relating to aircraft state selected from the group consisting of body-axis forward speed, body-axis sideward speed, and body-axis vertical speed.15. The method according to claim 10, wherein the step of predicting flight envelope limiting parameters further comprises predicting flight envelope limiting parameters that are nondimensional.16. The method according to claim 10, wherein the step of converting at least some observed parameters further comprises converting dimensional aircraft state parameters into nondimensional aircraft state parameters selected from the group consisting of inflow ratio, advance ratio, thrust coefficient, torque coefficient, rotor hub roll rate, and rotor hub pitch rate.17. The method according to claim 10, wherein the step of predicting flight envelope limiting parameters further comprises predicting parameters selected from the group consisting of inflow ratio, rotor thrust coefficient, rotor torque coefficient, and engine torque.18. A computer program product for determining tactile cueing limits for a flight control input apparatus, the computer program product comprising a