초록 ▼

A cruise speed control apparatus for aircraft wherein small differences between the target Mach command and the actual Mach number of the aircraft are used to displace the aircraft from its reference altitude to either increase or decrease actual Mach number in the short term. Long term differences

A cruise speed control apparatus for aircraft wherein small differences between the target Mach command and the actual Mach number of the aircraft are used to displace the aircraft from its reference altitude to either increase or decrease actual Mach number in the short term. Long term differences are corrected through a special isolation filter to separate the engine control loop and pitch control loop dynamics and an integration technique to adjust the automatic throttles about a thrust target for the commanded Mach. Large differences between the target Mach and the actual Mach or large changes in the commanded Mach are compensated for by a non-linear gain that effectively increases or decreases the target thrust to cause the aircraft to accelerate or decelerate to the commanded Mach.

대표청구항 ▼

A speed control system for aircraft having an automatic throttle control means for controlling the thrust imparted to the aircraft and having first dynamic response characteristics and an automatic altitude control means for controlling pitch attitude to maintain a predetermined altitude and having

A speed control system for aircraft having an automatic throttle control means for controlling the thrust imparted to the aircraft and having first dynamic response characteristics and an automatic altitude control means for controlling pitch attitude to maintain a predetermined altitude and having second dynamic response characteristics comprising: means providing a speed error signal proportional to the difference between a reference speed and the actual speed, means providing an altitude error signal proportional to the difference between a reference altitude and the actual altitude, first integrator means responsive to said speed error signal for controlling said throttle control means, second integrator means responsive to said altitude error signal and said speed error signal for controlling said altitude control means, and isolation filter means responsive to said speed error signal for additionally controlling said throttle control means, said filter having a frequency response to said speed error signal such as to minimize interference between said first and second dynamic response characteristics by accepting long term changes in airspeed and rejecting short term changes in airspeed due to changes in pitch attitude.