Total energy based flight control system

In a method of flight control in which a thrust command is computed based on a total aircraft energy rate error E.sub.S.epsilon. and an elevator command is computed based on an energy distribution rate error D.sub..epsilon., the improvement comprising computing an elevator control command in response to a control column input by the pilot;

• the computing including:
• (a) computing the energy distribution rate error as a function of an acceleration error, a current flight path angle .gamma., and a manual commanded flight path angle .gamma..sub.C.sbsb.MAN ;
• the .gamma..sub.C.sbsb.MAN signal initially being in excess of the sustainable flight path angle established for the prevailing thrust condition by an amount proportional to the column input;
• and
• (b) processing the .gamma..sub.C.sbsb.MAN signal so that the amount of .gamma..sub.C.sbsb.MAN in excess of the sustainable flight path angle for the prevailing thrust condition and an altered speed condition is eventually eliminated, with the aircraft establishing a change in speed relative to a set reference speed, the speed change being proportional to the column input.