This invention discloses an automatic
throttle speed control method and
system for aircraft based on dynamic inverse, belonging to the field of
design technology. The method includes: multiplying the difference between the
ground speed command and the
ground speed feedback by an acceleration
gain proportional term to obtain the desired
ground speed acceleration increment; solving for the ground speed acceleration increment using
climb angle,
angle of attack, sideslip angle, axial overload, lateral overload, and normal overload; multiplying the difference between the desired ground speed acceleration increment and the ground speed acceleration increment by a
state function related to the aircraft's
mass to obtain the desired thrust acceleration increment; obtaining the engine
thrust efficiency matrix by taking the partial derivative of the engine thrust with respect to the
throttle opening; multiplying the calculated desired thrust acceleration increment by the inverse of the
thrust efficiency matrix, and then adding the
throttle state variable from the previous cycle to obtain the final
throttle control command. The automatic
throttle control law of this invention is derived from pure
equations of motion, with clear physical meaning. The control law structure does not contain integrators, feedforward compensation, or other terms, reducing the "
trial and error" work of
gain preset while achieving consistent control performance. It exhibits high robustness and has broad
engineering application prospects.