Applying total energy control to designing feasible large aircraft longitudinal landing control system

Aim. The introduction of the full paper reviews some papers in the open literature, mostly in Chinese, and then applies total energy control to achieving its feasibility. Sections 1, 2 and 3 explain our design and give simulation results to verify its feasibility. The core of section 2 consists of: (1) we utilize the Eigen-structure assignment (EA) method to design the pitch inner-loop of aircraft and its control augmentation system; (2) taking both the uncertainty and complexity of aircraft engine control loop into consideration, we use the quantitative feedback theory (QFT) method to perform the compensation design of a thrust loop. The core of section 3 consists of: (1) we take a B-737-100TSRV aircraft as a numerical example to design its longitudinal landing control system; (2) we apply total energy control to coordinating the elevator of aircraft and its thrust commands, thus implementing the decoupling of flight path from speed control, glide-down and landing; (3) we perform the simulation of our aircraft longitudinal automatic landing control system; the simulation results, given in Figs. 4 and 5, and the analysis of Fig. 5 show preliminarily that the landing control system is feasible for decoupling the flight path of aircraft from its speed control and thus achieving precise landing.