| 摘要 |
A reference trajectory (4) is calculated over a prediction horizon based on data from a terrain database (6). The flight trajectory (2) is optimized for the prediction horizon, based on parameters including the reference trajectory and a load factor or the like acting on the aircraft. The optimization is based on the following non-linear model of the aircraft (1) : x(t) = f(x(t),u(t)) y(t) = Cx(t), where y(t) is the altitude of the aircraft, u(t) is a control sequence for the aircraft and x(t) is a state vector of the model. At least a first value of the control sequence providing the optimized flight trajectory is fed to aircraft control, the prediction horizon is updated and the optimization method is repeated. An Independent claim is also included for a device in an aircraft for carrying out this method. |
