| 摘要 |
Disclosed is a method for optimising the trajectory of an aircraft, comprising steps consisting of: determining one or more reference criteria CiRef from an initial non-optimised trajectory; determining one or more initial constraints K'j from the initial trajectory; determining a criterion Ci according to an analytical function of said criteria CiRef; and, by iterative cycle, determining an optimised trajectory; determining the intermediate constraints K'j from the optimised trajectory; minimising the criteria Ci determined under the initial constraints K'j and the intermediate constraints K'j; and determining q take-off parameters Pi. Developments describe an incremental iteration of the method, an interruption by the pilot, the use of criteria comprising fuel consumption, acoustic noise level, emission of chemical compounds, engine wear level, the use of a gradient descent and various optimisations. Aspects of the system and software are described. |
