| 摘要 |
The method involves selecting two flight parameters of an aircraft to be estimated. Flight mechanics equations that are respectively associated with the selected flight parameters are identified, where a dependency relationship exists between the selected flight parameters. An extended Kalman filter (10) is configured based on the identified equations associated with the flight parameters to receive values of input parameters. The extended Kalman filter is implemented during flight of the aircraft such that the filter delivers joint estimations of the selected flight parameters as output. The input parameters of the extended Kalman filter comprise inertial parameters, anemometric parameters, parameters specific to aircraft and intermediate parameters arising from onboard modeling. An independent claim is also included for a system for determining flight parameters of an aircraft in real time. |
