| 摘要 |
An auxiliary safety system for controlling the attitude of an aircraft (1) provides sensors placed on the aircraft (1) which identify stalling and/or other critical flying conditions that are imminent and/or have occurred, an electronic control unit (101, 201) connected to the sensors (106, 107, 108, 206, 207, 208), and propellers placed on the aircraft each suitable to generate a continuous thrust; the electronic control unit (101, 201) activates the propellers, in case the above mentioned conditions occur, in order to generate a continuous thrust for all the duration of the attitude correction and be able to recover the proper flight attitude of the aircraft. The system is reliable and easily controllable and has a low energy consumption. |
