| 摘要 |
The invention concerns an aircraft propulsion system comprising a combustion engine 10 and electrical generator 11 arranged to be driven by the engine, an electrical energy store 30 and a propulsive rotor 20 arranged to be driven by an electric motor 2. The system further comprises a controller for selectively varying the supply of power to the electric motor from the generator and/or energy store in dependence on one or more property of a vapour trail resulting from the engine exhaust flow 16. The system may comprise a plurality of engines, each engine being independently controllable by the controller. The controller may control a combustion parameter so as to alter the rate of soot particle production by the engine, or engine efficiency. The controller may control engine throttle. The controller varies supply of power to the electric motor or energy store in dependence upon optical depth or expected lifetime of a contrail. The system may comprise an ambient condition sensor such as a temperature sensor, humidity sensor and/or sunlight sensor. |
