发明名称 |
PROCEDE ET DISPOSITIF DE DETECTION DE GIVRAGE D'UNE ENTREE D'AIR D'UN TURBOMOTEUR |
摘要 |
A method of detecting that an aircraft is flying in icing conditions. A processor unit determines a real power developed by the turboshaft engine and a theoretical power that the engine can develop in theory, the theoretical power being determined using a theoretical model supplying a power as a function at least of a speed of rotation of a gas generator of the engine. The processor unit determines a difference between the real power and the theoretical power. The processor unit generates a warning to indicate the presence of icing conditions when the power difference is greater than a predetermined power threshold for a length of time longer than a time threshold, and when a temperature outside the aircraft lies between a low temperature threshold and a high temperature threshold. |
申请公布号 |
FR3024434(B1) |
申请公布日期 |
2016.08.05 |
申请号 |
FR20140001738 |
申请日期 |
2014.07.29 |
申请人 |
AIRBUS HELICOPTERS |
发明人 |
ROSSOTTO REGIS;CAMHI EMMANUEL |
分类号 |
B64D15/20;F01D25/02;G08B21/00 |
主分类号 |
B64D15/20 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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