发明名称 |
VORRICHTUNG ZUR REGELUNG DER KRAFTSTOFFZUFUHR BEI DREHFLUEGELFLUGZEUGEN |
摘要 |
Rotor speed is maintained at a reference speed 48 by a closed-loop fuel control system 40,44,46,48,54,58. Load factor potential is enhanced by increasing the reference speed as a function of the helicopter pitch rate 72 and optionally airspeed 80 when undergoing positive pitch rate manoeuvres. The reference may be increased only when a certain airspeed (cruise speed) has been reached. Alternatively load factor can be sensed directly or combined with pitch rate by use of an accelerometer 73. <IMAGE> |
申请公布号 |
DE3428224(A1) |
申请公布日期 |
1985.02.14 |
申请号 |
DE19843428224 |
申请日期 |
1984.07.31 |
申请人 |
UNITED TECHNOLOGIES CORP. |
发明人 |
EARL COOPER,DEAN;JOHN HOWLETT,JAMES |
分类号 |
B64C27/14;B64C27/00;B64C27/12;B64D31/00;B64D31/06;G05D1/08;H02P23/00 |
主分类号 |
B64C27/14 |
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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