发明名称 |
FUEL CONTROL FOR CONTROLLING HELICOPTER ROTOR/TURBINE ACCELERATION |
摘要 |
The difference in the speed (54, 56) of a helicopter gas engine (20), free turbine (40) from a reference speed (62, 64) generates (80) a desired acceleration signal (81). The difference (82) in actual turbine acceleration (84, 86) from desired acceleration is integrated (100) to provide an engine fuel command signal (67-73) whenever (88) the speed error signal exceeds (90) a predetermined threshold magnitude. |
申请公布号 |
DE3376993(D1) |
申请公布日期 |
1988.07.14 |
申请号 |
DE19833376993 |
申请日期 |
1983.04.15 |
申请人 |
CHANDLER EVANS INC. |
发明人 |
ZAGRANSKI, RAYMOND D.;HOWLETT, JAMES J. |
分类号 |
F02C3/10;F02C9/28;(IPC1-7):F02C9/28 |
主分类号 |
F02C3/10 |
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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