发明名称 |
Aircraft engine detonation indication system |
摘要 |
A detonation detection system for internal combustion piston engines which senses pressure within each cylinder through a piezoelectric force transducers installed under each spark plug producing pressure charged signals which signal is converted from inline charge to voltage. The signal is then passed through a gating comparator which segregates out the low pressure signals associated with intake and exhaust strokes. The signal then passes through a high-pass filter which removes normal combustion pressures. The filtered signal is then processed through an RMS (root mean square) to a DC converter which continuously computes the instantaneous square of the input signal, averages it, and takes the square root of the result to provide a DC voltage proportional to the RMS of the input. The DC signal is then processed through a peak and hold circuit which holds the peak signal for an adjustable reset-time period. A digital display is provided for each cylinder which receives and displays in numerical value the peak RMS signal.
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申请公布号 |
US5581016(A) |
申请公布日期 |
1996.12.03 |
申请号 |
US19940346822 |
申请日期 |
1994.11.29 |
申请人 |
THE CESSNA AIRCRAFT COMPANY |
发明人 |
GONZALEZ, CESAR;CHEEK, JAMES |
分类号 |
G01L23/22;(IPC1-7):G01L23/22 |
主分类号 |
G01L23/22 |
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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