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公开(公告)号：US5023797A
公开(公告)日：1991-06-11
申请号：US587495
申请日：1990-09-20
IPC分类号： G05D1/00
CPC分类号： G05D1/0005
摘要： The reference speed for a helicopter engine is incremented or decremented (237, 239) in dependence upon whether a specific range (miles per unit of fuel) has increased or decreased (236a) in a current period of time compared to the next preceding period of time, separated therefrom by at least 20 seconds (243, 244) to thereby set engine speed for minimizing use of fuel over distance traveled. Fuel is sampled only during steady flight (250-255).
摘要翻译： 直升机发动机的参考速度根据在当前时间段内的特定范围（单位燃料里程）是否增加或减少（236a）而增加或减少（236,39） 时间，与其隔开至少20秒（243,244），从而设定发动机转速，以使燃料在行驶距离上的使用最小化。 燃油仅在稳定飞行期间进行采样（250-255）。
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公开(公告)号：US5948023A
公开(公告)日：1999-09-07
申请号：US879205
申请日：1997-06-19
IPC分类号： G05D1/08 , G06F165/00
CPC分类号： G05D1/0858
摘要： A monitoring and control system for a dual-engine helicopter for OEI flight operations includes a parametric indicator operative in response to sensor signals for monitoring an engine gas generator speed parameter N1 during dual-engine and OEI flight operations. The indicator includes a rotatable needle that provides an analog indication of the current value of the N1 parameter. For dual-engine flight operations, the indicator includes a first DE indicia defining a normal operating range for the N1 parameter, a second DE indicia that defines a precautionary operating range for the N1 parameter, and a DE indicium that defines a take off power limit for the N1 parameter. For OEI flight operations, the indicator further includes an expanded scale, OEI indicia that defines an OEI precautionary operating range for the N1 parameter having a lower limit of that defines a maximum continuous OEI power rating for the N1 parameter, a first OEI indicium that defines a 2-minute OEI power rating for the N1 parameter, a second OEI indicium that defines a 30-second OEI power rating for the N1 parameter. The first and second OEI indicia in combination define a 30-second OEI operating range for the N1 parameter, and the first OEI indicium and the DE indicium in combination define a 2-minute OEI operating range for the N1 parameter. The indicator further includes a first dedicated bi-colored lamp fixture disposed in combination with the first OEI indicium that is operative in response to a first activation signal to illuminate in a first color to indicate that the 2-minute OEI power rating is enabled and is operative in response to a second activation signal to illuminate in a second color to indicate that the helicopter is being operated in the 2-minute OEI operating range, and a second dedicated bi-colored lamp fixture disposed in combination with the second OEI indicium that is operative in response to a first activation signal to illuminate in a first color to indicate that the 30-second OEI power rating is enabled and is operative in response to a second activation signal to illuminate in a second color to indicate that the helicopter is being operated in the 30-second OEI operating range. Control during OEI flight operations is provided by a three-position OEI switch assembly integrated in combination with the grip of the cyclic control stick, the three-position OEI switch assembly including a three-position select switch that is manually operable to select the 30-second OEI power rating, the 2-minute OEI power rating, or the maximum continuous OEI power rating for OEI flight operations by manual manipulation of the three-position select switch to a first position, a second position, and a third position, respectively.
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3.发明授权
公开(公告)号：US5020316A
公开(公告)日：1991-06-04
申请号：US354534
申请日：1989-05-19
申请人： David H. Sweet , Charles E. Greenberg , Nicholas D. Lappos , David M. Walsh , Richard P. Meisner
发明人： David H. Sweet , Charles E. Greenberg , Nicholas D. Lappos , David M. Walsh , Richard P. Meisner
CPC分类号： G05D1/0858
摘要： The speed 54,56 of the free turbine 40 of a helicopter engine 22 is compared 134,138 with the speed 142,140 of the helicopter rotor 10 to indicate 106,108 a specific magnitude of autorotation and the deceleration 150 of the rotor above either one of two threshold magnitudes 220,222 (dependent on the magnitude of autorotation) is utilized 81,68,69 to increase fuel flow 72 to the engine according to a specific schedule 160,162 determined by the type of autorotation, in anticipation of rotor speed droop which would otherwise occur during recovery from the autorotation maneuver.
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公开(公告)号：US4998202A
公开(公告)日：1991-03-05
申请号：US354533
申请日：1989-05-19
CPC分类号： G05D1/0858
摘要： A helicopter engine speed reference (66) is increased (113, 103-105) in response to heavy rotor loading (108). The reference speed is faded up (113, 104) at a rather rapid rate to 107% of rated speed (114). After a fixed time interval (118), reduced rotor loading (119) will cause the reference speed to be faded down slowly (120, 103-105) to rated speed (121). If torque exceeds 111% of rated torque (117), the reference speed is similarly faded down (120, 103-105).
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