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provide more of a "seamless" transfer from dual-channel control (in which each EEC provide V of the command signal simultaneously to position the effector and each receives a continuous feedback signal) to single-channel control since the amount of time for a channel to increase its command signal from %2 output to full output is nearly instantaneous. Also, in the event of a "runaway" command signal from one channel (e.g. a current driver failure), the other channel will tend to counteract the runaway by commanding the effector in the opposite direction of the failure, resulting in a smaller off-schedule transient of the effector. The disadvantage of an active-active system is that software complexity is increased substantially, driving up development and software maintenance costs. The second level of decomposition required for effector loops is the selection of the types ofeffectors and feedback devices. Requirements such as frequency response, contamination resistance, and hysteresis will affect the concept selection ofthe effector device, such as a single- stage electro-hydraulic servo valve (EHSV), two-stage EHSV, or direct-drive valve (DDV). Requirements such as accuracy, linearity, and reliability will drive the selection of the feedback device for the effector loop. Typical devices used for aerospace control systems are linear variable displacement transducers (LVDTs), rotary variable displacement transducers (RVDTs), and resolvers. As mentioned previously, it is desirable to adopt a common effector loop architecture for a particular propulsion system in order to have a single electronic interface design for the multiple loops required. The number of effector loops can range from around a half dozen in the case of the somewhat simple commercial engine control systems to 2-3 times that many in the case of state-of-the art military systems which employ thrust vectoring, thrust augmentation, and/or vertical lift functions. 46PDF Image | Improving Gas Turbine Engine Control System
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