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4.5 thermal environment for control system components is heavily influenced by the design of the engine bay ventilation system, which lags significantly behind. Again, somewhat conservative design assumptions must be made to allow control system components to meet the propulsion system development schedule. Chapter Summary This chapter discussed the current gas turbine engine control system development process as applied to Pratt & Whitney programs and provides a baseline against which to compare the revised framework. The current control system development process tends to be schedule- constrained based on manufacturing lead-times and hardware delivery requirements rather than on the availability of solid design requirements and design lead-time. The definition of risk as used in this work was provided and the current Pratt & Whitney risk mitigation process was described. The tools used for risk mitigation vary from company to company, but the basic approach to mitigate risk is consistent across the aerospace industry. The reasons for non- optimum control system component designs boil down to two basic issues: late definition of requirements and late definition of interfaces. Late control system requirements stems from the way the engine is designed (from the inside out). The turbomachinery, exhaust system and engine control laws must first have a reasonably mature design in order to generate control system requirements, however design and manufacturing lead times and the need to perform hardware/software integration tests on the closed-loop bench prior to engine test drive the control system component designs to be launched with significant requirement uncertainty. Additional schedule pressure results from the fact that many control system requirements are driven by interface and environmental requirements defined by the aircraft, whose development program typically lags behind the propulsion system by at least one year. 82PDF Image | Improving Gas Turbine Engine Control System
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