Source Management of an Aircraft Electrical Power System with Hardware in the Loop Verification

Paper #:
  • 2017-01-2034

Published:
  • 2017-09-19
Abstract:
Future aircrafts will demand a significant amount of flight critical electrical power to drive the primary flight control surfaces. These electrical architectures will need to meet the load requirements and provide power to the flight critical buses at all times. For this to happen, a fast, resilient, and autonomous control scheme is needed. In this presentation, formal methods and linear temporal logic are used to develop a contactor control scheme to meet the given specifications of an electrical power system. The resulting control strategy is able to manage multiple contactors during different types of generator failures, while ensuring that flight critical buses maintain power. To verify the feasibility of the proposed control scheme, a real-time simulation platform is developed. Capability to test the control strategy, along with any future versions, was implemented with a microprocessor and analog/digital I/O’s (Hardware in the Loop). During the simulation of the electrical system, various combinations of generator failures are tested, and contactor logic (on/off) of the flight critical buses are monitored. In addition, the simulation platform also monitors the transient voltages at each of the flight critical buses, in order to evaluate the control scheme for overall system stability. The methodology and simulation platform are thus helpful in the design and testing of different control schemes for any current or proposed electrical power system. Acknowledgment
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