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Research platforms require flight test instrumentation systems fulfilling the difficult compromise between minimum weight, space, energy consumption and maximum flexibility combined with a high number of different measurement requirements. This paper describes the challenges faced during the design of such an instrumentation system, the changes introduced in sequential iterations in the standard architectures of FTI (Flight Test Instrumentation) systems for large AC (aircraft) prototypes, as well as some limits met during the design.

9.4 - Design of a minimum weight/space/energy consumption instrumentation system