Integrated aeroelasticity measurement for vehicle health management

Systems and methods for aeroelasticity measurement and vehicle structural health analysis and monitoring are disclosed. In one embodiment, a computer based system to monitor structural integrity of an aircraft comprises a processor and a memory module coupled to the processor and comprising logic instructions stored on a computer readable medium which, when executed by the processor, configures the processor to receive a plurality of aeroelasticity measurements and associated flight parameters collected in real time during a flight operation, store the plurality of aeroelasticity measurements and associated flight parameters in a persistent storage medium, and generate an alert when one or more aeroelasticity parameters exceeds a threshold. The aeroelasticity measurement system may comprise a system to perform in-flight wing twist measurements of an aircraft.