A carbon nanocomposite-based contact mode interdigitated center of pressure sensor (CMIPS) has been developed.
The experimental study demonstrated that the CMIPS has the capability to measure the overall pressure as well as
the center of pressure in one dimension, simultaneously. A theoretical model for the CMIPS is established here
based on the equivalent circuit of the CMIPS configuration as well as the material properties of the sensor. The
experimental results match well with the theoretical modeling predictions. This theoretical model will provide
guidelines for future advanced sensor development based on the CMIPS. A system mapped with two or more pieces
of the CMIPS can be used to obtain information from the pressure distribution in multi-dimensions. As an
intelligent system component, the inexpensive CMIPS can be used broadly for improving sensing and control
capabilities of aircraft and measurement capabilities of biomedical research as well as chemical industries.
In the development and testing of novel structural and controls concepts, such as morphing aircraft wings, appropriate models are needed for proper system characterization. In most instances, available system models do not provide the required additional degrees of freedom for morphing structures but may be modified to some extent to achieve a compatible system. The objective of this study is to apply wind tunnel data collected for an Unmanned Air Vehicle (UAV), that implements trailing edge morphing, to create a non-linear dynamics simulator, using well defined rigid body equations of motion, where the aircraft stability derivatives change with control deflection. An analysis of this wind tunnel data, using data extraction algorithms, was performed to determine the reference aerodynamic force and moment coefficients for the aircraft. Further, non-linear influence functions were obtained for each of the aircraft's control surfaces, including the sixteen trailing edge flap segments. These non-linear controls influence functions are applied to the aircraft dynamics to produce deflection-dependent aircraft stability derivatives in a non-linear dynamics simulator. Time domain analysis of the aircraft motion, trajectory, and state histories can be performed using these nonlinear dynamics and may be visualized using a 3-dimensional aircraft model. Linear system models can be extracted to facilitate frequency domain analysis of the system and for control law development. The results of this study are useful in similar projects where trailing edge morphing is employed and will be instrumental in the University of Maryland's
continuing study of active wing load control.