An instrumented device for the study of airflow over a structure (10), comprises a support (16) forming a thin plate (24) adapted to be applied and shaped to the contour of a predetermined region of the structure. Connection structure (22) cements a portion of an inner surface of the support to that predetermined region, leaving a space (36) of low height between an inner surface of the plate (24) of the support and that predetermined region. This height is substantially equal to the thickness of said cementing structure. Instrumentation (18) is connected to the support, a portion (28) of this instrumentation and wire connections (20) therefor being disposed in that space (36), whereby the device is adapted to form a skin on the structure.
A gaseous fluid data sensor assembly for acquiring data regarding the ambient environment adjacent a surface of an airframe with adjacent air speeds below 40 knots (or another aerodynamic structure with low speed gaseous fluid flow adjacent thereto) having a flexible substrate adhesively conforming to the airframe surface, a conformable cover layer and a relatively thin air data sensor for sensing air pressure between the substrate and the cover layer. The assembly also includes a fiber optic communication link, a battery, a data acquisition subsystem, and a flexible printed circuit, all between the substrate and the cover layer. The cover layer is formed of a polymer film.
In a method and apparatus for measuring pressure, sound and vibration, particularly for the flow analysis on missiles or airplanes, a sensor device which is used to sense pressure or sound waves, is linked to a structure of a structural part in order to measure forces acting upon the structural part surface. The sensor device is arranged completely inside the structure of the structural part or on the rear side of the structural part surface. In particular, the sensor device may comprise a piezoelectric foil which is situated under the structural part surface.
