Abstract: Microthruster includes a combustion chamber comprising a substrate material, a fuel inlet, and a gas outlet. A first resistance heater is arranged in the combustion chamber. A catalyst is structured and arranged to decompose fuel entering the combustion chamber. First substrate material sections are heated by the first resistance heater to at least one of a predetermined temperature and a predetermined temperature range. This Abstract is not intended to define the invention disclosed in the specification, nor intended to limit the scope of the invention in any way.

Abstract: An integratable sensor for an airfoil of an aircraft such as an airplane and a helicopter comprises a sensor capsule, in whose inner chamber a measuring element for measuring an environmental parameter is situated. A capsule carrier is implemented to accommodate and removably attach the sensor capsule and is integratable in an airfoil of an airplane or a helicopter. Elastic contact elements are used for secure electrical connection of the sensor capsule to the capsule carrier. The sensor capsule is replaceable, while the capsule carrier is permanently integrated in the airfoil, in particular in a rotor blade. The measuring element is, for example, a pressure sensor.