High temperature, wireless seismometer sensor for Venus
Space agency mission plans state the need to measure the seismic activity on Venus. Because of the high temperature on Venus (462°C average surface temperature) and the difficulty in placing and wiring multiple sensors using robots, a high temperature, wireless sensor using a wide bandgap semiconductor is an attractive option. This paper presents the description and proof of concept measurements of a high temperature, wireless seismometer sensor for Venus. A variation in inductance of a coil caused by the movement of an aluminum probe held in the coil and attached to a balanced leaf-spring seismometer causes a variation of 700 Hz in the transmitted signal from the oscillator/sensor system at 426°C. This result indicates that the concept may be used on Venus.
Introduction to the Communications, Instrumentation, and Controls Division
AbstractThis paper explores the organizational history of the three core discipline areas currently residing within the Communications, Instrumentation, and Controls Division, which are harsh environment instrumentation/sensors/electronics, turbine engine controls and systems dynamics, and aerospace communications technology. Division and selected branch management will be identified by discipline in chronological order. In the second section, current division research areas will be listed by branch. Finally, future progress in the key disciplines is discussed by describing near-term future work and projecting a long-term future state beyond the horizon.
Evolution of a Mars Airplane Concept for the ARES Mars Scout Mission
ARES (Aerial Regional-scale Environmental Survey of Mars) is a proposed Mars Scout mission using an airplane to provide high-value science measurements in the areas of atmospheric chemistry, surface geology and mineralogy, and crustal magnetism. The use of an airplane for robotic exploration of Mars has been studied for over 25 years. There are, however, significant challenges associated with getting an airplane to Mars and flying through the thin, carbon dioxide Martian atmosphere. The traditional wisdom for aircraft design does not always apply for this type of vehicle and geometric, aerodynamic, and mission constraints result in a limited feasible design space. The ARES airplane design is the result of a concept exploration and evolution involving a number of trade studies, downselects, and design refinements. Industry, university, and NASA partners initially proposed a number of different concepts, drawing heavily on past Mars airplane design experience. Concept downselects were conducted with qualitative evaluation and high- level analyses, focused on the most important parameters for the ARES mission. Following a successful high altitude test flight of the basic configuration, additional design refinement led to the current design. The resulting Mars airplane concept enables the high-value science objectives of the ARES mission to be accomplished while also fulfilling the desire for a simple, low-risk design.