Abstract: A system for an electrically powered aircraft can comprise: a truss configured to couple to a structure of an aircraft; a battery system supported by the truss, the battery system including a first array of battery modules and a second array of battery modules, the first array of battery modules operably coupled to the second array of battery modules: and an exhaust system including a first exhaust manifold, a second exhaust manifold, and a common exhaust manifold, the first exhaust manifold coupled to each battery module in the first array of battery modules, the second exhaust manifold coupled to each battery module in the second array of battery modules, and the first exhaust manifold and the second exhaust manifold each coupled to the common exhaust manifold.

Abstract: The invention relates to a battery-based system for powering refrigerated transport and other industrial applications. It includes a battery-based system for supplying power comprising a housing encasing a battery unit, a battery management system connected to the battery unit and operable to manage battery unit, and a power management unit connected to the battery unit and operable to convert battery power from the battery unit to 3 phase power of between 380 and 480 Vac. One exemplary application of the invention is to replace diesel gen-sets in refrigerated transport with more reliable and reduced emission battery power.