Abstract: A system for determining a most probable cause of an event is presented. The system includes a processing subsystem coupled to a smart lighting subsystem and is configured to receive an event signature from the smart lighting subsystem, determine an event based on the event signature, determine an entropy of the event, connect with a plurality of historical data documents, determine information gain of at least a first subset of the plurality of historical data documents, identify and index a plurality of relevant documents from the first subset of the plurality of historical data documents based on the information gain and a determined threshold, determine one or more probable reasons of the event based on the plurality of relevant documents, and determine the most probable cause of the event at least based on the probable reasons, the plurality of relevant documents and the plurality of historical data documents.

Abstract: The present invention relates to a lightweight helicopter with features of coaxial, contra-rotating rotors and weight shift control. It has a rotary wing unit attached to a tricycle assembly through a hang bolt. The rotary wing unit has an engine mounted below a keel post, which drives a pair of contra-rotating coaxial rotors through a primary gearbox and a secondary gear box. The keel post is attached to a triangular control frame, the base of which forms the control bar. The keel post also supports a fuel tank connected to the engine and a tail plane having one or more articulated vertical flaps actuated by cables. The secondary gearbox is provided with a free-wheeling clutch, a pinion gear and bevel gears for transmitting the rotary movement of the engine to the counter rotating coaxial vertical shafts each carrying two rotor blades of airfoil cross section fixed by pitch bearing on teetering plates and teetering hinges to form horizontal rotors.

Abstract: The present invention relates to a lightweight helicopter, comprising of a rotary wing (1) unit and a frame assembly (2), the rotary wing consists of an engine (3) with a primary gear box (7), mounted below a keel post (8) and the keel post attached to a triangular control frame (28), the base of which forms the control bar (29), and is also provided with a tail plane (12) having one or more vertical articulable flaps (34). A secondary gearbox is provided with means capable of transmitting the rotary movement of the said engine to two horizontal rotors (9, 10) capable of pitch change. The rotary wing unit is suspended by means to a frame assembly having means (47) for pilot seating, landing gear (46) and provided with means for control of the engine, rotors, tailplane and landing gear.