Abstract: The present disclosure is directed to unmanned aerial vehicle (UAV) comprising a convertible body operably coupled to at least one sensor, and further configured to rotate at least about a longitudinal axis, thereby providing a full field of regard for the at least one sensor, and a plurality of arms extending laterally from the convertible body, each arm of the plurality of arms having a rotor assembly coupled thereto.

Abstract: Provided herein are various enhanced systems, apparatuses, and techniques for optical communication among a constellation of satellites. One example includes establishing an initial cross-connect configuration comprising optical communication links among a constellation of satellites. In the initial cross-connect configuration, the satellites can optically communicate with both adjacently positioned and non-adjacently positioned satellites in the constellation. The satellites obtain angular states of the optical communication links resultant from orbital motion of the satellites. When angular states of a portion of the optical communication links reach an exclusion range, the satellites establish a subsequent cross-connect configuration to avoid optically communicating within the exclusion range.

Abstract: A heat recuperating system is adapted for recuperating heat generated by mining devices, s.g. cryptocurrency miners, and for using the recuperating heat in agri-food industry applications. The heat recuperating system comprises a technical room comprising an air supply area, an exhausted air area and a computation area dividing the air supply area from the exhausted air area, wherein the computation area houses the mining devices. The heat recuperating system also comprises a heat exchanger system recuperating heat from the exhausted air area of the technical room and transmitting the recuperated heat to the agri-food industry applications. An associated method comprises supplying a technical room comprising a computation area wherein the mining devices are operating; supplying a heat exchanger system recuperating heat generated by the mining devices when operating; and transmitting the recuperated heat to the agri-food industry applications.

Abstract: A system includes a first structure having an upper surface coupled to a second structure by a fastener assembly including a bushing positioned within an opening in the upper surface of the first structure. An inner opening of the bushing defines an inner diameter, and a fastener is at least partially positioned within the bushing. An outer surface of the fastener defines an outer diameter of the fastener. The bushing and the fastener are configured such that a space between the outer surface of the fastener and the inner opening of the bushing defines a gap which increases in size in a direction extending from the upper surface to the lower surface of the first structure.

Abstract: Motion steering under kino dynamic constraints is provided. A system can receive an indication to return to a route generated for autonomous navigation by the aircraft to a destination. The system can generate a vector field formed of a plurality of vectors that merge into the route. The vector field can be generated responsive to the indication to return to the route. The system can provide instructions to steer the aircraft toward the destination along the route via one or more vectors of the plurality of vectors in the vector field. The instructions can be based on a cost function applied to the vector field.

Abstract: In one embodiment, systems and methods include using an inspection and projection system to measure the thickness of a coating and provide visual guidance for secondary operations. The inspection and projection system comprises a robotic arm operable to rotate about a plurality of axes, wherein an end effector is disposed at a distal end of the robotic arm. The inspection and projection system further comprises a linear rail system, wherein the robotic arm is coupled to the linear rail system, and wherein the robotic arm is operable to translate along the linear rail system. The inspection and projection system further comprises a frame, wherein the linear rail system is disposed on top of the frame, and an information handling system coupled to the frame, wherein the information handling system is operable to actuate the robotic arm and the linear rail system.

Abstract: In one embodiment, systems and methods include using a Langmuir probe to measure a plasma. The Langmuir probe comprises a housing, wherein the housing comprises an outer diameter and an inner diameter, wherein the inner diameter defines an internal cavity. The Langmuir probe further comprises a plurality of bodies, wherein the plurality of bodies is disposed at least partially within the inner cavity, wherein each of the plurality of bodies comprise a set of internal cavities. The Langmuir probe further comprises a plurality of double Langmuir probes disposed each set of the internal cavities.

Abstract: A rotor blade configured to be installed on a rotary-wing aircraft includes a main blade body including an inboard end configured to be coupled to a rotor blade hub and an outboard end. The rotor blade includes a blade tip removably coupled to the outboard end of the main blade body, the blade tip including an inner cavity. The rotor blade further includes a tip block including an inboard portion coupled to the outboard end of the main blade body and a cantilevered portion extending beyond the outboard end of the rotor blade and into the inner cavity of the blade tip.

Abstract: A vibration control assembly includes a housing having an interior region and an inner mass including a cage disposed within the interior region of the housing and being rotatable within the housing about a first axis and a gyroscope wheel disposed within the cage and rotatable about a second axis other than the first axis. At least one driving source includes a stator and is operable to interact with a magnetic field of the inner mass to drive rotation of the inner mass about at least one of the first axis and the second axis, wherein the at least one driving source is mounted within the interior region of the housing.

Abstract: The invention relates to the treatment of ascites, and especially refractory ascites, with an orally bioavailable prodrug of dopamine. A preferred prodrug of dopamine is docarpamine. In one embodiment treated patients are, prior to treatment, on doses of furosemide >80 mg/day and/or spironolactone >100 mg/day or equivalent doses of an alternative loop-acting and/or distal-acting diuretic. The ascites treated by the invention are typically caused by liver cirrhosis due to alcohol or non-alcoholic fatty liver disease and generally not due to viral hepatitis or primary biliary cholangitis. Typical patients have an activated renin-angiotensin-aldosterone levels as may be indicated by elevated levels of renin and/or aldosterone. Refractory ascites treatable according to the invention are such that patients beginning treatment require large volume paracentesis at a minimum of: (a) 3 times in 60 days, (b) 4 times in 90 days or (c) at least once every 30 days over a 90-day period.

Abstract: A rotor assembly including a fixed fairing including an interface portion and a hub fairing including a depression. The depression is configured to receive at least a portion of the interface portion. The hub fairing is rotatable relative to the fixed fairing.

Abstract: Systems and methods for transitioning between rotor positions based on detected parameters of an aircraft. One embodiment provides an aircraft comprising a rotor assembly and a controller. The controller is configured to monitor an operating characteristic of the aircraft. The controller is configured to select, in response to a rotor neutral state of the aircraft being enabled, one of a plurality of rotor neutral positions based on the operating characteristic, the plurality of rotor neutral positions including a first rotor neutral position configured for vertical takeoff of the aircraft and a second rotor neutral position configured for start-up and shutdown of the aircraft. The controller is configured to set the selected one of the plurality of rotor neutral positions as the rotor neutral position for the aircraft.

Abstract: A phased array antenna is provided that includes a plurality of antenna elements arranged in a plurality of subarrays. A plurality of first beamformers is coupled to respective elements of the plurality of antenna elements, and a plurality of second beamformers is coupled to respective subarrays of the plurality of subarrays. A controller is configured to steer a phase center for each of the plurality of subarrays using the plurality of first beamformers so that the phase centers for the plurality of subarrays are irregularly spaced.

Abstract: A system includes a robotic arm, a rotisserie control linkage, and a computer system. The robotic arm includes a touch probe and laser head. The rotisserie control linkage is configured to couple to a transport cart. The computer system is communicatively coupled to the robotic arm and the rotisserie control linkage and is configured to control the system to probe, using the touch probe of the robotic arm, a transparent outer layer of an aircraft canopy located on the transport cart in order to determine surface measurements of the aircraft canopy. The computer system also controls the system to ablate, using a plurality of predetermined parameters and the laser head of the robotic arm, an interface layer located between the transparent outer layer and the aircraft canopy, wherein movements of the robotic arm during the ablation are based on the surface measurements.

Abstract: A rotor blade includes a spar with forward end, an aft end, and a substantially oval cross-section. The cross-section includes an upper portion tapering from a first thickness to a smaller, second thickness beginning between about 55% and about 65% of the distance to the aft end from the forward end and ending between about 65% and about 75% of the distance to the aft end measured from the forward end, and a lower portion tapering from a third thickness to a smaller, fourth thickness beginning between about 55% and about 65% of the distance to the aft end from the forward end and ending between about 65% and about 75% of the distance to the aft end measured from the forward end. The rotor blade further includes an upper blade skin, a lower blade skin, and a leading edge sheath.