Abstract: A method for managing environmental conditions of an information handling system includes obtaining an ambient temperature and an ambient humidity of an environment proximate to the information handling system. The method also includes determining a target relative humidity for the information handling system and determining a target temperature for the information handling system based on the target relative humidity, the ambient temperature, and the ambient humidity. Further, the method includes determining that the target temperature is within an acceptable range of temperatures. In addition, the method includes adjusting an amount of air recirculated through the information handling system, and adjusting the amount of air recirculated is based on the determination that the target temperature is within an acceptable range of temperatures.

Abstract: A method for removing moisture from an airflow via a cooling system includes identifying a plurality of active cooling circuits in the cooling system. The method also includes lowering a first temperature set point of a first cooling circuit of the multiple cooling circuits. In addition, the method includes raising a second temperature set point of a second cooling circuit of the multiple cooling circuits.

Abstract: An information handling system includes multiple components and multiple zones, with each zone including a portion of a total number of the components. The information handling system also includes a processor programmed to determine that a communication failure has occurred with one of the components of the information handling system, identify a zone of the multiple zones that includes the one of the components; and instruct the zone to switch to a default mode.

Abstract: A method for environmentally managing environmental conditions of an information handling system includes obtaining an ambient temperature of an environment proximate to the information handling system. The method also includes obtaining an ambient humidity of the environment, determining a component temperature of a component in the information handling system, and determining a component humidity of the component based on the component temperature, the ambient temperature, and the ambient humidity. Further, the method includes determining an acceleration factor for the component based on the component humidity and the component temperature, and performing an action from an action set based on the acceleration factor.

Abstract: In an example implementation, a method includes receiving, at a computing device, borrower information and requested financing plan information. Likewise, a method includes outputting at least a portion of the received information to a second computing device and, after receiving an indication of a decision denying the requested financing plan, outputting at least a portion of the received information to a computing device associated with a lender and confirming, to a computing device associated with a borrower or a merchant that the information has been sent to the lender.

Abstract: An aircraft may include a body structure, a tail section articulatably coupled to the body structure and including a tail structure, a propulsion system coupled to the tail structure and configured to produce thrust for the aircraft, and a stabilizer coupled to the tail structure, and an actuation system configured to articulate the tail section relative to the body structure to change a thrust vector of the propulsion system and an angle of attack of the stabilizer during flight. The actuation system may be configured to articulate the tail section about at least two perpendicular rotational axes. The propulsion system may be configured to produce the thrust in a first thrust direction in a first flight mode (e.g., a rotor-borne flight mode) and to produce the thrust in a second thrust direction in a second flight mode (e.g., a wing-borne flight mode).

Abstract: An aircraft may include a body structure and a propulsion system coupled to the body structure and including a mounting shaft and a rotor. The rotor may include a rotor hub and a set of rotor blades, wherein the rotor is configured to orient the set of rotor blades at a first collective blade angle during a first flight mode and orient the set of rotor blades at a second collective blade angle during a second flight mode. The propulsion system may further include a motor coupled to the rotor and configured to rotate the rotor in a first rotational direction in the first flight mode to produce thrust in a first thrust direction and rotate the rotor in a second rotational direction opposite the first rotational direction in the second flight mode to produce thrust in a second thrust direction opposite the first thrust direction.

Abstract: An aircraft may include a fuselage, a propulsion assembly configured to produce thrust for the aircraft, and a gimballing mechanism articulatably coupling the propulsion assembly to the fuselage and configured to rotate the propulsion assembly about a first axis of rotation defined through a center of mass of the propulsion assembly, and rotate the propulsion assembly about a second axis of rotation defined through the center of mass of the propulsion assembly. The first axis of rotation may be perpendicular to the second axis of rotation. The first axis of rotation may be perpendicular to the second axis of rotation.

Abstract: An aircraft may include a body structure, a tail section articulatably coupled to the body structure and including a tail structure, a propulsion system coupled to the tail structure and configured to produce thrust for the aircraft, and a stabilizer coupled to the tail structure, and an actuation system configured to articulate the tail section relative to the body structure to change a thrust vector of the propulsion system and an angle of attack of the stabilizer during flight. The actuation system may be configured to articulate the tail section about at least two perpendicular rotational axes. The propulsion system may be configured to produce the thrust in a first thrust direction in a first flight mode (e.g., a rotor-borne flight mode) and to produce the thrust in a second thrust direction in a second flight mode (e.g., a wing-borne flight mode).

Abstract: An aircraft may include a body structure and a propulsion system coupled to the body structure and including a mounting shaft and a rotor. The rotor may include a rotor hub and a set of rotor blades, wherein the rotor is configured to orient the set of rotor blades at a first collective blade angle during a first flight mode and orient the set of rotor blades at a second collective blade angle during a second flight mode. The propulsion system may further include a motor coupled to the rotor and configured to rotate the rotor in a first rotational direction in the first flight mode to produce thrust in a first thrust direction and rotate the rotor in a second rotational direction opposite the first rotational direction in the second flight mode to produce thrust in a second thrust direction opposite the first thrust direction.

Abstract: An apparatus and method for automated launch, retrieval, and servicing of a hovering aircraft is provided. The apparatus includes a line which is elevatable while maintaining a principally horizontal axis. For retrieval, the aircraft translates principally spanwise over the line, following a path which is principally horizontal and normal to the line. At an appropriate moment, the line is elevated and contacts the aircraft's wing. As the aircraft continues translating, the line slides along the wing until captured in a cleat. The aircraft is then stably tethered in hover, and its position can be manipulated by articulating the line, such as to guide the aircraft into a docking station. For launch the aircraft lifts itself into hover while tethered to the line. Articulation of the line guides the aircraft into a launch position, at which point the line is disconnected from the cleat, thereby releasing the aircraft.

Abstract: An apparatus and method for automated launch, retrieval, and servicing of a hovering aircraft is provided. The apparatus includes a line which is elevatable while maintaining a principally horizontal axis. For retrieval, the aircraft translates principally spanwise over the line, following a path which is principally horizontal and normal to the line. At an appropriate moment, the line is elevated and contacts the aircraft's wing. As the aircraft continues translating, the line slides along the wing until captured in a cleat. The aircraft is then stably tethered in hover, and its position can be manipulated by articulating the line, such as to guide the aircraft into a docking station. For launch the aircraft lifts itself into hover while tethered to the line. Articulation of the line guides the aircraft into a launch position, at which point the line is disconnected from the cleat, thereby releasing the aircraft.

Abstract: An apparatus and method for automated launch, retrieval, and servicing of a hovering aircraft is provided. The apparatus includes a line which is elevatable while maintaining a principally horizontal axis. For retrieval, the aircraft translates principally spanwise over the line, following a path which is principally horizontal and normal to the line. At an appropriate moment, the line is elevated and contacts the aircraft's wing. As the aircraft continues translating, the line slides along the wing until captured in a cleat. The aircraft is then stably tethered in hover, and its position can be manipulated by articulating the line, such as to guide the aircraft into a docking station. For launch the aircraft lifts itself into hover while tethered to the line. Articulation of the line guides the aircraft into a launch position, at which point the line is disconnected from the cleat, thereby releasing the aircraft.

Abstract: Various embodiments of the present disclosure provide a tail-sitter aircraft having a leg assembly convertible from landing gear into a rear fuselage and empennage (or a tail assembly) of the aircraft. Generally, the leg assembly includes multiple legs movable from a closed configuration in which the legs form the tail assembly of the tail-sitter aircraft to an open configuration in which the legs form the landing gear of the tail-sitter aircraft (and vice-versa).

Abstract: An electric fence control unit includes a signal generator, a first signal receiver, a second signal receiver, a signal processing and control unit, and a communications interface. The signal generator generates and transmits an adjustable power signal along a conduction path of the electric fence. The signal receivers sample signal outputs at a driven end and at an open end of the fence line. The signal processing and control unit receives and analyzes the first signal output and the second signal output. The communications interface transmits results from processing the first signal output and the second signal output to a service center. The power signal is adjustable to any capacity power level between a maximum power level and a minimum power level to match a load of the electric fence. Methods of monitoring the electric fence, including adjusting a power level of the adjustable power signal, are also disclosed.

Abstract: Various embodiments of the present disclosure provide a tail-sitter aircraft having a leg assembly convertible from landing gear into a rear fuselage and empennage (or a tail assembly) of the aircraft. Generally, the leg assembly includes multiple legs movable from a closed configuration in which the legs form the tail assembly of the tail-sitter aircraft to an open configuration in which the legs form the landing gear of the tail-sitter aircraft (and vice-versa).

Abstract: An electric fence energizer provides automated reporting of faults and other events as well as fault location to reduce effort in diagnosing faults and intrusion events in electric fences by measuring impedance changes using a time-domain reflectometer. In some embodiments, methods determine the location of a fault in distance from the energizer and provide timely and appropriate condition information.

Abstract: An apparatus and method for automated launch, retrieval, and servicing of a hovering aircraft is provided. The apparatus includes a line which is elevatable while maintaining a principally horizontal axis. For retrieval, the aircraft translates principally spanwise over the line, following a path which is principally horizontal and normal to the line. At an appropriate moment, the line is elevated and contacts the aircraft's wing. As the aircraft continues translating, the line slides along the wing until captured in a cleat. The aircraft is then stably tethered in hover, and its position can be manipulated by articulating the line, such as to guide the aircraft into a docking station. For launch the aircraft lifts itself into hover while tethered to the line. Articulation of the line guides the aircraft into a launch position, at which point the line is disconnected from the cleat, thereby releasing the aircraft.

Abstract: An electric fence control unit includes a signal generator, a first signal receiver, a second signal receiver, a signal processing and control unit, and a communications interface. The signal generator generates and transmits an adjustable power signal along a conduction path of the electric fence. The signal receivers sample signal outputs at a driven end and at an open end of the fence line. The signal processing and control unit receives and analyzes the first signal output and the second signal output. The communications interface transmits results from processing the first signal output and the second signal output to a service center. The power signal is adjustable to any capacity power level between a maximum power level and a minimum power level to match a load of the electric fence. Methods of monitoring the electric fence, including adjusting a power level of the adjustable power signal, are also disclosed.

Abstract: An electric fence energizer provides automated reporting of faults and other events as well as fault location to reduce effort in diagnosing faults and intrusion events in electric fences by measuring impedance changes using a time-domain reflectometer. In some embodiments, methods determine the location of a fault in distance from the energizer and provide timely and appropriate condition information.