Abstract: A vertical takeoff and landing (VTOL) aircraft is configured with a front set of propellers mounted to a front wing and an aft set of propellers mounted to an aft wing wherein the propellers may be repositioned by rotating them around a front thrust vectoring axis and an aft thrust vectoring axis respectively. The positioning of the propellers with respect to the thrust vectoring axes and the positioning of the thrust vectoring axes with respect to the upper and lower limits of the passenger compartment ensure that, as the propellers are rotated from a vertical thrust position to a horizontal thrust position, the plane of rotation of the propellers never intersects with the portion of the passenger compartment where a failure of propeller components could result in debris penetrating the passenger compartment and causing injury.

Abstract: An aerospace hybrid powertrain system includes an engine, a power shaft, and an electric machine having the power shaft therein or passing therethrough. The aerospace hybrid powertrain system further includes a fan, impeller, or blower connected to the power shaft and configured to direct air toward components of at least one of the engine or the electric machine. The fan, impeller, or blower may further be configured to direct air toward cooling elements such as heat exchangers or finned heat sinks arranged to cool the components of at least one of the piston combustion engine or the electric machine.

Abstract: An energy source for an aircraft includes an enclosure, an engine, an electric generator, and at least one fuel tank configured to provide fuel to the engine; and electrical connectors for outputting power generated by the electric generator to at least one electrical component or electrical bus of the aircraft. The engine, the electric generator, and the at least one fuel tank are each housed within the enclosure.

Abstract: A hybrid powertrain system includes an engine, an electric machine having a power shaft therein, and a clutch configured to releasably engage an output of the engine and the power shaft of the electric machine. The electric machine further includes an electrical output. The power shaft is configured to mechanically attach to and provide mechanical power to a propulsion device. A controller is configured to control the engine, the electric machine, and the clutch to implement one or more power output modes.

Abstract: An aircraft safety system includes impact energy reduction systems including: an aircraft parachute, at least one rotor configured for autorotation, and an energy absorbing system. An automatic control system uses data from speed and altitude sensors to selectively and sequentially deploy the impact energy reduction systems depending on the portion of the aircraft speed and altitude flight envelope in which the aircraft is operating when an emergency is detected.

Abstract: An aircraft is configured with a propulsion system having a rotor with both cyclic and collective control, and an axis of rotation about which the propulsion system rotates with respect to the fuselage. A control system is configured to use torque generated through cyclic control of the rotor to reposition the propulsion system around the axis of rotation without the need for an independent actuator mechanism to rotate the propulsion system, thus reducing the weight and mechanical complexity of the aircraft. The control system may also utilize the torque provided by one or more rotors to position one or more wings with respect to the airflow over the aircraft, exerting torque on the aircraft to control the direction of the aircraft.

Abstract: A battery heating system for a hybrid aircraft powertrain includes a combustion engine, a battery pack, a combustion engine coolant circuit, and a battery pack coolant circuit. The battery heating system further includes a heat exchanger configured to exchange heat between the combustion engine coolant circuit and the battery pack coolant circuit. The battery heating system further includes at least one throttling device operatively connected to one of the combustion engine coolant circuit or the battery pack coolant circuit. The battery heating system further includes a controller configured to transmit a signal to the at least one throttling device to adjust a flow of coolant through the heat exchanger of at least one of the combustion engine coolant circuit or the battery pack coolant circuit.

Abstract: An aircraft safety system includes impact energy reduction systems including: an aircraft parachute, at least one rotor configured for autorotation, and an energy absorbing system. An automatic control system uses data from speed and altitude sensors to selectively and sequentially deploy the impact energy reduction systems depending on the portion of the aircraft speed and altitude flight envelope in which the aircraft is operating when an emergency is detected.

Abstract: An aircraft is configured with a propulsion system having a rotor with both cyclic and collective control, and an axis of rotation about which the propulsion system rotates with respect to the fuselage. A control system is configured to use torque generated through cyclic control of the rotor to reposition the propulsion system around the axis of rotation without the need for an independent actuator mechanism to rotate the propulsion system, thus reducing the weight and mechanical complexity of the aircraft. The control system may also utilize the torque provided by one or more rotors to position one or more wings with respect to the airflow over the aircraft, exerting torque on the aircraft to control the direction of the aircraft.

Abstract: A vertical takeoff and landing (VTOL) aircraft is configured with a front set of propellers mounted to a front wing and an aft set of propellers mounted to an aft wing wherein the propellers may be repositioned by rotating them around a front thrust vectoring axis and an aft thrust vectoring axis respectively. The positioning of the propellers with respect to the thrust vectoring axes and the positioning of the thrust vectoring axes with respect to the upper and lower limits of the passenger compartment ensure that, as the propellers are rotated from a vertical thrust position to a horizontal thrust position, the plane of rotation of the propellers never intersects with the portion of the passenger compartment where a failure of propeller components could result in debris penetrating the passenger compartment and causing injury.

Abstract: A vertical takeoff and landing aircraft includes an airframe with a wing having an airfoil, the airfoil having an airfoil chord line and the wing having a wingspan. The aircraft further includes at least one forward thrust rotor having a horizontal thrust offset angle defined between the airfoil chord line and an axis of rotation of the forward thrust rotor. The aircraft further includes a plurality of vertical thrust rotors, each of the plurality of vertical thrust rotors having a vertical thrust offset angle defined between the airfoil chord line and a plane of rotation of the vertical thrust rotor. The vertical thrust offset angle is between 3 degrees and 10 degrees. The axis of rotation of the forward thrust rotor and planes of rotation of the plurality of vertical thrust rotors define a plurality of relative thrust angles that are each less than the horizontal thrust offset angle.

Abstract: An aircraft control system includes a vertical thrust system, a horizontal thrust system, and an aerodynamic system. The system further includes a controller in at least indirect communication with the vertical thrust system, the horizontal thrust system, and the aerodynamic system. The controller is configured to substantially simultaneously control, based on at least one of a single yaw input, a single pitch input, and a single roll input, the aerodynamic system and a differential thrust generated by the plurality of vertical thrust rotors of the vertical thrust system to adjust at least one of pitch, yaw, and roll of a vertical takeoff and landing aircraft in at least one of a plurality of flight stages. The controller is further configured to independently and substantially simultaneously control the vertical and horizontal thrust systems to generate vertical and horizontal thrust in at least one of the plurality of flight stages.

Abstract: A mixed extractant solvent that includes at least one dialkyloxycalix[4]arenebenzocrown-6 compound, 4?,4?,(5?)-di-(t-butyldicyclohexano)-18-crown-6, at least one modifier, and, optionally, a diluent. The dialkyloxycalix[4]arenebenzocrown-6 compound is 1,3-alternate-25,27-di(octyloxy)calix[4]arenebenzocrown-6, 1,3-alternate-25,27-di(decyloxy)calix[4]arenebenzocrown-6, 1,3-alternate-25,27-di(dodecyloxy)calix[4]arenebenzocrown-6, 1,3-alternate-25,27-di(2-ethylhexyl-1-oxy)calix[4]arenebenzocrown-6, 1,3-alternate-25,27-di(3,7-dimethyloctyl-1-oxy)calix[4]arenebenzocrown-6, 1,3-alternate-25,27-di(4-butyloctyl-1-oxy)calix[4]arenebenzocrown-6, or combinations thereof. The modifier is a primary alcohol. A method of separating cesium and strontium from an aqueous feed is also disclosed, as are dialkyloxycalix[4]arenebenzocrown-6 compounds and an alcohol modifier.

Abstract: A mixed extractant solvent that includes at least one dialkyloxycalix[4]arenebenzocrown-6 compound, 4?,4?,(5?)-di-(t-butyldicyclohexano)-18-crown-6, at least one modifier, and, optionally, a diluent. The dialkyloxycalix[4]arenebenzocrown-6 compound is 1,3-alternate-25,27-di(octyloxy)calix[4] arenebenzocrown-6, 1,3-alternate-25,27-di(decyloxy)calix[4]arene-benzocrown-6, 1,3-alternate-25,27-di(dodecyloxy)calix[4]arenebenzocrown-6, 1,3-alternate-25,27-di(2-ethylhexyl-1-oxy)calix[4]arenebenzocrown-6, 1,3-alternate-25,27-di(3,7-dimethyloctyl-1-oxy)calix[4] arenebenzocrown-6, 1,3-alternate-25,27-di(4-butyloctyl-1-oxy)calix[4]arenebenzocrown-6, or combinations thereof. The modifier is a primary alcohol. A method of separating cesium and strontium from an aqueous feed is also disclosed, as are dialkyloxycalix[4]arenebenzocrown-6 compounds and an alcohol modifier.

Abstract: A sprayer, which in one embodiment, is a hand held ergonomic sprayer is disclosed herein. The sprayer may include: a housing through which water flows; a handle for gripping by a user, which is joined to the housing; at least one spray nozzle operatively connected to the housing; and, a connection for a hose, the connection being joined to the housing. In one non-limiting embodiment, when the sprayer has one end of a water-filled hose connected thereto, the combination of the sprayer and suspended portion of the hose has a combined center of gravity that passes through the axis of the sprayer handle. The sprayers described herein may also have other features, and provide other benefits that do not require the sprayers to have an ergonomic design.

Abstract: The present invention relates to a spraying device suitable for spraying cleaning compositions and rinse water onto hard surfaces, More particularly the spraying device may be attached to a hose, for example a conventional garden hose, so that the cleaning composition and rinse water can be applied to outside surfaces, such as vehicles or the outside surface of windows. The spraying device comprises a purifier located inside the cavity of a container and a spray head.

Abstract: Apparatus and methods for deodorizing and/or freshening the air are disclosed. In one non-limiting embodiment, the apparatus includes one or more passive members and an air moving member. The passive member can be detachable from the air moving member and used separately as a passive filter member, if it contains a deodorizing substance, or as a passive emitting member, if it contains a substance to be emitted into the air. Numerous combinations of passive filter members and passive emitting members can be used with the air moving member, or as stand-alone members in the described methods. In other non-limiting embodiments, devices can be provided that both deodorize and emit substances into the air. Kits are also provided. The substances to be emitted may be arranged in various ways to improve the amount of exposed surface area of the substance to be emitted. Intensity controlling mechanisms are also provided.

Abstract: The present invention relates to a spraying device suitable for spraying cleaning compositions and rinse water onto hard surfaces. More particularly the spraying device may be attached to a hose, for example a conventional garden hose, so that the cleaning composition and rinse water can be applied to outside surfaces, such as vehicles or the outside surface of windows. The spraying device comprises a purifier located inside the cavity of a container and a spray head.