Redundant electrochemical systems and methods for vehicles are described. The systems include a first electrochemical device located at a first position on the vehicle wherein the first electrochemical device is configured to generate at least one of inert gas, oxygen, and electrical power and a second electrochemical device located at a second position on the vehicle wherein the second electrochemical device is configured to generate at least one of inert gas, oxygen, and electrical power. The first electrochemical device is configured to operate in a first mode during normal operation of the vehicle and a second mode when the second electrochemical device fails, wherein in the second mode, the first electrochemical device provides the at least one of inert gas, oxygen, and electrical power for at least one vehicle critical system of the vehicle.

Grommet assembly and method for installing a grommet assembly in a penetration hole of a panel. In one embodiment, a grommet assembly is comprised of multiple parts, including end members having a diameter greater than the penetration hole, and a middle member having a diameter sized to fit within the penetration hole. Each of the members includes one or more conduit holes for a conduit that is routed through the penetration hole, and an installation slit disposed between an outer peripheral surface and a conduit hole.

Grommet assembly and method for installing a grommet assembly in a penetration hole of a panel. In one embodiment, a grommet assembly is comprised of multiple parts, including end members having a diameter greater than the penetration hole, and a middle member having a diameter sized to fit within the penetration hole. Each of the members includes one or more conduit holes for a conduit that is routed through the penetration hole, and an installation slit disposed between an outer peripheral surface and a conduit hole.

A method of generating a customized secondary power distribution assembly (SPDA) includes generating one or more customizable SPDAs. Each of the one or more customizable SPDAs is a construct corresponding with a microprocessor configured to control a set of customizable channels in each of a set of virtual line replaceable modules (vLRMs). The method also includes creating a mapping between one of the one or more customizable SPDAs and the customized SPDA, the mapping indicating line replaceable modules (LRMs) of the customized SPDA and defining each channel of each LRM, and deploying the customized SPDA in an application. The microprocessor is initiated to control the customized SPDA according to the mapping at startup.

Provided is a toroidal continuously variable transmission that can create a jet of oil resistant to the influence of wind generated by rotation of a power roller, thereby feeding a sufficient amount of oil to the power roller to cool the power roller with the oil; and a drive mechanism-integrated electricity generation apparatus for an aircraft, the electricity generation apparatus including the toroidal continuously variable transmission. The toroidal continuously variable transmission includes a discharge structure including an outlet that discharges an oil. The discharge structure includes first and second oil passages connected with each other inside the discharge structure, and arranged such that the oil flowing through the first oil passage and the second oil passage collide with each other in the vicinity of the outlet and that a jet of oil discharged from the outlet forms a flattened shape extending along a rotational direction of the power roller.

Provided is a toroidal continuously variable transmission that can create a jet of oil resistant to the influence of wind generated by rotation of a power roller, thereby feeding a sufficient amount of oil to the power roller to cool the power roller with the oil; and a drive mechanism-integrated electricity generation apparatus for an aircraft, the electricity generation apparatus including the toroidal continuously variable transmission. The toroidal continuously variable transmission includes a discharge structure including an outlet that discharges an oil. The discharge structure includes first and second oil passages connected with each other inside the discharge structure, and arranged such that the oil flowing through the first oil passage and the second oil passage collide with each other in the vicinity of the outlet and that a jet of oil discharged from the outlet forms a flattened shape extending along a rotational direction of the power roller.

A Multi-Mode Regenerative Fuel Cell system comprising a non-flow thru fuel cell operatively coupled to a high or medium pressure electrolyzer; a distributed reactant storage assembly comprising at least one hydrogen storage means and at least one oxygen storage means, said distributed reactant storage assembly operatively coupled to said fuel cell and electrolyzer; a pilot oxygen storage means operatively coupled to said oxygen storage means; a water storage means operatively coupled to said fuel cell and electrolyzer, and an aircraft power load operatively coupled to said fuel cell and electrolyzer.

A high-speed vertical take-off and landing aircraft has a lifting structure, a first rotor with a first and second blade, a second rotor with a first and second blade, an auxiliary propulsion unit for providing forward thrust, and a control system for controlling the pitch of each of the rotor blades. The aircraft has a first, rotor-only, flight mode for hovering and low speed maneuvering. It also has a second flight mode where the rotors are held in at fixed azimuth angles and forward thrust is provided by the auxiliary propulsion unit. Three axis control is provided during the second flight mode by adjusting the attack angles of the fixed rotor blades. Between these two flight modes, there is an intermediate flight mode covering a fully controlled transition between the first two flight modes.

A high-speed vertical take-off and landing aircraft has a lifting structure, a first rotor with a first and second blade, a second rotor with a first and second blade, an auxiliary propulsion unit for providing forward thrust, and a control system for controlling the pitch of each of the rotor blades. The aircraft has a first, rotor-only, flight mode for hovering and low speed maneuvering. It also has a second flight mode where the rotors are held in at fixed azimuth angles and forward thrust is provided by the auxiliary propulsion unit. Three axis control is provided during the second flight mode by adjusting the attack angles of the fixed rotor blades. Between these two flight modes, there is an intermediate flight mode covering a fully controlled transition between the first two flight modes.

A method for manufacturing a main rotor for a generator is provided. The method includes printing at least part of a rotor shaft by a three-dimensional printing process. The step of printing at least part of the rotor shaft includes printing a plurality of closed outlets and a plurality of open outlets. A rotor core is printed by the three-dimensional printing process. The step of printing the rotor core includes printing a plurality of liquid coolant conduits that extend through the rotor core and fluidly connecting the plurality of liquid coolant conduits to the plurality of closed openings.