An aircraft wheel hub protector is adapted to engage an aircraft wheel including an aircraft tire on a rim. The aircraft wheel hub protector having two or more cover sections with a protective protrusion and coupling mechanism guide extending from the a first cover section and passing through a bearing race and internal surface within a hub of the rim of the aircraft wheel in such a fashion so as to provide a void within the protective protrusion. The second cover section is engaged with an opposed side of the aircraft wheel from the first cover section. A coupling mechanism passes through the void in the protective protrusion without having contact with the bearing race and internal surfaces within the hub of the rim and coupling the first cover section and securing the aircraft wheel hub protector to the aircraft wheel.

Innovative peripheral bar assembly for a transportation vehicle is provided. The assembly includes a front bar housing with a front segment and a rear segment; a rear bar housing with a front segment coupled to the rear segment of the front bar housing; and an input/output (I/O) printed circuit board (“PCB”) having an I/O connector. The I/O PCB coupled to the rear segment of the front bar housing. The assembly is coupled to a chassis of a display system having a display module, and the I/O connector is coupled to a connector of the display module for enabling an electrical connection between the peripheral bar assembly and the display module.

Provided are embodiments for a direct drive wiper system. The system includes a motor that is operably coupled to a wiper system to drive one or more wiper arms of the wiper system, and a gearbox, wherein an input to the gearbox is coupled to the motor and an output of the gearbox is coupled to the wiper assembly, wherein the gearbox is configured to convert an input from the motor to an output to drive the wiper system. The system also includes a brake and stopper mechanism that is coupled to the gearbox and the wiper system. Also provided are embodiments for a method for operating the direct drive wiper system.

An aeronautical car includes a ground-travel system including a drivetrain; an air-travel system including a detachable portion configured to house a propulsion device configured to provide thrust and to be driven by the drivetrain when the detachable portion is connected to the aeronautical car, and at least one flight mechanism configured to provide lift once the aeronautical car is in motion; and a weather manipulation device. The weather manipulation device may be configured to manipulate at least one aspect of a weather condition while the aeronautical car is in the air.

A battery module can include multiple cell tubes, a first conductive plate, and multiple first spacers. The multiple cell tubes can accommodate multiple battery cells within the multiple cell tubes so that individual of the multiple battery cells are positioned within individual of the multiple cell tubes. The first conductive plate can include multiple first holes and electrically connect first terminals of the multiple cells. The multiple first spacers can be mounted in the multiple first holes and support the multiple tubes and the multiple cells with respect to the first conductive plate, the multiple first spacers being configured to provide thermal and electrical isolation between the multiple battery cells and the first conductive plate.

A battery module can include multiple cell tubes and a conductive plate. The multiple cell tubes can accommodate multiple battery cells within the multiple cell tubes so that individual of the multiple battery cells are positioned within individual of the multiple cell tubes. The conductive plate can include a printed circuit board. The printed circuit board can include a first conductive layer and an isolating layer. The isolating layer can include a blind hole through which a wire bonding extends. The wire bonding can be electrically connected to the first conductive layer.

A battery module can include multiple cell tubes, a first conductive plate, and multiple first spacers. The multiple cell tubes can accommodate multiple battery cells within the multiple cell tubes so that individual of the multiple battery cells are positioned within individual of the multiple cell tubes. The first conductive plate can include multiple first holes and electrically connect first terminals of the multiple cells. The multiple first spacers can be mounted in the multiple first holes and support the multiple tubes and the multiple cells with respect to the first conductive plate, the multiple first spacers being configured to provide thermal and electrical isolation between the multiple battery cells and the first conductive plate.

This invention is about a set of common features that will characterize any machine of the new type to be produced within the set of pumps, turbines and blowers. The machines in this new category, as will be here described, will be told apart from those already in use by one main peculiarity. They will feature a stationary (non-rotating) axle for the rotation of the impeller around it but the impeller will be a solid part of the housing which will be the rotating part. Firmly, on or through the hollow core of the axle, ducts will be fitted for the intake and discharge of the powering or pumped fluid. So the housing of the machine will deliver or receive power from the body in which it will be incorporated or connected (that is torque times angular velocity). An implementation of this invention is shown in the accompanying drawings. Here the rim of a wheel of an aircraft is the rotating body. Part of the rim will serve as the housing (containing shell) of an air-driven turbine (or pump as the case may be). Accordingly, the normal stationary hub of the (formerly idle) wheel will serve as the axle of rotation for the impeller born by the rotating housing. This turbine within the rim will be powered by compressed air from the fuselage to make torque for prespinning the wheel just before touchdown. During landing, this air may be redirected to the brakes for early cooling. The rim already transformed into an air-driven turbine can be utilized to taxi or pull-out the aircraft without a tractor. In this case the turbine of this invention can be made as a two-stage regenerative machine. Research on the capabilities of the just invented turbine at the phase of development will determine the feasibility of taxiing without the main engines at least partially, using pneumatic power from the Auxiliary Power Unit.

This disclosure describes at least embodiments of an aircraft monitoring system for an electric or hybrid airplane. The aircraft monitoring system can be constructed to enable the electric or hybrid aircraft to pass certification requirements relating to a safety risk analysis. The aircraft monitoring system can have different subsystems for monitoring and alerting of failures of a component, such as a battery pack, a motor controller, and/or a motors. The failures that pose a greater safety risk may be monitored and indicated by one or more subsystems without use of programmable components.

A method of a solar cell array arranged on the surface of a support by providing and utilizing an assembly fixture having a smooth, concave surface. An uncured supporting film composed of a composite material (such as a carbon fiber composite) is mounted directly on the back side of the solar cells; and the film of composite material is co-cured on the assembly fixture so that the array of interconnected solar cells is bonded to the supporting film. The bonded and cured film of composite material and an array of interconnected solar cells is then removed from the assembly fixture.