Disclosed is an instrument panel designed to be integrated into an aircraft cockpit, the instrument panel comprising a main structure, extending longitudinally and having a concave shape defining a cavity, this cavity being configured to receive a plurality of navigation command and/or control units, and at least one inner wall, configured to delimit at least two recesses each intended to receive at least one of the plurality of navigation command and/or control units, the instrument panel being characterized in that the main structure is made from a single piece made from a composite material.

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 seat track covering system and method are configured to cover a seat track and one or more cables within an internal cabin of a vehicle. The seat track covering system and method include a seat track cover that securely couples to the seat track, and at least one cover adjustment member moveably coupled to the seat track cover. The seat track cover and the cover adjustment member(s) cover at least a portion of the seat track and at least a portion of the cable(s).

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 packaged bearing unit is disclosed including an outer surface for receiving an aircraft landing gear wheel and an inner surface for receiving an axle. The unit may include first and second spaced-apart sets of tapered roller bearings, held between inner and outer raceways. There may be a bearing setting spacer which can be used when setting and pre-loading the bearings. The bearing unit may be a sealed unit which includes a pre-set amount of lubricant (grease) for lubricating the bearings. One or more sensors may be retained in a void between the sets of bearings. The bearing unit may remain fixed to the axle when the wheel is removed. The bearing unit may be serviced less frequently than the wheels, and may thus have a longer lifetime, possibly comparable with the lifetime of the major components of the landing gear.

Tunable multi-layer thermoplastic polymer sealants and tunable two-layer conductive thermoplastic polymer sealants, and substrates and assemblies comprising the tunable multi-layer sealants; and edge seals and fillet seals produced comprising such sealants; and substrates, components and objects comprising the tunable edge seals and fillet seals, and methods for making and applying such edge seals and fillet seals are disclosed.

A voltage controlled aircraft electric propulsion system includes an electric propulsion system. The voltage controlled aircraft electric propulsion system may include electric propulsors providing thrust for the aircraft. In hybrid systems, a gas turbine engine may also be included. The electric propulsion system may include at least one electric generator power source, at least one propulsor motor load, and at least one stored energy power source, such as a battery. The propulsor motor load may be supplied power from a power supply bus. The voltage of the power supply bus may be adjusted according to an altitude of the aircraft while maintaining a substantially constant current flow to the propulsor motor load. Due to the adjustment to lower voltages at increased altitude, insulations levels may be lower.

A heat shield assembly is disclosed. In various embodiments, the heat shield assembly defines a first circumferential side and a second circumferential side and an inboard end and an outboard end and includes a first layer defining a first surface of the heat shield assembly and having a first tab member disposed proximate the inboard end at the first circumferential side and a second tab member disposed proximate the outboard end at the first circumferential side; and a second layer defining a second surface of the heat shield assembly and having one or more first crimped portions extending along the first circumferential side and configured to engage the first tab member and the second tab member.

Tunable multi-layer thermoplastic polymer sealants and tunable two-layer conductive thermoplastic polymer sealants, and substrates and assemblies comprising the tunable multi-layer sealants; and edge seals and fillet seals produced comprising such sealants; and substrates, components and objects comprising the tunable edge seals and fillet seals, and methods for making and applying such edge seals and fillet seals are disclosed.

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.