Abstract: An avionics unit assembly for an aircraft can include an avionics unit (e.g., an underwater locator device, “ULD”), and a battery to power the avionics unit. The avionics unit assembly can further include a housing that encases the avionics unit and the battery. The housing includes a vent port for exhausting an emission from the housing during a failure of the avionics unit. The avionics unit assembly can further include one or more of a suppressor that filters the emission, a shield element that is resistant to chemical and/or thermal effects of the emission, and a bracket for mounting the avionics unit to a surface. A method integrating the avionics unit assembly onto a forward aircraft bulkhead at a mount location under an aircraft radome and for manufacturing the avionics unit, and an aircraft including the avionics unit are also described.

Abstract: Provided herein are methods, systems, apparatuses, and computer programs related to various devices in an enclosure, e.g., using identification capturing device such as in conjunction with a digital twin of the enclosure. The computer program may be utilized for commissioning, maintenance, sales, marketing, and/or customer service. The computer program may receive customer, and/or customer service, input. The computer program may facilitate use of customer and/or customer service, e.g., input for controlling the facility (e.g., various devices of the facility), input for structuring the facility, and/or input for placing assets such as devices of the facility.

Abstract: There is provided an oriented wire electrostatic radiation protection system for a spacecraft. The system has a wire management system, and first and second wires coupled to the wire management system. A first wire orientation apparatus orients the first wire in a first wire direction toward, and in parallel alignment with, an approach path of approaching solar particles. A second wire orientation apparatus orients the second wire in a second wire direction opposite to the first wire direction. The system has a control system, and a power supply to charge the first wire to a positively-charged wire and to charge the second wire to a negatively-charged wire. When the approaching solar particles travel alongside the positively-charged wire toward the spacecraft, the positively-charged wire deflects the approaching solar particles away from the spacecraft, via electrostatic repulsion, and the positively-charged wire creates a radiation protection shielded region around the spacecraft.

Abstract: An avionics unit assembly for an aircraft includes an avionics unit such as an underwater locator device (ULD) having a transmitter configured to output a radio frequency pulse and a battery configured to power the device. The avionics unit assembly can further include a housing that encases the transmitter and the battery and includes a vent port for exhausting an emission from the housing during a failure of the avionics unit. The avionics unit assembly can further include one or more of a suppressor that filters the emission, a shield element that is resistant to chemical and/or thermal effects of the emission, and a bracket for mounting the avionics unit assembly to a surface. The suppressor can include a plurality of channels, where each channel includes at least one blind alley that can capture/filter a particulate component and/or a liquid component from the emission and/or break up the particulate component.

Abstract: An avionics unit assembly for an aircraft can include an avionics unit (e.g., an underwater locator device, “ULD”), and a battery to power the avionics unit. The avionics unit assembly can further include a housing that encases the avionics unit and the battery. The housing includes a vent port for exhausting an emission from the housing during a failure of the avionics unit. The avionics unit assembly can further include one or more of a suppressor that filters the emission, a shield element that is resistant to chemical and/or thermal effects of the emission, and a bracket for mounting the avionics unit to a surface. A method integrating the avionics unit assembly onto a forward aircraft bulkhead at a mount location under an aircraft radome and for manufacturing the avionics unit, and an aircraft including the avionics unit are also described.

Abstract: An avionics unit assembly for an aircraft includes an avionics unit such as an underwater locator device (ULD) having a transmitter configured to output a radio frequency pulse and a battery configured to power the device. The avionics unit assembly can further include a housing that encases the transmitter and the battery and includes a vent port for exhausting an emission from the housing during a failure of the avionics unit. The avionics unit assembly can further include one or more of a suppressor that filters the emission, a shield element that is resistant to chemical and/or thermal effects of the emission, and a bracket for mounting the avionics unit assembly to a surface. The suppressor can include a plurality of channels, where each channel includes at least one blind alley that can capture/filter a particulate component and/or a liquid component from the emission and/or break up the particulate component.

Abstract: There is provided an oriented wire electrostatic radiation protection system for a spacecraft. The system has a wire management system, and first and second wires coupled to the wire management system. A first wire orientation apparatus orients the first wire in a first wire direction toward, and in parallel alignment with, an approach path of approaching solar particles. A second wire orientation apparatus orients the second wire in a second wire direction opposite to the first wire direction. The system has a control system, and a power supply to charge the first wire to a positively-charged wire and to charge the second wire to a negatively-charged wire. When the approaching solar particles travel alongside the positively-charged wire toward the spacecraft, the positively-charged wire deflects the approaching solar particles away from the spacecraft, via electrostatic repulsion, and the positively-charged wire creates a radiation protection shielded region around the spacecraft.

Abstract: A rechargeable battery comprises a chassis including a lower fixation plate, and a plurality of battery cells on the lower fixation plate. The lower fixation plate includes at least one flow channel positioned to collect condensate from the battery cells and move the collected condensate away from the battery cells.

Abstract: A rechargeable battery comprises a plurality of individual sealed battery cells, and dielectric separators between the battery cells for creating thermal barriers between opposing surfaces of the battery cells. The dielectric separators are made of a fiber composite.

Abstract: A steering column assembly includes an energy absorption assembly, an adjustment lever, and a rocker member. The energy absorption assembly has an energy absorption strap and a cam member. The adjustment lever is operatively connected to at least one of the upper jacket assembly and the lower jacket assembly. The rocker member has a rocker member body that extends between a first end connected to the adjustment lever and a second end configured to engage the cam member.

Abstract: A steering column assembly includes a plunger assembly received within an opening defined by a mounting bracket. The plunger assembly includes a sleeve, a plunger, and a biasing member. The sleeve disposed within the opening. The plunger slidably disposed within the sleeve. The biasing member that engages the plunger to bias the plunger towards a deployed position.

Abstract: A steering column assembly includes an energy absorption assembly, an adjustment lever, and a rocker member. The energy absorption assembly has an energy absorption strap and a cam member. The adjustment lever is operatively connected to at least one of the upper jacket assembly and the lower jacket assembly. The rocker member has a rocker member body that extends between a first end connected to the adjustment lever and a second end configured to engage the cam member.

Abstract: An aircraft comprises a rechargeable battery including an array of battery cells, and means for mitigating consequences of failure of the rechargeable battery due to aircraft operating cycles.

Abstract: A steering column assembly includes a plunger assembly received within an opening defined by a mounting bracket. The plunger assembly includes a sleeve, a plunger, and a biasing member. The sleeve disposed within the opening. The plunger slidably disposed within the sleeve. The biasing member that engages the plunger to bias the plunger towards a deployed position.

Abstract: A clamping mechanism for a steering column assembly includes an outboard cam configured to rotate about an axis between a first position and a second position, an inboard cam having a travel limiter portion configured to limit rotation of the outboard cam about the axis between the first position and the second position, and an intermediate stop disposed along a portion of the travel limiter portion. At least a portion of the outboard cam is shifted to a position adjacent the intermediate stop during an impact event of the steering column assembly, the intermediate stop preventing movement of the outboard cam from the first position to the second position.

Abstract: A clamping mechanism for a steering column assembly includes an outboard cam configured to rotate about an axis between a first position and a second position, an inboard cam having a travel limiter portion configured to limit rotation of the outboard cam about the axis between the first position and the second position, and an intermediate stop disposed along a portion of the travel limiter portion. At least a portion of the outboard cam is shifted to a position adjacent the intermediate stop during an impact event of the steering column assembly, the intermediate stop preventing movement of the outboard cam from the first position to the second position.

Abstract: A system and methods for magnetically managing combustion are presented. Fuel is injected into a magnetic field at least partially enclosed in a combustion chamber, and a combustion region comprising electrically conductive species is produced by combusting the fuel. The combustion region is magnetically controlled using the magnetic field operating on the electrically conductive species.

Abstract: In an exemplary embodiment of the invention, an energy absorbing device for a steering column assembly is provided. The device includes a first end configured to couple to a first component of the steering column assembly, a second end configured to couple to a second component of the steering column, and an intermediate portion extending between the first and second ends. The intermediate portion includes a curved portion having a radius, and an aperture extending through the intermediate portion. The aperture is configured to shift a collapse characteristic of the energy absorbing device and to facilitate maintaining the radius constant when a force moves the first end relative to the second end and deforms the energy absorbing device.

Abstract: In an embodiment of the invention, an anti-rotation assembly for a steering column is provided. The anti-rotation assembly includes a bushing and a pin having a detent for engaging the bushing when the pin is inserted into the bushing.

Abstract: In an exemplary embodiment of the invention, an energy absorbing device for a steering column assembly is provided. The device includes a first end configured to couple to a first component of the steering column assembly, a second end configured to couple to a second component of the steering column, and an intermediate portion extending between the first and second ends. The intermediate portion includes a curved portion having a radius, and an aperture extending through the intermediate portion. The aperture is configured to shift a collapse characteristic of the energy absorbing device and to facilitate maintaining the radius constant when a force moves the first end relative to the second end and deforms the energy absorbing device.