Abstract: In one aspect, conduction cooled modules are described herein. In some implementations, a conduction cooled module comprises first and second external support structures arranged in facing opposition to one another, forming a component envelope therebetween. In some implementations, the modules are configured to contact at least one cold plate and to retain at least one printed wiring board in the component envelope in between the first external support structure and the second external support structure.

Abstract: An electric brake system architecture for an aircraft with two or more electrical braking subsystems including brake system controls configured to communicate pilot pedal commands to electric brake actuator controllers that apply or release brakes in wheel groups. The system allows independent brake activation of wheel groups through a plurality of brake system controls and electric brake actuator controllers. The electric braking system further includes remote data consolidators to collect and transmit wheel data to brake system controls through a digital data communication bus. The system reduces aircraft weight, prevents inadvertent braking, and prevents error propagation between subsystems.

Abstract: Methods and means for reducing wear in electric or electro-hydraulic braking systems utilizing an adjustable (adaptive) filter, wherein the adaptive filter provides for rapid response during anti-skid operation and a smooth and filtered response during non-anti-skid operation.

Abstract: Methods and means for reducing wear in electric or electro-hydraulic braking systems utilizing an adjustable (adaptive) filter, wherein the adaptive filter provides for rapid response during anti-skid operation and a smooth and filtered response during non-anti-skid operation.

Abstract: In one aspect, conduction cooled modules are described herein. In some implementations, a conduction cooled module comprises first and second external support structures arranged in facing opposition to one another, forming a component envelope therebetween. In some implementations, the modules are configured to contact at least one cold plate and to retain at least one printed wiring board in the component envelope in between the first external support structure and the second external support structure.

Abstract: An electric brake system architecture for an aircraft with two or more electrical braking subsystems including brake system controls configured to communicate pilot pedal commands to electric brake actuator controllers that apply or release brakes in wheel groups. The system allows independent brake activation of wheel groups through a plurality of brake system controls and electric brake actuator controllers. The electric braking system further includes remote data consolidators to collect and transmit wheel data to brake system controls through a digital data communication bus. The system reduces aircraft weight, prevents inadvertent braking, and prevents error propagation between subsystems.

Abstract: A loop resistance tester (LRT) for shield integrity testing comprising three elements: a “drive” current coupler, a “sense” current coupler, joint probes, and an instrument assembly. A low-power excitation current is sent from the instrument into the drive coupler, which is essentially a transformer. This induces a current in the electrical cable under test, as long as that cable and the connected structure form a continuous current path, or loop. This induced loop current is detected by the “sense” current coupler (transformer) and is measured by the instrument. The ratio of the loop voltage to loop current, as phasor values, gives the complex loop impedance, the real part of which is the loop resistance.

Abstract: A method and apparatus for reducing multiple-source repetitive vibrations in a region or structure (12) by applying control vibrations to the region or structure via actuators (18), frequently recalculating the control vibrations based on source elements to accommodate for varying phase differences between the sources of the repetitive vibrations (14) and (16), and cyclically updating the source elements of the control vibrations is disclosed. The repetitive vibrations are sensed (20) synchronously with the repetitive vibration source chosen as the reference source and decomposed into a number of frequency components corresponding to the reference source. The control vibrations are formed of the same frequency components and applied synchronously with the reference source. Each frequency component of the control vibrations is defined by source elements, one for cancelling vibrations produced by each of the repetitive vibration sources.