Abstract: An Environmental Control System may use an electronic particle separation system to control humidity in an aircraft. The electronic particle separation system may include a particle separator, a sensor module, and a controller configured to receive signals from the sensor module, and operate the particle separator based on the received sensor signals. In some embodiments, the controller may include a processor which may determine whether the particle separator is being operated under an ozone related condition exceeding a threshold operating condition. If one of the threshold operating conditions is exceeded, the particle separator may be turned off which may control the amount of ozone present in the aircraft.

Abstract: An Environmental Control System may use an electronic air treatment system to control humidity in an aircraft. The electronic air treatment system may use an electronic charging system and a separation system. A turbine rotor may drive a power generating stage to provide high voltage power to the electronic charging system. The charging stage may charge airflow passing through to repel liquid particles away from the airflow. Liquid droplets may be collected and centrifugally flung toward a periphery of the separation system. The liquid particles may be collected outside of the airflow, which may be allowed to pass through the separation system and out to a destination in the aircraft without the collected liquid.

Abstract: An Environmental Control System may use an electronic particle separation system to control humidity in an aircraft. The electronic particle separation system may include a charging stage and a collecting stage. The charging stage may charge airflow passing through to repel liquid particles away from the airflow. Liquid droplets may be collected by the collecting stage and centrifugally flung toward a periphery of a separator. The liquid particles may be collected outside of the airflow which may be allowed to pass through the separator and out to a destination in the aircraft without the collected liquid.

Abstract: An Environmental Control System may use an electronic particle separation system to control humidity in an aircraft. The electronic particle separation system may include a particle separator, a sensor module, and a controller configured to receive signals from the sensor module, and operate the particle separator based on the received sensor signals. In some embodiments, the controller may include a processor which may determine whether the particle separator is being operated under an ozone related condition exceeding a threshold operating condition. If one of the threshold operating conditions is exceeded, the particle separator may be turned off which may control the amount of ozone present in the aircraft.

Abstract: An Environmental Control System may use an electronic particle separation system to control humidity in an aircraft. The electronic particle separation system may include a charging stage and a collecting stage. The charging stage may charge airflow passing through to repel liquid particles away from the airflow. Liquid droplets may be collected by the collecting stage and centrifugally flung toward a periphery of a separator. The liquid particles may be collected outside of the airflow which may be allowed to pass through the separator and out to a destination in the aircraft without the collected liquid.

Abstract: An Environmental Control System may use an electronic air treatment system to control humidity in an aircraft. The electronic air treatment system may use an electronic charging system and a separation system. A turbine rotor may drive a power generating stage to provide high voltage power to the electronic charging system. The charging stage may charge airflow passing through to repel liquid particles away from the airflow. Liquid droplets may be collected and centrifugally flung toward a periphery of the separation system. The liquid particles may be collected outside of the airflow, which may be allowed to pass through the separation system and out to a destination in the aircraft without the collected liquid.

Abstract: A controlled start up technique may eliminate the excessive peak junction temperature by controlling the speed of the electric device. Lower speed may result in reduced power to the load. Reduced power may result in reduced losses to maintain reliable operating junction temperatures. Once the junction reaches the predetermined temperature limit, speed may be controlled to hold the junction temperature constant. As time elapses, the coolant temperature may reduce, thereby allowing a higher power level without an increase in IGBT temperature. Unlike conventional methods which may allow for full power continuously upon start up, thereby either potentially causing a high temperature shut-down condition or requiring additional thermal inertia to handle a high heat load due to a continuous full-power start up, the controlled start up eliminates the design penalties for extensive thermal enhancements to accommodate the occasional extreme hot start up.

Abstract: A thermal spreader for electronic components may include a plurality of carbon fiber laminate layers having a layer of stitched fibers formed thereupon. The thermal spreader may be attached to the electronic components as a thermal pad, or the thermal spreader may be extended to include attachment to a cold plate. The use of a stitched fiber layer on top of a carbon fiber laminate results in increased thermal cooling efficiency due to the increase in surface area and convectional cooling area.