Abstract: A system for measuring a heat response of a cell during a thermal runaway event includes a housing. An insulation is positioned within the housing. A calorimeter is positioned within the insulation and the housing. The calorimeter is configured to have the cell positioned therein. The calorimeter is configured to measure a temperature increase of the cell, one or more components of the calorimeter, or a combination thereof during the thermal runaway event of the cell. A total energy yield of the thermal runaway event is configured to be determined based at least partially upon the temperature increase. A ratio is configured to be determined based at least partially upon the temperature increase. The ratio includes energy released through a casing of the cell during the thermal runaway event vs. energy released through ejecta material from the cell during the thermal runaway event.

Abstract: Various embodiments may provide a strain-sensing apparatus configured to be attached to a micrometeoroid and orbital debris (MMOD) shielding layer and data collection equipment in communication with the strain-sensing apparatus configured to detect an occurrence, a time, a location, and/or a severity of a MMOD strike on the MMOD shielding layer. The various embodiments may enable detection and/or location of potentially harmful MMOD strikes on both human occupied and unmanned spacecraft.

Abstract: Various embodiments may provide a strain-sensing apparatus configured to be attached to a micrometeoroid and orbital debris (MMOD) shielding layer and data collection equipment in communication with the strain-sensing apparatus configured to detect an occurrence, a time, a location, and/or a severity of a MMOD strike on the MMOD shielding layer. The various embodiments may enable detection and/or location of potentially harmful MMOD strikes on both human occupied and unmanned spacecraft.

Abstract: Methods and apparatus are provided for a single heavy-lift launch to place a complete, operational space station on-orbit. A payload including the space station takes the place of a Shuttle Orbiter using the launch vehicle of the Shuttle Orbiter. The payload includes a forward shroud, a core module, a propulsion module, and a transition module between the core module and the propulsion module. The essential subsystems are pre-integrated and verified on Earth. The core module provides means for attaching international modules with minimum impact to the overall design. The space station includes six control moment gyros for selectably operating in either LVLH (local-vertical local-horizontal) or SI (solar inertial) flight modes.