A protective assembly comprises a first region formulated and configured to provide protection from alpha, beta, and electromagnetic radiation and comprising a composite of particles and polymer; a second region formulated and configured to provide protection from ballistic impact and comprising a composite of fibers and polymer; and a third region formulated and configured to provide protection from thermal radiation and comprising a composite of particles, fiber, and polymer. The protective assembly may be provided on an aerospace structure. The protective assembly may be formed on the aerospace structure body using a co-curing process.

A protective assembly comprises a first region formulated and configured to provide protection from alpha, beta, and electromagnetic radiation and comprising a composite of particles and polymer; a second region formulated and configured to provide protection from ballistic impact and comprising a composite of fibers and polymer; and a third region formulated and configured to provide protection from thermal radiation and comprising a composite of particles, fiber, and polymer. The protective assembly may be provided on an aerospace structure. The protective assembly may be formed on the aerospace structure body using a co-curing process.

A temperature control system may include a heat exchanger configured to cool air within a pressurized enclosed crew cabin when the air is circulated across the heat exchanger and coolant is circulated through the heat exchanger. The system may further include a sublimator configured to cool the coolant. The system may also include a primary coolant line configured to transport the coolant from the sublimator through the heat exchanger.

A temperature control system may include a heat exchanger configured to cool air within a pressurized enclosed crew cabin when the air is circulated across the heat exchanger and coolant is circulated through the heat exchanger. The system may further include a sublimator configured to cool the coolant. The system may also include a primary coolant line configured to transport the coolant from the sublimator through the heat exchanger.

A method and satellite for capture-less management of orbital debris objects, include controlling a satellite having opposing thrusters to be maintained at a predetermined distance from an orbital debris object to be managed, i.e., paired with the orbital debris object. Management may include fine tracking of the orbital debris object and/or operating the opposing thrusters to apply force to the orbital debris object to generate a model of the orbital debris object, to change the attitude of the orbital debris object, to deorbit the orbital debris object, and/or breakup the orbital debris object.

A method and satellite for capture-less management of orbital debris objects, include controlling a satellite having opposing thrusters to be maintained at a predetermined distance from an orbital debris object to be managed, i.e., paired with the orbital debris object. Management may include fine tracking of the orbital debris object and/or operating the opposing thrusters to apply force to the orbital debris object to generate a model of the orbital debris object, to change the attitude of the orbital debris object, to deorbit the orbital debris object, and/or breakup the orbital debris object.

Space traffic is managed using data gathered by orbital sensors. A constellation of near-equatorial orbiting satellites can be established, with each satellite in the constellation including at least one sensor for tracking resident space objects (RSO). The tracking data gathered by these orbital sensors can be fused with previously-gathered orbital tracking data and/or tracking data from ground-based sensors and used to adjust orbital information for the RSOs. The adjusted orbital information for the RSOs can, in turn, be used to issue conjunction warnings, to adjust the orbits of one or more satellites in the constellation (e.g., to intercept a debris object; to intercept a target; to avoid an active spacecraft), and/or to adjust the orbits of one or more other spacecraft (e.g., to avoid debris).

Space traffic is managed using data gathered by orbital sensors. A constellation of near-equatorial orbiting satellites can be established, with each satellite in the constellation including at least one sensor for tracking resident space objects (RSO). The tracking data gathered by these orbital sensors can be fused with previously-gathered orbital tracking data and/or tracking data from ground-based sensors and used to adjust orbital information for the RSOs. The adjusted orbital information for the RSOs can, in turn, be used to issue conjunction warnings, to adjust the orbits of one or more satellites in the constellation (e.g., to intercept a debris object; to intercept a target; to avoid an active spacecraft), and/or to adjust the orbits of one or more other spacecraft (e.g., to avoid debris).

Methods and systems may provide for a structure having a plurality of interconnected panels, wherein each panel has a plurality of detection layers separated from one another by one or more non-detection layers. The plurality of detection layers may form a grid of conductive traces. Additionally, a monitor may be coupled to each grid of conductive traces, wherein the monitor is configured to detect damage to the plurality of interconnected panels in response to an electrical property change with respect to one or more of the conductive traces. In one example, the structure is part of an inflatable space platform such as a spacecraft or habitat.

Methods and systems may provide for a structure having a plurality of interconnected panels, wherein each panel has a plurality of detection layers separated from one another by one or more non-detection layers. The plurality of detection layers may form a grid of conductive traces. Additionally, a monitor may be coupled to each grid of conductive traces, wherein the monitor is configured to detect damage to the plurality of interconnected panels in response to an electrical property change with respect to one or more of the conductive traces. In one example, the structure is part of an inflatable space platform such as a spacecraft or habitat.