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A satellite recovery apparatus having a base configured to be attached to a satellite and having a pressurized gas chamber and a valve assembly. A plurality of walls are hingedly attached to the base and movable between a closed position, wherein the walls define a volume above the base, and an open

A satellite recovery apparatus having a base configured to be attached to a satellite and having a pressurized gas chamber and a valve assembly. A plurality of walls are hingedly attached to the base and movable between a closed position, wherein the walls define a volume above the base, and an open position, wherein the walls are disposed spaced away from the base. A heat shield is attached to the base. A deployable decelerator is attached to the heat shield and has an outer perimeter with an expandable torus that is operably connected to the valve assembly such that the expandable torus can be pressurized from the chamber. Pressurization of the expandable torus deploys the decelerator assembly from a non-deployed position within the volume to a deployed high-drag position.

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1. A satellite recovery system for returning a satellite to earth, the system comprising: a base portion configured to attach to the satellite, the base portion including a pressurized gas system;a heat shield attached to the base portion;a plurality of walls hingedly attached to the base portion, t

1. A satellite recovery system for returning a satellite to earth, the system comprising: a base portion configured to attach to the satellite, the base portion including a pressurized gas system;a heat shield attached to the base portion;a plurality of walls hingedly attached to the base portion, the plurality of walls being movable between a non-deployed position wherein the plurality of walls and the base portion define a cavity; and a deployed position wherein the plurality of walls are pivoted at least ninety degrees from the non-deployed position; anda deployable decelerator assembly movable from a non-deployed position wherein the decelerator assembly is disposed in the cavity defined by the plurality of walls and the base portion, and a deployed position, the decelerator assembly having an inner perimeter attached to the heat shield and an outer perimeter comprising an expandable torus that is operably connected to the pressurized gas system. 2. The satellite recovery system of claim 1, wherein the pressurized gas system comprises a pressure chamber, an inlet valve configured for pressurizing the pressure chamber, and a controllable outlet valve configured to fluidly connect the expandable torus to the pressurized chamber. 3. The satellite recovery system of claim 2, wherein the pressure chamber is pressurized with carbon dioxide, wherein at least a portion of the carbon dioxide is in liquid phase. 4. The satellite recovery system of claim 2, wherein the controllable outlet valve comprises a solenoid valve. 5. The satellite recovery system of claim 2, wherein the pressurized gas system further comprises a high pressure relief valve to prevent over-pressurization of the pressure chamber, and a low pressure relief valve to prevent over-pressurization of the expandable torus. 6. The satellite recovery system of claim 2, further comprising a restricting orifice disposed between the pressure chamber and the expandable torus, such that when the controllable outlet valve fluidly connects the expandable torus to the pressure chamber the restricting orifice impedes the flow to the torus such that pressure in the torus varies during reentry. 7. The satellite recovery system of claim 1, wherein the heat shield comprises a dome portion comprising a rigid, heat resistant material, and a base portion attached to the dome portion. 8. The satellite recovery system of claim 7, wherein the dome portion of the heat shield comprises at least one of a ceramic, a carbon-carbon composite, and a refractory metal alloy. 9. The satellite recovery system of claim 7, wherein the heat shield is attached to the base portion with a cable and an elongate tubular strut. 10. The satellite recovery system of claim 9, wherein the tubular strut includes a plurality of longitudinal features that define regions of relative weakness in the strut, and further wherein the base portion of the heat shield comprises an anvil portion configured to deform the strut upon impact of the heat shield with the ground, thereby absorbing a portion of the energy of the impact. 11. The satellite recovery system of claim 10, wherein the longitudinal features in the strut comprise elongate notches. 12. The satellite recovery system of claim 1, wherein the plurality of walls are hingedly attached to the base portion with four-bar linkage systems that are configured such that the walls are displaced outwardly away from the base when they are pivoted to the deployed position. 13. The satellite recovery system of claim 12, wherein the plurality of walls are biased toward the deployed position. 14. The satellite recovery system of claim 13, wherein the walls interlock when in the non-deployed position such that when a first wall of the plurality of walls is in the non-deployed position the other walls of the plurality of walls are constrained from pivoting to the deployed position, and when the first wall is pivoted to the deployed position the other walls are not constrained from pivoting to the deployed position. 15. The satellite recovery system of claim 14, further comprising a remotely actuatable release mechanism that restrains the first wall from pivoting to the deployed position prior to actuation, and releases the first wall to pivot to the deployed position when the actuatable release mechanism is actuated. 16. The satellite recovery system of claim 1, wherein the deployable decelerator assembly comprises a flexible fabric panel. 17. The satellite recovery system of claim 16, wherein the flexible fabric panel is formed from a high-temperature-resistant fabric selected from a thermoset liquid crystalline polyoxazole. 18. The satellite recovery system of claim 16, wherein the flexible fabric panel is coated with an ablative material. 19. The satellite recovery system of claim 18, wherein the ablative material comprises a reinforced elastomer. 20. The satellite recovery system of claim 16, wherein the expandable torus comprises one of a silicone rubber and a polyimide. 21. The satellite recovery system of claim 16, wherein the flexible fabric panel further comprises an inwardly-extending portion such that the flexible fabric panel defines an outer annular region that contains the expandable torus. 22. The satellite recovery system of claim 1, further comprising means for stabilizing the satellite during reentry. 23. The satellite recovery system of claim 22, wherein the means for stabilizing the satellite during reentry comprises an inner ring member that encircles a distal portion of the satellite, and a plurality of straps that extend from the inner ring member to an outer portion of the decelerator assembly.