1 . A method for creating an artificial reentry corridor, the method comprising steps of; deploying a plurality of orbital modules in series in a first orbital pathway, wherein the first orbital pathway is retrograde relative to a second orbital pathway of an orbital debris, wherein the first orbital pathway is parallel to the second orbital pathway; releasing a gas plume from each orbital module in the series of orbital modules, thereby creating an artificial reentry corridor consisting of the gas plume, wherein the gas plume expands over time such that the artificial reentry corridor overlaps with the second orbital pathway of the orbital debris; and allowing the orbital debris to pass through the artificial reentry corridor and thereby decelerate.
2 . The method as recited in claim 1 , wherein the gas plume is a spherical gas plume.
3 . The method as recited in claim 1 , wherein each orbital module in the plurality of orbital modules is spaced from adjacent orbital modules by a distance of at least 60 meters and less than or equal to 100 meters.
4 . The method as recited in claim 1 , wherein the step of releasing the gas plume releases at least 300 kg of a gas.
5 . The method as recited in claim 1 , wherein the step of releasing the gas plume releases between 300 kg and 1200 kg of a gas.
6 . The method as recited in claim 1 , wherein the step of releasing the gas plume releases at least 50 kg of a gas.
7 . The method as recited in claim 1 , wherein the step of releasing the gas plume releases between 50 kg and 60 kg of a gas.
8 . The method as recited in claim 7 , further comprising: waiting for the orbital debris to make an orbital pass around Earth; releasing a second gas plume from each orbital module in the series of orbital modules, thereby creating a second artificial reentry corridor consisting of the second gas plume, wherein the second gas plume expands over time such that the second artificial reentry corridor overlaps with the second orbital pathway of the orbital debris; allowing the orbital debris to pass through the second artificial reentry corridor and thereby decelerate.
9 . The method as recited in claim 8 , wherein the step of deploying deploys at least ten modules, each separated from adjacent modules by a distance of at least 60 meters and less than or equal to 100 meters.
10 . The method as recited in claim 1 , wherein the step of deploying deploys at least ten modules.
11 . The method as recited in claim 10 , wherein the step of releasing sequentially releases the gas plume from each orbital module.
12 . The method as recited in claim 1 , wherein the step of deploying deploys at least ten modules but seventy or fewer modules.
13 . The method as recited in claim 1 , wherein the step of releasing sequentially releases the gas plume from each orbital module.
14 . An orbital module comprising: a housing with at least one axis of symmetry; a storage tank disposed within the housing, the storage tank storing a fluid; a plurality of nozzles symmetrically disposed about the axis of symmetry, wherein each nozzle is fluidly connected to the storage tank; and a wireless receiver and a computer processor, the computer processor operatively configured to actuate a valve that releases the fluid from the storage tank thereby providing the fluid to each nozzle.
