Stabilization of unstable space debris
Disclosed herein, in certain embodiments, is a method of altering the stability of unstable space debris. In some embodiments, the method further comprises changing the orbit of the unstable space debris.
1. A satellite for stabilizing unstable space debris, comprising (a) routine systems and subsystems for operation of the satellite, and (b) at least a first and second nozzle configured to (i) generate a plurality of gas plume pulses from a gas, wherein the plurality of gas plume pulses have sufficient force to dampen rotational momentum about one or more axes of rotation of unstable space debris, and (ii) specifically target the plurality of gas plume pulses to at least a first target point and a second target point located on or near mutually orthogonal axes centered at center of mass of the unstable space debris.
2. The satellite of claim 1 , wherein the plurality of gas plume pulses are collimated, convergent, divergent, or a combination thereof.
3. The satellite of claim 1 , further comprising an active control system for maintaining position and attitude of the satellite.
4. The satellite of claim 1 , further comprising a laser tracking system, a radar tracking system, an optical tracking system, or a combination thereof.
5. The satellite of claim 1 , further comprising a computer module for calculating strength, duration, timing, and number of the gas plume pulses necessary to stabilize the unstable space debris.
6. The satellite of claim 5 , wherein the computer module is an on-board computer module, a ground-based computer module or a combination thereof.
7. The satellite of claim 1 , wherein the gas is compressed gas.
8. The satellite of claim 7 , wherein the gas is hydrogen (H 2 ), helium (He 2 ), xenon (Xe), argon (Ar), neon (Ne), freon, gaseous ammonia, or nitrogen (N 2 ).
9. The satellite of claim 1 , wherein the gas is the product of vaporization of a liquefied gas, combustion of an oxidizer and a propellant, exothermic decomposition of a monopropellant, or any combination thereof.
10. The satellite of claim 9 , wherein the oxidizer is selected from liquid oxygen (LOX), gaseous oxygen (GOX), fluorine (F 2 ), oxygen difluoride (OF 2 ), Tetrafluorohydrazine (N 2 F 2 ), or Chlorine pentafluoride (ClF 5 ); and a propellant is selected from hydrogen (H2), Kerosene products such as Rocket Propellant 1 (RP-1) and Rocket Propellant 2 (RP-2), Methane (CH4), or Monomethylhydrazine (MMH).
11. The satellite of claim 9 , wherein the monopropellant is hydrazine (N 2 H 4 ) or hydrogen peroxide (H 2 O 2 ).
12. The satellite of claim 1 , wherein the gas is energized and accelerated by electrothermal, electrostatic, or electromagnetic means.
13. The satellite of claim 12 , wherein the gas is selected from hydrogen (H 2 ), helium (He 2 ), xenon (Xe), argon (Ar), neon (Ne), nitrogen (N 2 ), ionized cesium (Cs), or ionized mercury (Hg).