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SMC-S-022
END-OF-LIFE DISPOSAL OF SATELLITES IN LOW-EARTH ORBIT
Year: 2010
Abstract: According to the U.S. Government Orbital Debris Standard Practices, a spacecraft or upper stage with perigee altitude below 2000 km in its final mission orbit may be disposed of by using an atmospheric reentry option. The guideline for atmospheric reentry is stated as follows:
"Leave the structure in an orbit in which, using conservative projections for solar activity, atmospheric drag will limit the lifetime to no longer than 25 years after completion of mission. If drag enhancement devices are to be used to reduce the orbit lifetime, it should be demonstrated that such devices will significantly reduce the area-time product of the system or will not cause spacecraft or large debris to fragment if a collision occurs while the system is decaying from orbit."
The Inter-Agency Space Debris Coordination Committee (IADC) Space Debris Mitigation Guidelines state:
"Whenever possible space systems that are terminating their operational phases in orbits that pass through the LEO region, or have the potential to interfere with the LEO region, should be de-orbited (direct re-entry is preferred) or where appropriate maneuvered into an orbit with a reduced lifetime. Retrieval is also a disposal option.
A space system should be left in an orbit in which, using an accepted nominal projection for solar activity, atmospheric drag will limit the orbital lifetime after completion of operations. A study on the effect of post-mission orbital lifetime limitation on collision rate and debris population growth has been performed by the IADC. This IADC and some other studies and a number of existing national guidelines have found 25 years to be a reasonable and appropriate lifetime limit. If a space system is to be disposed of by re-entry into the atmosphere, debris that survives to reach the surface of the Earth should not pose an undue risk to people or property. This may be accomplished by limiting the amount of surviving debris or confining the debris to uninhabited regions, such as broad ocean areas. Also, ground environmental pollution, caused by radioactive substances, toxic substances or any other environmental pollutants resulting from on-board articles, should be prevented or minimized in order to be accepted as permissible.
In the case of a controlled re-entry of a space system, the operator of the system should inform the relevant air traffic and maritime traffic authorities of the re-entry time and trajectory and the associated ground area."
This report specifies requirements for (1) planning for disposal of satellites operating in low Earth orbits with perigee altitude below 2000 km, (2) selecting the final disposal orbits whose perigee altitude is low enough to ensure a natural decay due to atmospheric drag within 25 years, (3) executing the disposal maneuver successfully, and (4) depleting all energy sources onboard the vehicle prior to end-of-life to minimize the possibility of a debris-producing event. Techniques for planning and determining the final disposal orbit are provided, considering current internationally accepted guidelines and operational best practices.
"Leave the structure in an orbit in which, using conservative projections for solar activity, atmospheric drag will limit the lifetime to no longer than 25 years after completion of mission. If drag enhancement devices are to be used to reduce the orbit lifetime, it should be demonstrated that such devices will significantly reduce the area-time product of the system or will not cause spacecraft or large debris to fragment if a collision occurs while the system is decaying from orbit."
The Inter-Agency Space Debris Coordination Committee (IADC) Space Debris Mitigation Guidelines state:
"Whenever possible space systems that are terminating their operational phases in orbits that pass through the LEO region, or have the potential to interfere with the LEO region, should be de-orbited (direct re-entry is preferred) or where appropriate maneuvered into an orbit with a reduced lifetime. Retrieval is also a disposal option.
A space system should be left in an orbit in which, using an accepted nominal projection for solar activity, atmospheric drag will limit the orbital lifetime after completion of operations. A study on the effect of post-mission orbital lifetime limitation on collision rate and debris population growth has been performed by the IADC. This IADC and some other studies and a number of existing national guidelines have found 25 years to be a reasonable and appropriate lifetime limit. If a space system is to be disposed of by re-entry into the atmosphere, debris that survives to reach the surface of the Earth should not pose an undue risk to people or property. This may be accomplished by limiting the amount of surviving debris or confining the debris to uninhabited regions, such as broad ocean areas. Also, ground environmental pollution, caused by radioactive substances, toxic substances or any other environmental pollutants resulting from on-board articles, should be prevented or minimized in order to be accepted as permissible.
In the case of a controlled re-entry of a space system, the operator of the system should inform the relevant air traffic and maritime traffic authorities of the re-entry time and trajectory and the associated ground area."
This report specifies requirements for (1) planning for disposal of satellites operating in low Earth orbits with perigee altitude below 2000 km, (2) selecting the final disposal orbits whose perigee altitude is low enough to ensure a natural decay due to atmospheric drag within 25 years, (3) executing the disposal maneuver successfully, and (4) depleting all energy sources onboard the vehicle prior to end-of-life to minimize the possibility of a debris-producing event. Techniques for planning and determining the final disposal orbit are provided, considering current internationally accepted guidelines and operational best practices.
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| contributor author | AIR FORCE - 02 - Air Force Network Integration Center (AFNIC) | |
| date accessioned | 2017-09-04T17:03:34Z | |
| date available | 2017-09-04T17:03:34Z | |
| date copyright | 03/19/2010 | |
| date issued | 2010 | |
| identifier other | BYASKEAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std/handle/yse/127190 | |
| description abstract | According to the U.S. Government Orbital Debris Standard Practices, a spacecraft or upper stage with perigee altitude below 2000 km in its final mission orbit may be disposed of by using an atmospheric reentry option. The guideline for atmospheric reentry is stated as follows: "Leave the structure in an orbit in which, using conservative projections for solar activity, atmospheric drag will limit the lifetime to no longer than 25 years after completion of mission. If drag enhancement devices are to be used to reduce the orbit lifetime, it should be demonstrated that such devices will significantly reduce the area-time product of the system or will not cause spacecraft or large debris to fragment if a collision occurs while the system is decaying from orbit." The Inter-Agency Space Debris Coordination Committee (IADC) Space Debris Mitigation Guidelines state: "Whenever possible space systems that are terminating their operational phases in orbits that pass through the LEO region, or have the potential to interfere with the LEO region, should be de-orbited (direct re-entry is preferred) or where appropriate maneuvered into an orbit with a reduced lifetime. Retrieval is also a disposal option. A space system should be left in an orbit in which, using an accepted nominal projection for solar activity, atmospheric drag will limit the orbital lifetime after completion of operations. A study on the effect of post-mission orbital lifetime limitation on collision rate and debris population growth has been performed by the IADC. This IADC and some other studies and a number of existing national guidelines have found 25 years to be a reasonable and appropriate lifetime limit. If a space system is to be disposed of by re-entry into the atmosphere, debris that survives to reach the surface of the Earth should not pose an undue risk to people or property. This may be accomplished by limiting the amount of surviving debris or confining the debris to uninhabited regions, such as broad ocean areas. Also, ground environmental pollution, caused by radioactive substances, toxic substances or any other environmental pollutants resulting from on-board articles, should be prevented or minimized in order to be accepted as permissible. In the case of a controlled re-entry of a space system, the operator of the system should inform the relevant air traffic and maritime traffic authorities of the re-entry time and trajectory and the associated ground area." This report specifies requirements for (1) planning for disposal of satellites operating in low Earth orbits with perigee altitude below 2000 km, (2) selecting the final disposal orbits whose perigee altitude is low enough to ensure a natural decay due to atmospheric drag within 25 years, (3) executing the disposal maneuver successfully, and (4) depleting all energy sources onboard the vehicle prior to end-of-life to minimize the possibility of a debris-producing event. Techniques for planning and determining the final disposal orbit are provided, considering current internationally accepted guidelines and operational best practices. | |
| language | English | |
| title | SMC-S-022 | num |
| title | END-OF-LIFE DISPOSAL OF SATELLITES IN LOW-EARTH ORBIT | en |
| type | standard | |
| page | 47 | |
| status | Active | |
| tree | AIR FORCE - 02 - Air Force Network Integration Center (AFNIC):;2010 | |
| contenttype | fulltext |