2026-09-20T07:56:25Zhttps://dspace.mit.edu/server/oai/requestoai:dspace.mit.edu:1721.1/467972022-01-13T07:54:11Zcom_1721.1_7582com_1721.1_7581col_1721.1_131023
Jeffrey A. Hoffman.
Waswa, M. B. Peter (Peter Moses Bweya)
Massachusetts Institute of Technology. Dept. of Aeronautics and Astronautics.
Massachusetts Institute of Technology. Department of Aeronautics and Astronautics
2009-09-24T20:47:32Z
2009-09-24T20:47:32Z
2008
2009
http://hdl.handle.net/1721.1/46797
429048142
Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2009.
This electronic version was submitted by the student author. The certified thesis is available in the Institute Archives and Special Collections.
Includes bibliographical references (p. 102-106) and index.
Uncontrolled reentry into the Earth atmosphere by LEO space missions whilst complying with stipulated NASA Earth atmospheric reentry requirements is a vital endeavor for the space community to pursue. An uncontrolled reentry mission that completely ablates does not require a provision for integrated controlled reentry capability. Consequently, not only will such a mission design be relatively simpler and cheaper, but also mission unavailability risk due to a controlled reentry subsystem failure is eliminated, which improves mission on-orbit reliability and robustness. Intentionally re-designing the mission such that the spacecraft components ablate (demise) during uncontrolled reentry post-mission disposal is referred to as Design-for-Demise (DfD). Re-designing spacecraft parts to demise guarantees adherence to NASA reentry requirements that dictate the risk of human casualty anywhere on Earth due to a reentering debris with KE =/> 15J be less than 1:10,000 (0.0001). NASA sanctioned missions have traditionally ad- dressed this requirement by integrating a controlled reentry provision. However, momentum is building for a new paradigm shift towards designing reentry missions to demise instead. Therefore, this thesis proposes a DfD decision making methodology; DfD implementation and execution strategy throughout the LEO mission life-cycle; scrutinizes reentry analysis software tools and uses NASA Debris Analysis Software (DAS) to demonstrate the reentry demisability analysis process; proposes methods to identify and redesign hardware parts for demise; and finally considers the HETE-2 mission as a DfD demisability case study. Reentry analysis show HETE-2 mission to be compliant with NASA uncontrolled atmospheric reentry requirements.
by Waswa M.B. Peter.
S.M.
109 p.
eng
Massachusetts Institute of Technology
M.I.T. theses are protected by
copyright. They may be viewed from this source for any purpose, but
reproduction or distribution in any format is prohibited without written
permission. See provided URL for inquiries about permission.
http://dspace.mit.edu/handle/1721.1/7582
Aeronautics and Astronautics.
Spacecraft design-for-demise strategy, analysis and impact on low earth orbit space missions
Thesis
application/pdf
Publication
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unknown
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<Abstract>Uncontrolled reentry into the Earth atmosphere by LEO space missions whilst complying with stipulated NASA Earth atmospheric reentry requirements is a vital endeavor for the space community to pursue. An uncontrolled reentry mission that completely ablates does not require a provision for integrated controlled reentry capability. Consequently, not only will such a mission design be relatively simpler and cheaper, but also mission unavailability risk due to a controlled reentry subsystem failure is eliminated, which improves mission on-orbit reliability and robustness. Intentionally re-designing the mission such that the spacecraft components ablate (demise) during uncontrolled reentry post-mission disposal is referred to as Design-for-Demise (DfD). Re-designing spacecraft parts to demise guarantees adherence to NASA reentry requirements that dictate the risk of human casualty anywhere on Earth due to a reentering debris with KE =/> 15J be less than 1:10,000 (0.0001). NASA sanctioned missions have traditionally ad- dressed this requirement by integrating a controlled reentry provision. However, momentum is building for a new paradigm shift towards designing reentry missions to demise instead. Therefore, this thesis proposes a DfD decision making methodology; DfD implementation and execution strategy throughout the LEO mission life-cycle; scrutinizes reentry analysis software tools and uses NASA Debris Analysis Software (DAS) to demonstrate the reentry demisability analysis process; proposes methods to identify and redesign hardware parts for demise; and finally considers the HETE-2 mission as a DfD demisability case study. Reentry analysis show HETE-2 mission to be compliant with NASA uncontrolled atmospheric reentry requirements.</Abstract>
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