Improving the accuracy of orbit lifetime analysis using enhanced general perturbations methods

Research output: Chapter in Book/Report/Conference proceedingConference contribution book

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Abstract

The general perturbations method for orbit lifetime analysis developed by the authors is improved by using spacecraft orbit decay tracking data to inform orbit lifetime predictions. This data is used to derive input parameters such as mass, and drag coefficient in order to make the method independent from error in these inputs, which can be a major source of error in orbit lifetime predictions. These derived inputs are then used to generate more accurate predictions while still maintaining the speed of the original method. The accuracy of the new method is validated against the authors' original method and historical data.

Original languageEnglish
Title of host publicationAAS/AIAA Spaceflight Mechanics Meeting 2016
EditorsMartin T. Ozimek, Renato Zanetti, Angela L. Bowes, Ryan P. Russell, Martin T. Ozimek
Pages2529-2542
Number of pages14
Volume158
Publication statusPublished - 17 Feb 2016
Event26th AAS/AIAA Space Flight Mechanics Meeting, 2016 - Napa, United States
Duration: 14 Feb 201618 Feb 2016

Conference

Conference26th AAS/AIAA Space Flight Mechanics Meeting, 2016
CountryUnited States
CityNapa
Period14/02/1618/02/16

Fingerprint

Orbits
perturbation
orbits
life (durability)
orbit decay
predictions
spacecraft orbits
drag coefficients
prediction
Drag coefficient
drag coefficient
Spacecraft
spacecraft
method
analysis

Keywords

  • general perturbations
  • orbit lifetime analysis
  • special perturbations
  • low Earth orbit
  • atmospheric drag
  • astronautics

Cite this

Kerr, E., & Macdonald, M. (2016). Improving the accuracy of orbit lifetime analysis using enhanced general perturbations methods. In M. T. Ozimek, R. Zanetti, A. L. Bowes, R. P. Russell, & M. T. Ozimek (Eds.), AAS/AIAA Spaceflight Mechanics Meeting 2016 (Vol. 158, pp. 2529-2542)
Kerr, Emma ; Macdonald, Malcolm. / Improving the accuracy of orbit lifetime analysis using enhanced general perturbations methods. AAS/AIAA Spaceflight Mechanics Meeting 2016. editor / Martin T. Ozimek ; Renato Zanetti ; Angela L. Bowes ; Ryan P. Russell ; Martin T. Ozimek. Vol. 158 2016. pp. 2529-2542
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abstract = "The general perturbations method for orbit lifetime analysis developed by the authors is improved by using spacecraft orbit decay tracking data to inform orbit lifetime predictions. This data is used to derive input parameters such as mass, and drag coefficient in order to make the method independent from error in these inputs, which can be a major source of error in orbit lifetime predictions. These derived inputs are then used to generate more accurate predictions while still maintaining the speed of the original method. The accuracy of the new method is validated against the authors' original method and historical data.",
keywords = "general perturbations, orbit lifetime analysis, special perturbations, low Earth orbit, atmospheric drag, astronautics",
author = "Emma Kerr and Malcolm Macdonald",
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Kerr, E & Macdonald, M 2016, Improving the accuracy of orbit lifetime analysis using enhanced general perturbations methods. in MT Ozimek, R Zanetti, AL Bowes, RP Russell & MT Ozimek (eds), AAS/AIAA Spaceflight Mechanics Meeting 2016. vol. 158, pp. 2529-2542, 26th AAS/AIAA Space Flight Mechanics Meeting, 2016, Napa, United States, 14/02/16.

Improving the accuracy of orbit lifetime analysis using enhanced general perturbations methods. / Kerr, Emma; Macdonald, Malcolm.

AAS/AIAA Spaceflight Mechanics Meeting 2016. ed. / Martin T. Ozimek; Renato Zanetti; Angela L. Bowes; Ryan P. Russell; Martin T. Ozimek. Vol. 158 2016. p. 2529-2542.

Research output: Chapter in Book/Report/Conference proceedingConference contribution book

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Kerr E, Macdonald M. Improving the accuracy of orbit lifetime analysis using enhanced general perturbations methods. In Ozimek MT, Zanetti R, Bowes AL, Russell RP, Ozimek MT, editors, AAS/AIAA Spaceflight Mechanics Meeting 2016. Vol. 158. 2016. p. 2529-2542