Design of a reconfigurable satellite constellation

Research output: Contribution to conferencePaper

2 Citations (Scopus)

Abstract

This paper provides a fully analytical method to describe a satellite constellation reconfiguration manoeuvre. By making use of low-thrust propulsion and exploiting the Earth’s natural perturbing forces it is possible to analytically describe the reconfiguration of a constellation, achieving a desired separation of both Right Ascension of Ascending Node (RAAN) and Argument of Latitude between satellites. An inherent trade-off exists between the time taken for a manoeuvre and the required ΔV, however the analytical solution presented here allows for a rapid visualisation of the trade-space and determination of the ideal transfer trajectory for a given mission. The general method presented can be applied across a range of scenarios, including constellation deployment and repurposing. The results show that for a scenario with an initial orbit semi-major axis of 6878.14km, and a desired final semi-major axis of 6778.14km it is possible to achieve a separation of 180° argument of latitude between a manoeuvring and a non-manoeuvring reference satellite in approximately 68 hours with a ΔV of 200m/s. To achieve the maximum possible RAAN separation of 90° with a ΔV of 200m/s requires a much longer time of over 218 days. Using two manoeuvring satellites with the same total manoeuvre ΔV was found to be more efficient only for short manoeuvre times. This is quantified and for the case considered it is found that using a 2-satellite manoeuvre is advantageous when changing the argument of latitude and when changing the RAAN <10° approximately. The ability to identify this turning point clearly is a distinct advantage of the analytical solution presented.
LanguageEnglish
PagesPaper IAC-15.C1.9.4
Number of pages9
Publication statusPublished - 12 Oct 2015
Event66th International Astronautical Congress, IAC2015 - Jerusalem, Israel
Duration: 12 Oct 201516 Oct 2015

Conference

Conference66th International Astronautical Congress, IAC2015
CountryIsrael
CityJerusalem
Period12/10/1516/10/15

Fingerprint

Satellites
Propulsion
Orbits
Visualization
Earth (planet)
Trajectories

Keywords

  • satellite constellation
  • reconfiguration technologies
  • low-thrust propulsion
  • RAAN
  • argument of latitude

Cite this

McGrath, C., & Macdonald, M. (2015). Design of a reconfigurable satellite constellation. Paper IAC-15.C1.9.4. Paper presented at 66th International Astronautical Congress, IAC2015, Jerusalem, Israel.
McGrath, Ciara ; Macdonald, Malcolm. / Design of a reconfigurable satellite constellation. Paper presented at 66th International Astronautical Congress, IAC2015, Jerusalem, Israel.9 p.
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McGrath, C & Macdonald, M 2015, 'Design of a reconfigurable satellite constellation' Paper presented at 66th International Astronautical Congress, IAC2015, Jerusalem, Israel, 12/10/15 - 16/10/15, pp. Paper IAC-15.C1.9.4.

Design of a reconfigurable satellite constellation. / McGrath, Ciara; Macdonald, Malcolm.

2015. Paper IAC-15.C1.9.4 Paper presented at 66th International Astronautical Congress, IAC2015, Jerusalem, Israel.

Research output: Contribution to conferencePaper

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N2 - This paper provides a fully analytical method to describe a satellite constellation reconfiguration manoeuvre. By making use of low-thrust propulsion and exploiting the Earth’s natural perturbing forces it is possible to analytically describe the reconfiguration of a constellation, achieving a desired separation of both Right Ascension of Ascending Node (RAAN) and Argument of Latitude between satellites. An inherent trade-off exists between the time taken for a manoeuvre and the required ΔV, however the analytical solution presented here allows for a rapid visualisation of the trade-space and determination of the ideal transfer trajectory for a given mission. The general method presented can be applied across a range of scenarios, including constellation deployment and repurposing. The results show that for a scenario with an initial orbit semi-major axis of 6878.14km, and a desired final semi-major axis of 6778.14km it is possible to achieve a separation of 180° argument of latitude between a manoeuvring and a non-manoeuvring reference satellite in approximately 68 hours with a ΔV of 200m/s. To achieve the maximum possible RAAN separation of 90° with a ΔV of 200m/s requires a much longer time of over 218 days. Using two manoeuvring satellites with the same total manoeuvre ΔV was found to be more efficient only for short manoeuvre times. This is quantified and for the case considered it is found that using a 2-satellite manoeuvre is advantageous when changing the argument of latitude and when changing the RAAN <10° approximately. The ability to identify this turning point clearly is a distinct advantage of the analytical solution presented.

AB - This paper provides a fully analytical method to describe a satellite constellation reconfiguration manoeuvre. By making use of low-thrust propulsion and exploiting the Earth’s natural perturbing forces it is possible to analytically describe the reconfiguration of a constellation, achieving a desired separation of both Right Ascension of Ascending Node (RAAN) and Argument of Latitude between satellites. An inherent trade-off exists between the time taken for a manoeuvre and the required ΔV, however the analytical solution presented here allows for a rapid visualisation of the trade-space and determination of the ideal transfer trajectory for a given mission. The general method presented can be applied across a range of scenarios, including constellation deployment and repurposing. The results show that for a scenario with an initial orbit semi-major axis of 6878.14km, and a desired final semi-major axis of 6778.14km it is possible to achieve a separation of 180° argument of latitude between a manoeuvring and a non-manoeuvring reference satellite in approximately 68 hours with a ΔV of 200m/s. To achieve the maximum possible RAAN separation of 90° with a ΔV of 200m/s requires a much longer time of over 218 days. Using two manoeuvring satellites with the same total manoeuvre ΔV was found to be more efficient only for short manoeuvre times. This is quantified and for the case considered it is found that using a 2-satellite manoeuvre is advantageous when changing the argument of latitude and when changing the RAAN <10° approximately. The ability to identify this turning point clearly is a distinct advantage of the analytical solution presented.

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McGrath C, Macdonald M. Design of a reconfigurable satellite constellation. 2015. Paper presented at 66th International Astronautical Congress, IAC2015, Jerusalem, Israel.