Estimation of mean orbital elements with unknown low-thrust acceleration

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

Abstract

Space Situational Awareness (SSA) has been recognized to be important for the safe space activities including these problems. As low-thrust propulsion technology becomes increasingly popular, SSA for low-thrust spacecraft may become an area of increasing interest. More frequently use of low-thrust propulsion to place satellites in orbit create more opportunities for collisions and radio frequency interference as these spacecraft travel slowly through altitude ranges. The purpose of this paper is to develop a method for estimation of the mean orbital elements for low-thrust spacecraft. To overcome the instability of the estimation problem with low-thrust acceleration, we estimate the mean elements instead of osculating elements. By use of the averaging technique, Hudson and Scheeres (2009) proposed an analytical model of secular variations of orbital elements under thrust acceleration. The resulting averaged equation has a nice property in which only finite number of Fourier coefficients of the thrust acceleration appear because of the orthogonality of the trigonometric function. Based on the nonlinear state equation representation for the extended state variable which include not only orbital elements but also unknown Fourier coefficients, mean orbital elements and thrust history are estimated from observation data of mean orbital elements. Moreover, the mapping from mean to osculating elements is derived which can be replaced by a measurement equation. Proposed method is demonstrated through numerical simulations

Original languageEnglish
Title of host publication65th International Astronautical Congress 2014, IAC 2014: Our World Needs Space
PublisherInternational Astronautical Federation, IAF
Pages4645-4655
Number of pages11
Volume7
ISBN (Electronic)9781634399869
Publication statusPublished - 2014
Event65th International Astronautical Congress 2014: Our World Needs Space, IAC 2014 - Toronto, Canada
Duration: Sep 29 2014Oct 3 2014

Other

Other65th International Astronautical Congress 2014: Our World Needs Space, IAC 2014
CountryCanada
CityToronto
Period9/29/1410/3/14

Fingerprint

low thrust
orbital elements
Spacecraft
thrust
low thrust propulsion
Propulsion
situational awareness
spacecraft
Analytical models
radio frequency interference
Orbits
trigonometric functions
secular variations
Satellites
orthogonality
coefficients
travel
Computer simulation
equations of state
histories

All Science Journal Classification (ASJC) codes

  • Space and Planetary Science
  • Aerospace Engineering
  • Astronomy and Astrophysics

Cite this

Bando, M., Date, N., & Hokamoto, S. (2014). Estimation of mean orbital elements with unknown low-thrust acceleration. In 65th International Astronautical Congress 2014, IAC 2014: Our World Needs Space (Vol. 7, pp. 4645-4655). International Astronautical Federation, IAF.

Estimation of mean orbital elements with unknown low-thrust acceleration. / Bando, Mai; Date, Naoki; Hokamoto, Shinji.

65th International Astronautical Congress 2014, IAC 2014: Our World Needs Space. Vol. 7 International Astronautical Federation, IAF, 2014. p. 4645-4655.

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

Bando, M, Date, N & Hokamoto, S 2014, Estimation of mean orbital elements with unknown low-thrust acceleration. in 65th International Astronautical Congress 2014, IAC 2014: Our World Needs Space. vol. 7, International Astronautical Federation, IAF, pp. 4645-4655, 65th International Astronautical Congress 2014: Our World Needs Space, IAC 2014, Toronto, Canada, 9/29/14.
Bando M, Date N, Hokamoto S. Estimation of mean orbital elements with unknown low-thrust acceleration. In 65th International Astronautical Congress 2014, IAC 2014: Our World Needs Space. Vol. 7. International Astronautical Federation, IAF. 2014. p. 4645-4655
Bando, Mai ; Date, Naoki ; Hokamoto, Shinji. / Estimation of mean orbital elements with unknown low-thrust acceleration. 65th International Astronautical Congress 2014, IAC 2014: Our World Needs Space. Vol. 7 International Astronautical Federation, IAF, 2014. pp. 4645-4655
@inproceedings{08660e1061d14ae09245957aaef6e421,
title = "Estimation of mean orbital elements with unknown low-thrust acceleration",
abstract = "Space Situational Awareness (SSA) has been recognized to be important for the safe space activities including these problems. As low-thrust propulsion technology becomes increasingly popular, SSA for low-thrust spacecraft may become an area of increasing interest. More frequently use of low-thrust propulsion to place satellites in orbit create more opportunities for collisions and radio frequency interference as these spacecraft travel slowly through altitude ranges. The purpose of this paper is to develop a method for estimation of the mean orbital elements for low-thrust spacecraft. To overcome the instability of the estimation problem with low-thrust acceleration, we estimate the mean elements instead of osculating elements. By use of the averaging technique, Hudson and Scheeres (2009) proposed an analytical model of secular variations of orbital elements under thrust acceleration. The resulting averaged equation has a nice property in which only finite number of Fourier coefficients of the thrust acceleration appear because of the orthogonality of the trigonometric function. Based on the nonlinear state equation representation for the extended state variable which include not only orbital elements but also unknown Fourier coefficients, mean orbital elements and thrust history are estimated from observation data of mean orbital elements. Moreover, the mapping from mean to osculating elements is derived which can be replaced by a measurement equation. Proposed method is demonstrated through numerical simulations",
author = "Mai Bando and Naoki Date and Shinji Hokamoto",
year = "2014",
language = "English",
volume = "7",
pages = "4645--4655",
booktitle = "65th International Astronautical Congress 2014, IAC 2014: Our World Needs Space",
publisher = "International Astronautical Federation, IAF",

}

TY - GEN

T1 - Estimation of mean orbital elements with unknown low-thrust acceleration

AU - Bando, Mai

AU - Date, Naoki

AU - Hokamoto, Shinji

PY - 2014

Y1 - 2014

N2 - Space Situational Awareness (SSA) has been recognized to be important for the safe space activities including these problems. As low-thrust propulsion technology becomes increasingly popular, SSA for low-thrust spacecraft may become an area of increasing interest. More frequently use of low-thrust propulsion to place satellites in orbit create more opportunities for collisions and radio frequency interference as these spacecraft travel slowly through altitude ranges. The purpose of this paper is to develop a method for estimation of the mean orbital elements for low-thrust spacecraft. To overcome the instability of the estimation problem with low-thrust acceleration, we estimate the mean elements instead of osculating elements. By use of the averaging technique, Hudson and Scheeres (2009) proposed an analytical model of secular variations of orbital elements under thrust acceleration. The resulting averaged equation has a nice property in which only finite number of Fourier coefficients of the thrust acceleration appear because of the orthogonality of the trigonometric function. Based on the nonlinear state equation representation for the extended state variable which include not only orbital elements but also unknown Fourier coefficients, mean orbital elements and thrust history are estimated from observation data of mean orbital elements. Moreover, the mapping from mean to osculating elements is derived which can be replaced by a measurement equation. Proposed method is demonstrated through numerical simulations

AB - Space Situational Awareness (SSA) has been recognized to be important for the safe space activities including these problems. As low-thrust propulsion technology becomes increasingly popular, SSA for low-thrust spacecraft may become an area of increasing interest. More frequently use of low-thrust propulsion to place satellites in orbit create more opportunities for collisions and radio frequency interference as these spacecraft travel slowly through altitude ranges. The purpose of this paper is to develop a method for estimation of the mean orbital elements for low-thrust spacecraft. To overcome the instability of the estimation problem with low-thrust acceleration, we estimate the mean elements instead of osculating elements. By use of the averaging technique, Hudson and Scheeres (2009) proposed an analytical model of secular variations of orbital elements under thrust acceleration. The resulting averaged equation has a nice property in which only finite number of Fourier coefficients of the thrust acceleration appear because of the orthogonality of the trigonometric function. Based on the nonlinear state equation representation for the extended state variable which include not only orbital elements but also unknown Fourier coefficients, mean orbital elements and thrust history are estimated from observation data of mean orbital elements. Moreover, the mapping from mean to osculating elements is derived which can be replaced by a measurement equation. Proposed method is demonstrated through numerical simulations

UR - http://www.scopus.com/inward/record.url?scp=84937718628&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=84937718628&partnerID=8YFLogxK

M3 - Conference contribution

VL - 7

SP - 4645

EP - 4655

BT - 65th International Astronautical Congress 2014, IAC 2014: Our World Needs Space

PB - International Astronautical Federation, IAF

ER -