Abstract
Perturbation solutions are obtained in spherical coordinates for the spacecraft relative motion problem in the case of a slightly eccentric chief orbit. The use of spherical coordinates eliminates many of the secular terms in the Cartesian coordinate solution and extends the range of validity of these solutions to larger intrack separations. Both the chief eccentricity and the normalized separation are treated as order ϵ. Finally, the third order solution is used in the "double transformation" to improve the accuracy of the "approximate double transformation" Cartesian solution and as an alternative method to obtain the proposed third order spherical solution.
| Original language | English (US) |
|---|---|
| Title of host publication | Spaceflight Mechanics 2016 |
| Publisher | Univelt Inc. |
| Pages | 3455-3474 |
| Number of pages | 20 |
| Volume | 158 |
| ISBN (Print) | 9780877036333 |
| State | Published - 2016 |
| Event | 26th AAS/AIAA Space Flight Mechanics Meeting, 2016 - Napa, United States Duration: Feb 14 2016 → Feb 18 2016 |
Other
| Other | 26th AAS/AIAA Space Flight Mechanics Meeting, 2016 |
|---|---|
| Country | United States |
| City | Napa |
| Period | 2/14/16 → 2/18/16 |
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ASJC Scopus subject areas
- Aerospace Engineering
- Space and Planetary Science
Cite this
Spherical coordinate perturbation solutions to relative motion equations : Application to double transformation spherical solution. / Butcher, Eric; Lovell, T. Alan.
Spaceflight Mechanics 2016. Vol. 158 Univelt Inc., 2016. p. 3455-3474.Research output: Chapter in Book/Report/Conference proceeding › Conference contribution
}
TY - GEN
T1 - Spherical coordinate perturbation solutions to relative motion equations
T2 - Application to double transformation spherical solution
AU - Butcher, Eric
AU - Lovell, T. Alan
PY - 2016
Y1 - 2016
N2 - Perturbation solutions are obtained in spherical coordinates for the spacecraft relative motion problem in the case of a slightly eccentric chief orbit. The use of spherical coordinates eliminates many of the secular terms in the Cartesian coordinate solution and extends the range of validity of these solutions to larger intrack separations. Both the chief eccentricity and the normalized separation are treated as order ϵ. Finally, the third order solution is used in the "double transformation" to improve the accuracy of the "approximate double transformation" Cartesian solution and as an alternative method to obtain the proposed third order spherical solution.
AB - Perturbation solutions are obtained in spherical coordinates for the spacecraft relative motion problem in the case of a slightly eccentric chief orbit. The use of spherical coordinates eliminates many of the secular terms in the Cartesian coordinate solution and extends the range of validity of these solutions to larger intrack separations. Both the chief eccentricity and the normalized separation are treated as order ϵ. Finally, the third order solution is used in the "double transformation" to improve the accuracy of the "approximate double transformation" Cartesian solution and as an alternative method to obtain the proposed third order spherical solution.
UR - http://www.scopus.com/inward/record.url?scp=85007341040&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=85007341040&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:85007341040
SN - 9780877036333
VL - 158
SP - 3455
EP - 3474
BT - Spaceflight Mechanics 2016
PB - Univelt Inc.
ER -