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A High Earth, Lunar Resonant Orbit for Lower Cost Space Science Missions | | Joseph W. Gangestad
; Gregory A. Henning
; Randy R. Persinger
; George R. Ricker
; | | Date: |
Sat, 22 Jun 2013 16:23:49 GMT (1883kb) | | Abstract: | NASA astrophysics robotic science missions often require continuous,
unobstructed fields-of view (FOV) of the celestial sphere and orbits that
provide stable thermal- and attitude-control environments. To date, the more
expensive "flagship" missions use the second Earth/Sun Lagrange point (L2)
approximately 1.5 million km from the Earth outside the orbit of the Moon or a
"drift away" orbit to distances >10 million km. A High Earth Orbit (HEO) offers
similar advantages with regard to continuous, unobstructed FOV and a thermally
stable environment with minimal station-keeping requirements. The "P/2-HEO," an
orbit in 2:1 resonance with the orbit of the Moon, also provides the
opportunity for data downlink at orbit perigee distances close to the Earth
allowing for lower-cost communications systems. The P/2-HEO oscillates on the
order of 12 years and trades orbit eccentricity for orbit inclination. This
orbit variability can be selected for optimum spacecraft performance by proper
choice of the conditions using a lunar flyby for gravitational assist. The
lunar flyby and the shorter distance for science data downlink offer lower cost
astrophysics missions the advantages of the more expensive L2 or "drift away"
orbits. | | Source: | arXiv, 1306.5333 | | Services: | Forum | Review | PDF | Favorites | |
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