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TECHNICAL
INFO |
Lunar
CRater Observation and Sensing Satellite (LCROSS) |
Impactor Targeting
Figure 1 |
Figures 1 and 2 depict the trajectory that will be used to target the
LCROSS Centaur upper stage and Shepherding Spacecraft into a North or
South Pole crater.
The Lunar Gravity-Assist, Lunar Return Orbit (LGALRO) orbit can be
Figure 2 |
established for any LRO launch opportunity and the Centaur impact can
be timed to allow LRO and key ground observatories to observe the ejecta
plume generated by a high-velocity and steep incident angle impact (Figure
3). Dual viewing of the Centaur impact by the LCROSS Shepherding Spacecraft
and LRO can provide additional perspective and redundant data collection.
The science scenario and Shepherding Spacecraft propellant sizing inputs
assume that the Shepherding Spacecraft separates from the Centaur about
9 hours before impact and that a braking maneuver will slow the Shepherding
Spacecraft 4 minutes behind the Centaur. This allows 4 minutes of instrument
observations and real-time transmission before the Shepherding Spacecraft
itself impacts the same permanently shadowed crater, or if desired, one
adjacent to it.
Figure 3 |
Technical Information
Overview | Mission
Rationale | Spacecraft and System Description
| Instrumentation | Water
Detection | Targeting
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