Descent and Landing
Descent and landing sequence
Descent and landing operations would be based on the following
- Descent to a minimum-altitude circular orbit
(50x50 km), maintained for typically five revolutions.
De-orbit burns to descend to a 50x20 km orbit.
Descent Initiation (PDI), with a braking manoeuvre under inertial
guidance, from an initial altitude of about 20 km.
- 'High gate', at about 1 km altitude, the point at which
altitude and velocity information from the radar would start to
be used for navigation updating (e.g. landing point may be
changed on the basis of slope information from a three-beam radar
altimeter). Further visual acquisition of the landing target is
planned from here on.
- Hovering phase (max. 2 min) allows
final verification of landing site from the ground (obstacle
EuroMoon 2000 (BR-122).
Published December 1996.
Developed by ESA-ESRIN ID/D.