AAE450 Spring 2009 Lunar Descent Final Numbers Josh Lukasak Attitude Group Lead Lunar Decent Phase Lead 03/12/09 [Josh Lukasak] [Attitude] (1)

AAE450 Spring Kilogram Payload Breakdown  The 10 kg payload architecture is a soft landing with the main Lunar Lander engine. At this point the 500 meter locomotion will occur using one 200 N hybrid thruster.  Mass Breakdown –Wet Mass in LLO (w/ payload) – kg –Mass on Lunar Surface (Pre-Hop) – kg –Dry Mass on Lunar Surface (Post-Hop) – kg [Josh Lukasak] [Attitude] (2)

AAE450 Spring 2009 Arbitrary Payload [Josh Lukasak] [Attitude] (3)  The arbitrary payload mission architecture involves a descent trajectory that hovers over the lunar surface and translates the 500 meters at a set height before finally touching down. Given 3542 kg deliverable to LLO.  Mass Breakdown –Wet Mass in LLO (w/o payload) – kg –Dry Mass of the Lander – kg –Deliverable Payload – kg

AAE450 Spring 2009  Back Up Slides [Josh Lukasak] [Attitude Group Lead] (4)

AAE450 Spring Gram Payload  The 100 gram payload mission architecture for the Lunar Lander involves the delivering of two roving balls to the lunar surface.  Mass Breakdown –Wet Mass in LLO (w/ payload) kg –Dry Mass on Lunar Surface – kg [Josh Lukasak] [Attitude Group Lead] (5)

AAE450 Spring 2009 Lunar Lander Attitude Control Thruster Configuration [Josh Lukasak] [Attitude Group Lead] (6) b3b3 b2b2

AAE450 Spring 2009 Lander Final Attitude Masses Device100 g Payload10 kg PayloadArbitrary Payload Attitude Determination 7.1 kg Thrusters Inert1.08 kg kg Piping2.57 kg2 kg6.56 kg Attitude Prop3.57 kg5.53 kg81.26 kg [Josh Lukasak] [Attitude] (7)