Week 4
Project Timeline
AAE450 Spring 2009
[Solomon Westerman] [PM]
Website Updates
 MDR Posted
 Folder for Mass/Volume/Power budgets
– Managed by STRC/THM
– Make sure to get component parameters to
your GL by Wed. evening so this budget can
be in presentation
AAE450 Spring 2009
[Solomon Westerman] [PM]
Today
 List major design characteristics
– Hard/Soft landing (Trajectory)
– Locomotion type
– Spin stabilization (OTV and/or Lander)
– TLI trajectory type
– Payload to lunar surface
 Discuss arbitrary mass payload
– Scalability
– Work forward from launch vehicle
AAE450 Spring 2009
Design (Week)
X0 (2)
X1 (3,4)
X2 (4)
X3 (4)
X4 (4)
Main Purpose
Initial design
Refined
GLXP
design
Scalability
analysis
Effect of firm
landing
Effect of spin
stabilization
Landing
Soft (<10g’s)
Soft (<10g’s) Soft (<10g’s)
Firm
(<100g’s)
TBD
Locomotion
Rover
Rover
Rover
TBD
TBD
TLI
Hohmann
(cryo)
Spiral (EP)
Spiral (EP)
Spiral (EP)
Spiral (EP)
Stabilization
3-axis
3-axis
3-axis
3-axis
Spin OTV or
lander
Mass to Lunar
surface
~250 kg
~ 150 kg?
As large as
X1 will allow
~ 150 kg?
~ 150 kg?
AAE450 Spring 2009