AAE450 Spring 2009 Kelly Leffel 2/5/09 Structures and Thermal Lunar Descent Phase Kelly Leffel Structures and Thermal 1

AAE450 Spring 2009 Mass – Volume  Lander total wet mass = 275 kg  Current available volume = 2.74 cubic meters  Current volume of equipment =.26 cubic meters Kelly Leffel Structures and Thermal 2

AAE450 Spring 2009 Lander Model and Moments of Inertia  Ixx=Iyy = 271 kg-m^2  Izz = 464 kg-m^2 Kelly Leffel Structures and Thermal 3

AAE450 Spring 2009 BACK-UP SLIDES Kelly Leffel Structures and Thermal 4 Division PartMass (kg)Power (W)Size (m) Power Batteries23.5 x.5 x.25 Solar Panels7 1 (dia) x.1 Communications CPU x.33 x.032 Camcorder0.38 Receiver x.13 x.022 Transmitter x.135 x.022 Antenna x.1 x.5 Motorized Ant x 0.21 x 0.21 Propulsion Structure42- Propellant diameter

AAE450 Spring 2009 Kelly Leffel Structures and Thermal 5 Attitude Thrusters2.5.3 x.1 (dia) star sensor x.032 x.016 Rover 45.4 x.4 x.4 Structure frame45 thermal control TotalLander Mass – Volume Continued

AAE450 Spring 2009 Volume Equations  Surface Area(SA) = pi*R*S + pi*R^2 – pi*r*s  Volume(V) = 1/3 * pi * R^2 * H – 1/3 *pi*r^2  Available Volume = V – SA*thickness of aluminum Kelly Leffel Structures and Thermal 6

AAE450 Spring 2009 Moments of Inertia Ixx = Iyy = m/4 * (1.5 *r ^2 + h^2) = 271 kg – m^2 Izz = 3 *m*r^2/4 = 464 kg – m^2 Ixy = Iyz = 3*m*r^2/8 = -232 kg – m^2 Ixz=Izx=Iyz=Izy = -90 kg-m^2 Kelly Leffel Structures and Thermal 7