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Structures and Thermal Analysis for Lunar Descent: Mass, Volume, and Inertia Calculations

This document provides a comprehensive analysis of the structures and thermal aspects regarding the lunar lander's descent phase. It details the total wet mass of the lander at 275 kg, available volume of 2.74 cubic meters, and current equipment volume. Significant calculations include moments of inertia (Ixx, Iyy, Izz) at 271 kg-m² and 464 kg-m² respectively, and the equations for volume and surface area based on geometric parameters. These insights are crucial for optimizing lander design and performance during lunar missions.

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Structures and Thermal Analysis for Lunar Descent: Mass, Volume, and Inertia Calculations

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  1. Kelly Leffel2/5/09 Structures and Thermal Lunar Descent Phase 1 Kelly Leffel Structures and Thermal

  2. 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

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

  4. BACK-UP SLIDES Kelly Leffel Structures and Thermal

  5. Mass – Volume Continued 5 Kelly Leffel Structures and Thermal

  6. Volume Equations Kelly Leffel Structures and Thermal 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

  7. 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 7 Kelly Leffel Structures and Thermal

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