1. By: Josh Lukasak Attitude Group Lead Lunar Descent Phase Manager
Final Slides
By: Josh Lukasak
Attitude Group Lead
Lunar Descent Phase Manager

2. Necessity of Attitude Control
The above animation shows how attitude control is employed for main engine offset.
Attitude Control is an important facet of all mission phases
Lunar Injection: The space craft must be oriented in a fashion such that the solar panels and communication satellites are properly pointed.
Lunar Descent: The space craft must be oriented in a fashion such that on touchdown the Lander legs can rest gently on the lunar surface.
Additionally attitude control thrusters can be used for translational motion.

3. Lander Final Attitude Masses
Device
100g Payload
10kg Payload
Large Payload
Attitude Determination
7.1 kg
Thrusters Inert
1.08 kg
10.92 kg
Piping
2.57 kg
2 kg
6.56 kg
Attitude Prop
3.57 kg
5.53 kg
81.26 kg
The above Table gives all the final attitude control masses for the Lunar Descent Vehicle. These masses are for all three payload cases.

4. Initial Hopper Analysis for Large Payload
The hopper design for the 10 kg payload cases has considerable savings.
Lander/Rover total system mass of 278 kg
Hopper total system mass of kg
Reduction in two COM systems, one on the Lander and one on the rover, totaling over $200,000.
The most viable use for the hopper design seemed to be in the Falcon 9 large payload case.
Initial Scale Up Considerations for the Falcon 9
Falcon 9 Hopper Payload
897kg
Falcon 9 Rover Payload
1197kg
Falcon 9 Rover Size
300kg

5. Attitude Propellant Calculations
M=r x F
M is the induced moment
F is the force or thrust
r is the radius from the force to the center of mass
m is the time averaged mass
g is the gravitation constant of m/s^2
Isp is the specific impulse of Monopropellant Hydrogen Peroxide
L is the distance from the thruster to the center of mass