1. AAE450 Spring 2009 Lunar Capture Altitude Mass to LLO for Arbitrary Time to Rotate Lander During Descent Camera/Dust Removal [Kara Akgulian] [Mission Ops] March 12, 2009 1

2. AAE450 Spring 2009 [Kara Akgulian] [Mission Ops] 2 Lunar Capture Orbit Altitude 100g and 10kg using Falcon 9 Arbitrary using Falcon 9 Circ Orbit (km)50453525 Total Prop Used (kg)78.9278.7778.4778.16 Savings from 50km (kg) 0.150.450.76 Orbit StabilityStable Circ Orbit (km)50453525 Total Prop Used (kg)1420.601417.901412.501406.90 Savings from 50km (kg) 2.708.101.01 Orbit StabilityStable Recommend circular orbit of 25 km. This will optimize mass savings. Any lower altitude and there will be problems with lunar terrain. Note: Prop mass calculated using John’s Descent Code. Stability Proven using Levi/Drew TLI Code

3. AAE450 Spring 2009 [Kara Akgulian] [Mission Ops] 3 Mass to LLO (Arbitrary) Values Used 400 km Earth Orbit to 25 km Lunar Orbit Thrust of 2118 mN Results Mass Flow Rate = 93.5 mg/s Payload to LLO = 3542 kg Price to LLO = 23864 $/kg Time to Rotate Lander (100g/10kg) Values Used 13.3 N Lander Thrusters Results 3.1534 seconds Note: Values iterated using Brad and Drew/Levi codes until values converged Note: Integrated into John’s Lunar Descent Code

4. AAE450 Spring 2009 [Kara Akgulian] [Mission Ops] 4 Orbit Altitude (km)Stability 208 days 2515 days 5056 days 100168 days 150431 days 2006.65 years 250>15 years Reference: AAE 450 Project Spring 2006. Project Infinity, pg 129 Example: 25 km Altitude Capture Orbit Starts at rx_in=3.8148 x 10 5 ry_out= 3.8275 x 10 5 Difference in position is 1260 km during 15 days, from the chart to the left the orbit is stable because for orbit of 250 km stability is for 15 years. Showing Orbit Stability From Levi/Drew Code