Final Slides

By: Kara AkgulianMission Ops

Locomotion Phase

1

Selecting the Capture Orbit

2

•Lunar Capture Orbit Altitude• 100g and 10kg using Falcon 9

• Arbitrary using Falcon 9

Circular Orbit (km) 50 45 35 25

Total Prop Used (kg) 78.92 78.77 78.47 78.16

Savings from 50km (kg) 0.15 0.45 0.76

Orbit Stability Stable Stable Stable Stable

Circular Orbit (km) 50 45 35 25

Total Prop Used (kg) 1420.60 1417.90 1412.50 1406.90

Savings from 50km (kg) 2.70 8.10 1.01

Orbit Stability Stable Stable Stable Stable

This will optimize mass savings. Any lower altitude and there is the possibility of crashing into high peaks in the Lunar terrain.

Landing Site

3

Mare CognitumSoutheast of Apollo

12 Landing

Trajectory Analysis for Large Payload

4

Parameter Value

Payload Mass (kg) 3542

Thrust (mN) 2118

Mass Flow Rate (mg/s) 93.5

Earth Phase Angle (deg) 216

Moon Phase Angle (deg) 270

Parking Orbit Altitude (km) 400

Capture Orbit Altitude (km) 25

Initial Mass (kg) 9953

Flight Time (days) 365

Space Ball Components

5

Parameter Value

Size 38 mm2

Mass 0.1 kg

Motor Frequency 155 kHz

Ultrasonic Vibrating Motor: M-674,164 PILine designed by PI

Dust Mitigation System

Radiation Hardened Camera

Parameter Value

Diameter 24 mm

Length 110 mm

Mass 0.54 kgUnderwater Color Camera: N34F by Ahlberg Electronics