→ Acts as a “bus” for the probes
→ Carries camera, communication equipment, and propulsion system
Embedded Files
→ Main focus of the project
→ Carries scientific equipment
→ Will lack propulsion or AODC
→ Will descend via parachutes
→ Target depth of 3 bar
Trajectory:
Venus, Venus, Earth flyby
Time of Flight 11 years
Launch Date of Jul - 2030
Impulse Maneuvers:
~2.6 km/s of delta v
Monomethyl hydrazine propellant
Travel to Uranus Propulsion:
Utilize Solar Electric Propulsion (SEP)
5.6 km/s of delta v
Four NASA NEXT Engines and Solar Panels for power
Use Xenon propellant
Jettisoned between 5-6 AU
Instrumentation:
4 Reaction wheels for attitude control
Combination of sun sensors, magnetometer, and inertial measurement unit for attitude determination
Transit, Orbit, and extended mission powered by General Purpose Heat Source Radioisotope Thermoelectric Generator (GPHSRTG).
Orbit Vehicle Size and Weight:
Current mass estimate: 5700 kg
4300 kg under budget
Current volume estimate 90 m3
100 m3 under budget
Current Power estimate:
Transit Stage: 781 Watts, 7000 under budget
Extended Mission: 250 Watts, 50 under budget
Diameter designed to fit Falcon Heavy payload attach fitting
Probe Front View
Probe Iso View
Dimensions:
→ Mass limit of 320 kg
→ Volume estimate of 2.2 m3 per probe
HEEET Heat Shield:
→ 2.65 m diameter
→ 0.125 m thickness
→ Approximately 30% of the total mass
→ Discarded with the parachute
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