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I nvestigating the C omposition of E nceladus via

I nvestigating the C omposition of E nceladus via. P rimary L ander and U nderwater M icroorganism E xplorer. Alex Gonring, Capri Pearson, Sam Robinson, Jake Rohrig, & Tyler Van Fossen University of Wisconsin - Madison. ICEPLUME Mission Overview. Aeroshell.

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I nvestigating the C omposition of E nceladus via

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  1. I nvestigatingtheC ompositionofE nceladusvia P rimaryL anderandU nderwaterM icroorganismE xplorer Alex Gonring, Capri Pearson, Sam Robinson, Jake Rohrig, & Tyler Van Fossen University of Wisconsin - Madison

  2. ICEPLUME Mission Overview Aeroshell Solar Electric Propulsion (SEP) Module Lander with Probe Inside Orbiter

  3. Saturn’s moon Enceladus shows unique characteristics. • Recent geological activity • Warm South Pole • Plume contributes to E-Ring • “Tiger Stripes” supply fresh ice • Fundamental needs for life • Water (Cassini measured 90%) • C H N O basic elements • Energy source • Astrobiology may exist on Enceladus 500 km

  4. Solar Electric Propulsion and Gravity Assists will provide the initial ΔV to Saturn. Ø 40 cm 8 m The 61.2 m2 solar arrays provide 27.6 kW to power the 5 NEXT thrusters. 2 m

  5. The Ultraflex solar panels provide power and xenon fuels the ion thrusters. AdvancedStirling Radioisotope Generators operate the instruments on the orbiter. Ultraflex solar panels 0.725 m Power processing unit ASRG Xenon tank

  6. An aeroshell is required for atmospheric entry during aero-gravity assist. Solar Electric Propulsion with aerocapture provides ~ 2.4x more mass delivered to final destination (~ 500 kg) Added complexities: 1) RCS thrusters for trajectory alignment 3) Payload configuration within volumetric constraint 2) Heat shield for thermal protection (~1500° C, 99% KE) MSL (Ø 4.5m) Orion heat shield (Ø 5m) ICEPLUME (Ø 5.0 m)

  7. Low-density materials are required to minimize aeroshell mass. Separation Plane Backshell • Structural Material: • graphite polycyanate composite • Aeroshell: 2.6 cm molded honeycomb • Framework: 1.6 cm isogrid • Face Sheets: 2 mm thick sheet 2.5 m Rib Longeron Thermal Protection Materials: ** 14-31% improvement on heritage aerial densities RCS Jets • PhenCarb-20 (500 W/cm2) • SRAM-20 (260 W/cm2) • SRAM-17 (210 W/cm2) • SRAM-14 (150 W/cm2) • Acusil II (100 W/cm2)

  8. 10X Separation Mechanism Ten separation mechanisms split the aeroshell and deploy the orbiter after aero-assist. • Requirements: • Permits rotation • Allows compression • Primarily Ti 6AI-4V Separation Nut Spherical Bearing Separation Bolt Separation Plane 3 m 6 in Compression Spring • ** Based on the Mars Science • Laboratory (MSL) design Bolt Extractor

  9. Multiple propulsion systems are needed to accomplish our mission. • System uses separate monopropellant and bipropellant propulsion modules • Monopropellant module will use 132 kg of hydrazine (N2H4) and 0.9 N thrusters for attitude control in conjunction with reaction wheels • Bipropellant module will use 3000 kg of monomethylhydrazine (MMH) for fuel and nitrogen tetroxide (NTO) for oxidizer

  10. The monopropellant system is used for attitude control and fine course corrections. Ø 0.128 m • Helium Recharge Tank • Used for a single-time recharge of the monopropellant system • Holds 0.4 kg of He 0.85 m • Monopropellant Tank • Purchased from Pressure Systems Inc. • Initial pressure 2.34 MPa (340 psi) • Holds 132 kg of Hydrazine • Thruster Clusters • 1 N thrusters purchased from Astrium • 8 clusters of 4 thrusters are placed on the top and bottom of the payload deck 270 mm 270 mm

  11. The bipropellant system is used for trajectory correction maneuvers. 0.96 m • Helium Pressurization Tank • Backfills He into oxidizer and bipropellant tanks to maintain pressure • Initial pressure 23.7 MPa Holds 8.6 kg of He 1.5 m • Oxidizer and Bipropellant Tanks • Pressurized to 689.4 kPa(100 psi) • Holds 1131 kg of fuel and 1869 kg of oxidizer • Booster Assembly • R-4D rocket engine by Aerojet • 490 N (110 lbf) nominal thrust • Gimbal up to 37° in all directions 0.9 m

  12. Science instruments similar to the Cassini mission will explore mission goals.

  13. The orbiter contains multiple communication systems. • Radio frequency subsystem with antennas provide communication for the orbiter to and from Earth. • High-gain Antenna (HGA) • Support communication with Earth while in orbit about Enceladus • S-band Probe/Lander communication • Two Low-gain Antennas (LGA) • Support communication with Earth during transit

  14. The orbiter’s structure is constructed primarily of a composite payload deck. 4.4 m 4.4 m 3.5 m 1.8 m 2.27 m 6.23 m 6.2 m 1.8 m • HGA Structural Material: • 6061-T6 aluminum I beams • 6061-T6 angle brackets • 7075-T73 aluminum sheet • Payload Deck Structural Material: • graphite polycyanate composite • Deck Panels: 2 cm isogrid • Face Sheets: 1.6 mm thick sheet 1.35m

  15. A majority of the total mass will be allotted towards payload delivery. Total Mass from LEO: 7559 kg

  16. The lander will be deployed from the back of the orbiter. • No aeroshell required • Heat flux value of (compared with ) • Lander held to orbiter with pyronuts • Deployed by expanding spring • Guided out on rails • 4X 22N descent thrusters • 16X 1N attitude thruster clusters • Radar 3.6m

  17. The main objective of the lander is to carry the probe to the surface. Science Instruments: Descent Camera Accelerometer Tiltmeter Seismometer Radar Low Gain Antenna 3.6 m Exploration Probe 12X 1N Attitude Thruster Clusters 12X 1N Attitude Thruster Clusters 22N Descent Thrusters Landing Feet Propellant Tanks (Monopropellant) Ø2.5 m

  18. Thank you! Questions?? The probe melts through 6.5 miles of ice in 1.5 years. IPPW-9 Staff & Student Organizing Committee University of Wisconsin Faculty and Staff Dr. Elder Prof. Hershkowitz Dr. Sandrik • Lander-probe separation mechanism (pyronuts) • Tether Bay houses tether for data relay • Science instruments (Chemical, mineral, thermal, magnetic, astrobiological measurements) • 2 GPHS-RTGs generate 100W electric power for instruments and 8600W thermal power to melt ice • Accelerometer, tiltmeter, water pump and jets 3.47 m

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