Europa Reconnaissance
Formation Mission

Presented By:

Aditya Raj Bhatia

Praneel Sharma

Dhanush Mamillapally

2nd Year Aerospace Engineering
SRM Institute of Science andTechnology, Kattankulathur, India

Yash VermaWhy Europa?
• Potentially habitable world rightwithin our reach• Made up of water ice and an
enormous saltwater ocean• The ocean could sustain life undercertain conditions• Carbon, Oxygen, Nitrogen, Sulfur &water presence on surface point topossibility of extraterrestrial life

Table of content
1.

Mission Objectives

2.

Launch and Orbital Design

3.

RAAG Engine

4.

CAMSAT5.

SCISAT: Magnetometer, LIDAR, Mass Spectrometer

6.

RADARSAT

7.

RELAY- Link Budget

8.

Common components in all satellites

9.

Mission Risks

10.

Mission Timeline

11.

Mission Impact

12.

Conclusion

Mission Objectives

Map the underground
topology of Europa by
Ice Penetrating Radar

Determine the surface
composition of Europa

Quantify the magnetic
field of Europa in astable orbit

Capture highest
resolution images ofEuropa’s surface

Generate a high-quality
3D model of Europa bycameras and LIDAR

Carrier Stage

RAAG
Rapid Astrogation Adaptative Generator

RAAG ENGINE
Thrust – 1500NMass Flow Rate – 0.5591 Kgs/s
NTO Mass Flow Rate – 0.338 Kgs/s

MMH Mass Flow Rate – 0.175 Kgs/s
O/F Ratio – 2.181
Chamber Pressure – 800 psi

Max Burn Time – 194 mins (116525sec)
Total Propellant Mass – 6500 kgs*NTO- Dinitrogen Tetroxide*MMH- Monomethyl Hydrazine*O/F- Oxidizer by fuel ratio*LEO- Low Earth Orbit*HCO- Heliocentric orbit*TCM- Trajectory Correction
Maneuver*JOI- Jupiter Orbital Insertion*EOI- Europa Orbital insertion

CAMSATSCISATHPMI PACKAGE(HIGH PRECISION MAGNETOMETER INSTRUMENT)CONSISTS OF :• A SCALAR MAGNETOMETER - CDSM(COUPLED DARK STATEMAGNETOMETER)• TWIN VECTOR MAGNETOMETERS – AMR ( ANISOTROPIC MAGNETORESISTANCE) MAGNETOMETER

WORKING:• THE CDSM magnetometer employs a multi-chromatic laser field and coherent population trapping
resonances for stable, precise, and temperature-independent magnetic field measurements. Prioritizing
simplicity, compactness, and efficiency.
• AMR magnetometer uses the data from CDSM as a reference to calculate direction and magnetic fieldstrength
CREDIT: NASA VTADTECHNICAL MODIFICATIONSTo Make AMR Magnetometer a Zero-field detection device
We used• Full Wheatstone bridge Configuration (full Wheatstone bridge configuration provides abalanced state at zero magnetic field)• Feedback Control System (actively adjusting parameters compensating magnetic fields, tomaintain the bridge in a balanced state)• Differential Measurements (Multiplesensors oriented in differentdirections)

HPMI PACKAGE SCHEMATICSAPPLICATIONS OF HPMI PACKAGE• CHARACTERIZING EUROPA’S MAGNETIC FIELDS IN
OVERALL, STRENGTH AND DIRECTION TO CREATE
DETAILED MAP OF MAGNETIC FIELDS ACROSSEUROPA• DETECTION OF ANOMALIES IN MAGENTIC FIELDS• INDICATES IN SUBSURFACE OCEAN BENEATHEUROPA• STUDYING ICE-MAGMA INTERACTION• UNDERSTANDING THE MOON’S INTERIORDYNAMICSBENEFITS OF HPMI PACKAGE•••

UNDERSTANDING OF EUROPA’S EVOLUTIONMISSION PLANNING AND NAVIGATION FOR FUTURE MISSIONSTESTING DIFFERENT HYPOTHESISThe LIDAR’s Mission• Long-range CubeSat LIDAR: Range of up to 1,000 km• Purpose: Mapping Europa's surface features, altimetry, and surface property analysis

How it Works:• Laser pulses from satellite to surface• Return signal captured by onboard telescope• Measures distance by analyzing time taken by laser pulse

Technical Specifications
Parameter

ValueRange Capability

Up to 1,000 km

Range Resolution

15 cm at long range, 60-degree cone atshort range

Power Consumption

14.3 W during operation

CO2 LIDAR Wavelength

2051 nmOperation Range

1.9 nm to 2.1 nm

Application and Benefits
Applications of LIDAR:• Detailed Surface Topography & Relief Mapping by combining data of CAMSAT• Eurapa’s Ice Thickness Estimation• Atmospheric Studies• Surface Composition Analysis• Mapping & Navigation
Benefits:• Detailed understanding of Europa's surface• Identifying potential landing sites• Estimation of subsurface ice thickness• Precise spacecraft navigation

RADARSATHF Configuration
Parameter
Value
Operation Frequency
9MHz
Bandwidth
1MHz
Pulse Time
20-100μs
Vertical Resolution≤300 mAlong Track Resolution≤5.5 km
Vertical Precision
150 m
Monopole antenna length8m
Radio Type
Frontier Radio Multi Lingual
Transmission
20W

Alternate VHF Configuration
Operation Frequency
16MHz
Shallow-depth≥3 km
Pulse Time
20-100μs
Vertical Resolution≤30 m
Along Track Resolution≤2 km
Dipole antenna
3mObjectives
1) Characterize the ice shell’s global structure2) Investigate material exchange processes among the ocean, ice shell, surface, and atmosphere3) Determine scientifically compelling sites for future lander missions4) Determine ice shell’s thermal conductivity5) Confirm presence of water and global subsurface ocean

RELAYRelay- Data Transmission
SchemeSCISAT:- Calculate data size to be sent
- Calculate transmission time for all three recon sats
- Transmit data & transfer time to relay at 7184.27 MHz- Relay sends signal at 8440.80 MHz indicating SCISAT transmission completion
RADARSAT:- Begins transmission 20 sec after SCISAT's completion- Transmits data to relay (stored in allocated memory)- Relay sends signal at 8.3GHz to alert CAMSATImage: Europa Clipper from NASACAMSAT:- Initiates transmission after signal from relay at 8.3GHz- Transmits images following the procedure of previous satellites
Relay:- After receiving all data, ADCS checks antenna position- Points antenna towards Earth with high precision- Begins transmission at 7173.87 MHz- Returns to charging mode if in sunlit area, sleep mode if eclipsed
Failure (if relay fails):- Reconsats relay data to Europa clipper- Transmission: reconsats to Europa clipper at 8424.5MHz- Europa clipper to Earth at 7170MHz (Channel 21 DSN)

Data - Link Budget
Primary Antenna:

32X32” High Gain Antenna [35dBi, 25
Mbps – 8/16 PSK/QAM, 1.3 Mbps - QPSK]Peer Antenna:

DSNTrackingStation [X 74.3 dBi 73 dBm[TL:9] QPSK 2.72 Mbps]

Relay Earth Uplink:

7173.87MHz

Relay – Earth Downlink

8428.58 MHz

Distance Max:

967264000000 m

Tx/Rx rate at max distance:

170.0 Kbps/1.36 Mbps

Distance Min:

587721000000 m

Tx/Rx rate at min distance:

340.0 Kbps/1.36 Mbps

ADCS (ATTITUDE DETERMINATION CONTROL SUBSYSTEMS) &POWER SYSTEMSAll these combines to provide an Accuracy of
365.9 arcseconds or 0.1
SSOC-D60 SUN SENSOR
Orthogonal Configuration
Accuracy of 0.3°
±60° FOV
0.039 Kgs

Adcole Coarse Sun Sensor
Accuracy of 0.75°±60°FOV
0.213Kgs

MAI-SS STAR TRACKER
Adcole Maryland Aerospace
Cross Axis-5.7 arcsec,
Boresight- 27 arcsec
0.305 Kgs 1.5 W

Measures the specific gravity andangular rate of the satellite
0.055 kgs uses 2 W per Sat

TITAN 350WHR MODULAR POWER
ARRAY
350WHR, 84000mAh, 1.050Kgs

MOOG 058-118
3.6N
Isp – 57 sec
1 of 8 CGT30Kgs of 𝐶𝑂2

1 of 4 Reaction Wheels
In Tetrahedral Configuration
0.555 kgs and 5.4 W per Sat
Providing ±0.5 mNm torque at0.04Nms

• RAAG Engine failure- Multiple ground testing increases
performance confidence

Mission Risks
and solutions• Micrometeorites- Carrier Stage Fairing decreases theprobability of damage• Reaction wheel failure- 4 wheels have been used so that
redundancy is increased• Lethal Jovian Radiation can destroy and make electronics
useless- Radiation chamber inside each satellite houses mostelectronics• Relay failure- Europa Clipper can be used as relay to senddata to EarthYearMonth
Design (Structural+Avionics)
Preliminary Design
Detailed Design
Design Freeze
Payload Development & Testing
OBC
Reaction Wheels
Solar Sensor
HeaterIMU
MAI-SS Star Tracker
Frontier Radio for Relay
Frontier Radio for RADARSAT
Battery
Solar Panels
X Band Transmitter and Receiver
Radiation Chamber for electronics
Mass Spectrometer
LIDARMagnetometer
Wide Field Camera
Narrow Fiels Camera
Cubesats structures
Carrier Stage Fuel Tanks
Carrier Stage Fairing
Carrier Stage Structures
CGT for Carrier Stage
RAAG Engine
RAAG Static fire
EIPR Antenna
PCS and electronic subsystems
Coupler for Falcon 9 attachment
Assembly
Orbit Refinement
Simulated environemtal testing
Acoustic and Vibration
Thermal and Vacuum
Radiation TestingContamination control
Integration with Falcon 9 FTStage Operations Readiness Review
Launch

2024
2025
2026
2027
Jan-Feb Mar-Apr May-Jun Jul-Aug Sep-Oct Nov-Dec Jan-Feb Mar-Apr May-Jun Jul-Aug Sep-Oct Nov-Dec Jan-Feb Mar-Apr May-Jun Jul-Aug Sep-Oct Nov-Dec Jan W1 Jan W2 Jan W3 Jan W4

Mission Impact• Global collaboration• Advancement in scientific database• Provides opportunities for new theories regarding Europa’s
magnetic field, surface characteristics and subsurface ocean• Lays foundation for future missions• First spacecraft to study Europa in a stable orbit• Helps in landing site determination for lander mission

THANK YOU