ORPHEUS — Venus Aerobot Mission
A high-altitude autonomous platform designed to float in Venus's atmosphere and uncover the relationship between its surface geology and atmospheric chemistry.
Overview
ORPHEUS is a NASA Discovery Program mission concept developed during the L'SPACE Mission Concept Academy (Spring 2025). The mission addresses a core question from the Planetary Science Decadal Survey: "How do planetary surfaces and interiors influence and interact with their host atmospheres?" To answer this, the team designed an Aerobot — a high-altitude autonomous balloon platform — capable of sustained observation within Venus's dense and chemically hostile atmosphere at approximately 55 km altitude.
The Aerobot targets Artemis Corona, one of Venus's largest coronae structures at ~2,600 km diameter, believed to have formed through mantle-plume interactions. The mission collects sulfur compound and CO₂ absorption spectra, thermal and pressure profiles over a 10 km atmospheric range, and gravitational anomaly data to determine whether mantle-plume penetrations directly create these geological structures — bridging the gap between geological activity and atmospheric changes.
The vehicle is a 41.967 kg system housed within a 1 m³ stowed volume, divided into five integrated subsystems: mechanical (gold-coated titanium chassis with silicon film for corrosion resistance), power (≥ 200 W solar generation), thermal (maintaining 0–40 °C internal range against Venus's 475 °C surface), CDH (onboard computer, data storage, and orbiter communication), and a science payload carrying an ultra-compact imaging spectrometer, infrared camera, and servo accelerometer.
As a member of ORPHEUS Team #1, I served as the team scientist who selected the scientific instrumentation, while also contributing to mechanical design, CAD modeling, FMEA (Failure Mode and Effect Analysis), and systems integration — working across subsystem interfaces to ensure the aerobot met structural, thermal, and launch-load requirements. The project culminated in a 180+ page Preliminary Design Review document presented to NASA reviewers.
3D Model
Interactive 3D model of the Aerobot payload subsystem — drag to orbit, scroll to zoom.
Technical Drawings
Process
01 — Inflation & Release
Balloon deployment at altitude
The Aerobot deploys from the Entry, Descent, and Inflation (EDI) system. The balloon inflates and stabilises at the target altitude within Venus's cloud layer (~55 km), establishing the floating platform for science operations.
02 — Stabilisation
Post-inflation systems check
Thermal regulation activates to maintain the 0–40 °C internal operating range against the extreme external environment. Power generation and distribution systems are confirmed nominal.
03 — Calibration
Instrument calibration & comms validation
All three science instruments — the ultra-compact imaging spectrometer, IR camera, and servo accelerometer — are calibrated in situ. Communication links with the orbiter are validated through scheduled transmission windows.
04 — Primary Science
Core data collection over Artemis Corona
The spectrometer captures sulfur species (S₂, S₄, S₈) and CO₂ absorption spectra. The IR camera detects thermal anomalies and surface emissions. The servo accelerometer records gravitational data to identify subsurface structures linked to plume activity. Data is sampled across a 10 km atmospheric swath as the balloon drifts with Venus's superrotating zonal winds.
05 — Extended Operations
Maximising scientific return
Data collection continues at a reduced duty cycle to conserve power and limit thermal stress. Optional altitude variation analyses atmospheric composition gradients. Final data is buffered and prepared for downlink to the orbiter.
06 — End of Life
Final transmission and shutdown
A final data-burst transmission is sent to the orbiter. All systems enter a controlled shutdown sequence, and the balloon structure passively degrades — marking the end of active operations after approximately 36 hours.
Engineering Details
Failure Mode and Effect Analysis (FMEA) — High Priority Risks
| Subsystem | Failure Mode | Cause | Severity | RPN | Mitigation Strategy |
|---|---|---|---|---|---|
| Power | Battery Thermal Failure | Extreme Venus temperatures (~75°C at cloud level) accelerating battery degradation | 9 | 378 | Redundant battery modules and thermal isolation to prevent single cell failure propagation |
| Structural | Balloon Envelope Rupture | Sulfuric acid corrosion of envelope material (pH ~0 environment) | 10 | 350 | Multi-layer envelope with acid-resistant coatings and a metallized gas barrier layer |
| Power / CDH | Power Distribution Bus Fault | Acid-induced electrical shorts and corrosion | 8 | 240 | Hermetically sealed, gold-plated connectors to resist acid corrosion |
| CDH | Antenna Pointing Failure | Turbulent high winds causing communication blackout | 9 | 216 | Gyro-stabilized antenna platform to maintain communication lock |
Subsystem Mass & Power Breakdown
| Subsystem | Mass (kg) | Max Power Drawn (W) | Notes |
|---|---|---|---|
| Mechanical | 14.200 | 10 | Gold-coated Ti chassis, 1x1x1m max volume |
| Power | 8.200 | N/A | Outputs ≥ 200W via solar generation |
| Thermal | 5.660 | 90 | Maintains 0-40°C internal operating range |
| CDH | 6.107 | 5 | Onboard computer and orbiter communications |
| Payload | 7.800 | 45 | Spectrometer, IR Camera, Accelerometer |
| TOTAL | 41.967 | 150 | Within 25kg chassis constraint |
Mechanical Subsystem Requirements (Verification Matrix)
| Req # | Requirement | Rationale | Verification Method |
|---|---|---|---|
| SYST-1 | Chassis shall not exceed 25 kg | Maintain overall mass budget while ensuring structural integrity | Inspection |
| SYST-2 | Stowed configuration ≤ 1 m³ | Required for integration with Entry, Descent, and Inflation (EDI) system | Analysis |
| SYST-3 | Survive 475°C, 90+ atm, sulfuric acid | Endure extreme Venusian surface and atmospheric conditions | Analysis / Testing |
| SYST-4 | Withstand launch and entry loads | Standard durability requirements for launch vehicle and atmospheric entry stresses | Analysis |
| SYST-5 | Provide mounting for science payload | Interface compatibility for spectrometer, IR camera, and accelerometer | Inspection |
Phase C-F Mission Budget Overview
| Budget Category | Cumulative Total (FY1-6) | Notes |
|---|---|---|
| Personnel | $34,000,000 | Engineering, science, and mission operations teams |
| Spacecraft Direct Costs | $33,000,000 | Manufacturing, materials, and payload development |
| Outreach | $60,000,000 | Educational programs and public engagement initiatives |
| Travel | $2,000,000 | Integration facilities and launch site operations |
| TOTAL | $129,000,000 | Fits within NASA Discovery Program cost caps |
Science Traceability Matrix (STM)
| Science Goal | Objective | Measurement Requirement | Instrument | Performance |
|---|---|---|---|---|
| Decadal 6.4: Surface-Atmosphere Interactions | Determine concentration of Sulfur & CO₂ above coronae | Identify S₂, S₄, S₈, and CO₂ profiles over 10km | Ultra-Compact Spectrometer | UV/Vis (200-800nm), 1ppm sensitivity |
| Decadal 6.4: Surface-Atmosphere Interactions | Analyze temperature & pressure variations | Collect thermal fluctuations across Artemis Corona | IR Imaging Camera | Mid-IR (1-5 µm) thermal emission tracking |
| Mantle Dynamics | Determine role of mantle plume penetrations | Detect gravitational anomalies over coronae | Servo Accelerometer | High-precision gravimetric data collection |
CDH Requirements Flow-down
| Req # | Requirement Summary | Rationale | Verification |
|---|---|---|---|
| CDH-1 | Manage intra/inter-communications and transmit to Orbiter | Seamless command execution and data handling | Demonstration |
| CDH-1.1 | Payload interface with CDH for data acquisition | Enable instruments to send data efficiently | Demonstration |
| CDH-1.1.1 | Collect data from Scientific Instruments | Ensure protocol compatibility | Analysis |
| CDH-1.1.1.1 | Routing device must sustain >30 Mbps data speed | Prevent bottlenecking of science data streams | Test |
| CDH-1.2.1.1 | High-gain antenna (>5dBic) for signal transmission | Maintain lock in turbulent high winds | Test |
Risk Analysis & Mitigation (Environmental & Integration)
| Risk | Condition | Consequence | Mitigation Strategy |
|---|---|---|---|
| High Pressure Deformation | Venus atmospheric pressure is 90+ bar | Deformation of balloon envelope compromising buoyancy | High-fidelity thermal/pressure simulation and multi-layer structural reinforcement |
| Assembly Misalignment | Integration of custom and COTS hardware | Geometric mismatch affecting deployment | GD&T modeling and strict mechanical interface verification during integration |
| Sulfuric Acid Corrosion | Flight through dense sulfuric acid clouds | Corrosion of exposed sensors and chassis | Silicon-coated titanium chassis and hermetic sealing on all exposed connectors |
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