Scalable, radiation-hardened spacecraft architectures engineered for cislunar operations, heliocentric transfer, and outer-planet science missions. Fully compliant with NASA SSP 50842 & ESA PSS-05-1.
Our deep space platforms utilize a modular bus architecture, enabling rapid configuration for diverse mission profiles while maintaining strict mass, power, and reliability margins.
High-thrust bi-propellant and electric propulsion integration with 15,000+ s specific impulse capability. Redundant GNC computers and fuel management systems rated for 10+ year lifespans.
Scalable power architecture supporting 1.5kW to 8kW depending on mission phase. Multi-layer MLI, active fluid loops, and deployable radiators maintain -40°C to +85°C payload envelopes.
Standardized 19U rack interface with optical data bus, redundant power distribution, and vibration-isolated mounting. Supports remote sensing, spectrometry, and sample return hardware.
Baseline configuration for the AeroVance DS-400 class. Custom delta-V and power scaling available upon request.
| Parameter | Specification |
|---|---|
| Dry Mass | 1,250 kg (baseline bus) |
| Wet Mass | 3,800 kg (fully fueled) |
| Total Delta-V | 6.2 km/s (chemical + ion hybrid) |
| Power Generation | 2.4 kW EOL (solar) / 110 W RTG option |
| GNC Architecture | Triple-redundant FPGAs + optical nav |
| Communication | X-band (32 Mbps) / Ka-band (100 Mbps) relay |
| Radiation Hardening | Class H (100 krad TID, SEL hardened) |
| Design Lifetime | 12 years (extendable to 15) |
| Payload Capacity | Up to 850 kg (Class A/B instruments) |
Integrated subsystems designed for autonomous operation in high-latency, radiation-intensive environments.
AI-driven system health monitoring with on-board reconfiguration and safe-mode sequencing.
Full compatibility with NASA DSN, ESA ESTRACK, and commercial relay constellations.
Capillary pumped loops and variable conductance heat pipes for cryogenic to high-heat flux zones.
Whipple-bumper multi-layer architecture rated for 50+ year operational exposure.
Standardized operational workflow from launch integration to end-of-mission disposal.
Vehicle fairing separation, bus initialization, and heliocentric/cislunar trajectory insertion. Autonomous checkout over 72 hours.
Mid-course corrections via ion thrusters. Gravity assist navigation and thermal/power equilibrium management.
LOI/MOI burn sequence. Precision orbital capture using optical navigation and star tracker alignment.
Full payload deployment. Continuous downlink, instrument calibration cycles, and anomaly resolution protocols.
Deployed in 2024, HELIOS utilizes the DS-400 platform to deliver high-gain communications relay and atmospheric spectrometry to Jupiter's Lagrange points. The platform achieved 99.8% autonomous uptime during the 18-month transit phase.
Access detailed technical manuals, interface control documents, and environmental test reports. Requires registered partner status for full access.