Buses & platforms

6U (and 8U variant) CubeSat bus optimised for communications payloads. Pointing knowledge <=0.5 deg, pointing accuracy <=0.5 deg. Payload power OAP 10 W. S-band TT&C and payload data: 128 kbps up / 512 kbps down. Data storage 4 GB. Low-noise bus design, de-orbit compliant. Optional Xiphos SDR integration. In-orbit heritage: Ymir-1 (VDES demonstrator), LusoSpace constellation (8U variant, 11 satellites planned late 2025).

6U CubeSat bus optimised for Earth observation. High-precision ADCS: pointing knowledge <=0.01 deg, pointing accuracy <=0.1 deg. Payload power OAP 10 W. S-band TT&C at 128 kbps up / 512 kbps down; X-band payload downlink at 80 Mbps. Platform data storage 4 GB (min); payload data storage 128 GB. GPS included. Launched as EPICHyper-1/2/3 (Wyvern Dragonette-001/002/003, 2023) and VIREON-1/2 (2026). TRL 9 in flight.

Flight-heritage 16U CubeSat bus by EnduroSat. Payload mass up to 24.5 kg, payload volume 10.3U (218 x 218 x 254 mm), payload power 25-60 W. S-band TT&C with X-band and K-band payload downlink up to 1 Gbps. Three-axis reaction wheel ADCS. Mission life 5 years. 6-month delivery-to-orbit timeline.

Flight-heritage 8U CubeSat bus by EnduroSat. Payload mass up to 6.8 kg, payload power 13-40 W (configuration dependent). S-band TT&C with X-band payload downlink up to 150 Mbps. Three-axis reaction wheel ADCS. Mission life 3-5 years. 80+ EnduroSat satellites in orbit across the full product range.

Large ESPA-class (24-inch) microsatellite bus by EnduroSat. Bus mass 200-250 kg, payload mass up to 300 kg, peak power 1.6 kW, max continuous 7 kW. Pointing accuracy <0.06 deg (3-sigma nadir). Propulsion: 400-1000 m/s delta-V. Payload data downlink up to 4 Gbps via 100G Ethernet / SpaceWire / SpaceFibre.

ESPA-class (15-inch) microsatellite bus by EnduroSat. Bus mass 85-100 kg, payload mass up to 70 kg, peak power 600 W, average payload power 105-410 W. Pointing accuracy <0.04 deg (3-sigma nadir). Propulsion: 40-400 m/s delta-V. Payload data downlink up to 2 Gbps. Target: commercial EO, SAR, orbital computing constellations.

Largest standard CubeSat bus in the ISIS product line. Payload volume 8-12U. S-band TT&C with up to 0.5 Mbps downlink. Optional propulsion up to 2000 Ns. Comprehensive ADCS suite. Design lifetime up to 3 years.

Standardised 3U CubeSat bus by ISISPACE, the entry-level commercial platform in the ISIS line. PC/104-based stack architecture, ARM9 OBC, ICEPS compact EPS, VHF/UHF transceiver. Payload volume 1.5-2U. Design lifetime up to 3 years.

Mid-range 6U CubeSat bus by ISISPACE. Payload volume 2.5-3U (or 3U in XL configuration). Optional propulsion up to 2000 Ns. VHF/UHF comms with up to 0.5 Mbps downlink. Design lifetime up to 3 years. Heritage: BRIK-II (2021), CSC-1/2 (2023), Cassini constellation.

Loft Orbital's standardised LEO satellite bus derived from the OneWeb constellation architecture, used across the YAM demonstration series and as the platform for the DESIR programme. Bus-agnostic Hub payload adapter attaches to Longbow, enabling payload-agnostic hosted-payload missions.

In-house-designed satellite bus underlying the six Pixxel Firefly satellites (FFLY-1 to FFLY-6). Custom rectangular microsatellite platform at approximately 60 kg total satellite mass (bus and payload combined; mass split not published). Flies in sun-synchronous orbit at approximately 550 km altitude. Propulsion on FFLY-1, FFLY-2, and FFLY-3 confirmed as Dawn Aerospace SatDrive green bi-propellant system (nitrous oxide and propene); propulsion for FFLY-4, FFLY-5, and FFLY-6 not separately confirmed. Peak downlink exceeding 500 Mbps reported in orbit; downlink frequency band not published. Pointing to tasked coordinates validated in-orbit; numeric pointing budget not published. Assembled, integrated, and tested at MegaPixxel, Pixxel's 30,000-plus square-foot Spacecraft AIT facility in Bengaluru (ISO Class 7 and 8 cleanrooms, capacity approximately 40 satellites per year). Platform is also licensed to Cosmoserve for an active debris removal demonstration mission (2026).

Airbus Defence and Space spacecraft platform for the Sentinel-2 missions. Approximately 1140 kg launch mass, designed for a sun-synchronous orbit at 786 km.