Blue Canyon Technologies

Manufacturer United States Verified
60 Products
18 Years Active
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About Blue Canyon Technologies

Blue Canyon Technologies (BCT), a wholly owned subsidiary of Raytheon, an RTX business, is a leading provider of small satellite buses, systems, and components for commercial, civil, and government space missions. Founded to solve the toughest challenges in space, BCT has amassed over 90 launched satellites and thousands of components delivered, with more than 230 years of combined on-orbit heritage for spacecraft, 350+ years for avionics assemblies, and 3,600+ years for individual components.

BCT's product line spans complete spacecraft buses, attitude determination and control systems, reaction wheels, star trackers, and other high-precision components, supporting missions across VLEO, LEO, GEO, lunar, and interplanetary trajectories. The company is known for low-jitter, arcsecond-class on-orbit pointing systems and high-volume manufacturing that maximizes payload mass and volume while minimizing overall mission costs.

With a total integrated mission solutions approach, BCT supports customers from initial design through build, test, and on-orbit operations. Its reliable, flight-proven, high-performing spacecraft solutions serve university-led science missions as well as national defense constellations.

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Products

60

Deployed solar arrays for 3U CubeSats, 27–34 W output, 30% efficient cells, Frangibolt release, SADA-compatible.

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Deployed solar arrays for 6U/12U CubeSats, 48–118 W output, 30% efficient cells, SADA gimbaling option.

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Larger single-gimbal CMG for SmallSats, 12 Nms rotor momentum, 12 Nm output torque, radiation-hardened with redundancy options.

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Single-gimbal CMG for SmallSats, 8 Nms rotor momentum, 8 Nm output torque, ~10x more torque than reaction wheels at ~5x less power.

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High-capacity small satellite CMG. 12 Nms momentum, 12 Nm torque, under 18 kg. For high-revisit Earth observation, ISR, and tactical missions requiring aggressive slewing.

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Small satellite CMG. 8 Nms momentum, 8 Nm torque, under 13 kg. Delivers 10x the torque of reaction wheels at up to 5x less power for rapid spacecraft reorientation.

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Li-ion battery packs for 3U-16U CubeSat buses (1P8S, 2P8S, IP8S), part of BCT's XB power subsystem.

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Deployable solar arrays for 3U, 6U/12U CubeSats, and microsatellite platforms, part of BCT's XB power subsystem.

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Flexible ADCS processor for SmallSat platforms, compatible with BCT sensors and third-party ADCS components. Scalable configuration.

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Highest-performance nano star tracker. 0.85 kg, 25x10x10 cm, 1 arcsec cross-boresight / 10 arcsec about-boresight. Maximum aperture for demanding deep-space and science missions.

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High-power deployed solar arrays for BCT X-Sat and microsat platforms, up to 2000 W class, 30% cells, SADA gimbaling.

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High-accuracy nano star tracker. 0.45 kg, 17x8.5x7 cm, 1 arcsec cross-boresight / 10 arcsec about-boresight. Lost-in-space, RS-422/RS-485. For precision imaging missions.

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Full-baffle nano star tracker, 1 arcsec cross-boresight accuracy, 850 g, 250×100×100 mm. Tightest sun exclusion (12–17.5°).

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Extended baffle nano star tracker, 1 arcsec cross-boresight accuracy, 450 g, 170×85×70 mm. Tighter sun exclusion (15–22°).

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Flight-proven nano star tracker for CubeSats and small satellites; 3 configurations (standard, mid-extension, full-extension) with starlight-in, quaternion-out output.

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Compact nano star tracker, 6 arcsec cross-boresight accuracy, 350 g, 100×55×50 mm. 179+ on-orbit heritage. 5–28 V supply.

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Flight-proven reaction wheel family covering 0.015 to 16 Nms momentum. 9 base models with High-Torque (HT) variants. 3200+ manufactured, 1300+ launched.

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Flight-proven CubeSat and small satellite reaction wheel family (RW1 through RW16 and RW-HT variants) for 3U to 16U and microsatellite platforms.

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SmallSat reaction wheel, 1 Nms momentum, 70 mNm torque, 950 g, 110×110×54 mm. Flight proven.

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BCT's largest reaction wheel, 16 Nms momentum, 250 mNm torque, 7.5 kg, 242×242×120 mm. For 400 kg+ spacecraft.

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High-torque variant of BCT's largest reaction wheel, 10 Nms momentum, 500 mNm torque, 7.5 kg.

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SmallSat reaction wheel bridging RW1–RW4 gap, 2 Nms momentum, 120 mNm torque. RS-422 interface.

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High-torque SmallSat reaction wheel, 1.2 Nms momentum, 250 mNm peak torque. Optimized for agile maneuvers.

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Mid-size SmallSat reaction wheel, 4 Nms momentum, 250 mNm torque, 3.2 kg, 175×175×72 mm. 105+ units launched.

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High-torque SmallSat reaction wheel, 2.3 Nms momentum, 500 mNm peak torque, 3.2 kg. Same housing as RW4.

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Large SmallSat reaction wheel, 8 Nms momentum, 250 mNm torque, 4.4 kg, 193×193×84 mm. 50+ units launched.

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High-torque SmallSat reaction wheel, 5 Nms momentum, 500 mNm peak torque, 4.4 kg. Same housing as RW8.

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Precision reaction wheel family for microsatellites and small satellites (RWP015, RWP050, RWP100, RWP500).

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Smallest BCT reaction wheel, 15 mNms momentum, 4 mNm torque, 130 g, 42×42×19 mm. For pico/nanosatellites and deep space CubeSats.

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CubeSat reaction wheel, 50 mNms momentum, 7 mNm torque, 240 g, 58×58×25 mm. RS-422 interface.

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CubeSat reaction wheel, 100 mNms momentum, 7 mNm torque, 330 g, 70×70×25 mm. RS-422 interface.

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SmallSat-compatible reaction wheel, 500 mNms momentum, 25 mNm torque, 860 g, integrated electronics. RS-422.

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ESPA-Grande 24-inch minisatellite bus. 30x30x40 inch payload volume, +-0.002 deg 3-axis pointing. Flown on DARPA Blackjack LEO constellation and NASA PANDORA exoplanet mission.

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ESPA-Grande / 4-point mount small satellite bus. 40x40x45 inch payload volume, +-0.002 deg pointing. SpaceX rideshare compliant. For demanding government and commercial missions.

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Flight-proven 3U CubeSat solar array. 27-34 W, 14.9 VDC Vmp. Linear, rotary and micro release options; carbon fiber and honeycomb structures. 310 arrays manufactured.

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Flight-proven 6U/12U CubeSat solar array. 48-118 W, 17 or 34.1 VDC Vmp. Dual voltage options for different bus architectures. Linear, rotary and micro release mechanisms.

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Solar arrays for ESPA-class microsatellites. 222-444 W, 36.2 VDC Vmp. For Venus-100 and Saturn-class platforms. Linear, rotary, micro release mechanisms available.

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Single-string 8-series Li-ion satellite battery with integrated heaters. 3.4 Ah, 99 Wh, under 650 g. For CubeSat and small satellite missions. 495 units manufactured.

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Dual-string 8-series Li-ion satellite battery. 6.8 Ah, 198 Wh, under 1200 g. Integrated heaters for low-temperature operation. For microsatellite and power-intensive missions.

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Compact nano star tracker with lost-in-space capability. 0.35 kg, 10x5x5.5 cm, 6 arcsec cross-boresight / 40 arcsec about-boresight accuracy. MIL-STD-461 tested.

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ESPA-Standard 15-inch microsatellite bus, +-0.002 deg pointing (3 axes, 2 trackers), LEO/GEO/deep space. Flown on NASA INCUS climate constellation and ispace lunar relay missions.

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Smallest BCT X-Sat microsat platform, 40 kg payload, 108 W solar, ±0.002° 3-axis pointing. LEO/GEO/deep space capable.

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BCT's largest X-Sat platform, 200 kg payload, 30×30×40 in bus, ±0.002° 3-axis pointing. For high-payload government/commercial missions.

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Mid-size BCT microsat platform, 70 kg payload, ±0.002° 3-axis pointing. Secure communications, radiation tolerant. LEO/GEO/deep space.

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Integrated ADCS for 12U CubeSats, 15 arcsec cross-boresight, 100 mNms momentum, 0.52 kg electronics. Flight proven.

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Integrated 0.5U ADCS for 1U–3U CubeSats, ±10 arcsec 2-axis pointing, 15 mNms momentum, 885 g. Star tracker + RW + magnetorquer in one unit.

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Integrated 0.75U ADCS for 3U–6U CubeSats, 1 arcsec cross-boresight pointing, 50 mNms momentum, 1.23 kg. Flight proven.

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Blue Canyon Technologies' flagship XB series is a modular, flight-proven CubeSat bus line (XB1 core avionics in 3U, 6U, 12U, and 16U configurations) built for high-precision pointing, agility, and rapid, cost-efficient mission deployment.

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TRL-9 12U CubeSat bus, 8U payload volume, 92–108 W payload power, ±0.002° 3-axis pointing. Flight-proven to GEO.

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BCT 12U CubeSat spacecraft bus with high pointing accuracy and expanded payload volume.

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12U CubeSat platform with 8U payload, +-0.002 degree pointing (3 axes, 2 trackers). First BCT bus flown in GEO orbit (AFRL ASCENT). Carried 19-payload Slingshot rideshare mission.

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BCT 16U CubeSat spacecraft bus — largest XB CubeSat configuration, up to 23 kg payload capacity.

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BCT's largest CubeSat bus, 16U form factor, 14U payload volume, 92–108 W payload power, high-precision ADCS.

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16U CubeSat platform with 12U payload, +-0.002 degree pointing (3 axes, 2 trackers), LEO/GEO/deep space. Flown on NASA INCUS climate science constellation and DoD ISR missions.

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BCT 3U CubeSat spacecraft bus built around XB1 core avionics with integrated ADCS, comms, power, and GPS.

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TRL-9 3U CubeSat bus with 1.5U payload volume, 27 W solar power, ±0.003° pointing. Flight-proven to GEO.

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3U CubeSat platform with 1.5U payload, +-0.003 degree pointing accuracy (2-axis, 1 tracker), LEO/GEO/deep space capable. 18 units launched. Used on NASA TROPICS and MIT CLICK missions.

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TRL-9 6U CubeSat bus, 4U payload volume, 92–108 W payload power, ±0.002° 3-axis pointing. Flight-proven to GEO.

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BCT 6U CubeSat spacecraft bus with dual-tracker high-precision pointing and proven flight heritage.

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6U CubeSat platform with 4U payload, +-0.002 degree pointing (3 axes, 2 trackers), LEO/GEO/deep space. 50+ units launched. Flown on NASA Starling swarm and upcoming SPARCS UV observatory.

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