Capability ALTAIR EX Series AQUILA M1 Baseline AQUILA M2 Baseline AQUILA M4 Baseline AQUILA M8 Baseline Options Performance Performance Performance Performance Instrument Mass 135 kg 180kg 210 kg 400 kg Scalable structure for increased mass Scalable power system for Instrument Power 55W OAP, 250W Peak Coming March 2014 335W OAP, 250W Peak 300W OAP, 1000W Peak increased power 3 3 3 Scalable structure for Instrument Volume 0.67m (110 x 60 x 110 cm) Coming March 2014 2.4m (110 x 110 x 200 cm) 16m (400 x 400 x 400 cm) increased volume Instrument Data Interface Coming Mar 2014 RS-422, LVDS RS-422, LVDS RS-422, LVDS RS-422, LVDS 1553, Spacewire, Proprietary/Custom Solar Array Articulated or Fixed Articulated or Fixed Articulated or Fixed Articulated Ask us how this extremely Increased data volume Data Storage low cost and flexible platform 8 Gbytes 8 Gbytes 8 Gbytes 8 Gbytes to > 1 TB can be tailored to meet your large scale deployment and X-band to 40 Mbps Downlink Rate 2 Mbps, S-band 2 Mbps, S-band 2 Mbps, S-band 2 Mbps, S-band constellation needs. Ka-band to > 400 Mbps Pointing Control 26 Arc-sec, 3σ Coming March 2014 26 Arc-sec, 3σ 26 Arc-sec, 3σ Stability 1 Arc-sec in 1 sec Coming March 2014 2 Arc-sec in 1 sec 1 Arc-sec in 1 sec Tighter GN&C performance, agility Knowledge 8 Arc-sec, 3σ Coming March 2014 8 Arc-sec, 3σ 8 Arc-sec, 3σ Bus Mass 82 kg 180 kg 330 kg 760 kg Observatory Mass 50 kg 217 kg 360 kg 540 kg 1160 kg Low Earth Orbit (standard) Geosynchronous Earth Orbit LEO, HEO, MEO, GEO, Deep Space Orbit VLEO ORBIT (option) Low Earth Orbit (standard) Low Earth Orbit (standard) Low Earth Orbit (standard) (standard) (as applicable) Pegasus, Taurus, Minotaur Series, Pegasus, Taurus, Minotaur Pegasus, Taurus, Launch Vehicle Minotaur Series, Taurus Falcon 9, EELV Most Secondary Rideshares Series, ESPA Compatible Minotaur Series Additional Selected Reduncancy or Block Lifetime 3+ years 3 to 5+ years 3 to 5+ years 3 to 5+ years Redundancy for > 5 years Mission Specific Hydrazine for orbit Hydrazine for orbit Hydrazine for orbit Propulsion Optional maintenance and deorbit maintenance and deorbit maintenance and deorbit Propulsion, larger tanks Development Schedule Ready for Payload Integration Ready for Payload Integration Ready for Payload Integration Ready for Payload Integration Ready for Payload Integration at ATP + 6 Months at ATP + 18 Months at ATP + 18 Months at ATP + 18 Months at ATP + 18 Months Science Grade GPS for precision Additional Options timing and emphemeris.