OTB-2: Orbital Test Bed Mission
Surrey’s second orbital test bed mission OTB-2 is dedicated to carrying demonstration payloads, subsystems, and equipment into low-Earth orbit aboard a flight-proven satellite bus. Surrey is currently planning to fly its own experimental optical payload on OTB-2.
The Surrey hosted payload business model is unique in the industry and continues its tradition of providing cost-effective access to space. The ride-share concept appeals to organizations that need to test satellite components or payload concepts in space with low risk and at a fraction of the cost of dedicated missions.
We have completed the flight manifest for our OTB mission now scheduled for launch in 2016. The first spacecraft integrated at the satellite facility in Englewood, Colorado, OTB will carry five experimental payloads for Surrey, NASA JPL, Air Force Research Laboratory, and academic institutions. Similar to OTB, OTB-2 is based on the SSTL-150 platform flown on numerous scientific and operational missions.
OTB-2 will have the baseline capability to support a payload suite of 50 kg and 50 W; however, we can expand and customize this baseline based on customer demand.
We will manufacture OTB-2 at our facility in Colorado where our engineering personnel adhere to Surrey satellite development, integration and test refined during 43 successful missions spanning three decades.
If you would like us to perform an assessment of your payload’s mission and operational requirements, please download and complete our Candidate Payload Requirements Form or contact Brent Abbott at email@example.com.
Download the OTB-2 datasheet
|Baseline Mission Compatibility
|Orbit Average Payload Power
||50 W (100 W peak) EOL
(expandable with the addition of deployable solar panels)
|Baseline Payload Mass
||50 kg (expandable)
|Bus Dry Mass
|Science Data Downlink
||105 Mbps (X-band) or
8 Mbps (high-rate S-band)
|Science Data Storage
||16 Gbytes (redundant and expandable)
||25 arcsec (1 sigma) all 3 axes
||36 arcsec (1 sigma) all 3 axes
|Pointing Stability (Jitter)
|Orbital Position Knowledge
|Mission Design Life
|Compatible Launch Vehicles
||Falcon, Atlas, Delta, Athena, and other launch vehicles
|Types of Orbits Available
||LEO 400 km to 1000 km, any inclination
|External Payload Volume
||730 x 455 x 774 mm
|Internal Payload Volume
||279.5 x 231.5 x 252.5 mm
|Attitude Control System
||3-axis control with reaction wheels, magnetorquers, and a star tracker
||Li-ion cells providing 15 Ah capacity
||Triple-junction GaAs cells, total area 1.15 m2
|Main Bus Voltage Range
|C&DH Bus Architecture
||Dual-redundant controller area network (CAN) bus
||S-band uplink/S-band downlink (expandable to X-band)
||Aluminum and aluminum-skinned honeycomb panels
||None (expandable to include gas propulsion)
||Dependent on the propellant used
||Primarily passive, plus limited use of heaters
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