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 2017. 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 Swift 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 processes.

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

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 103 kg
Science Data Downlink 105 Mbps (X-band) or
8 Mbps (high-rate S-band)
Science Data Storage 16 Gbytes (redundant and expandable)
Pointing Knowledge 25 arcsec (1 sigma) all 3 axes
Pointing Control 36 arcsec (1 sigma) all 3 axes
Pointing Stability (Jitter) 1.5 arcsec/sec
Orbital Position Knowledge 10 m
Mission Design Life 7 years
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

Platform Description

Attitude Control System 3-axis control with reaction wheels, magnetorquers, and a star tracker
Batteries Li-ion cells providing 15 Ah capacity
Solar Arrays Triple-junction GaAs cells, total area 1.15 m2
Main Bus Voltage Range 22–34 V
C&DH Bus Architecture Dual-redundant controller area network (CAN) bus
Communication Up/Downlink S-band uplink/S-band downlink (expandable to X-band)
Structure Aluminum and aluminum-skinned honeycomb panels
Propulsion None (expandable to include gas propulsion)
Delta V Dependent on the propellant used
Thermal Control Primarily passive, plus limited use of heaters


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