CYCLOPS

NASA Johnson Space Center’s (JSC) International Space Station (ISS) and Engineering communities in collaboration with the Department of Defense (DoD) Space Test Program (STP) developed a dedicated 50-100 kg class ISS small satellite deployment system. The system is known as Space Station Integrated Kinetic Launcher for Orbital Payload Systems (SSIKLOPS or “CYCLOPS”).  With CYCLOPS, launching of 50-100kg is now possible. Cyclops fills the payload deployment gap between small cubesat launchers and major payloads enabling a whole new range of payload possibilities.

Craig Technologies Aerospace Solutions (Craig) provides turnkey services to manage and execute the successful integration and on-orbit operations of satellite payloads using the Space Station Integrated Kinetic Launcher for Orbital Payload Systems (SSIKLOPS or “CYCLOPS”). Cyclops fills the payload deployment gap between small cubesat launchers and major payloads by supporting the microsatellite market (50-100kg).

Craig’s offerings include operation, engineering, and manufacturing to provide full life-cycle payload support. This Mission Operations and Integration expertise includes the capabilities of the Craig ISS flight test platform which supports commercial payloads related to science, STEM, art and entertainment, data or any other commercial endeavor requiring an exterior location in unpressurized space.

Cyclops  utilizes NASA’s ISS resupply vehicles to launch small sats to the ISS in a controlled pressurized environment in soft stow bags. The satellites are then processed through the ISS pressurized environment by the astronaut crew allowing satellite system diagnostics prior to orbit insertion. Orbit insertion is achieved through use of the Japan Aerospace Exploration Agency’s Experiment Module Robotic Airlock (JEM Airlock), and one of the ISS Robotic Arms.

CTAS provides complete end to end advocacy and support (we do all the hard lifting, You provide the data package, we create the safety package)

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Satellite Interfaces/Requirements

The interface between Cyclops and the satellite attaches to the satellite via 3 bolts. It has a mass of approximately 0.11 kg (0.25 lb).

Structural/Mechanical Interface The satellite mounting interface to the experiment attachment fixture shall meet the Cyclops specified requirements
Survivability The satellite shall be capable of functioning after exposure to the external environment for no less than 10 hours unpowered
Volume The satellite shall meet the defined allowable envelope

Cyclops interfaces with the JEM Airlock (AL) Slide Table, the ISS Robotic Arms, and the deployable satellites. It has been designed to be able to be utilized for the duration of the ISS mission for deployments of satellites. It is roughly a 127 cm L x 61 cm W x 7.6 cm H (50” L x 24” W x 3” H) platform capable of deploying satellites of any geometry up to 100 kg (220 lb) in size contingent upon the satellites meeting all Cyclops and ISS safety requirements.

Ballistic Number (BN) Satellite shall have a ballistic number of 100 kg/m2 or less. BN = Mass / (Frontal Area * Cd) where Cd=2.0
Center of Gravity (CG) Satellite shall meet the defined Cyclops’ defined CG corridor.*
Deployment Force The satellite shall be able to withstand the maximum force, 35lbf, applied from Cyclops at the deployment interface during deployment.
Electrical Bonding The satellite shall provide a Class S electrical bonding path to Cyclops.
Impact The satellite shall meet the ISS robotic arm potential transfer impact loads without creating debris
Inhibit Switch Contact Surfaces The satellite shall maintain keep out zones with its inhibit switch locations and contact surfaces.
Mass Satellite shall meet the mass of 100kg or less (includes the mass of the experiment attachment fixture).
Safety The satellite shall meet all ISS Payload Safety requirements.
Structural/Mechanical Interface The satellite mounting interface to the experiment attachment fixture shall meet the Cyclops specified requirements
Survivability The satellite shall be capable of functioning after exposure to the external environment for no less than 10 hours unpowered.
Volume The satellite shall meet the defined allowable envelope.
*X
(in)
Y
(in)
Z
(in)
-1.00 to +1.00 2.00 to 14.20 -1.00 to +1.00

Cyclops User Maximum Envelope

The deployable payload shall be contained within the Cyclops deployable payload envelope as shown below, Cyclops Deployable Payload Envelope.

Cyclops Satellite Launch Process

Once a satellite deployment has been scheduled, Cyclops will be removed from its on-orbit stowage bag and placed on the JEM Airlock Slide Table. The deployable satellite will be placed on Cyclops. Cyclops and its attached satellite will be processed through the JEM Airlock to the ISS external environment.

Upon completion of JEM Airlock operations Cyclops and its attached satellite will be grasped by either the ISS robotic arm or the JEM robotic arm and transported to its predetermined deployment position.

Cyclops will then deploy the satellite away from the ISS. After successful deployment of the satellite Cyclops will be maneuvered back to the JEM Airlock and secured on the JEM Airlock Slide Table. JEM Airlock operations will be conducted bringing Cyclops back inside the ISS where it will be removed from the JEM Airlock Slide Table and placed in its on-orbit stowage bag.

SpinSat Launched from Cyclops on ISS

WHY LAUNCH WITH CRAIG TECHNOLOGIES AND CYCLOPS?

Cyclops provides small satellites the infrastructure to be deployed from the ISS into orbit with minimal technical, environmental, logistical, and cost challenges

LOW COST

FREQUENT FLIGHT OPPORTUNITIES

SMALL SATELLITE FOCUSED

COMPLETE END TO END ADVOCACY AND SUPPORT

Learn more about how Craig can launch your satellite or experiment by clicking HERE