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Completed TRL 3 (started at 3, targeting 4)
NASA is currently studying an Asteroid Redirect and Utilization Mission using a robotic spacecraft to rendezvous, capture and steer a small asteroid to cislunar Space. In order to obtain a higher-fidelity understanding of mission/system dynamics, a proof of concept capture mechanism and testbed are required. During 2013, JPL internal funding was used to fabricate a basic testbed to study the two key issues that cannot be addressed purely through computer simulation: the possible binding of cinch-winch cords in the fabric of a capture bag and to realistically simulate the motion of the asteroid relative to the capture spacecraft by measuring actual forces (including fabric-snag forces) applied by the capture system to the asteroid. The prototype capture mechanism will be used to evaluate mission feasibility and research and development towards the flight capture mechanism design. A hardware testbed will be used to evaluate the capture mechanism design and to aid mission planning by iterating on a variety of mission scenarios. These simulated scenarios will help to reduce risk by studying the actions required to de-tumble, de-spin and safely transfer a small asteroid to a stable orbit in near-Earth space.
This task will extend an Asteroid Capture Testbed fabricated under JPL internal funding in 2013 and will simulate subscale asteroid capture physics with a prototype capture mechanism. The testbed will consist of a robotic arm instrumented with 6-axis force torque sensors that holds a rotating scaled asteroid, such that a full dynamic simulation of asteroid capture can be applied. A prototype capture mechanism will be designed, fabricated and tested under various mission scenarios with the simulator to insure forces on the spacecraft and capture bag are below design thresholds. Lessons-learned will inform a second-generation capture bag with improved (and more flight-realistic) fabric, inflatable structure, and cinch-winches.
This task will provide NASA with the capability to test the design of prototype asteroid capture mechanisms and their performance in capturing a small rotating asteroid mockup on a physical testbed, which will include simulation of subscale asteroid capture physics with a prototype capture mechanism.
The test-bed’s robotic arm will be capable of holding and rotating a scaled asteroid mockup, will be instrumented with 6-axis force torque sensors so that a full dynamic simulation of asteroid capture can be applied.
A prototype capture mechanism will be designed, fabricated and tested under various mission scenarios with the simulator to insure forces on the spacecraft and capture bag are below design thresholds. Lessons-learned will inform a second-generation capture bag with improved (and more flight-realistic) fabric, inflatable structure, and cinch-winches.
The final results of this technology development will be delivered to Asteroid Redirect Mission (ARM) planners. These deliveries will provide engineering data that will inform decisions as mission concepts mature.
Very early development of asteroid technologies as an R&D scaled effort has the potential to greatly reduce development cost and schedule, once its mission requirements are set.
Lessons-learned from the capture bag tests will inform a second-generation capture bag with improved (and more flight-realistic) fabric, inflatable structure, and cinch-winches.
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