Scalable, Lightweight, Low-Cost Aero/Electrodynamic Drag Deorbit Module

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$99,980.00
Award Year:
2011
Program:
SBIR
Phase:
Phase I
Contract:
NNX11CD35P
Award Id:
n/a
Agency Tracking Number:
104459
Solicitation Year:
2010
Solicitation Topic Code:
S4.01
Solicitation Number:
n/a
Small Business Information
WA, Bothell, WA, 98011-8808
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
877425330
Principal Investigator:
Robert Hoyt
Principal Investigator
(425) 486-0100
hoyt@tethers.com
Business Contact:
Robert Hoyt
Business Official
(425) 486-0100
hoyt@tethers.com
Research Institute:
Stub




Abstract
The proposed effort will develop the "Terminator Tape Deorbit Module", a lightweight, low-cost, scalable de-orbit module that will utilize both aerodynamic drag enhancement and electrodynamic drag to rapidly remove small satellites from LEO altitudes, enabling compliance with orbital lifetime restrictions such as NSS 1740.14 and DoD Instruction 3100.12, Sec. 6.4. Unlike de-orbit devices that rely solely upon aerodynamic drag, which provide no significant reduction in the probability of collision with another space object during orbital lifetime, the Terminator Tape's generation of electrodynamic drag can dramatically reduce the Area-Time-Product of the system, minimizing chances of debris-generating collisions. The proposed Terminator Tape design utilizes space-qualified materials, requires only standard pyro signals from the host spacecraft for activation, requires no internal avionics, and its deployment method has already been demonstrated successfully in microgravity. It can also accommodate installation of solar cells or other devices on its surface to minimize footprint impacts on small spacecraft. It can also be configured to serve as a multifunctional element, acting as multi-layer insulation (MLI). Positive control of de-orbit timing is provided through a simple actuation requiring only a pyro signal. The device is readily scalable from picosats up to large spacecraft, and in the proposed effort, we will develop a flight ready prototype sized for testing on a CubeSat as well as detailed designs of modules sized for 15 kg nanosats and 100 kg microsats. We will also investigate and test innovative methods for maximizing electrodynamic current, including photoemissive and low-work-function thermoelectric materials. These Phase I efforts will prepare us to perform a flight test on a CubeSat or other low cost platform in the Phase II effort.

* information listed above is at the time of submission.

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