Ms. Dana Turse Profile

Dana Turse

at Redwire Space Solutions LLC

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Publications (2)

SPIE Journal Paper | 22 August 2024 Open Access

SALTUS probe class space mission: observatory architecture and mission design

Leon Harding, Jonathan Arenberg, Benjamin Donovan, Dave Oberg, Ryan Goold, Bob Chang, Christopher Walker, Dana Turse, Jim Moore, Jim Pearson, John Kidd, Zach Lung, Dave Lung

JATIS, Vol. 10, Issue 04, 042303, (August 2024) https://doi.org/10.1117/12.10.1117/1.JATIS.10.4.042303

KEYWORDS: Space operations, Observatories, Design, Data storage, Equipment, Cryogenics, James Webb Space Telescope, Reflectors, Control systems, Sun

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We describe the space observatory architecture and mission design of the Single Aperture Large Telescope for Universe Studies (SALTUS) mission, a National Aeronautics and Space Administration (NASA) Astrophysics Probe Explorer concept. SALTUS will address key far-infrared science using a 14-m diameter <45 K primary reflector (M1) and will provide unprecedented levels of spectral sensitivity for planet, solar system, and galactic evolution studies and cosmic origins. Drawing from Northrop Grumman’s extensive NASA mission heritage, the observatory flight system is based on the LEOStar-3 spacecraft platform to carry the SALTUS Payload. The Payload is comprised of the inflation control system, sunshield module (SM), cold corrector module (CCM), warm instrument electronics module, and primary reflector module (PRM). The 14-m M1 is an off-axis inflatable membrane radiatively cooled by a two-layer sunshield (∼1000 m2 per layer). The CCM corrects for residual aberration from M1 and delivers a focused beam to two instruments—the High-Resolution Receiver (HiRX) and SAFARI-Lite. The CCM and PRM reside atop a truss-based composite deck that also provides a platform for the attitude control system. The SALTUS 5-year mission lifetime is driven by a two-consumable architecture: the propellant system and the inflation control system. The core interface module (CIM), a multi-faceted composite truss structure, provides a load path with high stiffness, mechanical attachment, and thermal separation between the Payload and spacecraft. The SM attaches outside the CIM with its aft end integrating directly to the bus. The spacecraft maintains an attitude off M1’s boresight with respect to the Sun line to facilitate the <45 K thermal environment. SALTUS will reside in a Sun–Earth halo L2 orbit with a maximum Earth slant range of 1.8 million km, thereby reducing orbit transfer delta-v. The instantaneous field of regard provides two continuous 20 deg viewing zones around the ecliptic poles, resulting in full sky coverage in 6 months.

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SPIE Journal Paper | 6 January 2021 Open Access

Demonstration of deployment repeatability of key subsystems of a furled starshade architecture

Manan Arya, Flora Mechentel, David Webb, John Steeves, Doug Lisman, Stuart Shaklan, Samuel Bradford, Eric Kelso, Kenzo Neff, Amanda Swain, Andrei Iskra, Neal Beidleman, John Stienmier, Gregg Freebury, Andrew Tomchek, Tayler Thomas, Craig Hazelton, Kassi Butler, Kamron Medina, Mike Pulford, Larry Adams, David Hepper, Dana Turse

JATIS, Vol. 7, Issue 02, 021202, (January 2021) https://doi.org/10.1117/12.10.1117/1.JATIS.7.2.021202

KEYWORDS: Tolerancing, Computer programming, Error analysis, Thermal effects, Temperature metrology, Exoplanets, Opacity, Interfaces, Statistical analysis, Aluminum

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