Development of a Multifunctional Inflatable Structure for the PowerSphere Concept

Simburger, Edward J.; Matsumoto, James H.; Lin, John; Rawal, Shristi; Peterson, Todd; Kerslake, Thomas W.; Knoll, Carl; Perry, Alan R.; Barnett, Dave; Curtis, H. B.; Giants, Thomas W.

doi:10.2514/6.2002-1707

Cited by 13 publications

(5 citation statements)

References 2 publications

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“…At the same time, tracking planar solar array systems are mass prohibitive for this class of microsat. An elegant solution to this power pinch challenge is the PowerSphere (Lin, et al, 2003 andSimburger, et al, 2002) concept shown in Figure 1. The PowerSphere space-inflatable, geodetic solar array provides attitudeindependent microsat power with very low mass and efficient launch packaging to enable microsat constellation deployment from a single carrier spacecraft.…”

mentioning

confidence: 99%

Durability of ITO-MgF2 Films for Space-Inflatable Polymer Structures

Kerslake

Waters²,

Schieman

et al. 2003

1st International Energy Conversion Engineering Conference (IECEC)

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mentioning

confidence: 99%

Durability of ITO-MgF2 Films for Space-Inflatable Polymer Structures

Kerslake

Waters²,

Schieman

et al. 2003

1st International Energy Conversion Engineering Conference (IECEC)

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“…By assuming Mars' atmospheric pressure of 4-5mbar and low gravity, the deployment using residual air inflation will be sufficient. The available inflatable volume can be further increased by either adding a coating that undergoes a phase-change in vacuum conditions [17] or a powder that sublimes into gas to provide additional vapor pressure to the inflating structure [18]. In order to adapt heliotropism to these space membranes, micro pumps were added between two adjacent cells to create a pressure difference between them resulting in a volume variation of the two cells.…”

Section: Inflatable Smart Structuresmentioning

confidence: 99%

Inflatable structures for Mars Base 10

Sinn

Doule²

2012

42nd International Conference on Environmental Systems

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A permanent manned settlement on the Martian surface requires the use of advanced technology concepts in order to become technically and financially feasible. The former developed Mars Base 10 concept incorporates novel ideas, increasing the feasibility of a continous human base on Mars. The most advanced feature of the MB10 design is the concept of increasing the habitable space of the Mars base once landed with an inflatable torus like structure. This paper gives an overview on the MB10 design and has its primary focus on the deployment of the inflatable structure. The deployment simulations show the final inflated shape of the MB10 concept on Mars from an un-inflated initial shape on Earth. The deployment strategy, simulations and rigidization techniques are discussed to provide a conceptual solution for large inflatable components of the MB10 habitat. Further applications of secondary inflatable smart structures are presented as well. These secondary structures are self deploying at the Martian ambient pressure which results in low storage volume and mass. These structures are well-suited to carry on for astronauts on EVAs for example. NomenclatureEDL = Entry Descent Landing EVA = Extra Vehicular Activity EVOH = Ethylene Vinyl Alcohol FEM = Finite Element Method IMOD = Inflatable Module (Thales Study) ISRU = In Situ Resource Utilisation LEO = Low Earth Orbit LMO = Low Mars Orbit MB10 = Mars Base 10 NASA ARC = NASA Ames Research Center PA-NYLON = Polyamide PE = Polyethylene PVDC = Polyvinylidene Chloride PU = Polyurethane SAM = Self-inflating Adaptive Membrane SMP = Shape Memory Polymer TRL = Technology Readiness Level UV = Ultraviolet

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“…The flex circuit is constructed of copper in a custom designed routing pattern, and then sandwiched in a Kapton® insulation layer. The flex circuit then serves as the primary power distribution system between the solar cells and the spacecraft 1,2,3 . Flex circuit material is the best candidate for the wiring harness because it allows for low force deployment of the solar cells by the inflatable hinges on the PowerSphere.…”

Section: Introductionmentioning

confidence: 99%

“…Flex circuit material is the best candidate for the wiring harness because it allows for low force deployment of the solar cells by the inflatable hinges on the PowerSphere. An additional frame structure, fabricated and assembled by ILC Dover, will reinforce the wrap around contact-flex blanket connection, thus providing a mechanically robust solar cell interconnect for the PowerSphere multifunctional program 4,5 . The PowerSphere team will use the wraparound contact design approach as the primary solution for solar cell integration and the flex blanket for power distribution.…”

Section: Introductionmentioning

confidence: 99%