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Controlled in vitro studies of cells and tissues under the conditions of microgravity (simulated on Earth, or actual in space) can improve our understanding of gravity sensing, transduction, and responses in living cells and tissues. This paper discusses the scientific results and practical implications of three NASA-related biotechnology projects: ground and space studies of microgravity tissue engineering (JSC-Houston), and the development of the cell culture unit for use aboard the International Space Station (ARC-Ames).

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SEHP is a novel, light, and portable material to control EEI effectively. It does not require another person for compression nor does it compromise the circulation. As EEI occurs with alarming frequency in the battlefield, SEHP may not only present an optimal hemostatic method for military applications but also be useful in the civilian prehospital setting.

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Nomenclature α = function of Technology Readiness Level (TRL) β = complexity of each connection between pairs of components γ = 1/n Π i = expected profit for missions of type i A = Design Structural Matrix C AIT = assembly, integration, and test cost C D = development cost of each satlet variant C NR = non-recurring development costs C PMSE = aggregate system level PMSE estimate C i R = recurring costs (manufacturing costs, operations costs, and launch costs) C 1 = complexity due to number and flight readiness of components C 2 = complexity due to pair-wise component interactions Distribution Statement A: Approved for Public Release, Distribution Unlimited.2 C 3 = complexity due to topology of system architecture and complexity of integration E(A) = graph energy of the DSM m = number of interfaces m i = number of specific missions of type i resulting from market projection n = number of components Ps i = probability of success of architecture in providing capabilities for mission type i R i = nominal maximum revenue from mission type i AFS = Aurora Flight Sciences AIT = assembly, integration and test CER = cost-estimating relationship DSM = Design Structural Matrix IMCE = Integrated Model-Centric Engineering JPL = Jet Propulsion Laboratory PMSE = Project Management and Systems Engineering PODS = Payload Orbital Delivery System Satlet = cellularized satellite building blocks SSCM = Small Satellite Cost Model SysML = Systems Modeling Language TDRS = Tracking and Data Relay Satellites TRL = Technology Readiness LevelThis paper describes a model-based architectural design and analysis approach developed to support the initial design of cellularized spacecraft architectures, such as the DARPA Phoenix program. As one of its technical pillars, the Phoenix program is aiming to construct new "aggregate satellites" on-orbit by combining cellularized building blocks referred to as "satlets." A critical question that needs to be addressed is "should there be a single satlet type that provides all the required satellite functionality, or should there be multiple specialized types"? Our initial approach includes capture of satlet design and aggregated satellite design trade spaces using the Systems Modeling Language (SysML), specification of requirements as parametric constraints on the set of acceptable solutions, automated search of this trade space and generation of paretooptimal satlet architectures that satisfy mission requirements while maximizing a specified value metric. The initial results of our analysis suggest that a cellularized architecture should include sets of more specialized satlets: a central satlet type that includes components for computation and data processing, centralized attitude sensing and ground communication, a satlet type that provides actuation in the form of either reaction wheels or thrusters, a payload satlet type to provide any specialized functionality for a particular mission (e.g., an RF transceiver), and finally, "connector" satlet types that provide structural, mechanical and power inte...

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This paper describes an architectural concept for a Small Lunar Exploration and Delivery System to operate as a platform for emplacing payloads into lunar orbit and onto the lunar surface, while providing mobility for surface exploration, science, and infrastructure. The concept leverages emerging services that are capable of delivering payloads to Low Earth Orbit (LEO), while utilizing new and old technologies to build a platform for transfer to Low Lunar Orbit (LLO). Advances and miniaturization in avionics, navigation, power, and propulsion systems enable a unique opportunity to develop a system that is both capable of landing on the lunar surface and providing surface mobility with the same system. Nomenclature deltaV = change in velocity, m/s Isp = specific impulse, s