Special Coverage

Iodine-Compatible Hall Effect Thruster
Precision Assembly of Systems on Surfaces (PASS)
Development of a Novel Electrospinning System with Automated Positioning and Control Software
2016 Create The Future Design Contest Open For Entries
Clamshell Sampler
Shape Memory Alloy Rock Splitter
Deployable Extra-Vehicular Activity Platform (DEVAP) for Planetary Surfaces
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Orion Heat Shield Thermal Mapping Tool

The Orion Heat Shield Mapping Tool collects data from a set of output files from various re-entry thermal response codes, interpolates the data, and maps the analysis code data onto a finely meshed finite element model.

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Distributed User Interface Management System for Interactive Collaborative Environments

This technology can be used in applications with complex user interfaces, such as control rooms, emergency and combat operations, and telemedicine. John F. Kennedy Space Center, Florida The Ground Systems Development and Operations (GSDO) Smart Firing Room Project aims to create a firing room using cutting-edge technologies of today that are expected to be the state-of-the-art for the 2020s. One aspect of this project is providing a seamless Interactive Collaborative Environment (ICE) across a diverse array of user-facing devices — numerous screens of varying sizes, personal mobile devices, and natural user interface (NUI) sensors for multi-touch, gesture, and voice inputs. Applications accessible through the ICE are expected to provide Distributed User Interfaces (DUIs) that support collaborative features such as sharing applications with remote users, multi-user interaction for collaborative editing, and modular User Interfaces (UIs) to support customized workspaces spread across multiple devices. Using current technologies, developing an application with a DUI supporting such a wide variety of platforms is extremely costly due to the tight coupling between UIs, host platforms, and the application logic.

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Design Reference Mission Tool for Exoplanet Starshade Mission Study

This approach is nearly optimal for each observational tier. NASA’s Jet Propulsion Laboratory, Pasadena, California The Design Reference Mission (DRM) tool was developed to support the Exo-Starshade (Exo-S) Science and Technology Definition Team for modeling both the Dedicated (30-m starshade, 1.1-m telescope) and Rendezvous (34-m starshade, 2.4-m telescope) missions. The DRM describes the sequence of observations to be performed and estimates the number of planets that will be detected and characterized. It is executed with a MATLAB-based tool developed for the Exo-S Study.

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Data Parallel Line Relaxation Code (DPLR) Version 3.05

Ames Research Center, Moffett Field, California The Reacting Flow Environments branch at NASA ARC is interested in characterizing the aerothermal environment of three main classes of problem: planetary entry vehicles, reusable launch vehicles (RLVs), and arc-jet (or other ground test) flow simulations. Each of these problem classes has unique physical characteristics, the understanding of which is at the cutting edge of the field. Proper modeling of the relevant physics is required to accurately simulate the aerothermal environments of these problem classes. These include, but are not limited to, chemical non-equilibrium, thermal non-equilibrium, shock layer radiation, surface catalycity, and thermal protection system material interaction with the aerothermal environment.

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Front End Data System (FEDS) Version 10.0

Goddard Space Flight Center, Greenbelt, Maryland In traditional missions at NASA, ground systems were normally custom-built for each project. Additionally, there would be separate ground systems for each part of the spacecraft as well as a totally separate ground system for mission operations. Each of these generally interfaced through non-standard protocols. These ground systems were very expensive to develop, required expensive custom hardware, and required a large investment of time in order to verify the plethora of interfaces between the different ground systems. Non-standard interfaces between various components required extensive engineering and testing efforts.

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Link Complexity Scheduling Algorithm

NASA’s Jet Propulsion Laboratory, Pasadena, California NASA’s Deep Space Network (DSN) provides communication and other services for planetary exploration for both NASA and international users. The DSN operates antennas at three complexes in California, Spain, and Australia, with the longitudinal distribution of the complexes enabling full sky coverage and generally providing some overlap in spacecraft visibility. Beginning in 2018, the DSN will be transitioning to a remote operations paradigm where local dayshift operators at each complex will be preparing and staffing the links (or contacts) for all antennas in the DSN. In addition, the number of simultaneous links an operator will be required to support will increase from two to three. Without tools to manage the increased link complexity, there is a risk that operators will be overloaded.

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BUMPER-CEV Micrometeoroid and Orbital Debris Risk Assessment Code Rev. A

Lyndon B. Johnson Space Center, Houston, Texas BUMPER-CEV Version 1.71 is used to perform micrometeoroid/orbital debris (MMOD) risk assessments for the Orion Multi-Purpose Crew Vehicle (MPCV) spacecraft. BUMPER is the primary risk analysis program used by NASA to provide for reliable and safe operations of spacecraft exposed to MMOD impacts. When provided with the physical shape and orbital parameters of a spacecraft, and a clear definition of failure, BUMPER calculates the risk of failure from MMOD impacts for all surfaces on a vehicle. Thousands of hypervelocity impact tests have been performed on representative samples of dozens of spacecraft shields and subsystems, thermal protection system (TPS) materials, and other spacecraft components to determine MMOD impact parameters at the failure limits of the various subsystems. The resulting verified ballistic limit equations and damage formulas are coded in BUMPER. Different versions of BUMPER have been created for ISS (International Space Station), Shuttle, and other spacecraft that differ in the ballistic limit subroutines embedded in the code, as well as the user prompts and other code to control execution and output of the code.

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