Special Coverage

Applying the Dynamic Inertia Measurement Method to Full-Scale Aerospace Vehicles
Method and Apparatus for Measuring Surface Air Pressure
Fully Premixed, Low-Emission, High-Pressure, Multi-Fuel Burner
Self-Healing Wire Insulation
Thermomechanical Methodology for Stabilizing Shape Memory Alloy (SMA) Response
Space Optical Communications Using Laser Beams
High Field Superconducting Magnets

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.

Posted in: Briefs, TSP, Electronics & Computers, Information Sciences


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.

Posted in: Briefs, Electronics & Computers, Information Sciences


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.

Posted in: Briefs, TSP, Electronics & Computers


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.

Posted in: Briefs, TSP, Electronics & Computers


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.

Posted in: Briefs, Electronics & Computers


Advanced Numerical Integration Techniques for High-Fidelity SDE Spacecraft Simulation

Goddard Space Flight Center, Greenbelt, Maryland Simulation study is an integral part of the validation of navigation algorithms for spacecraft. While it is possible to come up with an estimate of a navigation algorithm’s performance with a low-fidelity system model, the mathematical analysis is intractable for higher-fidelity models that include fuel slosh, flexible booms, sensor saturation, etc. Thus simulation study is a vital step in validating navigation algorithms before an actual satellite is launched.

Posted in: Briefs, TSP, Electronics & Computers, Software


Launch Environment Water Flow Simulations Using Smoothed Particle Hydrodynamics

This method has been used in applications involving ocean modeling, volcanic lava, sloshing, and fuel pumps.One of the crucial ground structures employed at the launch pad during the Space Shuttle program is the rainbird nozzle system, whose primary objective is to suppress acoustic energy generated by the launch vehicle during pad abort and nominal operations. It is important that the rainbird water flow does not impinge on the rocket nozzles and other sensitive ground support elements. For the new Space Launch System (SLS) vehicle, the operation is similar, regardless of the new mobile launcher and new engine configurations. The goal of the rainbird nozzle system remains sound suppression (SS), and the rocket engines still cannot get wet. However, the rearrangement of the rainbird water system for the SLS mobile launcher locates the rainbirds closer to the first-stage rocket engines, which are positioned above the exhaust hole. The close proximity of the rainbird nozzle system could potentially cause vehicle wetting during liftoff.

Posted in: Briefs, TSP, Electronics & Computers, Information Sciences, Software


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