550909 research outputs found
Sort by
Space Communications and Navigation
Get PDFThis project investigates upgrading multiple areas with MTRS equipment at McMurdo and at White Sands, to raise its efficiency in supporting the Soil Moisture Active Passive (SMAP) mission and future high data rate missions.This study is important because improving MTRS may significantly reduce costs and prevent the possibility of an unplanned long downtime. MTRS has difficulty supporting the SMAP mission because of the availability of TDRS. When TDRS is unavailable, the passes must be moved to an expensive commercial service. Coverage analysis of the MTRS and TDRS is shown in this presentation
Design and Testing of the CubeSat Form Factor Thermal Control Louvers
Get PDFAs CubeSat and SmallSat missions increase in complexity and power consumption they present innate thermal challenges. Science instruments may require thermal stability while a variety of factors such as high-powered components, sunlight and shadow on orbit, or tight spacecraft layout may produce a wide range of temperatures. The CubeSat Form Factor Thermal Control Louvers are a passive method of stabilizing the thermal environment inside of small spacecraft via miniature thermal louvers. These louvers are a patented design, with a technology demonstration version of the louvers operating correctly in flight on the Dellingr CubeSat in 2018. This paper will describe the methods used to develop and test this technology, as well as the results obtained and how this technology may be used in CubeSat and SmallSat missions
Transfer Trajectory Options for Servicing Sun-Earth-Moon Libration Point Missions
Get PDFFuture missions to the Sun-Earth Libration L1 and L2 regions will require scheduled servicing to maintain hardware and replenish consumables. While there have been statements made by various NASA programs regarding servicing of vehicles at these locations or in Cis-lunar space, a practical transfer study has not been extensively investigated in an operational fashion to determine the impacts of navigation and maneuver errors. This investigation uses dynamical systems and operational models to design transfer trajectories between the Sun-Earth Libration region (QuasiHalo orbit) and the Earth-Moon vicinity (Distant Retrograde Orbit, QuasiHalo Orbit, Halo Orbit, and Near Rectilinear Halo Orbit). We address the total V cost of transfers and operational considerations between each pair of locations using a Monte Carlo analysis
Cracking Failures in Ceramic Capacitors and the Existing Screening and Qualification Procedures
Get PDFThis presentation gives a review of recent project failures caused by cracks in ceramic capacitors and discusses deficiencies of the existing screening and qualification procedures that can reveal the propensity to cracking and effects of soldering stresses
L2 Station Keeping Maneuver Strategy for the James Webb Space Telescope
Get PDFThe station-keeping plan for the James Webb Space Telescope is zero velocity in the x-component at the fourth successive crossing of the XZ plane of the rotation libration point frame. A differential corrector is employed to determine the necessary delta-v. Maneuvering along the position component of the stable eigenvector of the monodromy matrix produces a minimum delta-v solution. The techniques developed to determine the minimum maneuver direction in a full ephemeris model, along with strategies to cope with the attitude constraints imposed by the sunshield that prevents the ability to maneuver along the stable eigenvector, are examined in this study
Model Intercomparison of Maize Response to Climate Change in Low-Input Smallholder Cropping Systems
Get PDFSmallholder farming systems are characterized by poor soil fertility and low agricultural input use; process-based crop growth models can help quantifying the potential impact of climate change on productivity in these systems.With limiting conditions (water and nutrients), crop models need to rigorously account for soil water, nutrient, CO2, and temperature interactions when simulating climate change effects
New Moon Explorer Mission Concept
Get PDFNew Moon Explorer (NME) is a smallsat reconnaissance mission concept to explore Earths New Moon, the recently discovered Earth orbital companion asteroid 469219 Kamooalewa (formerly 2016HO3), using solar sail propulsion. NME would determine Kamooalewas spin rate, pole position, shape, structure, mass, density, chemical composition, temperature, thermal inertia, regolith characteristics, and spectral type using onboard instrumentation. If flown, NME would demonstrate multiple enabling technologies, including solar sail propulsion, large-area thin film power generation, and small spacecraft technology tailored for interplanetary space missions. Leveraging the solar sail technology and mission expertise developed by NASA for the Near Earth Asteroid (NEA) Scout mission, affordably learning more about our newest near neighbor is now a possibility. The mission is not yet planned for flight
MUSTANG Applications
Get PDFReducing nonrecurring cost and shortening the build schedule for space qualified avionics has been a recurring theme in Space Industry. The NASA Goddard Space Flight Center has leverage its heritage flight qualified design and developed a portfolio of modular avionics comprised of 22 different board designs in a form factor named MUSTANG (Modular Unified Space Technology Avionics for Next Generation) that can be utilized in a variety flight applications. Since the design has no backplane, the modules can be mixed and match to meet the needed requirements. The MUSTANG form factor is sized to fill the void between 3U and 6U form factor and with flexibility to adapting the design without relaying out the boards
A Study of the 20 Day Superorbital Modulation in the High-Mass X-Ray Binary IGR J16493-4348
No full textWe report on Nuclear Spectroscopic Telescope Array (NuSTAR), Neil Gehrels Swift Observatory(Swift) X-ray Telescope (XRT), and Swift Burst Alert Telescope (BAT) observations of IGR J16493-4348, a wind-fed supergiant X-ray binary showing significant superorbital variability. From a discrete Fourier transform of the BAT light curve,we refine its superorbital period to be 20.0580.007 days. The BAT dynamic power spectrum and a fractional root mean square analysis both show strong variations in the amplitude of the superorbital modulation, but no observed changes in the period are found. The superorbital modulation is significantly weaker between MJD 55,700 and MJD 56,300. The joint NuSTAR and XRT observations, which were performed near the minimum and maximum of one cycle of the 20 day superorbital modulation, show that the flux increases by more than a factor of two between superorbital minimum and maximum. We find no significant changes in the 3-50 keV pulse profiles between superorbital minimum and maximum, which suggests a similar accretion regime. Modeling the pulse-phase-averaged spectra we find a possible Fe K emission line at 6.4 keV at superorbital maximum. This feature is not significant at superorbital minimum. While we do not observe any significant differences between the pulse-phase-averaged spectral continua apart from the overall flux change, we find that the hardness ratio near the broad main peak of the pulse profile increases from superorbital minimum to maximum. This suggests the spectral shape hardens with increasing luminosity. We discuss different mechanisms that might drive the observed superorbital modulation