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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.

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At least 37 records · Page 2
All sourcesNASA NTRSDOE OSTI
NASA NTRS2008

Ground Handling of Batteries at Test and Launch-site Facilities

Ground handling of flight as well as engineering batteries at test facilities and launch-site facilities is a safety critical process. Test equipment interfacing with the batteries should have the required controls to prevent a hazardous failure of the batteries. Test equipment failures should not induce catastrophic failures on the batteries. Transportation requirements for batteries should also be taken into consideration for safe transportation. This viewgraph presentation includes information on the safe handling of batteries for ground processing at test facilities as well as launch-site facilities.

Jeevarajan, Judith A.↗
NASA NTRS1977

Assessment of launch site accommodations versus Spacelab payload requirements

The Kennedy launch site capability for accommodating spacelab payload operations was assessed. Anomalies between facility accommodations and requirements for the Spacelab III (Strawman), OA Mission 83-2, Dedicated Life Sciences, and Combined Astronomy missions are noted. Recommendations for revision of the accommodations handbook are summarized.

Source record↗
NASA NTRS1993

Coherent launch-site atmospheric wind sounder - Theory and experiment

The coherent launch-site atmospheric wind sounder (CLAWS) is a lidar atmospheric wind sensor designed to measure the winds above space launch facilities to an altitude of 20 km. In our development studies, lidar sensor requirements are defined, a system to meet those requirements is defined and built, and the concept is evaluated, with recommendations for the most feasible and cost-effective lidar system for use as an input to a guidance and control system for missile or spacecraft launches. The ability of CLAWS to meet NASA goals for increased safety and launch/mission flexibility is evaluated in a field test program at Kennedy Space Center (KSC) in which we investigate maximum detection range, refractive turbulence, and aerosol backscattering efficiency. The Nd:YAG coherent lidar operating at 1.06 micron with 1-J energy per pulse is able to make real-time measurements of the 3D wind field at KSC to an altitude of 26 km, in good agreement with our performance simulations. It also shows the height and thickness of the volcanic layer caused by the volcanic eruption of Mount Pinatubo in the Philippines.

Hawley, James G.↗
NASA NTRS1976

Return-to-launch-site variable range-velocity line

The effect of moving the return-to-launch-site (RTLS) range-velocity (R-V) line closer to the landing site was studied. Results are presented which show that a five nautical mile shift in R-V line causes the last RTLS abort to occur approximately one second earlier and that the excess range capability to terminal-area-energy-management interface can be dissipated without an excessive roll angle history.

Bown, R. L.↗
NASA NTRS1988

The effects of RCS jet firing on the isolated Orbiter and mated coast phases of the glide return to launch site maneuver at Mach number 6 (IA302B)

An updated Space Shuttle aerodynamic data base was obtained in Tunnel B for two phases of the Glide Return to Launch Site (GRTLS) abort maneuver. One-and-a-quarter percent scale models of the Space Shuttle Orbiter and External Tank were used to measure the effects of various combinations of Reaction Control System (RCS) jet thrusters at Mach number 6. The angle-of-attack range for the isolated orbiter was -10 to 15 deg at sideslip angles from -5 to 10 deg during Phase 1 of testing. The angle-of-attack range for the mated orbiter and external tank was -5 to 15 deg with sideslip angles of -2 to 5 deg during Phase 2. The test was conducted at a unit Reynolds number of 0.75 million per foot.

Garrett, L. V.↗
NASA NTRS1975

Return-to-launch-site trajectory shaping

The results are presented of a study to show the effect on flyback trajectories of constant inertial attitude during the fuel dissipation phase of a return-to-launch-site abort. It is shown that the value of the constant inertial attitude can be chosen to shape the flyback trajectory.

Bown, R. L.↗
NASA NTRS1975

Return-to-launch-site three degree of freedom analysis, constant inertial attitude during the fuel dissipation phase

Results are presented of a study to show the effect of selecting a constant inertial attitude during the fuel dissipation phase of a return-to-launch-site abort. Results are also presented which show that the selection of the constant inertial attitude will affect the arrival point on the range-velocity target line. An alternate selection of the inertial attitude will provide control over the trajectory shape.

Bown, R. L.↗
NASA NTRS1980

Offshore Space Center (offshore launch site)

Any activity requiring the development of the HLLV can benefit by operations from an offshore space center (OSC) since operating near the equator provides a twenty percent increase in payload in an ecliptic plan orbit. Some OSC concepts considered include a moored floating (semisubmersible) design, a stationary design supported by fixed piles, and a combination of these two. The facility supports: a 15,000 foot long, 300 foot wide runway, designed to accommodate a two staged winged launch vehicle, with a one million pound payload capacity to low earth orbit; an industrial area for HLLV maintenance; an airport terminal, control and operation center, and observation tower; liquid hydrogen and liquid oxygen production and storage, and fuel storage platforms; a power generation station, docks with an unloading area; two separate launch sites; and living accommodations for 10,000 people. Potential sites include the Paramount Seamount in the Pacific Ocean off the north coast of South America. Cost estimates are considered.

Harvey, D. G.↗
NASA NTRS2013

Autonomous Cryogenic Leak Detector for Improving Launch Site Operations

NASA, military, and commercial satellite users need launch services that are highly reliable, less complex, easier to test, and cost effective. This project has developed a tapered optical fiber sensor for detecting hydrogen. The invention involves incorporating chemical indicators on the tapered end of an optical fiber using organically modified silicate nanomaterials. The Hazardous Gas Detection Lab (HGDL) at Kennedy Space Center is involved in the design and development of instrumentation that can detect and qualify various mission-critical chemicals. Historically, hydrogen, helium, nitrogen, oxygen, and argon are the first five gases of HGDL focus. The use of these cryogenic fluids in the area of propulsion offers challenges. Due to their extreme low temperatures, these fluids induce contraction of the materials they contact, a potential cause of leakage. Among them, hydrogen is of particular concern. Small sensors are needed in multiple locations without adding to the structural weight. The most vulnerable parts of the engine are the connection flanges on the transfer lines, which have to support cycles of large thermal amplitude. The thermal protection of the engine provides a closed area, increasing the likelihood of an explosive atmosphere. Thus, even a small leak represents an unacceptable hazardous condition during loading operations, in flight, or after an aborted launch. Tapered fibers were first fabricated from 1/1.3-mm core/cladding (silica/ plastic) optical fibers. Typically a 1-ft (approx. 30- cm) section of the 1-mm fiber is cut from the bundle and marked with a pen into five 2-.-in. (.5.7-cm) sections. A propane torch is applied at every alternate mark to burn the jacket and soften the glass core. While the core is softening, the two ends of the fiber are pulled apart slowly to create fine tapers of .- to .-in. (.6- to 12-mm) long on the 1-mm optical fiber. Following this, the non-tapered ends of the fibers are polished to a 0.3-micron finish. Then these fibers were coated with indicators sensitive to hydrogen. The tapered hydrogen detection system with its unique flexibility is the only system that can be placed in many locations inside the vehicles and detect the exact location of leaks, saving millions of dollars for launch vehicle industries.

Goswami, Kisholoy↗
NASA NTRS2014

Smart Coatings for Launch Site Corrosion Protection

Smart, environmentally friendly paint system for early corrosion detection, mitigation, and healing that will enable supportability in KSC launch facilities and ground systems through their operational life cycles. KSC's Corrosion Technology Laboratory is developing a smart, self-healing coating that can detect and repair corrosion at an early stage. This coating is being developed using microcapsules specifically designed to deliver the contents of their core when corrosion starts.

TechPort Portfolio System↗
NASA NTRSDate not supplied

NASA's Space Launch System Begins Moving To The Launch Site

NASA is accelerating plans for a human return to the Moon. NASA was directed by the White House in 2019 to land the first woman and next man on the Moon by 2024. NASA’s backbone for future deep space exploration is the Space Launch System (SLS), as well as the Orion crew spacecraft, Gateway outpost, and Human Landing System as part of the Artemis program. While the SLS upper stage, the Interim Cryogenic Propulsion Stage (ICPS), based on an existing commercial stage was shipped to Kennedy Space Center (KSC) in 2017, major completed components of SLS will soon begin their eastward journey that will see them at KSC in 2020 to be integrated for their history-making launch back to the Moon. Core Stage prime contractor Boeing completed the Artemis I core stage in 2019 at NASA’s Michoud Assembly Facility (MAF) and shipped it to NASA Stennis Space Center (SSC) for stage green run testing in 2020 and then to KSC. Northrop Grumman, prime contractor for the 5-segment solid rocket boosters, is scheduled to begin overland shipment of the Artemis I motor segments from Utah to KSC in 2020 to await integration. This paper will discuss SLS progress to date and planned 2020 milestones.

Bruce R Askins↗
NASA NTRS1995

Launch Site Computer Simulation and its Application to Processes

This paper provides an overview of computer simulation, the Lockheed developed STS Processing Model, and the application of computer simulation to a wide range of processes. The STS Processing Model is an icon driven model that uses commercial off the shelf software and a Macintosh personal computer. While it usually takes one year to process and launch 8 space shuttles, with the STS Processing Model this process is computer simulated in about 5 minutes. Facilities, orbiters, or ground support equipment can be added or deleted and the impact on launch rate, facility utilization, or other factors measured as desired. This same computer simulation technology can be used to simulate manufacturing, engineering, commercial, or business processes. The technology does not require an 'army' of software engineers to develop and operate, but instead can be used by the layman with only a minimal amount of training. Instead of making changes to a process and realizing the results after the fact, with computer simulation, changes can be made and processes perfected before they are implemented.

Sham, Michael D.↗
NASA NTRS1987

The influence of the launch site operational environment on Space Shuttle scientific payloads

The effects of prelaunch assembly, testing, and integration activities on the scientific payload at the KSC are examined. The functions of the Shuttle and payload organizations of the KSC are discussed. The processing of the various types of pyaloads, and the amount of access to the payload during processing and after landing are described. The KSC facility contains: an Operations and Checkout Building, a Vertical Processing Facility, Cargo Integration and Test Equipment, an Orbiter Processing Facility, a Payload Changeout Room, payload transportation equipment, and Shuttle launch pads.

Schuiling, Roelof L.↗