Small-Scale Metal Tanks for High Pressure Storage of Fluids

NASA Technical Reports Server (NTRS)

London, Adam (Inventor)

2016-01-01

Small scale metal tanks for high-pressure storage of fluids having tank factors of more than 5000 meters and volumes of ten cubic inches or less featuring arrays of interconnected internal chambers having at least inner walls thinner than gage limitations allow. The chambers may be arranged as multiple internal independent vessels. Walls of chambers that are also portions of external tank walls may be arcuate on the internal and/or external surfaces, including domed. The tanks may be shaped adaptively and/or conformally to an application, including, for example, having one or more flat outer walls and/or having an annular shape. The tanks may have dual-purpose inlet/outlet conduits of may have separate inlet and outlet conduits. The tanks are made by fusion bonding etched metal foil layers patterned from slices of a CAD model of the tank. The fusion bonded foil stack may be further machined.

A single launch lunar habitat derived from an NSTS external tank

NASA Technical Reports Server (NTRS)

King, Charles B.; Butterfield, Ansel J.; Hypes, Warren D.; Nealy, John E.; Simonsen, Lisa C.

1990-01-01

A concept for using a spent External Tank from the National Space Transportation System (Shuttle) to derive a Lunar habitat is described. The concept is that the External Tank is carried into Low-Earth Orbit (LEO) where the oxygen tank-intertank subassembly is separated from the hydrogen tank, berthed to Space Station Freedom and the subassembly outfitted as a 12-person Lunar habitat using extravehicular activity (EVA) and intravehicular activity (IVA). A single launch of the NSTS Orbiter can place the External Tank in LEO, provide orbiter astronauts for disassembly of the External Tank, and transport the required subsystem hardware for outfitting the Lunar habitat. An estimate of the astronauts' EVA and IVA is provided. The liquid oxygen tank-intertank modifications utilize existing structures and openings for human access without compromising the structural integrity of the tank. The modification includes installation of living quarters, instrumentation, and an air lock. Feasibility studies of the following additional systems include micrometeoroid and radiation protection, thermal-control, environmental-control and life-support, and propulsion. The converted Lunar habitat is designed for unmanned transport and autonomous soft landing on the Lunar surface without need for site preparation. Lunar regolith is used to fill the micrometeoroid shield volume for radiation protection using a conveyor. The Lunar habitat concept is considered to be feasible by the year 2000 with the concurrent development of a space transfer vehicle and a Lunar lander for crew changeover and resupply.

Exposure of a liquefied gas container to an external fire.

PubMed

Raj, Phani K

2005-06-30

In liquefied gas, bulk-storage facilities and plants, the separation distances between storage tanks and between a tank and a line of adjoining property that can be built are governed by local regulations and/or codes (e.g. National Fire Protection Association (NFPA) 58, 2004). Separation distance requirements have been in the NFPA 58 Code for over 60 years; however, no scientific foundations (either theoretical or experimental) are available for the specified distances. Even though the liquefied petroleum gas (LPG) industry has operated safely over the years, there is a question as to whether the code-specified distances provide sufficient safety to LPG-storage tanks, when they are exposed to large external fires. A radiation heat-transfer-based model is presented in this paper. The temporal variation of the vapor-wetted tank-wall temperature is calculated when exposed to thermal radiation from an external, non-impinging, large, 30.5 m (100 ft) diameter, highly radiative, hydrocarbon fuel (pool) fire located at a specified distance. Structural steel wall of a pressurized, liquefied gas container (such as the ASME LP-Gas tank) begins to lose its strength, when the wall temperature approaches a critical temperature, 810 K (1000 degrees F). LP-Gas tank walls reaching close to this temperature will be a cause for major concern because of increased potential for tank failure, which could result in catastrophic consequences. Results from the model for exposure of different size ASME (LP-Gas) containers to a hydrocarbon pool fire of 30.5 m (100 ft) in diameter, located with its base edge at the separation distances specified by NFPA 58 [NFPA 58, Liquefied Petroleum Gas Code, Table 6.3.1, 2004 ed., National Fire Protection Association, Quincy, MA, 2004] indicate that the vapor-wetted wall temperature of the containers never reach the critical temperature under common wind conditions (0, 5 and 10 m/s), with the flame tilting towards the tank. This indicates that the separation distances specified in the code are adequate for non-impingement type of fires. The model can be used to test the efficacy of other similar codes and regulations for other materials.

Aerodynamic results of a separation effects test conducted in the AEDC 40 by 40 inch tunnel A facility on the Rockwell International launch configuration 3 (model-OTS) integrated vehicle (IA13), volume 1

NASA Technical Reports Server (NTRS)

Campbell, J. H., II

1975-01-01

Experimental aerodynamic investigations were conducted from July 5 through July 17, 1973, on a 0.01 scale model. The AEDC captive trajectory system was utilized in conjunction with the tunnel primary sector to obtain grid-type data for external tank abort from the orbiter, and for nominal separation of one solid rocket booster from the orbiter-tank combination. Booster separation was investigated with and without separation motors plume simulation. The plumes were generated by eight M sub j = 2.15 nozzles using a 1500 psia cold air supply. Free stream data were obtained for all models (orbiter, tank, orbiter-tank, and right-hand booster) to provide baselines for evaluation of proximity effects.

STS-78 external tank documented after separation

NASA Image and Video Library

1996-07-09

STS078-457-006 (20 June 1996) --- One of the first still pictures recorded by the crew members was this 35mm image of the External Fuel Tank (ET) soon after being jettisoned on launch day. The mission, less than ten minutes old when this picture was made, went on to set a Space Shuttle duration record of almost seventeen-days in Earth-orbit. The Indian Ocean forms the backdrop for the image.

Integration and software for thermal test of heat rate sensors. [space shuttle external tank

NASA Technical Reports Server (NTRS)

Wojciechowski, C. J.; Shrider, K. R.

1982-01-01

A minicomputer controlled radiant test facility is described which was developed and calibrated in an effort to verify analytical thermal models of instrumentation islands installed aboard the space shuttle external tank to measure thermal flight parameters during ascent. Software was provided for the facility as well as for development tests on the SRB actuator tail stock. Additional testing was conducted with the test facility to determine the temperature and heat flux rate and loads required to effect a change of color in the ET tank external paint. This requirement resulted from the review of photographs taken of the ET at separation from the orbiter which showed that 75% of the external tank paint coating had not changed color from its original white color. The paint on the remaining 25% of the tank was either brown or black, indicating that it had degraded due to heating or that the spray on form insulation had receded in these areas. The operational capability of the facility as well as the various tests which were conducted and their results are discussed.

Seal Analysis for the Ares-I Upper Stage Fuel Tank Manhole Cover

NASA Technical Reports Server (NTRS)

Phillips, Dawn R.; Wingate, Robert J.

2010-01-01

Techniques for studying the performance of Naflex pressure-assisted seals in the Ares-I Upper Stage liquid hydrogen tank manhole cover seal joint are explored. To assess the feasibility of using the identical seal design for the Upper Stage as was used for the Space Shuttle External Tank manhole covers, a preliminary seal deflection analysis using the ABAQUS commercial finite element software is employed. The ABAQUS analyses are performed using three-dimensional symmetric wedge finite element models. This analysis technique is validated by first modeling a heritage External Tank liquid hydrogen tank manhole cover joint and correlating the results to heritage test data. Once the technique is validated, the Upper Stage configuration is modeled. The Upper Stage analyses are performed at 1.4 times the expected pressure to comply with the Constellation Program factor of safety requirement on joint separation. Results from the analyses performed with the External Tank and Upper Stage models demonstrate the effects of several modeling assumptions on the seal deflection. The analyses for Upper Stage show that the integrity of the seal is successfully maintained.

Method of providing a lunar habitat from an external tank

NASA Technical Reports Server (NTRS)

King, Charles B. (Inventor); Hypes, Warren D. (Inventor); Simonsen, Lisa C. (Inventor); Butterfield, Ansel J. (Inventor); Nealy, John E. (Inventor); Hall, Jr., John B. (Inventor)

1992-01-01

A lunar habitat is provided by placing an external tank of an orbiter in a low Earth orbit where the hydrogen tank is separated from the intertank and oxygen tank which form a base structure. The base structure is then outfitted with an air lock, living quarters, a thermal control system, an environmental control and life support system, and a propulsion system. After the mounting of an outer sheath about the base structure to act as a micrometeoroid shield, the base structure is propelled to a soft landing on the moon. The sheath is mounted at a distance from the base structure to provide a space therebetween which is filled with regolith after landing. Conveniently, a space station is used to outfit the base structure. Various elements of the oxygen tank and intertank are used in outfitting.

Abort staging characteristics of an external oxygen tank separating from the space shuttle 040-A orbiter (.006 scale model) at Mach numbers of 0.6, 2.0, and 4.0

NASA Technical Reports Server (NTRS)

Fossler, I. H.; Cole, P.

1972-01-01

Experimental aerodynamic investigations were conducted on a .006 scale model of the space shuttle 040-A orbiter and its external fuel tank utilizing the NASA/MFSC dual sting support system in the MFSC 14 x 14 inch Trisonic Wind Tunnel. Normal force, pitching moment and axial force components were recorded simultaneously on the orbiter and the tank at selected tank field positions beneath the orbiter as both models were pitched through an angle of attack range of -5 deg to 20 deg. Incidence angles between orbiter and tank of 0 deg, 5 deg, 10 deg and 15 deg were investigated. During these tests Mach number was set at 0.6, 2.0 and 4.0.

KSC-2012-4454

NASA Image and Video Library

2012-08-14

CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, a crane is used to load a space shuttle solid rocket booster and an external fuel tank on trucks for transport to separate museums. The solid rocket boosters, or SRBs, will be displayed at the California Science Center in Los Angeles. The external tank soon will be transported for display at the Wings of Dreams Aviation Museum at Keystone Heights Airport between Gainesville and Jacksonville, Fla. The 149-foot SRBs together provided six million pounds of thrust. The external fuel tank contained over 500,000 gallons of liquid hydrogen and liquid oxygen propellant for the shuttle orbiters' three main engines. The work is part of Transition and Retirement of the space shuttle. For more information, visit http://www.nasa.gov/transition Photo credit: NASA/ Dimitri Gerondidakis

KSC-2012-4453

NASA Image and Video Library

2012-08-14

CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, a crane is used to load a space shuttle solid rocket booster and an external fuel tank on trucks for transport to separate museums. The solid rocket boosters, or SRBs, will be displayed at the California Science Center in Los Angeles. The external tank soon will be transported for display at the Wings of Dreams Aviation Museum at Keystone Heights Airport between Gainesville and Jacksonville, Fla. The 149-foot SRBs together provided six million pounds of thrust. The external fuel tank contained over 500,000 gallons of liquid hydrogen and liquid oxygen propellant for the shuttle orbiters' three main engines. The work is part of Transition and Retirement of the space shuttle. For more information, visit http://www.nasa.gov/transition Photo credit: NASA/ Dimitri Gerondidakis

KSC-2012-4448

NASA Image and Video Library

2012-08-14

CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, a crane is used to load a space shuttle solid rocket booster and an external fuel tank on to trucks for transport to separate museums. The solid rocket boosters, or SRBs, will be displayed at the California Science Center in Los Angeles. The external tank soon will be transported for display at the Wings of Dreams Aviation Museum at Keystone Heights Airport between Gainesville and Jacksonville, Fla. The 149-foot SRBs together provided six million pounds of thrust. The external fuel tank contained over 500,000 gallons of liquid hydrogen and liquid oxygen propellant for the shuttle orbiters' three main engines. The work is part of Transition and Retirement of the space shuttle. For more information, visit http://www.nasa.gov/transition Photo credit: NASA/ Dimitri Gerondidakis

KSC-2012-4449

NASA Image and Video Library

2012-08-14

CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, a crane is used to load a space shuttle solid rocket booster and an external fuel tank on trucks for transport to separate museums. The solid rocket boosters, or SRBs, will be displayed at the California Science Center in Los Angeles. The external tank soon will be transported for display at the Wings of Dreams Aviation Museum at Keystone Heights Airport between Gainesville and Jacksonville, Fla. The 149-foot SRBs together provided six million pounds of thrust. The external fuel tank contained over 500,000 gallons of liquid hydrogen and liquid oxygen propellant for the shuttle orbiters' three main engines. The work is part of Transition and Retirement of the space shuttle. For more information, visit http://www.nasa.gov/transition Photo credit: NASA/ Dimitri Gerondidakis

KSC-2012-4450

NASA Image and Video Library

2012-08-14

CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, a crane is used to load a space shuttle solid rocket booster and an external fuel tank on trucks for transport to separate museums. The solid rocket boosters, or SRBs, will be displayed at the California Science Center in Los Angeles. The external tank soon will be transported for display at the Wings of Dreams Aviation Museum at Keystone Heights Airport between Gainesville and Jacksonville, Fla. The 149-foot SRBs together provided six million pounds of thrust. The external fuel tank contained over 500,000 gallons of liquid hydrogen and liquid oxygen propellant for the shuttle orbiters' three main engines. The work is part of Transition and Retirement of the space shuttle. For more information, visit http://www.nasa.gov/transition Photo credit: NASA/ Dimitri Gerondidakis

KSC-2012-4452

NASA Image and Video Library

2012-08-14

CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, a crane is used to load a space shuttle solid rocket booster and an external fuel tank on trucks for transport to separate museums. The solid rocket boosters, or SRBs, will be displayed at the California Science Center in Los Angeles. The external tank soon will be transported for display at the Wings of Dreams Aviation Museum at Keystone Heights Airport between Gainesville and Jacksonville, Fla. The 149-foot SRBs together provided six million pounds of thrust. The external fuel tank contained over 500,000 gallons of liquid hydrogen and liquid oxygen propellant for the shuttle orbiters' three main engines. The work is part of Transition and Retirement of the space shuttle. For more information, visit http://www.nasa.gov/transition Photo credit: NASA/ Dimitri Gerondidakis

KSC-2012-4451

NASA Image and Video Library

2012-08-14

CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, a crane is used to load a space shuttle solid rocket booster and an external fuel tank on trucks for transport to separate museums. The solid rocket boosters, or SRBs, will be displayed at the California Science Center in Los Angeles. The external tank soon will be transported for display at the Wings of Dreams Aviation Museum at Keystone Heights Airport between Gainesville and Jacksonville, Fla. The 149-foot SRBs together provided six million pounds of thrust. The external fuel tank contained over 500,000 gallons of liquid hydrogen and liquid oxygen propellant for the shuttle orbiters' three main engines. The work is part of Transition and Retirement of the space shuttle. For more information, visit http://www.nasa.gov/transition Photo credit: NASA/ Dimitri Gerondidakis

KSC-2012-4444

NASA Image and Video Library

2012-08-14

CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, preparations are underway to load a twin set of space shuttle solid rocket boosters and an external fuel tank on trucks for transport to separate museums. The solid rocket boosters, or SRBs, will be displayed at the California Science Center in Los Angeles. The external tank soon will be transported for display at the Wings of Dreams Aviation Museum at Keystone Heights Airport between Gainesville and Jacksonville, Fla. The 149-foot SRBs together provided six million pounds of thrust. The external fuel tank contained over 500,000 gallons of liquid hydrogen and liquid oxygen propellant for the shuttle orbiters' three main engines. The work is part of Transition and Retirement of the space shuttle. For more information, visit http://www.nasa.gov/transition Photo credit: NASA/ Dimitri Gerondidakis

KSC-2012-4442

NASA Image and Video Library

2012-08-14

CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, a crane is used to load a twin set of space shuttle solid rocket boosters and an external fuel tank on trucks for transport to separate museums. The solid rocket boosters, or SRBs, will be displayed at the California Science Center in Los Angeles. The external tank soon will be transported for display at the Wings of Dreams Aviation Museum at Keystone Heights Airport between Gainesville and Jacksonville, Fla. The 149-foot SRBs together provided six million pounds of thrust. The external fuel tank contained over 500,000 gallons of liquid hydrogen and liquid oxygen propellant for the shuttle orbiters' three main engines. The work is part of Transition and Retirement of the space shuttle. For more information, visit http://www.nasa.gov/transition Photo credit: NASA/ Dimitri Gerondidakis

KSC-2012-4438

NASA Image and Video Library

2012-08-14

CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, a crane is used to load a twin set of space shuttle solid rocket boosters and an external fuel tank on trucks for transport to separate museums. The solid rocket boosters, or SRBs, will be displayed at the California Science Center in Los Angeles. The external tank soon will be transported for display at the Wings of Dreams Aviation Museum at Keystone Heights Airport between Gainesville and Jacksonville, Fla. The 149-foot SRBs together provided six million pounds of thrust. The external fuel tank contained over 500,000 gallons of liquid hydrogen and liquid oxygen propellant for the shuttle orbiters' three main engines. The work is part of Transition and Retirement of the space shuttle. For more information, visit http://www.nasa.gov/transition Photo credit: NASA/ Dimitri Gerondidakis

An Overview of Spray-On Foam Insulation Applications on the Space Shuttle's External Tank: Foam Applications and Foam Shedding Mechanisms

NASA Technical Reports Server (NTRS)

Sullivan, Roy M.; Lerch, Bradley A.; Rogers, Patrick R.; Sparks, Scotty S.

2006-01-01

The Columbia Accident Investigation Board (CAIB) concluded that the cause of the tragic loss of the Space Shuttle Columbia and its crew was a breach in the thermal protection system on the leading edge of the left wing. The breach was initiated by a piece of insulating foam that separated from the left bipod ramp of the External Tank and struck the wing in the vicinity of the lower half of Reinforced Carbon-Carbon panel No. 8 at 81.9 seconds after launch. The CAIB conclusion has spawned numerous studies to identify the cause of and factors influencing foam shedding and foam debris liberation from the External Tank during ascent. The symposium on the Thermo-mechanics and Fracture of Space Shuttle External Tank Spray-On Foam Insulation is a collection of presentations that discuss the physics and mechanics of the ET SOFI with the objective of improving analytical and numerical methods for predicting foam thermo-mechanical and fracture behavior. This keynote presentation sets the stage for the presentations contained in this symposium by introducing the audience to the various types of SOFI applications on the Shuttle s External Tank and by discussing the various mechanisms that are believed to be the cause of foam shedding during the Shuttle s ascent to space

KSC-2012-4455

NASA Image and Video Library

2012-08-14

CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, a crane is used to load the aft skirt for a space shuttle solid rocket booster on a truck. A twin set of space shuttle solid rocket boosters and an external fuel tank are being prepared for transport to separate museums. The solid rocket boosters, or SRBs, will be displayed at the California Science Center in Los Angeles. The external tank soon will be transported for display at the Wings of Dreams Aviation Museum at Keystone Heights Airport between Gainesville and Jacksonville, Fla. The 149-foot SRBs together provided six million pounds of thrust. The external fuel tank contained over 500,000 gallons of liquid hydrogen and liquid oxygen propellant for the shuttle orbiters' three main engines. The work is part of Transition and Retirement of the space shuttle. For more information, visit http://www.nasa.gov/transition Photo credit: NASA/ Dimitri Gerondidakis

In-flight Video Captured by External Tank Camera System

NASA Technical Reports Server (NTRS)

2005-01-01

In this July 26, 2005 video, Earth slowly fades into the background as the STS-114 Space Shuttle Discovery climbs into space until the External Tank (ET) separates from the orbiter. An External Tank ET Camera System featuring a Sony XC-999 model camera provided never before seen footage of the launch and tank separation. The camera was installed in the ET LO2 Feedline Fairing. From this position, the camera had a 40% field of view with a 3.5 mm lens. The field of view showed some of the Bipod area, a portion of the LH2 tank and Intertank flange area, and some of the bottom of the shuttle orbiter. Contained in an electronic box, the battery pack and transmitter were mounted on top of the Solid Rocker Booster (SRB) crossbeam inside the ET. The battery pack included 20 Nickel-Metal Hydride batteries (similar to cordless phone battery packs) totaling 28 volts DC and could supply about 70 minutes of video. Located 95 degrees apart on the exterior of the Intertank opposite orbiter side, there were 2 blade S-Band antennas about 2 1/2 inches long that transmitted a 10 watt signal to the ground stations. The camera turned on approximately 10 minutes prior to launch and operated for 15 minutes following liftoff. The complete camera system weighs about 32 pounds. Marshall Space Flight Center (MSFC), Johnson Space Center (JSC), Goddard Space Flight Center (GSFC), and Kennedy Space Center (KSC) participated in the design, development, and testing of the ET camera system.

Thermal support for scale support

NASA Technical Reports Server (NTRS)

Dean, W. G.

1976-01-01

The thermal design work completed for the Thermal Protection System (TPS) of the Space Shuttle System (TPS) of the space shuttle vehicle was documented. This work was divided into three phases, the first two of which reported in previous documents. About 22 separate tasks were completed in phase III, such as: hot gas facility (HGF) support, guarded tank support, shuttle external tank (ET) thermal design handbook support, etc.

Microwave and Millimeter Wave Imaging of the Space Shuttle External Fuel Tank Spray on Foam Insulation (SOFI) using Synthetic Aperture Focusing Techniques (SAFT}

NASA Technical Reports Server (NTRS)

Case, J. T.; Robbins, J.; Kharkivskiy, S.; Hepburn, F.; Zoughi, R.

2005-01-01

The Space Shuttle Columbia s catastrophic failure is thought to have been caused by a dislodged piece of external tank spray on foam insulation (SOFI) striking the left wing of the orbiter causing significant damage to some of the reinforced carbodcarbon leading edge wing panels. Microwave and millimeter wave nondestructive evaluation methods have shown great potential for inspecting SOFI for the purpose of detecting anomalies such as small air voids that may cause separation of the SOFI from the external tank during a launch. These methods are capable of producing relatively high-resolution images of the interior of SOFI particularly when advanced imaging algorithms are incorporated into the overall system. To this end, synthetic aperture focusing techniques (SAFT) are being developed. This paper presents some of the preliminary results of this investigation using SAFT-based methods and microwave holography at relatively low frequencies illustrating their potential capabilities for operation at millimeter wave frequencies.

External tank aerothermal design criteria verification, volume 1

NASA Technical Reports Server (NTRS)

Crain, William K.; Frost, Cynthia; Warmbrod, John

1990-01-01

The objective of this study was to produce an independent set of ascent environments which would serve as a check on the Rockwell IVBC-3 environments and provide an independent reevaluation of the thermal design criteria for the External Tank (ET). Design heating rates and loads were calculated at 367 acreage body point locations. Ascent flight regimes covered were lift-off, first stage ascent, Solid Rocket Booster (SRB) staging and second stage ascent through ET separation. The purpose here is to document these results, briefly describe the methodology used and present the environments along with a comparison with the Rockwell IVBC-3 counterpart. The methodology and environment summaries are given.

KSC-2010-4648

NASA Image and Video Library

2010-09-13

CAPE CANAVERAL, Fla. -- At NASA's Kennedy Space Center in Florida, a left-side main separation bolt attaches the bottom of space shuttle Discovery to its external fuel tank in the Vehicle Assembly Building. As technicians were attaching the bolt Sept. 10, a bolt nut slipped back into Discovery's aft compartment. To retrieve it, technicians entered Discovery’s aft section through an access door. They then moved the nut back into position to finish attaching the bolt, which is used to separate Discovery from the external tank once the shuttle is in orbit. Discovery is scheduled to roll out to Launch Pad 39A later this month for its STS-133 launch to the International Space Station. Targeted to lift off Nov. 1, Discovery will take the Permanent Multipurpose Module (PMM) packed with supplies and critical spare parts, as well as Robonaut 2 (R2) to the station. Photo credit: NASA/Dimitri Gerondidakis

KSC-2010-4647

NASA Image and Video Library

2010-09-13

CAPE CANAVERAL, Fla. -- At NASA's Kennedy Space Center in Florida, a Vehicle Assembly Building technician adjusts a left-side main separation bolt that attaches the bottom of space shuttle Discovery to its external fuel tank. As technicians were attaching the bolt Sept. 10, a bolt nut slipped back into Discovery's aft compartment. To retrieve it, technicians entered Discovery’s aft section through an access door. They then moved the nut back into position to finish attaching the bolt, which is used to separate Discovery from the external tank once the shuttle is in orbit. Discovery is scheduled to roll out to Launch Pad 39A later this month for its STS-133 launch to the International Space Station. Targeted to lift off Nov. 1, Discovery will take the Permanent Multipurpose Module (PMM) packed with supplies and critical spare parts, as well as Robonaut 2 (R2) to the station. Photo credit: NASA/Dimitri Gerondidakis

Space Shuttle Projects

NASA Image and Video Library

1976-01-01

This is a cutaway illustration of the Space Shuttle external tank (ET) with callouts. The giant cylinder, higher than a 15-story building, with a length of 154-feet (47-meters) and a diameter of 27.5-feet (8.4-meters), is the largest single piece of the Space Shuttle. During launch, the ET also acts as a backbone for the orbiter and solid rocket boosters. Separate pressurized tank sections within the external tank hold the liquid hydrogen fuel and liquid oxygen oxidizer for the Shuttle's three main engines. During launch, the ET feeds the fuel under pressure through 17-inch (43.2-centimeter) ducts that branch off into smaller lines that feed directly into the main engines. The main engines consume 64,000 gallons (242,260 liters) of fuel each minute. Machined from aluminum alloys, the Space Shuttle's external tank is currently the only part of the launch vehicle that is not reused. After its 526,000-gallons (1,991,071 liters) of propellants are consumed during the first 8.5-minutes of flight, it is jettisoned from the orbiter and breaks up in the upper atmosphere, its pieces falling into remote ocean waters. The Marshall Space Flight Center was responsible for developing the ET.

LAUNCH (SOLID ROCKET BOOSTER [SRB]) - STS-1

NASA Image and Video Library

1981-04-12

S81-30505 (12 April 1981) --- Separation of space shuttle Columbia?s external tank, photographed by motion picture cameras in the umbilical bays, occurred following the shutdown of the vehicle?s three main engines. Columbia?s cameras were able to record the bottom side of the tank as the orbiter headed toward its Earth-orbital mission with astronauts John W. Young and Robert L. Crippen aboard and the fuel tank fell toward Earth, passing through the atmosphere rapidly. Liquid oxygen and liquid hydrogen umbilical connectors can be seen at the bottom of the tank. For orientation, the photo should be held with the rounded end at bottom of the frame. Photo credit: NASA

49 CFR 238.423 - Fuel tanks.

Code of Federal Regulations, 2010 CFR

2010-10-01

....423 Fuel tanks. (a) External fuel tanks. Each type of external fuel tank must be approved by FRA's... equivalent to a fuel tank that complies with the external fuel tank requirements in § 238.223(a). (b) Internal fuel tanks. Internal fuel tanks shall comply with the requirements specified in § 238.223(b). ...

Pressure and heat flux results from the space shuttle/external fuel tank interaction test at Mach numbers 16 and 19

NASA Technical Reports Server (NTRS)

Brewer, E. B.; Haberman, D. R.

1974-01-01

Heat transfer rates and pressures were measured on a 0.0175-scale model of the space shuttle external tank (ET), model MCR0200. Tests were conducted with the ET model separately and while mated with a 0.0175-scale model of the orbiter, model 21-OT (Grumman). The tests were conducted in the AEDC-VKF Hypervelocity Wind Tunnel (F) at Mach numbers 16 and 19. The primary data consisted of the interaction heating rates experienced by the ET while mated with the orbiter in the flight configuration. Data were taken for a range of Reynolds numbers from 50,000 to 65,000 under laminar flow conditions.

Additional experiments on flowability improvements of aviation fuels at low temperatures, volume 2

NASA Technical Reports Server (NTRS)

Stockemer, F. J.; Deane, R. L.

1982-01-01

An investigation was performed to study flow improver additives and scale-model fuel heating systems for use with aviation hydrocarbon fuel at low temperatures. Test were performed in a facility that simulated the heat transfer and temperature profiles anticipated in wing fuel tanks during flight of long-range commercial aircraft. The results are presented of experiments conducted in a test tank simulating a section of an outer wing integral fuel tank approximately full-scale in height, chilled through heat exchange panels bonded to the upper and lower horizontal surfaces. A separate system heated lubricating oil externally by a controllable electric heater, to transfer heat to fuel pumped from the test tank through an oil-to-fuel heat exchanger, and to recirculate the heated fuel back to the test tank.

Space Shuttle with rail system and aft thrust structure securing solid rocket boosters to external tank

NASA Technical Reports Server (NTRS)

Vonpragenau, G. L. (Inventor)

1984-01-01

The configuration and relationship of the external propellant tank and solid rocket boosters of space transportation systems such as the space shuttle are described. The space shuttle system with the improved propellant tank is shown. The external tank has a forward pressure vessel for liquid hydrogen and an aft pressure vessel for liquid oxygen. The solid rocket boosters are joined together by a thrust frame which extends across and behind the external tank. The thrust of the orbiter's main rocket engines are transmitted to the aft portion of the external tank and the thrust of the solid rocket boosters are transmitted to the aft end of the external tank.

Detail view of an Aft Skirt being prepared for mating ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

Detail view of an Aft Skirt being prepared for mating with sub assemblies in the Solid Rocket Booster (SRB) Assembly and Refurbishment Facility at Kennedy Space Center. This detail is showing the four Aft Booster Separation Motors. The Separation Motors burn for one second to ensure the SRBs drift away from the External Tank and Orbiter at separation. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

CFD Assessment of Forward Booster Separation Motor Ignition Overpressure on ET XT 718 Ice/Frost Ramp

NASA Technical Reports Server (NTRS)

Tejnil, Edward; Rogers, Stuart E.

2012-01-01

Computational fluid dynamics assessment of the forward booster separation motor ignition over-pressure was performed on the space shuttle external tank X(sub T) 718 ice/frost ramp using the flow solver OVERFLOW. The main objective of this study was the investigation of the over-pressure during solid rocket booster separation and its affect on the local pressure and air-load environments. Delta pressure and plume impingement were investigated as a possible contributing factor to the cause of the debris loss on shuttle missions STS-125 and STS-127. A simplified computational model of the Space Shuttle Launch Vehicle was developed consisting of just the external tank and the solid rocket boosters with separation motor nozzles and plumes. The simplified model was validated by comparison to full fidelity computational model of the Space Shuttle without the separation motors. Quasi steady-state plume solutions were used to calibrate the thrust of the separation motors. Time-accurate simulations of the firing of the booster-separation motors were performed. Parametric studies of the time-step size and the number of sub-iterations were used to find the best converged solution. The computed solutions were compared to previous OVERFLOW steady-state runs of the separation motors with reaction control system jets and to ground test data. The results indicated that delta pressure from the overpressure was small and within design limits, and thus was unlikely to have contributed to the foam losses.

A Match Made in Space

NASA Technical Reports Server (NTRS)

2006-01-01

Just before the space shuttle reaches orbit, its three main engines shut down so that it can achieve separation from the massive external tank that provided the fuel required for liftoff and ascent. In jettisoning the external tank, which is completely devoid of fuel at this point in the flight, the space shuttle fires a series of thrusters, separate from its main engines, that gives the orbiter the maneuvering ability necessary to safely steer clear of the descending tank and maintain its intended flight path. These thrusters make up the space shuttle s Reaction Control System. While the space shuttle s main engines only provide thrust in one direction (albeit a very powerful thrust), the Reaction Control System engines allow the vehicle to maneuver in any desired direction (via small amounts of thrust). The resulting rotational maneuvers are known as pitch, roll, and yaw, and are very important in ensuring that the shuttle docks properly when it arrives at the International Space Station and safely reenters the Earth s atmosphere upon leaving. To prevent the highly complex Reaction Control System from malfunctioning during space shuttle flights, and to provide a diagnosis if such a mishap were to occur, NASA turned to a method of artificial intelligence that truly defied the traditional laws of computer science.

Atlantis TPS Processing

NASA Image and Video Library

2003-10-01

In the Orbiter Processing Facility, Harrell Watts (left), with United Space Alliance, removes a tile from the thermal barrier around the umbilical areas, the external tank attach points, on the underside of Atlantis. The umbilical areas are closed off after ET separation by a door, seen here. The exposed area of each closed door is covered with reusable surface insulation.

Advanced silver zinc battery development for the SRB and ET range safety subsystems

NASA Technical Reports Server (NTRS)

Adamedes, Zoe

1994-01-01

This document presents in viewgraph format the design and development of silver zinc (AgZn) batteries for the solid rocket booster (SRB) and external tank (ET) range safety subsystems. Various engineering techniques, including composite separator systems, new electrode processing techniques, and new restraint techniques, were used to meet difficult requirements.

Closeup view of an Aft Skirt being prepared for mating ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

Close-up view of an Aft Skirt being prepared for mating with sub assemblies in the Solid Rocket Booster (SRB) Assembly and Refurbishment Facility at Kennedy Space Center. The most prominent feature in this view are the four Aft Booster Separation Motors on the left side of the skirt in this view. The Separation Motors burn for one second to ensure the SRBs drift away from the External Tank and Orbiter at separation. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Solid Rocket Booster Separation

NASA Technical Reports Server (NTRS)

1998-01-01

This Quick Time movie shows the Space Shuttle Solid Rocket Booster (SRB) separation from the external tank (ET). After separation, the boosters fall to the ocean from which they are retrieved and refurbished for reuse. The Shuttle's SRB's and solid rocket motors (SRM's) are the largest ever built and the first designed for refurbishment and reuse. Standing nearly 150-feet high, the twin boosters provide the majority of thrust for the first two minutes of flight, about 5.8 million pounds. That is equivalent to 44 million horsepower, or the combined power of 400,000 subcompact cars.

46 CFR 154.408 - Cargo tank external pressure load.

Code of Federal Regulations, 2010 CFR

2010-10-01

... minimum internal pressure (maximum vacuum), and the maximum external pressure to which any portion of the... 46 Shipping 5 2010-10-01 2010-10-01 false Cargo tank external pressure load. 154.408 Section 154... Equipment Cargo Containment Systems § 154.408 Cargo tank external pressure load. For the calculation...

49 CFR 238.223 - Locomotive fuel tanks.

Code of Federal Regulations, 2012 CFR

2012-10-01

... 49 Transportation 4 2012-10-01 2012-10-01 false Locomotive fuel tanks. 238.223 Section 238.223... Equipment § 238.223 Locomotive fuel tanks. Locomotive fuel tanks shall comply with either the following or....21: (a) External fuel tanks. External locomotive fuel tanks shall comply with the requirements...

49 CFR 238.223 - Locomotive fuel tanks.

Code of Federal Regulations, 2011 CFR

2011-10-01

... 49 Transportation 4 2011-10-01 2011-10-01 false Locomotive fuel tanks. 238.223 Section 238.223... Equipment § 238.223 Locomotive fuel tanks. Locomotive fuel tanks shall comply with either the following or....21: (a) External fuel tanks. External locomotive fuel tanks shall comply with the requirements...

The ET as it falls away from the orbiter after separation on STS-121

NASA Image and Video Library

2006-07-04

S121-E-05006 (4 July 2006) --- This picture of the STS-121 external tank was taken with a digital still camera by an astronaut only seconds after separation from the Space Shuttle Discovery on launch day. Engineers, managers and flight controllers have carefully studied this image and other frames from this series as well as a number of pictures showing the falling ET as photographed from umbilical well cameras.

The ET as it falls away from the orbiter after separation on STS-121

NASA Image and Video Library

2006-07-04

STS121-E-05011 (4 July 2006)-- This picture of the STS-121 external tank was taken with a digital still camera by an astronaut only seconds after separation from the Space Shuttle Discovery on launch day. Engineers, managers and flight controllers have carefully studied this image and other frames from this series as well as a number of pictures showing the falling ET as photographed from umbilical well cameras.

The ET as it falls away from the orbiter after separation on STS-121

NASA Image and Video Library

2006-07-04

STS121-E-05008 (4 July 2006)-- This picture of the STS-121 external tank was taken with a digital still camera by an astronaut only seconds after separation from the Space Shuttle Discovery on launch day. Engineers, managers and flight controllers have carefully studied this image and other frames from this series as well as a number of pictures showing the falling ET as photographed from umbilical well cameras.

Free-Spinning-Tunnel Investigation of a 1/28-Scale Model of the North American FJ-4 Airplane with External Fuel Tanks, TED No. NACA AD 3112

NASA Technical Reports Server (NTRS)

Healy, Frederick M.

1958-01-01

A supplementary investigation to determine the effect of external fuel tanks on the spin and recovery characteristics of a l/28-scale model of the North American FJ-4 airplane has been conducted in the Langley 20-foot free-spinning tunnel. The model had been extensively tested previously (NACA Research Memorandum SL38A29) and therefore only brief tests were made to evaluate the effect of tank installation. Erect spin tests of the model indicate that flat-type spins-are more prevalent with 200-gallon external fuel tanks than with tanks not installed. The recovery technique determined for spins without tanks, rudder reversal to full against the spin accompanied by simultaneous movement of ailerons to full with the spin, is recommended for spins encountered with external tanks installed. If inverted spins are encountered with external tanks installed, the tanks should be jettisoned and recovery attempted by rudder reversal to full against the spin with ailerons maintained at neutral.

49 CFR 238.423 - Fuel tanks.

Code of Federal Regulations, 2014 CFR

2014-10-01

... 49 Transportation 4 2014-10-01 2014-10-01 false Fuel tanks. 238.423 Section 238.423 Transportation....423 Fuel tanks. (a) External fuel tanks. Each type of external fuel tank must be approved by FRA's Associate Administrator for Safety upon a showing that the fuel tank provides a level of safety at least...

49 CFR 238.423 - Fuel tanks.

Code of Federal Regulations, 2011 CFR

2011-10-01

... 49 Transportation 4 2011-10-01 2011-10-01 false Fuel tanks. 238.423 Section 238.423 Transportation....423 Fuel tanks. (a) External fuel tanks. Each type of external fuel tank must be approved by FRA's Associate Administrator for Safety upon a showing that the fuel tank provides a level of safety at least...

49 CFR 238.423 - Fuel tanks.

Code of Federal Regulations, 2013 CFR

2013-10-01

... 49 Transportation 4 2013-10-01 2013-10-01 false Fuel tanks. 238.423 Section 238.423 Transportation....423 Fuel tanks. (a) External fuel tanks. Each type of external fuel tank must be approved by FRA's Associate Administrator for Safety upon a showing that the fuel tank provides a level of safety at least...

49 CFR 238.423 - Fuel tanks.

Code of Federal Regulations, 2012 CFR

2012-10-01

... 49 Transportation 4 2012-10-01 2012-10-01 false Fuel tanks. 238.423 Section 238.423 Transportation....423 Fuel tanks. (a) External fuel tanks. Each type of external fuel tank must be approved by FRA's Associate Administrator for Safety upon a showing that the fuel tank provides a level of safety at least...

49 CFR 229.217 - Fuel tank.

Code of Federal Regulations, 2013 CFR

2013-10-01

... 49 Transportation 4 2013-10-01 2013-10-01 false Fuel tank. 229.217 Section 229.217 Transportation... TRANSPORTATION RAILROAD LOCOMOTIVE SAFETY STANDARDS Locomotive Crashworthiness Design Requirements § 229.217 Fuel tank. (a) External fuel tanks. Locomotives equipped with external fuel tanks shall, at a minimum...

49 CFR 229.217 - Fuel tank.

Code of Federal Regulations, 2011 CFR

2011-10-01

... 49 Transportation 4 2011-10-01 2011-10-01 false Fuel tank. 229.217 Section 229.217 Transportation... TRANSPORTATION RAILROAD LOCOMOTIVE SAFETY STANDARDS Locomotive Crashworthiness Design Requirements § 229.217 Fuel tank. (a) External fuel tanks. Locomotives equipped with external fuel tanks shall, at a minimum...

49 CFR 229.217 - Fuel tank.

Code of Federal Regulations, 2014 CFR

2014-10-01

... 49 Transportation 4 2014-10-01 2014-10-01 false Fuel tank. 229.217 Section 229.217 Transportation... TRANSPORTATION RAILROAD LOCOMOTIVE SAFETY STANDARDS Locomotive Crashworthiness Design Requirements § 229.217 Fuel tank. (a) External fuel tanks. Locomotives equipped with external fuel tanks shall, at a minimum...

49 CFR 229.217 - Fuel tank.

Code of Federal Regulations, 2012 CFR

2012-10-01

... 49 Transportation 4 2012-10-01 2012-10-01 false Fuel tank. 229.217 Section 229.217 Transportation... TRANSPORTATION RAILROAD LOCOMOTIVE SAFETY STANDARDS Locomotive Crashworthiness Design Requirements § 229.217 Fuel tank. (a) External fuel tanks. Locomotives equipped with external fuel tanks shall, at a minimum...

Microwave and Millimeter Wave Imaging of the Space Shuttle External Fuel Tank Spray on Foam Insulation (SOFI) Using Synthetic Aperture Focusing Techniques (SAFT)

NASA Technical Reports Server (NTRS)

Case, J. T.; Robbins, J.; Kharkovshy, S.; Hepburn, F. L.; Zoughi, R.

2005-01-01

The Space Shuttle Columbia's catastrophic failure is thought to have been caused by a dislodged piece of external tank SOFI (Spray On Foam Insulation) striking the left wing of the orbiter causing significant damage to some of the reinforced carbodcarbon leading edge wing panels. Microwave and millimeter wave nondestructive evaluation methods, have shown great potential for inspecting the SOFI for the purpose of detecting anomalies such as small voids that may cause separation of the foam from the external tank during the launch. These methods are capable of producing relatively high-resolution images of the interior of SOH particularly when advanced imaging algorithms are incorporated into the overall system. To this end, synthetic aperture focusing techniques are being deveioped for this purpose. These iechniqiies pradiice high-resolution images that are independent of the distance of the imaging probe to the SOFI with spatial resolution in the order of the half size of imaging probe aperture. At microwave and millimeter wave frequencies these apertures are inherently small resulting in high-resolution images. This paper provides the results of this investigation using 2D and 3D SAF based methods and holography. The attributes of these methods and a full discussion of the results will also be provided.

An external tank is moved from a barge in the turn basin to the VAB

NASA Technical Reports Server (NTRS)

2000-01-01

A newly arrived external tank is transported from the turn basin to the Vehicle Assembly Building (VAB), seen behind the tank. External tanks are built by the NASA Michoud Assembly Facility in New Orleans and transported by barge to Cape Canaveral and then up the Banana River to the turn basin in the Launch Complex 39 Area. In the VAB, the tank will await stacking for a future Shuttle mission.

An external tank is moved from a barge in the turn basin to the VAB

NASA Technical Reports Server (NTRS)

2000-01-01

A newly arrived external tank heads from the turn basin toward the Vehicle Assembly Building (VAB), seen behind the tank. External tanks are built by the NASA Michoud Assembly Facility in New Orleans and transported by barge to Cape Canaveral and then up the Banana River to the turn basin in the Launch Complex 39 Area. In the VAB, the tank will await stacking for a future Shuttle mission.

Terahertz Lasers Reveal Information for 3D Images

NASA Technical Reports Server (NTRS)

2013-01-01

After taking off her shoes and jacket, she places them in a bin. She then takes her laptop out of its case and places it in a separate bin. As the items move through the x-ray machine, the woman waits for a sign from security personnel to pass through the metal detector. Today, she was lucky; she did not encounter any delays. The man behind her, however, was asked to step inside a large circular tube, raise his hands above his head, and have his whole body scanned. If you have ever witnessed a full-body scan at the airport, you may have witnessed terahertz imaging. Terahertz wavelengths are located between microwave and infrared on the electromagnetic spectrum. When exposed to these wavelengths, certain materials such as clothing, thin metal, sheet rock, and insulation become transparent. At airports, terahertz radiation can illuminate guns, knives, or explosives hidden underneath a passenger s clothing. At NASA s Kennedy Space Center, terahertz wavelengths have assisted in the inspection of materials like insulating foam on the external tanks of the now-retired space shuttle. "The foam we used on the external tank was a little denser than Styrofoam, but not much," says Robert Youngquist, a physicist at Kennedy. The problem, he explains, was that "we lost a space shuttle by having a chunk of foam fall off from the external fuel tank and hit the orbiter." To uncover any potential defects in the foam covering, such as voids or air pockets, that could keep the material from staying in place, NASA employed terahertz imaging to see through the foam. For many years, the technique ensured the integrity of the material on the external tanks.

High Resolution Millimeter Wave Inspecting of the Orbiter Acreage Heat Tiles of the Space Shuttle

NASA Technical Reports Server (NTRS)

Case, J. T.; Khakovsky, S.; Zoughi, r.; Hepburn, F.

2007-01-01

Presence of defects such as disbonds, delaminations, impact damage, in thermal protection systems can significantly reduce safety of the Space Shuttle and its crew. The physical cause of Space Shuttle Columbia's catastrophic failure was a breach in its thermal protection system, caused by a piece of external tank insulating foam separating from the external tank and striking the leading edge of the left wing of the orbiter. There is an urgent need for a rapid, robust and life-circle oriented nondestructive testing (NDT) technique capable of inspecting the external tank insulating foam as well as the orbiter's protective (acreage) heat tiles and its fuselage prior and subsequent to a launch. Such a comprehensive inspection technique enables NASA to perform life-cycle inspection on critical components of the orbiter and its supporting hardware. Consequently, NASA Marshall Space Flight Center initiated an investigation into several potentially viable NDT techniques for this purpose. Microwave and millimeter wave NDT methods have shown great potential to achieve these goals. These methods have been successfully used to produce images of the interior of various complex, thick and thin external tank insulating foam structures for real focused reflectometer at operating frequency from 50-100 GHz and for synthetic aperture techniques at Ku-band (12-18 GHz) and K-band (18-26 GHz). Preliminary results of inspecting heat tile specimens show that increasing resolution of the measurement system is an important issue. This paper presents recent results of an investigation for the purpose of detecting anomalies such as debonds and corrosion in metal substrate in complex multi-sectioned protective heat tile specimens using a real focused 150 GHz (D-band) reflectometer and wide-band millimeter wave holography at 33-50, GHz (Q-band).

High-Speed Machining (HSM) of Space Shuttle External Tank (ET) panels

NASA Astrophysics Data System (ADS)

Miller, J. A.

1983-02-01

The External Fuel Tank (ET) of the Space Shuttle is not recovered after launch and a new one must be provided for each launch. Currently, the external ""skin'' panels of the tank are produced by machining from solid wrought 2219-T87 aluminum plate stock approximately 1-3/4 inch thick. The reduction of costs in producing External Fuel Tank panels is obviously of increasing production rates and decreasing costs of the panels through the application of high-speed machining (HSM) techniques was conducted.

High-Speed Machining (HSM) of Space Shuttle External Tank (ET) panels

NASA Technical Reports Server (NTRS)

Miller, J. A.

1983-01-01

The External Fuel Tank (ET) of the Space Shuttle is not recovered after launch and a new one must be provided for each launch. Currently, the external ""skin'' panels of the tank are produced by machining from solid wrought 2219-T87 aluminum plate stock approximately 1-3/4 inch thick. The reduction of costs in producing External Fuel Tank panels is obviously of increasing production rates and decreasing costs of the panels through the application of high-speed machining (HSM) techniques was conducted.

Space Shuttle Status News Conference

NASA Technical Reports Server (NTRS)

2005-01-01

Richard Gilbech, External Tank "Tiger Team" Lead, begins this space shuttle news conference with detailing the two major objectives of the team. The objectives include: 1) Finding the root cause of the foam loss on STS-114; and 2) Near and long term improvements for the external tank. Wayne Hale, Space Shuttle Program Manager, presents a chart to explain the external tank foam loss during STS-114. He gives a possible launch date for STS-121 after there has been a repair to the foam on the External Tank. He further discusses the changes that need to be made to the surrounding areas of the plant in New Orleans, due to Hurricane Katrina. Bill Gerstemaier, NASA Associate Administrator for Space Operations, elaborates on the testing of the external tank foam loss. The discussion ends with questions from the news media about a fix for the foam, replacement of the tiles, foam loss avoidance, the root cause of foam loss and a possible date for a new external tank to be shipped to NASA Kennedy Space Center.

Filament wound metal lined propellant tanks for future Earth-to-orbit transports

NASA Technical Reports Server (NTRS)

Macconochie, Ian O.; Davis, Robert B.; Freeman, William T., Jr.

1988-01-01

For future Earth-to-orbit transport vehicles, reusability and lighter weights are sought for the main propellant tanks. To achieve this, a filament wound tank with a metal liner and an intermediate layer of foam-filled honeycomb is proposed. A hydrogen tank is used as an example. To accommodate mismatches in the expansion of liner and overwrap a design is proposed wherin the liner is configured so that the extension of the liner under pressure matches the expected contraction of the same liner due to the presence of a cryogen. In operation, the liner is pressurized at a rate such that the pressure strain matches the contraction due to decrease in temperature. As an alternate approach, compressive pre-stress is placed in the liner such that it will not separate from the overwrap. A finite element program is used to show stresses in the liner and overwrap for various tank pressures for the pre-stressed liner concept. A fracture mechanics analysis is made of the liners to determine tank life. The tank concept shown has a similar weight to the Shuttle external hydrogen tank, but the filament wound tank is expected to be reusable. Integration of the propellant tanks into a future transport vehicle is discussed.

The analysis of the transient pressure response of the shuttle EPS-ECS cryogenic tanks with external pressurization systems

NASA Technical Reports Server (NTRS)

Barton, J. E.; Patterson, H. W.

1973-01-01

An analysis of transient pressures in externally pressurized cryogenic hydrogen and oxygen tanks was conducted and the effects of design variables on pressure response determined. The analysis was conducted with a computer program which solves the compressible viscous flow equations in two-dimensional regions representing the tank and external loop. The external loop volume, thermal mass, and heat leak were the dominant design variables affecting the system pressure response. No significant temperature stratification occurred in the fluid contained in the tank.

Slide Release Device. Shuttle Orbiter/External Tank Forward Attachment

NASA Technical Reports Server (NTRS)

1981-01-01

A prototype release mechanism is discussed which is interchangeable with the existing orbiter/external tank separation bolt and offers reduced weight, shock, and cost. The components are reuseable. The unit takes maximum advantage of the shank diameter and installs in the monoball just as does the shear bolt, by threading in the completely assembled condition. Actuation is different, in that instead of axially breaking the shank by very high pressure (on the order of 60,000 psi) using a very large force (over 235, 000 pounds), this mechanism releases the shank by cross-axis movement against a lubricated surface. Once free, the shank is driven out of the monoball by an axially precompressed spring. Final weight can be as low as 30 pounds, and the cartridge contains less than one gram of powder. The components show no significant wear after eleven actuations under load.

KSC-03pd2762

NASA Image and Video Library

2003-10-01

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, Ryan Levann, with United Space Alliance, checks data on the tile removed from the thermal barrier around the umbilical areas, the external tank attach points, on the underside of Atlantis. The umbilical areas are closed off after ET separation by a door, seen here. The exposed area of each closed door is covered with reusable surface insulation.

Heat-transfer test results for a .0275-scale space shuttle external tank with a 10 deg/40 deg double cone-ogive nose in the NASA/AMES 3.5-foot hypersonic wind tunnel (FH14), volume 2

NASA Technical Reports Server (NTRS)

Carroll, H. R.

1977-01-01

A .0275 scale forebody model of the new baseline configuration of the space shuttle external tank vent cap configuration was tested to determine the flow field due to the double cone configuration. The tests were conducted in a 3.5 foot hypersonic wind tunnel at alpha = -5 deg, -4.59 deg, 0 deg, 5 deg, and 10 deg; beta = 0 deg, -3 deg, -5.51 deg, -6 deg, -9 deg, and +6 deg; nominal freestream Reynolds numbers per foot of 1.5 x 1 million, 3.0 x 1 million, and 5.0 x 1 million; and a nominal Mach number of 5. Separation and reattached flow from thermocouple data, shadowgraphs, and oil flows indicate that separation begins about 80% from the tip of the 10 deg cone, then reattaches on the vent cap and produces fully turbulent flow over most of the model forebody. The hardware disturbs the flow over a much larger area than present TPS application has assumed. A correction to the flow disturbance was experimentally suggested from the results of an additional test run.

Insulation systems for liquid methane fuel tanks for supersonic cruise aircraft

NASA Technical Reports Server (NTRS)

Brady, H. F.; Delduca, D.

1972-01-01

Two insulation systems for tanks containing liquid methane in supersonic cruise-type aircraft were designed and tested after an extensive materials investigation. One system is an external insulation and the other is an internal wet-type insulation system. Tank volume was maximized by making the tank shape approach a rectangular parallelopiped. One tank was designed to use the external insulation and the other tank to use the internal insulation. Performance of the external insulation system was evaluated on a full-scale tank under the temperature environment of -320 F to 700 F and ambient pressures of ground-level atmospheric to 1 psia. Problems with installing the internal insulation on the test tank prevented full-scale evaluation of performance; however, small-scale testing verified thermal conductivity, temperature capability, and installed density.

KENNEDY SPACE CENTER, FLA. - The external tank in the Vehicle Assembly Building (VAB) is destacked from the solid rocket boosters. The tank and SRBs were configured for Atlantis and mission STS-114. The tank will remain in the VAB.

NASA Image and Video Library

2003-05-20

KENNEDY SPACE CENTER, FLA. - The external tank in the Vehicle Assembly Building (VAB) is destacked from the solid rocket boosters. The tank and SRBs were configured for Atlantis and mission STS-114. The tank will remain in the VAB.

External tank project new technology plan. [development of space shuttle external tank system

NASA Technical Reports Server (NTRS)

1973-01-01

A production plan for the space shuttle external tank configuration is presented. The subjects discussed are: (1) the thermal protection system, (2) thermal coating application techniques, (3) manufacturing and tooling, (4) propulsion system configurations and components, (5) low temperature rotating and sliding joint seals, (6) lightning protection, and (7) nondestructive testing technology.

KSC-06pd0564

NASA Image and Video Library

2006-03-29

KENNEDY SPACE CENTER, FLA. - In the Vehicle Assembly Building at NASA's Kennedy Space Center, the nose cap on top of external tank number 119 has been removed. A new gaseous oxygen vent valve will be installed. Tank 119 is designated for mission STS-121. Vapors are created prior to launch as the liquid oxygen in the external tank boils off. At the forward end of each external tank propellant tank is a vent and relief valve that can be opened before launch for venting or by excessive tank pressure for relief. The vent function is available only before launch. Mission STS-121 to the International Space Station is scheduled for launch in July. Photo credit: NASA/Jim Grossmann

KSC-06pd0615

NASA Image and Video Library

2006-04-13

KENNEDY SPACE CENTER, FLA. - In the transfer aisle of the Vehicle Assembly Building, workers work on the rim around the nose cap of external tank number 119, the tank designated for mission STS-121. The cap was removed in order to install a new gaseous oxygen vent valve underneath. Vapors are created prior to launch as the liquid oxygen in the external tank boils off. At the forward end of each external tank propellant tank is a vent and relief valve that can be opened before launch for venting or by excessive tank pressure for relief. The vent function is available only before launch. Mission STS-121 to the International Space Station is scheduled for launch in July. Photo credit: NASA/Jim Grossmann

KSC-06pd0616

NASA Image and Video Library

2006-04-13

KENNEDY SPACE CENTER, FLA. - In the transfer aisle of the Vehicle Assembly Building, workers check the rim around the nose cap of external tank number 119, the tank designated for mission STS-121. The cap was removed in order to install a new gaseous oxygen vent valve underneath. Vapors are created prior to launch as the liquid oxygen in the external tank boils off. At the forward end of each external tank propellant tank is a vent and relief valve that can be opened before launch for venting or by excessive tank pressure for relief. The vent function is available only before launch. Mission STS-121 to the International Space Station is scheduled for launch in July. Photo credit: NASA/Jim Grossmann

Aerodynamic results of wind tunnel tests on a 0.010-scale model (32-QTS) space shuttle integrated vehicle in the AEDC VKF-40-inch supersonic wind tunnel (IA61)

NASA Technical Reports Server (NTRS)

Daileda, J. J.

1976-01-01

Plotted and tabulated aerodynamic coefficient data from a wind tunnel test of the integrated space shuttle vehicle are presented. The primary test objective was to determine proximity force and moment data for the orbiter/external tank and solid rocket booster (SRB) with and without separation rockets firing for both single and dual booster runs. Data were obtained at three points (t = 0, 1.25, and 2.0 seconds) on the nominal SRB separation trajectory.

Simulation and Analyses of Multi-Body Separation in Launch Vehicle Staging Environment

NASA Technical Reports Server (NTRS)

Pamadi, Bandu N.; Hotchko, Nathaniel J.; Samareh, Jamshid; Covell, Peter F.; Tartabini, Paul V.

2006-01-01

The development of methodologies, techniques, and tools for analysis and simulation of multi-body separation is critically needed for successful design and operation of next generation launch vehicles. As a part of this activity, ConSep simulation tool is being developed. ConSep is a generic MATLAB-based front-and-back-end to the commercially available ADAMS. solver, an industry standard package for solving multi-body dynamic problems. This paper discusses the 3-body separation capability in ConSep and its application to the separation of the Shuttle Solid Rocket Boosters (SRBs) from the External Tank (ET) and the Orbiter. The results are compared with STS-1 flight data.

Closeup view of the External Tank and Solid Rocket Boosters ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

Close-up view of the External Tank and Solid Rocket Boosters at the Launch Pad at Kennedy Space Center. Note the Hydrogen Vent Arm extending out from the Fixed Service Structure at attached to the Intertank segment of the External Tank. - Space Transportation System, Orbiter Discovery (OV-103), Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

46 CFR 91.40-3 - Drydock examination, internal structural examination, cargo tank internal examination, and...

Code of Federal Regulations, 2010 CFR

2010-10-01

... hull barge with internal framing 1 Double hull barge with external framing 2 Single hull barge with..., ends, and bottoms) when the structural framing is on the internal tank surface. 2 Applicable to double hull tank barges (double sides, ends, and bottoms) when the structural framing is on the external tank...

KSC-06pd0562

NASA Image and Video Library

2006-03-29

KENNEDY SPACE CENTER, FLA. - In the Vehicle Assembly Building at NASA's Kennedy Space Center, workers begin removal of the nose cap on top of external tank number 119, the tank designated for mission STS-121. The cap is being removed in order to install a new gaseous oxygen vent valve under the nose cap. Vapors are created prior to launch as the liquid oxygen in the external tank boils off. At the forward end of each external tank propellant tank is a vent and relief valve that can be opened before launch for venting or by excessive tank pressure for relief. The vent function is available only before launch. Mission STS-121 to the International Space Station is scheduled for launch in July. Photo credit: NASA/Jim Grossmann

KSC-06pd0563

NASA Image and Video Library

2006-03-29

KENNEDY SPACE CENTER, FLA. - In the Vehicle Assembly Building at NASA's Kennedy Space Center, workers remove the nose cap on top of external tank number 119, the tank designated for mission STS-121. The cap is being removed in order to install a new gaseous oxygen vent valve under the nose cap. Vapors are created prior to launch as the liquid oxygen in the external tank boils off. At the forward end of each external tank propellant tank is a vent and relief valve that can be opened before launch for venting or by excessive tank pressure for relief. The vent function is available only before launch. Mission STS-121 to the International Space Station is scheduled for launch in July. Photo credit: NASA/Jim Grossmann

KSC-06pd0614

NASA Image and Video Library

2006-04-13

KENNEDY SPACE CENTER, FLA. - In the transfer aisle of the Vehicle Assembly Building, workers get ready to ablate the rim around the nose cap of external tank number 119, the tank designated for mission STS-121. The cap was removed in order to install a new gaseous oxygen vent valve underneath. Vapors are created prior to launch as the liquid oxygen in the external tank boils off. At the forward end of each external tank propellant tank is a vent and relief valve that can be opened before launch for venting or by excessive tank pressure for relief. The vent function is available only before launch. Mission STS-121 to the International Space Station is scheduled for launch in July. Photo credit: NASA/Jim Grossmann

Manufacturing Challenges Implementing Material Changes for the Super Light Weight External Tank: A Welding Process Perspective

NASA Technical Reports Server (NTRS)

Lawless, K.; Jones, C.

2001-01-01

A viewgraph presentation gives an overview of the manufacturing challenges in implementing welding material changes for the super lightweight external tank. Details are given on the external tank configuration, the weld purging equipment used, planning the selection of weld filler wire alloy, the initial weld microstructure, the wide panel tensile testing, and the dome cap welding.

Pressurization System Modeling for a Generic Bimese Two- Stage-to-Orbit Reusable Launch Vehicle

NASA Technical Reports Server (NTRS)

Mazurkivich, Pete; Chandler, Frank; Nguyen, Han

2005-01-01

A pressurization system model was developed for a generic bimese Two-Stage-to-orbit Reusable Launch Vehicle using a cross-feed system and operating with densified propellants. The model was based on the pressurization system model for a crossfeed subscale water test article and was validated with test data obtained from the test article. The model consists of the liquid oxygen and liquid hydrogen pressurization models, each made up of two submodels, Booster and Orbiter tank pressurization models. The tanks are controlled within a 0.2-psi band and pressurized on the ground with ambient helium and autogenously in flight with gaseous oxygen and gaseous hydrogen. A 15-psi pressure difference is maintained between the Booster and Orbiter tanks to ensure crossfeed check valve closure before Booster separation. The analysis uses an ascent trajectory generated for a generic bimese vehicle and a tank configuration based on the Space Shuttle External Tank. It determines the flow rates required to pressurize the tanks on the ground and in flight, and demonstrates the model's capability to analyze the pressurization system performance of a full-scale bimese vehicle with densified propellants.

46 CFR 64.19 - External pressure.

Code of Federal Regulations, 2012 CFR

2012-10-01

... HANDLING SYSTEMS Standards for an MPT § 64.19 External pressure. (a) A tank without a vacuum breaker must be designed to withstand an external pressure of 71/2 psig or more. (b) A tank with a vacuum breaker...

46 CFR 64.19 - External pressure.

Code of Federal Regulations, 2013 CFR

2013-10-01

... HANDLING SYSTEMS Standards for an MPT § 64.19 External pressure. (a) A tank without a vacuum breaker must be designed to withstand an external pressure of 71/2 psig or more. (b) A tank with a vacuum breaker...

46 CFR 64.19 - External pressure.

Code of Federal Regulations, 2014 CFR

2014-10-01

... HANDLING SYSTEMS Standards for an MPT § 64.19 External pressure. (a) A tank without a vacuum breaker must be designed to withstand an external pressure of 71/2 psig or more. (b) A tank with a vacuum breaker...

46 CFR 64.19 - External pressure.

Code of Federal Regulations, 2011 CFR

2011-10-01

... HANDLING SYSTEMS Standards for an MPT § 64.19 External pressure. (a) A tank without a vacuum breaker must be designed to withstand an external pressure of 71/2 psig or more. (b) A tank with a vacuum breaker...

46 CFR 64.19 - External pressure.

Code of Federal Regulations, 2010 CFR

2010-10-01

... HANDLING SYSTEMS Standards for an MPT § 64.19 External pressure. (a) A tank without a vacuum breaker must be designed to withstand an external pressure of 71/2 psig or more. (b) A tank with a vacuum breaker...

KSC-05PD-0562

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. In the Vehicle Assembly Building at NASAs Kennedy Space Center, workers check the digital still camera they will mount in the External Tank (ET) umbilical well on the aft end of Space Shuttle Discovery. The camera is being used to obtain and downlink high-resolution images of the disconnect point on the ET following the tank's separation from the orbiter after launch. The Kodak camera will record 24 images, at one frame per 1.5 seconds, on a flash memory card. After orbital insertion, the crew will transfer the images from the memory card to a laptop computer. The files will then be downloaded through the Ku-band system to the Mission Control Center in Houston for analysis.

Structural Continuum Modeling of Space Shuttle External Tank Foam Insulation

NASA Technical Reports Server (NTRS)

Steeve, Brian; Ayala, Sam; Purlee, T. Eric; Shaw, Phillip

2006-01-01

The Space Shuttle External Tank is covered with rigid polymeric closed-cell foam insulation to prevent ice formation, protect the metallic tank from aerodynamic heating, and control the breakup of the tank during re-entry. The cryogenic state of the tank, as well as the ascent into a vacuum environment, places this foam under significant stress. Because the loss of the foam during ascent poses a critical risk to the shuttle orbiter, there is much interest in understanding the stress state in the foam insulation and how it may contribute to fracture and debris loss. Several foam applications on the external tank have been analyzed using finite element methods. This presentation describes the approach used to model the foam material behavior and compares analytical results to experiments.

High current lightning test of space shuttle external tank lightning protection system

NASA Technical Reports Server (NTRS)

Mumme, E.; Anderson, A.; Schulte, E. H.

1977-01-01

During lift-off, the shuttle launch vehicle (external tank, solid rocket booster and orbiter) may be subjected to a lightning strike. Tests of a proposed lightning protection method for the external tank and development materials which were subjected to simulated lightning strikes are described. Results show that certain of the high resistant paint strips performed remarkably well in diverting the 50 kA lightning strikes.

High Resolution Millimeter Wave Detection of Vertical Cracks in the Space Shuttle External Tank Spray-On-Foam Insulation (SOFI)

NASA Technical Reports Server (NTRS)

Kharkovsky, S.; Zoughi, R.; Hepburn, F.

2006-01-01

Space Shuttle Columbia s catastrophic failure, the separation of a piece of spray-on-foam insulation (SOFI) from the external tank (ET) in the Space Shuttle Discovery s flight in 2005 and crack detected in its ET foam prior to its successful launch in 2006 emphasize the need for effective nondestructive methods for inspecting the shuttle ET SOFI. Millimeter wave nondestructive testing methods have been considered as potential and effective inspection tools for evaluating the integrity of the SOFI. This paper presents recent results of an investigation for the purpose of detecting vertical cracks in SOFI panels using a focused millimeter wave (150 GHz) reflectometer. The presented images of the SOFI panels show the capability of this reflectometer for detecting tight vertical cracks (also as a function of crack opening dimension) in exposed SOFI panels and while covered by a piece of SOFI ramp simulating a more realistic and challenging situation.

Analysis of effect of internal and operating variables on performance of SVDS constraint model (ABIND)

NASA Technical Reports Server (NTRS)

Pendergrass, J. R.; Walsh, R. L.

1975-01-01

An examination of the factors which modify the simulation of a constraint in the motion of the aft attach points of the orbiter and external tank during separation has been made. The factors considered were both internal (spring and damper constants) and external (friction coefficient and dynamic pressure). The results show that an acceptable choice of spring/damper constant combinations exist over the expected range of the external factors and that the choice is consistent with a practical integration interval. The constraint model is shown to produce about a 10 percent increase in the relative body pitch angles over the unconstrained case whereas the MDC-STL constraint model is shown to produce about a 38 percent increase.

Hail damage on Atlantis' external tank is inspected

NASA Image and Video Library

2007-04-13

In the Vehicle Assembly Building, Mike Ravenscroft, with United Space Alliance, points to some of the foam repair done on the external tank of Space Shuttle Atlantis. Holes filled with foam are sanded flush with the adjacent area. In late February, Atlantis' external tank received hail damage during a severe thunderstorm that passed through the Kennedy Space Center Launch Complex 39 area. The hail caused visible divots in the giant tank's foam insulation as well as minor surface damage to about 26 heat shield tiles on the shuttle's left wing. The launch now is targeted for June 8.

Hypersonic aerodynamic characteristics of NR-ATP orbiter, orbiter with external tank, and ascent configuration

NASA Technical Reports Server (NTRS)

Ashby, G. C., Jr.

1973-01-01

A scale model of the North American Rockwell ATP Orbiter with and without the external tank has been tested in a 22-inch helium tunnel at Mach 20 and a Reynolds number based on model length, of 2.14 times one million. Longitudinal and lateral-directional data were determined for the orbiter alone while only longitudinal characteristics and elevon roll effectiveness were investigated for the orbiter/tank combination. Oil flow and electron beam flow visualization studies were conducted for the orbiter alone, orbiter with external tank and the ascent configuration.

Solid Rocket Boosters Separation

NASA Technical Reports Server (NTRS)

1982-01-01

This view, taken by a motion picture tracking camera for the STS-3 mission, shows both left and right solid rocket boosters (SRB's) at the moment of separation from the external tank (ET). After impact to the ocean, they were retrieved and refurbished for reuse. The Shuttle's SRB's and solid rocket motors (SRM's) are the largest ever built and the first designed for refurbishment and reuse. Standing nearly 150-feet high, the twin boosters provide the majority of thrust for the first two minutes of flight, about 5.8 million pounds. That is equivalent to 44 million horsepower, or the combined power of 400,000 subcompact cars.

KSC-07pd2453

NASA Image and Video Library

2007-09-14

KENNEDY SPACE CENTER, FLA. -- The Pegasus barge passes through the haulover canal on the Banana River with its cargo of external tank No. 125. The barge is being towed to the turn basin in the Launch Complex 39 Area where the external tank will be offloaded and moved to the Vehicle Assembly Building. The external tank will be used on space shuttle Atlantis for mission STS-122 targeted for launch on Dec. 6. Photo credit: NASA/Troy Cryder

46 CFR 151.04-5 - Inspection for certification.

Code of Federal Regulations, 2014 CFR

2014-10-01

... external examination of the tank is not possible because of insulation, the owner shall ensure that— (1) The amount of insulation deemed necessary by the marine inspector is removed during each cargo tank internal inspection to allow spot external examination of the tanks and insulation; or (2) The thickness of...

KSC-00padig095

NASA Image and Video Library

2000-11-21

KENNEDY SPACE CENTER, FLA. -- A newly arrived external tank is transported from the turn basin to the Vehicle Assembly Building (VAB), seen behind the tank. External tanks are built by the NASA Michoud Assembly Facility in New Orleans and transported by barge to Cape Canaveral and then up the Banana River to the turn basin in the Launch Complex 39 Area. In the VAB, the tank will await stacking for a future Shuttle mission

KSC00padig096

NASA Image and Video Library

2000-11-21

KENNEDY SPACE CENTER, FLA. -- A newly arrived external tank heads from the turn basin toward the Vehicle Assembly Building (VAB), seen behind the tank. External tanks are built by the NASA Michoud Assembly Facility in New Orleans and transported by barge to Cape Canaveral and then up the Banana River to the turn basin in the Launch Complex 39 Area. In the VAB, the tank will await stacking for a future Shuttle mission

KSC-00padig096

NASA Image and Video Library

2000-11-21

KENNEDY SPACE CENTER, FLA. -- A newly arrived external tank heads from the turn basin toward the Vehicle Assembly Building (VAB), seen behind the tank. External tanks are built by the NASA Michoud Assembly Facility in New Orleans and transported by barge to Cape Canaveral and then up the Banana River to the turn basin in the Launch Complex 39 Area. In the VAB, the tank will await stacking for a future Shuttle mission

Space Shuttle Projects

NASA Image and Video Library

1983-07-01

This photograph was taken during the final assembly phase of the Space Shuttle light weight external tanks (LWT) 5, 6, and 7 at the Michoud Assembly Facility in New Orleans, Louisiana. The giant cylinder, higher than a 15-story building, with a length of 154-feet (47-meters) and a diameter of 27.5-feet (8.4-meters), is the largest single piece of the Space Shuttle. During launch, the external tank (ET) acts as a backbone for the orbiter and solid rocket boosters. In separate, internal pressurized tank sections, the ET holds the liquid hydrogen fuel and liquid oxygen oxidizer for the Shuttle's three main engines. During launch, the ET feeds the fuel under pressure through 17-inch (43.2-centimeter) ducts which branch off into smaller lines that feed directly into the main engines. Some 64,000 gallons (242,260 liters) of fuel are consumed by the main engines each minute. Machined from aluminum alloys, the Space Shuttle's ET is the only part of the launch vehicle that currently is not reused. After its 526,000 gallons (1,991,071 liters) of propellants are consumed during the first 8.5 minutes of flight, it is jettisoned from the orbiter and breaks up in the upper atmosphere, its pieces falling into remote ocean waters. The Marshall Space Flight Center was responsible for developing the ET

KSC-04PD-1270

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. After leaving the Vehicle Assembly Building, the external tank seen here points its way toward the Turn Basin and the Banana River. The tank will be loaded onto the waiting barge and transferred to the Michoud Space Systems Assembly Facility near New Orleans where redesign of the external tank is underway for Return to Flight.

KSC-07pd2452

NASA Image and Video Library

2007-09-14

KENNEDY SPACE CENTER, FLA. -- Tugboats guide the Pegasus barge carrying external tank No. 125 in the Banana River after the barge's long journey around the Florida Peninsula from the Michoud Assembly Facility near New Orleans. The barge is being towed to the turn basin in the Launch Complex 39 Area where the external tank will be offloaded and moved to the Vehicle Assembly Building. The external tank will be used on space shuttle Atlantis for mission STS-122 targeted for launch on Dec. 6. Photo credit: NASA/Troy Cryder

KSC-99pp0199

NASA Image and Video Library

1999-02-09

KENNEDY SPACE CENTER, FLA. -- An external tank is suspended in the transfer aisle of the Vehicle Assembly Building before being placed into its storage compartment. The largest and heaviest element of the Space Shuttle, an external tank contains the liquid hydrogen fuel and liquid oxygen oxidizer for the three Space Shuttle main engines (SSMEs) in the orbiter during liftoff and ascent. When the SSMEs are shut down, the external tank is jettisoned, breaking up as it enters the Earth's atmopshere and impacting in a remote ocean area. It is not recovered

STS-121: Discovery Mission Management Team Briefing

NASA Technical Reports Server (NTRS)

2006-01-01

The briefing opened with Bruce Buckingham (NASA Public Affairs) introducing John Shannon (Chairman, Mission Management Team, JSC), John Chapman (External Tank Project Manager), Mike Leinbach (Shuttle Launch Director), and 1st Lt. Kaleb Nordgren (USAF 45th Weather Squadron). John Shannon reported that the team for hydrogen loading was proceeding well and the external tank detanking was completed. During detanking the inspection team cracked foam caused by condensation and ice formation as the tank expanded and contracted. Aerothermal analysis and analysis fro ice formation will be completed before launch. John Chapman explained the mechanics of the external tank design, the foam cracking, bracket design, etc. Mike Leinbach discussed the inspection teams and their inspection final inspection for ice formation before and after external tank filling. The inspection team of eight very experienced personnel also use telescopes with cameras to find any problems before launch. Kaleb Nordgren discussed weather and said there was a 40% chance of weather prohibiting launch. The floor was the opened for questions from the press.

KSC-04pd1269

NASA Image and Video Library

2004-04-28

KENNEDY SPACE CENTER, FLA. - With employees walking alongside, the external tank atop its transporter turns the corner from the Vehicle Assembly Building toward the Turn Basin and the Banana River. The tank will be loaded onto the waiting barge and transferred to the Michoud Space Systems Assembly Facility near New Orleans where redesign of the external tank is underway for Return to Flight.

KSC-04pd1268

NASA Image and Video Library

2004-04-28

KENNEDY SPACE CENTER, FLA. - Atop a transporter, the external tank seen here turns the corner from the Vehicle Assembly Building toward the Turn Basin and the Banana River. The tank will be loaded onto the waiting barge and transferred to the Michoud Space Systems Assembly Facility near New Orleans where redesign of the external tank is underway for Return to Flight.

KSC-04PD-1269

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. With employees walking alongside, the external tank atop its transporter turns the corner from the Vehicle Assembly Building toward the Turn Basin and the Banana River. The tank will be loaded onto the waiting barge and transferred to the Michoud Space Systems Assembly Facility near New Orleans where redesign of the external tank is underway for Return to Flight.

KSC-04PD-1268

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. Atop a transporter, the external tank seen here turns the corner from the Vehicle Assembly Building toward the Turn Basin and the Banana River. The tank will be loaded onto the waiting barge and transferred to the Michoud Space Systems Assembly Facility near New Orleans where redesign of the external tank is underway for Return to Flight.

Design, fabrication and test of a liquid hydrogen titanium honeycomb cryogenic test tank for use as a reusable launch vehicle main propellant tank

NASA Astrophysics Data System (ADS)

Stickler, Patrick B.; Keller, Peter C.

1998-01-01

Reusable Launch Vehicles (RLV's) utilizing LOX\\LH2 as the propellant require lightweight durable structural systems to meet mass fraction goals and to reduce overall systems operating costs. Titanium honeycomb sandwich with flexible blanket TPS on the windward surface is potentially the lightest-weight and most operable option. Light weight is achieved in part because the honeycomb sandwich tank provides insulation to its liquid hydrogen contents, with no need for separate cryogenic insulation, and in part because the high use temperature of titanium honeycomb reduces the required surface area of re-entry thermal protection systems. System operability is increased because TPS needs to be applied only to surfaces where temperatures exceed approximately 650 K. In order to demonstrate the viability of a titanium sandwich constructed propellant tank, a technology demonstration program was conducted including the design, fabrication and testing of a propellant tank-TPS system. The tank was tested in controlled as well as ambient environments representing ground hold conditions for a RLV main propellant tank. Data collected during each test run was used to validate predictions for air liquefaction, outside wall temperature, boil-off rates, frost buildup and its insulation effects, and the effects of placing a thermal protection system blanket on the external surface. Test results indicated that titanium honeycomb, when used as a RLV propellant tank material, has great promise as a light-weight structural system.

The qualification of the shuttle booster separation motors

NASA Technical Reports Server (NTRS)

Chase, C. A.; Fisher, K. M.; Eoff, W.

1978-01-01

Four booster separation motors (BSM) located at each end of every solid rocket booster (SRB) provide the needed side force to separate the boosters from the external tank at booster burnout. Four BSMs at the top of the SRB are located in a box pattern in the nose cone frustum. The four BSMs at the aft end of the SRB are arranged side-by-side on the SRB aft skirt. Aspects of BSM design and performance are considered, taking into account a motor design/performance summary, the case design, the insulation, the grain design, the nozzle/aft closure design, the ignition system, the propellant, and the motor assembly. Details of motor testing are also discussed, giving attention to development testing, qualification testing, and flight testing.

Closeup view of the Solid Rocket Booster (SRB) Frustum mounted ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

Close-up view of the Solid Rocket Booster (SRB) Frustum mounted on ground support equipment in the Solid Rocket Booster Assembly and Refurbishment Facility at Kennedy Space Center as it is being prepared to be mated with the Nose Cap and Forward Skirt. The Frustum contains the three Main Parachutes, Altitude Switches and forward booster Separation Motors. The Separation Motors burn for one second to ensure the SRBs drift away from the External Tank and Orbiter at separation. The three main parachutes are deployed to reduce speed as the SRBs descend to a splashdown in the Atlantic Ocean where they are recovered refurbished and reused. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Shuttle Propulsion Overview - The Design Challenges

NASA Technical Reports Server (NTRS)

Owen, James W.

2011-01-01

The major elements of the Space Shuttle Main Propulsion System include two reusable solid rocket motors integrated into recoverable solid rocket boosters, an expendable external fuel and oxidizer tank, and three reusable Space Shuttle Main Engines. Both the solid rocket motors and space shuttle main engines ignite prior to liftoff, with the solid rocket boosters separating about two minutes into flight. The external tank separates, about eight and a half minutes into the flight, after main engine shutdown and is safely expended in the ocean. The SSME's, integrated into the Space Shuttle Orbiter aft structure, are reused after post landing inspections. The configuration is called a stage and a half as all the propulsion elements are active during the boost phase, with only the SSME s continuing operation to achieve orbital velocity. Design and performance challenges were numerous, beginning with development work in the 1970's. The solid rocket motors were large, and this technology had never been used for human space flight. The SSME s were both reusable and very high performance staged combustion cycle engines, also unique to the Space Shuttle. The multi body side mount configuration was unique and posed numerous integration and interface challenges across the elements. Operation of the system was complex and time consuming. This paper describes the design challenges and key areas where the design evolved during the program.

49 CFR 179.200-8 - Tank heads.

Code of Federal Regulations, 2014 CFR

2014-10-01

... Transportation Other Regulations Relating to Transportation (Continued) PIPELINE AND HAZARDOUS MATERIALS SAFETY ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) SPECIFICATIONS FOR TANK CARS Specifications for Non-Pressure Tank Car Tanks (Classes DOT-111AW and 115AW) § 179.200-8 Tank heads. (a) All external tank heads...

49 CFR 179.200-8 - Tank heads.

Code of Federal Regulations, 2013 CFR

2013-10-01

... Transportation Other Regulations Relating to Transportation (Continued) PIPELINE AND HAZARDOUS MATERIALS SAFETY ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) SPECIFICATIONS FOR TANK CARS Specifications for Non-Pressure Tank Car Tanks (Classes DOT-111AW and 115AW) § 179.200-8 Tank heads. (a) All external tank heads...

40 CFR Table 1 to Subpart Bbbbbb... - Applicability Criteria, Emission Limits, and Management Practices for Storage Tanks

Code of Federal Regulations, 2010 CFR

2010-07-01

... and operate each internal and external floating roof gasoline storage tank according to the applicable... (b) Equip each internal floating roof gasoline storage tank according to the requirements in § 60... the requirements in § 60.112b(a)(1)(iv) through (ix) of this chapter; and (c) Equip each external...

KSC-07pd2455

NASA Image and Video Library

2007-09-14

KENNEDY SPACE CENTER, FLA. -- Tugboats tow the Pegasus barge through the bridge at the haulover canal on the Banana River. The barge is carrying external tank No. 125. After it is offloaded, the tank will be moved to the Vehicle Assembly Building. The external tank will be used on space shuttle Atlantis for mission STS-122 targeted for launch on Dec. 6. Photo credit: NASA/Troy Cryder

Analysis of stress concentration in the Dutton groove regions of the Super Lightweight External Tank

NASA Astrophysics Data System (ADS)

Ahmed, R.

1995-05-01

Because the 2195 aluminum-lithium material of the super lightweight external tank (SLWT ET) has a lower toughness than the 2219 aluminum used in previous ET's, careful attention must be paid to stress concentrations. This report details the analysis performed on some of the stress concentrations in the orthogrid panels of the liquid hydrogen tank.

Space Shuttle - Bringing cryohydrogen technology down to earth. [details of LH2 and LO2 technology and External Tank design

NASA Technical Reports Server (NTRS)

Odom, J. B.

1978-01-01

The External Tank must provide a safe storage container for both LH2 and LO2, a means of maintaining propellant quality in order to meet the engine pump net positive suction pressure requirements, and a structural strong-back for the Space Shuttle system, all at the minimum recurring cost and weight, while maintaining quality and reliability. The present paper summarizes External Tank design features and discusses the advantages of using LH2 and LO2 for the Space Shuttle system.

Structural Continuum Modeling of Space Shuttle External Tank Foam Insulation

NASA Technical Reports Server (NTRS)

Steeve, Brian; Ayala, Sam; Purlee, T. Eric; Shaw, Phillip

2006-01-01

This document is a viewgraph presentation reporting on work in modeling the foam insulation of the Space Shuttle External Tank. An analytical understanding of foam mechanics is required to design against structural failure. The Space Shuttle External Tank is covered primarily with closed cell foam to: Prevent ice, Protect structure from ascent aerodynamic and engine plume heating, and Delay break-up during re-entry. It is important that the foam does not shed unacceptable debris during ascent environment. Therefore a modeling of the foam insulation was undertaken.

LH2 Liquid Separator Tank Delivery

NASA Image and Video Library

2016-11-17

A new liquid hydrogen separator tank arrives at NASA's Kennedy Space Center in Florida. The tank will be lifted and rotated for delivery to Launch Pad 39B. The new separator/storage tank will be added to the pad's existing hydrogen vent system to assure gaseous hydrogen is delivered downstream to the flare stack. The 60,000 gallon tank was built by INOXCVA, in Baytown, Texas, a subcontractor of Precision Mechanical Inc. in Cocoa Florida. The new tank will support all future launches from the pad.

KSC-04pd2129

NASA Image and Video Library

2004-10-14

KENNEDY SPACE CENTER, FLA. - External Tank 118 (ET-118) is lowered from its cell in the Vehicle Assembly Building in order to place it on a transporter. The tank will be transferred to NASA’s Michoud Assembly Facility in New Orleans. The tank is being installed with an improved bipod fitting, which connects the external fuel tank to the Shuttle during launch. The new design, a significant milestone in the effort to return the Shuttle to safe flight, replaces the foam that was used to prevent ice buildup on the tank’s bipod fittings with four rod-shaped heaters. The heaters are being retrofitted on the 11 existing tanks and incorporated into the manufacture of all new tanks.

KSC-04pd2132

NASA Image and Video Library

2004-10-14

KENNEDY SPACE CENTER, FLA. - External Tank 118 (ET-118) is slowly moved above the transporter in the transfer aisle of the Vehicle Assembly Building before being lowered. The tank will be transferred to NASA’s Michoud Assembly Facility in New Orleans. The tank is being installed with an improved bipod fitting, which connects the external fuel tank to the Shuttle during launch. The new design, a significant milestone in the effort to return the Shuttle to safe flight, replaces the foam that was used to prevent ice buildup on the tank’s bipod fittings with four rod-shaped heaters. The heaters are being retrofitted on the 11 existing tanks and incorporated into the manufacture of all new tanks.

KSC-04pd2133

NASA Image and Video Library

2004-10-14

KENNEDY SPACE CENTER, FLA. - Workers in the transfer aisle of the Vehicle Assembly Building check the progress of External Tank 118 (ET-118) as it is lowered onto the transporter below it. The tank will be transferred to NASA’s Michoud Assembly Facility in New Orleans. The tank is being installed with an improved bipod fitting, which connects the external fuel tank to the Shuttle during launch. The new design, a significant milestone in the effort to return the Shuttle to safe flight, replaces the foam that was used to prevent ice buildup on the tank’s bipod fittings with four rod-shaped heaters. The heaters are being retrofitted on the 11 existing tanks and incorporated into the manufacture of all new tanks.

KSC-04pd2128

NASA Image and Video Library

2004-10-14

KENNEDY SPACE CENTER, FLA. - External Tank 118 (ET-118) is lifted from its cell in the Vehicle Assembly Building in order to place it on a transporter. The tank will be transferred to NASA’s Michoud Assembly Facility in New Orleans. The tank is being installed with an improved bipod fitting, which connects the external fuel tank to the Shuttle during launch. The new design, a significant milestone in the effort to return the Shuttle to safe flight, replaces the foam that was used to prevent ice buildup on the tank’s bipod fittings with four rod-shaped heaters. The heaters are being retrofitted on the 11 existing tanks and incorporated into the manufacture of all new tanks.

49 CFR 179.200-8 - Tank heads.

Code of Federal Regulations, 2012 CFR

2012-10-01

... 49 Transportation 3 2012-10-01 2012-10-01 false Tank heads. 179.200-8 Section 179.200-8... ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) SPECIFICATIONS FOR TANK CARS Specifications for Non-Pressure Tank Car Tanks (Classes DOT-111AW and 115AW) § 179.200-8 Tank heads. (a) All external tank heads...

49 CFR 179.200-8 - Tank heads.

Code of Federal Regulations, 2011 CFR

2011-10-01

... 49 Transportation 3 2011-10-01 2011-10-01 false Tank heads. 179.200-8 Section 179.200-8... ADMINISTRATION, DEPARTMENT OF TRANSPORTATION (CONTINUED) SPECIFICATIONS FOR TANK CARS Specifications for Non-Pressure Tank Car Tanks (Classes DOT-111AW and 115AW) § 179.200-8 Tank heads. (a) All external tank heads...

Elevations, Major Component Isometric, Propellant Flow Schematic, and External Tank ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

Elevations, Major Component Isometric, Propellant Flow Schematic, and External Tank Connection to Shuttle Main Engines - Space Transportation System, Space Shuttle Main Engine, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Heat transfer test of an 0.006-scale thin-skin thermocouple space shuttle model (50-0, 41-T) in the NASA-Ames Research Center 3.5-foot hypersonic wind tunnel at Mach 5.3 (IH28), volume 1

NASA Technical Reports Server (NTRS)

Cummings, J. W.; Foster, T. F.; Lockman, W. K.

1976-01-01

Data obtained from a heat transfer test conducted on an 0.006-scale space shuttle orbiter and external tank in the NASA-Ames Research Center 3.5-foot Hypersonic Wind Tunnel are presented. The purpose of this test was to obtain data under simulated return-to-launch-site abort conditions. Configurations tested were integrated orbiter and external tank, orbiter alone, and external tank alone at angles of attack of 0, + or - 30, + or - 60, + or - 90, and + or - 120 degrees. Runs were conducted at Mach numbers of 5.2 and 5.3 for Reynolds numbers of 1.0 and 4.0 million per foot, respectively. Heat transfer data were obtained from 75 orbiter and 75 external tank iron-constantan thermocouples.

KSC-2010-1071

NASA Image and Video Library

2010-01-07

CAPE CANAVERAL, Fla. - In Orbiter Processing Facility 1 at NASA's Kennedy Space Center in Florida, United Space Alliance technicians prepare to perform a push test on an external tank door beneath space shuttle Atlantis. Two umbilical doors, located on the shuttle's aft fuselage, close after external tank separation following launch. The test confirms that the door's actuators are functioning properly and that signals sent from the actuators correctly indicate that the doors have closed, creating the necessary thermal barrier for reentry. Atlantis is next slated to deliver an Integrated Cargo Carrier and Russian-built Mini Research Module to the International Space Station on the STS-132 mission. The second in a series of new pressurized components for Russia, the module will be permanently attached to the Zarya module. Three spacewalks are planned to store spare components outside the station, including six spare batteries, a boom assembly for the Ku-band antenna and spares for the Canadian Dextre robotic arm extension. A radiator, airlock and European robotic arm for the Russian Multi-purpose Laboratory Module also are payloads on the flight. Launch is targeted for May 14, 2010. Photo credit: NASA/Troy Cryder

KSC-2010-1075

NASA Image and Video Library

2010-01-07

CAPE CANAVERAL, Fla. - In Orbiter Processing Facility 1 at NASA's Kennedy Space Center in Florida, United Space Alliance technicians study the results of a push test performed on an external tank door on space shuttle Atlantis. Two umbilical doors, located on the shuttle's aft fuselage, close after external tank separation following launch. The test confirms that the door's actuators are functioning properly and that signals sent from the actuators correctly indicate that the doors have closed, creating the necessary thermal barrier for reentry. Atlantis is next slated to deliver an Integrated Cargo Carrier and Russian-built Mini Research Module to the International Space Station on the STS-132 mission. The second in a series of new pressurized components for Russia, the module will be permanently attached to the Zarya module. Three spacewalks are planned to store spare components outside the station, including six spare batteries, a boom assembly for the Ku-band antenna and spares for the Canadian Dextre robotic arm extension. A radiator, airlock and European robotic arm for the Russian Multi-purpose Laboratory Module also are payloads on the flight. Launch is targeted for May 14, 2010. Photo credit: NASA/Troy Cryder

KSC-2010-1070

NASA Image and Video Library

2010-01-07

CAPE CANAVERAL, Fla. - In Orbiter Processing Facility 1 at NASA's Kennedy Space Center in Florida, preparations are under way to perform a push test on an external tank door, shown in this close-up, of space shuttle Atlantis. Two umbilical doors, located on the shuttle's aft fuselage, close after external tank separation following launch. The test confirms that the door's actuators are functioning properly and that signals sent from the actuators correctly indicate that the doors have closed, creating the necessary thermal barrier for reentry. Atlantis is next slated to deliver an Integrated Cargo Carrier and Russian-built Mini Research Module to the International Space Station on the STS-132 mission. The second in a series of new pressurized components for Russia, the module will be permanently attached to the Zarya module. Three spacewalks are planned to store spare components outside the station, including six spare batteries, a boom assembly for the Ku-band antenna and spares for the Canadian Dextre robotic arm extension. A radiator, airlock and European robotic arm for the Russian Multi-purpose Laboratory Module also are payloads on the flight. Launch is targeted for May 14, 2010. Photo credit: NASA/Troy Cryder

KSC-2010-1073

NASA Image and Video Library

2010-01-07

CAPE CANAVERAL, Fla. - In Orbiter Processing Facility 1 at NASA's Kennedy Space Center in Florida, United Space Alliance technicians perform a push test on an external tank door on space shuttle Atlantis. Two umbilical doors, located on the shuttle's aft fuselage, close after external tank separation following launch. The test confirms that the door's actuators are functioning properly and that signals sent from the actuators correctly indicate that the doors have closed, creating the necessary thermal barrier for reentry. Atlantis is next slated to deliver an Integrated Cargo Carrier and Russian-built Mini Research Module to the International Space Station on the STS-132 mission. The second in a series of new pressurized components for Russia, the module will be permanently attached to the Zarya module. Three spacewalks are planned to store spare components outside the station, including six spare batteries, a boom assembly for the Ku-band antenna and spares for the Canadian Dextre robotic arm extension. A radiator, airlock and European robotic arm for the Russian Multi-purpose Laboratory Module also are payloads on the flight. Launch is targeted for May 14, 2010. Photo credit: NASA/Troy Cryder

Alternate space shuttle concepts study. Part 2: Technical summary. Volume 2: Orbiter definition

NASA Technical Reports Server (NTRS)

1971-01-01

A study was conducted of a three-engined external hydrogen tank orbiter/heat sink booster utilizing 415 K sea level thrust engines. The results of the study, pertaining to the orbiter portion of the configuration, are presented. A complete summary of characteristics is given for the external tank configuration along with some comparative data for a conventional internal tank configuration.

KSC-2011-8167

NASA Image and Video Library

2011-12-02

CAPE CANAVERAL, Fla. – A truck positions a full-size display of a space shuttle external fuel tank from the Kennedy Space Center Visitor Complex at a temporary storage area at NASA's Kennedy Space Center. The tank was part of a display of the external tank and two solid rocket boosters at the visitor complex that were used to show visitors the size of actual space shuttle components. A space shuttle rode piggyback on the tank and boosters at liftoff and during the ascent into space. The tank, which held propellants for the shuttle's three main engines, was not reused, but burned up in the atmosphere and fell into the ocean. Photo credit: NASA/Dmitri Gerondidakis

LH2 Liquid Separator Tank Lift, Rotate, and Move to Trailer

NASA Image and Video Library

2016-11-17

A new liquid hydrogen separator tank arrives at NASA's Kennedy Space Center in Florida. A crane is used to lift and rotate the tank before delivery to Launch Pad 39B. The new separator/storage tank will be added to the pad's existing hydrogen vent system to assure gaseous hydrogen is delivered downstream to the flare stack. The 60,000 gallon tank was built by INOXCVA, in Baytown, Texas, a subcontractor of Precision Mechanical Inc. in Cocoa Florida. The new tank will support all future launches from the pad.

LH2 Liquid Separator Tank Lift, Rotate, and Move to Trailer

NASA Image and Video Library

2016-11-17

A new liquid hydrogen separator tank arrives at NASA's Kennedy Space Center in Florida. A crane is used to lift the tank and rotate it before it is delivered to Launch Pad 39B. The new separator/storage tank will be added to the pad's existing hydrogen vent system to assure gaseous hydrogen is delivered downstream to the flare stack. The 60,000 gallon tank was built by INOXCVA, in Baytown, Texas, a subcontractor of Precision Mechanical Inc. in Cocoa Florida. The new tank will support all future launches from the pad.

LH2 Liquid Separator Tank Delivery

NASA Image and Video Library

2016-11-17

A new liquid hydrogen separator tank arrives at NASA's Kennedy Space Center in Florida. A crane will be used to lift and rotate the tank for delivery to Launch Pad 39B. The new separator/storage tank will be added to the pad's existing hydrogen vent system to assure gaseous hydrogen is delivered downstream to the flare stack. The 60,000 gallon tank was built by INOXCVA, in Baytown, Texas, a subcontractor of Precision Mechanical Inc. in Cocoa Florida. The new tank will support all future launches from the pad.

LH2 Liquid Separator Tank Lift, Rotate, and Move to Trailer

NASA Image and Video Library

2016-11-17

A new liquid hydrogen separator tank arrives at NASA's Kennedy Space Center in Florida. A crane is used to lift and rotate the tank before it is delivered to Launch Pad 39B. The new separator/storage tank will be added to the pad's existing hydrogen vent system to assure gaseous hydrogen is delivered downstream to the flare stack. The 60,000 gallon tank was built by INOXCVA, in Baytown, Texas, a subcontractor of Precision Mechanical Inc. in Cocoa Florida. The new tank will support all future launches from the pad.

Space Shuttle External Tank Project status

NASA Technical Reports Server (NTRS)

Davis, R. M.

1980-01-01

The External Tank Project is reviewed with emphasis on the DDT&E and production phases and the lightweight tank development. It is noted that the DDT&E phase is progressing well with the structural and ground vibration test article programs complete, the propulsion test article program progressing well, and the component qualification and verification testing 92% complete. New tools and facilities are being brought on line to support the increased build rate for the production phase. The lightweight tank, which will provide additional payload in orbit, is progressing to schedule with first delivery in early 1982.

KSC-04pd2131

NASA Image and Video Library

2004-10-14

KENNEDY SPACE CENTER, FLA. - Workers in the transfer aisle of the Vehicle Assembly Building prepare to lower the External Tank 118 (ET-118) to a horizontal position before being placed on a transporter. The tank will be transferred to NASA’s Michoud Assembly Facility in New Orleans. The tank is being installed with an improved bipod fitting, which connects the external fuel tank to the Shuttle during launch. The new design, a significant milestone in the effort to return the Shuttle to safe flight, replaces the foam that was used to prevent ice buildup on the tank’s bipod fittings with four rod-shaped heaters. The heaters are being retrofitted on the 11 existing tanks and incorporated into the manufacture of all new tanks.

KSC-04pd2130

NASA Image and Video Library

2004-10-14

KENNEDY SPACE CENTER, FLA. - After being lowered from its cell in the Vehicle Assembly Building, External Tank 118 (ET-118) is suspended above the transfer aisle before being placed on the transporter at left. The tank will be transferred to NASA’s Michoud Assembly Facility in New Orleans. The tank is being installed with an improved bipod fitting, which connects the external fuel tank to the Shuttle during launch. The new design, a significant milestone in the effort to return the Shuttle to safe flight, replaces the foam that was used to prevent ice buildup on the tank’s bipod fittings with four rod-shaped heaters. The heaters are being retrofitted on the 11 existing tanks and incorporated into the manufacture of all new tanks.

Views of the external tank as it falls away from Discovery

NASA Image and Video Library

1995-07-13

STS070-303-007 (13 JULY 1995) --- The external fuel tank (ET) for STS-70 is photographed just after falling away from the space shuttle Discovery en route to the 101st human-tended United States space flight.

KSC-99pp0198

NASA Image and Video Library

1999-02-09

KENNEDY SPACE CENTER, FLA. -- In the transfer aisle of the Vehicle Assembly Building, Atlantis awaits a vacancy in one of the Orbiter Processing Facility bays. Seen behind the left wing is an external tank being raised to a vertical position. The largest and heaviest element of the Space Shuttle, an external tank contains the liquid hydrogen fuel and liquid oxygen oxidizer for the three Space Shuttle main engines (SSMEs) in the orbiter during liftoff and ascent. When the SSMEs are shut down, the external tank is jettisoned, breaking up as it enters the Earth's atmopshere and impacting in a remote ocean area. It is not recovered

KSC-99pp0197

NASA Image and Video Library

1999-02-09

KENNEDY SPACE CENTER, FLA. -- In the transfer aisle of the Vehicle Assembly Building, Atlantis awaits a vacancy in one of the Orbiter Processing Facility bays. Seen behind the right wing is an external tank being raised to a vertical position. The largest and heaviest element of the Space Shuttle, an external tank contains the liquid hydrogen fuel and liquid oxygen oxidizer for the three Space Shuttle main engines (SSMEs) in the orbiter during liftoff and ascent. When the SSMEs are shut down, the external tank is jettisoned, breaking up as it enters the Earth's atmopshere and impacting in a remote ocean area. It is not recovered

Simulation of Foam Divot Weight on External Tank Utilizing Least Squares and Neural Network Methods

NASA Technical Reports Server (NTRS)

Chamis, Christos C.; Coroneos, Rula M.

2007-01-01

Simulation of divot weight in the insulating foam, associated with the external tank of the U.S. space shuttle, has been evaluated using least squares and neural network concepts. The simulation required models based on fundamental considerations that can be used to predict under what conditions voids form, the size of the voids, and subsequent divot ejection mechanisms. The quadratic neural networks were found to be satisfactory for the simulation of foam divot weight in various tests associated with the external tank. Both linear least squares method and the nonlinear neural network predicted identical results.

Ring stability of underground toroidal tanks

NASA Astrophysics Data System (ADS)

Lubis, Asnawi; Su'udi, Ahmad

2017-06-01

The design of pressure vessels subjected to internal pressure is governed by its strength, while the design of pressure vessels subjected to external pressure is governed by its stability, which is for circular cross-section is called the ring stability. This paper presented the results of finite element study of ring stability of circular toroidal tank without stiffener under external pressure. The tank was placed underground and external pressure load from soil was simulated as pressure at the top of the vessel along 30° circumferentially. One might ask the reason for choosing toroidal rather than cylindrical tank. Preliminary finite element studies showed that toroidal shells can withstand higher external pressure than cylindrical shells. In this study, the volume of the tank was fixed for 15,000 litters. The buckling external pressure (pL) was calculated for radius ratio (R/r) of 2, 3, and 4. The corresponding cross-section radiuses were 724.3 mm, 632.7 mm, and 574.9 mm, respectively. The selected element type was SHELL 281 from the ANSYS element library. To obtain the buckling load, the arc-length method was used in the nonlinear analysis. Both material and geometric nonlinearities were activated during the analysis. The conclusion of this study is that short-radius and thin-walled toroidal shell produces higher buckling load.

Draw forming of scale shuttle external tank dome gores

NASA Technical Reports Server (NTRS)

Garfield, G.

1974-01-01

The process for manufacturing external tank dome gores is discussed. The test fixture and test procedure are described. The characteristics of the draw forming die are analyzed. The specific subjects included are: (1) forming, (2) trimming, (3) cleaning, and (4) heat treatment.

LH2 Liquid Separator Tank Lift, Rotate, and Move to Trailer

NASA Image and Video Library

2016-11-17

A new liquid hydrogen separator tank arrives at NASA's Kennedy Space Center in Florida. The tank has been lifted and rotated by crane and lowered back onto the flatbed truck for transport to Launch Pad 39B. The new separator/storage tank will be added to the pad's existing hydrogen vent system to assure gaseous hydrogen is delivered downstream to the flare stack. The 60,000 gallon tank was built by INOXCVA, in Baytown, Texas, a subcontractor of Precision Mechanical Inc. in Cocoa Florida. The new tank will support all future launches from the pad.

LH2 Liquid Separator Tank Lift, Rotate, and Move to Trailer

NASA Image and Video Library

2016-11-17

A new liquid hydrogen separator tank arrives at NASA's Kennedy Space Center in Florida. Construction workers check lines as a crane is attached to the tank to lift and rotate it before it is delivered to Launch Pad 39B. The new separator/storage tank will be added to the pad's existing hydrogen vent system to assure gaseous hydrogen is delivered downstream to the flare stack. The 60,000 gallon tank was built by INOXCVA, in Baytown, Texas, a subcontractor of Precision Mechanical Inc. in Cocoa Florida. The new tank will support all future launches from the pad.

LH2 Liquid Separator Tank Lift, Rotate, and Move to Trailer

NASA Image and Video Library

2016-11-17

A new liquid hydrogen separator tank arrives at NASA's Kennedy Space Center in Florida. A crane has been attached to the tank to lift and rotate it before it is delivered to Launch Pad 39B. The new separator/storage tank will be added to the pad's existing hydrogen vent system to assure gaseous hydrogen is delivered downstream to the flare stack. The 60,000 gallon tank was built by INOXCVA, in Baytown, Texas, a subcontractor of Precision Mechanical Inc. in Cocoa Florida. The new tank will support all future launches from the pad.

IRD dropout study

NASA Technical Reports Server (NTRS)

Yalowitz, Jeffrey S.; Schroer, Michael A.; Dickson, John E., Jr.

1992-01-01

This final report describes work performed by SRS Technologies for the NASA Marshall Space Flight Center under Contract NAS8-39077, entitled 'Integrated Receiver-Decoder Dropout Study'. The purpose of the study was to determine causes of signal fading effects on ultra-high-frequency (UHF) range safety transmissions to the Space Shuttle during flyout. Of particular interest were deep fades observed at the External Tank (ET) Integrated Receiver-Decoder (IRD) during the flyout interval between solid rocket booster separation and ET separation. Analytical and simulation methods were employed in this study to assess observations captured in flight telemetry data records. Conclusions based on the study are presented in this report, and recommendations are given for future experimental validation of the results.

KSC-02pd0559

NASA Image and Video Library

2002-04-24

KENNEDY SPACE CENTER, FLA. -- A tug boat tows a newly arrived external tank in the Banana River to its offloading site. External tanks are built by the NASA Michoud Assembly Facility in New Orleans and transported by barge to Cape Canaveral and then up the Banana River to the turn basin in the Launch Complex 39 Area. From there it will be transported to the Vehicle Assembly Building where the tank will await stacking for a future Shuttle mission

Space Shuttle external tank: Today - DDT & E: Tomorrow - Production

NASA Technical Reports Server (NTRS)

Norton, A. M.; Tanner, E. J.

1979-01-01

The External Tank (ET) is the structural backbone of the Space Shuttle. The ET is discussed relative to its role; its design as a highly efficient Shuttle element; the liquid oxygen tank - a thin shelled monocoque; the intertank - the forward structural connection; the liquid hydrogen tank structure - the connection with the Orbiter; the ET structural verification; the propulsion system - a variety of functions; the electrical subsystem; electrical subsystem qualification; the thermal protection system; and other related problems. To date the qualification programs have been extremely successful and are almost complete, and the first flight tank has been delivered. Tomorrow's objectives will concentrate on establishing the facilities, tools and processes to achieve a production rate of 24 ETs/year.

Structural analysis of a frangible nut used on the NASA Space Shuttle

DOE Office of Scientific and Technical Information (OSTI.GOV)

Metzinger, K.E.

A structural analysis methodology has been developed for the NASA 2.5-inch frangible nut used on the Space Shuttle. Two of these nuts are used to secure the External Tank to the aft end of the Orbiter. Both nuts must completely fracture before the Orbiter can safely separate from the External Tank. Ideally, only one of the two explosive boosters contained in each nut must detonate to completely break a nut. However, after an uncontrolled change in the Inconel 718 material processing, recent tests indicate that in certain circumstances both boosters may be required. This report details the material characterization andmore » subsequent structural analyses of nuts manufactured from two lots of Inconel 718. The nuts from the HSX lot were observed to consistently separate with only one booster, while the nuts from the HBT lot never completely fracture with a single booster. The material characterization requires only tensile test data and the determination of a tearing parameter based on a computer simulation of a tensile test. Subsequent structural analyses using the PRONTO2D finite element code correctly predict the differing response of nuts fabricated from these two lots. This agreement is important because it demonstrates that this technique can be used to screen lots of Inconel 718 before manufacturing frangible nuts from them. To put this new capability to practice, Sandia personnel have transferred this technology to the Pyrotechnics Group at NASA-JSC.« less

Selected KSC Applied Physics Lab Responses to Shuttle Processing Measurement Requests

NASA Technical Reports Server (NTRS)

Youngquist, Robert C.

2010-01-01

The KSC Applied Physics Lab has been supporting Shuttle Ground Processing for over 20 years by solving problems brought to us by Shuttle personnel. Roughly half of the requests to our lab have been to find ways to make measurements, or to improve on an existing measurement process. This talk will briefly cover: 1) Centering the aft end of the External Tank between the Solid Rocket Boosters; 2) Positioning the GOX Vent Hood over the External Tank; 3) Remote Measurements of External Tank Damage; 4) Strain Measurement in the Orbiter Sling; and 5) Over-center Distance Measurement in an Over-center Mechanism.

KSC-2013-1079

NASA Image and Video Library

2013-01-11

CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, two space shuttle external fuel tank transporters are being prepared for transfer to the Wings of Dreams Aviation Museum at Keystone Heights Airport between Gainesville and Jacksonville, Fla. At the Wings of Dreams Aviation Museum a mock-up shuttle external fuel tank will be displayed. During space shuttle launches, the external tanks contained over 500,000 gallons of liquid hydrogen and liquid oxygen propellant for the shuttle orbiters' three main engines. The effort is part of Transition and Retirement of the space shuttle. For more information, visit http://www.nasa.gov/transition Photo credit: NASA/ Jim Grossmann

KSC-2013-1082

NASA Image and Video Library

2013-01-11

CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, two space shuttle external fuel tank transporters are being prepared for transfer to the Wings of Dreams Aviation Museum at Keystone Heights Airport between Gainesville and Jacksonville, Fla. At the Wings of Dreams Aviation Museum a mock-up shuttle external fuel tank will be displayed. During space shuttle launches, the external tanks contained over 500,000 gallons of liquid hydrogen and liquid oxygen propellant for the shuttle orbiters' three main engines. The effort is part of Transition and Retirement of the space shuttle. For more information, visit http://www.nasa.gov/transition Photo credit: NASA/ Jim Grossmann

KSC-2013-1080

NASA Image and Video Library

2013-01-11

CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, two space shuttle external fuel tank transporters are being prepared for transfer to the Wings of Dreams Aviation Museum at Keystone Heights Airport between Gainesville and Jacksonville, Fla. At the Wings of Dreams Aviation Museum a mock-up shuttle external fuel tank will be displayed. During space shuttle launches, the external tanks contained over 500,000 gallons of liquid hydrogen and liquid oxygen propellant for the shuttle orbiters' three main engines. The effort is part of Transition and Retirement of the space shuttle. For more information, visit http://www.nasa.gov/transition Photo credit: NASA/ Jim Grossmann

KSC-2013-1081

NASA Image and Video Library

2013-01-11

CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, two space shuttle external fuel tank transporters are being prepared for transfer to the Wings of Dreams Aviation Museum at Keystone Heights Airport between Gainesville and Jacksonville, Fla. At the Wings of Dreams Aviation Museum a mock-up shuttle external fuel tank will be displayed. During space shuttle launches, the external tanks contained over 500,000 gallons of liquid hydrogen and liquid oxygen propellant for the shuttle orbiters' three main engines. The effort is part of Transition and Retirement of the space shuttle. For more information, visit http://www.nasa.gov/transition Photo credit: NASA/ Jim Grossmann

Room temperature stretch forming of scale space shuttle external tank dome gores. Volume 1: Technical

NASA Technical Reports Server (NTRS)

Blunck, R. D.; Krantz, D. E.

1974-01-01

An account of activities and data gathered in the Room Temperature Stretch Forming of One-third Scale External Tank Bulkhead Gores for space shuttle study, and a tooling design and production cost study are reported. The following study phases are described: (1) the stretch forming of three approximately one-third scale external tank dome gores from single sheets of 2219-T37 aluminum alloy; (2) the designing of a full scale production die, including a determination of tooling requirements; and (3) the determination of cost per gore at the required production rates, including manufacturing, packaging, and shipping.

KSC-07pd3664

NASA Image and Video Library

2007-12-30

KENNEDY SPACE CENTER, FLA. -- At Launch Pad 39A, a team of external tank specialists from Lockheed Martin and the United Space Alliance undertakes the task of removing the hydrogen feed-through connector in support of space shuttle Atlantis' STS-122 mission. Here, a technician inspects the connector just removed from the external tank. Some of the tank's engine cutoff sensors, or ECO sensors, failed during propellant tanking for launch attempts on Dec. 6 and Dec. 9. Results of a tanking test on Dec. 18 pointed to an open circuit in the feed-through connector wiring, which is located at the base of the tank. The feed-through connector passes the wires from the inside of the tank to the outside. After the data from additional testing on the connector is analyzed, shuttle program managers will decide on a forward plan. Launch of STS-122 is targeted for January 2008. Photo credit: NASA/George Shelton

KSC-07pd3663

NASA Image and Video Library

2007-12-30

KENNEDY SPACE CENTER, FLA. -- At Launch Pad 39A, a team of external tank specialists from Lockheed Martin and the United Space Alliance undertakes the task of removing the hydrogen feed-through connector in support of space shuttle Atlantis' STS-122 mission. Here, a technician demates the connector from the external tank. Some of the tank's engine cutoff sensors, or ECO sensors, failed during propellant tanking for launch attempts on Dec. 6 and Dec. 9. Results of a tanking test on Dec. 18 pointed to an open circuit in the feed-through connector wiring, which is located at the base of the tank. The feed-through connector passes the wires from the inside of the tank to the outside. After the data from additional testing on the connector is analyzed, shuttle program managers will decide on a forward plan. Launch of STS-122 is targeted for January 2008. Photo credit: NASA/George Shelton

KSC-07pd3662

NASA Image and Video Library

2007-12-30

KENNEDY SPACE CENTER, FLA. -- At Launch Pad 39A, a team of external tank specialists from Lockheed Martin and the United Space Alliance undertakes the task of removing the hydrogen feed-through connector in support of space shuttle Atlantis' STS-122 mission. Here, a technician disconnects the connector before it is demated from the external tank. Some of the tank's engine cutoff sensors, or ECO sensors, failed during propellant tanking for launch attempts on Dec. 6 and Dec. 9. Results of a tanking test on Dec. 18 pointed to an open circuit in the feed-through connector wiring, which is located at the base of the tank. The feed-through connector passes the wires from the inside of the tank to the outside. After the data from additional testing on the connector is analyzed, shuttle program managers will decide on a forward plan. Launch of STS-122 is targeted for January 2008. Photo credit: NASA/George Shelton

76 FR 14643 - Hazardous Materials: Safety Requirements for External Product Piping on Cargo Tanks Transporting...

Federal Register 2010, 2011, 2012, 2013, 2014

2011-03-17

... for External Product Piping on Cargo Tanks Transporting Flammable Liquids AGENCY: Pipeline and...) seeking public comment on a proposal to prohibit the transportation of flammable liquids in exposed... DEPARTMENT OF TRANSPORTATION Pipeline and Hazardous Materials Safety Administration 49 CFR Part...

External Tank No. 120 heads for the open door of the VAB

NASA Image and Video Library

2007-07-30

Aboard a transporter, external tank No. 120 heads for the open door of the Vehicle Assembly Building. There it will be lifted into a checkout cell. ET-120 will be used for launching Space Shuttle Discovery on mission STS-120 in October.

Structural and mechanical design challenges of space shuttle solid rocket boosters separation and recovery subsystems

NASA Technical Reports Server (NTRS)

Woodis, W. R.; Runkle, R. E.

1985-01-01

The design of the space shuttle solid rocket booster (SRB) subsystems for reuse posed some unique and challenging design considerations. The separation of the SRBs from the cluster (orbiter and external tank) at 150,000 ft when the orbiter engines are running at full thrust meant the two SRBs had to have positive separation forces pushing them away. At the same instant, the large attachments that had reacted launch loads of 7.5 million pounds thrust had to be servered. These design considerations dictated the design requirements for the pyrotechnics and separation rocket motors. The recovery and reuse of the two SRBs meant they had to be safely lowered to the ocean, remain afloat, and be owed back to shore. In general, both the pyrotechnic and recovery subsystems have met or exceeded design requirements. In twelve vehicles, there has only been one instance where the pyrotechnic system has failed to function properly.

Closeup view of the Solid Rocket Booster (SRB) Frustum mounted ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

Close-up view of the Solid Rocket Booster (SRB) Frustum mounted on ground support equipment in the Solid Rocket Booster Assembly and Refurbishment Facility at Kennedy Space Center as it is being prepared to be mated with the Nose Cap and Forward Skirt. The Frustum contains the three Main Parachutes, Altitude Switches and forward booster Separation Motors. The Separation Motors burn for one second to ensure the SRBs drift away from the External Tank and Orbiter at separation. The three main parachutes are deployed to reduce speed as the SRBs descend to a splashdown in the Atlantic Ocean where they are recovered refurbished and reused. In this view the assembly is rotated so that the four Separation Motors are in view and aligned with the approximate centerline of the image. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

46 CFR 31.10-24 - Integral fuel oil tank examinations-T/ALL.

Code of Federal Regulations, 2010 CFR

2010-10-01

... tanks cleaned out and gas freed as necessary to permit internal examination of the tank or tanks... of each vessel during an internal structural examination at intervals not to exceed five years. (b... inspector is able to determine by external examination that the general condition of the tanks is...

Cell design concepts for aqueous lithium-oxygen batteries: A model-based assessment

NASA Astrophysics Data System (ADS)

Grübl, Daniel; Bessler, Wolfgang G.

2015-11-01

Seven cell design concepts for aqueous (alkaline) lithium-oxygen batteries are investigated using a multi-physics continuum model for predicting cell behavior and performance in terms of the specific energy and specific power. Two different silver-based cathode designs (a gas diffusion electrode and a flooded cathode) and three different separator designs (a porous separator, a stirred separator chamber, and a redox-flow separator) are compared. Cathode and separator thicknesses are varied over a wide range (50 μm-20 mm) in order to identify optimum configurations. All designs show a considerable capacity-rate effect due to spatiotemporally inhomogeneous precipitation of solid discharge product LiOH·H2O. In addition, a cell design with flooded cathode and redox-flow separator including oxygen uptake within the external tank is suggested. For this design, the model predicts specific power up to 33 W/kg and specific energy up to 570 Wh/kg (gravimetric values of discharged cell including all cell components and catholyte except housing and piping).

KSC-07pd0928

NASA Image and Video Library

2007-04-25

KENNEDY SPACE CENTER, FLA. -- In the Vehicle Assembly Building, workers check foam repairs on Atlantis' external tank. In late February, Atlantis' external tank received hail damage during a severe thunderstorm that passed through the Kennedy Space Center Launch Complex 39 area. The hail caused visible divots in the giant tank's foam insulation as well as minor surface damage to about 26 heat shield tiles on the shuttle's left wing. The launch now is targeted for June 8. Photo credit: NASA/Jack Pfaller

Quantitative analysis of ice films by near-infrared spectroscopy

NASA Technical Reports Server (NTRS)

Keiser, Joseph T.

1990-01-01

One of the outstanding problems in the Space Transportation System is the possibility of the ice buildup on the external fuel tank surface while it is mounted on the launch pad. During the T-2 hours (and holding) period, the frost/ice thickness on the external tank is monitored/measured. However, after the resumption of the countdown time, the tank surface can only be monitored remotely. Currently, remote sensing is done with a TV camera coupled to a thermal imaging device. This device is capable of identifying the presence of ice, especially if it is covered with a layer of frost. However, it has difficulty identifying transparent ice, and, it is not capable of determining the thickness of ice in any case. Thus, there is a need for developing a technique for measuring the thickness of frost/ice on the tank surface during this two hour period before launch. The external tank surface is flooded with sunlight (natural or simulated) before launch. It may be possible, therefore, to analyze the diffuse reflection of sunlight from the external tank to determine the presence and thickness of ice. The purpose was to investigate the feasibility of this approach. A near-infrared spectrophotometer was used to record spectra of ice. It was determined that the optimum frequencies for monitoring the ice films were 1.03 and 1.255 microns.

Aerial Refueling Clearance Process Guide

DTIC Science & Technology

2014-08-21

using multinational/bi-lateral agreements such as the ATARES Agreement, cross servicing agreements, replacement in kind agreements, Foreign Military...Lighting 8.7.8 External Paint Scheme 8.8 External Weapons/Drop Tanks 9.0 Physical /Aerodynamic Influences 9.1 Boom Clear Path To Receptacle dhkARSAG DOC...Cold Nose Sw. 8.5 External Fuel Tanks 9.0 Physical /Aerodynamic Influence R. 9.1 Probe Clear Path ie: Obstructions, Instruments etc. 9.2 Drogue Hookup

Separation Of Liquid And Gas In Zero Gravity

NASA Technical Reports Server (NTRS)

Howard, Frank S.; Fraser, Wilson S.

1991-01-01

Pair of reports describe scheme for separating liquid from gas so liquid could be pumped. Designed to operate in absence of gravitation. Jet of liquid, gas, or liquid/gas mixture fed circumferentially into cylindrical tank filled with liquid/gas mixture. Jet starts liquid swirling. Swirling motion centrifugally separates liquid from gas. Liquid then pumped from tank at point approximately diametrically opposite point of injection of jet. Vortex phase separator replaces such devices as bladders and screens. Requires no components inside tank. Pumps for gas and liquid outside tank and easily accessible for maintenance and repairs.

Development and Qualification of Alternate Blowing Agents for Space Shuttle External Tank Thermal Protection System

NASA Technical Reports Server (NTRS)

Williams, Charles W.; Cavalaris, James G.

1994-01-01

The Aerospace industry has a long history of using low density polyurethane and polyurethane-modified isocyanurate foam systems as lightweight, low cost, easily processed cryogenic Thermal Protection Systems (TPS) for ascent vehicles. The Thermal Protection System of the Space Shuttle External Tank (ET) is required so that quality liquid cryogenic propellant can be supplied to the Orbiter main engines and to protect the metal structure of the tanks from becoming too hot from aerodynamic heating, hence preventing premature break-up of the tank. These foams are all blown with CFC-1 I blowing agent which has been identified by the Environmental Protection Agency (EPA) as an ozone depleting substance. CFCs will not be manufactured after 1995, Consequently, alternate blowing agent substances must be identified and implemented to assure continued ET manufacture and delivery. This paper describes the various testing performed to select and qualify HCFC-1 41 b as a near term drop-in replacement for CFC-11. Although originally intended to be a one for one substitution in the formulation, several technical issues were identified regarding material performance and processability which required both formulation changes and special processing considerations to overcome. In order to evaluate these material changes, each material was subjected to various tests to qualify them to meet the various loads imposed on them during long term storage, pre-launch operations, launch, separation and re-entry. Each material was tested for structural, thermal, aeroshear, and stress/strain loads for the various flight environments each encounters. Details of the development and qualification program and the resolution of specific problems are discussed in this paper.

Operation and maintenance of the SOL-DANCE building solar system. Final report

DOE Office of Scientific and Technical Information (OSTI.GOV)

Not Available

1980-07-29

The Sol-Dance building solar heating system consists of 136 flat plate solar collectors divided evenly into two separate building systems, each providing its total output to a common thermal storage tank. An aromatic base transformer oil is circulated through a closed loop consisting of the collectors and a heat exchanger. Water from the thermal storage tank is passed through the same heat exchanger where heat from the oil is given up to the thermal storage. Back-up heat is provided by air source heat pumps. Heat is transferred from the thermal storage to the living space by liquid-to-air coils in themore » distribution ducts. Separate domestic hot water systems are provided for each building. The system consists of 2 flat plate collectors with a single 66 gallon storage tank with oil circulated in a closed loop through an external tube and shell heat exchanger. Some problems encountered and lessons learned during the project construction are listed as well as beneficial aspects and a project description. As-built drawings are provided as well as system photographs. An acceptance test plan is provided that checks the collection, thermal storage, and space and water heating subsystems and the total system installation. Predicted performance data are tabulated. Details are discussed regarding operation, maintenance, and repair, and manufacturers data are provided. (LEW)« less

Implementation of Precision Verification Solvents on the External Tank

NASA Technical Reports Server (NTRS)

Campbell, M.

1998-01-01

This paper presents the Implementation of Precision Verification Solvents on the External Tank. The topics include: 1) Background; 2) Solvent Usages; 3) TCE (Trichloroethylene) Reduction; 4) Solvent Replacement Studies; 5) Implementation; 6) Problems Occuring During Implementation; and 7) Future Work. This paper is presented in viewgraph form.

Detail view of the External Tank to Orbiter liquidhydrogen interface ...

Library of Congress Historic Buildings Survey, Historic Engineering Record, Historic Landscapes Survey

Detail view of the External Tank to Orbiter liquid-hydrogen interface panel as the Orbiter Discovery is being tested and prepped at the Vehicle Assembly Building at Kennedy Space Center. - Space Transportation System, Orbiter Discovery (OV-103), Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

STS-57 external tank (ET) falls away from Endeavour, OV-105, after jettison

NASA Image and Video Library

1993-06-21

STS057-03-017 (21 June 1993) --- The external fuel tank falls toward Earth after being jettisoned from the Space Shuttle Endeavour as the spacecraft headed toward its ten-day stay in Earth orbit. A 35mm camera was used to record the ET jettison.

KSC-04pd1275

NASA Image and Video Library

2004-05-05

KENNEDY SPACE CENTER, FLA. - A tug boat begins towing the barge containing an External Tank (ET) to Port Canaveral. There one of the SRB Retrieval Ships will take over and tow the ET to the Michoud Space Systems Assembly Facility near New Orleans where redesign of the external tank is underway for Return to Flight.

KSC-04pd1276

NASA Image and Video Library

2004-05-05

KENNEDY SPACE CENTER, FLA. - A tug boat tows the barge containing an External Tank (ET) to Port Canaveral. There one of the SRB Retrieval Ships will take over and tow the ET to the Michoud Space Systems Assembly Facility near New Orleans where redesign of the external tank is underway for Return to Flight.

KSC-04pd1277

NASA Image and Video Library

2004-05-05

KENNEDY SPACE CENTER, FLA. - A tug boat tows the barge containing an External Tank (ET) to Port Canaveral. There one of the SRB Retrieval Ships will take over and tow the ET to the Michoud Space Systems Assembly Facility near New Orleans where redesign of the external tank is underway for Return to Flight.

KSC-2011-8144

NASA Image and Video Library

2011-12-01

CAPE CANAVERAL, Fla. – Cranes remove a full-size replica of a space shuttle external fuel tank from the Kennedy Space Center Visitor Complex as the space-themed attraction makes way for a new exhibit featuring space shuttle Atlantis, which is currently undergoing preparations to go on public display. The tank is being placed into temporary storage at NASA's Kennedy Space Center. The tank was part of a mockup of the external tank and two solid rocket boosters at the visitor complex that were used to show visitors the size of actual space shuttle components. A space shuttle rode piggyback on the tank and boosters at liftoff and during the ascent into space. The tank, which held propellants for the shuttle's three main engines, was not reused, but burned up in the atmosphere and fell into the ocean. Photo credit: NASA/Jim Grossman

KSC-2011-8159

NASA Image and Video Library

2011-12-02

CAPE CANAVERAL, Fla. – A truck hauls a full-size display of a space shuttle external fuel tank from the Kennedy Space Center Visitor Complex as the space-themed attraction makes way for a new exhibit featuring space shuttle Atlantis, which is currently undergoing preparations to go on public display. The tank is being placed into temporary storage at NASA's Kennedy Space Center. The tank was part of a display of the external tank and two solid rocket boosters at the visitor complex that were used to show visitors the size of actual space shuttle components. A space shuttle rode piggyback on the tank and boosters at liftoff and during the ascent into space. The tank, which held propellants for the shuttle's three main engines, was not reused, but burned up in the atmosphere and fell into the ocean. Photo credit: NASA/Dmitri Gerondidakis

KSC-2011-8142

NASA Image and Video Library

2011-12-01

CAPE CANAVERAL, Fla. – Cranes remove a full-size replica of a space shuttle external fuel tank from the Kennedy Space Center Visitor Complex as the space-themed attraction makes way for a new exhibit featuring space shuttle Atlantis, which is currently undergoing preparations to go on public display. The tank is being placed into temporary storage at NASA's Kennedy Space Center. The tank was part of a mockup of the external tank and two solid rocket boosters at the visitor complex that were used to show visitors the size of actual space shuttle components. A space shuttle rode piggyback on the tank and boosters at liftoff and during the ascent into space. The tank, which held propellants for the shuttle's three main engines, was not reused, but burned up in the atmosphere and fell into the ocean. Photo credit: NASA/Jim Grossman

KSC-2011-8140

NASA Image and Video Library

2011-12-01

CAPE CANAVERAL, Fla. – Cranes remove a full-size replica of a space shuttle external fuel tank from the Kennedy Space Center Visitor Complex as the space-themed attraction makes way for a new exhibit featuring space shuttle Atlantis, which is currently undergoing preparations to go on public display. The tank is being placed into temporary storage at NASA's Kennedy Space Center. The tank was part of a mockup of the external tank and two solid rocket boosters at the visitor complex that were used to show visitors the size of actual space shuttle components. A space shuttle rode piggyback on the tank and boosters at liftoff and during the ascent into space. The tank, which held propellants for the shuttle's three main engines, was not reused, but burned up in the atmosphere and fell into the ocean. Photo credit: NASA/Jim Grossman

KSC-2011-8165

NASA Image and Video Library

2011-12-02

CAPE CANAVERAL, Fla. – A truck hauls a full-size display of a space shuttle external fuel tank from the Kennedy Space Center Visitor Complex as the space-themed attraction makes way for a new exhibit featuring space shuttle Atlantis, which is currently undergoing preparations to go on public display. The tank is being placed into temporary storage at NASA's Kennedy Space Center. The tank was part of a display of the external tank and two solid rocket boosters at the visitor complex that were used to show visitors the size of actual space shuttle components. A space shuttle rode piggyback on the tank and boosters at liftoff and during the ascent into space. The tank, which held propellants for the shuttle's three main engines, was not reused, but burned up in the atmosphere and fell into the ocean. Photo credit: NASA/Dmitri Gerondidakis

KSC-2011-8135

NASA Image and Video Library

2011-12-01

CAPE CANAVERAL, Fla. – Cranes remove a full-size replica of a space shuttle external fuel tank from the Kennedy Space Center Visitor Complex as the space-themed attraction makes way for a new exhibit featuring space shuttle Atlantis, which is currently undergoing preparations to go on public display. The tank is being placed into temporary storage at NASA's Kennedy Space Center. The tank was part of a mockup of the external tank and two solid rocket boosters at the visitor complex that were used to show visitors the size of actual space shuttle components. A space shuttle rode piggyback on the tank and boosters at liftoff and during the ascent into space. The tank, which held propellants for the shuttle's three main engines, was not reused, but burned up in the atmosphere and fell into the ocean. Photo credit: NASA/Jim Grossman

KSC-2011-8137

NASA Image and Video Library

2011-12-01

CAPE CANAVERAL, Fla. – A technician works on the removal of a full-size replica of a space shuttle external fuel tank from the Kennedy Space Center Visitor Complex as the space-themed attraction makes way for a new exhibit featuring space shuttle Atlantis, which is currently undergoing preparations to go on public display. The tank is being placed into temporary storage at NASA's Kennedy Space Center. The tank was part of a mockup of the external tank and two solid rocket boosters at the visitor complex that were used to show visitors the size of actual space shuttle components. A space shuttle rode piggyback on the tank and boosters at liftoff and during the ascent into space. The tank, which held propellants for the shuttle's three main engines, was not reused, but burned up in the atmosphere and fell into the ocean. Photo credit: NASA/Jim Grossman

KSC-2011-8141

NASA Image and Video Library

2011-12-01

CAPE CANAVERAL, Fla. – Cranes remove a full-size replica of a space shuttle external fuel tank from the Kennedy Space Center Visitor Complex as the space-themed attraction makes way for a new exhibit featuring space shuttle Atlantis, which is currently undergoing preparations to go on public display. The tank is being placed into temporary storage at NASA's Kennedy Space Center. The tank was part of a mockup of the external tank and two solid rocket boosters at the visitor complex that were used to show visitors the size of actual space shuttle components. A space shuttle rode piggyback on the tank and boosters at liftoff and during the ascent into space. The tank, which held propellants for the shuttle's three main engines, was not reused, but burned up in the atmosphere and fell into the ocean. Photo credit: NASA/Jim Grossman

KSC-2011-8146

NASA Image and Video Library

2011-12-01

CAPE CANAVERAL, Fla. – Cranes remove a full-size replica of a space shuttle external fuel tank from the Kennedy Space Center Visitor Complex as the space-themed attraction makes way for a new exhibit featuring space shuttle Atlantis, which is currently undergoing preparations to go on public display. The tank is being placed into temporary storage at NASA's Kennedy Space Center. The tank was part of a mockup of the external tank and two solid rocket boosters at the visitor complex that were used to show visitors the size of actual space shuttle components. A space shuttle rode piggyback on the tank and boosters at liftoff and during the ascent into space. The tank, which held propellants for the shuttle's three main engines, was not reused, but burned up in the atmosphere and fell into the ocean. Photo credit: NASA/Jim Grossman

KSC-2011-8166

NASA Image and Video Library

2011-12-02

CAPE CANAVERAL, Fla. – A truck hauls a full-size display of a space shuttle external fuel tank from the Kennedy Space Center Visitor Complex as the space-themed attraction makes way for a new exhibit featuring space shuttle Atlantis, which is currently undergoing preparations to go on public display. The tank is being placed into temporary storage at NASA's Kennedy Space Center. The tank was part of a display of the external tank and two solid rocket boosters at the visitor complex that were used to show visitors the size of actual space shuttle components. A space shuttle rode piggyback on the tank and boosters at liftoff and during the ascent into space. The tank, which held propellants for the shuttle's three main engines, was not reused, but burned up in the atmosphere and fell into the ocean. Photo credit: NASA/Dmitri Gerondidakis

KSC-2011-8145

NASA Image and Video Library

2011-12-01

CAPE CANAVERAL, Fla. – Cranes remove a full-size replica of a space shuttle external fuel tank from the Kennedy Space Center Visitor Complex as the space-themed attraction makes way for a new exhibit featuring space shuttle Atlantis, which is currently undergoing preparations to go on public display. The tank is being placed into temporary storage at NASA's Kennedy Space Center. The tank was part of a mockup of the external tank and two solid rocket boosters at the visitor complex that were used to show visitors the size of actual space shuttle components. A space shuttle rode piggyback on the tank and boosters at liftoff and during the ascent into space. The tank, which held propellants for the shuttle's three main engines, was not reused, but burned up in the atmosphere and fell into the ocean. Photo credit: NASA/Jim Grossman

KSC-2011-8164

NASA Image and Video Library

2011-12-02

CAPE CANAVERAL, Fla. – A truck hauls a full-size display of a space shuttle external fuel tank from the Kennedy Space Center Visitor Complex as the space-themed attraction makes way for a new exhibit featuring space shuttle Atlantis, which is currently undergoing preparations to go on public display. The tank is being placed into temporary storage at NASA's Kennedy Space Center. The tank was part of a display of the external tank and two solid rocket boosters at the visitor complex that were used to show visitors the size of actual space shuttle components. A space shuttle rode piggyback on the tank and boosters at liftoff and during the ascent into space. The tank, which held propellants for the shuttle's three main engines, was not reused, but burned up in the atmosphere and fell into the ocean. Photo credit: NASA/Dmitri Gerondidakis

KSC-2011-8134

NASA Image and Video Library

2011-12-01

CAPE CANAVERAL, Fla. – Cranes remove a full-size replica of a space shuttle external fuel tank from the Kennedy Space Center Visitor Complex as the space-themed attraction makes way for a new exhibit featuring space shuttle Atlantis, which is currently undergoing preparations to go on public display. The tank is being placed into temporary storage at NASA's Kennedy Space Center. The tank was part of a mockup of the external tank and two solid rocket boosters at the visitor complex that were used to show visitors the size of actual space shuttle components. A space shuttle rode piggyback on the tank and boosters at liftoff and during the ascent into space. The tank, which held propellants for the shuttle's three main engines, was not reused, but burned up in the atmosphere and fell into the ocean. Photo credit: NASA/Jim Grossman

KSC-2011-8162

NASA Image and Video Library

2011-12-02

CAPE CANAVERAL, Fla. – A truck hauls a full-size display of a space shuttle external fuel tank from the Kennedy Space Center Visitor Complex as the space-themed attraction makes way for a new exhibit featuring space shuttle Atlantis, which is currently undergoing preparations to go on public display. The tank is being placed into temporary storage at NASA's Kennedy Space Center. The tank was part of a display of the external tank and two solid rocket boosters at the visitor complex that were used to show visitors the size of actual space shuttle components. A space shuttle rode piggyback on the tank and boosters at liftoff and during the ascent into space. The tank, which held propellants for the shuttle's three main engines, was not reused, but burned up in the atmosphere and fell into the ocean. Photo credit: NASA/Dmitri Gerondidakis

KSC-2011-8160

NASA Image and Video Library

2011-12-02

CAPE CANAVERAL, Fla. – A truck hauls a full-size display of a space shuttle external fuel tank from the Kennedy Space Center Visitor Complex as the space-themed attraction makes way for a new exhibit featuring space shuttle Atlantis, which is currently undergoing preparations to go on public display. The tank is being placed into temporary storage at NASA's Kennedy Space Center. The tank was part of a display of the external tank and two solid rocket boosters at the visitor complex that were used to show visitors the size of actual space shuttle components. A space shuttle rode piggyback on the tank and boosters at liftoff and during the ascent into space. The tank, which held propellants for the shuttle's three main engines, was not reused, but burned up in the atmosphere and fell into the ocean. Photo credit: NASA/Dmitri Gerondidakis

KSC-2011-8161

NASA Image and Video Library

2011-12-02

CAPE CANAVERAL, Fla. – A truck hauls a full-size display of a space shuttle external fuel tank from the Kennedy Space Center Visitor Complex as the space-themed attraction makes way for a new exhibit featuring space shuttle Atlantis, which is currently undergoing preparations to go on public display. The tank is being placed into temporary storage at NASA's Kennedy Space Center. The tank was part of a display of the external tank and two solid rocket boosters at the visitor complex that were used to show visitors the size of actual space shuttle components. A space shuttle rode piggyback on the tank and boosters at liftoff and during the ascent into space. The tank, which held propellants for the shuttle's three main engines, was not reused, but burned up in the atmosphere and fell into the ocean. Photo credit: NASA/Dmitri Gerondidakis

KSC-2011-8143

NASA Image and Video Library

2011-12-01

CAPE CANAVERAL, Fla. – Cranes remove a full-size replica of a space shuttle external fuel tank from the Kennedy Space Center Visitor Complex as the space-themed attraction makes way for a new exhibit featuring space shuttle Atlantis, which is currently undergoing preparations to go on public display. The tank is being placed into temporary storage at NASA's Kennedy Space Center. The tank was part of a mockup of the external tank and two solid rocket boosters at the visitor complex that were used to show visitors the size of actual space shuttle components. A space shuttle rode piggyback on the tank and boosters at liftoff and during the ascent into space. The tank, which held propellants for the shuttle's three main engines, was not reused, but burned up in the atmosphere and fell into the ocean. Photo credit: NASA/Jim Grossman

KSC-2011-8139

NASA Image and Video Library

2011-12-01

CAPE CANAVERAL, Fla. – Cranes remove a full-size replica of a space shuttle external fuel tank from the Kennedy Space Center Visitor Complex as the space-themed attraction makes way for a new exhibit featuring space shuttle Atlantis, which is currently undergoing preparations to go on public display. The tank is being placed into temporary storage at NASA's Kennedy Space Center. The tank was part of a mockup of the external tank and two solid rocket boosters at the visitor complex that were used to show visitors the size of actual space shuttle components. A space shuttle rode piggyback on the tank and boosters at liftoff and during the ascent into space. The tank, which held propellants for the shuttle's three main engines, was not reused, but burned up in the atmosphere and fell into the ocean. Photo credit: NASA/Jim Grossman

KSC-2011-8136

NASA Image and Video Library

2011-12-01

CAPE CANAVERAL, Fla. – Cranes remove a full-size replica of a space shuttle external fuel tank from the Kennedy Space Center Visitor Complex as the space-themed attraction makes way for a new exhibit featuring space shuttle Atlantis, which is currently undergoing preparations to go on public display. The tank is being placed into temporary storage at NASA's Kennedy Space Center. The tank was part of a mockup of the external tank and two solid rocket boosters at the visitor complex that were used to show visitors the size of actual space shuttle components. A space shuttle rode piggyback on the tank and boosters at liftoff and during the ascent into space. The tank, which held propellants for the shuttle's three main engines, was not reused, but burned up in the atmosphere and fell into the ocean. Photo credit: NASA/Jim Grossman

KSC-2011-8138

NASA Image and Video Library

2011-12-01

CAPE CANAVERAL, Fla. – Cranes remove a full-size replica of a space shuttle external fuel tank from the Kennedy Space Center Visitor Complex as the space-themed attraction makes way for a new exhibit featuring space shuttle Atlantis, which is currently undergoing preparations to go on public display. The tank is being placed into temporary storage at NASA's Kennedy Space Center. The tank was part of a mockup of the external tank and two solid rocket boosters at the visitor complex that were used to show visitors the size of actual space shuttle components. A space shuttle rode piggyback on the tank and boosters at liftoff and during the ascent into space. The tank, which held propellants for the shuttle's three main engines, was not reused, but burned up in the atmosphere and fell into the ocean. Photo credit: NASA/Jim Grossman

KSC-2011-8147

NASA Image and Video Library

2011-12-01

CAPE CANAVERAL, Fla. – Cranes remove a full-size replica of a space shuttle external fuel tank from the Kennedy Space Center Visitor Complex as the space-themed attraction makes way for a new exhibit featuring space shuttle Atlantis, which is currently undergoing preparations to go on public display. The tank is being placed into temporary storage at NASA's Kennedy Space Center. The tank was part of a mockup of the external tank and two solid rocket boosters at the visitor complex that were used to show visitors the size of actual space shuttle components. A space shuttle rode piggyback on the tank and boosters at liftoff and during the ascent into space. The tank, which held propellants for the shuttle's three main engines, was not reused, but burned up in the atmosphere and fell into the ocean. Photo credit: NASA/Jim Grossman

Lunar habitat concept employing the space shuttle external tank.

PubMed

King, C B; Butterfield, A J; Hypes, W D; Nealy, J E; Simonsen, L C

1990-01-01

The space shuttle external tank, which consists of a liquid oxygen tank, an intertank structure, and a liquid hydrogen tank, is an expendable structure used for approximately 8.5 min during each launch. A concept for outfitting the liquid oxygen tank-intertank unit for a 12-person lunar habitat is described. The concept utilizes existing structures and openings for both man and equipment access without compromising the structural integrity of the tank. Living quarters, instrumentation, environmental control and life support, thermal control, and propulsion systems are installed at Space Station Freedom. The unmanned habitat is then transported to low lunar orbit and autonomously soft landed on the lunar surface. Design studies indicate that this concept is feasible by the year 2000 with concurrent development of a space transfer vehicle and manned cargo lander for crew changeover and resupply.

46 CFR 38.05-10 - Installation of cargo tanks-general-TB/ALL.

Code of Federal Regulations, 2011 CFR

2011-10-01

... prevent the tanks from shifting when subjected to external forces. Each tank shall be so supported as to prevent the concentration of excessive loads on the supporting portions of the shell or head as prescribed... consider the resonance of the cargo tank, or parts thereof, and the vibratory forces, found in the tank...

46 CFR 38.05-10 - Installation of cargo tanks-general-TB/ALL.

Code of Federal Regulations, 2012 CFR

2012-10-01

... prevent the tanks from shifting when subjected to external forces. Each tank shall be so supported as to prevent the concentration of excessive loads on the supporting portions of the shell or head as prescribed... consider the resonance of the cargo tank, or parts thereof, and the vibratory forces, found in the tank...

46 CFR 38.05-10 - Installation of cargo tanks-general-TB/ALL.

Code of Federal Regulations, 2014 CFR

2014-10-01

... prevent the tanks from shifting when subjected to external forces. Each tank shall be so supported as to prevent the concentration of excessive loads on the supporting portions of the shell or head as prescribed... consider the resonance of the cargo tank, or parts thereof, and the vibratory forces, found in the tank...

46 CFR 38.05-10 - Installation of cargo tanks-general-TB/ALL.

Code of Federal Regulations, 2010 CFR

2010-10-01

... prevent the tanks from shifting when subjected to external forces. Each tank shall be so supported as to prevent the concentration of excessive loads on the supporting portions of the shell or head as prescribed... consider the resonance of the cargo tank, or parts thereof, and the vibratory forces, found in the tank...

46 CFR 38.05-10 - Installation of cargo tanks-general-TB/ALL.

Code of Federal Regulations, 2013 CFR

2013-10-01

... prevent the tanks from shifting when subjected to external forces. Each tank shall be so supported as to prevent the concentration of excessive loads on the supporting portions of the shell or head as prescribed... consider the resonance of the cargo tank, or parts thereof, and the vibratory forces, found in the tank...

KSC-2010-1072

NASA Image and Video Library

2010-01-07

CAPE CANAVERAL, Fla. - In Orbiter Processing Facility 1 at NASA's Kennedy Space Center in Florida, United Space Alliance technicians verify the alignment of the test equipment that will be used to perform a push test on an external tank door on space shuttle Atlantis. Two umbilical doors, located on the shuttle's aft fuselage, close after external tank separation following launch. The test confirms that the door's actuators are functioning properly and that signals sent from the actuators correctly indicate that the doors have closed, creating the necessary thermal barrier for reentry. Atlantis is next slated to deliver an Integrated Cargo Carrier and Russian-built Mini Research Module to the International Space Station on the STS-132 mission. The second in a series of new pressurized components for Russia, the module will be permanently attached to the Zarya module. Three spacewalks are planned to store spare components outside the station, including six spare batteries, a boom assembly for the Ku-band antenna and spares for the Canadian Dextre robotic arm extension. A radiator, airlock and European robotic arm for the Russian Multi-purpose Laboratory Module also are payloads on the flight. Launch is targeted for May 14, 2010. Photo credit: NASA/Troy Cryder

KSC-2010-1076

NASA Image and Video Library

2010-01-07

CAPE CANAVERAL, Fla. - In Orbiter Processing Facility 1 at NASA's Kennedy Space Center in Florida, United Space Alliance technicians roll the test equipment away from an external tank door on space shuttle Atlantis following the successful completion of a push test. Two umbilical doors, located on the shuttle's aft fuselage, close after external tank separation following launch. The test confirms that the door's actuators are functioning properly and that signals sent from the actuators correctly indicate that the doors have closed, creating the necessary thermal barrier for reentry. Atlantis is next slated to deliver an Integrated Cargo Carrier and Russian-built Mini Research Module to the International Space Station on the STS-132 mission. The second in a series of new pressurized components for Russia, the module will be permanently attached to the Zarya module. Three spacewalks are planned to store spare components outside the station, including six spare batteries, a boom assembly for the Ku-band antenna and spares for the Canadian Dextre robotic arm extension. A radiator, airlock and European robotic arm for the Russian Multi-purpose Laboratory Module also are payloads on the flight. Launch is targeted for May 14, 2010. Photo credit: NASA/Troy Cryder

KSC-2010-1074

NASA Image and Video Library

2010-01-07

CAPE CANAVERAL, Fla. - In Orbiter Processing Facility 1 at NASA's Kennedy Space Center in Florida, United Space Alliance technicians remove the test equipment that was used to perform a push test on an external tank door on space shuttle Atlantis. Two umbilical doors, located on the shuttle's aft fuselage, close after external tank separation following launch. The test confirms that the door's actuators are functioning properly and that signals sent from the actuators correctly indicate that the doors have closed, creating the necessary thermal barrier for reentry. Atlantis is next slated to deliver an Integrated Cargo Carrier and Russian-built Mini Research Module to the International Space Station on the STS-132 mission. The second in a series of new pressurized components for Russia, the module will be permanently attached to the Zarya module. Three spacewalks are planned to store spare components outside the station, including six spare batteries, a boom assembly for the Ku-band antenna and spares for the Canadian Dextre robotic arm extension. A radiator, airlock and European robotic arm for the Russian Multi-purpose Laboratory Module also are payloads on the flight. Launch is targeted for May 14, 2010. Photo credit: NASA/Troy Cryder

KSC-07pd2397

NASA Image and Video Library

2007-09-05

KENNEDY SPACE CENTER, FLA. -- In the Vehicle Assembly Building at NASA's Kennedy Space Center, the top of external tank No. 120 is seen as the tank is lowered between the solid rocket boosters for mating on the mobile launcher platform. The external tank-SRB stack is being prepared for the orbiter Discovery, which will be mated to the stack in the VAB in two weeks. Space Shuttle Discovery is targeted to launch Oct. 23 on mission STS-120 to the International Space Station. Photo credit: NASA/George Shelton

KSC-07pd0927

NASA Image and Video Library

2007-04-25

KENNEDY SPACE CENTER, FLA. -- In the Vehicle Assembly Building, foam repairs on Atlantis' external tank include sanding and inspection, as seen here. In late February, Atlantis' external tank received hail damage during a severe thunderstorm that passed through the Kennedy Space Center Launch Complex 39 area. The hail caused visible divots in the giant tank's foam insulation as well as minor surface damage to about 26 heat shield tiles on the shuttle's left wing. The launch now is targeted for June 8. Photo credit: NASA/Jack Pfaller

KSC-07pd0929

NASA Image and Video Library

2007-04-25

KENNEDY SPACE CENTER, FLA. -- In the Vehicle Assembly Building, a worker carefully sands foam repairs on Atlantis' external tank. In late February, Atlantis' external tank received hail damage during a severe thunderstorm that passed through the Kennedy Space Center Launch Complex 39 area. The hail caused visible divots in the giant tank's foam insulation as well as minor surface damage to about 26 heat shield tiles on the shuttle's left wing. The launch now is targeted for June 8. Photo credit: NASA/Jack Pfaller

n/a

NASA Image and Video Library

1977-09-09

The first Space Shuttle External Tank, the Main Propulsion Test Article (MPTA), rolls off the assembly line September 9, 1977 at the Michoud Assembly Facility in New Orleans. The MPTA was then transported to the National Space Technology Laboratories in southern Mississippi where it was used in the first static firing of the three main engines. Marshall Space Flight Center had management responsibility for Space Shuttle propulsion elements, including the External Tank. Martin Marietta was the prime contractor who designed and assembled the tanks at Michoud.

Repairing the damage to Atlantis' External Tank

NASA Image and Video Library

2007-03-07

In high bay 1 of the Vehicle Assembly Building, a technician marks off an area for inspection on Atlantis' external tank. A severe thunderstorm with golf ball-sized hail caused visible divots in the giant tank's foam insulation and minor surface damage to about 26 heat shield tiles on the shuttle's left wing. Further evaluation of the tank is necessary to get an accurate accounting of foam damage and determine the type of repair required and the time needed for that work. A new target launch date has not been determined, but teams will focus on preparing Atlantis for liftoff in late April on mission STS-117.

Repairing the damage to Atlantis' External Tank

NASA Image and Video Library

2007-03-07

Technicians in the Vehicle Assembly Building prepare materials that will be used during repair of the nose cone on Atlantis' external tank. A severe thunderstorm with golf ball-sized hail caused visible divots in the giant tank's foam insulation and minor surface damage to about 26 heat shield tiles on the shuttle's left wing. Further evaluation of the tank is necessary to get an accurate accounting of foam damage and determine the type of repair required and the time needed for that work. A new target launch date has not been determined, but teams will focus on preparing Atlantis for liftoff in late April on mission STS-117.

Hail damage on Atlantis' external tank is inspected

NASA Image and Video Library

2007-04-13

In the Vehicle Assembly Building, markers show the hail damage being repaired on the external tank of Space Shuttle Atlantis. The white hole with a red circle around it is a hole prepared for molding and material application. The red material is sealant tape so the mold doesn't leak when the foam rises against the mold. The white/ translucent square mold is an area where the foam has been applied and the foam has risen and cured against the mold surface. The area will be de-molded and sanded flush with the adjacent area. In late February, Atlantis' external tank received hail damage during a severe thunderstorm that passed through the Kennedy Space Center Launch Complex 39 area. The hail caused visible divots in the giant tank's foam insulation as well as minor surface damage to about 26 heat shield tiles on the shuttle's left wing. The launch now is targeted for June 8.

KSC-07pd1407

NASA Image and Video Library

2007-06-07

KENNEDY SPACE CENTER, FLA. -- The "pencil sharpener" tool designed to trim the hand-sprayed foam repairs on the STS-117 external tank is on display for the media at the NASA News Center. This portable tool was designed in just 10 days specifically for this task by Lockheed Martin engineer Glenn Lapeyronnie at the Michoud external tank manufacturing facility in New Orleans. The pencil sharpener tool fits over the external tank nose cone spike at the top of the tank and extends down to where the hand-sprayed foam was used to repair the hail-damaged areas. The hail damage was incurred Feb. 28 while Space Shuttle Atlantis was on the launch pad for a March 15 launch. The shuttle returned to the Vehicle Assembly Building so that repairs could be made. Mission STS-117 is scheduled to launch at 7:38 p.m. EDT on June 8. Photo credit: NASA/Jack Pfaller

KSC-07pd1405

NASA Image and Video Library

2007-06-07

KENNEDY SPACE CENTER, FLA. -- The "pencil sharpener" tool designed to trim the hand-sprayed foam repairs on the STS-117 external tank is on display for the media at the NASA News Center. This portable tool was designed in just 10 days specifically for this task by Lockheed Martin engineer Glenn Lapeyronnie at the Michoud external tank manufacturing facility in New Orleans. The pencil sharpener tool fits over the external tank nose cone spike at the top of the tank and extends down to where the hand-sprayed foam was used to repair the hail-damaged areas. The hail damage was incurred Feb. 28 while Space Shuttle Atlantis was on the launch pad for a March 15 launch. The shuttle returned to the Vehicle Assembly Building so that repairs could be made. Mission STS-117 is scheduled to launch at 7:38 p.m. EDT on June 8. Photo credit: NASA/Jack Pfaller

KSC-07pd1406

NASA Image and Video Library

2007-06-07

KENNEDY SPACE CENTER, FLA. -- The "pencil sharpener" tool designed to trim the hand-sprayed foam repairs on the STS-117 external tank is on display for the media at the NASA News Center. This portable tool was designed in just 10 days specifically for this task by Lockheed Martin engineer Glenn Lapeyronnie at the Michoud external tank manufacturing facility in New Orleans. The pencil sharpener tool fits over the external tank nose cone spike at the top of the tank and extends down to where the hand-sprayed foam was used to repair the hail-damaged areas. The hail damage was incurred Feb. 28 while Space Shuttle Atlantis was on the launch pad for a March 15 launch. The shuttle returned to the Vehicle Assembly Building so that repairs could be made. Mission STS-117 is scheduled to launch at 7:38 p.m. EDT on June 8. Photo credit: NASA/Jack Pfaller

KSC-07pd1408

NASA Image and Video Library

2007-06-07

KENNEDY SPACE CENTER, FLA. -- The "pencil sharpener" tool designed to trim the hand-sprayed foam repairs on the STS-117 external tank is on display for the media at the NASA News Center. This portable tool was designed in just 10 days specifically for this task by Lockheed Martin engineer Glenn Lapeyronnie at the Michoud external tank manufacturing facility in New Orleans. The pencil sharpener tool fits over the external tank nose cone spike at the top of the tank and extends down to where the hand-sprayed foam was used to repair the hail-damaged areas. The hail damage was incurred Feb. 28 while Space Shuttle Atlantis was on the launch pad for a March 15 launch. The shuttle returned to the Vehicle Assembly Building so that repairs could be made. Mission STS-117 is scheduled to launch at 7:38 p.m. EDT on June 8. Photo credit: NASA/Jack Pfaller

Analysis and test for space shuttle propellant dynamics

NASA Technical Reports Server (NTRS)

Berry, R. L.; Demchak, L. J.; Tegart, J. R.

1983-01-01

This report presents the results of a study to develop an analytical model capable of predicting the dynamic interaction forces on the Shuttle External Tank, due to large amplitude propellant slosh during RTLS separation. The report details low-g drop tower and KC-135 test programs that were conducted to investigate propellant reorientation during RTLS. In addition, the development of a nonlinear finite element slosh model (LAMPS2, two dimensional, and one LAMPS3, three dimensional) is presented. Correlation between the model and test data is presented as a verification of the modeling approach.

The Effects of Spanwise Structures and Unsteady Forcing of Vortex Generators on a Shock-Induced Separated Flow Using Planar Laser Scattering

DTIC Science & Technology

2006-05-01

official policy or position of the United States Air Force, Department of Defense, or the U.S. Government." Report Documentation Page Form ApprovedOMB...I join my advisors in gratefully acknowledging the Air Force Office of Scientific Research for their support of this research under grant FA9550...was supplied with approximately 140 ft3 (4 m3) of air by a Worthington HB4 four-stage compressor. The air was stored in external tanks at a pressure

STS-1 operational flight profile. Volume 6: Abort analysis

NASA Technical Reports Server (NTRS)

1980-01-01

The abort analysis for the cycle 3 Operational Flight Profile (OFP) for the Space Transportation System 1 Flight (STS-1) is defined, superseding the abort analysis previously presented. Included are the flight description, abort analysis summary, flight design groundrules and constraints, initialization information, general abort description and results, abort solid rocket booster and external tank separation and disposal results, abort monitoring displays and discussion on both ground and onboard trajectory monitoring, abort initialization load summary for the onboard computer, list of the key abort powered flight dispersion analysis.

46 CFR 169.631 - Separation of machinery and fuel tank spaces from accommodation spaces.

Code of Federal Regulations, 2010 CFR

2010-10-01

... 46 Shipping 7 2010-10-01 2010-10-01 false Separation of machinery and fuel tank spaces from accommodation spaces. 169.631 Section 169.631 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED... machinery and fuel tank spaces from accommodation spaces. (a) Machinery and fuel tank spaces must be...

46 CFR 169.631 - Separation of machinery and fuel tank spaces from accommodation spaces.

Code of Federal Regulations, 2012 CFR

2012-10-01

... 46 Shipping 7 2012-10-01 2012-10-01 false Separation of machinery and fuel tank spaces from accommodation spaces. 169.631 Section 169.631 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED... machinery and fuel tank spaces from accommodation spaces. (a) Machinery and fuel tank spaces must be...

46 CFR 91.43-1 - When required.

Code of Federal Regulations, 2010 CFR

2010-10-01

... tanks cleaned out and gas freed as necessary to permit internal examination of the tank or tanks... of each vessel during an internal structural examination at intervals not to exceed five years. (b... inspector is able to determine by external examination that the general condition of the tanks is...

46 CFR 189.43-1 - When required.

Code of Federal Regulations, 2010 CFR

2010-10-01

... tanks cleaned out and gas freed as necessary to permit internal examination of the tank or tanks... of each vessel during an internal structural examination at intervals not to exceed five years. (b... inspector is able to determine by external examination that the general condition of the tanks is...

46 CFR 71.53-1 - When required.

Code of Federal Regulations, 2010 CFR

2010-10-01

... by internal examination of at least one forward double-bottom fuel oil tank, and by external... necessary to permit internal examination of the tank or tanks designated by the marine inspector. The owner or operator shall arrange for an examination of the fuel tanks of each vessel during an internal...

Simple method for forming thin-wall pressure vessels

NASA Technical Reports Server (NTRS)

Erickson, A. L.; Guist, L. R.

1972-01-01

Application of internal hydrostatic pressure to seam-welded circular cylindrical tanks having corner-welded, flat, circular ends forms large thin-walled high quality tanks. Form limits expansion of cylindrical portion of final tank while hemispherical ends develop freely; no external form or restraint is required to fabricate spherical tanks.

40 CFR 265.1085 - Standards: Tanks.

Code of Federal Regulations, 2010 CFR

2010-07-01

... controls shall use one of the following tanks: (1) A fixed-roof tank equipped with an internal floating... equipped with an external floating roof in accordance with the requirements specified in paragraph (f) of... controls air pollutant emissions from a tank using a fixed-roof with an internal floating roof shall meet...

Study of etchants for corrosion-resistant metals, space shuttle external tank

NASA Technical Reports Server (NTRS)

Simmons, J. R.

1980-01-01

Acceptable etchant concentrations and application and removal procedures for etching austenitic stainless steel, nickel base alloys, and titanium alloys (annealed) employed on the external tank were formulated. The etchant solutions were to be capable of removing a minimum of 0.4 mils of surface material in less than one hour.

Space Shuttle Project

NASA Image and Video Library

1978-04-21

This is an interior ground level view of the Shuttle Orbiter Enterprise being lowered for mating to External Tank (ET) inside Marshall Space Flight Center's Dynamic Test Stand for Mated Vertical Ground Vibration tests (MVGVT). The tests marked the first time ever that the entire shuttle complement (including Orbiter, external tank, and solid rocket boosters) were mated vertically.

Transition heating rates obtained on a matted and isolated 0.006 scale model (41-OT) space shuttle orbiter and external tank in the NASA/LaRC variable density hypersonic tunnel (IH17)

NASA Technical Reports Server (NTRS)

Cummings, J.

1976-01-01

Model information and data obtained from wind tunnel tests performed on a 0.006 scale model of the Rockwell International space shuttle orbiter and external tank in the 18 inch Variable Density Hypersonic Wind Tunnel (VDHT) at NASA Langley Research Center are presented. Tests were performed at a Mach number of 8.0 over a Reynolds Number range from 0.1 to 10.0 million per foot at 0 deg and -5 deg angle of attack and 0 deg sideslip angle. Transition heating rates were determined using thin skin thermocouples located at various locations on the orbiter and ET. The test was conducted in three stages: orbiter plus external tank (mated configuration); orbiter alone, and external tank alone. The effects of boundary layer trips were also included in the test sequence. The plotted results presented show the effect of configuration interference on the orbiter lower surface and on the ET. Tabulated data are given.

KSC-2011-8157

NASA Image and Video Library

2011-12-02

CAPE CANAVERAL, Fla. – A crane positions a full-size display of a space shuttle external fuel tank onto a truck to move it from the Kennedy Space Center Visitor Complex as the space-themed attraction makes way for a new exhibit featuring space shuttle Atlantis, which is currently undergoing preparations to go on public display. The tank is being placed into temporary storage at NASA's Kennedy Space Center. The tank was part of a display of the external tank and two solid rocket boosters at the visitor complex that were used to show visitors the size of actual space shuttle components. A space shuttle rode piggyback on the tank and boosters at liftoff and during the ascent into space. The tank, which held propellants for the shuttle's three main engines, was not reused, but burned up in the atmosphere and fell into the ocean. Photo credit: NASA/Dmitri Gerondidakis

KSC-2011-8158

NASA Image and Video Library

2011-12-02

CAPE CANAVERAL, Fla. – A crane positions a full-size display of a space shuttle external fuel tank onto a truck to move it from the Kennedy Space Center Visitor Complex as the space-themed attraction makes way for a new exhibit featuring space shuttle Atlantis, which is currently undergoing preparations to go on public display. The tank is being placed into temporary storage at NASA's Kennedy Space Center. The tank was part of a display of the external tank and two solid rocket boosters at the visitor complex that were used to show visitors the size of actual space shuttle components. A space shuttle rode piggyback on the tank and boosters at liftoff and during the ascent into space. The tank, which held propellants for the shuttle's three main engines, was not reused, but burned up in the atmosphere and fell into the ocean. Photo credit: NASA/Dmitri Gerondidakis

KSC-2010-5939

NASA Image and Video Library

2010-12-22

CAPE CANAVERAL, Fla. -- Preparations are under way in the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida to examine space shuttle Discovery's external fuel tank. Shown here, is one of two solid rocket boosters, which are still attached to the external tank and shuttle. Technicians will begin to remove thermal sensors that will give engineers data about the changes the tank went through during the loading and draining of super-cold propellants during a tanking test on Dec. 17. Engineers also will examine 21-foot-long support beams, called stringers, on the outside of the tank's intertank region. Also on the agenda, is to re-apply foam to the outside of the tank. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Dimitri Gerondidakis

KSC-2010-5945

NASA Image and Video Library

2010-12-22

CAPE CANAVERAL, Fla. -- Preparations are under way in the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida to examine space shuttle Discovery's external fuel tank. Shown here is the nose of the shuttle, which still is attached to the external tank and solid rocket boosters. Technicians will begin to remove thermal sensors that will give engineers data about the changes the tank went through during the loading and draining of super-cold propellants during a tanking test on Dec. 17. Engineers also will examine 21-foot-long support beams, called stringers, on the outside of the tank's intertank region. Also on the agenda, is to re-apply foam to the outside of the tank. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Dimitri Gerondidakis

KSC-07pd3657

NASA Image and Video Library

2007-12-29

KENNEDY SPACE CENTER, FLA. -- At Launch Pad 39A, a team of external tank specialists from Lockheed Martin and the United Space Alliance undertakes the task of removing the hydrogen feed-through connector in support of space shuttle Atlantis' STS-122 mission. Here, a technician cuts the external connector cable. Some of the tank's engine cutoff sensors, or ECO sensors, failed during propellant tanking for launch attempts on Dec. 6 and Dec. 9. Results of a tanking test on Dec. 18 pointed to an open circuit in the feed-through connector wiring, which is located at the base of the tank. The feed-through connector passes the wires from the inside of the tank to the outside. After the data from additional testing on the connector is analyzed, shuttle program managers will decide on a forward plan. Launch of STS-122 is targeted for January 2008. Photo credit: NASA/George Shelton

Reducing Liquid Loss during Ullage Venting in Microgravity

NASA Technical Reports Server (NTRS)

Nguyen, Bich; Nguyen, Lauren

2008-01-01

A centripetal-force-based liquid/gas separator has been proposed as a means of reducing the loss of liquid during venting of the ullage of a tank in microgravity as a new supply of liquid is pumped into the tank. Centripetal-force-based liquid/gas separators are used on Earth, where mechanical drives (e.g., pumps and spinners) are used to impart flow speeds sufficient to generate centripetal forces large enough to effect separation of liquids from gases. For the proposed application, the separator would be designed so that there would be no need for such a pump because the tank-pressure-induced outflow speed during venting of the ullage would be sufficient for centripetal separation. A relatively small pump would be used, not for separation, but for returning the liquid recovered by the separator to the tank.

40 CFR 63.685 - Standards: Tanks.

Code of Federal Regulations, 2010 CFR

2010-07-01

... in paragraph (c)(2)(i) of this section when a tank is used as an interim transfer point to transfer... fixed-roof tank equipped with an internal floating roof in accordance with the requirements specified in paragraph (e) of this section; (2) A tank equipped with an external floating roof in accordance with the...

Experimental and analytical study of cryogenic propellant boiloff to develop and verify alternate pressurization concepts for Space Shuttle external tank using a scaled down tank

NASA Technical Reports Server (NTRS)

Akyuzlu, K. M.; Jones, S.; Meredith, T.

1993-01-01

Self pressurization by propellant boiloff is experimentally studied as an alternate pressurization concept for the Space Shuttle external tank (ET). The experimental setup used in the study is an open flow system which is composed of a variable area test tank and a recovery tank. The vacuum jacketed test tank is geometrically similar to the external LOx tank for the Space Shuttle. It is equipped with instrumentation to measure the temperature and pressure histories within the liquid and vapor, and viewports to accommodate visual observations and Laser-Doppler Anemometry measurements of fluid velocities. A set of experiments were conducted using liquid Nitrogen to determine the temperature stratification in the liquid and vapor, and pressure histories of the vapor during sudden and continuous depressurization for various different boundary and initial conditions. The study also includes the development and calibration of a computer model to simulate the experiments. This model is a one-dimensional, multi-node type which assumes the liquid and the vapor to be under non-equilibrium conditions during the depressurization. It has been tested for a limited number of cases. The preliminary results indicate that the accuracy of the simulations is determined by the accuracy of the heat transfer coefficients for the vapor and the liquid at the interface which are taken to be the calibration parameters in the present model.

Main Propulsion Test Article (MPTA)

NASA Technical Reports Server (NTRS)

Snoddy, Cynthia

2010-01-01

Scope: The Main Propulsion Test Article integrated the main propulsion subsystem with the clustered Space Shuttle Main Engines, the External Tank and associated GSE. The test program consisted of cryogenic tanking tests and short- and long duration static firings including gimbaling and throttling. The test program was conducted on the S1-C test stand (Position B-2) at the National Space Technology Laboratories (NSTL)/Stennis Space Center. 3 tanking tests and 20 hot fire tests conducted between December 21 1 1977 and December 17, 1980 Configuration: The main propulsion test article consisted of the three space shuttle main engines, flightweight external tank, flightweight aft fuselage, interface section and a boilerplate mid/fwd fuselage truss structure.

Repairing the damage to Atlantis' External Tank

NASA Image and Video Library

2007-03-07

On an upper level of high bay 1 of the Vehicle Assembly Building, technicians prepare the area around the nose cone (left) of Atlantis' external tank that will undergo repair for hail damage. A severe thunderstorm with golf ball-sized hail caused visible divots in the giant tank's foam insulation and minor surface damage to about 26 heat shield tiles on the shuttle's left wing. Further evaluation of the tank is necessary to get an accurate accounting of foam damage and determine the type of repair required and the time needed for that work. A new target launch date has not been determined, but teams will focus on preparing Atlantis for liftoff in late April on mission STS-117.

Repairing the damage to Atlantis' External Tank

NASA Image and Video Library

2007-03-07

On an upper level of high bay 1 of the Vehicle Assembly Building, technicians place protective material around the nose cone of Atlantis' external tank. The nose cone will undergo repair for hail damage. A severe thunderstorm with golf ball-sized hail caused visible divots in the giant tank's foam insulation and minor surface damage to about 26 heat shield tiles on the shuttle's left wing. Further evaluation of the tank is necessary to get an accurate accounting of foam damage and determine the type of repair required and the time needed for that work. A new target launch date has not been determined, but teams will focus on preparing Atlantis for liftoff in late April on mission STS-117.

Repairing the damage to Atlantis' External Tank

NASA Image and Video Library

2007-03-07

On an upper level of high bay 1 of the Vehicle Assembly Building, technicians prepare the area around the nose cone (foreground) of Atlantis' external tank that will undergo repair for hail damage. A severe thunderstorm with golf ball-sized hail caused visible divots in the giant tank's foam insulation and minor surface damage to about 26 heat shield tiles on the shuttle's left wing. Further evaluation of the tank is necessary to get an accurate accounting of foam damage and determine the type of repair required and the time needed for that work. A new target launch date has not been determined, but teams will focus on preparing Atlantis for liftoff in late April on mission STS-117.

Application of Terahertz Imaging and Backscatter Radiography to Space Shuttle Foam Inspection

NASA Technical Reports Server (NTRS)

Ussery, Warren

2008-01-01

Two state of the art technologies have been developed for External Fuel Tank foam inspections. Results of POD tests have shown Backscatter Radiography and Terahertz imaging detect critical defects with no false positive issue. These techniques are currently in use on the External Tank program as one component in the foam quality assurance program.

External tank aerothermal design criteria verification, volume 2

NASA Technical Reports Server (NTRS)

Crain, William K.; Frost, Cynthia; Warmbrod, John

1990-01-01

The objective of the study was to produce an independent set of ascent environments which would serve as a check on the Rockwell International (RI) IVBC-3 environments and provide an independent reevaluation of the thermal design criteria for the External Tank (ET). Given here are the plotted timewise environments comparing REMTECH results to the RI IVBC results.

High speed machining of space shuttle external tank liquid hydrogen barrel panel

NASA Technical Reports Server (NTRS)

Hankins, J. D.

1983-01-01

Actual and projected optimum High Speed Machining data for producing shuttle external tank liquid hydrogen barrel panels of aluminum alloy 2219-T87 are reported. The data included various machining parameters; e.g., spindle speeds, cutting speed, table feed, chip load, metal removal rate, horsepower, cutting efficiency, cutter wear (lack of) and chip removal methods.

High speed machining of space shuttle external tank liquid hydrogen barrel panel

NASA Astrophysics Data System (ADS)

Hankins, J. D.

1983-11-01

Actual and projected optimum High Speed Machining data for producing shuttle external tank liquid hydrogen barrel panels of aluminum alloy 2219-T87 are reported. The data included various machining parameters; e.g., spindle speeds, cutting speed, table feed, chip load, metal removal rate, horsepower, cutting efficiency, cutter wear (lack of) and chip removal methods.

Position Paper External Tank Thermal Protection System (TPS) Manually Sprayed fly-as-is Foam Certification

NASA Technical Reports Server (NTRS)

Stadler, John H.

2009-01-01

During manufacture of the existing External Tanks (ETs), the Thermal Protection System (TPS) foam manual spray application processes lacked the enhanced controls/procedures to ensure that defects produced were less than the critical size. Therefore the only remaining option to certify the "fly-as-is" foam is to verify ET120 tank hardware meets the new foam debris requirements. The ET project has undertaken a significant effort studying the existing "fly-as-is" TPS foam. This paper contains the findings of the study.

Liquid oxygen sloshing in Space Shuttle External Tank

NASA Technical Reports Server (NTRS)

Kannapel, M. D.; Przekwas, A. J.; Singhal, A. K.; Costes, N. C.

1987-01-01

This paper describes a numerical simulation of the hydrodynamics within the liquid oxygen tank of the Space Shuttle External Tank during liftoff. Before liftoff, the tank is filled with liquid oxygen (LOX) to approximately 97 percent with the other 3 percent containing gaseous oxygen (GOX) and helium. During liftoff, LOX is drained from the bottom of the tank, and GOX is pumped into the tank's ullage volume. There is a delay of several seconds before the GOX reaches the tank which causes the ullage pressure to decrease for several seconds after liftoff; this pressure 'slump' is a common phenomenon in rocket propulsion. When four slosh baffles were removed from the tank, the ullage gas pressure dropped more rapidly than in all previous flights. The purpose of this analysis was to determine whether the removal of the baffles could have caused the increased pressure 'slump' by changing the LOX surface dynamics. The results show that the LOX surface undergoes very high vertical accelerations (up to 5 g) and, therefore, splashing almost certainly occurs. The number of baffles does not affect the surface if the structural motion is assumed; but, the number of baffles may affect the structural motion of the tank.

Research on Liquid Management Technology in Water Tank and Reactor for Propulsion System with Hydrogen Production System Utilizing Aluminum and Water Reaction

NASA Astrophysics Data System (ADS)

Imai, Ryoji; Imamura, Takuya; Sugioka, Masatoshi; Higashino, Kazuyuki

2017-12-01

High pressure hydrogen produced by aluminum and water reaction is considered to be applied to space propulsion system. Water tank and hydrogen production reactor in this propulsion system require gas and liquid separation function under microgravity condition. We consider to install vane type liquid acquisition device (LAD) utilizing surface tension in the water tank, and install gas-liquid separation mechanism by centrifugal force which swirling flow creates in the hydrogen reactor. In water tank, hydrophilic coating was covered on both tank wall and vane surface to improve wettability. Function of LAD in water tank and gas-liquid separation in reaction vessel were evaluated by short duration microgravity experiments using drop tower facility. In the water tank, it was confirmed that liquid was driven and acquired on the outlet due to capillary force created by vanes. In addition of this, it was found that gas-liquid separation worked well by swirling flow in hydrogen production reactor. However, collection of hydrogen gas bubble was sometimes suppressed by aluminum alloy particles, which is open problem to be solved.

A water blown urethane insulation for use in cryogenic environments

NASA Technical Reports Server (NTRS)

Blevins, Elana; Sharpe, Jon

1995-01-01

Thermal Protection Systems (TPS) of NASA's Space Shuttle External Tank include polyurethane and polyisocyanurate modified polyurethane foam insulations. These insulations, currently foamed with CFC 11 blowing agent, serve to maintain cryogenic propellant quality, maintain the external tank structural temperature limits, and minimize the formation of ice and frost that could potentially damage the ceramic insulation on the space shuttle orbiter. During flight the external tank insulations are exposed to mechanical, thermal and acoustical stresses. TPS must pass cryogenic flexure and substrate adhesion tests at -253 C, aerothermal and radiant heating tests at fluxes up to approximately 14 kilowatts per square meter, and thermal conductivity tests at cryogenic and elevated temperatures. Due to environmental concerns, the polyurethane insulation industry and the External Tank Project are tasked with replacing CFC 11. The flight qualification of foam insulations employing HCFC 141b as a foaming agent is currently in progress; HCFC 141b blown insulations are scheduled for production implementation in 1995. Realizing that the second generation HCFC blowing agents are an interim solution, the evaluation of third generation blowing agents with zero ozone depletion potential is underway. NASA's TPS Materials Research Laboratory is evaluating third generation blowing agents in cryogenic insulations for the External Tank; one option being investigated is the use of water as a foaming agent. A dimensionally stable insulation with low friability, good adhesion to cryogenic substrates, and acceptable thermal conductivity has been developed with low viscosity materials that are easily processed in molding applications. The development criteria, statistical experimental approach, and resulting foam properties will be presented.

Cost-effective upgrading of a biological wastewater treatment plant by using lamella separators with bypass operation.

PubMed

Jardin, N; Rath, L; Schönfeld, A; Grünebaum, T

2008-01-01

Based on a comprehensive cost analysis for the expansion of the Finnentrop WWTP, integration of lamella separators in the biological treatment stage was given priority as optimal solution to increase the solids concentration. The overall expansion project included the reconstruction of the former primary clarifier into a primary settling tank with short retention times and the use of the remaining volume for pre-denitrification. Four lamella separators were positioned in the existing carousel-type activated sludge tank. With the lamella assemblies ensuring it was possible to continue operation of the existing secondary settling tanks. To control an adequate solids concentration in the activated sludge tank and to avoid any overloading of the secondary settling tank, a newly developed bypass strategy was applied. With a controlled mixing of direct effluent from the lamella separators and the contents of the activated sludge tank, the solids concentration of the influent to the secondary settling tank could be maintained at a value of 2.2 kg/m(3). The lamella separator concept did not account for any significant changes in the sludge characteristics, and the overall elimination of nutrients and organic carbon was found to be excellent upon optimisation of the operational lamella strategy. IWA Publishing 2008.

Combined centrifugal force/gravity gas/liquid separator system

NASA Astrophysics Data System (ADS)

Lema, Luis E.

1993-04-01

A gas/liquid separator system has an outer enclosing tank filled with a demisting packing material. The tank has a gas outlet port and a liquid outlet port located at its top and bottom, respectively. At least one cylindrical, centrifugal force gas/liquid separator is vertically aligned and centrally located within the tank and is surrounded by the packing material. The cylindrical separator receives a gas/liquid mixture, separates the mixture into respective substantially gas and substantially liquid components, and allows the substantially gas components to exit its gas escape port. It also allows the substantially liquid components to exit its liquid escape port. The packing material in the tank further separates the substantially gas and liquid components as they rise and fall, respectively, through the packing material. An inflow line introduces the mixture into the cylindrical separator. The inflow line is upwardly inclined in a direction of flow of the mixture at a point where the inflow line communicates with the cylindrical separator.

Space Shuttle Atlantis' external tank repairs from Hail Damage

NASA Image and Video Library

2007-04-09

In the Vehicle Assembly Building, markers show the hail damage being repaired on the external tank of Space Shuttle Atlantis. The white hole with a red circle around it is a hole prepared for molding and material application. The red material is sealant tape so the mold doesn't leak when the foam rises against the mold. The white/ translucent square mold is an area where the foam has been applied and the foam has risen and cured against the mold surface. The area will be de-molded and sanded flush the with adjacent area. In late February, Atlantis' external tank received hail damage during a severe thunderstorm that passed through the Kennedy Space Center Launch Complex 39 area. The hail caused visible divots in the giant tank's foam insulation as well as minor surface damage to about 26 heat shield tiles on the shuttle's left wing. The March launch was postponed and has not yet been rescheduled due to the repair process.

Space Shuttle Atlantis' external tank repairs from Hail Damage

NASA Image and Video Library

2007-04-09

In the Vehicle Assembly Building, United Space Alliance technicians Brenda Morris and Brian Williams are applying foam and molds on Space Shuttle Atlantis' external tank to areas damaged by hail. The white hole with a red circle around it (upper right) is a hole prepared for molding and material application. The red material is sealant tape so the mold doesn't leak when the foam rises against the mold. The white/ translucent square mold is an area where the foam has been applied and the foam has risen and cured against the mold surface. In late February, Atlantis' external tank received hail damage during a severe thunderstorm that passed through the Kennedy Space Center Launch Complex 39 area. The hail caused visible divots in the giant tank's foam insulation as well as minor surface damage to about 26 heat shield tiles on the shuttle's left wing. The March launch was postponed and has not yet been rescheduled due to the repair process.

Physics-Based Fragment Acceleration Modeling for Pressurized Tank Burst Risk Assessments

NASA Technical Reports Server (NTRS)

Manning, Ted A.; Lawrence, Scott L.

2014-01-01

As part of comprehensive efforts to develop physics-based risk assessment techniques for space systems at NASA, coupled computational fluid and rigid body dynamic simulations were carried out to investigate the flow mechanisms that accelerate tank fragments in bursting pressurized vessels. Simulations of several configurations were compared to analyses based on the industry-standard Baker explosion model, and were used to formulate an improved version of the model. The standard model, which neglects an external fluid, was found to agree best with simulation results only in configurations where the internal-to-external pressure ratio is very high and fragment curvature is small. The improved model introduces terms that accommodate an external fluid and better account for variations based on circumferential fragment count. Physics-based analysis was critical in increasing the model's range of applicability. The improved tank burst model can be used to produce more accurate risk assessments of space vehicle failure modes that involve high-speed debris, such as exploding propellant tanks and bursting rocket engines.

CALUTRONS

DOEpatents

Lawrence, E.O.

1958-09-16

This patent relates to calutron devices and has for its object the arrangement of several independent ion separating mechanisms, i.e., ion source and ion receiver, within a single vacuum tank to econnmize on space and reduce the duplication of magnetic structure. In each of the two described embodiments the ion separating mechanisms are removably supported within the tank. In addition, the magnetic field is produced in the tank by coaxial coils supported outside the tank and magnetic structure is arranged to confine and provide a uniform field within the tank.

Investigation of failure to separate an Inconel 718 frangible nut

NASA Technical Reports Server (NTRS)

Hoffman, William C., III; Hohmann, Carl

1994-01-01

The 2.5-inch frangible nut is used in two places to attach the Space Shuttle Orbiter to the External Tank. It must be capable of sustaining structural loads and must also separate into two pieces upon command. Structural load capability is verified by proof loading each flight nut, while ability to separate is verified on a sample of a production lot. Production lots of frangible nuts beginning in 1987 experienced an inability to reliably separate using one of two redundant explosive boosters. The problems were identified in lot acceptance tests, and the cause of failure has been attributed to differences in the response of the Inconel 718. Subsequent tests performed on the frangible nuts resulted in design modifications to the nuts along with redesign of the explosive booster to reliably separate the frangible nut. The problem history along with the design modifications to both the explosive booster and frangible nut are discussed in this paper. Implications of this failure experience impact any pyrotechnic separation system involving fracture of materials with respect to design margin control and lot acceptance testing.

Results of test IA137 in the NASA/ARC 14 foot transonic wind tunnel of the 0.07 scale external tank forebody (model 68-T) to determine auxiliary aerodynamic data system feasibility

NASA Technical Reports Server (NTRS)

Thornton, D. E.

1976-01-01

Tests were conducted in a 14 foot transonic wind tunnel to examine the feasibility of the auxiliary aerodynamic data system (AADS) for determining angles of attack and sideslip during boost flight. The model used was a 0.07 scale replica of the external tank forebody consisting of the nose portion and a 60 inch (full scale) cylindrical section of the ogive cylinder tangency point. The model terminated in a blunt base with a 320.0 inch diameter at external tank (ET) station 1120.37. Pressure data were obtained from five pressure orifices (one total and four statics) on the nose probe, and sixteen surface static pressure orifices along the ET forebody.

Heat transfer tests of a 0.006-scale thin skin space shuttle model (50-0, 41-T) in the Langley Research Center nitrogen tunnel at Mach 19 (IH19)

NASA Technical Reports Server (NTRS)

Walstad, D. G.

1975-01-01

Data are presented from heat transfer tests on an 0.0006-scale space shuttle vehicle in the Langley Research Center Nitrogen Tunnel. The purpose of this test was to obtain ascent heating data at a high hypersonic Mach number. Configurations tested were integrated orbiter and external tank, orbiter alone, and external tank alone. All configurations were tested with and without boundary layer transition. Testing was conducted at a Mach number of 19, a Reynolds number of 0.5 million per foot, and angles of attack of 0, + or - 5, and + or - 10 degrees. Heat transfer data was obtained from 77 orbiter and 90 external tank iron-constantan thermocouples.

KSC-06pd2287

NASA Image and Video Library

2006-10-12

KENNEDY SPACE CENTER, FLA. - Inside the Vehicle Assembly Building, the external tank is transferred from the checkout cell for attaching to its twin solid rocket boosters on the mobile launch platform in highbay 3 for mission STS-116. The gigantic, rust-colored external tank is the largest element of the Space Shuttle system at 27.6-feet wide and 154-feet tall. The gigantic, rust-colored external tank is the largest element of the Space Shuttle system at 27.6-feet wide and 154-feet tall. STS-116 will be mission no. 20 to the International Space Station and construction flight 12A.1. The mission payload is the SPACEHAB module, the P5 integrated truss structure and other key components. Launch is scheduled for no earlier than Dec. 7. Photo credit: NASA/Jack Pfaller

Organic Separation Test Results

DOE Office of Scientific and Technical Information (OSTI.GOV)

Russell, Renee L.; Rinehart, Donald E.; Peterson, Reid A.

2014-09-22

Separable organics have been defined as “those organic compounds of very limited solubility in the bulk waste and that can form a separate liquid phase or layer” (Smalley and Nguyen 2013), and result from three main solvent extraction processes: U Plant Uranium Recovery Process, B Plant Waste Fractionation Process, and Plutonium Uranium Extraction (PUREX) Process. The primary organic solvents associated with tank solids are TBP, D2EHPA, and NPH. There is concern that, while this organic material is bound to the sludge particles as it is stored in the tanks, waste feed delivery activities, specifically transfer pump and mixer pump operations,more » could cause the organics to form a separated layer in the tank farms feed tank. Therefore, Washington River Protection Solutions (WRPS) is experimentally evaluating the potential of organic solvents separating from the tank solids (sludge) during waste feed delivery activities, specifically the waste mixing and transfer processes. Given the Hanford Tank Waste Treatment and Immobilization Plant (WTP) waste acceptance criteria per the Waste Feed Acceptance Criteria document (24590-WTP-RPT-MGT-11-014) that there is to be “no visible layer” of separable organics in the waste feed, this would result in the batch being unacceptable to transfer to WTP. This study is of particular importance to WRPS because of these WTP requirements.« less

Repairing the damage to Atlantis' External Tank

NASA Image and Video Library

2007-03-07

On an upper level of high bay 1 of the Vehicle Assembly Building, technicians secure protective material around the base of the nose cone of Atlantis' external tank. The nose cone will undergo repair for hail damage. A severe thunderstorm with golf ball-sized hail caused visible divots in the giant tank's foam insulation and minor surface damage to about 26 heat shield tiles on the shuttle's left wing. Further evaluation of the tank is necessary to get an accurate accounting of foam damage and determine the type of repair required and the time needed for that work. A new target launch date has not been determined, but teams will focus on preparing Atlantis for liftoff in late April on mission STS-117.

Repairing the damage to Atlantis' External Tank

NASA Image and Video Library

2007-03-07

On an upper level of high bay 1 of the Vehicle Assembly Building, technicians move protective material toward the nose cone (foreground) of Atlantis' external tank. The nose cone will undergo repair for hail damage. A severe thunderstorm with golf ball-sized hail caused visible divots in the giant tank's foam insulation and minor surface damage to about 26 heat shield tiles on the shuttle's left wing. Further evaluation of the tank is necessary to get an accurate accounting of foam damage and determine the type of repair required and the time needed for that work. A new target launch date has not been determined, but teams will focus on preparing Atlantis for liftoff in late April on mission STS-117.

Repairing the damage to Atlantis' External Tank

NASA Image and Video Library

2007-03-07

On an upper level of high bay 1 of the Vehicle Assembly Building, technicians secure protective material around Atlantis' external tank. The preparations are for future repair work of the hail damage that happened Feb. 27. A severe thunderstorm with golf ball-sized hail caused visible divots in the giant tank's foam insulation and minor surface damage to about 26 heat shield tiles on the shuttle's left wing. Further evaluation of the tank is necessary to get an accurate accounting of foam damage and determine the type of repair required and the time needed for that work. A new target launch date has not been determined, but teams will focus on preparing Atlantis for liftoff in late April on mission STS-117.

Experimental Investigation of Jet-Induced Mixing of a Large Liquid Hydrogen Storage Tank

NASA Technical Reports Server (NTRS)

Lin, C. S.; Hasan, M. M.; Vandresar, N. T.

1994-01-01

Experiments have been conducted to investigate the effect of fluid mixing on the depressurization of a large liquid hydrogen storage tank. The test tank is approximately ellipsoidal, having a volume of 4.89 m(exp 3) and an average wall heat flux of 4.2 W/m(exp 2) due to external heat input. A mixer unit was installed near the bottom of the tank to generate an upward directed axial jet flow normal to the liquid-vapor interface. Mixing tests were initiated after achieving thermally stratified conditions in the tank either by the introduction of hydrogen gas into the tank or by self-pressurization due to ambient heat leak through the tank wall. The subcooled liquid jet directed towards the liquid-vapor interface by the mixer induced vapor condensation and caused a reduction in tank pressure. Tests were conducted at two jet submergence depths for jet Reynolds numbers from 80,000 to 495,000 and Richardson numbers from 0.014 to 0.52. Results show that the rate of tank pressure change is controlled by the competing effects of subcooled jet flow and the free convection boundary layer flow due to external tank wall heating. It is shown that existing correlations for mixing time and vapor condensation rate based on small scale tanks may not be applicable to large scale liquid hydrogen systems.

External Tank Liquid Hydrogen (LH2) Prepress Regression Analysis Independent Review Technical Consultation Report

NASA Technical Reports Server (NTRS)

Parsons, Vickie s.

2009-01-01

The request to conduct an independent review of regression models, developed for determining the expected Launch Commit Criteria (LCC) External Tank (ET)-04 cycle count for the Space Shuttle ET tanking process, was submitted to the NASA Engineering and Safety Center NESC on September 20, 2005. The NESC team performed an independent review of regression models documented in Prepress Regression Analysis, Tom Clark and Angela Krenn, 10/27/05. This consultation consisted of a peer review by statistical experts of the proposed regression models provided in the Prepress Regression Analysis. This document is the consultation's final report.

KSC-07pd0886

NASA Image and Video Library

2007-04-13

KENNEDY SPACE CENTER, FLA. -- In the Vehicle Assembly Building, Mike Ravenscroft, with United Space Alliance, points to some of the foam repair done on the external tank of Space Shuttle Atlantis. Holes filled with foam are sanded flush with the adjacent area. In late February, Atlantis' external tank received hail damage during a severe thunderstorm that passed through the Kennedy Space Center Launch Complex 39 area. The hail caused visible divots in the giant tank's foam insulation as well as minor surface damage to about 26 heat shield tiles on the shuttle's left wing. The launch now is targeted for June 8. Photo credit: NASA/George Shelton

KSC-05PD-1575

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. The gate is open to Launch Pad 39B where Space Shuttle Discovery remains on the pad after scrub of Return to Flight mission STS-114. The July 13 mission was scrubbed when a low-level fuel cut-off sensor for the liquid hydrogen tank inside the External Tank failed a routine prelaunch check during the countdown July 13, causing mission managers to scrub Discovery's first launch attempt. The sensor protects the Shuttle's main engines by triggering their shutdown in the event fuel runs unexpectedly low. The sensor is one of four inside the liquid hydrogen section of the External Tank (ET).

Planning for Materials Processing in Space

NASA Technical Reports Server (NTRS)

1977-01-01

A systems design study to describe the conceptual evolution, the institutional interrelationshiphs, and the basic physical requirements to implement materials processing in space was conducted. Planning for a processing era, rather than hardware design, was emphasized. Product development in space was examined in terms of fluid phenomena, phase separation, and heat and mass transfer. The effect of materials processing on the environment was studied. A concept for modular, unmanned orbiting facilities using the modified external tank of the space shuttle is presented. Organizational and finding structures which would provide for the efficient movement of materials from user to space are discussed.

On-orbit flight control algorithm description

NASA Technical Reports Server (NTRS)

1975-01-01

Algorithms are presented for rotational and translational control of the space shuttle orbiter in the orbital mission phases, which are external tank separation, orbit insertion, on-orbit and de-orbit. The program provides a versatile control system structure while maintaining uniform communications with other programs, sensors, and control effectors by using an executive routine/functional subroutine format. Software functional requirements are described using block diagrams where feasible, and input--output tables, and the software implementation of each function is presented in equations and structured flow charts. Included are a glossary of all symbols used to define the requirements, and an appendix of supportive material.

40 CFR 60.692-3 - Standards: Oil-water separators.

Code of Federal Regulations, 2010 CFR

2010-07-01

... 40 Protection of Environment 6 2010-07-01 2010-07-01 false Standards: Oil-water separators. 60.692... Emissions From Petroleum Refinery Wastewater Systems § 60.692-3 Standards: Oil-water separators. (a) Each oil-water separator tank, slop oil tank, storage vessel, or other auxiliary equipment subject to the...

40 CFR 60.692-3 - Standards: Oil-water separators.

Code of Federal Regulations, 2013 CFR

2013-07-01

... 40 Protection of Environment 7 2013-07-01 2013-07-01 false Standards: Oil-water separators. 60.692... Emissions From Petroleum Refinery Wastewater Systems § 60.692-3 Standards: Oil-water separators. (a) Each oil-water separator tank, slop oil tank, storage vessel, or other auxiliary equipment subject to the...

40 CFR 60.692-3 - Standards: Oil-water separators.

Code of Federal Regulations, 2014 CFR

2014-07-01

... 40 Protection of Environment 7 2014-07-01 2014-07-01 false Standards: Oil-water separators. 60.692... Emissions From Petroleum Refinery Wastewater Systems § 60.692-3 Standards: Oil-water separators. (a) Each oil-water separator tank, slop oil tank, storage vessel, or other auxiliary equipment subject to the...

Microbiological Characterization of the International Space Station Water Processor Assembly External Filter Assembly S/N 01

NASA Technical Reports Server (NTRS)

Weir, Natalee; Wilson, Mark; Yoets, Airan; Yoets, Airan; Molina, Thomas; Bruce, Rebekah; Sitler, Glenn; Carter, Layne

2012-01-01

The External Filter Assembly (EFA) S/N 01 is a mesh screen filter with a pore size of approximately 300 micron that was installed in the International Space Station (ISS) Water Processor Assembly (WPA) between the Waste Tank and the Mostly Liquid Separator (MLS) on February 11, 2010 to protect clearances in the MLS solenoid valve SV_1121_3. A removal & replacement of the EFA Filter was performed on March 22, 2011 in response to increasing pressure across the Waste Tank solenoid valve SV_1121_1 and the EFA Filter. The EFA Filter was returned on ULF6 and received in the Boeing Huntsville Laboratory on June 13, 2011. The filter was aseptically removed from the housing, and the residual water was collected for enumeration and identification of bacteria and fungi. Swab samples of the filter surface were also collected for microbiological enumeration and identification. Sample analyses were performed by Boeing Huntsville Laboratory and NASA Johnson Space Center Microbiology for comparison. Photographic documentation of the EFA filter was performed using a stereo microscope and environmental scanning electron microscope. This paper characterizes the amount and types of microorganisms on the filter surface and in the residual water from the filter housing following 1 year of utilization in the ISS WPA.

A loose bolt delays loading of Endeavour's external tank

NASA Technical Reports Server (NTRS)

2000-01-01

This loose bracket, observed hanging down from the side of the White Room at Launch Pad 39B, delayed loading of Endeavour's external tank by several hours to allow technicians to remove it. A 'U' bolt connects the bracket to a fire suppression water line attached to the exterior of the White Room. The loose bolt could have possibly created a debris hazard.

The Variable Polarity Plasma Arc Welding Process: Its Application to the Space Shuttle External Tank

NASA Technical Reports Server (NTRS)

Nunes, A. C., Jr.; Bayless, E. O., Jr.; Wilson, W. A.

1984-01-01

This report describes progress in the implementation of the Variable Polarity Plasma Arc Welding (VPPAW) process at the External Tank (ET) assembly facility. Design allowable data has been developed for thicknesses up to 1.00 in. More than 24,000 in. of welding on liquid oxygen and liquid hydrogen cylinders has been made without an internal defect.

The variable polarity plasma arc welding process: Its application to the Space Shuttle external tank

NASA Technical Reports Server (NTRS)

Nunes, A. C., Jr.; Bayless, O. E., Jr.; Jones, C. S., III; Munafo, A. P.; Wilson, W. A.

1983-01-01

The technical history of the variable polarity plasma arc (VPPA) welding process being introduced as a partial replacement for the gas shielded tungsten arc process in assembly welding of the space shuttle external tank is described. Interim results of the weld strength qualification studies, and plans for further work on the implementation of the VPPA process are included.

40 CFR 264.1084 - Standards: Tanks.

Code of Federal Regulations, 2010 CFR

2010-07-01

... internal floating roof in accordance with the requirements specified in paragraph (e) of this section; (2) A tank equipped with an external floating roof in accordance with the requirements specified in... operator who controls air pollutant emissions from a tank using a fixed roof with an internal floating roof...

Recycling silicon wire-saw slurries: separation of silicon and silicon carbide in a ramp settling tank under an applied electrical field.

PubMed

Tsai, Tzu-Hsuan; Shih, Yu-Pei; Wu, Yung-Fu

2013-05-01

The growing demand for silicon solar cells in the global market has greatly increased the amount of silicon sawing waste produced each year. Recycling kerf Si and SiC from sawing waste is an economical method to reduce this waste. This study reports the separation of Si and SiC using a ramp settling tank. As they settle in an electrical field, small Si particles with higher negative charges have a longer horizontal displacement than SiC particles in a solution of pH 7, resulting in the separation of Si and SiC. The agreement between experimental results and predicted results shows that the particles traveled a short distance to reach the collection port in the ramp tank. Consequently, the time required for tiny particles to hit the tank bottom decreased, and the interference caused by the dispersion between particles and the fluid motion during settling decreased. In the ramp tank, the highest purities of the collected SiC and Si powders were 95.2 and 7.01 wt%, respectively. Using a ramp tank, the recycling fraction of Si-rich powders (SiC < 15 wt%) reached 22.67% (based on the whole waste). This fraction is greater than that achieved using rectangular tanks. Recycling Si and SiC abrasives from the silicon sawing waste is regarded as an economical solution to reduce the sawing waste. However, the separation of Si and SiC is difficult. This study reports the separation of Si and SiC using a ramp settling tank under an applied electrical field. As they settle in an electrical field, small Si particles with higher negative charges have a longer horizontal displacement than SiC particles in a solution of pH 7, resulting in the separation of Si and SiC. Compared with the rectangular tanks, the recycling fraction of Si-rich powders using a ramp tank is greater, and the proposed ramp settling tank is more suitable for industrial applications.

46 CFR 169.234 - Integral fuel oil tank examinations.

Code of Federal Regulations, 2010 CFR

2010-10-01

... operator of the vessel shall have the tanks cleaned out and gas freed as necessary to permit internal... an examination of the fuel tanks of each vessel during an internal structural examination at... and internally examined if the marine inspector is able to determine by external examination that the...

46 CFR 115.610 - Scope of drydock and internal structural examinations.

Code of Federal Regulations, 2010 CFR

2010-10-01

... plating, voids, and ballast, cargo, and fuel oil tanks. Where the internal framing or plating of the... oil tanks need not be cleaned out and internally examined if the marine inspector is able to determine by external examination that the general condition of the tanks is satisfactory. ...

Heat transfer tests of an 0.006-scale thin-skin space shuttle thermocouple model (141-OT) in the Langley Research Center Freon tunnel at M-6 (IH18). [wind tunnel tests

NASA Technical Reports Server (NTRS)

Walstad, D. G.

1976-01-01

Ascent heating data were obtained at conditions simulating real gas effects at hypersonic Mach numbers. The configurations tested were Orbiter alone, external tank alone, and mated Orbiter and external tank. A boundary layer trip investigation was conducted for all configurations. The test was conducted at Mach 6 and Reynolds number of one half million per foot for 0 deg and -5 deg angle-of-attack. Selected thermocouples were chosen from the Orbiter and external tank to be used for obtaining heat transfer measurements. A maximum of 42 thermocouples could be measured by the facility data acquisition at one time and no attempt was made to record the excess thermocouples located on the model. Photographs of the test configurations are shown.

KSC-99pp0517

NASA Image and Video Library

1999-05-12

At Launch Pad 39B, two holes caused by hail on Space Shuttle Discovery's external tank (ET) are visible. Left of the tank is one of the solid rocket boosters. Workers are investigating the damage and potential problems for launch posed by ice forming in the holes, which may number as many as 150 over the entire tank. The average size of the holes is one-half inch in diameter and one-tenth inch deep. The external tank contains the liquid hydrogen fuel and liquid oxygen oxidizer and supplies them under pressure to the three space shuttle main engines in the orbiter during liftoff and ascent. The ET thermal protection system consists of sprayed-on foam insulation. The Shuttle Discovery is targeted for launch of mission STS-96 on May 20 at 9:32 a.m

Propellant Expulsion in Unmanned Spacecraft

DTIC Science & Technology

1966-07-01

29 19. Experimental WAC Corporal piston tank .. ......... . 33 20. Three piston tank designs used in the Corporal program ..... 34 21...propellant. The only universal F. Filling seal at this writing is a metal bellows. Usually, piston tank assemblies are filled by a vacuum technique...externally gener- Piston tank assemblies are subjected to essentially the ated loads due to shock and vibration may be the sever- same tests as bladders. 31

Heat transfer in a tank with a cryogenic fluid under conditions of external heating

NASA Astrophysics Data System (ADS)

Notkin, V. L.

Heat transfer in the gas layer of a horizontal cylindrical tank with a fluctuating level of boiling liquid nitrogen is investigated experimentally. Criterial equations for heat transfer in the gas cavity of the tank are obtained. A procedure is proposed for calculating heat fluxes, temperature fields, and cryogenic fluid evaporation during the filling and draining of the tank.

Stability Analysis of Intertank Formed Skin/Stringer Compression Panel with Simulated Damage

NASA Technical Reports Server (NTRS)

Harper, David W.; Wingate, Robert J.

2012-01-01

The External Tank (ET) is a component of the Space Shuttle launch vehicle that contains fuel and oxidizer. During launch, the ET supplies the space shuttle main engines with liquid hydrogen and liquid oxygen. In addition to supplying fuel and oxidizer, it is the backbone structural component of the Space Shuttle. It is comprised of a liquid hydrogen (LH2) tank and a liquid oxygen (LOX) tank, which are separated by an Intertank. The Intertank is a stringer-stiffened cylindrical structure with hat-section stringers that are roll formed from aluminum-lithium alloy Al-2090. Cracks in the Intertank stringers of the STS-133 ET were noticed after a November 5, 2010 launch attempt. The cracks were approximately nine inches long and occurred on the forward end of the Intertank (near the LOX tank), along the fastener line, and were believed to have occurred while loading the ET with the cryogenic propellants. These cracks generated questions about the structural integrity of the Intertank. In order to determine the structural capability of the Intertank with varying degrees of damage, a finite element model (FEM) simulating a 1995 compression panel test was analyzed and correlated to test data. Varying degrees of damage were simulated in the FEM, and non-linear stability analyses were performed. The high degree of similarity between the compression panel and the Intertank provided confidence that the ET Intertank would have similar capabilities.

Photographic Analysis Technique for Assessing External Tank Foam Loss Events

NASA Technical Reports Server (NTRS)

Rieckhoff, T. J.; Covan, M.; OFarrell, J. M.

2001-01-01

A video camera and recorder were placed inside the solid rocket booster forward skirt in order to view foam loss events over an area on the external tank (ET) intertank surface. In this Technical Memorandum, a method of processing video images to allow rapid detection of permanent changes indicative of foam loss events on the ET surface was defined and applied to accurately count, categorize, and locate such events.

A loose bolt delays loading of Endeavour's external tank

NASA Technical Reports Server (NTRS)

2000-01-01

A closeup reveals the loose bracket, observed hanging down from the side of the White Room at Launch Pad 39B, that delayed loading of Endeavour's external tank by several hours to allow technicians to remove it. A 'U' bolt connects the bracket to a fire suppression water line attached to the exterior of the White Room. The loose bolt could have possibly created a debris hazard.

Analysis of heat-transfer measurements from 2 AEDC wind tunnels on the Shuttle external tank

NASA Technical Reports Server (NTRS)

Nutt, K. W.

1984-01-01

Previous aerodynamic heating tests have been conducted in the AEDC/VKF Supersonic Wind Tunnel (A) to aid in defining the design thermal environment for the space shuttle external tank. The quality of these data has been under discussion because of the effects of low tunnel enthalpy and slow model injection rates. Recently the AEDC/VKF Hypersonic Wind Tunnel (C) has been modified to provide a Mach 4 capability that has significantly higher tunnel enthalpy with more rapid model injection rates. Tests were conducted in Tunnel C at Mach 4 to obtain data on the external tank for comparison with Tunnel A results. Data were obtained on a 0.0175 scale model of the Space Shuttle Integrated Vehicle at Re/ft = 4 x 10 to the 6th power with the tunnel stagnation temperature varying from 740 to 1440 R. Model attitude varied from an angle of attack of -5 to 5 deg and an angle of sideslip of -3 to 3 deg. One set of data was obtained in Tunnel C at Re/ft = 6.9 x 10 to the 6th for comparison with flight data. Data comparisons between the two tunnels for numerous regions on the external tank are given.

Space shuttle phase B extension, volume 1

NASA Technical Reports Server (NTRS)

1971-01-01

In order to define a system which would significantly reduce payload delivery costs, activities were extended to modifications of the reusable space shuttle design concept. Considered were systems using orbiters with external propellant tanks and an interim expendable booster which allowed phased development of the usable orbiter and booster. Analyzed were: Merits of internal and external propellant tanks and the impact of external LH2 compared to L02 and LH2; impact of cargo bay size; impact abort; merit of expendable booster options; and merit of a phased development program. Studies showed that external L02/LH2 and the continued use of the J-2S engine on the orbiter reduced program cost and risk.

Stress Analysis and Testing at the Marshall Space Flight Center to Study Cause and Corrective Action of Space Shuttle External Tank Stringer Failures

NASA Technical Reports Server (NTRS)

Wingate, Robert J.

2012-01-01

After the launch scrub of Space Shuttle mission STS-133 on November 5, 2010, large cracks were discovered in two of the External Tank intertank stringers. The NASA Marshall Space Flight Center, as managing center for the External Tank Project, coordinated the ensuing failure investigation and repair activities with several organizations, including the manufacturer, Lockheed Martin. To support the investigation, the Marshall Space Flight Center formed an ad-hoc stress analysis team to complement the efforts of Lockheed Martin. The team undertook six major efforts to analyze or test the structural behavior of the stringers. Extensive finite element modeling was performed to characterize the local stresses in the stringers near the region of failure. Data from a full-scale tanking test and from several subcomponent static load tests were used to confirm the analytical conclusions. The analysis and test activities of the team are summarized. The root cause of the stringer failures and the flight readiness rationale for the repairs that were implemented are discussed.

STS-133 Space Shuttle External Tank Intertank Stringer Crack Investigation Stress Analysis

NASA Technical Reports Server (NTRS)

Steeve, Brian E.

2012-01-01

The first attempt to launch the STS-133 Space Shuttle mission in the fall of 2010 was halted due to indications of a gaseous hydrogen leak at the External Tank ground umbilical carrier plate seal. Subsequent inspection of the external tank (figure 1) hardware and recorded video footage revealed that the foam insulation covering the forward end of the intertank near the liquid oxygen tank had cracked severely enough to have been cause for halting the launch attempt on its own (figure 2). An investigation into the cause of the insulation crack revealed that two adjacent hat-section sheet metal stringers (figure 3) had cracks up to nine inches long in the forward ends of the stringer flanges, or feet, near the fasteners that attach the stringer to the skin of the intertank (figure 4). A repair of those two stringers was implemented and the investigation effort widened to understand the root cause of the stringer cracks and to determine whether there was sufficient flight rationale to launch with the repairs and the other installed stringers.

KSC-07pd0884

NASA Image and Video Library

2007-04-13

KENNEDY SPACE CENTER, FLA. -- In the Vehicle Assembly Building, the repair work of hail damage on Atlantis' external tank is inspected. At left is Brian Miller, with NASA Quality Assurance; at right is Mike Ravenscroft, with United Space Alliance. In the front is Sabrena Yedo, with NASA Safety. In late February, Atlantis' external tank received hail damage during a severe thunderstorm that passed through the Kennedy Space Center Launch Complex 39 area. The hail caused visible divots in the giant tank's foam insulation as well as minor surface damage to about 26 heat shield tiles on the shuttle's left wing. The launch now is targeted for June 8. Photo credit: NASA/George Shelton

49 CFR 179.400-13 - Support system for inner tank.

Code of Federal Regulations, 2010 CFR

2010-10-01

... FOR TANK CARS Specification for Cryogenic Liquid Tank Car Tanks and Seamless Steel Tanks (Classes DOT... magnitudes and directions when the inner tank is fully loaded and the car is equipped with a conventional... electrically, by either the support system, piping, or a separate electrical connection of approved design. ...

Multiple fuel supply system for an internal combustion engine

DOEpatents

Crothers, William T.

1977-01-01

A multiple fuel supply or an internal combustion engine wherein phase separation of components is deliberately induced. The resulting separation permits the use of a single fuel tank to supply components of either or both phases to the engine. Specifically, phase separation of a gasoline/methanol blend is induced by the addition of a minor amount of water sufficient to guarantee separation into an upper gasoline phase and a lower methanol/water phase. A single fuel tank holds the two-phase liquid with separate fuel pickups and separate level indicators for each phase. Either gasoline or methanol, or both, can be supplied to the engine as required by predetermined parameters. A fuel supply system for a phase-separated multiple fuel supply contained in a single fuel tank is described.

CALUTRON ASSEMBLING AND DISASSEMBLING MEANS

DOEpatents

Andrews, R.E.; Thornton, J.

1959-01-27

This patent relates to the assembling and disassembling of a calutron and, more specifically describes a calutron having the ion separating mechanism carried by a fuce plate removably secured to the tank. When it is desired to withdraw the ion separating mechanism from the tank, a motor is energized and a carriage attached through a bracket to the fuce plate is driven along a track. The face plate moves out from the tank in substantially a linear direction, preventing injury to the ion separating mechanism.

Study of methane fuel for subsonic transport aircraft

NASA Technical Reports Server (NTRS)

Carson, L. K.; Davis, G. W.; Versaw, E. F.; Cunnington, G. R., Jr.; Daniels, E. J.

1980-01-01

The cost and performance were defined for commercial transport using liquid methane including its fuel system and the ground facility complex required for the processing and storage of methane. A cost and performance comparison was made with Jet A and hydrogen powered aircraft of the same payload and range capability. Extensive design work was done on cryogenic fuel tanks, insulation systems as well as the fuel system itself. Three candidate fuel tank locations were evaluated, i.e., fuselage tanks, wing tanks or external pylon tanks.

DOE Office of Scientific and Technical Information (OSTI.GOV)

Espinosa-Loza, Francisco; Ross, Timothy O.; Switzer, Vernon A.

An insert for a cryogenic capable pressure vessel for storage of hydrogen or other cryogenic gases at high pressure. The insert provides the interface between a tank and internal and external components of the tank system. The insert can be used with tanks with any or all combinations of cryogenic, high pressure, and highly diffusive fluids. The insert can be threaded into the neck of a tank with an inner liner. The threads withstand the majority of the stress when the fluid inside the tank that is under pressure.

Failure Analysis of a Helicopter External Fuel-Tank Pylon

NASA Technical Reports Server (NTRS)

Newman, John A.; Piascik, Robert S.; Lindenberg, Richard A.

2002-01-01

An eight-inch-long (0.2 m) crack was found in an external fuel-tank pylon of a U.S. Coast Guard HH-60 helicopter. The damaged pylon was removed from service and destructively examined at NASA Langley Research Center (LaRC) to determine the cause of the crack. Results of the analysis revealed that crack initiation occurred at corrosion pits in a fastener hole and crack propagation was a result of cyclic loading.

Assessment of Technologies for the Space Shuttle External Tank Thermal Protection System and Recommendations for Technology Improvement - Part III: Material Property Characterization, Analysis, and Test Methods

NASA Technical Reports Server (NTRS)

Gates, Thomas S.; Johnson, Theodore F.; Whitley, Karen S.

2005-01-01

The objective of this report is to contribute to the independent assessment of the Space Shuttle External Tank Foam Material. This report specifically addresses material modeling, characterization testing, data reduction methods, and data pedigree. A brief description of the External Tank foam materials, locations, and standard failure modes is provided to develop suitable background information. A review of mechanics based analysis methods from the open literature is used to provide an assessment of the state-of-the-art in material modeling of closed cell foams. Further, this report assesses the existing material property database and investigates sources of material property variability. The report presents identified deficiencies in testing methods and procedures, recommendations for additional testing as required, identification of near-term improvements that should be pursued, and long-term capabilities or enhancements that should be developed.

Fracture Toughness Evaluation of Space Shuttle External Tank Thermal Protection System Polyurethane Foam Insulation Materials

NASA Technical Reports Server (NTRS)

McGill, Preston; Wells, Doug; Morgan, Kristin

2006-01-01

Experimental evaluation of the basic fracture properties of Thermal Protection System (TPS) polyurethane foam insulation materials was conducted to validate the methodology used in estimating critical defect sizes in TPS applications on the Space Shuttle External Fuel Tank. The polyurethane foam found on the External Tank (ET) is manufactured by mixing liquid constituents and allowing them to react and expand upwards - a process which creates component cells that are generally elongated in the foam rise direction and gives rise to mechanical anisotropy. Similarly, the application of successive foam layers to the ET produces cohesive foam interfaces (knitlines) which may lead to local variations in mechanical properties. This study reports the fracture toughness of BX-265, NCFI 24-124, and PDL-1034 closed-cell polyurethane foam as a function of ambient and cryogenic temperatures and knitline/cellular orientation at ambient pressure.

Simulation of Propellant Loading System Senior Design Implement in Computer Algorithm

NASA Technical Reports Server (NTRS)

Bandyopadhyay, Alak

2010-01-01

Propellant loading from the Storage Tank to the External Tank is one of the very important and time consuming pre-launch ground operations for the launch vehicle. The propellant loading system is a complex integrated system involving many physical components such as the storage tank filled with cryogenic fluid at a very low temperature, the long pipe line connecting the storage tank with the external tank, the external tank along with the flare stack, and vent systems for releasing the excess fuel. Some of the very important parameters useful for design purpose are the prediction of pre-chill time, loading time, amount of fuel lost, the maximum pressure rise etc. The physics involved for mathematical modeling is quite complex due to the fact the process is unsteady, there is phase change as some of the fuel changes from liquid to gas state, then conjugate heat transfer in the pipe walls as well as between solid-to-fluid region. The simulation is very tedious and time consuming too. So overall, this is a complex system and the objective of the work is student's involvement and work in the parametric study and optimization of numerical modeling towards the design of such system. The students have to first become familiar and understand the physical process, the related mathematics and the numerical algorithm. The work involves exploring (i) improved algorithm to make the transient simulation computationally effective (reduced CPU time) and (ii) Parametric study to evaluate design parameters by changing the operational conditions

Space Transportatioin System (STS) propellant scavenging system study. Volume 3: Cost and work breakdown structure-dictionary

NASA Technical Reports Server (NTRS)

1985-01-01

Fundamentally, the volumes of the oxidizer and fuel propellant scavenged from the orbiter and external tank determine the size and weight of the scavenging system. The optimization of system dimensions and weights is stimulated by the requirement to minimize the use of partial length of the orbiter payload bay. Thus, the cost estimates begin with weights established for the optimum design. Both the design, development, test, and evaluation and theoretical first unit hardware production costs are estimated from parametric cost weight scaling relations for four subsystems. For cryogenic propellants, the widely differing characteristics of the oxidizer and the fuel lead to two separate tank subsystems, in addition to the electrical and instrumentation subsystems. Hardwares costs also involve quantity, as an independent variable, since the number of production scavenging systems is not firm. For storable propellants, since the tankage volume of the oxidizer and fuel are equal, the hardware production costs for developing these systems are lower than for cryogenic propellants.

KSC-2010-5934

NASA Image and Video Library

2010-12-22

CAPE CANAVERAL, Fla. -- Work platforms inside the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida begin to surround space shuttle Discovery, its solid rocket boosters and external fuel tank at dawn. The shuttle rolled back from Launch Pad 39A so technicians can examine the external tank and re-apply foam where 89 sensors were installed on the tank's aluminum skin for an instrumented tanking test on Dec. 17. The sensors were used to measure changes in the tank as super-cold propellants were pumped in and drained out. Data and analysis from the test will be used to determine what caused the tops of two, 21-foot-long support beams, called stringers, on the outside of the intertank to crack during fueling on Nov. 5. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

KSC-2010-5935

NASA Image and Video Library

2010-12-22

CAPE CANAVERAL, Fla. -- Work platforms inside the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida begin to surround space shuttle Discovery, its solid rocket boosters and external fuel tank. The shuttle rolled back from Launch Pad 39A so technicians can examine the external tank and re-apply foam where 89 sensors were installed on the tank's aluminum skin for an instrumented tanking test on Dec. 17. The sensors were used to measure changes in the tank as super-cold propellants were pumped in and drained out. Data and analysis from the test will be used to determine what caused the tops of two, 21-foot-long support beams, called stringers, on the outside of the intertank to crack during fueling on Nov. 5. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frank Michaux

Technical evaluation of a tank-connected food waste disposer system for biogas production and nutrient recovery.

PubMed

Davidsson, Å; Bernstad Saraiva, A; Magnusson, N; Bissmont, M

2017-07-01

In this study, a tank-connected food waste disposer system with the objective to optimise biogas production and nutrient recovery from food waste in Malmö was evaluated. The project investigated the source-separation ratio of food waste through waste composition analyses, determined the potential biogas production in ground food waste, analysed the organic matter content and the limiting components in ground food waste and analysed outlet samples to calculate food waste losses from the separation tank. It can be concluded that the tank-connected food waste disposer system in Malmö can be used for energy recovery and optimisation of biogas production. The organic content of the collected waste is very high and contains a lot of energy rich fat and protein, and the methane potential is high. The results showed that approximately 38% of the food waste dry matter is collected in the tank. The remaining food waste is either found in residual waste (34% of the dry matter) or passes the tank and goes through the outlet to the sewer (28%). The relatively high dry matter content in the collected fraction (3-5% DM) indicates that the separation tank can thicken the waste substantially. The potential for nutrient recovery is rather limited considering the tank content. Only small fractions of the phosphorus (15%) and nitrogen (21%) are recyclable by the collected waste in the tank. The quality of the outlet indicates a satisfactory separation of particulate organic matter and fat. The organic content and nutrients, which are in dissolved form, cannot be retained in the tank and are rather led to the sewage via the outlet. Copyright © 2017 Elsevier Ltd. All rights reserved.

Space Shuttle Projects

NASA Image and Video Library

1989-03-01

This STS-29 mission onboard photo depicts the External Tank (ET) falling toward the ocean after separation from the Shuttle orbiter Discovery. The giant cylinder, higher than a 15-story building, with a length of 154-feet (47-meters) and a diameter of 27,5-feet (8.4-meters), is the largest single piece of the Space Shuttle. During launch, the ET also acts as a backbone for the orbiter and solid rocket boosters. In separate, internal pressurized tank sections, the ET holds the liquid hydrogen fuel and liquid oxygen oxidizer for the Shuttle's three main engines. During launch, the ET feeds the fuel under pressure through 17-inch (43.2-centimeter) ducts which branch off into smaller lines that feed directly into the main engines. Some 64,000 gallons (242,260 liters) of fuel are consumed by the main engines each minute. Machined from aluminum alloys, the Space Shuttle's ET is the only part of the launch vehicle that currently is not reused. After its 526,000 gallons (1,991,071 liters) of propellants are consumed during the first 8.5 minutes of flight, it is jettisoned from the orbiter and breaks up in the upper atmosphere, its pieces falling into remote ocean waters. The Marshall Space Flight Center was responsible for developing the ET.

[Study on the quantitative estimation method for VOCs emission from petrochemical storage tanks based on tanks 4.0.9d model].

PubMed

Li, Jing; Wang, Min-Yan; Zhang, Jian; He, Wan-Qing; Nie, Lei; Shao, Xia

2013-12-01

VOCs emission from petrochemical storage tanks is one of the important emission sources in the petrochemical industry. In order to find out the VOCs emission amount of petrochemical storage tanks, Tanks 4.0.9d model is utilized to calculate the VOCs emission from different kinds of storage tanks. VOCs emissions from a horizontal tank, a vertical fixed roof tank, an internal floating roof tank and an external floating roof tank were calculated as an example. The consideration of the site meteorological information, the sealing information, the tank content information and unit conversion by using Tanks 4.0.9d model in China was also discussed. Tanks 4.0.9d model can be used to estimate VOCs emissions from petrochemical storage tanks in China as a simple and highly accurate method.

In-Tank Elutriation Test Report And Independent Assessment

DOE Office of Scientific and Technical Information (OSTI.GOV)

Burns, H. H.; Adamson, D. J.; Qureshi, Z. H.

2011-04-13

The Department of Energy (DOE) Office of Environmental Management (EM) funded Technology Development and Deployment (TDD) to solve technical problems associated with waste tank closure for sites such as Hanford Site and Savannah River Site (SRS). One of the tasks supported by this funding at Savannah River National Laboratory (SRNL) and Pacific Northwest Laboratory (PNNL) was In-Tank Elutriation. Elutriation is the process whereby physical separation occurs based on particle size and density. This report satisfies the first phase of Task WP_1.3.1.1 In-Tank Elutriation, which is to assess the feasibility of this method of separation in waste tanks at Hanford Sitemore » and SRS. This report includes an analysis of scoping tests performed in the Engineering Development Laboratory of SRNL, analysis of Hanford's inadvertent elutriation, the viability of separation methods such as elutriation and hydrocyclones and recommendations for a path forward. This report will demonstrate that the retrieval of Hanford salt waste tank S-112 very successfully decreased the tank's inventories of radionuclides. Analyses of samples collected from the tank showed that concentrations of the major radionuclides Cs-136 and Sr-90 were decreased by factors of 250 and 6 and their total curie tank inventories decreased by factors of 60,000 and 2000. The total tank curie loading decreased from 300,000 Ci to 55 Ci. The remaining heel was nearly all innocuous gibbsite, Al(OH){sub 3}. However, in the process of tank retrieval approximately 85% of the tank gibbsite was also removed. Significant amounts of money and processing time could be saved if more gibbsite could be left in tanks while still removing nearly all of the radionuclides. There were factors which helped to make the elutriation of Tank S-112 successful which would not necessarily be present in all salt tanks. 1. The gibbsite particles in the tank were surprisingly large, as much as 200 {micro}m. The gibbsite crystals had probably grown in size over a period of decades. 2. The radionuclides were apparently either in the form of soluble compounds, like cesium, or micrometer sized particles of actinide oxides or hydroxides. 3. After the initial tank retrieval the tank contained cobble which is not conducive to elutriation. Only after the tank contents were treated with thousands of gallons of 50 wt% caustic, were the solids converted to sand which is compatible with elutriation. Discussions between SRNL and PNNL resulted in plans to test elutriation in two phases; in Phase 1 particles would be separated by differences in settling velocity in an existing scaled tank with its associated hardware and in Phase 2 additional hardware, such as a hydrocyclone, would be added downstream to separate slow settling partciels from liquid. Phase 1 of in-tank elutriation was tested for Proof of Principle in theEngineering Development Laboratory of SRNL in a 41" diameter, 87 gallon tank. The tank had been previously used as a 1/22 scale model of Hanford Waste Tank AY-102. The objective of the testing was to determine which tank operating parameters achieved the best separation between fast- and slow-settling particles. For Phase 1 testing a simulated waste tank supernatant, slow-settling particles and fast-settling particles were loaded to the scaled tank. Because this was a Proof of Principle test, readily available solids particles were used that represented fast-settling and slow-settling particles. The tank contents were agitated using rotating mixer jet pumps (MJP) which suspended solids while liquids and solids were drawn out of the tank with a suction tube. The goal was to determine the optimum hydraulic operating conditions to achieve clean separation in which the residual solids in the tank were nearly all fast-settling particles and the solids transferred out of the tank were nearly all slow-settling particles. Tests were conducted at different pump jet velocities, suction tube diameters and suction tube elevations. Testing revealed that the most important variable was jet velocity which translates to a downstream fluid velocity in the vicinity of the suction tube which can suspend particles and potentially allow their removal from the tank. The optimum jet velocity in the vicinity of the sucti9on tube was between 1.5 and 2 ft/s (4-5 gpm). During testing at lower velocities a significant amount of slow-settling particles remained in the tank. At higher velocities a significant amount of fast-settling particles were elutriated from the tank. It should be noted that this range of velocities is appropriate for this particular geometry and particles. However, the principle of In-Tank Elutriation was proved. In-tank elutriation has the potential to save much money in tank closure. However, more work, both analytical and experimental, must be done before an improved version of the process could be applied to actual waste tanks. It is recommended that testing with more prototypic simulants be conducted. Also, scale-up criteria for elutriation and the resulting size of pilot scale test equipment require investigation during future research. In addition, it is recommended that the use of hydrocyclones be pursued in Phase 2 testing. Hydrocyclones are a precise and efficient separation tool that are frequently used in industry.« less

Method and apparatus for production of subsea hydrocarbon formations

DOEpatents

Blandford, Joseph W.

1995-01-01

A system for controlling, separating, processing and exporting well fluids produced from subsea hydrocarbon formations is disclosed. The subsea well tender system includes a surface buoy supporting one or more decks above the water surface for accommodating equipment to process oil, gas and water recovered from the subsea hydrocarbon formation. The surface buoy includes a surface-piercing central flotation column connected to one or more external floatation tanks located below the water surface. The surface buoy is secured to the seabed by one or more tendons which are anchored to a foundation with piles imbedded in the seabed. The system accommodates multiple versions on the surface buoy configuration.

46 CFR 167.15-40 - Integral fuel oil tank examinations-T/ALL.

Code of Federal Regulations, 2010 CFR

2010-10-01

... vessel shall have the tanks cleaned out and gas freed as necessary to permit internal examination of the... examination of the fuel tanks of each vessel during an internal structural examination at intervals not to... examined if the marine inspector is able to determine by external examination that the general condition of...

46 CFR 154.452 - External pressure.

Code of Federal Regulations, 2012 CFR

2012-10-01

...: P1=the vacuum relief valve setting for tanks with a vacuum relief valve, or 24.5 kPa gauge (3.55 psig) for tanks without a vacuum relief valve. P2=0, or the pressure relief valve setting for an enclosed... weight of the tank, including corrosion allowance, weight of insulation, weight of dome, weight of pipe...

46 CFR 154.452 - External pressure.

Code of Federal Regulations, 2013 CFR

2013-10-01

...: P1=the vacuum relief valve setting for tanks with a vacuum relief valve, or 24.5 kPa gauge (3.55 psig) for tanks without a vacuum relief valve. P2=0, or the pressure relief valve setting for an enclosed... weight of the tank, including corrosion allowance, weight of insulation, weight of dome, weight of pipe...

46 CFR 154.452 - External pressure.

Code of Federal Regulations, 2010 CFR

2010-10-01

...: P1=the vacuum relief valve setting for tanks with a vacuum relief valve, or 24.5 kPa gauge (3.55 psig) for tanks without a vacuum relief valve. P2=0, or the pressure relief valve setting for an enclosed... weight of the tank, including corrosion allowance, weight of insulation, weight of dome, weight of pipe...

46 CFR 154.452 - External pressure.

Code of Federal Regulations, 2014 CFR

2014-10-01

...: P1=the vacuum relief valve setting for tanks with a vacuum relief valve, or 24.5 kPa gauge (3.55 psig) for tanks without a vacuum relief valve. P2=0, or the pressure relief valve setting for an enclosed... weight of the tank, including corrosion allowance, weight of insulation, weight of dome, weight of pipe...

46 CFR 154.452 - External pressure.

Code of Federal Regulations, 2011 CFR

2011-10-01

...: P1=the vacuum relief valve setting for tanks with a vacuum relief valve, or 24.5 kPa gauge (3.55 psig) for tanks without a vacuum relief valve. P2=0, or the pressure relief valve setting for an enclosed... weight of the tank, including corrosion allowance, weight of insulation, weight of dome, weight of pipe...

KSC-2010-5961

NASA Image and Video Library

2010-12-29

CAPE CANAVERAL, Fla. -- Inside the intertank of space shuttle Discovery's external fuel tank, a technician holds the film used to project computed radiography scans. The shuttle stack, consisting of the shuttle, external tank and solid rocket boosters, was moved from Launch Pad 39A to the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida so technicians could examine 21-foot-long support beams, called stringers, on the outside of the tank's intertank and re-apply foam insulation. Discovery's next launch opportunity to the International Space Station on the STS-133 mission is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Frankie Martin

KSC-05PD-1211

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. The crane lifting orbiter Discovery casts an arc shadow across the underside of the nose as a silhouetted worker at right watches. The orbiter, in high bay 1 of the Vehicle Assembly Building at NASAs Kennedy Space Center, is being lifted away from the External Tank and Solid Rocket Boosters. After demating from its External Tank (ET), the orbiter will be placed on a transporter in the transfer aisle and moved to high bay 3 for remating with another tank, ET-121. Discovery is expected to be rolled back to the launch pad in mid-June for Return to Flight mission STS-114. The launch window extends from July 13 to July 31.

STS-45 external tank (ET) falls back to Earth after jettisoning from OV-104

NASA Image and Video Library

1992-03-24

STS045-71-001 (24 March 1992) --- This 70mm photograph of the external fuel tank (ET) for STS-45 was photographed 4 1/2 minutes after having been jettisoned from Space Shuttle Atlantis. The excellent view of the starboard side of the ET shows both top and bottom attach points to the two solid rocket boosters (SRB). NASA engineers studying the STS-45 onboard photography deem the visible burn scars, caused by the SRBs, to be normal. The long thin pipe visible is the liquid oxygen line. At the bottom end of the large tank, both the liquid oxygen (nearest camera) and liquid hydrogen orbiter-to-ET attach hardware can be seen.

A loose bolt delays loading of Endeavour's external tank

NASA Technical Reports Server (NTRS)

2000-01-01

This view shows the pipe (center top) leading toward Endeavour from the side of the White Room at Launch Pad 39B. A loose bracket observed hanging down from the pipe delayed loading of Endeavour's external tank by several hours to allow technicians to remove it. A 'U' bolt connects the bracket to a fire suppression water line attached to the exterior of the White Room. The loose bolt could have possibly created a debris hazard.

External tank space debris considerations

NASA Technical Reports Server (NTRS)

Elfer, N.; Baillif, F.; Robinson, J.

1992-01-01

Orbital debris issues associated with maintaining a Space Shuttle External Tank (ET) on orbit are presented. The first issue is to ensure that the ET does not become a danger to other spacecraft by generating space debris, and the second is to protect the pressurized ET from penetration by space debris or meteoroids. Tests on shield designs for penetration resistance showed that when utilized with an adequate bumper, thermal protection system foam on the ET is effective in preventing penetration.

46 CFR 169.631 - Separation of machinery and fuel tank spaces from accommodation spaces.

Code of Federal Regulations, 2011 CFR

2011-10-01

... 46 Shipping 7 2011-10-01 2011-10-01 false Separation of machinery and fuel tank spaces from accommodation spaces. 169.631 Section 169.631 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) NAUTICAL SCHOOLS SAILING SCHOOL VESSELS Machinery and Electrical Ventilation § 169.631 Separation of...

49 CFR 179.400-13 - Support system for inner tank.

Code of Federal Regulations, 2012 CFR

2012-10-01

... CARS Specification for Cryogenic Liquid Tank Car Tanks and Seamless Steel Tanks (Classes DOT-113 and... directions when the inner tank is fully loaded and the car is equipped with a conventional draft gear... the support system, piping, or a separate electrical connection of approved design. ...

49 CFR 179.400-13 - Support system for inner tank.

Code of Federal Regulations, 2013 CFR

2013-10-01

... CARS Specification for Cryogenic Liquid Tank Car Tanks and Seamless Steel Tanks (Classes DOT-113 and... directions when the inner tank is fully loaded and the car is equipped with a conventional draft gear... the support system, piping, or a separate electrical connection of approved design. ...

49 CFR 179.400-13 - Support system for inner tank.

Code of Federal Regulations, 2014 CFR

2014-10-01

... CARS Specification for Cryogenic Liquid Tank Car Tanks and Seamless Steel Tanks (Classes DOT-113 and... directions when the inner tank is fully loaded and the car is equipped with a conventional draft gear... the support system, piping, or a separate electrical connection of approved design. ...

49 CFR 179.400-13 - Support system for inner tank.

Code of Federal Regulations, 2011 CFR

2011-10-01

... CARS Specification for Cryogenic Liquid Tank Car Tanks and Seamless Steel Tanks (Classes DOT-113 and... directions when the inner tank is fully loaded and the car is equipped with a conventional draft gear... the support system, piping, or a separate electrical connection of approved design. ...

Aerodynamic results of a separation effects test on a 0.010-scale model (52-OTS) of the integrated SSV in the AEDC/VKF 40-by-40 inch supersonic wind tunnel A (IA111), volume 1

NASA Technical Reports Server (NTRS)

Chee, E.

1976-01-01

Graphical data obtained during experimental wind tunnel aerodynamic investigations of a 0.010 scale model (52-OTS) of the integrated space shuttle vehicle was presented. The purpose of this investigation was to obtain data with the solid rocket booster (SRB) in proximity to the orbiter/external tank (O/ET), over a large O/ET initial angle of attack and sideslip range, as well as data on the SRB alone (greatly separated from the O/ET). A captive trajectory system, which supported the SRB, was used with the tunnel primary sector (supporting the O/ET) to obtain grid type separation effects data. One symmetrical SRB model was used interchangeably to obtain right-hand and left-hand SRB data. The entire investigation was conducted at a free-stream Mach number of 4.5 at unit Reynolds number of 3.95 and 5.9 million per foot.

40 CFR 270.305 - What tank information must I keep at my facility?

Code of Federal Regulations, 2011 CFR

2011-07-01

..., bypass systems, and pressure controls (e.g., vents). (d) A diagram of piping, instrumentation, and process flow for each tank system. (e) A description of materials and equipment used to provide external...

40 CFR 270.305 - What tank information must I keep at my facility?

Code of Federal Regulations, 2012 CFR

2012-07-01

..., bypass systems, and pressure controls (e.g., vents). (d) A diagram of piping, instrumentation, and process flow for each tank system. (e) A description of materials and equipment used to provide external...

40 CFR 270.305 - What tank information must I keep at my facility?

Code of Federal Regulations, 2013 CFR

2013-07-01

..., bypass systems, and pressure controls (e.g., vents). (d) A diagram of piping, instrumentation, and process flow for each tank system. (e) A description of materials and equipment used to provide external...

40 CFR 270.305 - What tank information must I keep at my facility?

Code of Federal Regulations, 2014 CFR

2014-07-01

..., bypass systems, and pressure controls (e.g., vents). (d) A diagram of piping, instrumentation, and process flow for each tank system. (e) A description of materials and equipment used to provide external...

Elastic-Plastic Nonlinear Response of a Space Shuttle External Tank Stringer. Part 2; Thermal and Mechanical Loadings

NASA Technical Reports Server (NTRS)

Knight, Norman F., Jr.; Warren, Jerry E.; Elliott, Kenny B.; Song, Kyongchan; Raju, Ivatury S.

2012-01-01

Elastic-plastic, large-deflection nonlinear thermo-mechanical stress analyses are performed for the Space Shuttle external tank s intertank stringers. Detailed threedimensional finite element models are developed and used to investigate the stringer s elastic-plastic response for different thermal and mechanical loading events from assembly through flight. Assembly strains caused by initial installation on an intertank panel are accounted for in the analyses. Thermal loading due to tanking was determined to be the bounding loading event. The cryogenic shrinkage caused by tanking resulted in a rotation of the intertank chord flange towards the center of the intertank, which in turn loaded the intertank stringer feet. The analyses suggest that the strain levels near the first three fasteners remain sufficiently high that a failure may occur. The analyses also confirmed that the installation of radius blocks on the stringer feet ends results in an increase in the stringer capability.

Space shuttle with common fuel tank for liquid rocket booster and main engines (supertanker space shuttle)

NASA Technical Reports Server (NTRS)

Thorpe, Douglas G.

1991-01-01

An operation and schedule enhancement is shown that replaces the four-body cluster (Space Shuttle Orbiter (SSO), external tank, and two solid rocket boosters) with a simpler two-body cluster (SSO and liquid rocket booster/external tank). At staging velocity, the booster unit (liquid-fueled booster engines and vehicle support structure) is jettisoned while the remaining SSO and supertank continues on to orbit. The simpler two-bodied cluster reduces the processing and stack time until SSO mate from 57 days (for the solid rocket booster) to 20 days (for the liquid rocket booster). The areas in which liquid booster systems are superior to solid rocket boosters are discussed. Alternative and future generation vehicles are reviewed to reveal greater performance and operations enhancements with more modifications to the current methods of propulsion design philosophy, e.g., combined cycle engines, and concentric propellant tanks.

KSC-2010-5883

NASA Image and Video Library

2010-12-17

CAPE CANAVERAL, Fla. -- Team members stationed at consoles in the Launch Control Center at NASA's Kennedy Space Center in Florida monitor space shuttle Discovery's external fuel tank as it is loaded with more than 535,000 gallons of cryogenic propellants. During today's tanking test, the team is paying particular attention to the external tank's ribbed intertank region. Beginning tomorrow, engineers will evaluate data on 21-foot-long, U-shaped aluminum brackets, called stringers, and the newly replaced ground umbilical carrier plate (GUCP). Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at the GUCP. In order to perform additional analysis on the tank, Discovery will be rolled back to the Vehicle Assembly Building, a move that is planned for next week. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Cory Huston

ICPP tank farm closure study. Volume 1

DOE Office of Scientific and Technical Information (OSTI.GOV)

Spaulding, B.C.; Gavalya, R.A.; Dahlmeir, M.M.

1998-02-01

The disposition of INEEL radioactive wastes is now under a Settlement Agreement between the DOE and the State of Idaho. The Settlement Agreement requires that existing liquid sodium bearing waste (SBW), and other liquid waste inventories be treated by December 31, 2012. This agreement also requires that all HLW, including calcined waste, be disposed or made road ready to ship from the INEEL by 2035. Sodium bearing waste (SBW) is produced from decontamination operations and HLW from reprocessing of SNF. SBW and HLW are radioactive and hazardous mixed waste; the radioactive constituents are regulated by DOE and the hazardous constituentsmore » are regulated by the Resource Conservation and Recovery Act (RCRA). Calcined waste, a dry granular material, is produced in the New Waste Calcining Facility (NWCF). Two primary waste tank storage locations exist at the ICPP: Tank Farm Facility (TFF) and the Calcined Solids Storage Facility (CSSF). The TFF has the following underground storage tanks: four 18,400-gallon tanks (WM 100-102, WL 101); four 30,000-gallon tanks (WM 103-106); and eleven 300,000+ gallon tanks. This includes nine 300,000-gallon tanks (WM 182-190) and two 318,000 gallon tanks (WM 180-181). This study analyzes the closure and subsequent use of the eleven 300,000+ gallon tanks. The 18,400 and 30,000-gallon tanks were not included in the work scope and will be closed as a separate activity. This study was conducted to support the HLW Environmental Impact Statement (EIS) waste separations options and addresses closure of the 300,000-gallon liquid waste storage tanks and subsequent tank void uses. A figure provides a diagram estimating how the TFF could be used as part of the separations options. Other possible TFF uses are also discussed in this study.« less

Control techniques to improve Space Shuttle solid rocket booster separation

NASA Technical Reports Server (NTRS)

Tomlin, D. D.

1983-01-01

The present Space Shuttle's control system does not prevent the Orbiter's main engines from being in gimbal positions that are adverse to solid rocket booster separation. By eliminating the attitude error and attitude rate feedback just prior to solid rocket booster separation, the detrimental effects of the Orbiter's main engines can be reduced. In addition, if angular acceleration feedback is applied, the gimbal torques produced by the Orbiter's engines can reduce the detrimental effects of the aerodynamic torques. This paper develops these control techniques and compares the separation capability of the developed control systems. Currently with the worst case initial conditions and each Shuttle system dispersion aligned in the worst direction (which is more conservative than will be experienced in flight), the solid rocket booster has an interference with the Shuttle's external tank of 30 in. Elimination of the attitude error and attitude rate feedback reduces that interference to 19 in. Substitution of angular acceleration feedback reduces the interference to 6 in. The two latter interferences can be eliminated by atess conservative analysis techniques, that is, by using a root sum square of the system dispersions.

Freedom Star tows a barge with an SLWT into Port Canaveral for the first time

NASA Technical Reports Server (NTRS)

1998-01-01

Freedom Star, one of NASA's two solid rocket booster recovery ships, tows a barge containing the third Space Shuttle super lightweight external tank (SLWT) into Port Canaveral. This SLWT will be used to launch the orbiter Discovery on mission STS-95 in October. This first-time towing arrangement, part of a cost savings plan by NASA to prudently manage existing resources, began June 12 from the Michoud Assembly Facility in New Orleans where the Shuttle's external tanks are manufactured. The barge will now be transported up the Banana River to the LC-39 turn basin using a conventional tugboat. Previously, NASA relied on an outside contractor to provide external tank towing services at a cost of about $120,000 per trip. The new plan allows NASA's Space Flight Operations contractor, United Space Alliance (USA), to provide the same service directly to NASA using the recovery ships during their downtime between Shuttle launches. Studies show a potential savings of about $50,000 per trip. The cost of the necessary ship modifications should be paid back by the fourteenth tank delivery. The other recovery ship, Liberty Star, has also undergone deck strengthening enhancements and will soon have the necessary towing winch installed.

Recovery Ship Freedom Star

NASA Technical Reports Server (NTRS)

1998-01-01

Freedom Star, one of NASA's two solid rocket booster recovery ships, is towing a barge containing the third Space Shuttle Super Lightweight External Tank (SLWT) into Port Canaveral. This SLWT was slated for use to launch the orbiter Discovery on mission STS-95 in October 1998. This first time towing arrangement, part of a cost saving plan by NASA to prudently manage existing resources, began June 12 from the Michoud Assembly Facility in New Orleans where the Shuttle's external tanks were manufactured. The barge was transported up Banana River to the LC-39 turn basin using a conventional tug boat. Previously, NASA relied on an outside contractor to provide external tank towing services at a cost of about $120,000 per trip. The new plan allowed NASA's Space Flight Operations contractor, United Space Alliance (USA), to provide the same service to NASA using the recovery ships during their downtime between Shuttle launches. Studies showed a potential savings of about $50,000 per trip. The cost of the necessary ship modifications would be paid back by the fourteenth tank delivery. The other recovery ship, Liberty Star, also underwent deck strengthening enhancements and had the necessary towing wench installed.

46 CFR 58.50-5 - Gasoline fuel tanks.

Code of Federal Regulations, 2014 CFR

2014-10-01

... 46 Shipping 2 2014-10-01 2014-10-01 false Gasoline fuel tanks. 58.50-5 Section 58.50-5 Shipping... AND RELATED SYSTEMS Independent Fuel Tanks § 58.50-5 Gasoline fuel tanks. (a) Construction—(1) Shape...) Installation. (1) Gasoline fuel tanks used for propulsion shall be located in water-tight compartments separate...

46 CFR 58.50-5 - Gasoline fuel tanks.

Code of Federal Regulations, 2010 CFR

2010-10-01

... 46 Shipping 2 2010-10-01 2010-10-01 false Gasoline fuel tanks. 58.50-5 Section 58.50-5 Shipping... AND RELATED SYSTEMS Independent Fuel Tanks § 58.50-5 Gasoline fuel tanks. (a) Construction—(1) Shape...) Installation. (1) Gasoline fuel tanks used for propulsion shall be located in water-tight compartments separate...

46 CFR 58.50-5 - Gasoline fuel tanks.

Code of Federal Regulations, 2012 CFR

2012-10-01

... 46 Shipping 2 2012-10-01 2012-10-01 false Gasoline fuel tanks. 58.50-5 Section 58.50-5 Shipping... AND RELATED SYSTEMS Independent Fuel Tanks § 58.50-5 Gasoline fuel tanks. (a) Construction—(1) Shape...) Installation. (1) Gasoline fuel tanks used for propulsion shall be located in water-tight compartments separate...

46 CFR 58.50-5 - Gasoline fuel tanks.

Code of Federal Regulations, 2013 CFR

2013-10-01

... 46 Shipping 2 2013-10-01 2013-10-01 false Gasoline fuel tanks. 58.50-5 Section 58.50-5 Shipping... AND RELATED SYSTEMS Independent Fuel Tanks § 58.50-5 Gasoline fuel tanks. (a) Construction—(1) Shape...) Installation. (1) Gasoline fuel tanks used for propulsion shall be located in water-tight compartments separate...

46 CFR 58.50-5 - Gasoline fuel tanks.

Code of Federal Regulations, 2011 CFR

2011-10-01

... 46 Shipping 2 2011-10-01 2011-10-01 false Gasoline fuel tanks. 58.50-5 Section 58.50-5 Shipping... AND RELATED SYSTEMS Independent Fuel Tanks § 58.50-5 Gasoline fuel tanks. (a) Construction—(1) Shape...) Installation. (1) Gasoline fuel tanks used for propulsion shall be located in water-tight compartments separate...

High-speed machining of Space Shuttle External Tank (ET) panels

NASA Technical Reports Server (NTRS)

Miller, J. A.

1983-01-01

Potential production rates and project cost savings achieved by converting the conventional machining process in manufacturing shuttle external tank panels to high speed machining (HSM) techniques were studied. Savings were projected from the comparison of current production rates with HSM rates and with rates attainable on new conventional machines. The HSM estimates were also based on rates attainable by retrofitting existing conventional equipment with high speed spindle motors and rates attainable using new state of the art machines designed and built for HSM.

Development of acceptance criteria for batches of silane primer for external tank thermal protection system bonding applications

NASA Technical Reports Server (NTRS)

Mikes, F.

1984-01-01

Silane primers for use as thermal protection on external tanks were subjected to various analytic techniques to determine the most effective testing method for silane lot evaluation. The analytic methods included high performance liquid chromatography, gas chromatography, thermogravimetry (TGA), and fourier transform infrared spectroscopy (FTIR). It is suggested that FTIR be used as the method for silane lot evaluation. Chromatograms, TGA profiles, bar graphs showing IR absorbances, and FTIR spectra are presented.

Application of Digital Radiography to Weld Inspection for the Space Shuttle External Fuel Tank

NASA Technical Reports Server (NTRS)

Ussery, Warren

2009-01-01

This slide presentation reviews NASA's use of digital radiography to inspect the welds of the external tanks used to hold the cryogenic fuels for the Space Shuttle Main Engines. NASA has had a goal of replacing a significant portion of film used to inspect the welds, with digital radiography. The presentation reviews the objectives for converting to a digital system from film, the characteristics of the digital system, the Probability of detection study, the qualification and implementation of the system.

Woodpecker Preventative measures at Launch Pad 39B

NASA Technical Reports Server (NTRS)

1995-01-01

Technicians at Launch Pad 39B take steps to prevent further damage from woodpeckers to the Space Shuttle Discovery, set to lift off July 13 on Mission STS-70. Installing balloons with scary eyes, such as these two near the external tank, are just one of the measures being taken to keep woodpeckers away since Discovery's second rollout to Pad B. Discovery had to be rolled back once to the Vehicle Assembly Building to repair woodpecker holes made in the insulation covering the external tank.

View of the SRB problems with Challenger after launch

NASA Technical Reports Server (NTRS)

1986-01-01

51-L investigation at time 73.200 seconds, Flash from region between orbiter and external tank (ET) liquid hydrogen (LH2) tank, USC-10. Kennedy Space Center alternative photo number is 108-KSC-386C-560/53.

Intelligent Evaluation Method of Tank Bottom Corrosion Status Based on Improved BP Artificial Neural Network

NASA Astrophysics Data System (ADS)

Qiu, Feng; Dai, Guang; Zhang, Ying

According to the acoustic emission information and the appearance inspection information of tank bottom online testing, the external factors associated with tank bottom corrosion status are confirmed. Applying artificial neural network intelligent evaluation method, three tank bottom corrosion status evaluation models based on appearance inspection information, acoustic emission information, and online testing information are established. Comparing with the result of acoustic emission online testing through the evaluation of test sample, the accuracy of the evaluation model based on online testing information is 94 %. The evaluation model can evaluate tank bottom corrosion accurately and realize acoustic emission online testing intelligent evaluation of tank bottom.

KSC-08pd3895

NASA Image and Video Library

2008-12-03

CAPE CANAVERAL, Fla. -- An alligator basks in the sun on the bank of the Banana River near NASA's Kennedy Space Center in Florida. It is witness to the passage of the Pegasus barge through the Banana River toward the turn basin near the Vehicle Assembly Building, or VAB, at NASA's Kennedy Space Center in Florida. Pegasus, carrying external tank 130, arrived in Florida after an ocean voyage towed by a solid rocket booster retrieval ship from NASA's Michoud Assembly Facility near New Orleans. After the Pegasus docks, the fuel tank will be offloaded and transported to the VAB. External tank 130 is the one designated for space shuttle Endeavour on the STS-127 mission targeted for launch on May 15. Photo credit: NASA/Troy Cryder

KSC-08pd3896

NASA Image and Video Library

2008-12-03

CAPE CANAVERAL, Fla. -- An alligator basks in the sun on the bank of the Banana River near NASA's Kennedy Space Center in Florida. It is witness to the passage of the Pegasus barge through the Banana River toward the turn basin near the Vehicle Assembly Building, or VAB, at NASA's Kennedy Space Center in Florida. Pegasus, carrying external tank 130, arrived in Florida after an ocean voyage towed by a solid rocket booster retrieval ship from NASA's Michoud Assembly Facility near New Orleans. After the Pegasus docks, the fuel tank will be offloaded and transported to the VAB. External tank 130 is the one designated for space shuttle Endeavour on the STS-127 mission targeted for launch on May 15. Photo credit: NASA/Troy Cryder

The Evolution of Nondestructive Evaluation Methods for the Space Shuttle External Tank Thermal Protection System

NASA Technical Reports Server (NTRS)

Walker, James L.; Richter, Joel D.

2006-01-01

Three nondestructive evaluation methods are being developed to identify defects in the foam thermal protection system (TPS) of the Space Shuttle External Tank (ET). Shearography is being developed to identify shallow delaminations, shallow voids and crush damage in the foam while terahertz imaging and backscatter radiography are being developed to identify voids and cracks in thick foam regions. The basic theory of operation along with factors affecting the results of these methods will be described. Also, the evolution of these methods from lab tools to implementation on the ET will be discussed. Results from both test panels and flight tank inspections will be provided to show the range in defect sizes and types that can be readily detected.

Thermal design of the space shuttle external tank

NASA Technical Reports Server (NTRS)

Bachrtel, F. D.; Vaniman, J. L.; Stuckey, J. M.; Gray, C.; Widofsky, B.

1985-01-01

The shuttle external tank thermal design presents many challenges in meeting the stringent requirements established by the structures, main propulsion systems, and Orbiter elements. The selected thermal protection design had to meet these requirements, and ease of application, suitability for mass production considering low weight, cost, and high reliability. This development led to a spray-on-foam (SOFI) which covers the entire tank. The need and design for a SOFI material with a dual role of cryogenic insulation and ablator, and the development of the SOFI over SLA concept for high heating areas are discussed. Further issuses of minimum surface ice/frost, no debris, and the development of the TPS spray process considering the required quality and process control are examined.

KSC-98pc265

NASA Image and Video Library

1998-02-03

KENNEDY SPACE CENTER, FLA. -- The Space Shuttle's first super lightweight external tank is moved on a barge by two tug boats toward a pier at Port Canaveral, Fla. The tank is scheduled to undergo processing at Kennedy Space Center for flight on STS-91, targeted for launch in late May. The improved tank is 7,500 pounds lighter than its predecessors and was developed to increase the Shuttle payload capacity on International Space Station assembly flights. The tank was sent from the NASA Michoud Assembly Facility in New Orleans

Residual Silicone Detection. [external tank and solid rocket booster surfaces

NASA Technical Reports Server (NTRS)

Smith, T.

1980-01-01

Both photoelectron emission and ellipsometry proved successful in detecting silicone contamination on unpainted and epoxy painted metal surfaces such as those of the external tank and the solid rocket booster. Great success was achieved using photoelectron emission (PEE). Panels were deliberately contaminated to controlled levels and then mapped with PEE to reveal the areas and levels that were contaminated. The panels were then tested with regard to adhesive properties. Tapes were bonded over the contaminated and uncontaminated regions and the peel force was measured, or the contaminated panels were bonded (with CPR 483 foam) to uncontaminated panels and made into lap shear specimens. Other panels were bonded and made into wedge specimens for hydrothermal stress endurance tests. Strong adhesion resulted if the PEE signal fell within an acceptance window, but was poor outside the acceptance window. A prototype instrument is being prepared which can automatically be scanned over the external liquid hydrogen tank and identify those regions that are contaminated and will cause bond degradation.

Results of investigations on a 0.010-scale model of the configuration 3 space shuttle orbiter and external tank in the NASA/Ames Research Center 3.5-foot hypersonic wind tunnel (IA15)

NASA Technical Reports Server (NTRS)

Petrozzi, M. T.; Milam, M. D.; Mellenthin, J. A.

1974-01-01

Experimental aerodynamic investigations were conducted in a 3.5-foot hypersonic wind tunnel. The model used for this test was a 0.010-scale of the Configuration 2 Space Shuttle Orbiter and the External Tank. Six-component aerodynamic force and moment data were recorded over an angle of attack range from -8 deg to +30 deg at 0 deg and 5 deg angles of sideslip. Data was also recorded during beta sweeps of -8 deg to +10 deg at angles of attack of -10 deg, 0 deg, and 30 deg. All testing was done at Mach 7.3. Various elevon, rudder and orbiter to external tank attaching structures and fairings were tested to determine longitudinal and lateral-directional stability characteristics. Non-metric exhaust plumes were installed during a portion of the testing to determine the effects of the main propulsion system rocket plumes.

Pad B Liquid Hydrogen Storage Tank

NASA Technical Reports Server (NTRS)

Hall, Felicia

2007-01-01

Kennedy Space Center is home to two liquid hydrogen storage tanks, one at each launch pad of Launch Complex 39. The liquid hydrogen storage tank at Launch Pad B has a significantly higher boil off rate that the liquid hydrogen storage tank at Launch Pad A. This research looks at various calculations concerning the at Launch Pad B in an attempt to develop a solution to the excess boil off rate. We will look at Perlite levels inside the tank, Boil off rates, conductive heat transfer, and radiant heat transfer through the tank. As a conclusion to the research, we will model the effects of placing an external insulation to the tank in order to reduce the boil off rate and increase the economic efficiency of the liquid hydrogen storage tanks.

[Analysis of the distribution of VOCs concentration field with oil static breathing loss in internal floating roof tank].

PubMed

Wu, Hong-Zhang; Huang, Wei-Qiu; Yang, Guang; Zhao, Chen-Lu; Wang, Ying-Xia; Cai, Dao-Fei

2013-12-01

Internal floating roof tank has the advantages of external floating roof tank and fixed roof tank and has its own evaporation loss properties. The influences of volatile organic compounds (VOCs) distribution gradient, molecular diffusion, thermal diffusion and forced convection on the evaporation loss of oil were studied in the space of the homemade platform of an internal floating roof tank. The results showed that thermal diffusion with temperature change was the main cause for the static loss in the internal floating roof tank. On this basis, there were some measures for reduction of the evaporation loss and formulas to calculate the evaporation loss of the internal floating roof tank in this research.

Flight control augmentation for AFT CG launch vehicles

NASA Technical Reports Server (NTRS)

Barret, Chris

1996-01-01

The Space Shuttle was only the first step in achieving routine access to space. Recently, the NASA Marshall Space Flight Center (MSFC) has been studying a whole spectrum of new launch vehicles (L/V's) for space transportation. Some of these could transport components of the Space Station to orbit, and some could take us to Mars and beyond to boldly expand our frontiers of knowledge. In all our future launch vehicle (L/V) designs, decreasing the structural weight will always be of great concern. This is tantamount to increased payload capability, which in turn means reduced cost-per-pound to orbit. One very significant increase in payload capability has been defined. In a L/V recently studied at MSFC it has been shown that a sizable weight savings can be realized by a rearrangement of the internal propellant tanks. Studies have been conducted both at MSFC and at Martin Marietta Corporation, maker of the Space Shuttle External Tank (ET) which show that a very substantial weight can be saved by inverting the relative positions of the liquid hydrogen (LH2) and the liquid oxygen (LOX) propellant tanks in a particular L/V studied. As the vehicle sits on the launch pad, in the conventional configuration the heavier LOX tank is located on top of the lighter LH2. This requires a heavy structural member between the two tanks to prevent the lighter LH2 tank from being crushed. This configuration also requires large, long, and even drag producing LOX feed lines running the length of the vehicle on the exterior fuselage. If the relative position of the propellant tanks is inverted, both the heavy structural separation member and the long LOX feed lines could be deleted. While the structures community at MSFC was elated with this finding, the LOX tank aft configuration gave the vehicle an aft center-of-gravity (cg) location which surfaced controllability concerns. In the conventional configuration the L/V is controlled in the ascent trajectory by the gimballing of its rocket engines. Studies have been conducted at MSFC which showed that the resulting aft cg configured L/V would not be adequately controllable with the engine gimballing alone.

Single bi-temperature thermal storage tank for application in solar thermal plant

DOEpatents

Litwin, Robert Zachary; Wait, David; Lancet, Robert T.

2017-05-23

Thermocline storage tanks for solar power systems are disclosed. A thermocline region is provided between hot and cold storage regions of a fluid within the storage tank cavity. One example storage tank includes spaced apart baffles fixed relative to the tank and arranged within the thermocline region to substantially physically separate the cavity into hot and cold storage regions. In another example, a flexible baffle separated the hot and cold storage regions and deflects as the thermocline region shifts to accommodate changing hot and cold volumes. In yet another example, a controller is configured to move a baffle within the thermocline region in response to flow rates from hot and cold pumps, which are used to pump the fluid.

46 CFR 38.05-3 - Design and construction of pressure vessel type cargo tanks-TB/ALL.

Code of Federal Regulations, 2013 CFR

2013-10-01

... subjected to external loads. Consideration shall also be given to excessive loads that can be imposed on the tanks by their support due to static and dynamic forces under operating conditions or during testing...

46 CFR 38.05-3 - Design and construction of pressure vessel type cargo tanks-TB/ALL.

Code of Federal Regulations, 2011 CFR

2011-10-01

... subjected to external loads. Consideration shall also be given to excessive loads that can be imposed on the tanks by their support due to static and dynamic forces under operating conditions or during testing...

46 CFR 38.05-3 - Design and construction of pressure vessel type cargo tanks-TB/ALL.

Code of Federal Regulations, 2014 CFR

2014-10-01

... subjected to external loads. Consideration shall also be given to excessive loads that can be imposed on the tanks by their support due to static and dynamic forces under operating conditions or during testing...

46 CFR 38.05-3 - Design and construction of pressure vessel type cargo tanks-TB/ALL.

Code of Federal Regulations, 2012 CFR

2012-10-01

... subjected to external loads. Consideration shall also be given to excessive loads that can be imposed on the tanks by their support due to static and dynamic forces under operating conditions or during testing...

40 CFR 60.281 - Definitions.

Code of Federal Regulations, 2011 CFR

2011-07-01

... wood in white liquor, and associated flash tank(s), blow tank(s), chip steamer(s), and condenser(s). (e... condenser(s) and hotwell(s) used to concentrate the spent cooking liquid that is separated from the pulp... calcium oxide. (o) Condensate stripper system means a column, and associated condensers, used to strip...

46 CFR 151.13-5 - Cargo segregation-tanks.

Code of Federal Regulations, 2010 CFR

2010-10-01

... CARRYING BULK LIQUID HAZARDOUS MATERIAL CARGOES Cargo Segregation § 151.13-5 Cargo segregation—tanks. (a... design. (2) Segregation of cargo space from machinery spaces and other spaces which have or could have a... separating medium. ii=Double bulkhead, required. Cofferdam, empty tank, pumproom, tank with Grade E Liquid...

46 CFR 151.13-5 - Cargo segregation-tanks.

Code of Federal Regulations, 2011 CFR

2011-10-01

... CARRYING BULK LIQUID HAZARDOUS MATERIAL CARGOES Cargo Segregation § 151.13-5 Cargo segregation—tanks. (a... design. (2) Segregation of cargo space from machinery spaces and other spaces which have or could have a... separating medium. ii=Double bulkhead, required. Cofferdam, empty tank, pumproom, tank with Grade E Liquid...

46 CFR 151.13-5 - Cargo segregation-tanks.

Code of Federal Regulations, 2012 CFR

2012-10-01

... CARRYING BULK LIQUID HAZARDOUS MATERIAL CARGOES Cargo Segregation § 151.13-5 Cargo segregation—tanks. (a... design. (2) Segregation of cargo space from machinery spaces and other spaces which have or could have a... separating medium. ii=Double bulkhead, required. Cofferdam, empty tank, pumproom, tank with Grade E Liquid...

27 CFR 22.132 - Deposit in storage tanks.

Code of Federal Regulations, 2010 CFR

2010-04-01

... 27 Alcohol, Tobacco Products and Firearms 1 2010-04-01 2010-04-01 false Deposit in storage tanks....132 Deposit in storage tanks. (a) Recovered alcohol shall be accumulated and kept in separate storage...) Recovered alcohol may be removed from storage tanks for packaging and shipment to a distilled spirits plant...

27 CFR 22.132 - Deposit in storage tanks.

Code of Federal Regulations, 2012 CFR

2012-04-01

... 27 Alcohol, Tobacco Products and Firearms 1 2012-04-01 2012-04-01 false Deposit in storage tanks....132 Deposit in storage tanks. (a) Recovered alcohol shall be accumulated and kept in separate storage...) Recovered alcohol may be removed from storage tanks for packaging and shipment to a distilled spirits plant...

Method and apparatus for production of subsea hydrocarbon formations

DOEpatents

Blandford, J.W.

1995-01-17

A system for controlling, separating, processing and exporting well fluids produced from subsea hydrocarbon formations is disclosed. The subsea well tender system includes a surface buoy supporting one or more decks above the water surface for accommodating equipment to process oil, gas and water recovered from the subsea hydrocarbon formation. The surface buoy includes a surface-piercing central flotation column connected to one or more external flotation tanks located below the water surface. The surface buoy is secured to the sea bed by one or more tendons which are anchored to a foundation with piles imbedded in the sea bed. The system accommodates multiple versions on the surface buoy configuration. 20 figures.

KSC-05PD-0565

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. In the Vehicle Assembly Building at NASAs Kennedy Space Center, a digital still camera has been mounted in the External Tank (ET) umbilical well on the aft end of Space Shuttle Discovery. The camera is being used to obtain and downlink high-resolution images of the disconnect point on the ET following ET separation from the orbiter after launch. The Kodak camera will record 24 images, at one frame per 1.5 seconds, on a flash memory card. After orbital insertion, the crew will transfer the images from the memory card to a laptop computer. The files will then be downloaded through the Ku-band system to the Mission Control Center in Houston for analysis.

KSC-05PD-0564

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. In the Vehicle Assembly Building at NASAs Kennedy Space Center, a worker mounts a digital still camera in the External Tank (ET) umbilical well on the aft end of Space Shuttle Discovery. The camera is being used to obtain and downlink high-resolution images of the disconnect point on the ET following the ET separation from the orbiter after launch. The Kodak camera will record 24 images, at one frame per 1.5 seconds, on a flash memory card. After orbital insertion, the crew will transfer the images from the memory card to a laptop computer. The files will then be downloaded through the Ku-band system to the Mission Control Center in Houston for analysis.

KSC-05PD-0561

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. In the Vehicle Assembly Building at NASAs Kennedy Space Center, workers prepare a digital still camera they will mount in the External Tank (ET) umbilical well on the aft end of Space Shuttle Discovery. The camera is being used to obtain and downlink high-resolution images of the disconnect point on the ET following its separation from the orbiter after launch. The Kodak camera will record 24 images, at one frame per 1.5 seconds, on a flash memory card. After orbital insertion, the crew will transfer the images from the memory card to a laptop computer. The files will then be downloaded through the Ku-band system to the Mission Control Center in Houston for analysis.

KSC-05PD-0563

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. In the Vehicle Assembly Building at NASAs Kennedy Space Center, workers prepare a digital still camera they will mount in the External Tank (ET) umbilical well on the aft end of Space Shuttle Discovery. The camera is being used to obtain and downlink high-resolution images of the disconnect point on the ET following the ET separation from the orbiter after launch. The Kodak camera will record 24 images, at one frame per 1.5 seconds, on a flash memory card. After orbital insertion, the crew will transfer the images from the memory card to a laptop computer. The files will then be downloaded through the Ku-band system to the Mission Control Center in Houston for analysis.

Investigation of thermoelastic stresses induced at high altitudes on aircraft external fuel tanks

NASA Astrophysics Data System (ADS)

Mousseau, Stephanie Lynn Steber

As composite technology has grown over the past several decades, the use of composite materials in military applications has become more feasible and widely accepted. Although composite materials provide many benefits, including strength optimization and reduced weight, damage and repair of these materials creates an additional challenge, especially when operating in a marine environment, such as on a carrier deck. This is evident within the Navy, as excessive damage often leads to the scrapping of F/A-18 External Fuel Tanks. This damage comes in many forms, the most elusive of which is delamination. Often the delamination found on the tanks is beyond repairable limits and the cause unknown, making it difficult to predict and prevent. The purpose of this investigation was to study the structure of the Navy's 330 gallon External Fuel Tanks and investigate one potential cause of delamination, stresses induced at high altitudes by cold temperatures. A stress analysis was completed using finite element software, and validation of the model was accomplished through testing of a scale model specimen. Due to the difficulties in modeling and predicting delamination, such as unknown presence of voids and understanding failure criteria, delamination was not modeled in Abaqus, rather stresses were observed and characteristics were studied to understand the potential for delamination within the layup. In addition, studies were performed to understand the effect of material properties and layup sequence on the stress distribution within the tank. Alternative design solutions are presented which could reduce the radial stresses within the tank, and recommendations are made for further study to understand the trade-offs between stress, cost, and manufacturability.

40 CFR 61.131 - Definitions.

Code of Federal Regulations, 2011 CFR

2011-07-01

... circulation tank means any vessel that functions to store or contain flushing liquor that is separated from... that functions to condense benzene-containing vapors. Light-oil decanter means any vessel, tank, or other type of device in the light-oil recovery operation that functions to separate light oil from water...

40 CFR 61.131 - Definitions.

Code of Federal Regulations, 2012 CFR

2012-07-01

... circulation tank means any vessel that functions to store or contain flushing liquor that is separated from... that functions to condense benzene-containing vapors. Light-oil decanter means any vessel, tank, or other type of device in the light-oil recovery operation that functions to separate light oil from water...

40 CFR 61.131 - Definitions.

Code of Federal Regulations, 2013 CFR

2013-07-01

... circulation tank means any vessel that functions to store or contain flushing liquor that is separated from... that functions to condense benzene-containing vapors. Light-oil decanter means any vessel, tank, or other type of device in the light-oil recovery operation that functions to separate light oil from water...

KSC-2009-2277

NASA Image and Video Library

2009-03-24

CAPE CANAVERAL, Fla. – In the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida, space shuttle Atlantis is moved toward High Bay 3 where the top of its external fuel tank can be seen. In the bay, the shuttle will be lowered and mated with the external tank and solid rocket boosters on the mobile launcher platform. After additional preparations are made, the shuttle will be rolled out to Launch Pad 39A for a targeted launch on May 12 on the STS-125 mission to service NASA's Hubble Space Telescope. Photo credit: NASA/Kim Shiflett

Utilization of Space Shuttle External Tank materials by melting and powder metallurgy

NASA Technical Reports Server (NTRS)

Chern, T. S.

1985-01-01

The Crucible Melt Extraction Process was demonstrated to convert scraps of aluminum alloy 2219, used in the Space Shuttle External Tank, into fibers. The cast fibers were then consolidated by cold welding. The X-ray diffraction test of the cast fibers was done to examine the crystallinity and oxide content of the fibers. The compressive stress-strain behavior of the consolidated materials was also examined. Two conceptual schemes which would adapt the as-developed Crucible Melt Extraction Process to the microgravity condition in space were finally proposed.

Nondestructive Evaluation of Foam Insulation for the External Tank Return to Flight

NASA Technical Reports Server (NTRS)

Walker, James L.; Richter, Joel D.

2006-01-01

Nondestructive evaluation methods have been developed to identify defects in the foam thermal protection system (TPS) of the Space Shuttle External Tank (ET). Terahertz imaging and backscatter radiography have been brought from prototype lab systems to production hardened inspection tools in just a few years. These methods have been demonstrated to be capable of detecting void type defects under many inches of foam which, if not repaired, could lead to detrimental foam loss. The evolution of these methods from lab tools to implementation on the ET will be discussed.

Utilization of space shuttle external tank materials by melting and powder metallurgy

NASA Astrophysics Data System (ADS)

Chern, Terry S.

The Crucible Melt Extraction Process was demonstrated to convert scraps of aluminum alloy 2219, used in the Space Shuttle External Tank, into fibers. The cast fibers were then consolidated by cold welding. The X-ray diffraction test of the cast fibers was done to examine the crystallinity and oxide content of the fibers. The compressive stress-strain behavior of the consolidated materials was also examined. Two conceptual schemes which would adapt the as-developed Crucible Melt Extraction Process to the microgravity condition in space were finally proposed.

KENNEDY SPACE CENTER, FLA. - A camera is installed on the aft skirt of a solid rocket booster in preparation for a vibration test of the Mobile Launcher Platform with SRBs and external tank mounted. The MLP will roll from one bay to another in the Vehicle Assembly Building.

NASA Image and Video Library

2003-11-06

KENNEDY SPACE CENTER, FLA. - A camera is installed on the aft skirt of a solid rocket booster in preparation for a vibration test of the Mobile Launcher Platform with SRBs and external tank mounted. The MLP will roll from one bay to another in the Vehicle Assembly Building.

KSC-2010-4793

NASA Image and Video Library

2010-09-20

NEW ORLEANS -- To commemorate the history of the Space Shuttle Program's last external fuel tank, its intertank door is emblazoned with an ET-122 insignia. The external tank will travel 900 miles by sea from NASA's Michoud Assembly Facility in New Orleans to NASA's Kennedy Space Center in Florida secured aboard the Pegasus Barge, offloaded and moved to Kennedy's Vehicle Assembly Building where it will be integrated to space shuttle Endeavour for the STS-134 mission to the International Space Station. The tank, which is the largest element of the space shuttle stack, was damaged during Hurricane Katrina in August 2005 and restored to flight configuration by Lockheed Martin Space Systems Company employees. STS-134, targeted to launch Feb. 2011, currently is scheduled to be the last mission in the Space Shuttle Program. Photo credit: NASA/Kim Shiflett

KSC-2010-5852

NASA Image and Video Library

2010-12-14

CAPE CANAVERAL, Fla. -- Space shuttle Discovery's external fuel tank is outfitted with approximately 89 strain gauges, thermocouples and wiring in preparation for a tanking test no earlier than Dec. 17 on Launch Pad 39A at NASA's Kennedy Space Center in Florida. During the test, engineers will monitor what happens to 21-foot long, U-shaped aluminum brackets, called stringers, located at the external tank's intertank area, as well as the newly replaced ground umbilical carrier plate (GUCP), during the loading of cryogenic propellants. Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at GUCP. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Jim Grossmann

KSC-2010-5848

NASA Image and Video Library

2010-12-14

CAPE CANAVERAL, Fla. -- Space shuttle Discovery's external fuel tank is outfitted with approximately 89 strain gauges, thermocouples and wiring in preparation for a tanking test no earlier than Dec. 17 on Launch Pad 39A at NASA's Kennedy Space Center in Florida. During the test, engineers will monitor what happens to 21-foot long, U-shaped aluminum brackets, called stringers, located at the external tank's intertank area, as well as the newly replaced ground umbilical carrier plate (GUCP), during the loading of cryogenic propellants. Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at GUCP. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Jim Grossmann

KSC-2010-5851

NASA Image and Video Library

2010-12-14

CAPE CANAVERAL, Fla. -- Technicians outfit space shuttle Discovery's external fuel tank with approximately 89 strain gauges, thermocouples and wiring in preparation for a tanking test no earlier than Dec. 17 on Launch Pad 39A at NASA's Kennedy Space Center in Florida. During the test, engineers will monitor what happens to 21-foot long, U-shaped aluminum brackets, called stringers, located at the external tank's intertank area, as well as the newly replaced ground umbilical carrier plate (GUCP), during the loading of cryogenic propellants. Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at GUCP. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Jim Grossmann

KSC-2010-5849

NASA Image and Video Library

2010-12-14

CAPE CANAVERAL, Fla. -- Technicians outfit space shuttle Discovery's external fuel tank with approximately 89 strain gauges, thermocouples and wiring in preparation for a tanking test no earlier than Dec. 17 on Launch Pad 39A at NASA's Kennedy Space Center in Florida. During the test, engineers will monitor what happens to 21-foot long, U-shaped aluminum brackets, called stringers, located at the external tank's intertank area, as well as the newly replaced ground umbilical carrier plate (GUCP), during the loading of cryogenic propellants. Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at GUCP. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Jim Grossmann

KSC-2010-5855

NASA Image and Video Library

2010-12-14

CAPE CANAVERAL, Fla. -- Technicians outfit space shuttle Discovery's external fuel tank with approximately 89 strain gauges, thermocouples and wiring in preparation for a tanking test no earlier than Dec. 17 on Launch Pad 39A at NASA's Kennedy Space Center in Florida. During the test, engineers will monitor what happens to 21-foot long, U-shaped aluminum brackets, called stringers, located at the external tank's intertank area, as well as the newly replaced ground umbilical carrier plate (GUCP), during the loading of cryogenic propellants. Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at GUCP. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Jim Grossmann

KSC-2010-5854

NASA Image and Video Library

2010-12-14

CAPE CANAVERAL, Fla. -- Technicians outfit space shuttle Discovery's external fuel tank with approximately 89 strain gauges, thermocouples and wiring in preparation for a tanking test no earlier than Dec. 17 on Launch Pad 39A at NASA's Kennedy Space Center in Florida. During the test, engineers will monitor what happens to 21-foot long, U-shaped aluminum brackets, called stringers, located at the external tank's intertank area, as well as the newly replaced ground umbilical carrier plate (GUCP), during the loading of cryogenic propellants. Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at GUCP. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Jim Grossmann

KSC-2010-5853

NASA Image and Video Library

2010-12-14

CAPE CANAVERAL, Fla. -- Space shuttle Discovery's external fuel tank is outfitted with approximately 89 strain gauges, thermocouples and wiring in preparation for a tanking test no earlier than Dec. 17 on Launch Pad 39A at NASA's Kennedy Space Center in Florida. During the test, engineers will monitor what happens to 21-foot long, U-shaped aluminum brackets, called stringers, located at the external tank's intertank area, as well as the newly replaced ground umbilical carrier plate (GUCP), during the loading of cryogenic propellants. Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at GUCP. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Jim Grossmann

KSC-2010-5850

NASA Image and Video Library

2010-12-14

CAPE CANAVERAL, Fla. -- Technicians outfit space shuttle Discovery's external fuel tank with approximately 89 strain gauges, thermocouples and wiring in preparation for a tanking test no earlier than Dec. 17 on Launch Pad 39A at NASA's Kennedy Space Center in Florida. During the test, engineers will monitor what happens to 21-foot long, U-shaped aluminum brackets, called stringers, located at the external tank's intertank area, as well as the newly replaced ground umbilical carrier plate (GUCP), during the loading of cryogenic propellants. Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at GUCP. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Jim Grossmann

KSC-07pd2371

NASA Image and Video Library

2007-08-24

KENNEDY SPACE CENTER, FLA. -- The super lightweight ablator, or SLA, cork insulation has been removed from the external tank and a United Space Alliance external tank technician sands off the residue from the LO2 feed line bracket. The BX265 foam insulation will later be reapplied without the SLA. The tank is scheduled to fly on Space Shuttle Discovery in October 2007 on mission STS-120. Discovery's crew will add the module Harmony that will serve as a port for installing additional international laboratories. Harmony will be the first expansion of the living and working space on the complex since the Russian Pirs airlock was installed in 2001. The mission also will move the first set of solar arrays installed on the station to a permanent location on the complex and redeploy them. Photo credit: NASA/Jim Grossmann

KSC-99pp0518

NASA Image and Video Library

1999-05-12

At Launch pad 39B, Mike Barber, with United Space Alliance safety, points to one of the holes caused by hail on Space Shuttle Discovery's external tank (ET). Workers are investigating the damage and potential problems for launch posed by ice forming in the holes, which may number as many as 150 over the entire tank. The average size of the holes is one-half inch in diameter and one-tenth inch deep. The external tank contains the liquid hydrogen fuel and liquid oxygen oxidizer and supplies them under pressure to the three space shuttle main engines in the orbiter during liftoff and ascent. The ET thermal protection system consists of sprayed-on foam insulation. The Shuttle Discovery is targeted for launch of mission STS-96 on May 20 at 9:32 a.m

KSC-99pp0514

NASA Image and Video Library

1999-05-12

At Launch Pad 39B, the top of the external tank (ET) mated to Space Shuttle Discovery is dotted with nearly a dozen visible dings from recent hail storms. Workers are investigating the damage and potential problems for launch posed by ice forming in the holes, which may number as many as 150 over the entire tank. The average size of the dings is one-half inch in diameter and one-tenth inch deep. The external tank contains the liquid hydrogen fuel and liquid oxygen oxidizer and supplies them under pressure to the three space shuttle main engines in the orbiter during liftoff and ascent. The ET thermal protection system consists of sprayed-on foam insulation. The Shuttle Discovery is targeted for launch of mission STS-96 on May 20 at 9:32 a.m

KSC-99pp0515

NASA Image and Video Library

1999-05-12

A hole, created by recent hail storms, is identified as number one on the surface of the external tank (ET) mated to Space Shuttle Discovery at Launch Pad 39B. Workers are investigating the damage and potential problems for launch posed by ice forming in the holes, which may number as many as 150 over the entire tank. The average size of the holes is one-half inch in diameter and one-tenth inch deep. The external tank contains the liquid hydrogen fuel and liquid oxygen oxidizer and supplies them under pressure to the three space shuttle main engines in the orbiter during liftoff and ascent. The ET thermal protection system consists of sprayed-on foam insulation. The Shuttle Discovery is targeted for launch of mission STS-96 on May 20 at 9:32 a.m

KSC-99pp0516

NASA Image and Video Library

1999-05-12

A hole, created by recent hail storms, is identified as number two on the surface of the external tank (ET) mated to Space Shuttle Discovery at Launch Pad 39B. Workers are investigating the damage and potential problems for launch posed by ice forming in the holes, which may number as many as 150 over the entire tank. The average size of the holes is one-half inch in diameter and one-tenth inch deep. The external tank contains the liquid hydrogen fuel and liquid oxygen oxidizer and supplies them under pressure to the three space shuttle main engines in the orbiter during liftoff and ascent. The ET thermal protection system consists of sprayed-on foam insulation. The Shuttle Discovery is targeted for launch of mission STS-96 on May 20 at 9:32 a.m

TANK ISSUES: DESIGN AND PLACEMENT OF FLOATING LIQUID MONITORING WELLS

EPA Science Inventory

Liquid product monitoring is the predominant method of external leak detection where the water table is within the zone of excavation. his paper discusses the use of liquid product monitors at new and old tank installations for detecting leaks from underground hydrocarbon storage...

Experimental and numerical investigation of one and two phase natural convection in storage tanks

NASA Astrophysics Data System (ADS)

Aszodi, A.; Krepper, E.; Prasser, H.-M.

Experiments were performed to investigate heating up processes of fluids in storage tanks under the influence of an external heat source. As a consequence of an external fire, the heat-up of the inventory may lead to the evaporation of the liquid and to release of significant quantities of dangerous gases into the environment. Several tests were performed both with heating from the bottom and with heating from the side walls. In recent tests in addition to thermocouples, the tank was equipped with needle probes for measuring of the local void fraction. The paper presents experimental and numerical investigations of single and two phase heating up processes of tanks with side wall heating. The measurement of the temperature and of the void fraction makes interesting phenomena evident, which could be explained by an own 2D model. The gained experimental results may be used for the validation of boiling models in 3D CFD codes.

Thermodynamic aspects of an LNG tank in fire and experimental validation

NASA Astrophysics Data System (ADS)

Hulsbosch-Dam, Corina; Atli-Veltin, Bilim; Kamperveen, Jerry; Velthuis, Han; Reinders, Johan; Spruijt, Mark; Vredeveldt, Lex

Mechanical behaviour of a Liquefied Natural Gas (LNG) tank and the thermodynamic behaviour of its containment under extreme heat load - for instance when subjected to external fire source as might occur during an accident - are extremely important when addressing safety concerns. In a scenario where external fire is present and consequent release of LNG from pressure relief valves (PRV) has occurred, escalation of the fire might occur causing difficulty for the fire response teams to approach the tank or to secure the perimeter. If the duration of the tank exposure to fire is known, the PRV opening time can be estimated based on the thermodynamic calculations. In this paper, such an accidental scenario is considered, relevant thermodynamic equations are derived and presented. Moreover, an experiment is performed with liquid nitrogen and the results are compared to the analytical ones. The analytical results match very well with the experimental observations. The resulting analytical models are suitable to be applied to other cryogenic liquids.

KSC-2010-5886

NASA Image and Video Library

2010-12-17

CAPE CANAVERAL, Fla. -- Shuttle Launch Director Mike Leinbach monitors space shuttle Discovery's external fuel tank as it is loaded with more than 535,000 gallons of cryogenic propellants from his console in the Launch Control Center at NASA's Kennedy Space Center in Florida. During today's tanking test, the team is paying particular attention to the external tank's ribbed intertank region. Beginning tomorrow, engineers will evaluate data on 21-foot-long, U-shaped aluminum brackets, called stringers, and the newly replaced ground umbilical carrier plate (GUCP). Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at the GUCP. In order to perform additional analysis on the tank, Discovery will be rolled back to the Vehicle Assembly Building, a move that is planned for next week. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Cory Huston

KSC-06pd0599

NASA Image and Video Library

2006-04-11

KENNEDY SPACE CENTER, FLA. - Inside the Vehicle Assembly Building at NASA's Kennedy Space Center, a worker watches external tank number 119 as it is being lifted from the checkout cell. The tank will be placed horizontally on the transporter in the transfer aisle. Once in the transfer aisle, technicians will reapply the thermal protection system foam that was removed in order to replace the tank's four liquid hydrogen engine cutoff sensors. The tank is being prepared to launch Space Shuttle Discovery on mission STS-121 in July. Photo credit: NASA/Cory Huston

ANNUAL RADIOACTIVE WASTE TANK INSPECTION PROGRAM- 2007

DOE Office of Scientific and Technical Information (OSTI.GOV)

West, B; Ruel Waltz, R

2008-06-05

Aqueous radioactive wastes from Savannah River Site (SRS) separations and vitrification processes are contained in large underground carbon steel tanks. The 2007 inspection program revealed that the structural integrity and waste confinement capability of the Savannah River Site waste tanks were maintained. A very small amount of material had seeped from Tank 12 from a previously identified leaksite. The material observed had dried on the tank wall and did not reach the annulus floor. A total of 5945 photographs were made and 1221 visual and video inspections were performed during 2007. Additionally, ultrasonic testing was performed on four Waste Tanksmore » (15, 36, 37 and 38) in accordance with approved inspection plans that met the requirements of WSRC-TR-2002- 00061, Revision 2 'In-Service Inspection Program for High Level Waste Tanks'. The Ultrasonic Testing (UT) In-Service Inspections (ISI) are documented in a separate report that is prepared by the ISI programmatic Level III UT Analyst. Tanks 15, 36, 37 and 38 are documented in 'Tank Inspection NDE Results for Fiscal Year 2007'; WSRC-TR-2007-00064.« less

Preliminary survey of separations technology applicable to the pretreatment of Hanford tank waste (1992--1993)

DOE Office of Scientific and Technical Information (OSTI.GOV)

Lawrence, W.E.; Kurath, D.E.

1994-04-01

The US Department of Energy has established the Tank Waste Remediation System (TWRS) to manage and dispose of radioactive wastes stored at the Hanford Site. Within this program are evaluations of pretreatment system alternatives through literature reviews. The information in this report was collected as part of this project at Pacific Northwest Laboratory. A preliminary survey of literature on separations recently entered into the Hanford electronic databases (1992--1993) that have the potential for pretreatment of Hanford tank waste was conducted. Separation processes that can assist in the removal of actinides (uranium, plutonium, americium), lanthanides, barium, {sup 137}Cs, {sup 90}Sr,{sup 129more » }I, {sup 63}Ni, and {sup 99}Tc were evaluated. Separation processes of interest were identified through literature searches, journal reviews, and participation in separation technology conferences. This report contains brief descriptions of the potential separation processes, the extent and/or selectivity of the separation, the experimental conditions, and observations. Information was collected on both national and international separation studies to provide a global perspective on recent research efforts.« less

KSC-07pd0837

NASA Image and Video Library

2007-04-06

KENNEDY SPACE CENTER, FLA. -- After passing through the Banana River bridge, the Pegasus barge, with its cargo of the external tank prepared for mission STS-118, is towed upriver to the turn basin near the Vehicle Assembly Building. There the tank will be offloaded and moved to the VAB. Photo credit: Jack Pfaller

KSC-07pd0836

NASA Image and Video Library

2007-04-06

KENNEDY SPACE CENTER, FLA. -- The Pegasus barge, with its cargo of the external tank prepared for mission STS-118, moves through the upraised Banana River bridge. The barge is being towed to the turn basin near the Vehicle Assembly Building where the tank will be offloaded and moved to the VAB. Photo credit: Jack Pfaller

KSC-07pd0835

NASA Image and Video Library

2007-04-06

KENNEDY SPACE CENTER, FLA. -- The Pegasus barge, with its cargo of the external tank prepared for mission STS-118, moves toward the upraised Banana River bridge. The barge is being towed to the turn basin near the Vehicle Assembly Building where the tank will be offloaded and moved to the VAB. Photo credit: Jack Pfaller

Thermal Energy Briefing with FPL

NASA Image and Video Library

2017-02-17

Bart Gaetjens, Florida Power & Light's FPL area external affairs manager, addresses the news media and NASA Social about the new Thermal Energy Storage (TES) tank Feb. 17. The TES tank works like a giant battery and is saving the center utility cost. These savings will be applied to new sustainable projects at Kennedy.

Assessment of the hydrogen external tank pressure decay anomaly on Space Transportation System (STS) 51-L

NASA Technical Reports Server (NTRS)

Buckley, Theresa M.

1988-01-01

Following the Challenger tragedy, an evaluation of the integrated main propulsion system flight data revealed a premature decay in the hydrogen external tank ullage pressure. A reconstruction of predicted ullage pressure versus time indicated an inconsistency between predicted and measured ullage pressure starting at approximately 65.5 seconds into the flight and reaching a maximum value between 72 and 72.9 seconds. This discrepancy could have been caused by a hydrogen gas leak or by a liquied hydrogen leak that occurred either in the pressurization system or in the external tank. The corresponding leak rates over the time interval from 65.5 to 72.9 seconds were estimated to range from 0.28 kg/s (0.62 lbm/s) + or - 41 percent to between 0.43 and 0.51kg/s (0.94 and 1.12lbs/s) + or - 1 percent for a gas leak and from 72.9 kg/s (160.5 lbs/s) + or - 41 percent to between 111.6 and 133.2 kg/s (245.8 and 293.3 lbs/s) + or - 1 percent for a liquid leak. No speculation is made to ascertain whether the leak is liquid or gas, as this cannot be determined from the analysis performed. Four structural failures in the hydrogen external tank were considered to explain the leak rates. A break in the 5-cm (2 in) pressurization line, in the 13-cm (5 in) vent line, or in the 43-cm (17 in) feedline is not likely. A break in the 10-cm (4 in) recirculation line with a larger structural failure occurring in the 72 to 73-second time period, the time of the visibly identified premature pressure decay, does seem plausible and the most likely of the four modes considered. These modes are not all-inclusive and do not preclude the possibility of a leak elsewhere in the tank.

46 CFR 154.195 - Aluminum cargo tank: Steel enclosure.

Code of Federal Regulations, 2012 CFR

2012-10-01

... Equipment Hull Structure § 154.195 Aluminum cargo tank: Steel enclosure. (a) An aluminum cargo tank and its dome must be enclosed by the vessel's hull structure or a separate steel cover. (b) The steel cover for... 46 Shipping 5 2012-10-01 2012-10-01 false Aluminum cargo tank: Steel enclosure. 154.195 Section...

46 CFR 154.195 - Aluminum cargo tank: Steel enclosure.

Code of Federal Regulations, 2013 CFR

2013-10-01

... Equipment Hull Structure § 154.195 Aluminum cargo tank: Steel enclosure. (a) An aluminum cargo tank and its dome must be enclosed by the vessel's hull structure or a separate steel cover. (b) The steel cover for... 46 Shipping 5 2013-10-01 2013-10-01 false Aluminum cargo tank: Steel enclosure. 154.195 Section...

46 CFR 154.195 - Aluminum cargo tank: Steel enclosure.

Code of Federal Regulations, 2010 CFR

2010-10-01

... Equipment Hull Structure § 154.195 Aluminum cargo tank: Steel enclosure. (a) An aluminum cargo tank and its dome must be enclosed by the vessel's hull structure or a separate steel cover. (b) The steel cover for... 46 Shipping 5 2010-10-01 2010-10-01 false Aluminum cargo tank: Steel enclosure. 154.195 Section...

46 CFR 154.195 - Aluminum cargo tank: Steel enclosure.

Code of Federal Regulations, 2014 CFR

2014-10-01

... Equipment Hull Structure § 154.195 Aluminum cargo tank: Steel enclosure. (a) An aluminum cargo tank and its dome must be enclosed by the vessel's hull structure or a separate steel cover. (b) The steel cover for... 46 Shipping 5 2014-10-01 2014-10-01 false Aluminum cargo tank: Steel enclosure. 154.195 Section...

46 CFR 154.195 - Aluminum cargo tank: Steel enclosure.

Code of Federal Regulations, 2011 CFR

2011-10-01

... Equipment Hull Structure § 154.195 Aluminum cargo tank: Steel enclosure. (a) An aluminum cargo tank and its dome must be enclosed by the vessel's hull structure or a separate steel cover. (b) The steel cover for... 46 Shipping 5 2011-10-01 2011-10-01 false Aluminum cargo tank: Steel enclosure. 154.195 Section...

Results from the Water Flow Test of the Tank 37 Backflush Valve

DOE Office of Scientific and Technical Information (OSTI.GOV)

Fowley, M.D.

2002-11-01

A flow test was conducted in the Thermal Fluids Lab with the Tank 37 Backflush Valve to determine the pressure drop of water flow through the material transfer port. The flow rate was varied from 0 to 100 gpm. The pressure drop through the Backflush Valve for flow rates of 20 and 70 gpm was determined to be 0.18 and 1.77 feet of H2O, respectively. An equivalent length of the Backflush Valve was derived from the flow test data. The equivalent length was used in a head loss calculation for the Tank 37 Gravity Drain Line. The calculation estimated themore » flow rate that would fill the line up to the Separator Tank, and the additional flow rate that would fill the Separator Tank. The viscosity of the fluid used in the calculation was 12 centipoise. Two specific gravities were investigated, 1.4 and 1.8. The Gravity Drain Line was assumed to be clean, unobstructed stainless steel pipe. The flow rate that would fill the line up to the Separator Tank was 73 and 75 gpm for the 1.4 or 1.8 specific gravity fluids, respectively. The flow rate that would fill the Separator Tank was 96 and 100 gpm for the 1.4 or 1.8 specific gravity fluids, respectively. These results indicate that concentrate will not back up into the Separator Tank during evaporator normal operation, 15-25 gpm, or pot liftout, 70 gpm. A noteworthy observation during the flow test was water pouring from the holes in the catheterization tube. Water poured from the holes at 25 gpm and above. Data from the water flow test indicates that at 25 gpm the pressure drop through the Backflush Valve is 0.26 ft of H2O. A concentrate with a specific gravity of 1.8 and a viscosity of 12 cp will produce the same pressure drop at 20 gpm. This implies that concentrate from the evaporator may spill out into the BFV riser during a transfer.« less

KSC-07pd2369

NASA Image and Video Library

2007-08-24

KENNEDY SPACE CENTER, FLA. -- A United Space Alliance external tank technician has completed the removal of a layer of BX265 foam insulation from the LO2 feed line bracket on the external tank. The BX265 foam insulation will later be reapplied without the super lightweight ablator, or SLA, cork insulation. The tank is scheduled to fly on Space Shuttle Discovery in October 2007 on mission STS-120. Discovery's crew will add the module Harmony that will serve as a port for installing additional international laboratories. Harmony will be the first expansion of the living and working space on the complex since the Russian Pirs airlock was installed in 2001. The mission also will move the first set of solar arrays installed on the station to a permanent location on the complex and redeploy them. Photo credit: NASA/Jim Grossmann

KSC-05PD-1177

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. At NASAs Kennedy Space Center, Space Shuttle Discovery, resting on the Mobile Launcher Platform, rolls into high bay 1 of the Vehicle Assembly Building (VAB). The Shuttle is being rolled back from Launch Pad 39B. It will be demated from its External Tank and lifted into the transfer aisle. On or about June 7, Discovery will be attached to its new tank and Solid Rocket Boosters, which are already in the VAB. Only the 15th rollback in Space Shuttle Program history, the 4.2- mile journey allows additional modifications to be made to the External Tank prior to a safe Return to Flight. Discovery is expected to be rolled back to the launch pad in mid-June for Return to Flight mission STS-114. The launch window extends from July 13 to July 31. [Photo courtesy of Scott Andrews

Ice/frost detection using millimeter wave radiometry. [space shuttle external tank

NASA Technical Reports Server (NTRS)

Gagliano, J. A.; Newton, J. M.; Davis, A. R.; Foster, M. L.

1981-01-01

A series of ice detection tests was performed on the shuttle external tank (ET) and on ET target samples using a 35/95 GHz instrumentation radiometer. Ice was formed using liquid nitrogen and water spray inside a test enclosure containing ET spray on foam insulation samples. During cryogenic fueling operations prior to the shuttle orbiter engine firing tests, ice was formed with freon and water over a one meter square section of the ET LOX tank. Data analysis was performed on the ice signatures, collected by the radiometer, using Georgia Tech computing facilities. Data analysis technique developed include: ice signature images of scanned ET target; pixel temperature contour plots; time correlation of target data with ice present versus no ice formation; and ice signature radiometric temperature statistical data, i.e., mean, variance, and standard deviation.

Waste Separations and Pretreatment Workshop report

DOE Office of Scientific and Technical Information (OSTI.GOV)

Cruse, J.M.; Harrington, R.A.; Quadrel, M.J.

1994-01-01

This document provides the minutes from the Waste Separations and Pretreatment Workshop sponsored by the Underground Storage Tank-Integrated Demonstration in Salt Lake City, Utah, February 3--5, 1993. The Efficient Separations and Processing-Integrated Program and the Hanford Site Tank Waste Remediation System were joint participants. This document provides the detailed minutes, including responses to questions asked, an attendance list, reproductions of the workshop presentations, and a revised chart showing technology development activities.

Wind tunnel tests of Space Shuttle external tank insulation material in the aerothermal tunnel at elevated (1440 deg F) total temperatures

NASA Technical Reports Server (NTRS)

Hartman, A. S.; Nutt, K. W.

1982-01-01

Tests of the space shuttle external tank foam insulation were conducted in the von Karman Gas Dynamics Facility Tunnel C. For these tests, Tunnel C was run at Mach 4 with a total temperature of 1440 F and a total pressure which varied from 30-100 psia. Cold wall heating rates were changed by varying the test article support wedge angle and by adding and removing a shock generator or a cylindrical protuberance. Selected results are presented to illustrate the test techniques and typical data obtained.

KENNEDY SPACE CENTER, FLA. - Workers in the Orbiter Processing Facility insert the liquid oxygen feedline for the 17-inch disconnect in the orbiter Discovery. The 17-inch liquid oxygen and liquid hydrogen disconnects provide the propellant feed interface from the external tank to the orbiter main propulsion system and the three Shuttle main engines.

NASA Image and Video Library

2003-11-11

KENNEDY SPACE CENTER, FLA. - Workers in the Orbiter Processing Facility insert the liquid oxygen feedline for the 17-inch disconnect in the orbiter Discovery. The 17-inch liquid oxygen and liquid hydrogen disconnects provide the propellant feed interface from the external tank to the orbiter main propulsion system and the three Shuttle main engines.

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, workers install the liquid oxygen feedline for the 17-inch disconnect on orbiter Discovery. The 17-inch liquid oxygen and liquid hydrogen disconnects provide the propellant feed interface from the external tank to the orbiter main propulsion system and the three Shuttle main engines.

NASA Image and Video Library

2003-11-11

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, workers install the liquid oxygen feedline for the 17-inch disconnect on orbiter Discovery. The 17-inch liquid oxygen and liquid hydrogen disconnects provide the propellant feed interface from the external tank to the orbiter main propulsion system and the three Shuttle main engines.

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, workers raise the liquid oxygen feedline for the 17-inch disconnect toward orbiter Discovery for installation. The 17-inch liquid oxygen and liquid hydrogen disconnects provide the propellant feed interface from the external tank to the orbiter main propulsion system and the three Shuttle main engines.

NASA Image and Video Library

2003-11-11

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, workers raise the liquid oxygen feedline for the 17-inch disconnect toward orbiter Discovery for installation. The 17-inch liquid oxygen and liquid hydrogen disconnects provide the propellant feed interface from the external tank to the orbiter main propulsion system and the three Shuttle main engines.

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, workers lift the liquid oxygen feedline for the 17-inch disconnect toward orbiter Discovery for installation. The 17-inch liquid oxygen and liquid hydrogen disconnects provide the propellant feed interface from the external tank to the orbiter main propulsion system and the three Shuttle main engines.

NASA Image and Video Library

2003-11-11

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, workers lift the liquid oxygen feedline for the 17-inch disconnect toward orbiter Discovery for installation. The 17-inch liquid oxygen and liquid hydrogen disconnects provide the propellant feed interface from the external tank to the orbiter main propulsion system and the three Shuttle main engines.

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, workers move the liquid oxygen feedline for the 17-inch disconnect toward orbiter Discovery for installation. The 17-inch liquid oxygen and liquid hydrogen disconnects provide the propellant feed interface from the external tank to the orbiter main propulsion system and the three Shuttle main engines.

NASA Image and Video Library

2003-11-11

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, workers move the liquid oxygen feedline for the 17-inch disconnect toward orbiter Discovery for installation. The 17-inch liquid oxygen and liquid hydrogen disconnects provide the propellant feed interface from the external tank to the orbiter main propulsion system and the three Shuttle main engines.

External tank processing from barge to pad

NASA Technical Reports Server (NTRS)

Carpenter, J. E.

1985-01-01

Delivery and launch readiness events for the External Tanks (ET) are discussed. The ET is off-loaded at the KSC Barge Turning Basin and towed to the Vertical Assembly Building (VAB), High Bay Transfer Aisle. It is erected vertically and placed in the ET Checkout Area of High Bay 2 or 4 for standalone checkout. At the completion of checkout the ET is transferred to storage or to the Integration Area of High Bay 1 or 3 for SRB and Orbiter Mate. A Systems Integration Test performed with the Orbiter and Solid Rocket Booster is described. Final checkout activities are also described.

X-15A-2 with full scale ablative and external tanks installed parked in front of hangar

NASA Image and Video Library

1967-08-04

X-15A-2 with full scale ablative and external tanks installed parked in front of hangar. In June 1967, the X-15A-2 rocket-powered research aircraft received a full-scale ablative coating to protect the craft from the high temperatures associated with hypersonic flight (above Mach 5). This pink eraser-like substance, applied to the X-15A-2 aircraft (56-6671), was then covered with a white sealant coat before flight. This coating would help the #2 aircraft reach the record speed of 4,520 mph (Mach 6.7).

Intelligent process development of foam molding for the Thermal Protection System (TPS) of the space shuttle external tank

NASA Technical Reports Server (NTRS)

Bharwani, S. S.; Walls, J. T.; Jackson, M. E.

1987-01-01

A knowledge based system to assist process engineers in evaluating the processability and moldability of poly-isocyanurate (PIR) formulations for the thermal protection system of the Space Shuttle external tank (ET) is discussed. The Reaction Injection Molding- Process Development Advisor (RIM-PDA) is a coupled system which takes advantage of both symbolic and numeric processing techniques. This system will aid the process engineer in identifying a startup set of mold schedules and in refining the mold schedules to remedy specific process problems diagnosed by the system.

KSC-06pd2292

NASA Image and Video Library

2006-10-13

KENNEDY SPACE CENTER, FLA. - Inside the Vehicle Assembly Building, the external tank is mated to its twin solid rocket boosters on the mobile launch platform in high bay 3 for mission STS-116. The gigantic, rust-colored external tank is the largest element of the Space Shuttle system at 27.6 feet wide and 154 feet tall. STS-116 will be mission No. 20 to the International Space Station and construction flight 12A.1. The mission payload is the SPACEHAB module, the P5 integrated truss structure and other key components. Launch is scheduled for no earlier than Dec. 7. Photo credit: NASA/Jack Pfaller

KSC-06pd2291

NASA Image and Video Library

2006-10-13

KENNEDY SPACE CENTER, FLA. - Inside the Vehicle Assembly Building, the external tank is mated to its twin solid rocket boosters on the mobile launch platform in high bay 3 for mission STS-116. The gigantic, rust-colored external tank is the largest element of the Space Shuttle system at 27.6 feet wide and 154 feet tall. STS-116 will be mission No. 20 to the International Space Station and construction flight 12A.1. The mission payload is the SPACEHAB module, the P5 integrated truss structure and other key components. Launch is scheduled for no earlier than Dec. 7. Photo credit: NASA/Jack Pfaller

KSC-06pd2289

NASA Image and Video Library

2006-10-13

KENNEDY SPACE CENTER, FLA. - Inside the Vehicle Assembly Building, the external tank is mated to its twin solid rocket boosters on the mobile launch platform in high bay 3 for mission STS-116. The gigantic, rust-colored external tank is the largest element of the Space Shuttle system at 27.6-feet wide and 154-feet tall. STS-116 will be mission No. 20 to the International Space Station and construction flight 12A.1. The mission payload is the SPACEHAB module, the P5 integrated truss structure and other key components. Launch is scheduled for no earlier than Dec. 7. Photo credit: NASA/Jack Pfaller

KSC-06pd2290

NASA Image and Video Library

2006-10-13

KENNEDY SPACE CENTER, FLA. - Inside the Vehicle Assembly Building, the external tank is mated to its twin solid rocket boosters on the mobile launch platform in high bay 3 for mission STS-116. The gigantic, rust-colored external tank is the largest element of the space shuttle system at 27.6 feet wide and 154 feet tall. STS-116 will be mission No. 20 to the International Space Station and construction flight 12A.1. The mission payload is the SPACEHAB module, the P5 integrated truss structure and other key components. Launch is scheduled for no earlier than Dec. 7. Photo credit: NASA/Jack Pfaller

KSC-06pd2293

NASA Image and Video Library

2006-10-13

KENNEDY SPACE CENTER, FLA. - Inside the Vehicle Assembly Building, the external tank is mated to its twin solid rocket boosters on the mobile launch platform in high bay 3 for mission STS-116. The gigantic, rust-colored external tank is the largest element of the Space Shuttle system at 27.6 feet wide and 154 feet tall. STS-116 will be mission No. 20 to the International Space Station and construction flight 12A.1. The mission payload is the SPACEHAB module, the P5 integrated truss structure and other key components. Launch is scheduled for no earlier than Dec. 7. Photo credit: NASA/Jack Pfaller

KSC-05PD-0031

NASA Technical Reports Server (NTRS)

2005-01-01

KENNEDY SPACE CENTER, FLA. The barge carrying the newly redesigned External Tank (ET), designated for use on Return to Flight mission STS-114, is finally docked at the Launch Complex 39 Area Turn Basin. The ET can be seen inside the barge. The External Tank arrived safely early this morning at Port Canaveral, Fla., after an approximately 900-mile journey at sea. It departed from the Michoud Assembly Facility in New Orleans Dec. 31 and was transported on the Pegasus, NASAs specially designed barge, pulled by Solid Rocket Booster retrieval ship Liberty Star. At the port, the barge was then hooked up to the tugs for the last part of the journey. Next, the External Tank will be off-loaded from the barge and transported to the Vehicle Assembly Building for its final checkout and mating to the twin Solid Rocket Boosters and orbiter Discovery. NASA and Lockheed Martin Corp. spent nearly two years modifying the 15-story, bronze-colored tank to make it safer for liftoff. Among dozens of changes is a redesigned forward bipod fitting -- a design that meets the recommendation of the Columbia Accident Investigation Board to reduce the risk to the Space Shuttle from falling debris during ascent. STS-114 is targeted for a launch opportunity beginning in May. The seven-member Discovery crew will fly to the International Space Station primarily to test and evaluate new procedures for flight safety, including Space Shuttle inspection and repair techniques.

Freedom Star tows a barge with an SLWT into Port Canaveral for the first time

NASA Technical Reports Server (NTRS)

1998-01-01

Freedom Star, one of NASA's two solid rocket booster recovery ships, tows a barge containing the third Space Shuttle super lightweight external tank (SLWT) into Port Canaveral. This SLWT will be used to launch the orbiter Discovery on mission STS-95 in October. This first-time towing arrangement, part of a cost savings plan by NASA to prudently manage existing resources, began June 12 from the Michoud Assembly Facility in New Orleans where the Shuttle's external tanks are manufactured. The barge will now be transported up the Banana River to the LC-39 turn basin using a conventional tugboat. Previously, NASA relied on an outside contractor to provide external tank towing services at a cost of about $120,000 per trip. The new plan allows NASA's Space Flight Operations contractor, United Space Alliance (USA), to provide the same service directly to NASA using the recovery ships during their downtime between Shuttle launches. Studies show a potential savings of about $50,000 per trip. The cost of the necessary ship modifications should be paid back by the fourteenth tank delivery. The other recovery ship, Liberty Star, has also undergone deck strengthening enhancements and will soon have the necessary towing winch installed. The other recovery vessel, Liberty Star, has undergone deck strengthening enhancements along with Freedom Star and will soon have the necessary towing winch installed.

Reusable Launch Vehicle Tank/Intertank Sizing Trade Study

NASA Technical Reports Server (NTRS)

Dorsey, John T.; Myers, David E.; Martin, Carl J.

2000-01-01

A tank and intertank sizing tool that includes effects of major design drivers, and which allows parametric studies to be performed, has been developed and calibrated against independent representative results. Although additional design features, such as bulkheads and field joints, are not currently included in the process, the improved level of fidelity has allowed parametric studies to be performed which have resulted in understanding of key tank and intertank design drivers, design sensitivities, and definition of preferred design spaces. The sizing results demonstrated that there were many interactions between the configuration parameters of internal/external payload, vehicle fineness ratio (half body angle), fuel arrangement (LOX-forward/LOX-aft), number of tanks, and tank shape/arrangement (number of lobes).

KSC-98pc282

NASA Image and Video Library

1998-02-12

KENNEDY SPACE CENTER, FLA. -- The Space Shuttle's first super lightweight external tank is lifted in KSC's Vehicle Assembly Building for STS-91 pre-flight processing. STS-91 is targeted for launch in late May. The improved tank is 7,500 pounds lighter than its predecessors and was developed to increase the Shuttle payload capacity on International Space Station assembly flights. Major changes to the lighter tank include the use of new materials and a revised internal design. The new liquid oxygen and liquid hydrogen tanks are constructed of aluminum lithium a lighter, stronger material than the metal alloy currently used. The redesigned walls of the liquid hydrogen tank were machined to provide additional strength and stability as well

KSC-98pc283

NASA Image and Video Library

1998-02-12

KENNEDY SPACE CENTER, FLA. -- The Space Shuttle's first super lightweight external tank is lifted in KSC's Vehicle Assembly Building for STS-91 pre-flight processing. STS-91 is targeted for launch in late May. The improved tank is 7,500 pounds lighter than its predecessors and was developed to increase the Shuttle payload capacity on International Space Station assembly flights. Major changes to the lighter tank include the use of new materials and a revised internal design. The new liquid oxygen and liquid hydrogen tanks are constructed of aluminum lithium a lighter, stronger material than the metal alloy currently used. The redesigned walls of the liquid hydrogen tank were machined to provide additional strength and stability as well

KSC-98pc281

NASA Image and Video Library

1998-02-12

KENNEDY SPACE CENTER, FLA. -- The Space Shuttle's first super lightweight external tank is lifted in KSC's Vehicle Assembly Building for STS-91 pre-flight processing. STS-91 is targeted for launch in late May. The improved tank is 7,500 pounds lighter than its predecessors and was developed to increase the Shuttle payload capacity on International Space Station assembly flights. Major changes to the lighter tank include the use of new materials and a revised internal design. The new liquid oxygen and liquid hydrogen tanks are constructed of aluminum lithium a lighter, stronger material than the metal alloy currently used. The redesigned walls of the liquid hydrogen tank were machined to provide additional strength and stability as well

Space Shuttle Projects

NASA Image and Video Library

2004-09-13

The Space Shuttle External Tank 120 is shown here during transfer in NASA’s Michoud Assembly Facility in New Orleans. Slated for launch on the Orbiter Discovery scheduled for next Spring, the tank will be erected vertically in preparation for its new foam application process on the liquid hydrogen tank-to-inter tank flange area, a tank structural connection point. The foam will be applied with an enhanced finishing procedure that requires two technicians, one for a new mold-injection procedure to the intertank’s ribbing and one for real-time videotaped surveillance of the process. Marshall Space Flight Center played a significant role in the development of the new application process designed to replace the possible debris shedding source previously used.

Space Shuttle Projects

NASA Image and Video Library

2004-09-13

The Space Shuttle External Tank 120 is shown here in its vertical position in NASA’s Michoud Assembly Facility in New Orleans. Slated for launch on the Orbiter Discovery scheduled for next Spring, the tank is in position for its new foam application process on the liquid hydrogen tank-to-inter tank flange area, a tank structural connection point. The foam will be applied with an enhanced finishing procedure that requires two technicians, one for a new mold-injection procedure to the intertank’s ribbing and one for real-time videotaped surveillance of the process. Marshall Space Flight Center played a significant role in the development of the new application process designed to replace the possible debris shedding source previously used.

KSC-06pd0598

NASA Image and Video Library

2006-04-11

KENNEDY SPACE CENTER, FLA. - Inside the Vehicle Assembly Building at NASA's Kennedy Space Center, external tank number 119 is being lifted from the checkout cell and will be placed horizontally on the transporter in the transfer aisle. Once in the transfer aisle, technicians will reapply the thermal protection system foam that was removed in order to replace the tank's four liquid hydrogen engine cutoff sensors. The tank is being prepared to launch Space Shuttle Discovery on mission STS-121 in July.

KSC-06pd0685

NASA Image and Video Library

2006-04-18

KENNEDY SPACE CENTER, FLA. -- Lockheed Martin technicians in the Vehicle Assembly Building at NASA's Kennedy Space Center apply new foam over the manhole cover on the lower end of external tank No. 119. The manhole was removed to access the area where the tank's four liquid hydrogen engine cutoff sensors were replaced. Once reinstalled, the manhole required new foam to be applied. The tank is being prepared to launch Space Shuttle Discovery on mission STS-121 in July. Photo credit: NASA/Jim Grossmann

Study of alternate space shuttle concepts

NASA Technical Reports Server (NTRS)

1971-01-01

A study of alternate space shuttle concepts was conducted to examine the stage-and-one-half concept and its potential for later conversion and use in the two stage reusable shuttle system. A study of external hydrogen tank concepts was conducted to determine the issues involved in the design and production of a low-cost expendable tank system. The major objectives of the study were to determine: (1) realistic drop tank program cost estimates, (2) estimated drop tank program cost for selected specific designs, and (3) change in program cost due to variations in design and manufacturing concepts and changes in program assumptions.

KSC-07pd0598

NASA Image and Video Library

2007-03-09

KENNEDY SPACE CENTER, FLA. -- In Highbay 1 inside the Vehicle Assembly Building, technicians work on repair techniques to the hail-damaged external tank. They are inside a tented area that protects the tank. Scaffolding around the tank can be seen below. A severe thunderstorm with golf ball-sized hail caused visible divots in the giant tank's foam insulation and minor surface damage to about 26 heat shield tiles on the shuttle's left wing. A new target launch date has not been determined, but teams will focus on preparing Atlantis for liftoff in late April on mission STS-117. Photo credit: NASA/Jim Grossmann

KSC-06pd1018

NASA Image and Video Library

2006-06-09

KENNEDY SPACE CENTER, FLA. - Tug boats maneuver the Pegasus barge next to the dock in the turn basin at the Launch Complex 39 Area. The barge holds the redesigned external fuel tank, designated ET-118, that will launch Space Shuttle Atlantis on the next shuttle mission, STS-115. The tank was shipped from the Michoud Assembly Facility in New Orleans. After off-loading, the tank will be moved into the Vehicle Assembly Building and lifted into a checkout cell for further work. The tank will fly with many major safety changes, including the removal of the protuberance air load ramps. Photo credit: NASA/Kim Shiflett

KSC-06pd1019

NASA Image and Video Library

2006-06-09

KENNEDY SPACE CENTER, FLA. - Tug boats maneuver the Pegasus barge next to the dock in the turn basin at the Launch Complex 39 Area. The barge holds the redesigned external fuel tank, seen inside, that will launch Space Shuttle Atlantis on the next shuttle mission, STS-115. The tank, designated ET-118, was shipped from the Michoud Assembly Facility in New Orleans. After off-loading, the tank will be moved into the Vehicle Assembly Building and lifted into a checkout cell for further work. The tank will fly with many major safety changes, including the removal of the protuberance air load ramps. Photo credit: NASA/Kim Shiflett

Where Did the Water Go?: Boyle's Law and Pressurized Diaphragm Water Tanks

ERIC Educational Resources Information Center

Brimhall, James; Naga, Sundar

2007-01-01

Many homes use pressurized diaphragm tanks for storage of water pumped from an underground well. These tanks are very carefully constructed to have separate internal chambers for the storage of water and for the air that provides the pressure. One might expect that the amount of water available for use from, for example, a 50-gallon tank would be…

KSC-pa-et-2

NASA Image and Video Library

1998-02-06

The Space Shuttle's first super lightweight external tank is on its way to Kennedy Space Center's Vehicle Assembly Building for processing. The tank, which is scheduled for flight on STS-91 in late May, arrived Feb. 3 in Port Canaveral, where it remained until Feb. 6 due to high winds. The improved tank is 7,500 pounds lighter than its predecessors and was developed to increase the Shuttle payload capacity on International Space Station assembly flights. Major changes to the lighter tank include the use of new materials and a revised internal design. The new liquid oxygen and liquid hydrogen tanks are constructed of aluminum lithium a lighter, stronger material than the metal alloy currently used. The redesigned walls of the liquid hydrogen tank were machined to provide additional strength and stability as well

KSC-pa-et-1

NASA Image and Video Library

1998-02-06

The Space Shuttle's first super lightweight external tank is on its way to Kennedy Space Center's Vehicle Assembly Building for processing. The tank, which is scheduled for flight on STS-91 in late May, arrived Feb. 3 in Port Canaveral, where it remained until Feb. 6 due to high winds. The improved tank is 7,500 pounds lighter than its predecessors and was developed to increase the Shuttle payload capacity on International Space Station assembly flights. Major changes to the lighter tank include the use of new materials and a revised internal design. The new liquid oxygen and liquid hydrogen tanks are constructed of aluminum lithium a lighter, stronger material than the metal alloy currently used. The redesigned walls of the liquid hydrogen tank were machined to provide additional strength and stability as well

KSC-pa-et-3

NASA Image and Video Library

1998-02-06

The Space Shuttle's first super lightweight external tank is on its way to Kennedy Space Center's Vehicle Assembly Building for processing. The tank, which is scheduled for flight on STS-91 in late May, arrived Feb. 3 in Port Canaveral, where it remained until Feb. 6 due to high winds. The improved tank is 7,500 pounds lighter than its predecessors and was developed to increase the Shuttle payload capacity on International Space Station assembly flights. Major changes to the lighter tank include the use of new materials and a revised internal design. The new liquid oxygen and liquid hydrogen tanks are constructed of aluminum lithium a lighter, stronger material than the metal alloy currently used. The redesigned walls of the liquid hydrogen tank were machined to provide additional strength and stability as well

KSC-98pc273

NASA Image and Video Library

1998-02-06

KENNEDY SPACE CENTER, FLA. -- The Space Shuttle's first super lightweight external tank is on its way to Kennedy Space Center's Vehicle Assembly Building for processing. The tank, which is scheduled for flight on STS-91 in late May, arrived Feb. 3 in Port Canaveral, where it remained until Feb. 6 due to high winds. The improved tank is 7,500 pounds lighter than its predecessors and was developed to increase the Shuttle payload capacity on International Space Station assembly flights. Major changes to the lighter tank include the use of new materials and a revised internal design. The new liquid oxygen and liquid hydrogen tanks are constructed of aluminum lithium a lighter, stronger material than the metal alloy currently used. The redesigned walls of the liquid hydrogen tank were machined to provide additional strength and stability as well

KSC-pa-et-5

NASA Image and Video Library

1998-02-06

The Space Shuttle's first super lightweight external tank is on its way to Kennedy Space Center's Vehicle Assembly Building for processing. The tank, which is scheduled for flight on STS-91 in late May, arrived Feb. 3 in Port Canaveral, where it remained until Feb. 6 due to high winds. The improved tank is 7,500 pounds lighter than its predecessors and was developed to increase the Shuttle payload capacity on International Space Station assembly flights. Major changes to the lighter tank include the use of new materials and a revised internal design. The new liquid oxygen and liquid hydrogen tanks are constructed of aluminum lithium a lighter, stronger material than the metal alloy currently used. The redesigned walls of the liquid hydrogen tank were machined to provide additional strength and stability as well

KSC-98pc275

NASA Image and Video Library

1998-02-06

KENNEDY SPACE CENTER, FLA. -- The Space Shuttle's first super lightweight external tank is on its way into Kennedy Space Center's Vehicle Assembly Building for processing. The tank, which is scheduled for flight on STS-91 in late May, arrived Feb. 3 in Port Canaveral, where it remained until Feb. 6 due to high winds. The improved tank is 7,500 pounds lighter than its predecessors and was developed to increase the Shuttle payload capacity on International Space Station assembly flights. Major changes to the lighter tank include the use of new materials and a revised internal design. The new liquid oxygen and liquid hydrogen tanks are constructed of aluminum lithium a lighter, stronger material than the metal alloy currently used. The redesigned walls of the liquid hydrogen tank were machined to provide additional strength and stability as well

KSC-98pc279

NASA Image and Video Library

1998-02-06

KENNEDY SPACE CENTER, FLA. -- The Space Shuttle's first super lightweight external tank is on its way to Kennedy Space Center's Vehicle Assembly Building for processing. The tank, which is scheduled for flight on STS-91 in late May, arrived Feb. 3 in Port Canaveral, where it remained until Feb. 6 due to high winds. The improved tank is 7,500 pounds lighter than its predecessors and was developed to increase the Shuttle payload capacity on International Space Station assembly flights. Major changes to the lighter tank include the use of new materials and a revised internal design. The new liquid oxygen and liquid hydrogen tanks are constructed of aluminum lithium a lighter, stronger material than the metal alloy currently used. The redesigned walls of the liquid hydrogen tank were machined to provide additional strength and stability as well

KSC-pa-et-4

NASA Image and Video Library

1998-02-06

The Space Shuttle's first super lightweight external tank is on its way to Kennedy Space Center's Vehicle Assembly Building for processing. The tank, which is scheduled for flight on STS-91 in late May, arrived Feb. 3 in Port Canaveral, where it remained until Feb. 6 due to high winds. The improved tank is 7,500 pounds lighter than its predecessors and was developed to increase the Shuttle payload capacity on International Space Station assembly flights. Major changes to the lighter tank include the use of new materials and a revised internal design. The new liquid oxygen and liquid hydrogen tanks are constructed of aluminum lithium a lighter, stronger material than the metal alloy currently used. The redesigned walls of the liquid hydrogen tank were machined to provide additional strength and stability as well

Annual Radioactive Waste Tank Inspection Program 1994

DOE Office of Scientific and Technical Information (OSTI.GOV)

McNatt, F.G. Sr.

1995-04-01

Aqueous radioactive wastes from Savannah River Site (SRS) separations processes are contained in large underground carbon steel tanks. Inspections made during 1994 to evaluate these vessels and evaluations based on data accrued by inspections made since the tanks were constructed are the subject of this report.

KSC-04PD-1812

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. In the Orbiter Processing Facility, United Space Alliance worker Craig Meyer fits an External Tank (ET) digital still camera in the right-hand liquid oxygen umbilical well on Space Shuttle Atlantis. NASA is pursuing use of the camera, beginning with the Shuttles Return To Flight, to obtain and downlink high-resolution images of the ET following separation of the ET from the orbiter after launch. The Kodak camera will record 24 images, at one frame per 1.5 seconds, on a flash memory card. After orbital insertion, the crew will transfer the images from the memory card to a laptop computer. The files will then be downloaded through the Ku-band system to the Mission Control Center in Houston for analysis.

KSC-04PD-1813

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. In the Orbiter Processing Facility, an External Tank (ET) digital still camera is positioned into the right-hand liquid oxygen umbilical well on Space Shuttle Atlantis to determine if it fits properly. NASA is pursuing use of the camera, beginning with the Shuttles Return To Flight, to obtain and downlink high-resolution images of the ET following separation of the ET from the orbiter after launch. The Kodak camera will record 24 images, at one frame per 1.5 seconds, on a flash memory card. After orbital insertion, the crew will transfer the images from the memory card to a laptop computer. The files will then be downloaded through the Ku-band system to the Mission Control Center in Houston for analysis.

KSC-04pd1813

NASA Image and Video Library

2004-09-17

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, an External Tank (ET) digital still camera is positioned into the right-hand liquid oxygen umbilical well on Space Shuttle Atlantis to determine if it fits properly. NASA is pursuing use of the camera, beginning with the Shuttle’s Return To Flight, to obtain and downlink high-resolution images of the ET following separation of the ET from the orbiter after launch. The Kodak camera will record 24 images, at one frame per 1.5 seconds, on a flash memory card. After orbital insertion, the crew will transfer the images from the memory card to a laptop computer. The files will then be downloaded through the Ku-band system to the Mission Control Center in Houston for analysis.

KSC-04pd1812

NASA Image and Video Library

2004-09-17

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, United Space Alliance worker Craig Meyer fits an External Tank (ET) digital still camera in the right-hand liquid oxygen umbilical well on Space Shuttle Atlantis. NASA is pursuing use of the camera, beginning with the Shuttle’s Return To Flight, to obtain and downlink high-resolution images of the ET following separation of the ET from the orbiter after launch. The Kodak camera will record 24 images, at one frame per 1.5 seconds, on a flash memory card. After orbital insertion, the crew will transfer the images from the memory card to a laptop computer. The files will then be downloaded through the Ku-band system to the Mission Control Center in Houston for analysis.

DOE Office of Scientific and Technical Information (OSTI.GOV)

Congram, G.E.

When Plantation Pipe Line Co., Greensboro, NC purchased an adjacent tank farm containing six above ground steel storage tanks, the facilities had been idle for 18 months. As a result, major repairs and modifications were needed before the tanks and associated equipment could be returned to service. The main challenge, however, was to bring the 50-year old storage tanks up to operating standards as quickly and cost-effectively as possible. Varying degrees of restoration and a variety of procedures were implemented as solutions to the restoration project. Of particular concern was assuring the overall integrity of the steel tank bottoms andmore » that they were fully protected from internal and external corrosion. Work on the six newly-acquired tanks began in July 1994 and was completed in five months. Configurations ranged from 84 feet in diameter cone roof tanks with interior steel floaters to 110 in diameter tanks with open top floating roofs, to 140 feet in diameter cone roof tanks. All tanks were in different states of condition and many of the same maintenance procedures were used during restoration. This paper reviews the various renovation techniques used to restore these tanks to service.« less

33 CFR 183.220 - Preconditioning for tests.

Code of Federal Regulations, 2010 CFR

2010-07-01

... motor and controls and for the submerged weight or the battery, respectively. (e) Permanent fuel tanks must be filled with fuel and each external opening into the fuel tank must be sealed. (f) The boat must... be placed in the normal operating position of the motor and controls and the battery in lieu of this...

49 CFR 178.338-13 - Supporting and anchoring.

Code of Federal Regulations, 2010 CFR

2010-10-01

... whole or in part the structural member used in place of a motor vehicle frame, the cargo tank or the... vehicle frame, the tank or jacket must be supported by external cradles, load rings, or longitudinal... subchapter), multiplied by the following factors. The effects of fatigue must also be considered in the...

KSC-07pd0834

NASA Image and Video Library

2007-04-06

KENNEDY SPACE CENTER, FLA. -- The Pegasus barge arrives at Port Canaveral in Florida with its cargo of the external tank prepared for mission STS-118. The barge will be towed up the Banana River to the turn basin near the Vehicle Assembly Building where the tank will be offloaded and moved to the VAB. Photo credit: Jack Pfaller

KSC-2010-5882

NASA Image and Video Library

2010-12-17

CAPE CANAVERAL, Fla. -- Team members stationed at consoles in the Launch Control Center at NASA's Kennedy Space Center in Florida monitor space shuttle Discovery's external fuel tank as it is loaded with more than 535,000 gallons of cryogenic propellants. From left, are NASA Commentator Allard Beutel, Discovery's NASA Vehicle Manager Jennifer Nufer and Lead NASA Test Director Charlie Blackwell-Thompson. During today's tanking test, the team is paying particular attention to the external tank's ribbed intertank region. Beginning tomorrow, engineers will evaluate data on 21-foot-long, U-shaped aluminum brackets, called stringers, and the newly replaced ground umbilical carrier plate (GUCP). Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at the GUCP. In order to perform additional analysis on the tank, Discovery will be rolled back to the Vehicle Assembly Building, a move that is planned for next week. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Cory Huston

KSC-2010-5885

NASA Image and Video Library

2010-12-17

CAPE CANAVERAL, Fla. -- Team members stationed at consoles in the Launch Control Center at NASA's Kennedy Space Center in Florida monitor space shuttle Discovery's external fuel tank as it is loaded with more than 535,000 gallons of cryogenic propellants. From back, are STS-133 Assistant NASA Test Director Jeff Spaulding, STS-133 NASA Test Director Steve Payne and Launch Orbiter Test Conductor John Kracsun. During today's tanking test, the team is paying particular attention to the external tank's ribbed intertank region. Beginning tomorrow, engineers will evaluate data on 21-foot-long, U-shaped aluminum brackets, called stringers, and the newly replaced ground umbilical carrier plate (GUCP). Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at the GUCP. In order to perform additional analysis on the tank, Discovery will be rolled back to the Vehicle Assembly Building, a move that is planned for next week. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Cory Huston

KSC-2010-5878

NASA Image and Video Library

2010-12-17

CAPE CANAVERAL, Fla. -- The Final Inspection Team, also known as the Ice Team, gathers before heading out to Launch Pad 39A at NASA's Kennedy Space Center in Florida to inspect space shuttle Discovery's external fuel tank during the loading of more than 535,000 gallons of cryogenic propellants. During today's tanking test, the team members will pay particular attention to the external tank's ribbed intertank region and report their findings to engineers located in the Launch Control Center. Beginning tomorrow, engineers will evaluate data on 21-foot-long, U-shaped aluminum brackets, called stringers, and the newly replaced ground umbilical carrier plate (GUCP). Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at the GUCP. In order to perform additional analysis on the tank, Discovery will be rolled back to the Vehicle Assembly Building, a move that is planned for next week. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Cory Huston

KSC-2010-5884

NASA Image and Video Library

2010-12-17

CAPE CANAVERAL, Fla. -- Team members stationed at consoles in the Launch Control Center at NASA's Kennedy Space Center in Florida monitor space shuttle Discovery's external fuel tank as it is loaded with more than 535,000 gallons of cryogenic propellants. From back, are STS-133 Assistant NASA Test Director Jeff Spaulding, STS-133 NASA Test Director Steve Payne, Launch Orbiter Test Conductor John Kracsun and Assistant Launch Orbiter Test Conductor Mark Taffet. During today's tanking test, the team is paying particular attention to the external tank's ribbed intertank region. Beginning tomorrow, engineers will evaluate data on 21-foot-long, U-shaped aluminum brackets, called stringers, and the newly replaced ground umbilical carrier plate (GUCP). Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at the GUCP. In order to perform additional analysis on the tank, Discovery will be rolled back to the Vehicle Assembly Building, a move that is planned for next week. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Cory Huston

KSC-2010-5879

NASA Image and Video Library

2010-12-17

CAPE CANAVERAL, Fla. -- The Final Inspection Team, also known as the Ice Team, gathers before heading out to Launch Pad 39A at NASA's Kennedy Space Center in Florida to inspect space shuttle Discovery's external fuel tank during the loading of more than 535,000 gallons of cryogenic propellants. During today's tanking test, the team members will pay particular attention to the external tank's ribbed intertank region and report their findings to engineers located in the Launch Control Center. Beginning tomorrow, engineers will evaluate data on 21-foot-long, U-shaped aluminum brackets, called stringers, and the newly replaced ground umbilical carrier plate (GUCP). Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at the GUCP. In order to perform additional analysis on the tank, Discovery will be rolled back to the Vehicle Assembly Building, a move that is planned for next week. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Cory Huston

KSC-2010-5881

NASA Image and Video Library

2010-12-17

CAPE CANAVERAL, Fla. -- Team members stationed at consoles in the Launch Control Center at NASA's Kennedy Space Center in Florida monitor space shuttle Discovery's external fuel tank as it is loaded with more than 535,000 gallons of cryogenic propellants. From left, are STS-133 Assistant NASA Test Director Jeff Spaulding, NASA Test Director Jeremy Graeber and STS-133 NASA Test Director Steve Payne. During today's tanking test, the team is paying particular attention to the external tank's ribbed intertank region. Beginning tomorrow, engineers will evaluate data on 21-foot-long, U-shaped aluminum brackets, called stringers, and the newly replaced ground umbilical carrier plate (GUCP). Discovery's first launch attempt for STS-133 was scrubbed in early November due to a hydrogen gas leak at the GUCP. In order to perform additional analysis on the tank, Discovery will be rolled back to the Vehicle Assembly Building, a move that is planned for next week. The next launch opportunity is no earlier than Feb. 3, 2011. For more information on STS-133, visit www.nasa.gov/mission_pages/shuttle/shuttlemissions/sts133/. Photo credit: NASA/Cory Huston

NASA Tech Briefs, September 2010

NASA Technical Reports Server (NTRS)

2010-01-01

Topics covered include: Instrument for Measuring Thermal Conductivity of Materials at Low Temperatures; Multi-Axis Accelerometer Calibration System; Pupil Alignment Measuring Technique and Alignment Reference for Instruments or Optical Systems; Autonomous System for Monitoring the Integrity of Composite Fan Housings; A Safe, Self-Calibrating, Wireless System for Measuring Volume of Any Fuel at Non-Horizontal Orientation; Adaptation of the Camera Link Interface for Flight-Instrument Applications; High-Performance CCSDS Encapsulation Service Implementation in FPGA; High-Performance CCSDS AOS Protocol Implementation in FPGA; Advanced Flip Chips in Extreme Temperature Environments; Diffuse-Illumination Systems for Growing Plants; Microwave Plasma Hydrogen Recovery System; Producing Hydrogen by Plasma Pyrolysis of Methane; Self-Deployable Membrane Structures; Reactivation of a Tin-Oxide-Containing Catalys; Functionalization of Single-Wall Carbon Nanotubes by Photo-Oxidation; Miniature Piezoelectric Macro-Mass Balance; Acoustic Liner for Turbomachinery Applications; Metering Gas Strut for Separating Rocket Stages; Large-Flow-Area Flow-Selective Liquid/Gas Separator; Counterflowing Jet Subsystem Design; Water Tank with Capillary Air/Liquid Separation; True Shear Parallel Plate Viscometer; Focusing Diffraction Grating Element with Aberration Control; Universal Millimeter-Wave Radar Front End; Mode Selection for a Single-Frequency Fiber Laser; Qualification and Selection of Flight Diode Lasers for Space Applications; Plenoptic Imager for Automated Surface Navigation; Maglev Facility for Simulating Variable Gravity; Hybrid AlGaN-SiC Avalanche Photodiode for Deep-UV Photon Detection; High-Speed Operation of Interband Cascade Lasers; 3D GeoWall Analysis System for Shuttle External Tank Foreign Object Debris Events; Charge-Spot Model for Electrostatic Forces in Simulation of Fine Particulates; Hidden Statistics Approach to Quantum Simulations; Reconstituted Three-Dimensional Interactive Imaging; Determining Atmospheric-Density Profile of Titan; Digital Microfluidics Sample Analyzer; Radiation Protection Using Carbon Nanotube Derivatives; Process to Selectively Distinguish Viable from Non-Viable Bacterial Cells; and TEAMS Model Analyzer.