Closeup view of the interior of an Aft Skirt being ...

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

Close-up view of the interior of an Aft Skirt being tested and prepared for mating with sub assemblies in the Solid Rocket Booster (SRB) Assembly and Refurbishment Facility at Kennedy Space Center. This view is showing the SRB Thrust Vector Control (TVC) System which includes independent auxiliary power units for each actuator to pressurize their respective hydraulic systems. When the Nozzle is mated with the Aft Skirt the two actuators, located on the left and right side of the TVC System in this view, can swivel it up to 3.5 degrees to redirect the thrust to steer and maintain the Shuttle's programmed trajectory. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

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

Probabilistic Structural Analysis of the Solid Rocket Booster Aft Skirt External Fitting Modification

NASA Technical Reports Server (NTRS)

Townsend, John S.; Peck, Jeff; Ayala, Samuel

2000-01-01

NASA has funded several major programs (the Probabilistic Structural Analysis Methods Project is an example) to develop probabilistic structural analysis methods and tools for engineers to apply in the design and assessment of aerospace hardware. A probabilistic finite element software code, known as Numerical Evaluation of Stochastic Structures Under Stress, is used to determine the reliability of a critical weld of the Space Shuttle solid rocket booster aft skirt. An external bracket modification to the aft skirt provides a comparison basis for examining the details of the probabilistic analysis and its contributions to the design process. Also, analysis findings are compared with measured Space Shuttle flight data.

Space Shuttle Main Engine structural analysis and data reduction/evaluation. Volume 1: Aft Skirt analysis

NASA Technical Reports Server (NTRS)

Berry, David M.; Stansberry, Mark

1989-01-01

Using the ANSYS finite element program, a global model of the aft skirt and a detailed nonlinear model of the failure region was made. The analysis confirmed the area of failure in both STA-2B and STA-3 tests as the forging heat affected zone (HAZ) at the aft ring centerline. The highest hoop strain in the HAZ occurs in this area. However, the analysis does not predict failure as defined by ultimate elongation of the material equal to 3.5 percent total strain. The analysis correlates well with the strain gage data from both the Wyle influence test of the original design aft sjirt and the STA-3 test of the redesigned aft skirt. it is suggested that the sensitivity of the failure area material strength and stress/strain state to material properties and therefore to small manufacturing or processing variables is the most likely cause of failure below the expected material ultimate properties.

Finite Element Simulation of a Space Shuttle Solid Rocket Booster Aft Skirt Splashdown Using an Arbitrary Lagrangian-Eulerian Approach

NASA Astrophysics Data System (ADS)

Melis, Matthew E.

2003-01-01

Explicit finite element techniques employing an Arbitrary Lagrangian-Eulerian (ALE) methodology, within the transient dynamic code LS-DYNA, are used to predict splashdown loads on a proposed replacement/upgrade of the hydrazine tanks on the thrust vector control system housed within the aft skirt of a Space Shuttle Solid Rocket Booster. Two preliminary studies are performed prior to the full aft skirt analysis: An analysis of the proposed tank impacting water without supporting aft skirt structure, and an analysis of space capsule water drop tests conducted at NASA's Langley Research Center. Results from the preliminary studies provide confidence that useful predictions can be made by applying the ALE methodology to a detailed analysis of a 26-degree section of the skirt with proposed tank attached. Results for all three studies are presented and compared to limited experimental data. The challenges of using the LS-DYNA ALE capability for this type of analysis are discussed.

Finite Element Simulation of a Space Shuttle Solid Rocket Booster Aft Skirt Splashdown Using an Arbitrary Lagrangian-eulerian Approach

NASA Technical Reports Server (NTRS)

Melis, Matthew E.

2003-01-01

Explicit finite element techniques employing an Arbitrary Lagrangian-Eulerian (ALE) methodology, within the transient dynamic code LS-DYNA, are used to predict splashdown loads on a proposed replacement/upgrade of the hydrazine tanks on the thrust vector control system housed within the aft skirt of a Space Shuttle Solid Rocket Booster. Two preliminary studies are performed prior to the full aft skirt analysis: An analysis of the proposed tank impacting water without supporting aft skirt structure, and an analysis of space capsule water drop tests conducted at NASA's Langley Research Center. Results from the preliminary studies provide confidence that useful predictions can be made by applying the ALE methodology to a detailed analysis of a 26-degree section of the skirt with proposed tank attached. Results for all three studies are presented and compared to limited experimental data. The challenges of using the LS-DYNA ALE capability for this type of analysis are discussed.

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 Assembly and Refurbishment Facility at Kennedy Space Center. The most prominent feature in this view are the six Thrust Vector Control System access ports, three per hydraulic actuator. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Aft Skirt Electrical Umbilical (ASEU) and Vehicle Support Post (

NASA Image and Video Library

2016-12-09

A flatbed truck carries a vertical support post (VSP) for NASA's Space Launch System (SLS) rocket to the Mobile Launcher Yard at NASA's Kennedy Space Center in Florida. The two aft skirt electrical umbilicals (ASEUs) and the first of the vehicle support posts underwent a series of tests to confirm they are functioning properly and ready to support the SLS for launch. The ASEUs will connect to the SLS rocket at the bottom outer edge of each booster and provide electrical power and data connections to the rocket until it lifts off from the launch pad. The eight VSPs will support the load of the solid rocket boosters, with four posts for each of the boosters. The center’s Engineering Directorate and the Ground Systems Development and Operations Program are overseeing processing and testing of the umbilicals.

Aft Skirt Electrical Umbilical (ASEU) and Vehicle Support Post (

NASA Image and Video Library

2016-12-09

A flatbed truck carries a vertical support post (VSP) for NASA's Space Launch System (SLS) rocket to the Mobile Launcher Yard at NASA's Kennedy Space Center in Florida. In view is the mobile launcher. The two aft skirt electrical umbilicals (ASEUs) and the first of the vehicle support posts underwent a series of tests to confirm they are functioning properly and ready to support the SLS for launch. The ASEUs will connect to the SLS rocket at the bottom outer edge of each booster and provide electrical power and data connections to the rocket until it lifts off from the launch pad. The eight VSPs will support the load of the solid rocket boosters, with four posts for each of the boosters. The center’s Engineering Directorate and the Ground Systems Development and Operations Program are overseeing processing and testing of the umbilicals.

Aft Skirt Electrical Umbilical (ASEU) and Vehicle Support Post (

NASA Image and Video Library

2016-12-09

A construction worker is in view as a flatbed truck passes by carrying a vertical support post (VSP) for NASA's Space Launch System (SLS) rocket to the Mobile Launcher Yard at NASA's Kennedy Space Center in Florida. The two aft skirt electrical umbilicals (ASEUs) and the first of the vehicle support posts underwent a series of tests to confirm they are functioning properly and ready to support the SLS for launch. The ASEUs will connect to the SLS rocket at the bottom outer edge of each booster and provide electrical power and data connections to the rocket until it lifts off from the launch pad. The eight VSPs will support the load of the solid rocket boosters, with four posts for each of the boosters. The center’s Engineering Directorate and the Ground Systems Development and Operations Program are overseeing processing and testing of the umbilicals.

Explicit Finite Element Techniques Used to Characterize Splashdown of the Space Shuttle Solid Rocket Booster Aft Skirt

NASA Technical Reports Server (NTRS)

Melis, Matthew E.

2003-01-01

NASA Glenn Research Center s Structural Mechanics Branch has years of expertise in using explicit finite element methods to predict the outcome of ballistic impact events. Shuttle engineers from the NASA Marshall Space Flight Center and NASA Kennedy Space Flight Center required assistance in assessing the structural loads that a newly proposed thrust vector control system for the space shuttle solid rocket booster (SRB) aft skirt would expect to see during its recovery splashdown.

Water impact test of aft skirt end ring, and mid ring segments of the Space Shuttle Solid Rocket Booster

NASA Technical Reports Server (NTRS)

1983-01-01

The results of water impact loads tests using aft skirt end ring, and mid ring segments of the Space Shuttle Solid Rocket Booster (SRB) are examined. Dynamic structural response data is developed and an evaluation of the model in various configurations is presented. Impact velocities are determined for the SRB with the larger main chute system. Various failure modes are also investigated.

Results of tests on a specimen of the SRB aft skirt heat shield curtain in the MSFC LRLF

NASA Technical Reports Server (NTRS)

Dean, W. G.

1980-01-01

A full scale segment of the actual Solid Rocket Booster aft skirt heat shield curtain was tested in the Large Radiant Lamp Facility (LRLF) at Marshall Space Flight Center. The curtain was mounted in the horizontal position in the same manner as it is to be mounted on the SRB. A shaker rig was designed and used to provide a motion of the curtain, simulating that to be caused in flight by vehicle acoustics. Thermocouples were used to monitor curtain materials temperatures. Both ascent and reentry heat loads were applied to the test specimen. All aspects of the test setup performed as expected, and the test was declared successful.

Use of photostress and strain gages to analyze behavior of weldments and use of photostress and strain gages to analyze behavior of an aft skirt test specimen

NASA Technical Reports Server (NTRS)

Gambrell, S. C.; Karr, Gerald R.

1993-01-01

Previous work using Photostress on TIG welded, heat treated specimens of 2219-T87 parent material and 2319 weld material indicated that behavior of the joint can be highly irregular and non-uniform. Welded joints 1.40 inches thick exhibited a totally non-uniform behavior through the weld thickness with the 'wide' side of the weld being much more ductile than the 'narrow' side. It is believed that this difference in behavior through the weld is, in part, caused by procedures used when laying the weld bead. Joints similar to weldments in references 1 and 2 are an integral part of the aft skirt of the SRB of the shuttle. Since the ultimate safety factor for the lower portion of the weld is below the minimum required safety factor, a photostress analysis of this lower portion will be conducted in the vicinity of the weld. A test program using photostress will be conducted in accordance with the project planning document entitled 'Photostress Evaluation Requirements for AFT Skirt Test Article No. 4'.

The Repair and Return to Flight of Solid Rocket Booster Forward Skirt Serial Number 20022

NASA Technical Reports Server (NTRS)

Malone, T. W.; Jones, C. S.; Honeycutt, J. H., Sr.

2008-01-01

On April 5, 1991, a solid rocket booster (SRB) forward skirt serial number (S/N) 20022 sustained buckling damage during water impact after the launch of Space Transportation System Flight 37 (STS-37). As of that date, five forward skirts had been lost during water impact. Repair attempts began with the least damaged skirt available (S/N 20022). Sp ecial hydraulic tooling was used to remove buckled areas of the skirt. Afterwards, its aft clevis pinholes were found to be out of alignment with the redesigned solid rocket motor (RSRM) check gauge, but weld passes were used to correct this condition. Meanwhile, USA Analytics generated mechanical property data for buckled and subsequently debuckled material. Their analysis suggested that structural integrity might be improved by adding stringer reinforcements, stiffeners, to the aft bay section of the skirt. This improvement was recommended as a fleet modification to be implemented on a case-by-case basis.

Use of photostress to analyze behavior of an aft skirt test specimen

NASA Technical Reports Server (NTRS)

Gambrell, S. C., Jr.

1994-01-01

Strains at twenty-one selected points in the critical lower weld region of a aft skirt of a solid rocket booster of the shuttle were measured using photoelastic coatings and stress separator gages. Data were taken at loads of 5, 14, 20, 28, 42, 56, and 70 percent of the design limit load. Results indicate that general yielding occurred in the weld metal and for a short distance outside the fusion boundaries on either side of the weld metal. The fusion boundaries did not yield at the 70 percent load. Slight non-linearity in the load strain curves were observed at several points above the 20 percent load level. Maximum measured strains occurred at points in the forged metal of the holddown post along a line 0.50 inches from the centerline of the weld. Maximum shearing strains within the area covered by the photoelastic coating occurred at points approximately 0.33 inches to the right of the weld centerline near points 6 and 7 and lying along a yellow vertical line extending from just below point 6 to point 11. Photoelastic coatings were shown to be an excellent method to provide the whole field strain distribution in the region of the critical weld and to enhance the overall understanding of the behavior of the welded joint.

General view of the Aft Rocket Motor mated with the ...

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

General view of the Aft Rocket Motor mated with the External Tank Attach Ring and Aft Skirt Assembly being transported from the Rotation Processing and Surge Facility to the Vehicle Assembly Building at Kennedy Space Center. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

General view of the Aft Rocket Motor mated with the ...

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

General view of the Aft Rocket Motor mated with the External Tank Attach Ring and Aft Skirt Assembly in the process of being mounted onto the Mobile Launch Platform in the Vehicle Assembly Building at Kennedy Space Center. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Closeup view of the Solid Rocket Booster (SRB) Forward Skirt ...

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

Close-up view of the Solid Rocket Booster (SRB) Forward Skirt sitting on ground support equipment in the Solid Rocket Booster Assembly and Refurbishment Facility at Kennedy Space Center while being prepared for mating with the Frustum-Nose Cap Assembly and the Forward Rocket Motor Segment. The prominent feature in this view is the electrical, data, telemetry and safety systems terminal which connects to the Aft Skirt Assembly systems via the Systems Tunnel that runs the length of the Rocket Motor. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

General view of the Aft Solid Rocket Motor Segment mated ...

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

General view of the Aft Solid Rocket Motor Segment mated with the Aft Skirt Assembly and External Tank Attach Ring in the Rotation Processing and Surge Facility at Kennedy Space Center and awaiting transfer to the Vehicle Assembly Building where it will be mounted onto the Mobile Launch Platform. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Optimal slot dimension for skirt support structure of coke drums

NASA Astrophysics Data System (ADS)

Wang, Edward; Xia, Zihui

2018-03-01

The skirt-to-shell junction weld on coke drums is susceptible to fatigue failure due to severe thermal cyclic stresses. One method to decrease junction stress is to add slots near the top of the skirt, thereby reducing the local stiffness close to the weld. The most common skirt slot design is thin relative to its circumferential spacing. A new slot design, which is significantly wider, is proposed. In this study, thermal-mechanical elastoplastic 3-D finite element models of coke drums are created to analyze the effect of different skirt designs on the stress/strain field near the shell-to-skirt junction weld, as well as any other critical stress locations in the overall skirt design. The results confirm that the inclusion of the conventional slot design effectively reduces stress in the junction weld. However, it has also been found that the critical stress location migrates from the shell-to-skirt junction weld to the slot ends. A method is used to estimate the fatigue life near the critical areas of each skirt slot design. It is found that wider skirt slots provide a significant improvement on fatigue life in the weld and slot area.

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.

Aft Skirt Electrical Umbilical (ASEU) and Vehicle Support Post (

NASA Image and Video Library

2016-12-09

A view from underneath one of the vertical support posts for NASA's Space Launch System rocket. Two after skirt electrical umbilicals (ASEUs) and the first of the vertical support post were transported by flatbed truck from the Launch Equipment Test Facility to the Mobile Launcher Yard as NASA's Kennedy Space Center in Florida. The ASEUs and the VSP underwent a series of tests to confirm they are functioning properly and ready to support the SLS for launch. The ASEUs will connect to the SLS rocket at the bottom outer edge of each booster and provide electrical power and data connections to the rocket until it lifts off from the launch pad. The eight VSPs will support the load of the solid rocket boosters, with four posts for each of the boosters. The center’s Engineering Directorate and the Ground Systems Development and Operations Program are overseeing processing and testing of the umbilicals.

Skirted projectiles for railguns

DOEpatents

Hawke, Ronald S.; Susoeff, Allan R.

1994-01-01

A single skirt projectile (20) having an insulating skirt (22) at its rear, or a dual trailing skirt projectile (30, 40, 50, 60) having an insulating skirt (32, 42, 52, 62) succeeded by an arc extinguishing skirt (34, 44, 54, 64), is accelerated by a railgun accelerator 10 having a pair of parallel conducting rails (1a, 1b) which are separated by insulating wall spacers (11). The insulating skirt (22, 32, 42, 52, 62) includes a plasma channel (38). The arc extinguishing skirt (34, 44, 54, 64) interrupts the conduction that occurs in the insulating skirt channel (38) by blocking the plasma arc (3) from conducting current from rail to rail (1a, 1b) at the rear of the projectile (30, 40, 50, 60). The arc extinguishing skirt may be comprised of two plates (36a, 36b) which form a horseshoe wherein the plates are parallel to the rails (1a, b); a chisel-shape design; cross-shaped, or it may be a cylindrical (64). The length of the insulating skirt channel is selected such that there is sufficient plasma in the channel to enable adequate current conduction between the rails (1a, 1b).

Skirted projectiles for railguns

DOEpatents

Hawke, R.S.; Susoeff, A.R.

1994-01-04

A single skirt projectile (20) having an insulating skirt (22) at its rear, or a dual trailing skirt projectile (30, 40, 50, 60) having an insulating skirt (32, 42, 52, 62) succeeded by an arc extinguishing skirt (34, 44, 54, 64), is accelerated by a railgun accelerator 10 having a pair of parallel conducting rails (1a, 1b) which are separated by insulating wall spacers (11). The insulating skirt (22, 32, 42, 52, 62) includes a plasma channel (38). The arc extinguishing skirt (34, 44, 54, 64) interrupts the conduction that occurs in the insulating skirt channel (38) by blocking the plasma arc (3) from conducting current from rail to rail (1a, 1b) at the rear of the projectile (30, 40, 50, 60). The arc extinguishing skirt may be comprised of two plates (36a, 36b) which form a horseshoe wherein the plates are parallel to the rails (1a, b); a chisel-shape design; cross-shaped, or it may be a cylindrical (64). The length of the insulating skirt channel is selected such that there is sufficient plasma in the channel to enable adequate current conduction between the rails (1a, 1b).

KENNEDY SPACE CENTER, FLA. - The camera installed on the aft skirt of a solid rocket booster is seen here, framed by the railing. The installation is 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. - The camera installed on the aft skirt of a solid rocket booster is seen here, framed by the railing. The installation is 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.

Space Shuttle STS-1 SRB damage investigation

NASA Technical Reports Server (NTRS)

Nevins, C. D.

1982-01-01

The physical damage incurred by the solid rocket boosters during reentry on the initial space shuttle flight raised the question of whether the hardware, as designed, would yield the low cost per flight desired. The damage was quantified, the cause determined and specific design changes recommended which would preclude recurrence. Flight data, postflight analyses, and laboratory hardware examinations were used. The resultant findings pointed to two principal causes: failure of the aft skirt thermal curtain at the onset of reentry aerodynamic heating, and overloading of the aft shirt stiffening rings during water impact. Design changes were recommended on both the thermal curtain and the aft skirt structural members to prevent similar damage on future missions.

STS-40 orbiter Columbia payload bay aft firewall and thermal insulation

NASA Image and Video Library

1999-06-09

STS040-031-030 (5-14 June 1991) --- Early on the first day of STS-40, the crew noticed that some of the thermal material on the aft firewall had loosened. They shot this 35mm frame of the area, which proved to pose no problems for the flight.

24 CFR 3285.504 - Skirting.

Code of Federal Regulations, 2010 CFR

2010-04-01

... MODEL MANUFACTURED HOME INSTALLATION STANDARDS Optional Features § 3285.504 Skirting. (a) Skirting, if... skirting within 6 inches of the ground must be pressure-treated in accordance with AWPA Standard U1...

24 CFR 3285.504 - Skirting.

Code of Federal Regulations, 2012 CFR

2012-04-01

... MODEL MANUFACTURED HOME INSTALLATION STANDARDS Optional Features § 3285.504 Skirting. (a) Skirting, if... skirting within 6 inches of the ground must be pressure-treated in accordance with AWPA Standard U1...

24 CFR 3285.504 - Skirting.

Code of Federal Regulations, 2011 CFR

2011-04-01

... MODEL MANUFACTURED HOME INSTALLATION STANDARDS Optional Features § 3285.504 Skirting. (a) Skirting, if... skirting within 6 inches of the ground must be pressure-treated in accordance with AWPA Standard U1...

The flaming gypsy skirt injury.

PubMed

Leong, S C L; Emecheta, I E; James, M I

2007-01-01

On review of admissions over a 12-month period, we noted a significant number of women presenting with gypsy skirt burns. We describe all six cases to highlight the unique distribution of the wounds and the circumstances in which the accidents occurred. Four skirts were ignited by open fire heaters: two skirts ignited whilst the women were standing nearby, distracted with a telephone conversation; one brushed over the flame as she was walking past the heater; other whilst dancing in the lounge. One skirt was ignited by decorative candles placed on the floor during a social gathering. Another skirt was set alight by cigarette ember, whilst smoking in the toilet. Percentage surface area burned, estimated according to the rule of nines, showed that gypsy skirt burns were significant ranging from 7 to 14% total body surface area (TBSA) and averaging 9% TBSA. Two patients required allogenic split-skin grafts. Common sense care with proximity to naked flame is all that is needed to prevent this injury.

An evaluation of Orbital Workshop passive thermal control surfaces

NASA Technical Reports Server (NTRS)

Daniels, D. J.; Kawano, P. I.; Sieker, W. D.; Walters, D. E.; Witherspoon, G. F.; Grunditz, D. W.

1974-01-01

The optical properties of selected Orbital Workshop thermal control surfaces are discussed from the time of their installation through the end of the Skylab missions. The surfaces considered are the goldized Kapton tape on the habitation area sidewall, the S-13G white paint on the Workshop aft skirt, and the multilayer insulation system on the forward dome of the habitation area. A quantitative assessment of the effects of exposure to the ascent and orbital environments is made including the effects of rocket exhaust plume contamination. Although optical property degradation of the external surfaces was noted, satisfactory thermal performance was maintained throughout the Skylab missions.

STS-40 Columbia, OV-102, payload bay aft firewall and thermal insulation

NASA Image and Video Library

1991-06-14

STS040-31-029 (5-14 June 1991) --- This close-up 35mm scene of the aft firewall in the Space Shuttle Columbia's cargo bay reveals a piece of thermal insulation that had loosened. The crew discovered the loose blanket soon after opening the cargo bay doors on June 5, 1991.

Pressurized water reactor flow skirt apparatus

DOEpatents

Kielb, John F.; Schwirian, Richard E.; Lee, Naugab E.; Forsyth, David R.

2016-04-05

A pressurized water reactor vessel having a flow skirt formed from a perforated cylinder structure supported in the lower reactor vessel head at the outlet of the downcomer annulus, that channels the coolant flow through flow holes in the wall of the cylinder structure. The flow skirt is supported at a plurality of circumferentially spaced locations on the lower reactor vessel head that are not equally spaced or vertically aligned with the core barrel attachment points, and the flow skirt employs a unique arrangement of hole patterns that assure a substantially balanced pressure and flow of the coolant over the entire underside of the lower core support plate.

The response of Galileo aft cover components to laser radiation

NASA Technical Reports Server (NTRS)

Metzger, J. W.

1982-01-01

The aft region of the Galileo probe will be subjected to severe heat transfer rates dominated by the radiation contributions. To assess the response of several vehicle aft region components to thermal radiation, tests employing a 10 KW CO2 laser were conducted. The experiments evaluated the annulus/aft cover interface, the umbilical feedthrough assembly and the mortar cover seal assembly. Experimental evidence of the response of the phenolic nylon heatshield and quantitative measures of its effect on gap geometries of several vehicle components were acquired. In addition, qualitative measures of the survivability of the irradiated components were obtained.

Alternate Design of ITER Cryostat Skirt Support System

NASA Astrophysics Data System (ADS)

Pandey, Manish Kumar; Jha, Saroj Kumar; Gupta, Girish Kumar; Bhattacharya, Avik; Jogi, Gaurav; Bhardwaj, Anil Kumar

2017-04-01

The skirt support of ITER cryostat is a support system which takes all the load of cryostat cylinder and dome during normal and operational condition. The present design of skirt support has full penetration weld joints at the bottom (shell to horizontal plate joint). To fulfil the requirements of tolerances and control the welding distortions, we have proposed to change the full penetration weld into fillet weld. A detail calculation is done to check the feasibility and structural impact due to proposed design. The calculations provide the size requirements of fillet weld. To verify the structural integrity during most severe load case, finite element analysis (FEA) has been done in line with ASME section VIII division 2 [1]. By FEA ‘Plastic Collapse’ and ‘Local Failure’ modes has been assessed. 5° sector of skirt clamp has been modelled in CATIA V5 R21 and used in FEA. Fillet weld at shell to horizontal plate joint has been modelled and symmetry boundary condition at ± 2.5° applied. ‘Elastic Plastic Analysis’ has been performed for the most severe loading case i.e. Category IV loading. The alternate design of Cryostat Skirt support system has been found safe by analysis against Plastic collapse and Local Failure Modes with load proportionality factor 2.3. Alternate design of Cryostat skirt support system has been done and validated by FEA. As per alternate design, the proposal of fillet weld has been implemented in manufacturing.

Closeup view of the Solid Rocket Booster (SRB) Forward Skirt, ...

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

Close-up view of the Solid Rocket Booster (SRB) Forward Skirt, Frustum and Nose Cap mated assembly undergoing final preparations in the Solid Rocket Booster Assembly and Refurbishment Facility at Kennedy Space Center. In this view the access panel on the Forward Skirt is removed and you can see a small portion of the interior of the Forward Skirt. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Steam exit flow design for aft cavities of an airfoil

DOEpatents

Storey, James Michael; Tesh, Stephen William

2002-01-01

Turbine stator vane segments have inner and outer walls with vanes extending therebetween. The inner and outer walls have impingement plates. Steam flowing into the outer wall passes through the impingement plate for impingement cooling of the outer wall surface. The spent impingement steam flows into cavities of the vane having inserts for impingement cooling the walls of the vane. The steam passes into the inner wall and through the impingement plate for impingement cooling of the inner wall surface and for return through return cavities having inserts for impingement cooling of the vane surfaces. A skirt or flange structure is provided for shielding the steam cooling impingement holes adjacent the inner wall aerofoil fillet region of the nozzle from the steam flow exiting the aft nozzle cavities. Moreover, the gap between the flash rib boss and the cavity insert is controlled to minimize the flow of post impingement cooling media therebetween. This substantially confines outflow to that exiting via the return channels, thus furthermore minimizing flow in the vicinity of the aerofoil fillet region that may adversely affect impingement cooling thereof.

Forward Skirt Structural Testing on the Space Launch System (SLS) Program

NASA Technical Reports Server (NTRS)

Lohrer, J. D.; Wright, R. D.

2016-01-01

Structural testing was performed to evaluate heritage forward skirts from the Space Shuttle program for use on the Space Launch System (SLS) program. One forward skirt is located in each solid rocket booster. Heritage forward skirts are aluminum 2219 welded structures. Loads are applied at the forward skirt thrust post and ball assembly. Testing was needed because SLS ascent loads are roughly 40% higher than Space Shuttle loads. Testing objectives were to determine margins of safety, demonstrate reliability, and validate analytical models. Two forward skirts were structurally tested using the test configuration. The test stand applied loads to the thrust post. Four hydraulic actuators were used to apply axial load and two hydraulic actuators were used to apply radial and tangential loads. The first test was referred to as FSTA-1 (Forward Skirt Structural Test Article) and was performed in April/May 2014. The purpose of FSTA-1 was to verify the ultimate capability of the forward skirt subjected to ascent ultimate loads. Testing consisted of two liftoff load cases taken to 100% limit load followed by an ascent load case taken to 110% limit load. The forward skirt was unloaded to no load after each test case. Lastly, the forward skirt was tested to 140% limit and then to failure using the ascent loads. The second test was referred to as FSTA-2 and performed in July/August of 2014. The purpose of FSTA-2 was to verify the ultimate capability of the forward skirt subjected to liftoff ultimate loads. Testing consisted of six liftoff load cases taken to 100% limit load followed by the six liftoff cases taken to 140% limit load. Two ascent load cases were then tested to 100% limit load. The forward skirt was unloaded to no load after each test case. Lastly, the forward skirt was tested to 140% limit and then to failure using the ascent loads. The forward skirts on FSTA-1 and FSTA-2 successfully carried all applied liftoff and ascent load cases. Both FSTA-1 and FSTA-2 were

Using a wrap skirt to improve the pelvic examination experience.

PubMed

Neuhaus, Lilian R; Memeti, Elza; Schäffer, Marie-Kristin; Zimmermann, Roland; Schäffer, Leonhard

2016-05-01

The study aims were to analyze the experience of women and their physicians of nakedness when moving between changing room and examination chair and during pelvic examination itself, and to assess the protective benefit of a wrap skirt in alleviating the associated discomfort and vulnerability. We offered 1000 women a wrap skirt for pelvic examination and asked them to complete a post-procedure questionnaire. Physicians were invited to complete a similar but separate questionnaire. Data were analyzed using chi-squared contingency tables. A total of 425 women (43%, age 15-78 years) completed the questionnaire; 51% felt uncomfortable and embarrassed during the examination, Muslim women significantly more so (p < 0.001). Most women (n = 255; 58%) rated the wrap skirt a significant improvement; 69% requested it for future examinations, significantly more so if the physician was male rather than female (66% vs. 54%, p = 0.003). Even the one-third of women experiencing no discomfort reported improvement. Most examiners (n = 45; 56%) found the wrap skirt beneficial; 31 (38%) were unconvinced. Pelvic examination as practiced in many countries, on women naked from the waist down throughout, causes unnecessary embarrassment. A simple protective measure, such as a wrap skirt, significantly alleviates the discomfort and sense of vulnerability associated with nakedness. © 2016 Nordic Federation of Societies of Obstetrics and Gynecology.

Tuning thermal mismatch between turbine rotor parts with a thermal medium

DOEpatents

Schmidt, Mark Christopher

2001-01-01

In a turbine rotor, an aft shaft wheel and the final-stage wheel of the rotor are coupled together, including by a rabbeted joint. During shutdown and startup of the turbine, a thermal mismatch between the aft shaft wheel and final-stage wheel is avoided by respectively heating and cooling the aft shaft wheel to maintain the thermal mismatch within acceptable limits, thereby avoiding opening of the rabbeted joint and the potential for unbalancing the rotor and rotor vibration. The thermal medium may be supplied by piping in the aft bearing cavity into the cavity between the forward closure plate and the aft shaft wheel.

Core Stage Forward Skirt Umbilical Installation onto Mobile Laun

NASA Image and Video Library

2017-05-25

Construction workers assist as a crane lifts the Core Stage Forward Skirt Umbilical up for installation on the mobile launcher tower at NASA's Kennedy Space Center in Florida. The mobile launcher tower will be equipped with a number of lines, called umbilicals that will connect to the Space Launch System (SLS) rocket and Orion spacecraft for Exploration Mission-1 (EM-1). The CSFSU will be located at about the 180-foot level on the tower, above the liquid oxygen tank. The CSFSU is an umbilical that will swing into position to provide connections to the core stage forward skirt of the SLS rocket, and then swing away before launch. Its main purpose is to provide conditioned air/GN2 to the SLS core stage forward skirt cavity. The Ground Systems Development and Operations Program is overseeing installation of the umbilicals.

Core Stage Forward Skirt Umbilical Installation onto Mobile Laun

NASA Image and Video Library

2017-05-25

A crane has been attached to the Core Stage Forward Skirt Umbilical (CSFSU) to lift it up for installation on the mobile launcher tower at NASA's Kennedy Space Center in Florida. The mobile launcher tower will be equipped with a number of lines, called umbilicals that will connect to the Space Launch System (SLS) rocket and Orion spacecraft for Exploration Mission-1 (EM-1). The CSFSU will be located at about the 180-foot level on the tower, above the liquid oxygen tank. The CSFSU is an umbilical that will swing into position to provide connections to the core stage forward skirt of the SLS rocket, and then swing away before launch. Its main purpose is to provide conditioned air/GN2 to the SLS core stage forward skirt cavity. The Ground Systems Development and Operations Program is overseeing installation of the umbilicals.

Core Stage Forward Skirt Umbilical Installation onto Mobile Laun

NASA Image and Video Library

2017-05-25

Cranes and rigging are being used to lift up the Core Stage Forward Skirt Umbilical (CSFSU) for installation on the mobile launcher tower at NASA's Kennedy Space Center in Florida. The mobile launcher tower will be equipped with a number of lines, called umbilicals that will connect to the Space Launch System (SLS) rocket and Orion spacecraft for Exploration Mission-1 (EM-1). The CSFSU will be located at about the 180-foot level on the tower, above the liquid oxygen tank. The CSFSU is an umbilical that will swing into position to provide connections to the core stage forward skirt of the SLS rocket, and then swing away before launch. Its main purpose is to provide conditioned air/GN2 to the SLS core stage forward skirt cavity. The Ground Systems Development and Operations Program is overseeing installation of the umbilicals.

Core Stage Forward Skirt Umbilical Installation onto Mobile Laun

NASA Image and Video Library

2017-05-25

Cranes and rigging are being used to lift the Core Stage Forward Skirt Umbilical (CSFSU) into position for installation on the mobile launcher tower at NASA's Kennedy Space Center in Florida. The mobile launcher tower will be equipped with a number of lines, called umbilicals that will connect to the Space Launch System (SLS) rocket and Orion spacecraft for Exploration Mission-1 (EM-1). The CSFSU will be located at about the 180-foot level on the tower, above the liquid oxygen tank. The CSFSU is an umbilical that will swing into position to provide connections to the core stage forward skirt of the SLS rocket, and then swing away before launch. Its main purpose is to provide conditioned air/GN2 to the SLS core stage forward skirt cavity. The Ground Systems Development and Operations Program is overseeing installation of the umbilicals.

Core Stage Forward Skirt Umbilical Installation onto Mobile Laun

NASA Image and Video Library

2017-05-25

A construction worker welds a metal part during installation of the Core Stage Forward Skirt Umbilical on the mobile launcher tower at NASA's Kennedy Space Center in Florida. The mobile launcher tower will be equipped with a number of lines, called umbilicals that will connect to the Space Launch System (SLS) rocket and Orion spacecraft for Exploration Mission-1 (EM-1). The CSFSU will be located at about the 180-foot level on the tower, above the liquid oxygen tank. The CSFSU is an umbilical that will swing into position to provide connections to the core stage forward skirt of the SLS rocket, and then swing away before launch. Its main purpose is to provide conditioned air/GN2 to the SLS core stage forward skirt cavity. The Ground Systems Development and Operations Program is overseeing installation of the umbilicals.

Core Stage Forward Skirt Umbilical Installation onto Mobile Laun

NASA Image and Video Library

2017-05-25

Construction workers assist as a crane lifts the Core Stage Forward Skirt Umbilical into position for installation on the mobile launcher tower at NASA's Kennedy Space Center in Florida. The mobile launcher tower will be equipped with a number of lines, called umbilicals that will connect to the Space Launch System (SLS) rocket and Orion spacecraft for Exploration Mission-1 (EM-1). The CSFSU will be located at about the 180-foot level on the tower, above the liquid oxygen tank. The CSFSU is an umbilical that will swing into position to provide connections to the core stage forward skirt of the SLS rocket, and then swing away before launch. Its main purpose is to provide conditioned air/GN2 to the SLS core stage forward skirt cavity. The Ground Systems Development and Operations Program is overseeing installation of the umbilicals.

Core Stage Forward Skirt Umbilical Installation onto Mobile Laun

NASA Image and Video Library

2017-05-25

Seeming to hang in midair, the Core Stage Forward Skirt Umbilical (CSFSU) is lifted high up by crane for installation on the mobile launcher tower at NASA's Kennedy Space Center in Florida. The mobile launcher tower will be equipped with a number of lines, called umbilicals that will connect to the Space Launch System rocket and Orion spacecraft for Exploration Mission-1 (EM-1). The CSFSU will be located at about the 180-foot level on the tower, above the liquid oxygen tank. The CSFSU is an umbilical that will swing into position to provide connections to the core stage forward skirt of the SLS rocket, and then swing away before launch. Its main purpose is to provide conditioned air/GN2 to the SLS core stage forward skirt cavity. The Ground Systems Development and Operations Program is overseeing installation of the umbilicals.

Forward Skirt Structural Testing on the Space Launch System (SLS) Program

NASA Technical Reports Server (NTRS)

Lohrer, Joe; Wright, R. D.

2016-01-01

Introduction: (a) Structural testing was performed to evaluate Space Shuttle heritage forward skirts for use on the Space Launch System (SLS) program, (b) Testing was required because SLS loads are approximately 35% greater than shuttle loads; and (c) Two forwards skirts were tested to failure.

Detail view of the flight deck looking aft. The aft ...

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

Detail view of the flight deck looking aft. The aft viewing windows are uncovered in this view and look out towards the payload bay. The overhead viewing windows have exterior covers in place in this view. The aft flight deck contains displays and controls for executing maneuvers for rendezvous, docking, payload deployment and retrieval, payload monitoring and the remote manipulator arm controls. Payload bay doors are also operated from this location. This view was taken in the Orbiter Processing Facility at the Kennedy Space Center. - Space Transportation System, Orbiter Discovery (OV-103), Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

The buoyancy-driven motion of a single skirted bubble or drop rising through a viscous liquid

NASA Astrophysics Data System (ADS)

Ohta, Mitsuhiro; Sussman, Mark

2012-11-01

The buoyancy-driven motion of a single skirted bubble or drop rising through a viscous liquid is computationally explored by way of 3d-axisymmetric computations. The Navier-Stokes equations for incompressible two-fluid flow are solved numerically in which the coupled level-set and volume-of-fluid method is used to simulate the deforming bubble/drop boundary and the interface jump conditions on the deforming boundary are enforced through a sharp interface numerical treatment. Dynamic, block structured adaptive grid refinement is employed in order to sufficiently resolve the thin skirts. Results on the sensitivity of the thickness of trailing bubble/drop skirts to the density ratio and viscosity ratio are reported. It is shown that both the density ratio (not the density difference) and the viscosity ratio effect the skirt thickness. Previous theory for predicting skirt thickness can be refined as a result of our calculations. It is also discovered that the formation of thin skirts for bubbles and drops have little effect on the rise velocity. In other words, the measured Re number for cases without skirt formation have almost the same values for Re as cases with a thin skirt.

View aft of compartment D23, aft steering station; note steering ...

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

View aft of compartment D-23, aft steering station; note steering unit with crosshead and shaft bearing supports. Note framing supports for armored protective deck at top of photo. (p60) - USS Olympia, Penn's Landing, 211 South Columbus Boulevard, Philadelphia, Philadelphia County, PA

Real-Time Measurements of Aft Dome Insulation Erosion on Space Shuttle Reusable Solid Rocket Motor

NASA Technical Reports Server (NTRS)

McWhorter, Bruce; Ewing, Mark; Albrechtsen, Kevin; Noble, Todd; Longaker, Matt

2004-01-01

Real-time erosion of aft dome internal insulation was measured with internal instrumentation on a static test of a lengthened version of the Space Shuffle Reusable Solid Rocket Motor (RSRM). This effort marks the first time that real-time aft dome insulation erosion (Le., erosion due to the combined effects of thermochemical ablation and mechanical abrasion) was measured in this kind of large motor static test [designated as Engineering Test Motor number 3 (ETM3)I. This paper presents data plots of the erosion depth versus time. The data indicates general erosion versus time behavior that is in contrast to what would be expected from earlier analyses. Engineers have long known that the thermal environment in the aft dome is severe and that the resulting aft dome insulation erosion is significant. Models of aft dome erosion involve a two-step process of computational fluid dynamics (CFD) modeling and material ablation modeling. This modeling effort is complex. The time- dependent effects are difficult to verify with only prefire and postfire insulation measurements. Nozzle vectoring, slag accumulation, and changing boundary conditions will affect the time dependence of aft dome erosion. Further study of this data and continued measurements on future motors will increase our understanding of the aft dome flow and erosion environment.

Skirt clouds associated with the soufriere eruption of 17 april 1979.

PubMed

Barr, S

1982-06-04

A fortuitous and dramatic photograph of the Soufriere eruption column of 17 April 1979 displays a series of highly structured skirt clouds. The gentle distortion of thin, quasi-horizontal layers of moist air has been documented in meteorological situations. It is proposed that at St. Vincent subhorizontal layers of moist air were intensely deformed by the rapidly rising eruption column and were carried to higher altitudes, where they condensed to form the skirt clouds.

Orion EM-1 Forward Skirt Move from Hangar AF to BFF

NASA Image and Video Library

2017-08-30

The Exploration Mission-1 (EM-1) left-hand forward skirt for NASA's Space Launch System (SLS) solid rocket boosters arrives inside the high bay at the Booster Fabrication Facility (BFF) at NASA's Kennedy Space Center in Florida. In the BFF, the forward skirt will be inspected and prepared for use on the left-hand solid rocket booster for EM-1. NASA's Orion spacecraft will fly atop the SLS rocket on its first uncrewed flight test.

Forward Skirt Structural Testing on the Space Launch System (SLS) Program

NASA Technical Reports Server (NTRS)

Lohrer, J. D.; Wright, R. D.

2016-01-01

Structural testing was performed to evaluate heritage forward skirts from the Space Shuttle program for use on the NASA Space Launch System (SLS) program. Testing was needed because SLS ascent loads are 35% higher than Space Shuttle loads. Objectives of testing were to determine margins of safety, demonstrate reliability, and validate analytical models. Testing combined with analysis was able to show heritage forward skirts were acceptable to use on the SLS program.

Ares I-X Ascent Base Environments

NASA Technical Reports Server (NTRS)

Mobley, B. L.; Bender, R. L.; Canabal, F.; Smith, Sheldon D.

2011-01-01

Plume induced base heating environments were measured during the flight of the NASA Constellation Ares I-X developmental launch vehicle, successfully flown on October 28, 2009. The Ares IX first stage is a four segment Space Shuttle derived booster with base consisting of a flared aft skirt, deceleration and tumble motors, and a thermal curtain surrounding the first stage 7.2 area ratio nozzle. Developmental Flight Instrumentation (DFI) consisted of radiometers, calorimeters, pressure transducers and gas temperature probes installed on the aft skirt and nozzle to measure the base environments. In addition, thermocouples were also installed between the layers of the flexible thermal curtain to provide insight into the curtain response to the base environments and to assist in understanding curtain failure during reentry. Plume radiation environment predictions were generated by the Reverse Monte Carlo (RMC) code and the convective base heating predictions utilized heritage MSFC empirical methods. These predictions were compared to the DFI data and results from the flight videography. Radiation predictions agreed with the flight measured data early in flight but gauge failures prevented high altitude comparisons. The convective environment comparisons demonstrated the need to improve the prediction methodology; particularly for low altitude, local plume recirculation. The convective comparisons showed relatively good agreement at altitudes greater than 50,000 feet.

Orion EM-1 Forward Skirt Move from Hangar AF to BFF

NASA Image and Video Library

2017-08-30

The Exploration Mission-1 (EM-1) left-hand forward skirt for NASA's Space Launch System (SLS) solid rocket boosters arrives at the entrance to the high bay at the Booster Fabrication Facility (BFF) at NASA's Kennedy Space Center in Florida. In the BFF, the forward skirt will be inspected and prepared for use on the left-hand solid rocket booster for EM-1. NASA's Orion spacecraft will fly atop the SLS rocket on its first uncrewed flight test.

Design and evaluation of artificial cornea with core-skirt design using polyhydroxyethyl methacrylate and graphite.

PubMed

Sinha, Mukty; Gupte, Tanvi

2017-06-10

Artificial cornea is the effective treatment option for corneal blindness. One of the challenges with the artificial cornea is limited, or no tissue integration necessitates reimplantation due to necrosis or corneal melting. We propose here a new formulation approach for core-skirt incorporating graphite in the outer skirt region to improve cell adhesion. Hydroxyethyl methacrylate (HEMA) and ethylene glycol dimethacrylate were procured from Sigma-Aldrich. Polyhydroxyethyl methacrylate (PHEMA) was synthesized by free radical polymerization of HEMA. PHEMA hydrogel core with graphite incorporated skirt was developed with the help of mould and spacer. Pores were introduced into the skirt by salt leaching technique using sodium chloride as porogen. The porous skirt was improved for its aesthetic appeal of black colour and mechanical strength to sustain intraocular pressure by incorporating graphite. The material properties of the newly developed design were evaluated in terms of wetting behaviour, mechanical strength, water vapour permeability, degradation profile and cell adhesion. The polymerization of HEMA was confirmed by thin layer chromatography and FTIR. Water content of the polymeric film was optimized at 50% where maximum transparency with required refractive index of 1.4 was obtained. The concentration of salt vital for the essential porosity was also optimized using optical microscopy and scanning electron microscopy. Other properties, namely mechanical strength, water vapour transmission rate and degradation behaviour, showed that the developed design is suitable for ocular applications. Furthermore, cell adhesion study confirmed tissue adhesion in the skirt region but absent in the core. The core-skirt design may offer an efficient cornea replacement alternative with enhanced tissue integration in addition to desired mechanical behaviour with a clear and aesthetic vision.

Clinicopathological, endoscopic, and molecular characteristics of the "skirt" - a new entity of lesions at the margin of laterally spreading tumors.

PubMed

Osera, Shozo; Fujii, Satoshi; Ikematsu, Hiroaki; Miyamoto, Hideaki; Oono, Yasuhiro; Yano, Tomonori; Ochiai, Atsushi; Yoshino, Takayuki; Ohtsu, Atsushi; Kaneko, Kazuhiro

2016-05-01

A slightly elevated flat lesion with wide pits has occasionally been observed at the margin of laterally spreading tumors (LSTs) and is known as a "skirt." The aim of this study was to evaluate the clinicopathological, endoscopic, and genetic characteristics of a skirt. Consecutive LSTs were examined to evaluate the pathological, endoscopic, and genetic characteristics. Pathological characteristics, including the dimension of the cryptic opening (DCO), width of the individual gland (WIG), DCO to WIG ratio, and microvessel diameter were elucidated and compared with those of hyperplastic polyps, low grade dysplasia (LGD), and normal mucosa. The endoscopic findings of pit and microvascular patterns were assessed. Gene mutation analyses were performed for the KRAS, BRAF, NRAS, and PIK3CA genes. A skirt was identified in 35 of 1023 LSTs, and 80 % of lesions with a skirt had a component of either intramucosal or submucosal adenocarcinoma. The DCO, WIG, and DCO to WIG ratio of the skirt were significantly larger than those of other lesions. The microvessel diameters in skirts were significantly smaller than those in LGDs. Regarding the endoscopic findings, 30 skirts showed pits with a coral reef-like appearance, and all skirt regions were found to have a type I capillary pattern. KRAS mutation at codon 146 was found in the nodular part in one of five LSTs with a skirt. The skirt is a newly identified lesion distinct from hyperplastic polyps and LGDs, suggesting the presence of a novel pathway for rectal carcinogenesis from LSTs with a skirt. © Georg Thieme Verlag KG Stuttgart · New York.

Orion EM-1 Forward Skirt Transport from Hangar AF to BFF

NASA Image and Video Library

2017-08-30

The Exploration Mission-1 (EM-1) left-hand forward skirt for NASA's Space Launch System (SLS) solid rocket boosters is transported by truck to the Booster Fabrication Facility (BFF) at NASA's Kennedy Space Center in Florida from Hangar AE at Cape Canaveral Air Force Station. In the BFF, the forward skirt will be inspected and prepared for use on the left-hand solid rocket booster for EM-1. NASA's Orion spacecraft will fly atop the SLS rocket on its first uncrewed flight test.

Orion EM-1 Forward Skirt Move from Hangar AF to BFF

NASA Image and Video Library

2017-08-30

The Exploration Mission-1 (EM-1) left-hand forward skirt for NASA's Space Launch System (SLS) solid rocket boosters arrives at the Booster Fabrication Facility (BFF) at NASA's Kennedy Space Center in Florida from Hangar AE at Cape Canaveral Air Force Station. In the BFF, the forward skirt will be inspected and prepared for use on the left-hand solid rocket booster for EM-1. NASA's Orion spacecraft will fly atop the SLS rocket on its first uncrewed flight test.

Transient thermal stresses analysis and thermal fatigue damage evaluation for skirt attachment of coke drum

NASA Astrophysics Data System (ADS)

Ambarita, H.; Siahaan, A. S.; Kawai, H.; Daimaruya, M.

2018-02-01

In the last decade, the demand for delayed coking capacity has been steadily increasing. The trend in the past 15 to 20 years has been for operators to try to maximize the output of their units by reducing cycle times. This mode of operation can result in very large temperature gradients within the drums during preheating stage and even more so during the quench cycle. This research provide the optimization estimation of fatigue life due to each for the absence of preheating stage and cutting stage. In the absence of preheating stage the decreasing of fatigue life is around 19% and the increasing of maximum stress in point 5 of shell-to-skirt junction is around 97 MPa. However for the absence of cutting stage it was found that is more severe compare to normal cycle. In this adjustment fatigue life reduce around 39% and maximum stress is increased around 154 MPa. It can concluded that for cycle optimization, eliminating preheating stage possibly can become an option due to the increasing demand of delayed coking process.

FitSKIRT: genetic algorithms to automatically fit dusty galaxies with a Monte Carlo radiative transfer code

NASA Astrophysics Data System (ADS)

De Geyter, G.; Baes, M.; Fritz, J.; Camps, P.

2013-02-01

We present FitSKIRT, a method to efficiently fit radiative transfer models to UV/optical images of dusty galaxies. These images have the advantage that they have better spatial resolution compared to FIR/submm data. FitSKIRT uses the GAlib genetic algorithm library to optimize the output of the SKIRT Monte Carlo radiative transfer code. Genetic algorithms prove to be a valuable tool in handling the multi- dimensional search space as well as the noise induced by the random nature of the Monte Carlo radiative transfer code. FitSKIRT is tested on artificial images of a simulated edge-on spiral galaxy, where we gradually increase the number of fitted parameters. We find that we can recover all model parameters, even if all 11 model parameters are left unconstrained. Finally, we apply the FitSKIRT code to a V-band image of the edge-on spiral galaxy NGC 4013. This galaxy has been modeled previously by other authors using different combinations of radiative transfer codes and optimization methods. Given the different models and techniques and the complexity and degeneracies in the parameter space, we find reasonable agreement between the different models. We conclude that the FitSKIRT method allows comparison between different models and geometries in a quantitative manner and minimizes the need of human intervention and biasing. The high level of automation makes it an ideal tool to use on larger sets of observed data.

Bioactive composite for keratoprosthesis skirt.

PubMed

Laattala, Kaisa; Huhtinen, Reeta; Puska, Mervi; Arstila, Hanna; Hupa, Leena; Kellomäki, Minna; Vallittu, Pekka K

2011-11-01

In this study, the fabrication and properties of a synthetic keratoprosthesis skirt for use in osteo-odonto-keratoprosthesis (OOKP) surgery are discussed. In the search for a new material concept, bioactive glass and polymethyl methacrylate (PMMA)-based composites were prepared. Three different bioactive glasses (i.e. 45S5, S53P4 and 1-98) and one slowly resorbing glass, FL107, with two different forms (i.e. particles and porous glass structures) were employed in the fabrication of specimens. In in vitro studies, the dissolution behaviour in simulated aqueous humour, compressive properties, and pore formation of the composites were investigated. According to the results, FL107 dissolved very slowly (2.4% of the initial glass content in three weeks); thus, the pore formation of the FL107 composite was also observed to be restricted. The dissolution rates of the bioactive glass-PMMA composites were greater (12%-17%). These faster dissolving bioactive glass particles caused some porosity on the outermost surfaces of the composite. The slight surface porosity was also confirmed by a decrease in compressive properties. During six weeks' in vitro dissolution, the compressive strength of the test specimens containing particles decreased by 22% compared to values in dry conditions (90-107 MPa). These results indicate that the bioactive composites could be stable synthetic candidates for a keratoprosthesis skirt in the treatment of severely damaged or diseased cornea. Copyright © 2011 Elsevier Ltd. All rights reserved.

Space shuttle solid rocket booster water entry cavity collapse loads

NASA Technical Reports Server (NTRS)

Keefe, R. T.; Rawls, E. A.; Kross, D. A.

1982-01-01

Solid rocket booster cavity collapse flight measurements included external pressures on the motor case and aft skirt, internal motor case pressures, accelerometers located in the forward skirt, mid-body area, and aft skirt, as well as strain gages located on the skin of the motor case. This flight data yielded applied pressure longitudinal and circumferential distributions which compare well with model test predictions. The internal motor case ullage pressure, which is below atmospheric due to the rapid cooling of the hot internal gas, was more severe (lower) than anticipated due to the ullage gas being hotter than predicted. The structural dynamic response characteristics were as expected. Structural ring and wall damage are detailed and are considered to be attributable to the direct application of cavity collapse pressure combined with the structurally destabilizing, low internal motor case pressure.

AFT-QuEST Consortium Yearbook. Proceedings of the AFT-QuEST Consortium (April 22-26, 1973).

ERIC Educational Resources Information Center

American Federation of Teachers, Washington, DC.

This document is a report on the proceedings of the 1973 American Federation of Teachers-Quality Educational Standards in Teaching (AFT-QuEST) consortium sponsored by the AFT. Included in this document are the texts of speeches and outlines of workshops and iscussions. The document is divided into the following sections: goals, major proposals,…

Building No. 918, detail of skirt board and concrete post ...

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

Building No. 918, detail of skirt board and concrete post foundation with termite shield - Presidio of San Francisco, Enlisted Men's Barracks Type, West end of Crissy Field, between Pearce & Maudlin Streets, San Francisco, San Francisco County, CA

Piston-Skirt Lubrication System For Compressor

NASA Technical Reports Server (NTRS)

Schroeder, Edgar C.; Burzynski, Marion, Jr.

1994-01-01

Piston-skirt lubrication system provides steady supply of oil to piston rings of gas compressor. No need for oil-filled crankcase or external oil pump. Instead, part of each piston acts as its own oil pump circulating oil from reservoir. Annular space at bottom of piston and cylinder constitutes working volume of small oil pump. Depending on application, reservoir open to atmosphere, or sealed and pressurized in bellows to prevent contact between oil and atmosphere. Filter removes particles worn away from piston rings and cylinder wall during normal operation.

Core Stage Forward Skirt Umbilical Installation onto Mobile Laun

NASA Image and Video Library

2017-06-30

Just north of the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida, the core stage forward skirt umbilical is installed on the mobile launcher. The mobile launcher is designed to support the assembly, testing and check-out of the agency's Space Launch System (SLS) rocket and the Orion spacecraft.

Core Stage Forward Skirt Umbilical Installation onto Mobile Laun

NASA Image and Video Library

2017-06-30

Just north of the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida, technicians install the core stage forward skirt umbilical on the mobile launcher. The mobile launcher is designed to support the assembly, testing and check-out of the agency's Space Launch System (SLS) rocket and the Orion spacecraft.

Core Stage Forward Skirt Umbilical Installation onto Mobile Launcher

NASA Image and Video Library

2017-06-29

Just north of the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida, the core stage forward skirt umbilical is installed on the mobile launcher. The mobile launcher is designed to support the assembly, testing and check-out of the agency's Space Launch System (SLS) rocket and the Orion spacecraft.

KSC-2009-3690

NASA Image and Video Library

2009-06-12

CAPE CANAVERAL, Fla. – In the Rotation, Processing, and Surge Facility at NASA's Kennedy Space Center in Florida, the Ares I-X aft skirt is mated to the aft segment. The complete Ares I-X will be assembled in the Vehicle Assembly Building. The launch of Ares I-X is targeted for August 2009. Photo credit: NASA/Jack Pfaller

KSC-2009-3692

NASA Image and Video Library

2009-06-12

CAPE CANAVERAL, Fla. – In the Rotation, Processing, and Surge Facility at NASA's Kennedy Space Center in Florida, the Ares I-X aft skirt is mated to the aft segment. The complete Ares I-X will be assembled in the Vehicle Assembly Building. The launch of Ares I-X is targeted for August 2009. Photo credit: NASA/Jack Pfaller

KSC-2009-3691

NASA Image and Video Library

2009-06-12

CAPE CANAVERAL, Fla. – In the Rotation, Processing, and Surge Facility at NASA's Kennedy Space Center in Florida, the Ares I-X aft skirt is mated to the aft segment. The complete Ares I-X will be assembled in the Vehicle Assembly Building. The launch of Ares I-X is targeted for August 2009. Photo credit: NASA/Jack Pfaller

Commander Brand sleeps on aft flight deck

NASA Technical Reports Server (NTRS)

1982-01-01

Commander Brand, with hands folded in front of his chest, sleeps on aft flight deck. Brand's head is just above aft flight deck floor with his back to onorbit station panels. The back and feet of a second crewmember appear next to Brand.

ARC-1980-AC80-0107-2

NASA Image and Video Library

1980-02-06

The first solid rocket booster solid motor segemnts to arrive at KSC, the left and right hand aft segments are off-loaded into High Bay 4 in the Vehicle Assembly Building and mated to their respective SRB aft skirts. The two aft assemblies will support the entire 150 foot tall solid boosters, in turn supporting the external tank and Orbiter Columbia on the Mobile Launcher Platform, for the first orbital flight test of the Space Shuttle.

ARC-1980-AC80-0107-3

NASA Image and Video Library

1980-02-06

The first solid rocket booster solid motor segemnts to arrive at KSC, the left and right hand aft segments are off-loaded into High Bay 4 in the Vehicle Assembly Building and mated to their respective SRB aft skirts. The two aft assemblies will support the entire 150 foot tall solid boosters, in turn supporting the external tank and Orbiter Columbia on the Mobile Launcher Platform, for the first orbital flight test of the Space Shuttle.

KSC-2009-3586

NASA Image and Video Library

2009-06-08

CAPE CANAVERAL, Fla. – The Ares I-X aft skirt moves past the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida on its way to the Rotation, Processing and Surge Facility. In the RPSF, it will be stacked with the aft motor to form the aft assembly. The complete Ares I-X will be assembled in the Vehicle Assembly Building. The launch of Ares I-X is targeted for August 2009. Photo credit: NASA/Jim Grossmann

KSC-2009-3587

NASA Image and Video Library

2009-06-08

CAPE CANAVERAL, Fla. – The Ares I-X aft skirt moves past the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida on its way to the Rotation, Processing and Surge Facility. In the RPSF, it will be stacked with the aft motor to form the aft assembly. The complete Ares I-X will be assembled in the Vehicle Assembly Building. The launch of Ares I-X is targeted for August 2009. Photo credit: NASA/Jim Grossmann

PHOTOGRAPHER: KSC The first solid rocket booster solid motor segemnts to arrive at KSC, the left and

NASA Technical Reports Server (NTRS)

1980-01-01

PHOTOGRAPHER: KSC The first solid rocket booster solid motor segemnts to arrive at KSC, the left and right hand aft segments are off-loaded into High Bay 4 in the Vehicle Assembly Building and mated to their respective SRB aft skirts. The two aft assemblies will support the entire 150 foot tall solid boosters, in turn supporting the external tank and Orbiter Columbia on the Mobile Launcher Platform, for the first orbital flight test of the Space Shuttle.

Photographer: KSC The first solid rocket booster solid motor segemnts to arrive at KSC, the left and

NASA Technical Reports Server (NTRS)

1980-01-01

Photographer: KSC The first solid rocket booster solid motor segemnts to arrive at KSC, the left and right hand aft segments are off-loaded into High Bay 4 in the Vehicle Assembly Building and mated to their respective SRB aft skirts. The two aft assemblies will support the entire 150 foot tall solid boosters, in turn supporting the external tank and Orbiter Columbia on the Mobile Launcher Platform, for the first orbital flight test of the Space Shuttle.

Core Stage Forward Skirt Umbilical Installation onto Mobile Laun

NASA Image and Video Library

2017-06-30

Just north of the Vehicle Assembly Building at NASA's Kennedy Space Center in Florida, a crane lifts the core stage forward skirt umbilical for installation onto the mobile launcher. The mobile launcher is designed to support the assembly, testing and check-out of the agency's Space Launch System (SLS) rocket and the Orion spacecraft.

Design of a space shuttle structural dynamics model

NASA Technical Reports Server (NTRS)

1972-01-01

A 1/8 scale structural dynamics model of a parallel burn space shuttle has been designed. Basic objectives were to represent the significant low frequency structural dynamic characteristics while keeping the fabrication costs low. The model was derived from the proposed Grumman Design 619 space shuttle. The design includes an orbiter, two solid rocket motors (SRM) and an external tank (ET). The ET consists of a monocoque LO2 tank an interbank skirt with three frames to accept SRM attachment members, an LH2 tank with 10 frames of which 3 provide for orbiter attachment members, and an aft skirt with on frame to provide for aft SRM attachment members. The frames designed for the SRM attachments are fitted with transverse struts to take symmetric loads.

AFT: Extending Solar Cycle Prediction with Data Assimilation

NASA Astrophysics Data System (ADS)

Upton, L.; Hathaway, D. H.

2017-12-01

The Advective Flux Transport (AFT) model is an innovative surface flux transport model that simulates the evolution of the radial magnetic field on the surface of the Sun. AFT was designed to be as realistic as possible by 1: incorporating the observed surface flows (meridional flow, differential rotation, and an explicit evolving convective pattern) and by 2: using data assimilation to incorporate the observed magnetic fields directly from line-of-sight (LOS) magnetograms. AFT has proven to be successful in simulating the evolution of the surface magnetic fields on both short time scales (days-weeks) as well as for long time scales (years). In particular, AFT has been shown to accurately predict the evolution of the Sun's dipolar magnetic field 3-5 years in advance. Since the Sun's polar magnetic field strength at solar cycle minimum is the best indicator of the amplitude of the next cycle, this has in turn extended our ability to make solar cycle predictions to 3-5 years before solar minimum occurs. Here, we will discuss some of the challenges of implementing data assimilation into AFT. We will also discuss the role of data assimilation in advancing solar cycle predictive capability.

Enabling a Better Aft Heat Shield Solution for Future Mars Science Laboratory Class Vehicles

NASA Technical Reports Server (NTRS)

McGuire, Mary K.; Covington, Melmoth A.; Goldstein, Howard E.; Arnold, James O.; Beck, Robin

2013-01-01

System studies are described that compare masses and estimated manufacturing costs of options for the as-flown Mars Science Laboratory (MSL) aft body Thermal Light Weight Ablator (SLA) 561-V and its thickness was not optimized using the standard TPS Sizer Tool widely used for heat shield design. Use of the TPS sizing tool suggests that optimization of the SLA thickness could reduce the aft heat shield mass by 40 percent. Analysis of the predicted aft-shell aerothermodynamics suggests that the bulk of MSL class entry vehicle heat shields could incorporate Advanced Flexible Reusable Surface Insulation (AFRSI). AFRSI has a wellestablished record of relatively inexpensive manufacturing and flight certification based on its use on the lee side of the Space Shuttle. Runs with the TPS Sizer show that the AFRSI solution would be 60 percent lighter than the as-flown SLA. The issue of Reaction Control System (RCS) heating on the aft shell could be addressed by locally impregnating the AFRSI with silicone to enhance its robustness to short bursts ofheating. Stagnation point arcjet testing has shown that silicone impregnated AFRSI performs well at heat rates of 115 W/cm2 and 0.1 atmospheres for a duration of 40 seconds, far beyond conditions that are expected for MSL class vehicles. The paper concludes with a discussion of manufacturing processes for AFRSI, impregnation approaches and relative cost comparisons to the SLA solution.

6. VIEW LOOKING AFT ON PORT SIDE OF MAIN DECK ...

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

6. VIEW LOOKING AFT ON PORT SIDE OF MAIN DECK FROM POINT NEAR GALLEY STOVE CHIMNEY. DECKHOUSES ARE (FORE TO AFT) GALLEY COMPANIONWAY, ENGINE ROOM SKYLIGHT, PILOTS' CABIN SKYLIGHT, AFT COMPANIONWAY TO PILOTS' CABIN AND STEERING GEAR BOX - Pilot Schooner "Alabama", Moored in harbor at Vineyard Haven, Vineyard Haven, Dukes County, MA

Dynamics of skirting droplets

NASA Astrophysics Data System (ADS)

Akers, Caleb; Hale, Jacob

2014-11-01

It has been observed that non-coalescence between a droplet and pool of like fluid can be prolonged or inhibited by sustained relative motion between the two fluids. In this study, we quantitatively describe the motion of freely moving droplets that skirt across the surface of a still pool of like fluid. Droplets of different sizes and small Weber number were directed horizontally onto the pool surface. After stabilization of the droplet shape after impact, the droplets smoothly moved across the surface, slowing until coalescence. Using high-speed imaging, we recorded the droplet's trajectory from a top-down view as well as side views both slightly above and below the fluid surface. The droplets' speed is observed to decrease exponentially, with the smaller droplets slowing down at a greater rate. Droplets infused with neutral density micro beads showed that the droplet rolls along the surface of the pool. A qualitative model of this motion is presented.

Effect of gate skirts on pedestrian behavior at highway-rail grade crossings

DOT National Transportation Integrated Search

2013-12-31

The Federal Railroad Administration was interested in evaluating one type of pedestrian safety device, commonly known as gate skirts, that consists of a secondary horizontal hanging gate under the existing pedestrian gate to better block access to th...

Axial thermal medium delivery tubes and retention plates for a gas turbine rotor

DOEpatents

Mashey, Thomas Charles

2002-01-01

In a multi-stage turbine rotor, tubes are disposed in openings adjacent the rotor rim for flowing a thermal medium to rotor buckets and returning spent thermal medium. The tubes have axially spaced lands of predetermined wall thickness with thin-walled tube sections between the lands and of increasing thickness from the forward to the aft ends of the tubes. A pair of retention plates are carried on the aft end face of the aft wheel and straddle the tube and engage against a shoulder on the tube to preclude displacement of the tube in an aft direction.

Thermally-Conductive Metallic Coatings and Applications for Heat Removal on In-Space Cryogenic Vehicles

NASA Technical Reports Server (NTRS)

Ameen, Lauren; Hervol, David; Waters, Deborah

2017-01-01

For large in-space cryogenic upper stages, substantial axial heat removal from a forward skirt by vapor-based heat interception may not be achieved by simple attachment methods unless sufficient thermal conductance from the skirt to the cooling fluid can be achieved. Preferable methods would allow for the addition of the cooling system to existing structure with minimal impact on the structure. Otherwise, significant modification to the basic structural design andor novel and complex attachment mechanisms with high effective thermal conductance are likely to be required. The approach being pursued by evolvable Cryogenics (eCryo) is to increase the thermal performance of a relatively simple attachment system by applying metallic or other thermally conductive material coatings to the mating surface area of the fluid channel where it is attached the skirt wall. The expectation of candidate materials is that the dramatic increase in conductivity of pure metals at temperatures close to liquid hydrogen vapor temperature will compensate for the reduced actual contact area typical of mechanical joints. Basic contact conductance data at low temperatures for candidate interface materials is required to enable the test approach. A test rig was designed at NASA Glenn Research Center to provide thermal contact resistance testing between small sample coupons coated with conductive material via electron beam evaporation, a low-temperature option that will not affect physical properties of base materials. Average coating thicknesses were 10 k. The test fixture was designed to mount directly to a cryocooler cold head within a vacuum test chamber. The purpose of this test was to determine qualitative contact conductance between various test samples. Results from this effort will be implemented in a sub-scale vapor-based heat interception test, where the applicability for increased heat removal on large structural skirts will be considered.

46 CFR 153.234 - Fore and aft location.

Code of Federal Regulations, 2014 CFR

2014-10-01

... Containment Systems § 153.234 Fore and aft location. Except as allowed in § 153.7, each ship must meet the... 46 Shipping 5 2014-10-01 2014-10-01 false Fore and aft location. 153.234 Section 153.234 Shipping COAST GUARD, DEPARTMENT OF HOMELAND SECURITY (CONTINUED) CERTAIN BULK DANGEROUS CARGOES SHIPS CARRYING...

Refurbishment of SRB aluminum components by walnut hull blast removal of protective coatings

NASA Technical Reports Server (NTRS)

Colberg, W. R.; Gordon, G. H.; Jackson, C. H.

1982-01-01

A test program was conducted to develop, optimize, and scale up an abrasive blasting procedure was developed for refurbishment of specific SRB components: aft skirt, forward skirt, frustrum, and painted piece parts. Test specimens utilizing 2219 T87 aluminum substrate of varying thicknesses were prepared and blasted at progressively increasing pressures with selected abrasives. Specimens were analyzed for material response. The optimum blasting parameters were determined on panel specimens and verified on a large cylindrical integrated test bed.

The AFT Charter School Study: Not News. Point of View Essay

ERIC Educational Resources Information Center

Bracey, Gerald

2004-01-01

The recent flap over the American Federation of Teachers' (AFT) charter school report is surprising, not because the study used the wrong methods or reached the wrong conclusions, it didn't, but because AFT's conclusions are nothing new. The AFT study "is" the first to use the National Assessment of Educational Progress (NAEP) as its…

Effect of Axisymmetric Aft Wall Angle Cavity in Supersonic Flow Field

NASA Astrophysics Data System (ADS)

Jeyakumar, S.; Assis, Shan M.; Jayaraman, K.

2018-03-01

Cavity plays a significant role in scramjet combustors to enhance mixing and flame holding of supersonic streams. In this study, the characteristics of axisymmetric cavity with varying aft wall angles in a non-reacting supersonic flow field are experimentally investigated. The experiments are conducted in a blow-down type supersonic flow facility. The facility consists of a supersonic nozzle followed by a circular cross sectional duct. The axisymmetric cavity is incorporated inside the duct. Cavity aft wall is inclined with two consecutive angles. The performance of the aft wall cavities are compared with rectangular cavity. Decreasing aft wall angle reduces the cavity drag due to the stable flow field which is vital for flame holding in supersonic combustor. Uniform mixing and gradual decrease in stagnation pressure loss can be achieved by decreasing the cavity aft wall angle.

Noise from Aft Deck Exhaust Nozzles: Differences in Experimental Embodiments

NASA Technical Reports Server (NTRS)

Bridges, James

2014-01-01

Two embodiments of a rectangular nozzle on an aft deck are compared. In one embodiment the lower lip of the nozzle was extended with the sidewalls becoming triangles. In a second embodiment a rectangular nozzle was fitted with a surface that fit flush to the lower lip and extended outward from the sides of the nozzle, approximating a semi-infinite plane. For the purpose of scale-model testing, making the aft deck an integral part of the nozzle is possible for relatively short deck lengths, but a separate plate model is more flexible, accounts for the expanse of deck to the sides of the nozzle, and allows the nozzle to stand off from the deck. Both embodiments were tested and acoustic far-field results were compared. In both embodiments the extended deck introduces a new noise source, but the amplitude of the new source was dependent upon the span (cross-stream dimension) of the aft deck. The noise increased with deck length (streamwise dimension), and in the case of the beveled nozzle it increased with increasing aspect ratio. In previous studies of slot jets in wings it was noted that the increased noise from the extended aft deck appears as a dipole at the aft deck trailing edge, an acoustic source type with different dependence on velocity than jet mixing noise. The extraneous noise produced by the aft deck in the present studies also shows this behavior both in directivity and in velocity scaling.

33. View aft of main deck, port side, taken from ...

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

33. View aft of main deck, port side, taken from just aft of forecastle bulkhead showing foremast, fore shrouds, pig house, midship house and boat skids. - Ship BALCLUTHA, 2905 Hyde Street Pier, San Francisco, San Francisco County, CA

Detail view of the port side of the aft fuselage ...

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

Detail view of the port side of the aft fuselage of the Orbiter Discovery in the transfer aisle of the Vehicle Assembly Building at Kennedy Space Center with a lifting frame attached to the aft attach points of the orbiter. In this view, the Orbiter Maneuvering/Reaction Control Systems pod is in place. Also note the darker-colored trapezoidal aft fuselage access door and the T-0 umbilical panel to its right in the view. - Space Transportation System, Orbiter Discovery (OV-103), Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Noise reduction for model counterrotation propeller at cruise by reducing aft-propeller diameter

NASA Technical Reports Server (NTRS)

Dittmar, James H.; Stang, David B.

1987-01-01

The forward propeller of a model counterrotation propeller was tested with its original aft propeller and with a reduced diameter aft propeller. Noise reductions with the reduced diameter aft propeller were measured at simulated cruise conditions. Reductions were as large as 7.5 dB for the aft-propeller passing tone and 15 dB in the harmonics at specific angles. The interaction tones, mostly the first, were reduced probably because the reduced-diameter aft-propeller blades no longer interacted with the forward propeller tip vortex. The total noise (sum of primary and interaction noise) at each harmonic was significantly reduced. The chief noise reduction at each harmonic came from reduced aft-propeller-alone noise, with the interaction tones contributing little to the totals at cruise. Total cruise noise reductions were as much as 3 dB at given angles for the blade passing tone and 10 dB for some of the harmonics. These reductions would measurably improve the fuselage interior noise levels and represent a definite cruise noise benefit from using a reduced diameter aft propeller.

Aft flight deck documentation with freefloating headset interface unit (HIU)

NASA Image and Video Library

1983-09-05

STS008-18-479 (5 Sept 1983) --- Aft flight deck documentation includes on orbit station with control panel A2, aft viewing window W9, and communications kit assembly (ASSY) headset (HDST) interface unit (HIU) and cable free floating in front of it.

New strategy for design and fabrication of polymer hydrogel with tunable porosity as artificial corneal skirt.

PubMed

Cao, Danfeng; Zhang, Yingchao; Cui, Zhanchen; Du, Yuanyuan; Shi, Zuosen

2017-01-01

In order to obtain an ideal material using for artificial corneal skirt, a porous polymer hydrogel containing 2-hydroxyethyl methacrylate (HEMA), trimethylolpropane triacrylate (TMPTA) and butyl acrylate was prepared through one-step radical polymerization method and the usage of CaCO 3 whisker as porogen. The physical-chemical properties of the fabricated polymer hydrogel can be adjusted by CaCO 3 whisker content, such as pore size, porosity, water content of materials and surface topography. Then a series of cell biology experiments of human corneal fibroblasts (HCFs) were carried out to evaluate its properties as an artificial corneal skirt, such as the adhesion of cells on the materials with different pore size and porosity, the apoptosis on materials with different characteristics, the distribution of the cells on the material surface. The results revealed that high porosity not only could improve water content of hydrogel, but also strengthen the adhesion of HCFs on hydrogel. In addition, high porosity hydrogel with the whisker shape of pores showed much elongate spindle-like morphology than those low porosity hydrogels. MTT assay certified that the resulted polymer hydrogel material possessed excellent biocompatibility and was suitable for HCFs growing, making it promising for being developed as artificial corneal skirt. Copyright © 2016 Elsevier B.V. All rights reserved.

7. VIEW LOOKING AFT ON PORT SIDE OF MAIN DECK ...

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

7. VIEW LOOKING AFT ON PORT SIDE OF MAIN DECK FROM POINT NEAR ENGINE ROOM SKYLIGHT. ENGINE ROOM SKYLIGHT IS AT EXTREME LEFT, FOLLOWED BY PILOTS' CABIN SKYLIGHT, AFT COMPANIONWAY AND STEERING GEAR BOX - Pilot Schooner "Alabama", Moored in harbor at Vineyard Haven, Vineyard Haven, Dukes County, MA

Aft segment dome-to-stiffener factory joint insulation void elimination

NASA Technical Reports Server (NTRS)

Jensen, S. K.

1991-01-01

Since the detection of voids in the internal insulation of the dome-to-stiffener factory joint of the 15B aft segment, all aft segment dome-to-stiffener factory joints were x-rated and all were found to contain voids. Using a full-scale process simulation article (PSA), the objective was to demonstrate that the proposed changes in the insulation layup and vacuum bagging processes will greatly reduce or eliminate voids without adversely affecting the configuration of performance of the insulation which serves as a primary seal over the factory joint. The PSA-8 aft segment was insulated and cured using standard production processes.

Aft Skirt Electrical Umbilical (ASEU) and Vehicle Support Post (

NASA Image and Video Library

2016-12-09

Construction workers assist as a crane is used to lower a vertical support post for NASA's Space Launch System (SLS) onto a platform at the Mobile Launcher Yard at NASA's Kennedy Space Center in Florida. Two ASEUs and the first of the vertical support posts underwent a series of tests at the Launch Equipment Test Facility to confirm they are functioning properly and ready to support the SLS for launch. The ASEUs will connect to the SLS rocket at the bottom outer edge of each booster and provide electrical power and data connections to the rocket until it lifts off from the launch pad. The eight VSPs will support the load of the solid rocket boosters, with four posts for each of the boosters. The center’s Engineering Directorate and the Ground Systems Development and Operations Program are overseeing processing and testing of the umbilicals.

SRB Processing Facilities Media Event

NASA Image and Video Library

2016-03-01

The right-hand aft skirt, one part of the aft booster assembly for NASA’s Space Launch System solid rocket boosters, is in view in a processing cell inside the Booster Fabrication Facility (BFF) at NASA’s Kennedy Space Center in Florida. Orbital ATK is a contractor for NASA’s Marshall Space Flight Center in Alabama, and operates the BFF to prepare aft booster segments and hardware for the SLS rocket boosters. The SLS rocket and Orion spacecraft will launch on Exploration Mission-1 in 2018. The Ground Systems Development and Operations Program is preparing the infrastructure to process and launch spacecraft for deep-space missions and the journey to Mars.

Histologic evaluation during healing of hydrogel core-and-skirt keratoprostheses in the rabbit eye.

PubMed

Vijayasekaran, S; Hicks, C R; Chirila, T V; Fitton, J H; Clayton, A B; Lou, X; Platten, S; Crawford, G J; Constable, I J

1997-05-01

We developed two models that are modifications of our original poly(2-hydroxyethyl methacrylate) (PHEMA) core-and-skirt keratoprosthesis. In these keratoprostheses, the mechanical strength of the skirt has been considerably increased with divinyl glycol (DVG) as a cross-linking agent during polymerization. In one (KPro I), methyl methacrylate (MMA) was added as comonomer to increase cell adhesion, and in the other (KPro II), HEMA was polymerized with DVG without comonomer. The aim of this study was to evaluate the process of healing and biocolonization and to ascertain whether KPro I demonstrates better ingrowth than the mechanically stronger KPro II, after implantation in rabbit eyes. Ten rabbits were used for each model and studied at five predetermined end points up to 26 weeks. The device was implanted as a full-thickness keratoprosthesis covered with a conjunctival flap. Neither prosthesis demonstrated extrusion or retroprosthetic membrane formation. There was no significant difference between the two types of prosthesis with respect to tissue ingrowth and surrounding tissue melting. Histologically, inflammation was not severe, but calcification was seen in most specimens. Evidence of biodegradation of the prosthesis also was seen. In our original keratoprosthesis, fibrovascular invasion had occurred into the prosthetic skirt, but wound dehiscence and low mechanical strength resulted in an unfavorable outcome. In this series, the mechanical properties were improved, and KPro II was stronger than KPro I. Therefore KPro II would be the preferred polymer combination for surgical manipulation. However, biodegradation and calcification require further investigation into the degree and significance of these adverse reactions.

Robinson on aft flight deck

NASA Image and Video Library

1998-10-30

STS095-E-5065 (30 Oct. 1998) --- Astronaut Stephen K. Robinson, STS-95 mission specialist, looks toward Earth in this electronic still camera's (ESC) image of Flight Day two activity aboard the Space Shuttle Discovery. The scene was recorded on the aft flight deck at 12:02:11 GMT, Oct. 30.

Liquid Rocket Booster (LRB) for the Space Transportation System (STS) systems study. Appendix A: Stress analysis report for the pump-fed and pressure-fed liquid rocket booster

NASA Technical Reports Server (NTRS)

1989-01-01

Pressure effects on the pump-fed Liquid Rocket Booster (LRB) of the Space Transportation System are examined. Results from the buckling tests; bending moments tests; barrel, propellant tanks, frame XB1513, nose cone, and intertank tests; and finite element examination of forward and aft skirts are presented.

Closeup view of the aft flight deck of the Orbiter ...

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

Close-up view of the aft flight deck of the Orbiter Discovery looking at the aft center control panels A6, A7, A8, A12, A13, A14, A16 and A17. This View was taken at Kennedy Space Center. - Space Transportation System, Orbiter Discovery (OV-103), Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

KSC-04pd0524

NASA Image and Video Library

2004-03-05

KENNEDY SPACE CENTER, FLA. - The STS-114 crew pose for a photo in front of a solid rocket booster aft skirt in the SRB Assembly and Refurbishment Facility. In front, from left, are Cynthia Perrons, electrical technician with United Space Alliance; Commander Eileen Collins, Pilot James Kelly, and Mission Specialists Charles Camarda and Andrew Thomas. In back are Paul Gutierrez, associate program manager in SRB Element, USA; John Cleary Jr., electrical engineer with USA; Mike Leppert, project lead, Manufacturing Operations, USA; Don Noah, Materials and Processes engineer, USA; Bob Herman, deputy associate program manager, SRB Element, USA; Mission Specialist Soichi Noguchi; Dale Marlow, thermal protection system engineer with USA; Mission Specialist Stephen Robinson; Greg Henry, director, Manufacturing Operations, USA.

PLT Polansky on aft flight deck

NASA Image and Video Library

2001-02-10

STS98-E-5084 (10 February 2001) --- Astronaut Mark L. Polansky, STS-98 pilot, takes notes on the aft flight deck of the Space Shuttle Atlantis. The scene was recorded with a digital still camera during Flight Day 4 activities.

Closeup view of the Solid Rocket Booster (SRB) Forward Skirt, ...

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

Close-up view of the Solid Rocket Booster (SRB) Forward Skirt, Frustum and Nose Cap mated assembly undergoing final preparations in the Solid Rocket Booster Assembly and Refurbishment Facility at Kennedy Space Center. The prominent feature in this view is the Forward Thrust Attach Fitting which mates up with the Forward Thrust Attach Fitting of the External Tank (ET) at the ends of the SRB Beam that runs through the ET's Inter Tank Assembly. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Development of Lead Free Energy Absorber for Space Shuttle Blast Container

NASA Technical Reports Server (NTRS)

Balles, Donald; Ingram, Thomas; Novak, Howard; Schricker, Albert

1998-01-01

The Space Shuttle is connected to the mobile launch platform (MLP) by four aft skirt hold down studs on each solid rocket booster (SRB). Prior to lift-off, the frangible nuts inside the aft skirt blast containers are severed into two nut halves by two pyrotechnic booster cartridges. This action releases the Space Shuttle and allows the hold down studs to eject through the aft skirt bore and then down into the MLP. USBI has been tasked to upgrade the blast container for two specific reasons: (1) To eliminate lead for environmental concerns, and (2) To reduce the chance of nut recontact with the holddown stud. Nut recontact with the stud has been identified as a likely contributor to stud hang-ups. This upgrade will replace the lead liner with a unique open cell aluminum foam material, that has commercial and military uses. The aluminum foam used as an energy absorber is a proven design in many other aerospace/defense applications. Additional benefits of using the open cell, energy absorbent aluminum foam in place of the solid lead liner are: (A) Lead handling/exposure and possible contamination, along with hazardous waste disposal, will be eliminated; (B) Approximately 200 lbs. weight savings will be contributed to each Space Shuttle flight by using aluminum foam instead of lead; (C) The new aluminum liner is designed to catch all shrapnel from frangible nuts, thus virtually eliminating chance of debris exiting the HDP and causing potential damage to the vehicle; and (D) Using the lighter aluminum liner instead of lead, allows for easier assembly and disassembly of blast container elements, which also improves safety, operator handling, and the efficiency of operations.

Development of Lead Free Energy Absorber for Space Shuttle Blast Container

NASA Technical Reports Server (NTRS)

Balles, Donald; Ingram, Thomas; Novak, Howard; Schricker, Albert

1999-01-01

The Space Shuttle is connected to the mobile launch platform (MLP) by four aft skirt hold down studs on each solid rocket booster (SRB). Prior to lift-off, the frangible nuts inside the aft skirt blast containers are severed into two nut halves by two pyrotechnic booster cartridges. This action releases the Space Shuttle and allows the hold down studs to eject through the aft skirt bore and then down into the MLP. USBI has been tasked to upgrade the blast container for two specific reasons: (1) To eliminate lead for environmental concerns, and (2) To reduce the chance of nut recontact with the holddown stud. Nut recontact with the stud has been identified as a likely contributor to stud hang-ups. This upgrade will replace the lead liner with a unique open cell aluminum foam material, that has commercial and military uses. The aluminum foam used as an energy absorber is a proven design in many other aerospace/defense applications. Additional benefits of using the open cell, energy absorbent aluminum foam in place of the solid lead liner are: (1) Lead handling / exposure and possible contamination, along with hazardous waste disposal, will be eliminated; (2) Approximately 200 lbs. weight savings will be contributed to each Space Shuttle flight by using aluminum foam instead of lead; (3) The new aluminum liner is designed to catch all shrapnel from frangible nuts, thus virtually eliminating chance of debris exiting the HDP and causing potential damage to the vehicle; (4) Using the lighter aluminum liner instead of lead, allows for easier assembly and disassembly of blast container elements, which also improves safety, operator handling, and the efficiency of operations.

SKIRT: Hybrid parallelization of radiative transfer simulations

NASA Astrophysics Data System (ADS)

Verstocken, S.; Van De Putte, D.; Camps, P.; Baes, M.

2017-07-01

We describe the design, implementation and performance of the new hybrid parallelization scheme in our Monte Carlo radiative transfer code SKIRT, which has been used extensively for modelling the continuum radiation of dusty astrophysical systems including late-type galaxies and dusty tori. The hybrid scheme combines distributed memory parallelization, using the standard Message Passing Interface (MPI) to communicate between processes, and shared memory parallelization, providing multiple execution threads within each process to avoid duplication of data structures. The synchronization between multiple threads is accomplished through atomic operations without high-level locking (also called lock-free programming). This improves the scaling behaviour of the code and substantially simplifies the implementation of the hybrid scheme. The result is an extremely flexible solution that adjusts to the number of available nodes, processors and memory, and consequently performs well on a wide variety of computing architectures.

Internal Performance of a Fixed-Shroud Nonaxisymmetric Nozzle Equipped with an Aft-Hood Exhaust Deflector

NASA Technical Reports Server (NTRS)

Asbury, Scott C.

1997-01-01

An investigation was conducted in the model preparation area of the Langley 16-Foot Transonic Tunnel to determine the internal performance of a fixed-shroud nonaxisymmetric nozzle equipped with an aft-hood exhaust deflector. Model geometric parameters investigated included nozzle power setting, aft-hood deflector angle, throat area control with the aft-hood deflector deployed, and yaw vector angle. Results indicate that cruise configurations produced peak performance in the range consistent with previous investigations of nonaxisymmetric convergent-divergent nozzles. The aft-hood deflector produced resultant pitch vector angles that were always less than the geometric aft-hood deflector angle when the nozzle throat was positioned upstream of the deflector exit. Significant losses in resultant thrust ratio occurred when the aft-hood deflector was deployed with an upstream throat location. At each aft-hood deflector angle, repositioning the throat to the deflector exit improved pitch vectoring performance and, in some cases, substantially improved resultant thrust ratio performance. Transferring the throat to the deflector exit allowed the flow to be turned upstream of the throat at subsonic Mach numbers, thereby eliminating losses associated with turning supersonic flow. Internal throat panel deflections were largely unsuccessful in generating yaw vectoring.

Cycle 0(CY1991) NLS trade studies and analyses report. Book 1: Structures and core vehicle

NASA Technical Reports Server (NTRS)

1992-01-01

This report (SR-1: Structures, Trades, and Analysis), documents the Core Tankage Trades and analyses performed in support of the National Launch System (NLS) Cycle 0 preliminary design activities. The report covers trades that were conducted on the Vehicle Assembly, Fwd Skirt, LO2 Tank, Intertank, LH2 Tank, and Aft Skirt of the NLS Core Tankage. For each trade study, a two page executive summary and the detail trade study are provided. The trade studies contain study results, recommended changes to the Cycle 0 Baselines, and suggested follow on tasks to be performed during Cycle 1.

The Hog1p kinase regulates Aft1p transcription factor to control iron accumulation.

PubMed

Martins, Telma S; Pereira, Clara; Canadell, David; Vilaça, Rita; Teixeira, Vítor; Moradas-Ferreira, Pedro; de Nadal, Eulàlia; Posas, Francesc; Costa, Vítor

2018-01-01

Iron acquisition systems have to be tightly regulated to assure a continuous supply of iron, since it is essential for survival, but simultaneously to prevent iron overload that is toxic to the cells. In budding yeast, the low‑iron sensing transcription factor Aft1p is a master regulator of the iron regulon. Our previous work revealed that bioactive sphingolipids modulate iron homeostasis as yeast cells lacking the sphingomyelinase Isc1p exhibit an upregulation of the iron regulon. In this study, we show that Isc1p impacts on iron accumulation and localization. Notably, Aft1p is activated in isc1Δ cells due to a decrease in its phosphorylation and an increase in its nuclear levels. Consistently, the expression of a phosphomimetic version of Aft1p-S210/S224 that favours its nuclear export abolished iron accumulation in isc1Δ cells. Notably, the Hog1p kinase, homologue of mammalian p38, interacts with and directly phosphorylates Aft1p at residues S210 and S224. However, Hog1p-Aft1p interaction decreases in isc1Δ cells, which likely contributes to Aft1p dephosphorylation and consequently to Aft1p activation and iron overload in isc1Δ cells. These results suggest that alterations in sphingolipid composition in isc1Δ cells may impact on iron homeostasis by disturbing the regulation of Aft1p by Hog1p. To our knowledge, Hog1p is the first kinase reported to directly regulate Aft1p, impacting on iron homeostasis. Copyright © 2017 Elsevier B.V. All rights reserved.

Close up oblique view aft, port side of the Orbiter ...

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

Close up oblique view aft, port side of the Orbiter Discovery in the Vehicle Assembly Building at NASA's Kennedy Space Center. This view shows a close up of the elevons and underside of the port wing. On the aft fuselage in the approximate center rift of the image is the T-0 umbilical panels. - Space Transportation System, Orbiter Discovery (OV-103), Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Effect of AFT Rotor on the Inter-Rotor Flow of an Open Rotor Propulsion System

NASA Technical Reports Server (NTRS)

Slaboch, Paul E.; Stephens, David B.; Van Zante, Dale E.

2016-01-01

The effects of the aft rotor on the inter-rotor flow field of an open rotor propulsion rig were examined. A Particle Image Velocimetry (PIV) dataset that was acquired phase locked to the front rotor position has been phase averaged based on the relative phase angle between the forward and aft rotors. The aft rotor phase was determined by feature tracking in raw PIV images through an image processing algorithm. The effect of the aft rotor potential field on the inter-rotor flow were analyzed and shown to be in good agreement with Computational Fluid Dynamics (CFD) simulations. It was shown that the aft rotor had no substantial effect on the position of the forward rotor tip vortex but did have a small effect on the circulation strength of the vortex when the rotors were highly loaded.

General view of the aft section of the Orbiter Discovery ...

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

General view of the aft section of the Orbiter Discovery in the Vehicle Assembly Building at NASA's Kennedy Space Center. Note the main engines and Orbiter Maneuvering System/Reaction Control System pods are removed in this photo. The flexible hoses protruding from the starboard aft section are to control temperature, humidity and pressure in the orbiter's void spaces during its down time. - Space Transportation System, Orbiter Discovery (OV-103), Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

General view of the aft, starboard section of the Orbiter ...

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

General view of the aft, starboard section of the Orbiter Discovery in the Vehicle Assembly Building at NASA's Kennedy Space Center. Note the main engines and Orbiter Maneuvering System/Reaction Control System pods are removed in this photo. The flexible hoses protruding from the starboard aft section are to control temperature, humidity and pressure in the orbiter's void spaces during its down time. - Space Transportation System, Orbiter Discovery (OV-103), Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Crewmember in the aft flight deck.

NASA Image and Video Library

1992-11-01

STS052-24-014 (22 Oct-1 Nov 1992) --- Canadian payload specialist Steven G. MacLean tries out gymnastics in the weightlessness of space on the aft flight deck of the Earth-orbiting Space Shuttle Columbia. MacLean, along with five NASA astronauts, spent ten days aboard Columbia for the STS-52 mission.

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.

Tension Builds over AFT Reform Agenda

ERIC Educational Resources Information Center

Sawchuk, Stephen

2012-01-01

Can a teachers' union successfully be both a hardball-playing defender of its rights and a collaborative force for the common good? It is both a question of philosophy and, increasingly, one of policy direction for the American Federation of Teachers (AFT), whose biennial convention in Detroit showed delegates grappling with the tension between…

AFT Chief Promises Due-Process Reform

ERIC Educational Resources Information Center

Sawchuk, Stephen

2010-01-01

The president of the American Federation of Teachers (AFT), Randi Weingarten, is putting the sensitive issue of due process on the education reform table, with a pledge to work with districts to streamline the often-cumbersome procedures for dismissing teachers who fail to improve their performance after receiving help and support. She has also…

Closeup oblique view of the aft fuselage of the Orbiter ...

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

Close-up oblique view of the aft fuselage of the Orbiter Discovery looking forward and port with the Space Shuttle Main Engines (SSME) and Orbiter Maneuvering System/Reaction Control System pods still in place. However. the heat shields have been removed from the SSMEs providing a good view toward the interior of the aft fuselage. This image was taken inside the Orbiter Processing Facility at Kennedy Space Center. - Space Transportation System, Orbiter Discovery (OV-103), Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Closeup oblique view of the aft fuselage of the Orbiter ...

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

Close-up oblique view of the aft fuselage of the Orbiter Discovery looking forward and starboard with the Space Shuttle Main Engines (SSME) and Orbiter Maneuvering System/Reaction Control System pods removed. The openings for the SSMEs have been covered with a flexible barrier to create a positive pressure envelope inside of the aft fuselage. This image was taken inside the Orbiter Processing Facility at Kennedy Space Center. - Space Transportation System, Orbiter Discovery (OV-103), Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Closeup oblique view of the aft fuselage of the Orbiter ...

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

Close-up oblique view of the aft fuselage of the Orbiter Discovery looking forward and starboard with the Space Shuttle Main Engines (SSME) and Orbiter Maneuvering System/Reaction Control System pods still in place. However. the heat shields have been removed from the SSMEs providing a good view toward the interior of the aft fuselage. This image was taken inside the Orbiter Processing Facility at Kennedy Space Center. - Space Transportation System, Orbiter Discovery (OV-103), Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

P6 Truss aft radiator seen during EVA

NASA Image and Video Library

2007-02-04

ISS014-E-13293 (4 Feb. 2007) --- The partially retracted aft radiator of the P6 truss of the International Space Station is featured in this image photographed during the second of three sessions of extravehicular activity (EVA) in nine days by astronauts Michael E. Lopez-Alegria (out of frame), Expedition 14 commander and NASA space station science officer; and Sunita L. Williams (out of frame), flight engineer. The Zvezda Service Module and the Zarya module are visible at left. During the spacewalk, Williams and Lopez-Alegria reconfigured the second of two cooling loops for the Destiny laboratory module, secured the aft radiator of the P6 truss after retraction and prepared the obsolete Early Ammonia Servicer (EAS) for removal this summer.

P6 Truss aft radiator seen during EVA

NASA Image and Video Library

2007-02-04

ISS014-E-13296 (4 Feb. 2007) --- The partially retracted aft radiator of the P6 truss of the International Space Station is featured in this image photographed during the second of three sessions of extravehicular activity (EVA) in nine days by astronauts Michael E. Lopez-Alegria (out of frame), Expedition 14 commander and NASA space station science officer; and Sunita L. Williams (out of frame), flight engineer. The Zvezda Service Module and the Zarya module are visible at left. During the spacewalk, Williams and Lopez-Alegria reconfigured the second of two cooling loops for the Destiny laboratory module, secured the aft radiator of the P6 truss after retraction and prepared the obsolete Early Ammonia Servicer (EAS) for removal this summer.

Engine protection system for recoverable rocket booster

NASA Technical Reports Server (NTRS)

Shelby, Jr., Jerry A. (Inventor)

1994-01-01

A rocket engine protection system for a recoverable rocket booster which is arranged to land in a salt water body in substantially a nose down attitude. The system includes an inflatable bag which is stowed on a portion of a flat annular rim of the aft skirt of the booster. The bag is hinged at opposing sides and is provided with springs that urge the bag open. The bag is latched in a stowed position during launch and prior to landing for recovery is unlatched to permit the bag to be urged open and into sealing engagement with the rim. A source of pressurized gas further inflates the bag and urges it into sealing engagement with the rim of the skirt where it is locked into position. The gas provides a positive pressure upon the interior of the bag to preclude entry of salt water into the skirt and into contact with the engine. A flotation arrangement may assist in precluding the skirt of the booster from becoming submerged.

Closeup view of the Solid Rocket Booster (SRB) Forward Skirt ...

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

Close-up view of the Solid Rocket Booster (SRB) Forward Skirt sitting on ground support equipment in the Solid Rocket Booster Assembly and Refurbishment Facility at Kennedy Space Center while being prepared for mating with the Frustum-Nose Cap Assembly and the Forward Rocket Motor Segment. The prominent feature in this view is the Forward Thrust Attach Fitting which mates up with the Forward Thrust Attach Fitting of the External Tank (ET) at the ends of the SRB Beam that runs through the ET's Inter Tank Assembly. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Crewmembers in the aft flight deck.

NASA Image and Video Library

1992-12-09

STS053-01-034 (2-9 Dec 1992) --- From the Space Shuttle Discovery's aft flight deck, astronaut Guion S. Bluford, mission specialist, uses a handheld 70mm Hasselblad to photograph a point on Earth. Bluford was joined by four other NASA astronauts for the eight-day mission in Earth-orbit, dedicated to the Department of Defense (DOD).

Pilot Fullerton reviews checklist on Aft Flight Deck Onorbit Station

NASA Technical Reports Server (NTRS)

1982-01-01

Pilot Fullerton, wearing communication kit assembly (assy) mini headset, reviews checklist and looks at remote manipulator system (RMS) closed circuit television (CCTV) views displayed on CCTV monitors at Aft Flight Deck Onorbit Station. Taken from the aft flight deck starboard side, Fullerton is seen in front of Panels A7 and A8 with remote manipulator syste (RMS) translation hand control (THC) and RMS rotation hand control (RHC) in the foreground and surrounded by University of Michigan (U of M) GO BLUE and United States Air Force - A Great Way of Life Decals.

Brown on aft flight deck with microphone

NASA Image and Video Library

1998-10-31

STS095-E-5177 (31 Oct. 1998) --- On Discovery's aft flight deck, astronaut Curtis L. Brown Jr., STS-95 commander, checks over notes with ground controllers in Houston. The photo was taken with an electronic still camera (ESC) at 00:41:51 GMT, Oct. 31.

Open cycle ocean thermal energy conversion system

DOEpatents

Wittig, J. Michael

1980-01-01

An improved open cycle ocean thermal energy conversion system including a flash evaporator for vaporizing relatively warm ocean surface water and an axial flow, elastic fluid turbine having a vertical shaft and axis of rotation. The warm ocean water is transmitted to the evaporator through a first prestressed concrete skirt-conduit structure circumferentially situated about the axis of rotation. The unflashed warm ocean water exits the evaporator through a second prestressed concrete skirt-conduit structure located circumferentially about and radially within the first skirt-conduit structure. The radially inner surface of the second skirt conduit structure constitutes a cylinder which functions as the turbine's outer casing and obviates the need for a conventional outer housing. The turbine includes a radially enlarged disc element attached to the shaft for supporting at least one axial row of radially directed blades through which the steam is expanded. A prestressed concrete inner casing structure of the turbine has upstream and downstream portions respectively situated upstream and downstream from the disc element. The radially outer surfaces of the inner casing portions and radially outer periphery of the axially interposed disc cooperatively form a downwardly radially inwardly tapered surface. An annular steam flowpath of increasing flow area in the downward axial direction is radially bounded by the inner and outer prestressed concrete casing structures. The inner casing portions each include a transversely situated prestressed concrete circular wall for rotatably supporting the turbine shaft and associated structure. The turbine blades are substantially radially coextensive with the steam flowpath and receive steam from the evaporator through an annular array of prestressed concrete stationary vanes which extend between the inner and outer casings to provide structural support therefor and impart a desired flow direction to the steam.

Regenerative air heater

DOEpatents

Hasselquist, P.B.; Baldner, R.

1980-11-26

A gas-cooled steel skirt is used to support a refractory cored brick matrix and dome structure in a high temperature regenerative air heater useful in magnetohydrodynamic power generation. The steel skirt thermally expands to accommodate the thermal expansion of the dome structure despite substantial temperature differential thereby reducing relative movement between the dome bricks. Gas cooling of the steel skirt allows the structure to operate above its normal temperature during clean-out cycles and also allows for the control of the thermal expansion of the steel skirt.

Regenerative air heater

DOEpatents

Hasselquist, Paul B.; Baldner, Richard

1982-01-01

A gas-cooled steel skirt is used to support a refractory cored brick matrix and dome structure in a high temperature regenerative air heater useful in magnetohydrodynamic power generation. The steel skirt thermally expands to accommodate the thermal expansion of the dome structure despite substantial temperature differential thereby reducing relative movement between the dome bricks. Gas cooling of the steel skirt allows the structure to operate above its normal temperature during clean-out cycles and also allows for the control of the thermal expansion of the steel skirt.

General view looking aft from the starboard side of the ...

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

General view looking aft from the starboard side of the Orbiter Discovery looking into the payload bay and the bulkhead of the aft fuselage. Note that the Orbiter Boom Sensor System is still attached while the Remote Manipulator System has been removed. Also note the suspended protective panels and walkways in place to protect the interior surfaces of the payload bay doors while in their open position. This view was taken from a service platform in the Orbiter Processing Facility at Kennedy Space Center. - Space Transportation System, Orbiter Discovery (OV-103), Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Autogenic-Feedback Training Exercise (AFTE) Method and System

NASA Technical Reports Server (NTRS)

Cowings, Patricia S. (Inventor)

1997-01-01

The Autogenic-Feedback Training Exercise (AFTE) method of the present invention is a combined application of physiologic and perceptual training techniques. such as autogenic therapy and biofeedback. This combined therapy approach produces a methodology that is appreciably more effective than either of the individual techniques used separately. The AFTE method enables sufficient magnitude of control necessary to significantly reduce the behavioral and physiologic reactions to severe environmental stressors. It produces learned effects that are persistent over time and are resistant to extinction and it can be administered in a short period of time. The AFTE method may be used efficiently in several applications, among which are the following: to improve pilot and crew performance during emergency flying conditions; to train people to prevent the occurrence of nausea and vomiting associated with motion and sea sickness, or morning sickness in early pregnancy; as a training method for preventing or counteracting air-sickness symptoms in high-performance military aircraft; for use as a method for cardiovascular training, as well as for multiple other autonomic responses, which may contribute to the alleviation of Space Motion Sickness (SMS) in astronauts and cosmonauts; training people suffering from migraine or tension headaches to control peripheral blood flow and reduce forehead and/or trapezius muscle tension; training elderly people suffering from fecal incontinence to control their sphincter muscles; training cancer patients to reduce the nauseagenic effects of chemotherapy; and training patients with Chronic Intestinal Pseudo-obstruction (CIP).

Space Shuttle Projects

NASA Image and Video Library

1978-09-01

This photograph shows stacking of the left side of the solid rocket booster (SRB) segments in the Dynamic Test Stand at the east test area of the Marshall Space Flight Center (MSFC). Staging shown here are the aft skirt, aft segment, and aft center segment. The SRB was attached to the external tank (ET) and then the orbiter later for the Mated Vertical Ground Vibration Test (MVGVT), that resumed in October 1978. The stacking of a complete Shuttle in the Dynamic Test Stand allowed test engineers to perform ground vibration testing on the Shuttle in its liftoff configuration. The purpose of the MVGVT is to verify that the Space Shuttle would perform as predicted during launch. The platforms inside the Dynamic Test Stand were modified to accommodate two SRB's to which the ET was attached.

Walheim on Aft Flight Deck during Deorbit Preparations

NASA Image and Video Library

2011-07-21

S135-E-012383 (21 July 2011) --- Astronaut Rex Walheim, STS-135 mission specialist, makes preparations on space shuttle Atlantis' aft flight deck for the mission's re-entry phase and the final landing of a NASA space shuttle. Photo credit: NASA

Aft2, a Novel Transcription Regulator, Is Required for Iron Metabolism, Oxidative Stress, Surface Adhesion and Hyphal Development in Candida albicans

PubMed Central

Xu, Ning; Cheng, Xinxin; Yu, Qilin; Qian, Kefan; Ding, Xiaohui; Liu, Ruming; Zhang, Biao; Xing, Laijun; Li, Mingchun

2013-01-01

Morphological transition and iron metabolism are closely relevant to Candida albicans pathogenicity and virulence. In our previous study, we demonstrated that C. albicans Aft2 plays an important role in ferric reductase activity and virulence. Here, we further explored the roles of C. albicans Aft2 in numerous cellular processes. We found that C. albicans Aft2 exhibited an important role in iron metabolism through bi-directional regulation effects on iron-regulon expression. Deletion of AFT2 reduced cellular iron accumulation under iron-deficient conditions. Furthermore, both reactive oxygen species (ROS) generation and superoxide dismutase (SOD) activity were remarkably increased in the aft2Δ/Δ mutant, which were thought to be responsible for the defective responses to oxidative stress. However, we found that over-expression of C. albicans AFT2 under the regulation of the strong PGK1 promoter could not effectively rescue Saccharomyces cerevisiae aft1Δ mutant defects in some cellular processes, such as cell-wall assembly, ion homeostasis and alkaline resistance, suggesting a possibility that C. albicans Aft2 weakened its functional role of regulating some cellular metabolism during the evolutionary process. Interestingly, deletion of AFT2 in C. albicans increased cell surface hydrophobicity, cell flocculation and the ability of adhesion to polystyrene surfaces. In addition, our results also revealed that C. albicans Aft2 played a dual role in regulating hypha-specific genes under solid and liquid hyphal inducing conditions. Deletion of AFT2 caused an impaired invasive growth in solid medium, but an increased filamentous aggregation and growth in liquid conditions. Moreover, iron deficiency and environmental cues induced nuclear import of Aft2, providing additional evidence for the roles of Aft2 in transcriptional regulation. PMID:23626810

86. AFT CREWS' GALLEY STARBOARD LOOKING TO PORT SHOWING ...

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

86. AFT CREWS' GALLEY - STARBOARD LOOKING TO PORT SHOWING STEAM KETTLES, GRIDDLES, COUNTER TOP AND MIXING MACHINE. - U.S.S. HORNET, Puget Sound Naval Shipyard, Sinclair Inlet, Bremerton, Kitsap County, WA

Boron epoxy rocket motor case program

NASA Technical Reports Server (NTRS)

Stang, D. A.

1971-01-01

Three 28-inch-diameter solid rocket motor cases were fabricated using 1/8 inch wide boron/epoxy tape. The cases had unequal end closures (4-1/8-inch-diameter forward flanges and 13-inch-diameter aft flanges) and metal attachment skirts. The flanges and skirts were titanium 6Al-4V alloy. The original design for the first case was patterned after the requirements of the Applications Technology Satellite apogee kick motor. The second and third cases were designed and fabricated to approximate the requirements of a small Applications Technology Satellite apogee kick motor. The program demonstrated the feasibility of designing and fabricating large-scale filament-wound solid propellant rocket motor cases with boron/epoxy tape.

Detail view of the starboard side of the aft fuselage ...

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

Detail view of the starboard side of the aft fuselage of the Orbiter Discovery in the Orbiter Processing Facility at Kennedy Space Center with the Orbiter Maneuvering/Reaction Control Systems Pod removed and exposing the insulating foil used to protect the orbiter structure from the heat generated by the maneuvering and reaction control engines. Also note in the view that the aft fuselage access door has bee removed and also note the ground support equipment attached to the T-0 umbilical plate in the lower left of the view. - Space Transportation System, Orbiter Discovery (OV-103), Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

100. COBBLER SHOP AFT LOOKING FORWARD VISIBLE ARE ...

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

100. COBBLER SHOP - AFT LOOKING FORWARD - VISIBLE ARE THE FINISHING MACHINE, DAVIS STITCHING MACHINE, SINGER SEWING MACHINE FROM TAILOR SHOP, STORAGE SHELVES, WORK BENCH AND SHOE TREE STAND. - U.S.S. HORNET, Puget Sound Naval Shipyard, Sinclair Inlet, Bremerton, Kitsap County, WA

In Pennsylvania Primary, AFT Hits the Streets

ERIC Educational Resources Information Center

Hoff, David J.

2008-01-01

Every day, 14 retired teachers and other school employees arrive at the Philadelphia Federation of Teachers' headquarters and go to work for Hillary Rodham Clinton. The retirees--working with volunteers and union staff members from as far away as Alaska--are working to inform teachers' union members why the American Federation of Teachers (AFT)…

87. AFT CREWS' MESS DECK STARBOARD LOOKING TO PORT ...

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

87. AFT CREWS' MESS DECK - STARBOARD LOOKING TO PORT SHOWING COFFEE MAKER, ICE CREAM FREEZER, TABLES AND SCUTTLEBUTTS. - U.S.S. HORNET, Puget Sound Naval Shipyard, Sinclair Inlet, Bremerton, Kitsap County, WA

44. #3 ARRESTING GEAR ENGINE AFT LOOKING FORWARD SHOWING ...

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

44. #3 ARRESTING GEAR ENGINE - AFT LOOKING FORWARD SHOWING MURAL OF LUCY AND CHARLIE BROWN ON HYDRAULIC OIL ACCUMULATOR. - U.S.S. HORNET, Puget Sound Naval Shipyard, Sinclair Inlet, Bremerton, Kitsap County, WA

The effect of friction in the hold down post spherical bearings on hold down post loads

NASA Technical Reports Server (NTRS)

Richardson, James A.

1990-01-01

The effect of friction at the connection of the Solid Rocket Booster (SRB) aft skirt and the mobile launch platform (MLP) hold down posts was analyzed. A simplified model of the shuttle response during the Space Shuttle Main Engine (SSME) buildup was constructed. The model included the effect of stick-slip friction for the rotation of the skirt about the spherical bearing. Current finite element models assume the joint is completely frictionless in rotation and therefore no moment is transferred between the skirt and the hold down posts. The model was partially verified against test data and preliminary parameter studies were performed. The parameter studies indicated that the coefficient of friction strongly influenced the moment on the hold down posts. The coefficient of friction had little effect on hold down post vertical loads, however. Further calibration of the model is necessary before the effect of friction on the hold down post horizontal loads can be analyzed.

Glen and Brown on aft flight deck

NASA Image and Video Library

1998-10-31

STS095-E-5180 (31 Oct. 1998) --- Astronaut Curtis L. Brown Jr. (left), STS-95 commander, stands by on Discovery's aft flight deck as U.S. Sen. John H. Glenn Jr., payload specialist, talks with ground controllers in Houston. The photo was taken with an electronic still camera (ESC) at 00:48:48 GMT, Oct. 31.

Drag Characteristics of Several Towed Decelerator Models at Mach 3

NASA Technical Reports Server (NTRS)

Miserentino, Robert; Bohon, Herman L.

1970-01-01

An investigation has been made to determine the possibility of using toroid-membrane and wide-angle conical shapes as towed decelerators. Parameter variations were investigated which might render toroid-membrane models and wide-angle- cone models stable without loss of the high drag coefficients obtainable with sting-mounted models. The parameters varied included location of center of gravity, location of the pivot between the towline and the model, and configuration modifications of the aft end as the addition of a corner radius and the addition of a skirt. The toroid membrane can be made into a stable towed decelerator with a suitable configuration modification of the aft end.

Effects of an aft facing step on the surface of a laminar flow glider wing

NASA Technical Reports Server (NTRS)

Sandlin, Doral R.; Saiki, Neal

1993-01-01

A motor glider was used to perform a flight test study on the effects of aft facing steps in a laminar boundary layer. This study focuses on two dimensional aft facing steps oriented spanwise to the flow. The size and location of the aft facing steps were varied in order to determine the critical size that will force premature transition. Transition over a step was found to be primarily a function of Reynolds number based on step height. Both of the step height Reynolds numbers for premature and full transition were determined. A hot film anemometry system was used to detect transition.

71. CHIEF PETTY OFFICERS' LOUNGE AFT LOOKING FORWARD PORT ...

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

71. CHIEF PETTY OFFICERS' LOUNGE - AFT LOOKING FORWARD PORT TO STARBOARD SHOWING COFFEE MESS, ICE CREAM COOLER, ICE MACHINE AND SCUTTLEBUTT. - U.S.S. HORNET, Puget Sound Naval Shipyard, Sinclair Inlet, Bremerton, Kitsap County, WA

Fighting for the Profession: A History of AFT Higher Education. Item Number 36-0701

ERIC Educational Resources Information Center

American Federation of Teachers, 2003

2003-01-01

This document provides a history of the relationship between higher education faculty and the American Federation of Teachers (AFT). Highlights include the first AFT higher education local formed in 1918, the role played by the union in the expansion of the G.I. Bill following World War II, increased activism in the 1950s and 1960s to win…

49. COMMAND INFORMATION CENTER (CIC) AFT LOOKING FORWARD PORT ...

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

49. COMMAND INFORMATION CENTER (CIC) - AFT LOOKING FORWARD PORT TO STARBOARD SHOWING VARIOUS TYPES OF RADAR UNITS, PLOT TABLES AND PLOTTING BOARDS. - U.S.S. HORNET, Puget Sound Naval Shipyard, Sinclair Inlet, Bremerton, Kitsap County, WA

101. STARBOARD AIRPLANE ELEVATOR MACHINERY ROOM AFT LOOKING FORWARD ...

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

101. STARBOARD AIRPLANE ELEVATOR MACHINERY ROOM - AFT LOOKING FORWARD PORT TO STARBOARD SHOWING ELEVATOR ENGINE, LIFTING WIRES, HYDRAULIC PIPING WITH REMOTE OPERATOR. - U.S.S. HORNET, Puget Sound Naval Shipyard, Sinclair Inlet, Bremerton, Kitsap County, WA

In vitro effect of a corrosive hostile ocular surface on candidate biomaterials for keratoprosthesis skirt

PubMed Central

Tan, Xiao Wei; Riau, Andri; Shi, Zhi Long; Tan, Anna C S; Neoh, Koon Gee; Khor, Khiam Aik; Beuerman, Roger W; Tan, Donald; Mehta, Jodhbir S

2012-01-01

Aim Keratoprosthesis (KPro) devices are prone to long-term corrosion and microbiological assault. The authors aimed to compare the inflammatory response and material dissolution properties of two candidate KPro skirt materials, hydroxyapatite (HA) and titania (TiO2) in a simulated in vitro cornea inflammation environment. Methods Lipopolysaccharide-stimulated cytokine secretions were evaluated with human corneal fibroblasts on both HA and TiO2. Material specimens were subjected to electrochemical and long-term incubation test with artificial tear fluid (ATF) of various acidities. Topography and surface roughness of material discs were analysed by scanning electron microscopy and atomic force microscopy. Results There were less cytokines secreted from human corneal fibroblasts seeded on TiO2 substrates as compared with HA. TiO2 was more resistant to the corrosion effect caused by acidic ATF in contrast to HA. Moreover, the elemental composition of TiO2 was more stable than HA after long-term incubation with ATF. Conclusions TiO2 is more resistant to inflammatory degradation and has a higher corrosion resistance as compared with HA, and in this regard may be a suitable material to replace HA as an osteo-odonto-keratoprosthesis skirt. This would reduce resorption rates for KPro surgery. PMID:22802307

Casper points camera out of aft flight deck window

NASA Image and Video Library

1996-05-26

S77-E-5109 (26 May 1996) --- Astronaut John H. Casper, commander, pauses during a photography session on the aft flight deck of the Space Shuttle Endeavour. The scene was recorded with an Electronic Still Camera (ESC).

Autogenic-Feedback Training Exercise (AFTE) Mitigates the Effects of Spatial Disorientation to Simulated Orion Spacecraft Re-Entry: Individual Differences

NASA Technical Reports Server (NTRS)

Cowings, Patricia S.; Toscano, William B.; Reschke, Millard F.; Gebreyesus, Fiyori; Rocha, Christopher

2017-01-01

NASA has identified a potential risk of spatial disorientation to future astronauts during re-entry of the proposed Orion spacecraft. The purpose of this study was to determine if a 6-hour physiological training procedure, Autogenic-Feedback Training Exercise (AFTE), can mitigate these effects. Twenty subjects were assigned to two groups (AFTE and Control) matched for motion sickness susceptibility and gender. All subjects received a standard rotating chair test to determine motion sickness susceptibility; three training sessions on a manual performance task; and four exposures to a simulated Orion re-entry test in the rotating chair. Treatment subjects were given two hours of AFTE training before each Orion test. A diagnostic scale was used to evaluate motion sickness symptom severity. Results showed that 2 hours of AFTE significantly reduced motion sickness symptoms during the second Orion test. AFTE subjects were able to maintain lower heart rates and skin conductance levels and other responses than the control group subjects during subsequent tests. Trends show that performance was less degraded for AFTE subjects. The results of this study indicate that astronauts could benefit from receiving at least 2 hours of preflight AFTE. In addition, flight crews could benefit further by practicing physiologic self-regulation using mobile devices.

A new semi-supervised learning model combined with Cox and SP-AFT models in cancer survival analysis.

PubMed

Chai, Hua; Li, Zi-Na; Meng, De-Yu; Xia, Liang-Yong; Liang, Yong

2017-10-12

Gene selection is an attractive and important task in cancer survival analysis. Most existing supervised learning methods can only use the labeled biological data, while the censored data (weakly labeled data) far more than the labeled data are ignored in model building. Trying to utilize such information in the censored data, a semi-supervised learning framework (Cox-AFT model) combined with Cox proportional hazard (Cox) and accelerated failure time (AFT) model was used in cancer research, which has better performance than the single Cox or AFT model. This method, however, is easily affected by noise. To alleviate this problem, in this paper we combine the Cox-AFT model with self-paced learning (SPL) method to more effectively employ the information in the censored data in a self-learning way. SPL is a kind of reliable and stable learning mechanism, which is recently proposed for simulating the human learning process to help the AFT model automatically identify and include samples of high confidence into training, minimizing interference from high noise. Utilizing the SPL method produces two direct advantages: (1) The utilization of censored data is further promoted; (2) the noise delivered to the model is greatly decreased. The experimental results demonstrate the effectiveness of the proposed model compared to the traditional Cox-AFT model.

34. PRIMARY FLIGHT CONTROL STATION AFT LOOKING FORWARD ON ...

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

34. PRIMARY FLIGHT CONTROL STATION - AFT LOOKING FORWARD ON PORT SIDE SHOWING FLIGHT DECK LIGHTING BOARD, ARRESTING GEAR CONTROL CONSOLE AND FRESNEL LENS OPTICAL LANDING SYSTEM. - U.S.S. HORNET, Puget Sound Naval Shipyard, Sinclair Inlet, Bremerton, Kitsap County, WA

Spin Forming Aluminum Crew Module (CM) Metallic Aft Pressure Vessel Bulkhead (APVBH) - Phase II

NASA Technical Reports Server (NTRS)

Hoffman, Eric K.; Domack, Marcia S.; Torres, Pablo D.; McGill, Preston B.; Tayon, Wesley A.; Bennett, Jay E.; Murphy, Joseph T.

2015-01-01

The principal focus of this project was to assist the Multi-Purpose Crew Vehicle (MPCV) Program in developing a spin forming fabrication process for manufacture of the Orion crew module (CM) aft pressure vessel bulkhead. The spin forming process will enable a single piece aluminum (Al) alloy 2219 aft bulkhead resulting in the elimination of the current multiple piece welded construction, simplify CM fabrication, and lead to an enhanced design. Phase I (NASA TM-2014-218163 (1)) of this assessment explored spin forming the single-piece CM forward pressure vessel bulkhead. The Orion MPCV Program and Lockheed Martin (LM) recently made two critical decisions relative to the NESC Phase I work scope: (1) LM selected the spin forming process to manufacture a single-piece aft bulkhead for the Orion CM, and (2) the aft bulkhead will be manufactured from Al 2219. Based on the Program's new emphasis related to the spin forming process, the NESC was asked to conduct a Phase II assessment to assist in the LM manufacture of the aft bulkhead and to conduct a feasibility study into spin forming the Orion CM cone. This activity was approved on June 19, 2013. Dr. Robert Piascik, NASA Technical Fellow for Materials at the Langley Research Center (LaRC), was selected to lead this assessment. The project plan was approved by the NASA Engineering and Safety Center (NESC) Review Board (NRB) on July 18, 2013. The primary stakeholders for this assessment were the NASA and LM MPCV Program offices. Additional benefactors are commercial launch providers developing CM concepts.

Spin Forming Aluminum Crew Module (CM) Metallic Aft Pressure Vessel Bulkhead (APVBH) - Phase II

NASA Technical Reports Server (NTRS)

Hoffman, Eric K.; Domack, Marcia S.; Torres, Pablo D.; McGill, Preston B.; Tayon, Wesley A.; Bennett, Jay E.; Murphy, Joseph T.

2015-01-01

The principal focus of this project was to assist the Multi-Purpose Crew Vehicle (MPCV) program in developing a spin forming fabrication process for manufacture of the Orion crew module (CM) aft pressure vessel bulkhead. The spin forming process will enable a single piece aluminum (Al) alloy 2219 aft bulkhead resulting in the elimination of the current multiple piece welded construction, simplify CM fabrication, and lead to an enhanced design. Phase I (NASA TM-2014-218163, (1)) of this assessment explored spin forming the single-piece CM forward pressure vessel bulkhead. The MPCV Program and Lockheed Martin (LM) recently made two critical decisions relative to the NESC Phase I work scope: (1) LM selected the spin forming process to manufacture a singlepiece aft bulkhead for the Orion CM, and (2) the aft bulkhead will be manufactured from Al 2219. Based on the Program's new emphasis related to the spin forming process, the NESC was asked to conduct a Phase II assessment to assist in the LM manufacture of the aft bulkhead and to conduct a feasibility study into spin forming the Orion CM cone. This activity was approved on June 19, 2013. Dr. Robert Piascik, NASA Technical Fellow for Materials at the Langley Research Center (LaRC), was selected to lead this assessment. The project plan was approved by the NASA Engineering and Safety Center (NESC) Review Board (NRB) on July 18, 2013. The primary stakeholders for this assessment are the NASA and LM MPCV Program offices. Additional benefactors are commercial launch providers developing CM concepts.

Aerodynamic Control-Augmentation Devices For Saturn-Class Launch Vehicles With Aft Centers Of Gravity

NASA Technical Reports Server (NTRS)

Barret, Chris

1995-01-01

Report describes study of aerodynamic flight-control-augmentation devices proposed for use in increasing payload capabilities of future launch vehicles by allowing more aft centers of gravity. Proposed all-movable devices not only provide increased control authority during ascent trajectory, but also reduce engine gimballing requirements and enhance crew safety. Report proposes various aerodynamic control surfaces mounted fore and aft on Saturn-class launch vehicle.

STS-47 Mission Specialist (MS) Jemison conducts AFTE in SLJ module on OV-105

NASA Technical Reports Server (NTRS)

1992-01-01

STS-47 Mission Specialist (MS) Mae C. Jemison, wearing autogenic feedback training system 2 suit, conducts the Autogenic Feedback Training Experiment (AFTE) in Spacelab Japan (SLJ) science module aboard Endeavour, Orbiter Vehicle (OV) 105. AFTE's objective is to teach astronauts to use biofeedback rather than drugs to combat nausea and other effects of space motion sickness. Jemison's physical responses are monitored by sensors attached to the suit.

General view looking out from the Fixed Service Structure at ...

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

General view looking out from the Fixed Service Structure at Launch Complex 39 B at Kennedy Space Center. This view shows a Solid Rocket Booster (SRB) attached to the External Tank (ET) as well as the Orbiter Discovery attached to the ET for a complete launch stack assembly being prepared for launch. The most prominent features of the SRB shown in this view id the ET Attach Ring in the lower center of the view and the Systems Tunnel running vertically from the Aft Skirt Assembly, beyond the lower edge of this view, to the Forward Skirt near the Frustum at the top center of this view. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Flight motor set 360L001 (STS-26R). Volume 1: System overview, revision A

NASA Technical Reports Server (NTRS)

Garecht, Diane M.

1990-01-01

The NASA space shuttle flight STS-26R, launched at 11:37.00.009 am, EDT on 29 Sep. 1988, used the redesigned solid rocket motors (RSRM) 360L001A and 360L001B. Evaluation of the ground environment instrumentation (GEI) data recorded prior to flight showed no launch commit criteria violations; that the field joint heater and aft skirt thermal conditioning systems performed adequately; and that the GEI data showed good agreement with thermal model predictions. Evaluation of the developmental flight instrumentation (DFI) revealed excellent agreement with both the predicted and required ballistic specifications. All parameters were well within the GEI specification requirements including propellant burn rates, specific impulse values, and thrust imbalance. Recorded strain values also indicated satisfactory radial growth and stress levels, as well as verification of adequate safety factors. Postflight inspection of the insulation, seals, case, and nozzles showed overall excellent performance. Some thermal DFI protective cork was missing, and inoperative field joint vent valves on the thermal protection cork allowed water entry into the field joints upon splashdown. Evaluation of these anomalies, as well as complete evaluation of all Redesigned Solid Rocket Motor components, is contained.

Flight motor set 360L001 (STS-26R), volume 1

NASA Technical Reports Server (NTRS)

Ricks, Glen A.

1988-01-01

The NASA space shuttle flight STS-26R, launched at 11:37.00.009 a.m. EDT on 29 Sep. 1988, used the redesigned solid rocket motors (RSRM) 360LOO1A and 360LOO1B. Evaluation of the ground environment instrumentation (GEI) data recorded prior to flight showed: (1) no launch commit criteria violations, (2) that the field joint heater and aft skirt thermal conditioning systems performed adequately, and (3) that the GEI data showed good agreement with thermal model predictions. Evaluation of the developmental flight instrumentation (DFI) revealed excellent agreement with both the predicted and required ballistic specifications. All parameters were well within the CEI specification requirements including propellant burn rates, specific impulse values, and thrust imbalance. Recorded strain values also indicated satisfactory radial growth and stress levels, as well as verification of adequate safety factors. Postflight inspection of the insulation, seals, case, and nozzles showed overall excellent performance. Some thermal DFI protective cork was missing, and inoperative field joint vent valves on the thermal protection cork allowed water entry into the field joints upon splashdown. Evaluation of these anomalies, as well as complete evaluation of all RSRM components, is presented.

Shock Characteristics Measured Upstream of Both a Forward-Swept and an Aft-Swept Fan

NASA Technical Reports Server (NTRS)

Podboy, Gary G.; Krupar, Martin J.; Sutliff, Daniel L.; Horvath, Csaba

2007-01-01

Three different types of diagnostic data-blade surface flow visualization, shroud unsteady pressure, and laser Doppler velocimeter (LDV)--were obtained on two fans, one forward-swept and one aft-swept, in order to learn more about the shocks which propagate upstream of these rotors when they are operated at transonic tip speeds. Flow visualization data are presented for the forward-swept fan operating at 13831 rpm(sub c), and for the aft-swept fan operating at 12500 and 13831 rpm(sub c) (corresponding to tip rotational Mach numbers of 1.07 and 1.19, respectively). The flow visualization data identify where the shocks occur on the suction side of the rotor blades. These data show that at the takeoff speed, 13831 rpm(sub c), the shocks occurring in the tip region of the forward-swept fan are further downstream in the blade passage than with the aft-swept fan. Shroud unsteady pressure measurements were acquired using a linear array of 15 equally-spaced pressure transducers extending from two tip axial chords upstream to 0.8 tip axial chords downstream of the static position of the tip leading edge of each rotor. Such data are presented for each fan operating at one subsonic and five transonic tip speeds. The unsteady pressure data show relatively strong detached shocks propagating upstream of the aft-swept rotor at the three lowest transonic tip speeds, and weak, oblique pressure disturbances attached to the tip of the aft-swept fan at the two highest transonic tip speeds. The unsteady pressure measurements made with the forward-swept fan do not show strong shocks propagating upstream of that rotor at any of the tested speeds. A comparison of the forward-swept and aft-swept shroud unsteady pressure measurements indicates that at any given transonic speed the pressure disturbance just upstream of the tip of the forward-swept fan is much weaker than that of the aft-swept fan. The LDV data suggest that at 12500 and 13831 rpm(sub c), the forward-swept fan swallowed the

MS Ivins at the Atlantis aft flight deck controls

NASA Image and Video Library

2001-02-10

STS98-E-5078 (10 February 2001) --- Astronaut Marsha S. Ivins, STS-98 mission specialist, monitors communications from ground controllers from her post at the aft flight deck controls on the Space Shuttle Atlantis. The scene was recorded with a digital still camera.

65. FORWARD EMERGENCY DIESEL GENERATOR SET AFT LOOKING FORWARD ...

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

65. FORWARD EMERGENCY DIESEL GENERATOR SET - AFT LOOKING FORWARD SHOWING TOP HALF OF FAIRBANKS MORSE 36D81/8 TEN CYLINDER DIESEL ENGINE SERIAL #951230 AND EXHAUST SYSTEM. - U.S.S. HORNET, Puget Sound Naval Shipyard, Sinclair Inlet, Bremerton, Kitsap County, WA

118. #3 SHAFT ALLEY (PROPELLER SHAFT) FORWARD LOOKING AFT ...

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

118. #3 SHAFT ALLEY (PROPELLER SHAFT) - FORWARD LOOKING AFT ON PORT SIDE SHOWING THE SHAFT, SHAFT PACKING GLAND, SHAFT SEAL COOLING WATER LINE AND FIVE INCH FIRE MAIN PIPING. - U.S.S. HORNET, Puget Sound Naval Shipyard, Sinclair Inlet, Bremerton, Kitsap County, WA

41. #1 ARRESTING GEAR ENGINE AFT LOOKING FORWARD PORT ...

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

41. #1 ARRESTING GEAR ENGINE - AFT LOOKING FORWARD PORT TO STARBOARD SHOWING ARRESTING GEAR ENGINE ACCUMULATOR, AIR FLASK, CONTROL VALVE, WITH CONTROL RAM, SHEAVES AND WIRES UNDERNEATH ENGINE STAND. - U.S.S. HORNET, Puget Sound Naval Shipyard, Sinclair Inlet, Bremerton, Kitsap County, WA

73. TORPEDO WORK SHOP FORWARD LOOKING AFT SHOWING TORPEDO ...

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

73. TORPEDO WORK SHOP - FORWARD LOOKING AFT SHOWING TORPEDO ELEVATOR, HIGH PRESSURE AIR REDUCING STATION, SCUTTLEBUTT, TORPEDO AFTERBODY WORKSHOP, OVERHEAD CHAIN MOIST AND RAIL SYSTEM AND OVERHEAD SPRINKLER SYSTEM. - U.S.S. HORNET, Puget Sound Naval Shipyard, Sinclair Inlet, Bremerton, Kitsap County, WA

Crystal structures of Boro-AFm and sBoro-AFt phases

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

Champenois, Jean-Baptiste; Mesbah, Adel; Clermont Universite, ENSCCF, Institut de Chimie de Clermont-Ferrand, BP 10448, F-63000 Clermont-Ferrand

2012-10-15

Crystal structures of boron-containing AFm (B-AFm) and AFt (B-AFt) phases have been solved ab-initio and refined from X-ray powder diffraction. {sup 11}B NMR and Raman spectroscopies confirm the boron local environment in both compounds: three-fold coordinated in B-AFm corresponding to HBO{sub 3}{sup 2-} species, and four-fold coordinated in B-AFt corresponding to B (OH){sub 4}{sup -} species. B-AFm crystallizes in the rhombohedral R3{sup Macron }c space group and has the 3CaO{center_dot}Al{sub 2}O{sub 3}{center_dot}CaHBO{sub 3}{center_dot}12H{sub 2}O (4CaO{center_dot}Al{sub 2}O{sub 3}{center_dot}1/2B{sub 2}O{sub 3}{center_dot}12.5H{sub 2}O, C{sub 4}AB{sub 1/2}H{sub 12.5}) general formulae with planar trigonal HBO{sub 3}{sup 2-} anions weakly bonded at the centre of themore » interlayer region. One HBO{sub 3}{sup 2-} anion is statistically distributed with two weakly bonded water molecules on the same crystallographic site. B-AFt crystallizes in the trigonal P3cl space group and has the 3CaO{center_dot}Al{sub 2}O{sub 3}{center_dot}Ca(OH){sub 2}{center_dot}2Ca(B (OH){sub 4}){sub 2}{center_dot}24H{sub 2}O (6CaO{center_dot}Al{sub 2}O{sub 3}{center_dot}2B{sub 2}O{sub 3}{center_dot}33H{sub 2}O, C{sub 6}AB{sub 2}H{sub 33}) general formulae with tetrahedral B (OH){sub 4}{sup -} anions located in the channel region of the structure. All tetrahedral anions are oriented in a unique direction, leading to a hexagonal c lattice parameter about half that of ettringite.« less

Brown at RMS controls on the aft flight deck

NASA Image and Video Library

1998-11-24

STS095-366-031 (29 Oct-7 Nov 1998) --- Astronaut Curtis L. Brown, Jr., mission commander, operates controls on the aft flight deck of the Space Shuttle Discovery. Brown was joined by four other NASA astronauts and two payload specialists for the nine-day mission.

Closeup view looking aft from the starboard side of the ...

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

Close-up view looking aft from the starboard side of the Orbiter Discovery looking into the payload bay and the bulkhead of the aft fuselage. Note the vertical stabilizer protruding slightly from beyond the clear sheeting used to keep positive pressure in the mid-fuselage and payload bay area during servicing. Note that the Orbiter Boom Sensor System is still attached while the Remote Manipulator System has been removed. Also note the suspended protective panels and walkways in place to protect the interior surfaces of the payload bay doors while in their open position. This view was taken from a service platform in the Orbiter Processing Facility at Kennedy Space Center. - Space Transportation System, Orbiter Discovery (OV-103), Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

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.

Lightweight Energy Absorbers for Blast Containers

NASA Technical Reports Server (NTRS)

Balles, Donald L.; Ingram, Thomas M.; Novak, Howard L.; Schricker, Albert F.

2003-01-01

Kinetic-energy-absorbing liners made of aluminum foam have been developed to replace solid lead liners in blast containers on the aft skirt of the solid rocket booster of the space shuttle. The blast containers are used to safely trap the debris from small explosions that are initiated at liftoff to sever frangible nuts on hold-down studs that secure the spacecraft to a mobile launch platform until liftoff.

B-1 AFT Nacelle Flow Visualization Study

NASA Technical Reports Server (NTRS)

Celniker, Robert

1975-01-01

A 2-month program was conducted to perform engineering evaluation and design tasks to prepare for visualization and photography of the airflow along the aft portion of the B-1 nacelles and nozzles during flight test. Several methods of visualizing the flow were investigated and compared with respect to cost, impact of the device on the flow patterns, suitability for use in the flight environment, and operability throughout the flight. Data were based on a literature search and discussions with the test personnel. Tufts were selected as the flow visualization device in preference to several other devices studied. A tuft installation pattern has been prepared for the right-hand aft nacelle area of B-1 air vehicle No.2. Flight research programs to develop flow visualization devices other than tufts for use in future testing are recommended. A design study was conducted to select a suitable motion picture camera, to select the camera location, and to prepare engineering drawings sufficient to permit installation of the camera. Ten locations on the air vehicle were evaluated before the selection of the location in the horizontal stabilizer actuator fairing. The considerations included cost, camera angle, available volume, environmental control, flutter impact, and interference with antennas or other instrumentation.

Brown at aft flight deck control during SPARTAN capture

NASA Image and Video Library

1998-11-03

STS095-E-5134 (3 Nov. 1998) --- Astronaut Curtis L. Brown, STS-95 commander, on Discovery's aft flight deck during operations to retrieve the free-flying Spartan 201-05 satellite. The photograph was taken with an electronic still camera (ESC) at 3:17:38 GMT, Nov. 3.

Horowitz at the aft flight deck during rendezvous ops

NASA Image and Video Library

2001-08-12

STS105-E-5061 (12 August 2001) --- Astronaut Scott J. Horowitz, STS-105 mission commander, looks over a checklist on the aft flight deck of the Space Shuttle Discovery during rendezvous operations with the International Space Station (ISS). The image was recorded with a digital still camera.

31. ENGINE ROOM LOOKING AFT ON STARBOARD SIDE SHOWING BOTH ...

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

31. ENGINE ROOM LOOKING AFT ON STARBOARD SIDE SHOWING BOTH CATERPILLAR DIESELS AND ONE GENERATOR. - U.S. Coast Guard Cutter WHITE PINE, U.S. Coast Guard 8th District Base, South Broad Street, Mobile, Mobile County, AL

Condensation on crew compartment aft flight deck window W10

NASA Image and Video Library

1982-03-30

STS003-24-211 (22-30 March 1982) --- Crew compartment aft flight deck viewing window W10 fogged with condensation. The condensation is a result of the spacecraft's position in relation to the sun. Photo credit: NASA

Pilot Fullerton sleeps on aft flight deck

NASA Image and Video Library

1982-03-30

STS003-22-113 (24 March 1982) --- Astronaut Gordon Fullerton, STS-3 pilot, wearing communication kit assembly mini-headset (HDST), sleeps on aft flight deck resting his back against the floor and his feet against commander's ejection seat (S1) back. On-orbit station control panel A8 and payload station panel L15 appear above Fullerton. Special clips for holding notebooks open and beverage containers are velcroed on various panels. Photo credit: NASA

Payload commander Voss on aft flight deck

NASA Image and Video Library

2012-09-18

STS083-305-010 (4-8 April 1997) --- Astronaut Janice E. Voss, mission specialist, works with communications systems on the aft flight deck of the Earth-orbiting Space Shuttle Columbia. Voss, along with five other NASA astronauts and two payload specialist supporting the Microgravity Sciences Laboratory (MSL-1) mission, were less than a fourth of the way through a scheduled 16-day flight when a power problem cut short their planned stay.

Pilot Fullerton reviews checklist on Aft Flight Deck Onorbit Station

NASA Image and Video Library

1982-03-31

S82-28906 (27 March 1982) --- Astronaut C. Gordon Fullerton, STS-3 pilot, mans the right hand aft station of the flight deck on the Earth-orbiting Columbia. The photograph was taken with a 35mm camera by astronaut Jack R. Lousma, crew commander. The "Go Blue" sticker is a University of Michigan memento of Lousma, and the Air Force sign was put up by Fullerton, a USAF colonel. Lousma, a USMC colonel, received his BS degree in aeronautical engineering in 1959 from UM. One of two aft windows for cargo bay viewing and one of two ceiling windows are visible in the photo. Fullerton and Lousma watched the activity of the remote manipulator system (RMS) arm out the lower window and they took a number of photos of Earth from the upper window. Photo credit: NASA

SRM attrition rate study of the aft motor case segments due to water impact cavity collapse loading

NASA Technical Reports Server (NTRS)

Crockett, C. D.

1976-01-01

The attrition assessment of the aft segments of Solid Rocket Motor due to water impact requires the establishment of a correlation between loading occurrences and structural capability. Each discrete load case, as identified by the water impact velocities and angle, varies longitudinally and radially in magnitude and distribution of the external pressure. The distributions are further required to be shifted forward or aft one-fourth the vehicle diameter to assure minimization of the effect of test instrumentation location for the load determinations. The asymmetrical load distributions result in large geometric nonlinearities in structural response. The critical structural response is progressive buckling of the case. Discrete stiffeners have been added to these aft segments to aid in gaining maximum structural capability for minimum weight addition for resisting these loads. This report presents the development of the attrition assessment of the aft segments and includes the rationale for eliminating all assessable conservatisms from this assessment.

Resolving the chronology of the South African landscape through joint inverse modelling of AFT and apatite (U-Th)/He data

NASA Astrophysics Data System (ADS)

Wildman, Mark; Brown, Roderick; Beucher, Romain; Persano, Cristina; Stuart, Finlay

2013-04-01

Application of Low temperature thermochronometry (LTT) is a powerful method of constraining thermal history information on samples as they pass through isotherms in the upper crust. Inverse modelling of LTT data generates thermal history information which can then be correlated with independent datasets to infer geological processes that are responsible for producing the observed thermal history held in the thermochronometry record. A critical consideration when choosing which LTT method to use are the closure temperatures associated with each system. In order to generate more complete and robust thermal histories a single sample can be analysed using multiple low temperature thermochronometers that are sensitive over different but complimentary temperature ranges. The main focus of LTT work in South Africa has been on apatite fission track (AFT) analysis which is a world renowned method of constraining thermal history information between c. 60 and 110±10°C. The general conclusions that have been drawn from the South African AFT dataset is that the present day regional topography represents an eroded remnant of an elevated interior that experienced a significant uplift event with km-scale erosion in the Cretaceous following the break-up of Gondwana [1]. The exact nature of Cretaceous uplift and erosion varies both spatially and temporally, especially in south western Africa where at least two distinct denudation events are recorded at c. 130Ma and 90 Ma [2]. There are, however, alternative views suggesting significant epeirogenic-style uplift and subsequent erosion throughout the Cenozoic [3]. A key aspect of this debate which is yet to be fully resolved is the influence of mantle dynamics on the evolution of the overlying topography. To further investigate the timing and amount of Cenozoic uplift and erosion and to what degree this can be ascribed to dynamic topography, efforts have been made to complement the existing AFT record with Apatite (U-Th)/He analysis

Iron-Induced Dissociation of the Aft1p Transcriptional Regulator from Target Gene Promoters Is an Initial Event in Iron-Dependent Gene Suppression

PubMed Central

Ueta, Ryo; Fujiwara, Naoko; Yamaguchi-Iwai, Yuko

2012-01-01

Aft1p is an iron-responsive transcriptional activator that plays a central role in the regulation of iron metabolism in Saccharomyces cerevisiae. Aft1p is regulated by accelerated nuclear export in the presence of iron, mediated by Msn5p. However, the transcriptional activity of Aft1p is suppressed under iron-replete conditions in the Δmsn5 strain, although Aft1p remains in the nucleus. Aft1p dissociates from its target promoters under iron-replete conditions due to an interaction between Aft1p and the monothiol glutaredoxin Grx3p or Grx4p (Grx3/4p). The binding of Grx3/4p to Aft1p is induced by iron repletion and requires binding of an iron-sulfur cluster to Grx3/4p. The mitochondrial transporter Atm1p, which has been implicated in the export of iron-sulfur clusters and related molecules, is required not only for iron binding to Grx3p but also for dissociation of Aft1p from its target promoters. These results suggest that iron binding to Grx3p (and presumably Grx4p) is a prerequisite for the suppression of Aft1p. Since Atm1p plays crucial roles in the delivery of iron-sulfur clusters from the mitochondria to the cytoplasm and nucleus, these results support the previous observations that the mitochondrial iron-sulfur cluster assembly machinery is involved in cellular iron sensing. PMID:23045394

Thick section aluminum weldments for SRB structures

NASA Technical Reports Server (NTRS)

Bayless, E.; Sexton, J.

1978-01-01

The Space Shuttle Solid Rocket Booster (SRB) forward and aft skirts were designed with fracture control considerations used in the design data. Fracture control is based on reliance upon nondestructive evaluation (NDE) techniques to detect potentially critical flaws. In the aerospace industry, welds on aluminum in the thicknesses (0.500 to 1.375 in.) such as those encountered on the SRB skirts are normally welded from both sides to minimize distortion. This presents a problem with the potential presence of undefined areas of incomplete fusion and the inability to detect these potential flaws by NDE techniques. To eliminate the possibility of an undetectable defect, weld joint design was revised to eliminate blind root penetrations. Weld parameters and mechanical property data were developed to verify the adequacy of the new joint design.

20. HANGAR BAY #2 FORWARD LOOKING AFT ON CENTERLINE ...

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

20. HANGAR BAY #2 - FORWARD LOOKING AFT ON CENTERLINE - STARBOARD SIDE SHOWING CONFLAGRATION STATION, UPTAKE SPACE AND DEHUMIDIFICATION MACHINES - PORT SIDE SHOWING VARIOUS DECK WINCHES, ROLLER DOORS, HANGAR DECK PLANE CONTROL STATION AND AQUEOUS FIRE FIGHTING FOAM HOSE REELS. - U.S.S. HORNET, Puget Sound Naval Shipyard, Sinclair Inlet, Bremerton, Kitsap County, WA

Plans: Aft Gun Platform, Quarters for 16 Gunmen, Poop Deck, ...

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

Plans: Aft Gun Platform, Quarters for 16 Gunmen, Poop Deck, Boat Deck, House Top, Bridge Deck, Upper Bridge Deck, Navigating Bridge, Forecastle Deck, Gun Platform, Upper Deck, Second Deck and Hold Plan - Mission Santa Ynez, Suisun Bay Reserve Fleet, Benicia, Solano County, CA

Compartment A123 crews WC (head) looking aft; to forward; note ...

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

Compartment A-123 crews WC (head) looking aft; to forward; note wire lockers for transient stowage of clothing while showering. (026) - USS Olympia, Penn's Landing, 211 South Columbus Boulevard, Philadelphia, Philadelphia County, PA

Skylab

NASA Image and Video Library

1970-01-01

Assembling activities of the Skylab cluster are shown in this photograph. The Orbital Workshop (OWS) was lowered for joining to aft skirt and placed over the thrust structure inside the assembly tower. The OWS provided living and working quarters for the Skylab crew and the thruster provided short-term attitude control of the Skylab. The Marshall Space Flight Center had responsibilities for the design and development of the Skylab hardware, and management of experiments.

Commander Truly on aft flight deck holding communication kit assembly (ASSY)

NASA Technical Reports Server (NTRS)

1983-01-01

On aft flight deck, Commander Truly holds communication kit assembly (ASSY) headset (HDST) interface unit (HIU) and mini-HDST in front of the onorbit station. HASSELBLAD camera is positioned on overhead window W8.

12. VIEW AFT IN MAIN HOLD OF THE EVELINA M. ...

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

12. VIEW AFT IN MAIN HOLD OF THE EVELINA M. GOULART. OPENING IN THE BULKHEAD WAS CUT TO IMPROVE ACCESS TO ENGINE ROOM SO THAT ENGINE COULD BE REMOVED. - Auxiliary Fishing Schooner "Evelina M. Goulart", Essex Shipbuilding Museum, 66 Main Street, Essex, Essex County, MA

30. View of main deck at bow (looking aft from ...

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

30. View of main deck at bow (looking aft from samson post, upper deck removed), showing anchor windlass (left foreground), head (right foregound), and forward deckhouse; weather canopy overhead not an original or permanent feature - Schooner WAWONA, 1018 Valley Street, Seattle, King County, WA

Aeroacoustic effects of reduced aft tip speed at constant thrust for a model counterrotation turboprop at takeoff conditions

NASA Technical Reports Server (NTRS)

Woodward, Richard P.; Hughes, Christopher E.

1990-01-01

A model high-speed, advanced counterrotation propeller, F7/A7, was tested in the NASA Lewis Research Center's 9- by 15-foot anechoic wind tunnel at simulated takeoff and approach conditions of Mach 0.2. The propeller was operated in a baseline configuration with the forward and aft rotor blade setting angles (36.2deg and 35.4 deg) and forward and aft rotational speeds essentially equal. Two additional configurations were tested with the aft rotor at increased blade setting angles and the rotational speed reduced to achieve overall performance similar to that of the baseline configuration. The aft rotor blade angles were adjusted such that the thrust and power absorption for each rotor remained the same as for the baseline configuration. Acoustic data were taken with an axially translating microphone probe that was attached to the tunnel floor. Concurrent aerodynamic data were taken to define propeller operating conditions. The aft rotor fundamental tone was about 6 dB lower with the 36.2 deg and 38.4 deg blade setting angles, and about 9 dB lower with the 36.2 and 41.4 deg blade setting angles. Predicted noise reductions based on tip speed considerations were 5 and 9.5 dB, respectively, for the two altered blade setting angles.

Commander Lousma works with EEVT experiment and cryogenic tube on aft middeck

NASA Image and Video Library

1982-03-31

Commander Jack Lousma works with Electrophoresis Equipment Verification Test (EEVT) electrophoresis unit, cryogenic freezer and tube, and stowage locker equipment located on crew compartment middeck aft bulkhead.

View of the O-ring in the top of the aft segment of the right SRB

NASA Technical Reports Server (NTRS)

1986-01-01

This is a close-out photograph of the O-ring in the top of the aft segment of the right solid rocket booster (SRB) flown on Space Shuttle mission 51-L. The photograph was released following a hearing on the accident (10163); Close-out photograph of the top of the aft segment of the right SRB flown on Space Shuttle mission 51-L (10164).

Examining porous bio-active glass as a potential osteo-odonto-keratoprosthetic skirt material.

PubMed

Huhtinen, Reeta; Sandeman, Susan; Rose, Susanna; Fok, Elsie; Howell, Carol; Fröberg, Linda; Moritz, Niko; Hupa, Leena; Lloyd, Andrew

2013-05-01

Bio-active glass has been developed for use as a bone substitute with strong osteo-inductive capacity and the ability to form strong bonds with soft and hard tissue. The ability of this material to enhance tissue in-growth suggests its potential use as a substitute for the dental laminate of an osteo-odonto-keratoprosthesis. A preliminary in vitro investigation of porous bio-active glass as an OOKP skirt material was carried out. Porous glass structures were manufactured from bio-active glasses 1-98 and 28-04 containing varying oxide formulation (1-98, 28-04) and particle size range (250-315 μm for 1-98 and 28-04a, 315-500 μm for 28-04b). Dissolution of the porous glass structure and its effect on pH was measured. Structural 2D and 3D analysis of porous structures were performed. Cell culture experiments were carried out to study keratocyte adhesion and the inflammatory response induced by the porous glass materials. The dissolution results suggested that the porous structure made out of 1-98 dissolves faster than the structures made from glass 28-04. pH experiments showed that the dissolution of the porous glass increased the pH of the surrounding solution. The cell culture results showed that keratocytes adhered onto the surface of each of the porous glass structures, but cell adhesion and spreading was greatest for the 98a bio-glass. Cytokine production by all porous glass samples was similar to that of the negative control indicating that the glasses do not induce a cytokine driven inflammatory response. Cell culture results support the potential use of synthetic porous bio-glass as an OOKP skirt material in terms of limited inflammatory potential and capacity to induce and support tissue ingrowth.

STS-59 Endeavour's aft cargo bay in orbit

NASA Image and Video Library

1994-04-10

STS059-50-011 (9-20 April 94) --- A greenish appearing aurora forms the backdrop for this 35mm scene of the Earth orbiting Space Shuttle Endeavour's aft cargo bay. Featured in the bay are the antennae for the SIR-C/X-SAR imaging radar instruments, illuminated by moonlight. The crew sighted the southern lights (aurora australis) several times during each of the eleven days of the mission.

Aeroacoustic effects of reduced aft tip speed at constant thrust for a model counterrotation turboprop at takeoff conditions

NASA Technical Reports Server (NTRS)

Woodward, Richard P.; Hughes, Christopher E.

1990-01-01

A model high-speed, advanced counterrotation propeller, F7/A7, was tested in the anechoic wind tunnel at simulated takeoff and approach conditions of Mach 0.2. The propeller was operated in a baseline configuration with the forward and aft rotor blade setting angles and forward and aft rotational speeds essentially equal. Two additional configurations were tested with the aft rotor at increased blade setting angles and the rotational speed reduced to achieve overall performance similar to that of the baseline configuration. Acoustic data were taken with an axially translating microphone probe that was attached to the tunnel floor. Concurrent aerodynamic data were taken to define propeller operating conditions.

MS Massimino on aft flight deck during EVA 5

NASA Image and Video Library

2002-03-09

STS109-E-5761 (9 March 2002) --- Astronaut Michael J. Massimino, STS-109 mission specialist, looks through an overhead window on the aft flight deck of the Space Shuttle Columbia during the crew’s final interface with the Hubble Space Telescope (HST). The telescope was released at 4:04 a.m. (CST). The image was recorded with a digital still camera.

Caldwell in the aft FD of STS-118 Space Shuttle Endeavor

NASA Image and Video Library

2007-08-12

ISS015-E-22145 (12 Aug. 2007) --- Astronaut Tracy Caldwell, STS-118 mission specialist, looks over her shoulder for a photo while working the controls on the aft flight deck of Space Shuttle Endeavour while docked with the International Space Station.

Autogenic-Feedback Training (AFT) as a preventive method for space motion sickness: Background and experimental design

NASA Technical Reports Server (NTRS)

Cowings, Patricia S.; Toscano, William B.

1993-01-01

Finding an effective treatment for the motion sickness-like symptoms that occur in space has become a high priority for NASA. The background research is reviewed and the experimental design of a formal life sciences shuttle flight experiment designed to prevent space motion sickness in shuttle crew members is presented. This experiment utilizes a behavioral medicine approach to solving this problem. This method, Autogenic-Feedback Training (AFT), involves training subjects to voluntarily control several of their own physiological responses to environmental stressors. AFT has been used reliably to increase tolerance to motion sickness during ground-based tests in over 200 men and women under a variety of conditions that induce motion sickness, and preliminary evidence from space suggests that AFT may be an effective treatment for space motion sickness as well. Proposed changes to this experiment for future manifests are included.

96. View aft, port side, from just forward of the ...

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

96. View aft, port side, from just forward of the mizzenmast. Cans in foreground store Fluid Film, used to protect structural steel below waterline from oxidation. Sails stored on shelving in background have since been moved to Museum Storage. - Ship BALCLUTHA, 2905 Hyde Street Pier, San Francisco, San Francisco County, CA

Why the NEA and AFT Sought To Merge--and Failed.

ERIC Educational Resources Information Center

Fusarelli, Lance D.; Cooper, Bruce S.

1999-01-01

Four key reasons underlie the push for teacher union solidarity in 1998: desire to fulfill Al Shanker's dream of a unified mission, to end union competition, to bolster Democratic Party weaknesses, and to stop privatization. The NEA/AFT merger failed because of conflicting organizational cultures and teachers' gradualist, localist, and…

KSC-04pd0523

NASA Image and Video Library

2004-03-05

KENNEDY SPACE CENTER, FLA. - At the SRB Assembly and Refurbishment Facility, STS-114 crew members look at the booster separation motors (BSM) on a solid rocket booster aft skirt. The BSMs have had booster trowlable ablative removed by liquid nitrogen cutting. The STS-114 crew is at KSC for familiarization with Shuttle and mission equipment. The mission is Logistics Flight 1, which is scheduled to deliver supplies and equipment, plus the external stowage platform, to the International Space Station.

Space shuttle main engine high pressure fuel pump aft platform seal cavity flow analysis

NASA Technical Reports Server (NTRS)

Lowry, S. A.; Keeton, L. W.

1987-01-01

A general purpose, three-dimensional computational fluid dynamics code named PHOENICS, developed by CHAM Inc., is used to model the flow in the aft-platform seal cavity in the high pressure fuel pump of the space shuttle main engine. The model is used to predict the temperatures, velocities, and pressures in the cavity for six different sets of boundary conditions. The results are presented as input for further analysis of two known problems in the region, specifically: erratic pressures and temperatures in the adjacent coolant liner cavity and cracks in the blade shanks near the outer diameter of the aft-platform seal.

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

MS Reilly with laser range finder on aft flight deck

NASA Image and Video Library

2001-07-14

STS104-E-5026 (14 July 2001) --- Positioned near a window on the aft flight deck of the Space Shuttle Atlantis, astronaut James F. Reilly, STS-104 mission specialist, uses a laser ranging device to hone in on the International Space Station (ISS) during pre-docking operations about 237 miles above Earth.

Computational and Experimental Study of Supersonic Nozzle Flow and Aft-Deck Interactions

NASA Technical Reports Server (NTRS)

Bruce, Walter E., IV; Carter, Melissa B.; Elmiligui, Alaa A.; Winski, Courtney S.; Nayani, Sudheer N.; Castner, Raymond S.

2016-01-01

NASA has been conducting research into reducing sonic boom and changing FAA regulations to allow for supersonic commercial transport over land in the United States. This particular study looks at a plume passing through a shock generated from an aft deck on a nacelle; the aft deck is meant to represent the trailing edge of a wing. NASA Langley Research Center USM3D CFD code results are compared to the experimental data taken at the NASA Glenn Research Center 1-foot by 1-foot Supersonic Wind Tunnel. This study included examining two turbulence models along with different volume sourcing methods for grid generation. The results show that using the k-epsilon turbulence model within USM3D produced shock signatures that closely follow the experimental data at a variety of nozzle pressure ratio settings.

Compartment A20 construction stories locker looking from forward to aft ...

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

Compartment A-20 construction stories locker looking from forward to aft showing wooden ladder and storage bins. Heavy frame supports armored protective deck. Armor plate hatch at top left penetrates protective deck. (05) - USS Olympia, Penn's Landing, 211 South Columbus Boulevard, Philadelphia, Philadelphia County, PA

Development and Implementation of Environmentally Compatible Solid Film Lubricants

NASA Technical Reports Server (NTRS)

Novak, Howard L.; Hall, Phillip B.

1999-01-01

Multi-body launch vehicles require the use of Solid Film Lubricants (SFLs) to allow for unrestricted relative motion between structural assemblies and components during lift-off and ascent into orbit. The Space Shuttle Solid Rocket Booster (SRB), uses a dual coat, ceramic-bonded high temperature SFL in several locations such as restraint hardware between the SRB aft skirt and the Mobile Launch Platform (MLP), the aft SRB/External Tank (ET) attach struts, and the forward skirt SRB/ET attach ball assembly. Future launch systems may require similar applications of SFLs for attachment and restraint hardware. A family of environmentally compatible non-lead/antimony bearing alternative SFLs have been developed including a compatible repair material. In addition, commercial applications for SFLs on transportation equipment, all types of lubricated fasteners, and energy related equipment allow for wide usage's of these new lubricants. The new SFLs trade named BOOSTERLUBE is a family of single layer thin film (0.001 inch maximum) coatings that are a unique mixture of non-hazardous pigments in a compatible resin system that allows for low temperature curing (450 F). Significant savings in energy and processing time as well as elimination of hazardous material usage and disposal would result from the non-toxic one-step SFL application. Compatible air-dry field repair lubricants will help eliminate disassembly of launch vehicle restraint hardware during critical time sensitive assembly operations.

SRB Processing Facilities Media Event

NASA Image and Video Library

2016-03-01

Inside the Booster Fabrication Facility (BFF) at NASA’s Kennedy Space Center in Florida, members of the news media view the right-hand aft skirt that will be used on a solid rocket booster for NASA’s Space Launch System (SLS) rocket. Orbital ATK is contractor for NASA’s Marshall Space Flight Center in Alabama, and operates the BFF to prepare aft booster segments and hardware for the SLS solid rocket boosters. At far right, in the royal blue shirt, Rick Serfozo, Orbital ATK Florida site director, talks to the media. The SLS rocket and Orion spacecraft will launch on Exploration Mission-1 in 2018. The Ground Systems Development and Operations Program is preparing the infrastructure to process and launch spacecraft for deep-space missions and the journey to Mars.

AFT Program Description Navigation/Strike Tasks. Phase II,

DTIC Science & Technology

1972-09-01

1 Subroutine ............... 2- 96 2-23 Data Input/Output - PMSG : 1 Subroutine ................ 2-97 2-24 Data Input/Output - LPMSG: 1 Subroutine...T99DI3 GOFLAG Exercise Start Flag PAD Roll Rate (degrees/second) PHIS Bank Angle (degrees) PMSG 17 KBP Message INPUT STUDENT FILE DATA 2-41 PMSG T3 KBP...Message CRASH PMSG T4 KBP Message DEPRESS THE RESET-TO-ZERO CONSOLE BUTTON PSI F-4 Heading (degrees) PSIAFT Desired AFT Heading RCIS Average Rate-of

Closeup view of the mid deck aft wall of the ...

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

Close-up view of the mid deck aft wall of the Orbiter Discovery showing a mission specific configuration of stowage lockers within the modular system designed for maximum flexibility. This photograph was taken at Kennedy Space Center. - Space Transportation System, Orbiter Discovery (OV-103), Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

General view looking aft along the starboard side of the ...

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

General view looking aft along the starboard side of the Orbiter Discovery in the Vehicle Assembly Building at NASA's Kennedy Space Center. This view shows a close up view of the reinforced carbon-carbon leading edge of the Orbiter wing. - Space Transportation System, Orbiter Discovery (OV-103), Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Astronaut Leestma during an EVA in the aft cargo hold

NASA Image and Video Library

1984-10-13

41G-101-014 (13 October 1984) --- Astronaut David C. Leestma, in a 35mm frame exposed by fellow mission specialist, Astronaut Kathryn D. Sullivan, participates in extravehicular activity of Oct. 11 in the Challenger's aft cargo bay. Leestma's right hand (out of frame) was inside a special work station called the orbital refueling system (ORS).

Effect of reduced aft diameter and increased blade number of high-speed counterrotation propeller performance

NASA Technical Reports Server (NTRS)

Gayle, E. Rose; Jeracki, Robert J.

1989-01-01

Performance data of 0.17-scale model counterrotation pusher propeller configurations were taken in the NASA Lewis 8- by 6-Foot Supersonic Wind Tunnel at Mach numbers of 0.66, 0.71, 0.75, and 0.79. These tests investigated the aerodynamic performance of the unducted fan (UDF) demonstrator propeller engine developed in a joint program by General Electric and NASA. Data were recorded to show the effect on counterrotation propeller cruise efficiency of two takeoff noise-reduction concepts. These two concepts are reduced aft blade diameter and increased forward blade number. The four configurations tested were a baseline (F1/A1 8/8) configuration, a reduced aft diameter (F1/A3 8/8) configuration, an increase forward blade number (F1/A1 9/8) configuration, and a combination of the latter two (F1/A3 9/8) configurations. Data were collected with a complex counterrotation propeller test rig via rotating thrust and torque balances and pressure instrumentation. Data comparisons documented the power differences between the baseline and the reduced aft diameter concepts. Performance comparisons to the baseline configuration showed that reducing the aft blade diameter reduced the net efficiency, and adding a blade to the front rotor increased the net efficiency. The combination of the two concepts showed only slightly lower net efficiency than the baseline configuration. It was also found that the counterrotation demonstrator propeller model (F7/A7 8/8) configuration outperformed the baseline (F1/A1 8/8) configuration.

Effect of reduced aft diameter and increased blade number on high-speed counterrotation propeller performance

NASA Technical Reports Server (NTRS)

Rose, Gayle E.; Jeracki, Robert J.

1989-01-01

Performance data of 0.17-scale model counterrotation pusher propeller configurations were taken in the NASA Lewis 8- by 6-Foot Supersonic Wind Tunnel at Mach numbers of 0.66, 0.71, 0.75, and 0.79. These tests investigated the aerodynamic performance of the unducted fan (UDF) demonstrator propeller engine developed in a joint program by General Electric and NASA. Data were recorded to show the effect on counterrotation propeller cruise efficiency of two takeoff noise-reduction concepts. These two concepts are reduced aft blade diameter and increased forward blade number. The four configurations tested were a baseline (F1/A1 8/8) configuration, a reduced aft diameter (F1/A3 8/8) configuration, an increase forward blade number (F1/A1 9/8) configuration, and a combination of the latter two (F1/A3 9/8) configurations. Data were collected with a complex counterrotation propeller test rig via rotating thrust and torque balances and pressure instrumentation. Data comparisons documented the power differences between the baseline and the reduced aft diameter concepts. Performance comparisons to the baseline configuration showed that reducing the aft blade diameter reduced the net efficiency, and adding a blade to the front rotor increased the net efficiency. The combination of the two concepts showed only slightly lower net efficiency than the baseline configuration. It was also found that the counterrotation demonstrator propeller model (F7/A7 8/8) configuration outperformed the baseline (F1/A1 8/8) configuration.

KSC-06pd0261

NASA Image and Video Library

2005-12-27

VANDENBERG AIR FORCE BASE, CALIF. - Inside Orbital Sciences Building 1555 at Vandenberg Air Force Base in California, a worker installs one of the fins on the aft skirt of the Pegasus XL rocket that will launch the Space Technology 5 spacecraft later this month. ST5 contains three micro-satellites that will be positioned in a "string of pearls" constellation to perform simultaneous multi-point measurements of the Earth's magnetic field using highly sensitive magnetometers. The scheduled launch date is Feb. 28.

KSC-06pd0258

NASA Image and Video Library

2005-12-27

VANDENBERG AIR FORCE BASE, CALIF. - Inside Orbital Sciences Building 1555 at Vandenberg Air Force Base in California, workers move the aft skirt toward the Pegasus XL launch vehicle for mating. The Pegasus will launch the Space Technology 5 spacecraft later this month. ST5 contains three micro-satellites that will be positioned in a "string of pearls" constellation to perform simultaneous multi-point measurements of the Earth's magnetic field using highly sensitive magnetometers. The scheduled launch date is Feb. 28.

RMS upper boom framed by aft flight deck viewing window W10

NASA Technical Reports Server (NTRS)

1983-01-01

Remote Manipulator System (RMS) upper arm boom (tear in multilayer beta cloth) deployed during dynamic interaction test using Payload Flight Test Article (PFTA) is visible outside aft viewing window W10. RMS 'Canada' insignia or logo appears on boom.

Commander Truly on aft flight deck holding communication kit assembly (ASSY)

NASA Image and Video Library

1983-09-05

STS008-04-106 (30 Aug-5 Sept 1983) --- On aft flight deck, Richard M. Truly, STS-8 commander, holds communication kit assembly (ASSY) headset (HDST) interface unit (HIU) and mini-HDST in front of the on orbit station. Hasselblad camera is positioned on overhead window W8.

General view of the aft Flight Deck looking at the ...

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

General view of the aft Flight Deck looking at the mission specialist seats directly behind and to the side of the commander and pilot's seats. These seats are removed, packed and stowed during on-orbit activities. This image was taken at Kennedy Space Center. - Space Transportation System, Orbiter Discovery (OV-103), Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

25. Hot well, as seen from port side aft. Waste ...

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

25. Hot well, as seen from port side aft. Waste water overflow pipe appears at left, behind which is bilge pump. At base of hot well on either side are reciprocating boiler feedwater pumps driven from hot well crosshead. (Labels were applied by HAER recording team and are not original to equipment.) - Steamboat TICONDEROGA, Shelburne Museum Route 7, Shelburne, Chittenden County, VT

27. VIEW LOOKING AFT ON STARBOARD SIDE OF MAIN DECK ...

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

27. VIEW LOOKING AFT ON STARBOARD SIDE OF MAIN DECK WITH TENDER ANNIE RUTH ALONGSIDE. COVER OF FORWARD COMPANIONWAY HAS BEEN PLACED ON MAIN DECK; SUN AWNING A TYPICAL FEATURE IN TROPICAL CLIMATES. CREW MEMBERS UNKNOWN Original 4-3/4'x6-3/4' photograph taken c. 1930? - Pilot Schooner "Alabama", Moored in harbor at Vineyard Haven, Vineyard Haven, Dukes County, MA

28. SONAR CONTROL ROOM FORWARD LOOKING AFT SHOWING AN/SQS23G ...

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

28. SONAR CONTROL ROOM - FORWARD LOOKING AFT SHOWING AN/SQS-23G DETECTING-RANGING SET, MARK & CONTROL PANEL, CAN-55134 RECORDER, SPEED INDICATOR, VARIOUS ALARMS AND INTERNAL COMMUNICATION CIRCUITS. - U.S.S. HORNET, Puget Sound Naval Shipyard, Sinclair Inlet, Bremerton, Kitsap County, WA

Static and dynamic deflection studies of the SRM aft case-nozzle joint

NASA Technical Reports Server (NTRS)

Christian, David C.; Kos, Lawrence D.; Torres, Isaias

1989-01-01

The redesign of the joints on the solid rocket motor (SRM) has prompted the need for analyzing the behavior of the joints using several different types of analyses. The types of analyses performed include modal analysis, static analysis, transient response analysis, and base driving response analysis. The forces used in these analyses to drive the mathematical model include SRM internal chamber pressure, nozzle blowout and side forces, shuttle vehicle lift-off dynamics, SRM pressure transient rise curve, gimbal forces and moments, actuator gimbal loads, and vertical and radial bolt preloads. The math model represented the SRM from the aft base tangent point (1,823.95 in) all the way back to the nozzle, where a simplified, tuned nozzle model was attached. The new design used the radial bolts as an additional feature to reduce the gap opening at the aft dome/nozzle fixed housing interface.

NEA/AFT Membership: The Critical Issues. EPI Series on Teacher Unions.

ERIC Educational Resources Information Center

Haar, Charlene K.; Lieberman, Myron

This booklet, one in the Education Policy Institute series about teacher union issues, examines issues related to membership in the National Education Association (NEA) and American Federation of Teachers (AFT). Both unions aggressively strive to enroll more members or require teachers to pay agency fees. If teachers want to change union policy,…

Brown at aft controls during PAMS STU deploy

NASA Image and Video Library

1996-05-22

S77-E-5066 (22 May 1996) --- Astronaut Curtis L. Brown, Jr., pilot, is seen on the starboard side of the Space Shuttle Endeavour's aft flight deck just prior to the deployment of the Satellite Test Unit (STU), part of the Passive Aerodynamically Stabilized Magnetically Damped Satellite (PAMS). Brown's image was captured with an Electronic Still Camera (ESC). Minutes later the camera was being used to document the deployment of PAMS-STU. The six-member crew will continue operations (tracking, rendezvousing and station-keeping) with PAMS-STU periodically throughout the remainder of the mission.

Recovery of piece of the aft center segment tang joint of SRB

NASA Technical Reports Server (NTRS)

1986-01-01

A 4000 pound, 11' x 20' piece of the aft center segment tang joint of the Shuttle Challenger's right-hand solid rocket booster is off loaded from the Stena Workhorse after its recovery on April 13, 1986. The burned out area is 15' x 28'.

Compartment A19, paint & oils locker from bulkhead #9 aft ...

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

Compartment A-19, paint & oils locker from bulkhead #9 aft to forward; wood storage shelves at center of photograph are for storing containers. Sea valve at lower right is on the starboard side. This would be opened if it was necessary to scuttle the vessel. Heavy frame marked "A-2" supports armored protective deck. (03) - USS Olympia, Penn's Landing, 211 South Columbus Boulevard, Philadelphia, Philadelphia County, PA

18. VIEW AFT INTO ENGINE ROOM AND UP INTO CAPTAIN'S ...

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

18. VIEW AFT INTO ENGINE ROOM AND UP INTO CAPTAIN'S CABIN. THE AFTER BULKHEAD OF THE ENGINE ROOM WAS REMOVED WHEN THE ENGINE WAS SALVAGED. ENGINE BED AND GEARBOX ARE REMNANTS OF THE ENGINE INSTALLATION. CABLES AND CHAINS ARE IN PLACE TO HELP STABILIZE THE HULL AND TRANSOM. - Auxiliary Fishing Schooner "Evelina M. Goulart", Essex Shipbuilding Museum, 66 Main Street, Essex, Essex County, MA

Oblique view at ground level looking at the aft and ...

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

Oblique view at ground level looking at the aft and port side of the Orbiter Discovery in the Vehicle Assembly Building at NASA's Kennedy Space Center. Note that the Orbiter Maneuvering System/Reaction Control System pods and the Shuttle Main Engines are removed in this image. - Space Transportation System, Orbiter Discovery (OV-103), Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

MS Linnehan watches EVA 2 from aft flight deck

NASA Image and Video Library

2002-03-05

STS109-E-5621 (5 March 2002) --- Astronaut Richard M. Linnehan, mission specialist, monitors the STS-109 mission's second space walk from the aft flight deck of the Space Shuttle Columbia. Astronauts James H. Newman and Michael J. Massimino were working on the Hubble Space Telescope (HST), temporarily captured in the shuttle's cargo bay. Linnehan had participated in the mission's first space walk on the previous day. This image was recorded with a digital still camera.

Cassidy holds laser range finder in aft FD during Joint Operations

NASA Image and Video Library

2009-07-28

S127-E-011291 (28 July 2009) --- Astronauts Tom Marshburn (left) and Christopher Cassidy, both STS-127 mission specialists, look through an overhead window on the aft flight deck of Space Shuttle Endeavour during flight day 14 activities. Cassidy is holding a handheld laser ranging device -- designed to measure the range between two spacecraft.

Looking Back, Looking Ahead: A Reflection on Paraprofessionals and the AFT

ERIC Educational Resources Information Center

Johnson, Loretta

2016-01-01

In this article, secretary-treasurer of the American Federation of Teachers (AFT) Lorretta Johnson reflects on her early work as a paraprofessional at Liberty Elementary School (Baltimore, Maryland) and what sparked her union activism nearly 50 years ago in 1966. It was that year that she and her colleagues joined the Baltimore Teachers Union…

Feeding of swimming Paramecium with fore-aft asymmetry in viscous fluid

NASA Astrophysics Data System (ADS)

Zhang, Peng; Jana, Saikat; Giarra, Matthew; Vlachos, Pavlos; Jung, Sunghwan

2013-11-01

Swimming behaviours and feeding efficiencies of Paramecium Multimicronucleatum with fore-aft asymmetric body shapes are studied experimentally and numerically. Among various possible swimming ways, ciliates typically exhibit only one preferred swimming directions in favorable conditions. Ciliates, like Paramecia, with fore-aft asymmetric shapes preferably swim towards the slender anterior while feeding fluid to the oral groove located at the center of the body. Since both feeding and swimming efficiencies are influenced by fluid motions around the body, it is important to reveal the fluid mechanics around a moving object. Experimentally, μ-PIV methods are employed to characterize the source-dipole streamline patterns and fluid motions around Paramecium. Numerical simulations by boundary element methods are also used to evaluate surface stresses and velocities, which give insights into the efficiencies of swimming and feeding depending on body asymmetry. It is concluded that a slender anterior and fat posterior increases the combined efficiency of swimming and feeding, which matches well with actual shapes of Paramecium. Discrepancies between experiments and simulations are also discussed.

Skirting the issue: women and international health in historical perspective.

PubMed Central

Birn, A E

1999-01-01

Over the last decades women have become central to international health efforts, but most international health agencies continue to focus narrowly on the maternal and reproductive aspects of women's health. This article explores the origins of this paradigm as demonstrated in the emergence of women's health in the Rockefeller Foundation's public health programs in Mexico in the 1920s and 1930s. These efforts bore a significant reproductive imprint; women dispensed and received services oriented to maternal and childbearing roles. Women's health and social advocacy movements in Mexico and the United States partially shaped this interest. Even more important, the emphasis on women in the Rockefeller programs proved an expedient approach to the Foundation's underlying goals: promoting bacteriologically based public health to the government, medical personnel, business interests, and peasants; helping legitimize the Mexican state; and transforming Mexico into a good political and commercial neighbor. The article concludes by showing the limits to the maternal and reproductive health model currently advocated by most donor agencies, which continue to skirt--or sidestep--major concerns that are integral to the health of women. Images p400-a p401-a p402-a p403-a PMID:10076494

KSC-06pd0260

NASA Image and Video Library

2005-12-27

VANDENBERG AIR FORCE BASE, CALIF. - Inside Orbital Sciences Building 1555 at Vandenberg Air Force Base in California, workers get ready to install one of the fins on the aft skirt of the Pegasus XL rocket that will launch the Space Technology 5 spacecraft later this month. ST5 contains three micro-satellites that will be positioned in a "string of pearls" constellation to perform simultaneous multi-point measurements of the Earth's magnetic field using highly sensitive magnetometers. The scheduled launch date is Feb. 28.

KSC-02pd0090

NASA Image and Video Library

2002-02-04

KENNEDY SPACE CENTER, FLA. -- At Cape Canaveral Air Force Station, Fla., Mark McManus makes a final inspection of the first stage aft skirt on the Pegasus XL rocket, the vehicle that will launch the High Energy Solar Spectroscopic Imager (HESSI). The primary mission of HESSI is to explore the basic physics of particle acceleration and energy release in solar flares. The launch of PegasusXL/HESSI is scheduled for Feb. 5, 2002, from beneath the Orbital Sciences Corp. L-1011 aircraft seen here

KSC-04PD-0392

NASA Technical Reports Server (NTRS)

2004-01-01

KENNEDY SPACE CENTER, FLA. At the SRB Assembly and Refurbishment Facility, STS-114 Commander Eileen Collins (center) is flanked by Bob Herman (left), SRB deputy associate program manager with United Space Alliance, and Jim Carleton (right), director, SRB Program Management, as they walk past solid rocket booster aft skirts. The crew is at KSC for familiarization with Shuttle and mission equipment. The STS-114 mission is Logistics Flight 1, which is scheduled to deliver supplies and equipment, plus the external stowage platform, to the International Space Station.

STS-26 Pilot Covey, wearing sleep mask, rests on aft flight deck

NASA Technical Reports Server (NTRS)

1988-01-01

STS-26 Pilot Richard O. Covey, wearing sleep mask (blindfold) and a headset, props his feet under the pilots seat and rests his head and back on the aft flight deck onorbit station panels while he sleeps. At Covey's right are the mission station control panels.

STS-33 MS Carter operates translation hand control (THC) on aft flight deck

NASA Technical Reports Server (NTRS)

1989-01-01

STS-33 Mission Specialist (MS) Manley L. Carter, Jr operates translation hand control (THC) at the aft flight deck onorbit station while peering out overhead window W7. Carter's communications kit assembly headset microphone extends across his face.

Effects of Bifurcations on Aft-Fan Engine Nacelle Noise

NASA Technical Reports Server (NTRS)

Nark, Douglas M.; Farassat, Fereidoun; Pope, D. Stuart; Vatsa, Veer N.

2004-01-01

Aft-fan engine nacelle noise is a significant factor in the increasingly important issue of aircraft community noise. The ability to predict such noise within complex duct geometries is a valuable tool in studying possible noise attenuation methods. A recent example of code development for such predictions is the ducted fan noise propagation and radiation code CDUCT-LaRC. This work focuses on predicting the effects of geometry changes (i.e. bifurcations, pylons) on aft fan noise propagation. Beginning with simplified geometries, calculations show that bifurcations lead to scattering of acoustic energy into higher order modes. In addition, when circumferential mode number and the number of bifurcations are properly commensurate, bifurcations increase the relative importance of the plane wave mode near the exhaust plane of the bypass duct. This is particularly evident when the bypass duct surfaces include acoustic treatment. Calculations involving more complex geometries further illustrate that bifurcations and pylons clearly affect modal content, in both propagation and radiation calculations. Additionally, results show that consideration of acoustic radiation results may provide further insight into acoustic treatment effectiveness for situations in which modal decomposition may not be straightforward. The ability of CDUCT-LaRC to handle complex (non-axisymmetric) multi-block geometries, as well as axially and circumferentially segmented liners, allows investigation into the effects of geometric elements (bifurcations, pylons).

13. Coal ejectors mounted on aft bulkhead of coal bunker. ...

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

13. Coal ejectors mounted on aft bulkhead of coal bunker. Ejectors were used to flush overboard live coals and clinkers from firebed (pipe for carrying coals overboard has been removed from ejector in foreground). Coal doors from bunker appear beside ejector in foreground). Coal doors from bunker appear beside ejectors at deck; note firing shovels in background against hull. - Steamboat TICONDEROGA, Shelburne Museum Route 7, Shelburne, Chittenden County, VT

Closeup view of the payload bay side of the aft ...

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

Close-up view of the payload bay side of the aft crew compartment bulkhead of the Orbiter Discovery. Showing the airlock, the beam-truss attach structure supporting it and its attach points to the payload bay sill longerons. This photograph was taken in the Orbiter Processing Facility at Kennedy Space Center. - Space Transportation System, Orbiter Discovery (OV-103), Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Detailed view inside the aft fuselage of the Orbiter Discovery ...

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

Detailed view inside the aft fuselage of the Orbiter Discovery showing the network of supply, distribution and feed lines to deliver fuel, oxidizer and other vital gasses and fluids to the Space Shuttle Main Engines (SSMEs). This photograph was taken in the Orbiter Processing Facility at the Kennedy Space Center. - Space Transportation System, Orbiter Discovery (OV-103), Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

General view of the aft fuselage of the Orbiter Discovery ...

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

General view of the aft fuselage of the Orbiter Discovery looking forward showing Space Shuttle Main Engines (SSMEs) installed in positions one and three and an SSME on the process of being installed in position two. This photograph was taken in the Orbiter Processing Facility at the Kennedy Space Center. - Space Transportation System, Orbiter Discovery (OV-103), Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Closeup view of the payload bay side of the aft ...

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

Close-up view of the payload bay side of the aft fuselage bulkhead of the Orbiter Discovery. This image has a detailed portions of the Remote Manipulator System and the Orbiter Maneuvering System/Reaction Control System Pods. This photograph wa taken in the Orbiter Processing Facility at Kennedy Space Center. - Space Transportation System, Orbiter Discovery (OV-103), Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Development of Lead Free Energy Absorber for Space Shuttle Blast Container

NASA Technical Reports Server (NTRS)

Ingram, T.; Balles, D.; Schricker, A.; Novak, H.

1998-01-01

The Space Shuttle vehicle (SSV) is connected to the mobile launch platform (MLP) by four aft skirt hold down studs on each solid rocket booster (SRB). Prior to lift-off, the frangible nuts inside the aft skirt blast containers (BC) are severed into two nut halves by two pyrotechnic booster cartridges. This action releases the SSV and allows the hold down studs to eject through the aft skirt bore and then down into the MLP. USBI has been tasked to upgrade the BC for two specific reasons; 1. to eliminate lead for environmental concerns, and 2. to reduce the chance of nut recontact with the holddown stud. Nut recontact with the stud has been identified as a likely contributor to stud hangups. This upgrade will replace the lead liner with an aluminum foam material. The aluminum foam used as a energy absorber is a proven design in many other aerospace/defense applications. Additional benefits of using the open cell, energy absorbent aluminum foam in place of the solid lead liner are: A. Lead handling/ exposure, and possible contamination, along with hazardous waste disposal will be eliminated; B. Approximately 200 lbs. weight savings will be contributed to each Space Shuttle flight by using aluminum foam over lead; C. The new aluminum liner is designed to catch all shrapnel from frangible nuts thus virtually eliminating chance of foreign object debris (FOD) exiting the HDP, and causing potential damage to the vehicle; D. Potential of using the lighter aluminum liner over lead, allows for easier assembly and disassembly of blast container elements, also allowing for improvements in safety, operator handling, and efficiency of operations. Six BC firing tests will be required to determine if the new liner material will perform in a way to decrease the chance of stud hangups and enhance the ability of the BC to retain blast debris. Testing will be performed at the Kennedy Space Center (KSC) facility known as the Launch Equipment Test Facility (LETF), and will simulate the

Cassidy uses laser range finder in the aft FD during Joint Operations

NASA Image and Video Library

2009-07-28

S127-E-011166 (28 July 2009) --- Astronaut Christopher Cassidy, STS-127 mission specialist, uses a handheld laser ranging device -- designed to measure the range between two spacecraft -- through one of the overhead windows on the aft flight deck of Space Shuttle Endeavour after undocking from the International Space Station.

77 FR 37768 - Airworthiness Directives; Aeronautical Accessories, Inc., High Landing Gear Aft Crosstube Assembly

Federal Register 2010, 2011, 2012, 2013, 2014

2012-06-25

... establishing a life limit and creating a component history card or equivalent record for one of the affected... crosstube already has limits established) and creating a component history card or equivalent record for aft...

View forward to aft of dynamo room (compartment A21) showing ...

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

View forward to aft of dynamo room (compartment A-21) showing port ventilation fan; electrical generator is at left center of photograph. Platform for generator is at bottom center of photograph. Hatch for passing powder up from magazine is located just above the generator base. Frames support armored protective deck. (018) - USS Olympia, Penn's Landing, 211 South Columbus Boulevard, Philadelphia, Philadelphia County, PA

Astronaut Daniel W. Bursch, mission specialist, pauses during a photography session on the aft

NASA Technical Reports Server (NTRS)

1996-01-01

STS-77 ESC VIEW --- Astronaut Daniel W. Bursch, mission specialist, pauses during a photography session on the aft flight deck of the Space Shuttle Endeavour. The scene was recorded with an Electronic Still Camera (ESC).

General view looking aft from the starboard side of the ...

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

General view looking aft from the starboard side of the mid fuselage of the Orbiter Discovery. This view has a close-up view of the remote sensor boom and its retention mechanisms at its attach points to the starboard longeron. This photograph was taken in the Orbiter Processing Facility at the Kennedy Space Center. - Space Transportation System, Orbiter Discovery (OV-103), Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

26. Port side of engine room looking forward from aft ...

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

26. Port side of engine room looking forward from aft bulkhead. This area contains mostly electrical equipment. Two single-cylinder steam-driven dynamos are located near the engine bed, one at right foreground, the other in background. At left in image are a motor-generator set installed to convert DC current (from dynamos) to AC current. Edge-on view of control panel appears near center of image. - Ferry TICONDEROGA, Route 7, Shelburne, Chittenden County, VT

STS-46 ESA MS Nicollier and PLC Hoffman pose on OV-104's aft flight deck

NASA Technical Reports Server (NTRS)

1992-01-01

STS-46 European Space Agency (ESA) Mission Specialist (MS) Claude Nicollier (left) and MS and Payload Commander (PLC) Jeffrey A. Hoffman pose in front of the onorbit station controls on the aft flight deck of Atlantis, Orbiter Vehicle (OV) 104. The overhead windows W7 and W8 appear above their heads and the aft flight deck viewing windows W9 and W10 behind them. Hoffman and Nicollier have been training together for a dozen years at JSC. Hoffman was an astronaut candidate in 1978 and Nicollier accompanied a group of trainees in 1980. Note the partially devoured chocolate Space Shuttle floating near the two.

Analysis of SRB reentry acoustic environments. [aeroacoustic spectra determined from wind tunnel tests

NASA Technical Reports Server (NTRS)

Coffin, T.; Dandridge, R. E.; Haddock, U. W.

1979-01-01

Space shuttle solid rocket booster reentry aeroacoustic environments were estimated. Particular emphasis was given to the aft skirt/exit plane region for the Mach number regime 0.6 = or greater than M infinity = or less than 3.5. The analysis is based on the evaluation of wind tunnel model results in conjunction with Monte Carlo simulation of trajectory parameters. The experimental approach is described as well as the evaluation process utilized. Predicted environments are presented in terms of one-third octave band spectra representing space averaged values for critical regions on the solid rocket booster.

Enhancement Of Water-Jet Stripping Of Foam

NASA Technical Reports Server (NTRS)

Cosby, Steven A.; Shockney, Charles H.; Bates, Keith E.; Shalala, John P.; Daniels, Larry S.

1995-01-01

Improved robotic high-pressure-water-jet system strips foam insulation from parts without removing adjacent coating materials like paints, primers, and sealants. Even injects water into crevices and blind holes to clean out foam, without harming adjacent areas. Eliminates both cost of full stripping and recoating and problem of disposing of toxic solutions used in preparation for coating. Developed for postflight refurbishing of aft skirts of booster rockets. System includes six-axis robot provided with special end effector and specially written control software, called Aftfoam. Adaptable to cleaning and stripping in other industrial settings.

General view of a Solid Rocket Motor Nozzle in the ...

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

General view of a Solid Rocket Motor Nozzle in the Solid Rocket Booster (SRB) Assembly and Refurbishment Facility at Kennedy Space Center, being prepared to be mated with the Aft Skirt. In this view you can see the attach brackets where the Thrust Vector Control System actuators connect to the nozzle which can swivel the nozzle up to 3.5 degrees to redirect the thrust to steer and maintain the Shuttle's programmed trajectory. - Space Transportation System, Solid Rocket Boosters, Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

STS-46 aft flight deck payload station 'Marsha's workstation' aboard OV-104

NASA Technical Reports Server (NTRS)

1992-01-01

STS-46 payload station nicknamed 'Marsha's (Ivins) workstation' on the aft flight deck of Atlantis, Orbiter Vehicle (OV) 104, is cluttered with food, cameras, camera gear, cassettes, flight text material, and other paraphernalia. This area is just behind the commanders station. Fellow crewmembers nicknamed the station and good-naturedly kidded Ivins about the mess.

STS-26 Pilot Covey, wearing sleep mask, rests on aft flight deck

NASA Image and Video Library

1988-10-03

STS026-09-021 (3 Oct 1988) --- Astronaut Richard O. Covey, STS-26 pilot, wearing sleep mask (blindfold) and a headset, props his feet under the pilots seat and rests his head and back on the aft flight deck on orbit station panels while he sleeps. At Covey's right are the mission station control panels.

Adaptive Aft Signature Shaping of a Low-Boom Supersonic Aircraft Using Off-Body Pressures

NASA Technical Reports Server (NTRS)

Ordaz, Irian; Li, Wu

2012-01-01

The design and optimization of a low-boom supersonic aircraft using the state-of-the- art o -body aerodynamics and sonic boom analysis has long been a challenging problem. The focus of this paper is to demonstrate an e ective geometry parameterization scheme and a numerical optimization approach for the aft shaping of a low-boom supersonic aircraft using o -body pressure calculations. A gradient-based numerical optimization algorithm that models the objective and constraints as response surface equations is used to drive the aft ground signature toward a ramp shape. The design objective is the minimization of the variation between the ground signature and the target signature subject to several geometric and signature constraints. The target signature is computed by using a least-squares regression of the aft portion of the ground signature. The parameterization and the deformation of the geometry is performed with a NASA in- house shaping tool. The optimization algorithm uses the shaping tool to drive the geometric deformation of a horizontal tail with a parameterization scheme that consists of seven camber design variables and an additional design variable that describes the spanwise location of the midspan section. The demonstration cases show that numerical optimization using the state-of-the-art o -body aerodynamic calculations is not only feasible and repeatable but also allows the exploration of complex design spaces for which a knowledge-based design method becomes less effective.

STS-33 MS Carter operates translation hand control (THC) on aft flight deck

NASA Image and Video Library

1989-11-27

STS033-93-011 (27 Nov 1989) --- Astronaut Manley L. Carter, Jr., STS-33 mission specialist, operates translation hand control (THC) at the aft flight deck on orbit station while peering out overhead window W7. Carter's communications kit assembly headset microphone extends across his face.

Flight Motor Set 360L003 (STS-29R)

NASA Technical Reports Server (NTRS)

Riehr, Glen A.

1989-01-01

The redesigned solid rocket motor (RSRM) flight set 360L003 was launched on March 13, 1989 as part of NASA space shuttle mission STS-29R. As was the case with flight sets 360L001 and 360L002 (STS-26R and STS-27R), both motors (360L003A and 360L003B) performed in an excellent manner. Evaluation of the ground environment instrumentation measurements verified thermal model analysis data and showed agreement with predicted environmental effects. The right-hand aft field joint primary heater failed during the countdown; the secondary heater was activated and performed as designed. All other field joint heaters and aft skirt thermal conditioning systems had no anomalies. Shuttle thermal imager infrared readings compared favorably with measured ground environment instrumentation data. No thermal launch commit criteria violations occurred at any time. Evaluation of the development flight instrumentation showed exceptional propulsion performance. All ballistic parameters closely matched the predicted values and were well within the required specification levels. Girth and biaxial strain gage measurements compared closely with corresponding gages on previous flight motors, static tests, and with preflight predictions. Adequate safety factors were verified. (Some ignition transient spiking was noted in a few girth gages; the spiking was determined not to be representative of actual case behavior, but an instrumentation phenomena.) The accelerometers again measured high vibration amplitude levels during the ignition transient and the reentry Max Q phases. Postflight inspection showed that all combustion gas was contained by the insulation in the field and case-to-nozzle joints. No anomalous insulation erosion patterns were found, and the seals that did directly contain motor pressure showed no heat effects, erosion, or blowby. All anomalies identified were a result of splashdown damage, with the exception of fretting in the case field joint interference (nonsealing) surfaces

Elastomeric Thermal Insulation Design Considerations in Long, Aluminized Solid Rocket Motors

NASA Technical Reports Server (NTRS)

Martin, Heath T.

2017-01-01

An all-new sounding rocket was designed at NASA's Marshall Space Flight Center that featured an aft finocyl, aluminized solid propellant grain and silica-filled ethylene-propylene-diene monomer (SFEPDM) internal insulation. Upon the initial static firing of the first of this new design, the solid rocket motor (SRM) case failed thermally just upstream of the aft closure early in the burn time. Subsequent fluid modeling indicated that the high-velocity combustion-product jets emanating from the fin-slots in the propellant grain were likely inducing a strongly swirling flow, thus substantially increasing the severity of the convective environment on the exposed portion of the SFEPDM insulation in this region. The aft portion of the fin-slots in another of the motors were filled with propellant to eliminate the possibility of both direct jet impingement on the exposed SFEPDM and the appearance of strongly swirling flow in the aft region of the motor. When static-fired, this motor's case still failed in the same axial location, and, though somewhat later than for the first static firing, still in less than 1/3rd of the desired burn duration. These results indicate that the extreme material decomposition rates of the SFEPDM in this application are not due to gas-phase convection or shear but rather to interactions with burning aluminum or alumina slag. Further comparisons with between SFEPDM performance in this design and that in other hot-fire tests provide insight into the mechanisms of SFEPDM decomposition in SRM aft domes that can guide the upcoming redesign effort, as well as other future SRM designs. These data also highlight the current limitations of modeling elastomeric insulators solely with diffusion-controlled, gas-phase thermochemistry in SRM regions with significant viscous shear and/or condense-phase impingement or flow.

Real-time thickness measurement of MCC ablator material

NASA Technical Reports Server (NTRS)

Greenway, R. Bryan, Jr.

1994-01-01

One of the most favorable characteristics of the Space Shuttle Program is the reusability of two of its primary components: the orbiter itself and the Solid Rocket Boosters (SRB). The SRB's provide the primary source of propulsion for the Space Shuttle during take-off after which they are recovered for refurbishment and reuse. During refurbishment, the SRB's are stripped of all remaining ablative (heat resistant) coating. A new layer is applied to the appropriate sections (nose cone, frustum, forward skirt, and aft skirt). It is the process of applying the ablative coating which provided the impetus for this project. The thickness of this protective layer is considered to be of primary importance to the level of thermal protection provided. The objectives of this effort are to investigate possible techniques for measuring the thickness of MCC, and if possible to test the specific capabilities of those considered good candidates for implementation. The system would be able to take measurements in real-time as close to the spray gun as possible. This will allow the information to be used in the control of the process without an inordinate time delay between a measurement and its appropriate response. The thickness of the deposited material is to be measured with less than 0.100 in if uncertainty. This is the defined tolerance window for the ablator thickness. Finally, it must operate within the confines of the chamber which encloses the turntable, robot, and spray system, and therefore is required to be insensitive to, or at least maintainable in, that environment.

Pilot Fullerton in ejection escape suit (EES) on aft flight deck

NASA Image and Video Library

1982-03-30

STS003-31-290 (30 March 1982) --- Astronaut Gordon Fullerton, STS-3 pilot, wearing communications kit assembly (ASSY) mini-headset (HDST) and ejection escape suit (EES), holds flexible hose attached to his EES vent hose fitting and second hose for commander's EES while behind pilots ejection seat (S2) seat back on the aft flight deck. Forward flight deck control panels are visible in the background. Photo credit: NASA

11. VIEW FROM JUST AFT OF THE KING POST IN ...

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

11. VIEW FROM JUST AFT OF THE KING POST IN THE FOC'S'LE OF THE EVELINA M. GOULART. FIRE EXTINGUISHER IS MOUNTED ON STUB OF FOREMAST. OBJECT AT LOWER LEFT IS A FOLDING MESS TABLE. LADDER LEADS TO DECK. CABINET AT RIGHT CENTER HOUSED SINK FOR CLEAN-UP AND COOKING. A SMALL CHINA SINK AT RIGHT CENTER SERVED FOR PERSONAL CLEAN-UP AND SHAVING. - Auxiliary Fishing Schooner "Evelina M. Goulart", Essex Shipbuilding Museum, 66 Main Street, Essex, Essex County, MA

STS-103 Wiring inspections in the aft compartment of Discovery

NASA Technical Reports Server (NTRS)

1999-01-01

Todd Biddle, with United Space Alliance, inspects wiring in the aft compartment of Discovery before launch. Electrical wire inspections and repairs in the orbiter's payload bay, external tank umbilical and engine compartment have been ongoing for more than a month and are near completion. Launch of Space Shuttle Discovery on mission STS-103 is scheduled for Dec. 11 at 11:42 p.m. from Launch Pad 39B. STS-103 is the third servicing mission for the Hubble Space Telescope.

View looking aft along the starboard side of the midfuselage ...

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

View looking aft along the starboard side of the mid-fuselage of the Orbiter Discovery. This view shows the wing profile as it intersects with the fuselage. Also note in the foreground the panels protecting the Reinforced Carbon-Carbon leading edge of the wing. This view was taken from the service platform in the Orbiter Processing Facility at Kennedy Space Center. - Space Transportation System, Orbiter Discovery (OV-103), Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Effect of underwing aft-mounted nacelles on the longitudinal aerodynamic characteristics of a high-wing transport airplane

NASA Technical Reports Server (NTRS)

Abeyounis, W. K.; Patterson, J. C., Jr.

1985-01-01

As part of a propulsion/airframe integration program, tests were conducted in the Langley 16-Foot Transonic Tunnel to determine the longitudinal aerodynamic effects of installing flow through engine nacelles in the aft underwing position of a high wing transonic transfer airplane. Mixed flow nacelles with circular and D-shaped inlets were tested at free stream Mach numbers from 0.70 to 0.85 and angles of attack from -2.5 deg to 4.0 deg. The aerodynamic effects of installing antishock bodies on the wing and nacelle upper surfaces as a means of attaching and supporting nacelles in an extreme aft position were investigated.

STS-36 Mission Specialist Hilmers with AEROLINHOF camera on aft flight deck

NASA Image and Video Library

1990-03-03

STS-36 Mission Specialist (MS) David C. Hilmers points the large-format AEROLINHOF camera out overhead window W7 on the aft flight deck of Atlantis, Orbiter Vehicle (OV) 104. Hilmers records Earth imagery using the camera. Hilmers and four other astronauts spent four days, 10 hours and 19 minutes aboard OV-104 for the Department of Defense (DOD) devoted mission.

Fabrication of the V-22 composite AFT fuselage using automated fiber placement

NASA Technical Reports Server (NTRS)

Pinckney, Robert L.

1991-01-01

Boeing Helicopters and its subcontractors are working together under an Air Force Wright Research and Development Center (WRDC)-Manufacturing-Technology Large-Composite Primary Structure Fuselage program to develop and demonstrate new manufacturing techniques for producing composite fuselage skin and frame structures. Three sets of aft fuselage skins and frames have been fabricated and assembled, and substantial reductions in fabrication and assembly costs demonstrated.

STS-116 crew at orbiter aft flight deck window during EVA 2

NASA Image and Video Library

2007-12-14

ISS014-E-09804 (14 Dec. 2006) --- From the aft flight deck on Space Shuttle Discovery, astronauts William A. (Bill) Oefelein (left), STS-116 pilot; Nicholas J. M. Patrick, mission specialist; and Mark L. Polansky, commander, look through an overhead window toward their spacewalking crewmembers, who captured the image during the mission's second of three planned sessions of extravehicular activity (EVA).

Noise of a model counterrotation propeller with reduced aft rotor diameter at simulated takeoff/approach conditions (F7/A3)

NASA Technical Reports Server (NTRS)

Woodward, Richard P.; Gordon, Eliott B.

1988-01-01

A model high-speed advanced counterrotation propeller, F7/A3, was tested in the NASA Lewis Research Center 9 by 15 foot Anechoic Wind Tunnel at simulated takeoff/approach conditions of 0.2 Mach number. Acoustic measurements were taken with an axially translating microphone probe, and with a polar microphone probe which was fixed to the propeller nacelle and could take both sideline and circumferential acoustic surveys. Aerodynamic measurements were also made to establish propeller operating conditions. The propeller was run at two setting angles (front angle/rear angle) of 36.4/43.5 and 41.1/46.4 degrees, forward rotor tip speeds from 165 to 259 m/sec, rotor spacings from 8.48 to 14.99 cm based on pitch change axis separation, and angles of attack to 16 degrees. The aft rotor diameter was 85 percent of the forward rotor diameter to reduce tip vortex-aft rotor interaction as a major interaction noise source. Results are compared with equal diameter F7/A7 data which was previously obtained under similar operating conditions. The aft rotor-alone tone was 7 dB lower for the reduced diameter aft rotor, due to reduced tip speed at constant rpm. Interaction tone levels for the F7/A3 propeller were higher at minimum row spacing and lower at maximum spacing.

STS-109 MS Linnehan on aft flight deck with laser rangefinder

NASA Image and Video Library

2002-03-03

STS109-346-011 (3 March 2002) --- Astronaut Richard M. Linnehan, STS-109 mission specialist, uses a laser ranging device designed to measure the range between two spacecraft. Linnehan positioned himself on the cabin's aft flight deck as the Space Shuttle Columbia approached the Hubble Space Telescope. A short time later, the STS-109 crew captured and latched down the giant telescope in the vehicle's cargo bay for several days of work on the Hubble.

Compartment A1, trim tanks viewed aft to forward from watertight ...

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

Compartment A-1, trim tanks viewed aft to forward from watertight bulkhead no. 6. Using remotely controlled valves, the tanks could be flooded with water or pumped clear to compensate for variations in the ship's displacement and maintain the water line at the desired point. The trim tanks could also be used to counteract the effect of variations in sea water density. (02) - USS Olympia, Penn's Landing, 211 South Columbus Boulevard, Philadelphia, Philadelphia County, PA

General view looking aft along the port side of the ...

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

General view looking aft along the port side of the Orbiter Discovery into its payload bay. Note the Remote Manipulator System, Canadarm, in the foreground mounted on the port side longeron. The Remote Sensor Arm is mounted on the opposite, starboard, longeron. Also note the airlock and the protective covering over the docking mechanism. This image was taken in the Orbiter Processing Facility at Kennedy Space Center. - Space Transportation System, Orbiter Discovery (OV-103), Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

27. VIEW FROM AFT OF MAIN HOISTING ENGINE WITH HOISTING ...

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

27. VIEW FROM AFT OF MAIN HOISTING ENGINE WITH HOISTING DRUM IN FOREGROUND. NOTE MAIN HOISTING DRUM IS A STEP DRUM, WITH TWO DIAMETERS ON DRUM. WHEN BUCKET IS IN WATER THE CABLE IS ON THE SMALLER STEP, AS PICTURED, GIVING MORE POWER TO THE LINE. THE CABLE STEPS TO LARGER DIAMETER WHEN BUCKET IS OUT OF WATER, WHERE SPEED IS MORE IMPORTANT THAN POWER. SMALLER BACKING DRUM IN BACKGROUND. - Dredge CINCINNATI, Docked on Ohio River at foot of Lighthill Street, Pittsburgh, Allegheny County, PA

Closeup view of the aft fuselage of the Orbiter Discovery ...

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

Close-up view of the aft fuselage of the Orbiter Discovery on the starboard side looking forward. This view is of the attach surface for the Orbiter Maneuvering System/Reaction Control System (OMS/RCS) Pod. The OMS/RCS pods are removed for processing and reconditioning at another facility. This view was taken from a service platform in the Orbiter Processing Facility at Kennedy Space Center. - Space Transportation System, Orbiter Discovery (OV-103), Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

STS-103 Wiring inspections in the aft compartment of Discovery

NASA Technical Reports Server (NTRS)

1999-01-01

Chris Kidd, with United Space Alliance (USA) stands by outside the aft compartment of Discovery while Todd Biddle (USA) inspects wiring inside. Electrical wire inspections and repairs in the orbiter's payload bay, external tank umbilical and engine compartment have been ongoing for more than a month and are near completion. Launch of Space Shuttle Discovery on mission STS-103 is scheduled for Dec. 11 at 11:42 p.m. from Launch Pad 39B. STS-103 is the third servicing mission for the Hubble Space Telescope.

Cancer survival analysis using semi-supervised learning method based on Cox and AFT models with L1/2 regularization.

PubMed

Liang, Yong; Chai, Hua; Liu, Xiao-Ying; Xu, Zong-Ben; Zhang, Hai; Leung, Kwong-Sak

2016-03-01

One of the most important objectives of the clinical cancer research is to diagnose cancer more accurately based on the patients' gene expression profiles. Both Cox proportional hazards model (Cox) and accelerated failure time model (AFT) have been widely adopted to the high risk and low risk classification or survival time prediction for the patients' clinical treatment. Nevertheless, two main dilemmas limit the accuracy of these prediction methods. One is that the small sample size and censored data remain a bottleneck for training robust and accurate Cox classification model. In addition to that, similar phenotype tumours and prognoses are actually completely different diseases at the genotype and molecular level. Thus, the utility of the AFT model for the survival time prediction is limited when such biological differences of the diseases have not been previously identified. To try to overcome these two main dilemmas, we proposed a novel semi-supervised learning method based on the Cox and AFT models to accurately predict the treatment risk and the survival time of the patients. Moreover, we adopted the efficient L1/2 regularization approach in the semi-supervised learning method to select the relevant genes, which are significantly associated with the disease. The results of the simulation experiments show that the semi-supervised learning model can significant improve the predictive performance of Cox and AFT models in survival analysis. The proposed procedures have been successfully applied to four real microarray gene expression and artificial evaluation datasets. The advantages of our proposed semi-supervised learning method include: 1) significantly increase the available training samples from censored data; 2) high capability for identifying the survival risk classes of patient in Cox model; 3) high predictive accuracy for patients' survival time in AFT model; 4) strong capability of the relevant biomarker selection. Consequently, our proposed semi

STS-43 MS Adamson checks OCTW experiment on OV-104's aft flight deck

NASA Image and Video Library

1991-08-11

STS043-04-038 (2-11 Aug 1991) --- Astronaut James C. Adamson, STS-43 mission specialist, checks on an experiment on Atlantis? flight deck. Part of the experiment, Optical Communications Through the Shuttle Window (OCTW), can be seen mounted in upper right. The OCTW system consists of two modules, one inside the orbiter crew cabin (as pictured here) and one in the payload bay. The crew compartment version houses an optoelectronic transmitter/receiver pair for video and digital subsystems, test circuitry and interface circuitry. The payload bay module serves as a repeater station. During operation a signal is transmitted through the shuttle window to a bundle of optical fiber cables mounted in the payload bay near an aft window. The cables carry optical signals from the crew compartment equipment to the OCTW payload bay module. The signals are returned via optical fiber cable to the aft flight deck window, retransmitted through the window, and received by the crew compartment equipment.

STS-81 pilot Jett on aft flight deck during approach to Mir

NASA Image and Video Library

1997-02-26

STS081-368-011 (12-22 Jan. 1997) --- Astronaut Brent W. Jett, Jr., STS-81 pilot, appears restful and unfazed as Russia's Mir Space Station appears in the window over his shoulder on the Space Shuttle Atlantis' aft flight deck. Following docking of Mir and Atlantis, Jett and his crew mates went on to spend several days sharing experiments and supply-transfer with the Mir-22 crewmembers.

Ground Test Investigation on a Thermal Protection System Junction

NASA Astrophysics Data System (ADS)

Panerai, F.; Thoemel, J.; Chazot, O.

2009-01-01

During the atmospheric reentry of a spacecraft, the dissociated flow around its Thermal Protection System (TPS) could travel from a low cat- alytic to a high catalytic surface. In this situation a peak of heat flux is experienced at the junction between the two materials. A safe vehicle design cannot preclude investigations on such a phenomenon, since the consequent heating could be harmful for the integrity of TPS. The present work finds its framework on the EXPERT (Eu- ropean eXPErimental Re-entry Testbed) project. The EXPERT vehicle TPS is composed of a C/SiC nose and a PM1000 skirt, so that a catalytic transition occurs in correspondence of their junction. Experiments on wall catalysis phenomena over Thermal Protection Materials (TPM) are performed in this project, using the von Karman Institute (VKI) induction-coupled plasma generator (Plasmatron), under operating conditions representative for real flight situation. In- frared thermography and pyrometry temperature measurements are performed in order to experimentally prove and quantify the transition.

Detail view looking aft along the starboard side of the ...

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

Detail view looking aft along the starboard side of the Orbiter Discovery where the forward section meets the mid-fuselage. Note the head of the jack stand and its mechanism to connect to the one of the forward hoist attach points of the orbiter. Also note the support structure of the service platforms. This view was taken from the service platform in the Orbiter Processing Facility at Kennedy Space Center. - Space Transportation System, Orbiter Discovery (OV-103), Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Detail view of the aft section, port side, of the ...

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

Detail view of the aft section, port side, of the Orbiter Discovery from an elevated platform in the Vehicle Assembly Building at NASA's Kennedy Space Center. Note the removed Orbiter Maneuvering System/Reaction Control System pod from the base of the vertical stabilizer the strongback ground-support equipment attached to the payload bay door. This view is also a good view of the leading edge and top surface of the Orbiter wing. - Space Transportation System, Orbiter Discovery (OV-103), Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Closeup view of the aft fuselage looking forward along the ...

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

Close-up view of the aft fuselage looking forward along the approximate centerline of the Orbiter Discovery looking at the expansion nozzles of the Space Shuttle Main Engines (SSME) and the Orbiter Maneuvering System. Also in the view is the orbiter's body flap with a protective covering over the High-temperature Reusable Surface Insulation tiles on the surface facing the SSMEs. This image was taken inside the Orbiter Processing Facility at Kennedy Space Center. - Space Transportation System, Orbiter Discovery (OV-103), Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Astronaut Carl Walz test portable foot restraint in aft cargo bay

NASA Image and Video Library

1993-09-16

STS051-98-021 (16 Sept. 1993) --- In the Space Shuttle Discovery's aft cargo bay, astronaut Carl E. Walz gets his turn on the Portable Foot Restraint (PFR). Astronauts Walz, waving to his crew mates inside Discovery's cabin, and James H. Newman each put in some time evaluating the PFR, one of the pieces of gear to be used on the Hubble Space Telescope (HST) STS-61 servicing mission (scheduled later this year) and other Shuttle missions.

Astronaut John H. Casper, commander, pauses during a photography session on the aft flight deck of

NASA Technical Reports Server (NTRS)

1996-01-01

STS-77 ESC VIEW --- Astronaut John H. Casper, commander, pauses during a photography session on the aft flight deck of the Space Shuttle Endeavour. The scene was recorded with an Electronic Still Camera (ESC).

MS Currie at RMS controls on aft flight deck

NASA Image and Video Library

2002-03-07

STS109-E-5685 (7 March 2002) --- Astronaut Nancy J. Currie, mission specialist, works the controls for Columbia's Remote Manipulator System (RMS) on the crew cabin's aft flight deck. On a week with one lengthy space walk per day, Currie has had her hands full with RMS duties to support the space walks of four crewmates. Astronauts James H. Newman and Michael J. Massimino had just begin EVA-4, during which the duo required the services of Currie to control the robotic arm to maneuver them around the various workstations on the Hubble Space Telescope (HST). The image was recorded with a digital still camera.

Flight set 360L007 (STS-33R) field joint protection system, thermal protection system, and systems tunnel components, volume 7

NASA Technical Reports Server (NTRS)

1990-01-01

The performance of the thermal protection system, field joint protection system, and systems tunnel components of flight set 360L007 is presented as evaluated by postflight hardware inspection. The condition of both motors was similar to previous flights. Four aft edge strikes were noted on the ground environment instrumentation thermal protection system. The hits all left a clean substrate, indicating that the damage was caused by nozzle severance debris and/or water impact. No National Space Transportation System debris criteria for missing thermal protection system were violated. Two problem reports were written against the field joint protection system. The first concerned two cracks in the K5NA closeout over the trunnion/vent valve location on the left-hand aft field joint. A similar condition was observed on Flight 5 (360H005). The second problem report referred to a number of small surface cracks between two impact marks on the left-hand forward field joint. Neither area exhibited loose material or any abnormal heat effects, and they have no impact on flight safety.

STS-57 Commander Grabe adjusts Thermal Enclosure System (TES) aboard OV-105

NASA Technical Reports Server (NTRS)

1993-01-01

STS-57 Commander Ronald J. Grabe adjusts a bolt on the Thermal Enclosure System (TES) with Crystal Observation System (COS) experiment installation located in an aft locker (MA16J) on the middeck of Endeavour, Orbiter Vehicle (OV) 105. Holding a camcorder in his right hand, Grabe prepares to monitor and record the crystal growth. The open airlock hatch is partially visible in the background.

A study of flight control requirements for advanced, winged, earth-to-orbit vehicles with far-aft center-of-gravity locations

NASA Technical Reports Server (NTRS)

Hepler, A. K.; Zeck, H.; Walker, W. H.; Polack, A.

1982-01-01

Control requirements of Controlled Configured Design Approach vehicles with far-aft center of gravity locations are studied. The baseline system investigated is a fully reusable vertical takeoff/horizontal landing single stage-to-orbit vehicle with mission requirements similar to that of the space shuttle vehicle. Evaluations were made to determine dynamic stability boundaries, time responses, trim control, operational center-of-gravity limits, and flight control subsystem design requirements. Study tasks included a baseline vehicle analysis, an aft center of gravity study, a payload size study, and a technology assessment.

STS-43 crewmembers perform various tasks on OV-104's aft flight deck

NASA Image and Video Library

1991-08-11

STS043-37-012 (2-11 Aug 1991) --- Three STS-43 astronauts are busy at work onboard the earth-orbiting space shuttle Atlantis. Astronaut Shannon W. Lucid is pictured performing one of several tests on Computer hardware with space station applications in mind. Sharing the aft flight deck with Lucid are Michael A. Baker (left), pilot and John E. Blaha, mission commander.

Aerodynamic Impact of an Aft-Facing Slat-Step on High Re Airfoils

NASA Astrophysics Data System (ADS)

Kibble, Geoffrey; Petrin, Chris; Jacob, Jamey; Elbing, Brian; Ireland, Peter; Black, Buddy

2016-11-01

Typically, the initial aerodynamic design and subsequent testing and simulation of an aircraft wing assumes an ideal wing surface without imperfections. In reality, however the surface of an in-service aircraft wing rarely matches the surface characteristics of the test wings used during the conceptual design phase and certification process. This disconnect is usually deemed negligible or overlooked entirely. Specifically, many aircraft incorporate a leading edge slat; however, the mating between the slat and the top surface of the wing is not perfectly flush and creates a small aft-facing step behind the slat. In some cases, the slat can create a step as large as one millimeter tall, which is entirely submerged within the boundary layer. This abrupt change in geometry creates a span-wise vortex behind the step and in transonic flow causes a shock to form near the leading edge. This study investigates both experimentally and computationally the implications of an aft-facing slat-step on an aircraft wing and is compared to the ideal wing surface for subsonic and transonic flow conditions. The results of this study are useful for design of flow control modifications for aircraft currently in service and important for improving the next generation of aircraft wings.

Feasibility of using neutron radiography to inspect the Space Shuttle solid rocket booster aft skirt, forward skirt and frustum. Part 1: Summary report

NASA Technical Reports Server (NTRS)

Barton, J. P.; Bader, J. W.; Brenizer, J. S.; Hosticka, B.

1992-01-01

The space shuttle's solid rocket boosters (SRB) include components made primarily of aluminum that are parachuted back for retrieval from the ocean and refurbished for repeated usage. Nondestructive inspection methods used on these aging parts to reduce the risk of unforeseen problems include x-ray, ultrasonics, and eddy current. Neutron radiography tests on segments of an SRB component show that entrapped moisture and naturally occurring aluminum corrosion can be revealed by neutron radiography even if present in only small amounts. Voids in sealant can also be evaluated. Three alternatives are suggested to follow-up this study: (1) take an SRB component to an existing neutron radiography system; (2) take an existing mobile neutron radiography system to the NASA site; or (3) plan a dedicated system custom designed for NASA applications.

Astronaut Apt takes photos of the Earth from the aft flight deck

NASA Image and Video Library

1996-10-28

STS079-341-036 (16-26 Sept. 1996) --- Following the space shuttle Atlantis' separation from the Russian Mir Space Station, astronaut Jerome (Jay) Apt, mission specialist, eyeballs a photographic target on Earth prior to capturing it on film with a handheld 70mm camera from the aft flight deck. Scientists at the Johnson Space Center (JSC), who helped to plan the various target sites, will later analyze the film in their Houston laboratories.

View of the Columbia's aft section while over Mediterranean Sea

NASA Image and Video Library

1982-03-31

This southerly looking view photographed from the orbiting Space Shuttle Columbia shows a small portion of the vehichle's aft section. The 50-ft Canadian built remote manipulator system (RMS) is in a resting posture (lower right corner) stretched out along the 60-ft. long cargo bay. Many of the components of the OSS-1 payload package are in the bottom center. The Mediterranean Sea is at right foreground. Parts of the Sinai peninsula, Israel, Egypt, Saudi Arabia, Jordan, Palestine, Syria, and Lebanon can be located in the photo. The Red Sea, Gulf of Aqaba, Suez Canal are near the photo's horizon.

13. CLOSEUP OF AFT BULKHEAD IN THE MAIN HOLD. HORIZONTAL ...

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

13. CLOSE-UP OF AFT BULKHEAD IN THE MAIN HOLD. HORIZONTAL ALUMINUM SCALE RESTING ON STEP IS FOUR FEET LONG. THE BOTTOM OF THE HOLD IS MADE OF POURED CONCRETE AND HAS A CENTER DRAIN TO COLLECT WATER FROM MELTING ICE AND OTHER FLUIDS. THE DRAIN LED TO A SUMP CLEARED BY A BILGE PUMP WHICH PUMPED OVERBOARD. THE RECTANGULAR OPENING IN THE BULKHEAD WAS CUT TO ENABLE EASIER REMOVAL OF THE ENGINE AFTER THE EVELINA M. GOULART WAS ABANDONED. - Auxiliary Fishing Schooner "Evelina M. Goulart", Essex Shipbuilding Museum, 66 Main Street, Essex, Essex County, MA

Detail view in engine bay three in the the aft ...

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

Detail view in engine bay three in the the aft fuselage of the Orbiter Discovery. This view shows the engine interface fittings and the hydraulic-actuator support structure. The propellant feed lines are the large plugged and capped orifices. Note the handwritten references on the thrust plate in proximity to the actuators that read E3 Pitch and E3 Yaw. This view was taken from a service platform in the Orbiter Processing Facility at Kennedy Space Center. - Space Transportation System, Orbiter Discovery (OV-103), Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

View of the Columbia's aft section while over Mediterranean Sea

NASA Technical Reports Server (NTRS)

1982-01-01

This southerly looking view photographed from the orbiting Space Shuttle Columbia shows a small portion of the vehichle's aft section. The 50-ft Canadian built remote manipulator system (RMS) is in a resting posture (lower right corner) stretched out along the 60-ft. long cargo bay. Many of the components of the OSS-1 payload package are in the bottom center. The Mediterranean Sea is at right foreground. Parts of the Sinai peninsula, Israel, Egypt, Saudi Arabia, Jordan, Palestine, Syria, and Lebanon can be located in the photo. The Red Sea, Gulf of Aqaba, Suez Canal are near the photo's horizon.

Astronaut Susan Helms on aft flight deck with RMS controls

NASA Image and Video Library

1994-09-12

STS064-05-028 (9-20 Sept. 1994) --- On the space shuttle Discovery's aft flight deck, astronaut Susan J. Helms handles controls for the Remote Manipulator System (RMS). The robot arm operated by Helms, who remained inside the cabin, was used to support several tasks performed by the crew during the almost 11-day mission. Those tasks included the release and retrieval of the free-flying Shuttle Pointed Autonomous Research Tool For Astronomy 201 (SPARTAN 201), a six-hour spacewalk and the Shuttle Plume Impingement Flight Experiment (SPIFEX). Photo credit: NASA or National Aeronautics and Space Administration

Combined Aero and Underhood Thermal Analysis for Heavy Duty Trucks

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

Vegendla, Prasad; Sofu, Tanju; Saha, Rohit

2017-01-31

Aerodynamic analysis of the medium-duty delivery truck was performed to achieve vehicle design optimization. Three dimensional CFD simulations were carried out for several improved designs, with a detailed external component analysis of wheel covers, side skirts, roof fairings, and rounded trailer corners. The overall averaged aerodynamics drag reduction through the design modifications were shown up to 22.3% through aerodynamic considerations alone, which is equivalent to 11.16% fuel savings. The main identified fuel efficiencies were based on second generation devices, including wheel covers, side skirts, roof fairings, and rounded trailer corners. The important findings of this work were; (i) the optimummore » curvature radius of the rounded trailer edges found to be 125 mm, with an arc length of 196.3 mm, (ii) aerodynamic drag reduction increases with dropping clearance of side skirts between wheels and ground, and (iii) aerodynamic drag reduction increases with an extension of front bumper towards the ground.« less

STS-65 Japanese Payload Specialist Mukai on OV-102's aft flight deck

NASA Technical Reports Server (NTRS)

1994-01-01

STS-65 Japanese Payload Specialist Chiaki Mukai freefloats on Columbia's, Orbiter Vehicle (OV) 102's, aft flight deck in front of overhead windows W7 and W8 while holding a cassette case with bean sprouts in her left hand. Mukai, a physician, represented Japan's National Space Development Agency (NASDA) on the two week mission in support of the International Microgravity Laboratory 2 (IML-2).

Spin Forming of an Aluminum 2219-T6 Aft Bulkhead for the Orion Multi-Purpose Crew Vehicle: Phase II Supplemental Report

NASA Technical Reports Server (NTRS)

Piascik, Robert S.; Squire, Michael D.; Domack, Marcia S.; Hoffman, Eric K.

2015-01-01

The principal focus of this project was to assist the Orion Multi-Purpose Crew Vehicle (MPCV) Program in developing a spin forming fabrication process for manufacture of the aft bulkhead of the pressure vessel. The spin forming process will enable a single piece aluminum (Al) 2219 aft bulkhead which will eliminate the current multiple piece welded construction, simplify fabrication, and lead to an enhanced design that will reduce vehicle weight by eliminating welds. Phase I of this assessment explored spin forming the single-piece forward pressure vessel bulkhead from aluminum-lithium 2195.

6 Ma age of carving Westernmost Grand Canyon: Reconciling geologic data with combined AFT, (U-Th)/He, and 4He/3He thermochronologic data

NASA Astrophysics Data System (ADS)

Winn, Carmen; Karlstrom, Karl E.; Shuster, David L.; Kelley, Shari; Fox, Matthew

2017-09-01

/3He analysis of a key sample from Separation Canyon can only be reconciled by a ;young; Canyon. Additional new AFT (5 samples) and AHe data (3 samples) in several locations along the canyon corridor also support a ;young; Canyon. This inconsistency, which mimics the overall controversy of the age of the Grand Canyon, is reconciled here by optimizing cooling paths so they are most consistent with multiple thermochronometers from the same rocks. To do this, we adjusted model parameters and uncertainties to account for uncertainty in the rate of radiation damage annealing in these apatites during sedimentary burial and the resulting variations in He retentivity. In westernmost Grand Canyon, peak burial conditions (temperature and duration) during the Laramide were likely insufficient to fully anneal radiation damage that accumulated during prolonged, near-surface residence since the Proterozoic. We conclude that application of multiple thermochronometers from common rocks reconciles conflicting thermochronologic interpretations and the data presented here are best explained by a ;young; westernmost Grand Canyon. Samples spread along the river corridor also suggest the possibility of variable mid-Tertiary thermal histories beneath north-retreating cliffs.

Low-speed stability and control characteristics of a transport model with aft-fuselage-mounted advanced turboprops

NASA Technical Reports Server (NTRS)

Applin, Z. T.; Coe, P. L., Jr.

1986-01-01

A limited experimental investigation was conducted in the Langley 4- by 7-Meter Tunnel to explore the effects of aft-fuselage-mounted advanced turboprop installations on the low-speed stability and control characteristics of a representative transport aircraft in a landing configuration. In general, the experimental results indicate that the longitudinal and lateral-directional stability characteristics for the aft-fuselage-mounted single-rotation tractor and counter-rotation pusher propeller configurations tested during this investigation are acceptable aerodynamically. For the single-rotation tractor configuration, the propeller-induced aerodynamics are significantly influenced by the interaction of the propeller slipstream with the pylon and nacelle. The stability characteristics for the counter-rotation pusher configuration are strongly influenced by propeller normal forces. The longitudinal and directional control effectiveness, engine-out characteristics, and ground effects are also presented. In addition, a tabulated presentation of all aerodynamic data presented in this report is included as an appendix.

STS-28 Columbia, OV-102, MS Brown uses ARRIFLEX camera on aft flight deck

NASA Image and Video Library

1989-08-13

STS028-17-033 (August 1989) --- Astronaut Mark N. Brown, STS-28 mission specialist, pauses from a session of motion-picture photography conducted through one of the aft windows on the flight deck of the Earth-orbiting Space Shuttle Columbia. He is using an Arriflex camera. The horizon of the blue and white appearing Earth and its airglow are visible in the background.

Propellant grain dynamics in aft attach ring of shuttle solid rocket booster

NASA Technical Reports Server (NTRS)

Verderaime, V.

1979-01-01

An analytical technique for implementing simultaneously the temperature, dynamic strain, real modulus, and frequency properties of solid propellant in an unsymmetrical vibrating ring mode is presented. All dynamic parameters and sources are defined for a free vibrating ring-grain structure with initial displacement and related to a forced vibrating system to determine the change in real modulus. Propellant test data application is discussed. The technique was developed to determine the aft attach ring stiffness of the shuttle booster at lift-off.

STS-109 MS Linnehan with laser range finder on aft flight deck

NASA Image and Video Library

2002-03-02

STS109-E-5003 (3 March 2002) --- Astronaut Richard M. Linnehan, mission specialist, uses a laser ranging device designed to measure the range between two spacecraft. Linnehan positioned himself on the cabin's aft flight deck as the Space Shuttle Columbia approached the Hubble Space Telescope. A short time later, the STS-109 crew captured and latched down the giant telescope in the vehicle's cargo bay for several days of work on the Hubble. The image was recorded with a digital still camera.

STS-109 MS Linnehan with laser range finder on aft flight deck

NASA Image and Video Library

2002-03-02

STS109-E-5002 (3 March 2002) --- Astronaut Richard M. Linnehan, mission specialist, uses a laser ranging device designed to measure the range between two spacecraft. Linnehan positioned himself on the cabin's aft flight deck as the Space Shuttle Columbia approached the Hubble Space Telescope. A short time later, the STS-109 crew captured and latched down the giant telescope in the vehicle's cargo bay for several days of work on the Hubble. The image was recorded with a digital still camera.

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, an orbital maneuvering system (OMS) pod is moved into place on Atlantis. It is one of two OMS pods attached to the upper aft fuselage left and right sides. Fabricated primarily of graphite epoxy composite and aluminum, each pod is 21.8 feet long and 11.37 feet wide at its aft end and 8.41 feet wide at its forward end, with a surface area of approximately 435 square feet. Each pod houses the Reaction Control System propulsion components used for inflight maneuvering and is attached to the aft fuselage with 11 bolts.

NASA Image and Video Library

2003-10-30

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, an orbital maneuvering system (OMS) pod is moved into place on Atlantis. It is one of two OMS pods attached to the upper aft fuselage left and right sides. Fabricated primarily of graphite epoxy composite and aluminum, each pod is 21.8 feet long and 11.37 feet wide at its aft end and 8.41 feet wide at its forward end, with a surface area of approximately 435 square feet. Each pod houses the Reaction Control System propulsion components used for inflight maneuvering and is attached to the aft fuselage with 11 bolts.

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, an orbital maneuvering system (OMS) pod is moved closer to Atlantis for installation. Two OMS pods are attached to the upper aft fuselage left and right sides. Fabricated primarily of graphite epoxy composite and aluminum, each pod is 21.8 feet long and 11.37 feet wide at its aft end and 8.41 feet wide at its forward end, with a surface area of approximately 435 square feet. Each pod houses the Reaction Control System propulsion components used for inflight maneuvering and is attached to the aft fuselage with 11 bolts.

NASA Image and Video Library

2003-10-30

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, an orbital maneuvering system (OMS) pod is moved closer to Atlantis for installation. Two OMS pods are attached to the upper aft fuselage left and right sides. Fabricated primarily of graphite epoxy composite and aluminum, each pod is 21.8 feet long and 11.37 feet wide at its aft end and 8.41 feet wide at its forward end, with a surface area of approximately 435 square feet. Each pod houses the Reaction Control System propulsion components used for inflight maneuvering and is attached to the aft fuselage with 11 bolts.

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, one of two orbital maneuvering system (OMS) pods is being moved for installation on Atlantis. The OMS pods are attached to the upper aft fuselage left and right sides. Fabricated primarily of graphite epoxy composite and aluminum, each pod is 21.8 feet long and 11.37 feet wide at its aft end and 8.41 feet wide at its forward end, with a surface area of approximately 435 square feet. Each pod houses the Reaction Control System propulsion components used for inflight maneuvering and is attached to the aft fuselage with 11 bolts.

NASA Image and Video Library

2003-10-30

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, one of two orbital maneuvering system (OMS) pods is being moved for installation on Atlantis. The OMS pods are attached to the upper aft fuselage left and right sides. Fabricated primarily of graphite epoxy composite and aluminum, each pod is 21.8 feet long and 11.37 feet wide at its aft end and 8.41 feet wide at its forward end, with a surface area of approximately 435 square feet. Each pod houses the Reaction Control System propulsion components used for inflight maneuvering and is attached to the aft fuselage with 11 bolts.

KSC-06pd2232

NASA Image and Video Library

2006-09-27

KENNEDY SPACE CENTER, FLA. - In the Assembly and Refurbishment Facility at NASA's Kennedy Space Center, the solid rocket booster aft skirt designated for use on the first stage of the ARES I-1 launch vehicle is being prepared for its first test flight. Ares I is the vehicle being developed for launch of the crew exploration vehicle (CEV), named Orion. Ares I-1 is currently targeted for launch from Launch Pad 39B in 2009 using the SRB first stage and a simulated second stage and simulated CEV. Ares I ascent tests and Ares I orbital tests will also take place at Kennedy at later dates. Photo credit: NASA/Jack Pfaller

STS-30 aft flight deck onboard view of overhead window, Earth limb, cow photo

NASA Image and Video Library

1989-05-08

STS030-10-008 (4-8 May 1989) --- Since the beginning manned space travel, astronauts have taken with them items of personal sentiment. In case of Mark C. Lee, STS-30 mission specialist, a picture of a cow testifies to his background as one reared on a Wisconsin farm. The scene, through a flight deck aft window, also shows Earth some 160 nautical miles away.

Open cycle ocean thermal energy conversion system structure

DOEpatents

Wittig, J. Michael

1980-01-01

A generally mushroom-shaped, open cycle OTEC system and distilled water producer which has a skirt-conduit structure extending from the enlarged portion of the mushroom to the ocean. The enlarged part of the mushroom houses a toroidal casing flash evaporator which produces steam which expands through a vertical rotor turbine, partially situated in the center of the blossom portion and partially situated in the mushroom's stem portion. Upon expansion through the turbine, the motive steam enters a shell and tube condenser annularly disposed about the rotor axis and axially situated beneath the turbine in the stem portion. Relatively warm ocean water is circulated up through the radially outer skirt-conduit structure entering the evaporator through a radially outer portion thereof, flashing a portion thereof into motive steam, and draining the unflashed portion from the evaporator through a radially inner skirt-conduit structure. Relatively cold cooling water enters the annular condenser through the radially inner edge and travels radially outwardly into a channel situated along the radially outer edge of the condenser. The channel is also included in the radially inner skirt-conduit structure. The cooling water is segregated from the potable, motive steam condensate which can be used for human consumption or other processes requiring high purity water. The expansion energy of the motive steam is partially converted into rotational mechanical energy of the turbine rotor when the steam is expanded through the shaft attached blades. Such mechanical energy drives a generator also included in the enlarged mushroom portion for producing electrical energy. Such power generation equipment arrangement provides a compact power system from which additional benefits may be obtained by fabricating the enclosing equipment, housings and component casings from low density materials, such as prestressed concrete, to permit those casings and housings to also function as a floating

Closeup oblique view of the aft fuselage of the Orbiter ...

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

Close-up oblique view of the aft fuselage of the Orbiter Discovery looking forward and port as the last Space Shuttle Main Engine is being removed, it can be seen on the left side of the image frame. Note that one of the Orbiter Maneuvering System/ Reaction Control System has been removed while one of them remains. Also note that the body flap, below the engine positions has a protective covering to prevent damage to the High-temperature Reusable Surface Insulation tiles. This image was taken inside the Orbiter Processing Facility at Kennedy Space Center. - Space Transportation System, Orbiter Discovery (OV-103), Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Closeup oblique view of the aft fuselage of the Orbiter ...

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

Close-up oblique view of the aft fuselage of the Orbiter Discovery looking forward and starboard as the last Space Shuttle Main Engine is being removed, it can be seen on the right side of the image frame. Note that one of the Orbiter Maneuvering System/ Reaction Control System has been removed while one of them remains. Also note that the body flap, below the engine positions has a protective covering to prevent damage to the High-temperature Reusable Surface Insulation tiles. This image was taken inside the Orbiter Processing Facility at Kennedy Space Center. - Space Transportation System, Orbiter Discovery (OV-103), Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Currie at RMS controls on the aft flight deck

NASA Image and Video Library

1998-12-05

S88-E-5030 (12-05-98) --- Astronaut Nancy J. Currie gently mated the 12.8-ton Unity connecting module to Endeavour's docking system late afternoon of Dec. 5, successfully completing the first task in assembling the new International Space Station. Deftly manipulating the shuttle's 50-foot-long robot arm, Currie placed Unity just inches above the extended outer ring on Endeavour's docking mechanism, enabling astronaut Robert D. Cabana, mission commander, to fire downward maneuvering jets, locking the shuttle's docking system to one of two Pressurized Mating Adapters (PMA) attached to Unity. Turning her head to her right, Currie is using one of the TV monitors on the aft flight deck to assist in the precise maneuver. The photo was taken with an electronic still camera (ESC) at 22:31:08 GMT, Dec. 5.

View of HST as it approaches Endeavour, taken from aft flight deck window

NASA Image and Video Library

1993-12-04

STS061-53-026 (4 Dec 1993) --- One of the Space Shuttle Endeavour's aft flight deck windows frames this view of the Hubble Space Telescope (HST) as it approaches the Endeavour. Backdropped against western Australia, the Remote Manipulator System (RMS) arm awaits the arrival of the telescope. Once berthed in Endeavour's cargo bay, HST underwent five days of servicing provided by four space walking crew members. Shark Bay (upper left) and Perth (lower left) are visible in the frame.

Solid motor aft closure insulation erosion. [heat flux correlation for rate analysis

NASA Technical Reports Server (NTRS)

Stampfl, E.; Landsbaum, E. M.

1973-01-01

The erosion rate of aft closure insulation in a number of large solid propellant motors was empirically analyzed by correlating the average ablation rate with a number of variables that had previously been demonstrated to affect heat flux. The main correlating parameter was a heat flux based on the simplified Bartz heat transfer coefficient corrected for two-dimensional effects. A multiplying group contained terms related to port-to-throat ratio, local wall angle, grain geometry and nozzle cant angle. The resulting equation gave a good correlation and is a useful design tool.

The SRB heat shield: Aeroelastic stability during reentry

NASA Technical Reports Server (NTRS)

Ventres, C. S.; Dowell, E. H.

1977-01-01

Wind tunnel tests of a 3% scale model of the aft portion of the SRB equipped with partially scaled heat shields were conducted for the purpose of measuring fluctuating pressure levels in the aft skirt region. During these tests, the heat shields were observed to oscillate violently, the oscillations in some instances causing the heat shields to fail. High speed films taken during the tests reveal a regular pattern of waves in the fabric starting near the flow stagnation point and progressing around both sides of the annulus. The amplitude of the waves was too great, and their pattern too regular, for them to be attributed to the fluctuating pressure levels measured during the tests. The cause of the oscillations observed in the model heat shields, and whether or not similar oscillations will occur in the full scale SRB heat shield during reentry were investigated. Suggestions for modifying the heat shield so as to avoid the oscillations are provided, and recommendations are made for a program of vibration and wind tunnel tests of reduced-scale aeroelastic models of the heat shield.

STS-39 MS Veach monitors AFP-675 panel on OV-103's aft flight deck

NASA Image and Video Library

1991-05-06

STS039-09-036 (28 April-6 May 1991) --- Astronaut Charles L. (Lacy) Veach monitors experiment data on the aft flight deck of the Earth-orbiting Discovery. The photograph was taken with a 35mm camera. Veach and six other NASA astronauts spent over eight days in space busily collecting data for this mission, dedicated to the Department of Defense.

Clearance Analysis of Node 3 Aft CBM to the Stowed FGB Solar Array

NASA Technical Reports Server (NTRS)

Liddle, Donn

2014-01-01

In early 2011, the ISS Vehicle Configuration Office began considering the relocation of the Permanent Multipurpose Module (PMM) to the aft facing Common Berthing Mechanism (CBM) on Node 3 to open a berthing location for visiting vehicles on the Node 1 nadir CBM. In this position, computer-aided design (CAD) models indicated that the aft end of the PMM would be only a few inches from the stowed Functional Cargo Block (FGB) port solar array. To validate the CAD model clearance analysis, in the late summer of 2011 the Image Science and Analysis Group (ISAG) was asked to determine the true geometric relationship between the on-orbit aft facing Node 3 CBM and the FGB port solar array. The desired measurements could be computed easily by photogrammetric analysis if current imagery of the ISS hardware were obtained. Beginning in the fall of 2011, ISAG used the Dynamic Onboard Ubiquitous Graphics (DOUG) program to design a way to acquire imagery of the aft face of Node 3, the aft end-cone of Node 1, the port side of pressurized mating adapter 1 (PMA1), and the port side of the FGB out to the tip of the port solar array using cameras on the Space Station Remote Manipulator System (SSRMS). This was complicated by the need to thread the SSRMS under the truss, past Node 3 and the Cupola, and into the space between the aft side of Node 3 and the FGB solar array to acquire more than 100 images from multiple positions. To minimize the number of SSRMS movements, the Special Purpose Dexterous Manipulator (SPDM) would be attached to the SSRMS. This would make it possible to park the SPDM in one position and acquire multiple images by changing the viewing orientation of the SPDM body cameras using the pan/tilt units on which the cameras are mounted. Using this implementation concept, ISAG identified four SSRMS/SPDM positions from which all of the needed imagery could be acquired. Based on a photogrammetric simulation, it was estimated that the location of the FGB solar array could be

Agreement between Vermont State Colleges and Vermont State Colleges Faculty Federation, AFT, VFT, Local 3180, AFL-CIO.

ERIC Educational Resources Information Center

Vermont State Commission on Higher Education.

The collective bargaining agreement between Vermont State Colleges (VSC) and Vermont State Colleges Faculty Federation, an affiliate of the American Federation of Teachers (AFT), is presented that covers the period from September 1, 1986 through August 31, 1988. The following 48 articles are included: definitions, recognition, management rights,…

Latch of HST aft shroud photographed by Electronic Still Camera

NASA Image and Video Library

1993-12-04

S61-E-010 (4 Dec 1993) --- This close-up view of a latch on the minus V3 aft shroud door of the Hubble Space Telescope (HST) was photographed with an Electronic Still Camera (ESC), and down linked to ground controllers soon afterward. Endeavour's crew captured the HST on December 4, 1993 in order to service the telescope over a period of five days. Four of the crew members will work in alternating pairs outside Endeavour's shirt sleeve environment to service the giant telescope. Electronic still photography is a relatively new technology which provides the means for a handheld camera to electronically capture and digitize an image with resolution approaching film quality. The electronic still camera has flown as an experiment on several other shuttle missions.

Adsorption effect on the degradation of 4,6-o-dinitrocresol and p-nitrophenol in a montmorillonite clay slurry by AFT.

PubMed

Ye, Peng; Lemley, Ann T

2009-03-01

The adsorption and degradation of 4,6-o-dinitrocresol (DNOC) and p-nitrophenol (PNP) in SWy-2 montmorillonite clay slurry were investigated. The pH and type of cation of the slurry were varied. Results showed that adsorption of DNOC and PNP increased at lower pH values, and when pH < pKa(4.4) of DNOC, DNOC was almost completely adsorbed on the clay under given experimental conditions. The specific cation also had a significant effect on adsorption, which was dramatically enhanced in the presence of K+ and NH4+, compared with the presence of Na+ or Ca2+. Anodic Fenton treatment (AFT) degradation of DNOC and PNP in the clay slurry was studied, and it was found that DNOC degradation rates were greatly affected by the initial pH and the types of electrolytes. Due to the higher adsorption, the degradation rate substantially decreased in the clay slurry system in the presence of K+ and low pH, with a large amount of DNOC residue remaining after 60 min treatment. AFT degradation of PNP was completed within 30 min treatment. Based on LC-MS data, a DNOC degradation pathway was proposed. Overall, the results showed the inhibition effect of adsorption on the degradation of nitroaromatic compounds in montmorillonite clay slurry by AFT, providing important implications for water and soil remediation.

Aft Engine shop worker removes a heat shield on Columbia's main engines

NASA Technical Reports Server (NTRS)

2002-01-01

KENNEDY SPACE CENTER, FLA. - Doug Buford, with the Aft Engine shop, works at removing a heat shield on Columbia, in the Orbiter Processing Facility. After small cracks were discovered on the LH2 Main Propulsion System (MPS) flow liners in two other orbiters, program managers decided to move forward with inspections on Columbia before clearing it for flight on STS-107. After removal of the heat shields, the three main engines will be removed. Inspections of the flow liners will follow. The July 19 launch of Columbia on STS-107 has been delayed a few weeks

Aft Engine shop worker removes a heat shield on Columbia's main engines

NASA Technical Reports Server (NTRS)

2002-01-01

KENNEDY SPACE CENTER, FLA. -- Doug Buford, with the Aft Engine shop, works at removing a heat shield on Columbia, in the Orbiter Processing Facility. After small cracks were discovered on the LH2 Main Propulsion System (MPS) flow liners in two other orbiters, program managers decided to move forward with inspections on Columbia before clearing it for flight on STS-107. After removal of the heat shields, the three main engines will be removed. Inspections of the flow liners will follow. The July 19 launch of Columbia on STS-107 has been delayed a few weeks

Aft Engine shop worker removes a heat shield on Columbia's main engines

NASA Technical Reports Server (NTRS)

2002-01-01

KENNEDY SPACE CENTER, FLA. -- Doug Buford (top), with the Aft Engine shop, along with another worker, removes a heat shield on one of Columbia's engines. After small cracks were discovered on the LH2 Main Propulsion System (MPS) flow liners in two other orbiters, program managers decided to move forward with inspections on Columbia before clearing it for flight on STS-107. After removal of the heat shields, the three main engines will be removed. Inspections of the flow liners will follow. The July 19 launch of Columbia on STS-107 has been delayed a few weeks

The effect of front-to-rear propeller spacing on the interaction noise at cruise conditions of a model counterrotation propeller having a reduced diameter aft propeller

NASA Technical Reports Server (NTRS)

Dittmar, James H.; Gordon, Eliott B.; Jeracki, Robert J.

1988-01-01

The effect of forward-to-aft propeller spacing on the interaction noise of a counterrotation propeller with reduced aft diameter was measured at cruise conditions. In general, the tones at 100 percent speed decreased from close to nominal spacing as expected from a wake decay model. However, when the spacing was further increased to the far position, the noise did not decrease as expected and in some cases increased. The behavior at the far spacing was attributed to changing forward propeller performance, which produced larger wakes. The results of this experiment indicate that simple wake decay model is sufficient to describe the behavior of the interaction noise only if the aerodynamic coupling of the two propellers does not change with spacing. If significant coupling occurs such that the loading of the forward propeller is altered, the interaction noise does not necessarily decrease with larger forward-to-aft propeller spacing.

Thermal history and evolution of the Rio de Janeiro - Barbacena section of the southeastern Brazilian continental margin

NASA Astrophysics Data System (ADS)

Neri Gezatt, Julia; Stephenson, Randell; Macdonald, David

2015-04-01

The transect between the Brazilian cities of Rio de Janeiro and Barbacena (22°54'S, 43°12'W and 21°13'S, 43°46'W, respectively) runs through a segment of a complex range of N-NE/S-SW trending basement units of the Ribeira Belt and southern Sao Francisco Craton, intensely reworked during the Brasiliano-Pan-African orogenic cycle. The ortho- and paragneisses in the area have metamorphic ages between 650 and 540 Ma and are intruded by pre-, syn- and post-tectonic granitic bodies. The transect, perpendicular to the strike direction of the continental margin, crosses the Serra do Mar escarpment, where the sample density is higher in order to better constrain occasional significant age changes. For logistical reasons, the 40 samples collected were processed in two separate batches for apatite fission track (AFT) analysis. The first batch comprised 19 samples, from which 15 produced fission track ages. Analyses were carried out at University College London (UCL), following standard procedures. Preliminary results for the study show AFT ages between 85.9±6.3 and 54.1±4.2 Ma, generally with younger ages close to the coast and progressively older ages towards the continental interior. The highest area sampled, around the city of Teresopolis, ranges from 740 to 1216 m above sea level and shows ages between 85.9±6.3 and 71.3±5.3 Ma. There is no evident lithological or structural distribution control. Medium track length values range from 12.57 to 13.89 µm and distributions are unimodal. Thermal history modelling was done using software QTQt. Individual sample model cooling curves can be divided into two groups: a dominant one, showing a single, slower cooling trend, and a second one with a rapid initial cooling curve, which becomes less steep around 65 Ma. In both groups the maximum paleotemperatures are around 110 Ma. The thermal history model for the first batch of samples is compatible with a single cooling event for the area following continental rifting and

STS-30 aft flight deck onboard view of overhead window, Earth limb, cow photo

NASA Technical Reports Server (NTRS)

1989-01-01

Since the beginning of manned space travel, astronauts have taken onboard with them items of person sentiment. During STS-30 onboard Atlantis, Orbiter Vehicle (OV) 104, Mission Specialist Mark C. Lee brought along a photograph of a cow. The photo testifies to his background as one reared on a Wisconsin farm and is displayed on aft flight deck alongside an overhead window. Outside the window, some 160 nautical miles away, is the cloud-covered Earth surface.

SRB Processing Facilities Media Event

NASA Image and Video Library

2016-03-01

Inside the Booster Fabrication Facility (BFF) at NASA’s Kennedy Space Center in Florida, members of the news media photograph a frustrum that will be stacked atop a forward skirt for one of NASA’s Space Launch System (SLS) solid rocket boosters. Orbital ATK is a contractor for NASA’s Marshall Space Flight Center in Alabama, and operates the BFF to prepare aft booster segments and hardware for the SLS solid rocket boosters. The SLS rocket and Orion spacecraft will launch on Exploration Mission-1 in 2018. The Ground Systems Development and Operations Program is preparing the infrastructure to process and launch spacecraft on deep-space missions and the journey to Mars.

KSC-06pd2233

NASA Image and Video Library

2006-09-27

KENNEDY SPACE CENTER, FLA. - In the Assembly and Refurbishment Facility at NASA's Kennedy Space Center, workers examine some of the hardware inside the solid rocket booster aft skirt designated for use on the first stage of the ARES I-1 launch vehicle in its first test flight. Ares I is the vehicle being developed for launch of the crew exploration vehicle (CEV), named Orion. Ares I-1 is currently targeted for launch from Launch Pad 39B in 2009 using the SRB first stage and a simulated second stage and simulated CEV. Ares I ascent tests and Ares I orbital tests will also take place at Kennedy at later dates. Photo credit: NASA/Jack Pfaller

Currie at RMS controls on the aft flight deck

NASA Image and Video Library

1998-12-05

S88-E-5010 (12-05-98) --- Operating at a control panel on Endeavour's aft flight deck, astronaut Nancy J. Currie works with the robot arm prior to mating the 12.8-ton Unity connecting module to Endeavour's docking system. The mating took place on late afternoon of Dec. 5. A nearby monitor provides a view of the remote manipulator system's (RMS) movements in the cargo bay. The feat marked an important step in assembling the new International Space Station. Manipulating the shuttle's 50-foot-long robot arm, Currie placed Unity just inches above the extended outer ring on Endeavour's docking mechanism, enabling Robert D. Cabana, mission commander to fire downward maneuvering jets, locking the shuttle's docking system to one of two Pressurized Mating Adapters (PMA) attached to Unity. The mating occurred at 5:45 p.m. Central time, as Endeavour sailed over eastern China.

STS-26 MS Nelson operates controls for PVTOS-2 experiment on aft middeck

NASA Technical Reports Server (NTRS)

1988-01-01

STS-26 Mission Specialist (MS) George D. Nelson operates generic electronics module for the Physical Vapor Transport of Organic Solids 2 (PVTOS-2) experiment on Discovery's, Orbiter Vehicle (OV) 103's, aft middeck. PVTOS-2 consists of nine independent experimental cells about 12 inches long and 3 inches in diameter. They are mounted in a circular base plate inside the drum-like experimental apparatus container (EAC). PVTOS-2 is sponsored by NASA's Office of Commercial Programs and is being conducted by 3M's Space Research and Applications Laboratory.

Numerical assessment of fore-and-aft suspension performance to reduce whole-body vibration of wheel loader drivers

NASA Astrophysics Data System (ADS)

Fleury, Gérard; Mistrot, Pierre

2006-12-01

While driving off-road vehicles, operators are exposed to whole-body vibration acting in the fore-and-aft direction. Seat manufacturers supply products equipped with fore-and-aft suspension but only a few studies report on their performance. This work proposes a computational approach to design fore-and-aft suspensions for wheel loader seats. Field tests were conducted in a quarry to analyse the nature of vibration to which the driver was exposed. Typical input signals were recorded to be reproduced in the laboratory. Technical specifications are defined for the suspension. In order to evaluate the suspension vibration attenuation performance, a model of a sitting human body was developed and coupled to a seat model. The seat model combines the models of each suspension component. A linear two-degree-of-freedom model is used to describe the dynamic behaviour of the sitting driver. Model parameters are identified by fitting the computed apparent mass frequency response functions to the measured values. Model extensions are proposed to investigate postural effects involving variations in hands and feet positions and interaction of the driver's back with the backrest. Suspension design parameters are firstly optimized by computing the seat/man model response to sinusoidal acceleration. Four criteria including transmissibility, interaction force between the driver's back and the backrest and relative maximal displacement of the suspension are computed. A new suspension design with optimized features is proposed. Its performance is checked from calculations of the response of the seat/man model subjected to acceleration measured on the wheel loader during real work conditions. On the basis of the computed values of the SEAT factors, it is found possible to design a suspension that would increase the attenuation provided by the seat by a factor of two.

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, an orbital maneuvering system (OMS) pod is suspended in air as it is moved toward Atlantis for installation. Two OMS pods are attached to the upper aft fuselage left and right sides. Fabricated primarily of graphite epoxy composite and aluminum, each pod is 21.8 feet long and 11.37 feet wide at its aft end and 8.41 feet wide at its forward end, with a surface area of approximately 435 square feet. Each pod houses the Reaction Control System propulsion components used for inflight maneuvering and is attached to the aft fuselage with 11 bolts.

NASA Image and Video Library

2003-10-30

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, an orbital maneuvering system (OMS) pod is suspended in air as it is moved toward Atlantis for installation. Two OMS pods are attached to the upper aft fuselage left and right sides. Fabricated primarily of graphite epoxy composite and aluminum, each pod is 21.8 feet long and 11.37 feet wide at its aft end and 8.41 feet wide at its forward end, with a surface area of approximately 435 square feet. Each pod houses the Reaction Control System propulsion components used for inflight maneuvering and is attached to the aft fuselage with 11 bolts.

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, workers discuss the next step in moving the orbital maneuvering system (OMS) pod behind them. The OMS pod will be installed on Atlantis. Two OMS pods are attached to the upper aft fuselage left and right sides. Fabricated primarily of graphite epoxy composite and aluminum, each pod is 21.8 feet long and 11.37 feet wide at its aft end and 8.41 feet wide at its forward end, with a surface area of approximately 435 square feet. Each pod houses the Reaction Control System propulsion components used for inflight maneuvering and is attached to the aft fuselage with 11 bolts.

NASA Image and Video Library

2003-10-30

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, workers discuss the next step in moving the orbital maneuvering system (OMS) pod behind them. The OMS pod will be installed on Atlantis. Two OMS pods are attached to the upper aft fuselage left and right sides. Fabricated primarily of graphite epoxy composite and aluminum, each pod is 21.8 feet long and 11.37 feet wide at its aft end and 8.41 feet wide at its forward end, with a surface area of approximately 435 square feet. Each pod houses the Reaction Control System propulsion components used for inflight maneuvering and is attached to the aft fuselage with 11 bolts.

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, technicians make adjustments to the orbital maneuvering system (OMS) pod being installed on Atlantis. The OMS pod is one of two that are attached to the upper aft fuselage left and right sides. Fabricated primarily of graphite epoxy composite and aluminum, each pod is 21.8 feet long and 11.37 feet wide at its aft end and 8.41 feet wide at its forward end, with a surface area of approximately 435 square feet. Each pod houses the Reaction Control System propulsion components used for inflight maneuvering and is attached to the aft fuselage with 11 bolts.

NASA Image and Video Library

2003-10-30

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, technicians make adjustments to the orbital maneuvering system (OMS) pod being installed on Atlantis. The OMS pod is one of two that are attached to the upper aft fuselage left and right sides. Fabricated primarily of graphite epoxy composite and aluminum, each pod is 21.8 feet long and 11.37 feet wide at its aft end and 8.41 feet wide at its forward end, with a surface area of approximately 435 square feet. Each pod houses the Reaction Control System propulsion components used for inflight maneuvering and is attached to the aft fuselage with 11 bolts.

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, technicians move an orbital maneuvering system (OMS) pod into the correct position on Atlantis. The OMS pod is one of two that are attached to the upper aft fuselage left and right sides. Fabricated primarily of graphite epoxy composite and aluminum, each pod is 21.8 feet long and 11.37 feet wide at its aft end and 8.41 feet wide at its forward end, with a surface area of approximately 435 square feet. Each pod houses the Reaction Control System propulsion components used for inflight maneuvering and is attached to the aft fuselage with 11 bolts.

NASA Image and Video Library

2003-10-30

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, technicians move an orbital maneuvering system (OMS) pod into the correct position on Atlantis. The OMS pod is one of two that are attached to the upper aft fuselage left and right sides. Fabricated primarily of graphite epoxy composite and aluminum, each pod is 21.8 feet long and 11.37 feet wide at its aft end and 8.41 feet wide at its forward end, with a surface area of approximately 435 square feet. Each pod houses the Reaction Control System propulsion components used for inflight maneuvering and is attached to the aft fuselage with 11 bolts.

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, technicians make final adjustments to the orbital maneuvering system (OMS) pod being installed on Atlantis. The OMS pod is one of two that are attached to the upper aft fuselage left and right sides. Fabricated primarily of graphite epoxy composite and aluminum, each pod is 21.8 feet long and 11.37 feet wide at its aft end and 8.41 feet wide at its forward end, with a surface area of approximately 435 square feet. Each pod houses the Reaction Control System propulsion components used for inflight maneuvering and is attached to the aft fuselage with 11 bolts.

NASA Image and Video Library

2003-10-30

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, technicians make final adjustments to the orbital maneuvering system (OMS) pod being installed on Atlantis. The OMS pod is one of two that are attached to the upper aft fuselage left and right sides. Fabricated primarily of graphite epoxy composite and aluminum, each pod is 21.8 feet long and 11.37 feet wide at its aft end and 8.41 feet wide at its forward end, with a surface area of approximately 435 square feet. Each pod houses the Reaction Control System propulsion components used for inflight maneuvering and is attached to the aft fuselage with 11 bolts.

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, one of two orbital maneuvering system (OMS) pods is lifted off its stand to move it toward Atlantis for installation. The OMS pods are attached to the upper aft fuselage left and right sides. Fabricated primarily of graphite epoxy composite and aluminum, each pod is 21.8 feet long and 11.37 feet wide at its aft end and 8.41 feet wide at its forward end, with a surface area of approximately 435 square feet. Each pod houses the Reaction Control System propulsion components used for inflight maneuvering and is attached to the aft fuselage with 11 bolts.

NASA Image and Video Library

2003-10-30

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, one of two orbital maneuvering system (OMS) pods is lifted off its stand to move it toward Atlantis for installation. The OMS pods are attached to the upper aft fuselage left and right sides. Fabricated primarily of graphite epoxy composite and aluminum, each pod is 21.8 feet long and 11.37 feet wide at its aft end and 8.41 feet wide at its forward end, with a surface area of approximately 435 square feet. Each pod houses the Reaction Control System propulsion components used for inflight maneuvering and is attached to the aft fuselage with 11 bolts.

Latch of HST aft shroud photographed by Electronic Still Camera

NASA Image and Video Library

1993-12-04

S61-E-005 (4 Dec 1993) --- This close-up view of a latch on the minus V3 aft shroud door of the Hubble Space Telescope (HST) was photographed with an Electronic Still Camera (ESC), and down linked to ground controllers soon afterward. Endeavour's crew captured the HST on December 4, 1993 in order to service the telescope. Over a period of five days, four of the seven crew members will work in alternating pairs outside Endeavour's shirt sleeve environment to service the giant telescope. Electronic still photography is a relatively new technology which provides the means for a handheld camera to electronically capture and digitize an image with resolution approaching film quality. The electronic still camera has flown as an experiment on several other shuttle missions.

Latch of HST aft shroud photographed by Electronic Still Camera

NASA Image and Video Library

1993-12-04

S61-E-004 (4 Dec 1993) --- This close-up view of a latch on the minus V3 aft shroud door of the Hubble Space Telescope (HST) was photographed with an Electronic Still Camera (ESC), and down linked to ground controllers soon afterward. Endeavour's crew captured the HST on December 4, 1993 in order to service the telescope. Over a period of five days, four of the seven crew members will work in alternating pairs outside Endeavour's shirt sleeve environment to service the giant telescope. Electronic still photography is a relatively new technology which provides the means for a handheld camera to electronically capture and digitize an image with resolution approaching film quality. The electronic still camera has flown as an experiment on several other shuttle missions.

On the possible high +Gz tolerance increase by multimodal brain imaging controlled respiratory AFTE biofeedback training exercise

NASA Astrophysics Data System (ADS)

Smietanowski, Maciej; Achimowicz, Jerzy; Lorenc, Kamil; Nowicki, Grzegorz; Zalewska, Ewa; Truszczynski, Olaf

The experimental data related to Valsalva manouvers and short term voluntary apnea, available in the literature, suggest that the cerebral blood flow increase and reduction of the peripheral one may be expected if the specific AFTE based respiratory training is performed. The authors had verified this hypothesis by studying the relations between EEG measured subject relaxation combined with voluntary apnea by multimodal brain imaging technique (EEG mapping, Neuroscan and fMRI) in a group of healthy volunteers. The SPM analysis of respiratory related changes in cortical and subcortical BOLD signal has partially confirmed the hypothesis. The mechanism of this effect is probably based on the simultaneous blood pressure increase and total peripheral resistance increase. However the question is still open for further experimental verification if AFTE can be treated as the tool which can increase pilot/astronaut situation awareness in the extreme environment typical for aerospace operations where highly variable accelerations due to liftoff, rapid maneuvers, and vibrations can be expected in the critical phases of the mission.

Vertical Stabilizer and OMS pods from the aft FD window during STS-123 mission

NASA Image and Video Library

2008-03-11

S123-E-005073 (11 Mar. 2008) --- This view out the aft windows on Endeavour's flight deck was one of a series of images recorded by the STS-123 crewmembers during their first full day in space. The end of the Canadian-built remote manipulator system's robot arm (right edge) along with the shuttle's vertical stabilizer and its two orbital maneuvering system (OMS) pods are visible. A heavily cloud-covered area of Earth fills the top half of the frame.

MS Hadfield aims a laser range finder through a window on the aft flight deck of Endeavour

NASA Image and Video Library

2001-04-21

S100-E-5141 (21 April 2001) --- Astronaut Chris A. Hadfield of the Canadian Space Agency (CSA) uses a laser ranging device to keep up with the precise location of the International Space Station (ISS) from his post on the aft flight deck of the Space Shuttle Endeavour. The image was recorded with a digital still camera.

STS-46 Commander Shriver eats candy (M and Ms) on OV-104's aft flight deck

NASA Technical Reports Server (NTRS)

1992-01-01

STS-46 Commander Loren J. Shriver, wearing a communications kit assembly headset and with his mouth open, pursues several floating chocolate-covered peanut candies (M and Ms) on the aft flight deck of Atlantis, Orbiter Vehicle (OV) 104. Shriver is positioned in front of overhead window W7. Outside the window the cloud-covered surface of the Earth and the Earth's limb are visible.

General view of the middeck looking aft and port. In ...

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

General view of the mid-deck looking aft and port. In this view you can clearly see the crew access hatch and the airlock hatch. The hose and ladder in the image are pieces of ground support equipment. The hose is part of the climate control apparatus used while orbiters are being processed. The ladder is used to access the inter-deck passage, leading to the flight deck, while the orbiter is in 1g (earth's gravity). A careful observer will notice a void in the wall near the base of the access ladder, this is the Waste Management Compartment with the Waste Management System, i.e. Space Potty, removed. This view was taken in the Orbiter Processing Facility at the Kennedy Space Center. - Space Transportation System, Orbiter Discovery (OV-103), Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Transfer orbit stage mechanisms thermal vacuum test

NASA Technical Reports Server (NTRS)

Oleary, Scott T.

1990-01-01

A systems level mechanisms test was conducted on the Orbital Sciences Corp.'s Transfer Orbit Stage (TOS). The TOS is a unique partially reusable transfer vehicle which will boost a satellite into its operational orbit from the Space Shuttle's cargo bay. The mechanical cradle and tilt assemblies will return to earth with the Space Shuttle while the Solid Rocket Motor (SRM) and avionics package are expended. A mechanisms test was performed on the forward cradle and aft tilting assemblies of the TOS under thermal vacuum conditions. Actuating these assemblies under a 1 g environment and thermal vacuum conditions proved to be a complex task. Pneumatic test fixturing was used to lift the forward cradle, and tilt the SRM, and avionics package. Clinometers, linear voltage displacement transducers, and load cells were used in the thermal vacuum chamber to measure the performance and characteristics of the TOS mechanism assembly. Incorporation of the instrumentation and pneumatic system into the test setup was not routine since pneumatic actuation of flight hardware had not been previously performed in the facility. The methods used are presented along with the problems experienced during the design, setup and test phases.

Developing and utilizing an Euler computational method for predicting the airframe/propulsion effects for an aft-mounted turboprop transport. Volume 2: User guide

NASA Technical Reports Server (NTRS)

Chen, H. C.; Neback, H. E.; Kao, T. J.; Yu, N. Y.; Kusunose, K.

1991-01-01

This manual explains how to use an Euler based computational method for predicting the airframe/propulsion integration effects for an aft-mounted turboprop transport. The propeller power effects are simulated by the actuator disk concept. This method consists of global flow field analysis and the embedded flow solution for predicting the detailed flow characteristics in the local vicinity of an aft-mounted propfan engine. The computational procedure includes the use of several computer programs performing four main functions: grid generation, Euler solution, grid embedding, and streamline tracing. This user's guide provides information for these programs, including input data preparations with sample input decks, output descriptions, and sample Unix scripts for program execution in the UNICOS environment.

Flight motor set 360T004 (STS-30R). Volume 1: System overview

NASA Technical Reports Server (NTRS)

Ricks, Glenn A.

1989-01-01

The fourth NASA space shuttle flight incorporating redesigned solid rocket motors began on 4 May 1989. The flight motors were designated 360Q004A (left-hand) and 360H004B (right-hand); the mission was designated STS-30R. Overall engine performance was excellent. The low sample rate data that was available showed exceptional propulsion performance. All ballistic and mass property parameters closely matched the predicted values and were well within the required contract end item specification levels that could be assessed. No strain, vibration, or aft skirt heating environments could be addressed due to developmental flight instrumentation deletion. Infrared readings from the shuttle thermal imager were considered very good when compared with ground environment instrumentation readings taken during both the aborted and the actual countdowns. However, hand-held infrared gun reading/ground environment instrumentation comparisons were considered poor during both countdowns, with the exception of the T - 3 hour timeframe during the actual launch. Postflight inspection again verified superior performance of the insulation, phenolics, metal parts, and seals. All combustion gas was contained by the insulation in the field and case-to-nozzle joints. Inadequate parachute performance on the left-hand booster caused high splashdown loads, which resulted in a displaced nozzle and factory joint weatherseal unbond anomalies. Recommendations were made concerning improved thermal modeling and instruments. The rationale for these recommendations, the dispositions of all anomalies, and complete result details are given.

Vacuum foil insulation system

DOEpatents

Hanson, John P.; Sabolcik, Rudolph E.; Svedberg, Robert C.

1976-11-16

In a multifoil thermal insulation package having a plurality of concentric cylindrical cups, means are provided for reducing heat loss from the penetration region which extends through the cups. At least one cup includes an integral skirt extending from one end of the cup to intersection with the penetration means. Assembly of the insulation package with the skirted cup is facilitated by splitting the cup to allow it to be opened up and fitted around the other cups during assembly.

The results of studies to determine the impact of far-aft center-of-gravity locations on the design of a single-stage-to-orbit vehicle system

NASA Technical Reports Server (NTRS)

Freeman, D. C., Jr.; Powell, R. W.

1979-01-01

Aft center-of-gravity locations dictated by the large number of rocket engines required has been a continuing problem of single-stage-to-orbit vehicles. Recent work at Langley has demonstrated that these aft center-of-gravity problems become more pronounced for the proposed heavy-lift mission, creating some unique design problems for both the SSTO and staged vehicle systems. During the course of this study, an effort was made to bring together automated vehicle design, wind-tunnel tests, and flight control analyses to assess the impact of longitudinal and lateral-directional instability, and control philosophy on entry vehicle design technology.

Technicians test OV-102's aft fuselage LRU hydrogen recirculation pump

NASA Technical Reports Server (NTRS)

1990-01-01

Donald C. Buckner, a Lockheed mechanical lead technician, installs an aft fuselage line replaceable unit (LRU) liquid hydrogen recirculation pump from Columbia, Orbiter Vehicle (OV) 102 into JSC's Thermochemical Test Area (TTA) Support Laboratory Bldg 350 test stand. Technicians ran the pump package through the battery of leak tests. Preliminary indications showed only minor, acceptable leakage from the package and Kennedy Space Center (KSC) technicians have replaced a crushed seal on the prevalve of the main propulsion system they believe may have caused the STS-35 hydrogen leak. In addition to Buckner, (left to right) Larry Kilbourn, a Rockwell Service Center lead mechanical technician from Cape Canaveral, and John Dickerson, a quality inspector with EBASCO Services, also monitored the test at JSC. Photo taken by JSC photographer Benny Benavides.

SRB Processing Facilities Media Event

NASA Image and Video Library

2016-03-01

Inside the Booster Fabrication Facility (BFF) at NASA’s Kennedy Space Center in Florida, members of the news media view a forward skirt that will be used on a solid rocket booster for NASA’s Space Launch System (SLS) rocket. Orbital ATK is a contractor for NASA’s Marshall Space Flight Center in Alabama, and operates the BFF to prepare aft booster segments and hardware for the SLS solid rocket boosters. Rick Serfozo, Orbital ATK Florida site director, talks to the media. The SLS rocket and Orion spacecraft will launch on Exploration Mission-1 in 2018. The Ground Systems Development and Operations Program is preparing the infrastructure to process and launch spacecraft for deep-space missions and the journey to Mars.

KSC-2014-1936

NASA Image and Video Library

2014-04-02

CAPE CANAVERAL, Fla. – Kennedy Space Center Director Bob Cabana speaks during an Open House event at Hangar N at Cape Canaveral Air Force Station in Florida, to celebrate the one-year anniversary of PaR Systems' partnership with Kennedy. Under a 15-year lease agreement, PaR Systems is utilizing Hangar N and its unique nondestructive testing equipment. Behind Cabana is the robotic inspection cell that contains an automated X-ray system once used to scan the aft skirts of the solid rocket boosters for the space shuttle. The partnership agreement was established by Kennedy's Center Planning and Development Directorate. The agreement is just one example of the types of partnerships that Kennedy is seeking to create a multi-user spaceport. Photo credit: NASA/Cory Huston

STS-3 main parachute failure

NASA Technical Reports Server (NTRS)

Runkle, R.; Henson, K.

1982-01-01

A failure analysis of the parachute on the Space Transportation System 3 flight's solid rocket booster's is presented. During the reentry phase of the two Solid Rocket Boosters (SRBs), one 115 ft diameter main parachute failed on the right hand SRB (A12). This parachute failure caused the SRB to impact the Ocean at 110 ft/sec in lieu of the expected 3 parachute impact velocity of 88 ft/sec. This higher impact velocity relates directly to more SRB aft skirt and more motor case damage. The cause of the parachute failure, the potential risks of losing an SRB as a result of this failure, and recommendations to ensure that the probability of chute failures of this type in the future will be low are discussed.

Inverted Apatite (U-Th)/He and Fission-track Dates from the Rae craton, Baffin Island, Canada and Implications for Apatite Radiation Damage-He Diffusivity Models

NASA Astrophysics Data System (ADS)

Ault, A. K.; Reiners, P. W.; Thomson, S. N.; Miller, G. H.

2015-12-01

Coupled apatite (U-Th)/He and fission-track (AFT) thermochronology data from the same sample can be used to decipher complex low temperature thermal histories and evaluate compatibility between these two methods. Existing apatite He damage-diffusivity models parameterize radiation damage annealing as fission-track annealing and yield inverted apatite He and AFT dates for samples with prolonged residence in the He partial retention zone. Apatite chemistry also impacts radiation damage and fission-track annealing, temperature sensitivity, and dates in both systems. We present inverted apatite He and AFT dates from the Rae craton, Baffin Island, Canada, that cannot be explained by apatite chemistry or existing damage-diffusivity and fission track models. Apatite He dates from 34 individual analyses from 6 samples range from 237 ± 44 Ma to 511 ± 25 Ma and collectively define a positive date-eU relationship. AFT dates from these same samples are 238 ± 15 Ma to 350 ± 20 Ma. These dates and associated track length data are inversely correlated and define the left segment of a boomerang diagram. Three of the six samples with 20-90 ppm eU apatite grains yield apatite He and AFT dates inverted by 300 million years. These samples have average apatite Cl chemistry of ≤0.02 wt.%, with no correlation between Cl content and Dpar. Thermal history simulations using geologic constraints, an apatite He radiation damage accumulation and annealing model, apatite He dates with the range of eU values, and AFT date and track length data, do not yield any viable time-temperature paths. Apatite He and AFT data modeled separately predict thermal histories with Paleozoic-Mesozoic peaks reheating temperatures differing by ≥15 °C. By modifying the parameter controlling damage annealing (Rmr0) from the canonical 0.83 to 0.5-0.6, forward models reproduce the apatite He date-eU correlation and AFT dates with a common thermal history. Results imply apatite radiation damage anneals at

Fore-Aft Ground Force Adaptations to Induced Forelimb Lameness in Walking and Trotting Dogs

PubMed Central

Abdelhadi, Jalal; Wefstaedt, Patrick; Nolte, Ingo; Schilling, Nadja

2012-01-01

Animals alter their locomotor mechanics to adapt to a loss of limb function. To better understand their compensatory mechanisms, this study evaluated the changes in the fore-aft ground forces to forelimb lameness and tested the hypothesis that dogs unload the affected limb by producing a nose-up pitching moment via the exertion of a net-propulsive force when the lame limb is on the ground. Seven healthy Beagles walked and trotted at steady speed on an instrumented treadmill while horizontal force data were collected before and after a moderate lameness was induced. Peak, mean and summed braking and propulsive forces as well as the duration each force was exerted and the time to reach maximum force were evaluated for both the sound and the lame condition. Compared with the sound condition, a net-propulsive force was produced by the lame diagonal limbs due to a reduced braking force in the affected forelimb and an increased propulsive force in the contralateral hindlimb when the dogs walked and trotted. To regain pitch stability and ensure steady speed for a given locomotor cycle, the dogs produced a net-braking force when the sound diagonal limbs were on the ground by exerting greater braking forces in both limbs during walking and additionally reducing the propulsive force in the hindlimb during trotting. Consistent with the proposed mechanism, dogs maximize their double support phases when walking. Likely associated with the fore-aft force adaptations to lameness are changes in muscle recruitment that potentially result in short- and long-term effects on the limb and trunk muscles. PMID:23300614

An experimental study of the effects of aft blowing on a 3.0 caliber tangent ogive body at high angles of attack

NASA Technical Reports Server (NTRS)

Gittner, Nathan M.; Chokani, Ndaona

1991-01-01

An experimental study of the effects of aft blowing on the forebody vortex asymmetry over a 3.0 caliber tangent ogive body at high angles of attack was conducted. The tip of the ogive body was equipped with a single blowing nozzle whose position could be adjusted. The tests were conducted in a subsonic wind tunnel at laminar flow conditions. The effects of model roll, angle of attack, blowing coefficient, and blowing nozzle axial position were independently studied. Surface pressure measurements and flow visualization results were obtained. Aft blowing was observed to alleviate the degree of vortex asymmetry at all angles of attack. The blowing was found to be more effective at the higher angles of attack. However, proportional control of the degree of vortex asymmetry was not observed, because the initial flowfield was highly asymmetric.

30. Engine controls and valve gear, looking aft on main ...

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

30. Engine controls and valve gear, looking aft on main (promenade) deck level. Threaded admission valve lift rods (two at immediate left of chronometer) permit adjustment of valve timing in lower and upper admission valves of cylinder (left rod controls lower valve, right rod upper valve). Valve rods are lifted by jaw-like "wipers" during operation. Exhaust valve lift rods and wipers are located to right of chronometer. Crank at extreme right drives valve wiper shaft when engaged to end of eccentric rod, shown under "Crank Indicator" dial. Pair of handles to immediate left of admission valve rods control condenser water valves; handles to right of exhaust valve rods control feedwater flow to boilers from pumps. Gauges indicate boiler pressure (left) and condenser vacuum (right); "Crank Indicator" on wall aids engineer in keeping engine crank off "dead-center" at stop so that engine may be easily restarted. - Steamboat TICONDEROGA, Shelburne Museum Route 7, Shelburne, Chittenden County, VT

Developing and utilizing an Euler computational method for predicting the airframe/propulsion effects for an aft-mounted turboprop transport. Volume 1: Theory document

NASA Technical Reports Server (NTRS)

Chen, H. C.; Yu, N. Y.

1991-01-01

An Euler flow solver was developed for predicting the airframe/propulsion integration effects for an aft-mounted turboprop transport. This solver employs a highly efficient multigrid scheme, with a successive mesh-refinement procedure to accelerate the convergence of the solution. A new dissipation model was also implemented to render solutions that are grid insensitive. The propeller power effects are simulated by the actuator disk concept. An embedded flow solution method was developed for predicting the detailed flow characteristics in the local vicinity of an aft-mounted propfan engine in the presence of a flow field induced by a complete aircraft. Results from test case analysis are presented. A user's guide for execution of computer programs, including format of various input files, sample job decks, and sample input files, is provided in an accompanying volume.

Demonstration of short haul aircraft aft noise reduction techniques on a twenty inch (50.8 cm) diameter fan, volume 3

NASA Technical Reports Server (NTRS)

Stimpert, D. L.

1975-01-01

Tests of a twenty inch diameter, low tip speed, low pressure ratio fan which investigated aft fan noise reduction techniques are reported. The 1/3 octave band sound data are presented for all the configurations tested. The model data are presented on 17 foot arc and extrapolated to 200 foot sideline.

View of compartment A102 bread room from forward to AFT. ...

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

View of compartment A-102 bread room from forward to AFT. Wood slat decking and ceiling helps to provide adequate air circulation to aid in preservation of flour and baking supplies. Enclosed structure at right of photograph is a portion of the port side coffer dam. The coffer dam ia a partial inner hull to prevent flooding if the outer hull was breached. Originally the coffer dam was filled with water-resistant cellulose mad from corncobs. This material would swell with incoming water if the hull was breached and seal off the hole. Ordinary leakage kept the material wet and created ideal conditions for rot. The material was removed from the coffer dam. Ducts at right provide fresh air to the bread room. (09) - USS Olympia, Penn's Landing, 211 South Columbus Boulevard, Philadelphia, Philadelphia County, PA

STS-48 Pilot Reightler on OV-103's aft flight deck poses for ESC photo

NASA Technical Reports Server (NTRS)

1991-01-01

STS-48 Pilot Kenneth S. Reightler, Jr, positioned under overhead window W8, poses for an electronic still camera (ESC) photo on the aft flight deck of the earth-orbiting Discovery, Orbiter Vehicle (OV) 103. Crewmembers were testing the ESC as part of Development Test Objective (DTO) 648, Electronic Still Photography. The digital image was stored on a removable hard disk or small optical disk, and could be converted to a format suitable for downlink transmission. The ESC is making its initial appearance on this Space Shuttle mission.

STS-35 MS Hoffman operates ASTRO-1 MPC on OV-102's aft flight deck

NASA Image and Video Library

1990-12-10

STS035-12-015 (2-11 Dec 1990) --- Astronaut Jeffrey A. Hoffman, STS 35 mission specialist, uses a manual pointing controller (MPC) for the Astro-1 mission's Instrument Pointing System (IPS). By using the MPC, Hoffman and other crewmembers on Columbia's aft flight deck, were able to command the IPS, located in the cargo bay, to record astronomical data. Hoffman is serving the "Blue" shift which complemented the currently sleeping "Red" shift of crewmembers as the mission collected scientific data on a 24-hour basis. The scene was photographed with a 35mm camera.

Primate translational vestibuloocular reflexes. II. Version and vergence responses to fore-aft motion

NASA Technical Reports Server (NTRS)

McHenry, M. Q.; Angelaki, D. E.

2000-01-01

To maintain binocular fixation on near targets during fore-aft translational disturbances, largely disjunctive eye movements are elicited the amplitude and direction of which should be tuned to the horizontal and vertical eccentricities of the target. The eye movements generated during this task have been investigated here as trained rhesus monkeys fixated isovergence targets at different horizontal and vertical eccentricities during 10 Hz fore-aft oscillations. The elicited eye movements complied with the geometric requirements for binocular fixation, although not ideally. First, the corresponding vergence angle for which the movement of each eye would be compensatory was consistently less than that dictated by the actual fixation parameters. Second, the eye position with zero sensitivity to translation was not straight ahead, as geometrically required, but rather exhibited a systematic dependence on viewing distance and vergence angle. Third, responses were asymmetric, with gains being larger for abducting and downward compared with adducting and upward gaze directions, respectively. As frequency was varied between 4 and 12 Hz, responses exhibited high-pass filter properties with significant differences between abduction and adduction responses. As a result of these differences, vergence sensitivity increased as a function of frequency with a steeper slope than that of version. Despite largely undercompensatory version responses, vergence sensitivity was closer to ideal. Moreover, the observed dependence of vergence sensitivity on vergence angle, which was varied between 2.5 and 10 MA, was largely linear rather than quadratic (as geometrically predicted). We conclude that the spatial tuning of eye velocity sensitivity as a function of gaze and viewing distance follows the general geometric dependencies required for the maintenance of foveal visual acuity. However, systematic deviations from ideal behavior exist that might reflect asymmetric processing of

Thermal history and differential exhumation across the Eastern Musgrave Province, South Australia: Insights from low-temperature thermochronology

NASA Astrophysics Data System (ADS)

Glorie, Stijn; Agostino, Kate; Dutch, Rian; Pawley, Mark; Hall, James; Danišík, Martin; Evans, Noreen J.; Collins, Alan S.

2017-04-01

Multi-method geo- and thermochronological data obtained for Palaeo- and Mesoproterozoic granitoids traversing the main structural architecture of the eastern Musgrave Province within South Australia reveal multiphase cooling histories. Apatite U-Pb dating on six samples yield consistent ages of 1075-1025 Ma, suggesting a thermal reset coinciding with mantle-derived magmatism of the greater Warakurna Large Igneous Province ( 1080-1040 Ma). Apatite fission track (AFT) analysis indicate that four discrete thermal events affected the study area, inducing cooling through the AFT partial annealing zone ( 60-120 °C), supported by apatite and zircon (U-Th-Sm)/He data. Late Neoproterozoic cooling from deep crustal levels to temperatures < 200 °C was discerned, which is thought to be related to exhumation and denudation during the Petermann Orogeny. Subsequent cooling events at 450-400 Ma (Silurian-Devonian) and 310-290 Ma (Late Carboniferous) are interpreted to represent exhumation associated with the Alice Springs Orogeny. The latter event exhumed the sampled plutons to shallow crustal depths. An additional Triassic - early Jurassic thermal event, likely recording elevated geothermal gradients at that time, was observed throughout the study area, however, more data is needed to further support this interpretation. The high sample density across the structural architecture of the study area furthermore reveals patterns of fault reactivation and resulting differential exhumation, indicating shallower exhumation levels in the centre and deeper exhumation towards the margins of the sampled transect. The observed differential exhumation patterns match with existing seismic data and fit a model of an inverted graben system for the Phanerozoic evolution of the eastern Musgraves. The results highlight a complex Phanerozoic thermal history for the eastern Musgraves and help to elucidate the poorly appreciated tectonic evolution of inland Australia. This study further demonstrates

Aft-End Flow of a Large-Scale Lifting Body During Free-Flight Tests

NASA Technical Reports Server (NTRS)

Banks, Daniel W.; Fisher, David F.

2006-01-01

Free-flight tests of a large-scale lifting-body configuration, the X-38 aircraft, were conducted using tufts to characterize the flow on the aft end, specifically in the inboard region of the vertical fins. Pressure data was collected on the fins and base. Flow direction and movement were correlated with surface pressure and flight condition. The X-38 was conceived to be a rescue vehicle for the International Space Station. The vehicle shape was derived from the U.S. Air Force X-24 lifting body. Free-flight tests of the X-38 configuration were conducted at the NASA Dryden Flight Research Center at Edwards Air Force Base, California from 1997 to 2001.

Hydroxyapatite promotes superior keratocyte adhesion and proliferation in comparison with current keratoprosthesis skirt materials.

PubMed

Mehta, J S; Futter, C E; Sandeman, S R; Faragher, R G A F; Hing, K A; Tanner, K E; Allan, B D S

2005-10-01

Published clinical series suggest the osteoodontokeratoprosthesis (OOKP) may have a lower extrusion rate than current synthetic keratoprostheses. The OOKP is anchored in the eye wall by autologous tooth. The authors' aim was to compare adhesion, proliferation, and morphology for telomerase transformed keratocytes seeded on calcium hydroxyapatite (the principal mineral constituent of tooth) and materials used in the anchoring elements of commercially available synthetic keratoprostheses. Test materials were hydroxyapatite, polytetrafluoroethylene (PTFE), polyhydroxyethyl methacrylate (HEMA), and glass (control). Cell adhesion and viability were quantified at 4 hours, 24 hours, and 1 week using a calcein-AM/EthD-1 viability/cytotoxicity assay. Focal contact expression and cytoskeletal organisation were studied at 24 hours by confocal microscopy with immunoflourescent labelling. Further studies of cell morphology were performed using light and scanning electron microscopy. Live cell counts were significantly greater on hydroxyapatite surfaces at each time point (p<0.04). Dead cell counts were significantly higher for PTFE at 7 days (p<0.002). ss(1) integrin expression was highest on hydroxyapatite. Adhesion structures were well expressed in flat, spread out keratocytes on both HA and glass. Keratocytes tended to be thinner and spindle shaped on PTFE. The relatively few keratocytes visible on HEMA test surfaces were rounded and poorly adherent. Keratocyte adhesion, spreading, and viability on hydroxyapatite test surfaces is superior to that seen on PTFE and HEMA. Improving the initial cell adhesion environment in the skirt element of keratoprostheses may enhance tissue integration and reduce device failure rates.

Tectono-thermal evolution of the southwestern Alxa Tectonic Belt, NW China: Constrained by apatite U-Pb and fission track thermochronology

NASA Astrophysics Data System (ADS)

Song, Dongfang; Glorie, Stijn; Xiao, Wenjiao; Collins, Alan S.; Gillespie, Jack; Jepson, Gilby; Li, Yongchen

2018-01-01

The Central Asian Orogenic Belt (CAOB) is regarded to have undergone multiple phases of intracontinental deformation during the Meso-Cenozoic. Located in a key position along the southern CAOB, the Alxa Tectonic Belt (ATB) connects the northernmost Tibetan Plateau with the Mongolian Plateau. In this paper we apply apatite U-Pb and fission track thermochronological studies on varieties of samples from the southwestern ATB, in order to constrain its thermal evolution. Precambrian bedrock samples yield late Ordovician-early Silurian ( 430-450 Ma) and late Permian ( 257 Ma) apatite U-Pb ages; the late Paleozoic magmatic-sedimentary samples yield relatively consistent early Permian ages from 276 to 290 Ma. These data reveal that the ATB experienced multiple Paleozoic tectono-thermal events, as the samples passed through the apatite U-Pb closure temperature ( 350-550 °C). We interpret these tectonic events to record the long-lived subduction-accretion processes of the Paleo-Asian Ocean during the formation of the southern CAOB, with possible thermal influence of the Permian Tarim mantle plume. Apatite fission track (AFT) data and thermal history modelling reveal discrete low-temperature thermal events for the ATB, inducing cooling/reheating through the AFT partial annealing zone ( 120-60 °C). During the Permian, the samples underwent rapid cooling via exhumation or denudation from deep crustal levels to temperatures < 200 °C. Subsequent thermal events in the Triassic were thought to be associated with the final amalgamation of the CAOB or the closure of the Paleotethys. During the Jurassic-Cretaceous the study area experienced heating by burial, followed by renewed cooling, which may be related with the construction and subsequent collapse of the Mongol-Okhotsk Orogeny, or the Lhasa-Eurasia collision and subsequent slab break-off. These results indicate that the ATB may have been stable after late Cretaceous in contrast to the Qilian Shan and Tianshan. Finally, our

Acoustic analysis of aft noise reduction techniques measured on a subsonic tip speed 50.8 cm (twenty inch) diameter fan. [quiet engine program

NASA Technical Reports Server (NTRS)

Stimpert, D. L.; Clemons, A.

1977-01-01

Sound data which were obtained during tests of a 50.8 cm diameter, subsonic tip speed, low pressure ratio fan were analyzed. The test matrix was divided into two major investigations: (1) source noise reduction techniques; and (2) aft duct noise reduction with acoustic treatment. Source noise reduction techniques were investigated which include minimizing second harmonic noise by varying vane/blade ratio, variation in spacing, and lowering the Mach number through the vane row to lower fan broadband noise. Treatment in the aft duct which includes flow noise effects, faceplate porosity, rotor OGV treatment, slant cell treatment, and splitter simulation with variable depth on the outer wall and constant thickness treatment on the inner wall was investigated. Variable boundary conditions such as variation in treatment panel thickness and orientation, and mixed porosity combined with variable thickness were examined. Significant results are reported.

Flight Set 360L006 STS-34 field joint protection system, thermal protection system, and systems tunnel components, volume 4

NASA Technical Reports Server (NTRS)

Wilkinson, J. P.

1990-01-01

The performance of the thermal protection system, field joint protection system, and systems tunnel components of Flight Set 360L006, are documented, as evaluated by postflight hardware inspection. The condition of both motors was similar to previous flights. Sixteen aft edge hits were noted on the ground environment instrumentation thermal protection system. Each hit left a clean substrate, indicating that the damage was caused by nozzle severance debris and/or water impact. No National Space and Transporation System debris criteria for missing thermal protection system were violated. One 5.0 by 1.0 in. unbond was observed on the left hand center field joint K5NA closeout and was elevated to an in-flight anomaly (STS-34-M-4) by the NASA Ice/Debris team. Aft edge damage to the K5NA and an associated black streak indicate that burning debris from the nozzle severance system was the likely cause of the damage. Minor divots caused by debris were seen on previous flights, but this is the first occurrence of a K5NA unbond. Since the unbond occurred after booster separation there is no impact on flight safety and no corrective actions was taken. The right hand center field joint primary heater failed the dielectric withstanding voltage test after joint closeout. The heater was then disabled by opening the circuit breaker, and the redundant heater was used. The redundant heater performed nominally during the launch countdown. A similar condition occurred on Flight 4 when a secondary joint heater failed the dielectric withstanding voltage test.

STS-42 Payload Specialist Merbold with drink on OV-103's aft flight deck

NASA Technical Reports Server (NTRS)

1992-01-01

STS-42 Payload Specialist Ulf D. Merbold, wearing a lightweight headset (HDST), experiments with a grapefruit drink and straw on the aft flight deck of Discovery, Orbiter Vehicle (OV) 103. Merbold watches the liquid ball of grapefruit drink he created float in the weightlessness of space. The Los Angeles Dodger cap Merbold is wearing is part of a tribute to Manley L. (Sonny) Carter, originally assigned as a mission specialist on this flight. During the eight-day flight, the crewmembers each wore the cap on a designated day. Carter, a versatile athlete and avid Dodger fan, died in the crash of a commuter airline in 1991.

Electronic Still Camera view of Aft end of Wide Field/Planetary Camera in HST

NASA Image and Video Library

1993-12-06

S61-E-015 (6 Dec 1993) --- A close-up view of the aft part of the new Wide Field/Planetary Camera (WFPC-II) installed on the Hubble Space Telescope (HST). WFPC-II was photographed with the Electronic Still Camera (ESC) from inside Endeavour's cabin as astronauts F. Story Musgrave and Jeffrey A. Hoffman moved it from its stowage position onto the giant telescope. Electronic still photography is a relatively new technology which provides the means for a handheld camera to electronically capture and digitize an image with resolution approaching film quality. The electronic still camera has flown as an experiment on several other shuttle missions.

Tracking the multi-stage exhumation history of the western Chinese Tianshan by Apatite Fission Track (AFT) dating - Implications for the preservation of epithermal deposits in ancient orogenic belt

NASA Astrophysics Data System (ADS)

Wang, Yannan; Cai, Keda

2017-04-01

The western Chinese Tianshan, located in the southern domain of the Central Asian Orogenic Belt (CAOB), was originally constructed by multiple accretion-collision processes in the Paleozoic, and was superimposed by complex intracontinental tectonic evolution in the Mesozoic-Cenozoic. Understanding the timing and mechanism of the latter geological processes is critical to unravel the preservation conditions of the epithermal deposits in the western Chinese Tianshan. This work presents new apatite fission track (AFT) data for three mountain ranges of the western Chinese Tianshan to track their exhumation history. Our AFT data gave a wide range of ages from 76.8 ± 5.5 Ma to 182.3 ± 9.9 Ma, and the mean confined fission track lengths are between 9.8 ± 0.5 μm and 12.3 ± 0.2 μm. The new data, in combination with the thermal history modeling，enable us to attribute the exhumation history to three primary stages, including Early Permian (300-280 Ma), Late Triassic-Early Cretaceous (230-130 Ma), and Late Oligocene-Early Miocene (30-20 Ma). The first stage may be caused by the terrane accretion-collision in the late Paleozoic. The second stage was likely related to the closure of the Mongol-Okhotsk Ocean during the Mesozoic. The last one is regarded as the result of the collision between the Indian Plate and the Eurasia Plate in the Cenozoic. The extraordinary exhumation processes of these three major mountain ranges might have been responsible for sediment supply to the corresponding intra-mountain basins in the western Chinese Tianshan, and the particularly mountain-basin coupling evolution is ascribed to an essential condition for the preservation of epithermal deposits in ancient orogenic belt.

STS-65 Pilot Halsell cleans window on the aft flight deck of Columbia, OV-102

NASA Technical Reports Server (NTRS)

1994-01-01

On the aft flight deck of Columbia, Orbiter Vehicle (OV) 102, STS-65 Pilot James D. Halsell, Jr cleans off overhead window W8. Mission Specialist (MS) Carl E. Walz looks on (photo's edge). A plastic toy dinosaur, velcroed in front of W9, also appears to be watching the housekeeping activity. A variety of onboard equipment including procedural checklists, a spotmeter, a handheld microphone, and charts are seen in the view. The two shared over fourteen days in Earth orbit with four other NASA astronauts and a Japanese payload specialist in support of the second International Microgravity Laboratory (IML-2) mission.

STS-48 MS Brown on OV-103's aft flight deck poses for ESC photo

NASA Technical Reports Server (NTRS)

1991-01-01

STS-48 Mission Specialist (MS) Mark N. Brown looks away from the portable laptop computer screen to pose for an Electronic Still Camera (ESC) photo on the aft flight deck of the earth-orbiting Discovery, Orbiter Vehicle (OV) 103. Brown was working at the payload station before the interruption. Crewmembers were testing the ESC as part of Development Test Objective (DTO) 648, Electronic Still Photography. The digital image was stored on a removable hard disk or small optical disk, and could be converted to a format suitable for downlink transmission. The ESC is making its initial appearance on this Space Shuttle mission.

STS-48 Commander Creighton on OV-103's aft flight deck poses for ESC photo

NASA Technical Reports Server (NTRS)

1991-01-01

STS-48 Commander John O. Creighton, positioned under overhead window W8, interrupts an out-the-window observation to display a pleasant countenance for an electronic still camera (ESC) photo on the aft flight deck of the earth-orbiting Discovery, Orbiter Vehicle (OV) 103. Crewmembers were testing the ESC as part of Development Test Objective (DTO) 648, Electronic Still Photography. The digital image was stored on a removable hard disk or small optical disk, and could be converted to a format suitable for downlink transmission. The ESC is making its initial appearance on this Space Shuttle mission.

KSC-2014-1935

NASA Image and Video Library

2014-04-02

CAPE CANAVERAL, Fla. – Brian Behm, president, aerospace robotics, PaR Systems Inc., speaks during an Open House event at Hangar N at Cape Canaveral Air Force Station in Florida, to celebrate the one-year anniversary of a partnership with NASA Kennedy Space Center. Under a 15-year lease, PaR Systems is utilizing Hangar N and its unique nondestructive testing equipment. Behind Behm is the robotic inspection cell that contains an automated X-ray system once used to scan the aft skirts of the solid rocket boosters for the space shuttle. The partnership agreement was established by Kennedy's Center Planning and Development Directorate. The agreement is just one example of the types of partnerships that Kennedy is seeking to create a multi-user spaceport. Photo credit: NASA/Cory Huston

KSC-2014-1932

NASA Image and Video Library

2014-04-02

CAPE CANAVERAL, Fla. – Brian Behm partially hidden, president, aerospace robotics, PaR Systems Inc., speaks during an Open House event at Hangar N at Cape Canaveral Air Force Station in Florida, to celebrate the one-year anniversary of a partnership with NASA Kennedy Space Center. Under a 15-year lease agreement, PaR Systems is utilizing Hangar N and its unique nondestructive testing equipment. Behind Behm is the robotic inspection cell that contains an automated X-ray system once used to scan the aft skirts of the solid rocket boosters for the space shuttle. The partnership agreement was established by Kennedy's Center Planning and Development Directorate. The agreement is just one example of the types of partnerships that Kennedy is seeking to create a multi-user spaceport. Photo credit: NASA/Cory Huston

KSC-2014-1931

NASA Image and Video Library

2014-04-02

CAPE CANAVERAL, Fla. – Brian Behm, president, aerospace robotics, PaR Systems Inc., speaks during an Open House event at Hangar N at Cape Canaveral Air Force Station in Florida, to celebrate the one-year anniversary of a partnership with NASA Kennedy Space Center. Under a 15-year lease agreement, PaR Systems is utilizing Hangar N and its unique nondestructive testing equipment. Behind Behm is the robotic inspection cell that contains an automated X-ray system once used to scan the aft skirts of the solid rocket boosters for the space shuttle. The partnership agreement was established by Kennedy's Center Planning and Development Directorate. The agreement is just one example of the types of partnerships that Kennedy is seeking to create a multi-user spaceport. Photo credit: NASA/Cory Huston

Blade-to-Blade Variations in Shocks Upstream of Both a Forward-Swept and an Aft-Swept Fan

NASA Technical Reports Server (NTRS)

Podboy, Gary G.; Krupar, Martin J.

2006-01-01

Detailed laser Doppler velocimeter (LDV) flow field measurements were made upstream of two fans, one forward-swept and one aft-swept, in order to learn more about the shocks which propagate upstream of these rotors when they are operated at supersonic tip speeds. The blade-to-blade variations in the flows associated with these shocks are thought to be responsible for generating Multiple Pure Tone (MPT) noise. The measured blade-to-blade variations are documented in this report through a series of slideshows which show relative Mach number contours computed from the velocity measurements. Data are presented for the forward-swept fan operating at three speeds (corresponding to tip relative Mach numbers of 0.817, 1.074, and 1.189), and for the aft-swept fan operating at two (tip relative Mach numbers of 1.074 and 1.189). These LDV data illustrate how the perturbations in the upstream flow field created by the rotating blades vary with axial position, radial position and rotor speed. As expected, at the highest tested speed the forward-swept fan swallowed the shocks which occur in the tip region, whereas the aftswept fan did not. This resulted in a much smaller flow disturbance just upstream of the tip of the forward-swept fan. Nevertheless, further upstream the two fan flows were much more similar.

STS-56 crewmembers on aft flight deck of Discovery, Orbiter Vehicle (OV) 103

NASA Technical Reports Server (NTRS)

1993-01-01

STS-56 crewmembers pose on aft flight deck of Discovery, Orbiter Vehicle (OV) 103, for this in-cabin electronic still camera (ESC) photograph. Clockwise from the bottom right corner are Commander Kenneth Cameron, Mission Specialist 3 (MS3) Ellen Ochoa, MS2 Kenneth D. Cockrell, and Pilot Stephen S. Oswald. The crewmembers are positioned in front of the onorbit station. The image was recorder with the Hand-held, Earth-oriented, Real-time, Cooperative, User-friendly, Location-targeting and Environmental System (HERCULES). HERCULES is a device that makes it simple for Shuttle crewmembers to take pictures of Earth as they merely point and shoot any interesting feature, whose latitude and longitude are automatically determined in real time. In-cabin shots are for test purposes only.

500 Myr of thermal history elucidated by multi-method detrital thermochronology of North Gondwana Cambrian sandstone (Eilat area, Israel)

NASA Astrophysics Data System (ADS)

Vermeesch, P.; Avigad, D.

2009-04-01

Eilat. The detrital apatites we studied all have extremely rounded cores suggestive of a distant provenance, but some grains also feature distinct euhedral U-rich apatite overgrowth rims. Authigenic apatite may have grown during the late Devonian thermal event we dated by ZFT, coinciding with existing Rb-Sr ages from authigenic clays in the same deposits and leading to the conclusion that the Devonian event was probably hydrothermal. Like the ZFT ages, the detrital apatite fission track (AFT) ages were also completely reset after deposition. Sixty single grain detrital apatite fission track (AFT) ages group at ~270 Ma with significant dispersion. Inverse modeling of the AFT data indicate extended and/or repeated residence in the AFT partial annealing zone, in turn suggesting an episodic burial-erosion history during the Mesozoic caused by low-amplitude vertical motions. Seven detrital apatite (U-Th)/He ages scatter between 33 and 77 Ma, possibly resulting from extreme compositional zonation associated with the authigenic U-rich overgrowths. The ~70 Ma (U-Th)/He ages are more likely to be accurate, setting 1-2 km as an upper limit (depending on the geothermal gradient) on the post-Cretaceous exhumation of the Cambrian sandstone and showing no evidence for substantial denudation related to Tertiary rifting of the Red Sea.

Closeup view of the aft fuselage of the Orbiter Discovery ...

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

Close-up view of the aft fuselage of the Orbiter Discovery looking at the thrust structure that supports the Space Shuttle Main Engines (SSMEs). In this view, SSME number two position is on the left and SSME number three position is on the right. The thrust structure transfers the forces produce by the engines into and through the airframe of the orbiter. The thrust structure includes the SSMEs load reaction truss structure, engine interface fittings and the hydraulic-actuator support structure. The propellant feed lines are the plugged and capped orifices within the engine bays. Note that SSME position two is rotated ninety degrees from position three and one. This was needed to enable enough clearance for the engines to fit and gimbal. Note in engine bay three is a clear view of the actuators that control the gambling of that engine. This view was taken from a service platform in the Orbiter Processing Facility at Kennedy Space Center. - Space Transportation System, Orbiter Discovery (OV-103), Lyndon B. Johnson Space Center, 2101 NASA Parkway, Houston, Harris County, TX

Numerical Modelling of Staged Combustion Aft-Injected Hybrid Rocket Motors

NASA Astrophysics Data System (ADS)

Nijsse, Jeff

The staged combustion aft-injected hybrid (SCAIH) rocket motor is a promising design for the future of hybrid rocket propulsion. Advances in computational fluid dynamics and scientific computing have made computational modelling an effective tool in hybrid rocket motor design and development. The focus of this thesis is the numerical modelling of the SCAIH rocket motor in a turbulent combustion, high-speed, reactive flow framework accounting for solid soot transport and radiative heat transfer. The SCAIH motor is modelled with a shear coaxial injector with liquid oxygen injected in the center at sub-critical conditions: 150 K and 150 m/s (Mach ≈ 0.9), and a gas-generator gas-solid mixture of one-third carbon soot by mass injected in the annual opening at 1175 K and 460 m/s (Mach ≈ 0.6). Flow conditions in the near injector region and the flame anchoring mechanism are of particular interest. Overall, the flow is shown to exhibit instabilities and the flame is shown to anchor directly on the injector faceplate with temperatures in excess of 2700 K.

Integrated Thermal Protection Systems and Heat Resistant Structures

NASA Technical Reports Server (NTRS)

Pichon, Thierry; Lacoste, Marc; Glass, David E.

2006-01-01

In the early stages of NASA's Exploration Initiative, Snecma Propulsion Solide was funded under the Exploration Systems Research & Technology program to develop integrated thermal protection systems and heat resistant structures for reentry vehicles. Due to changes within NASA's Exploration Initiative, this task was cancelled early. This presentation provides an overview of the work that was accomplished prior to cancellation. The Snecma team chose an Apollo-type capsule as the reference vehicle for the work. They began with the design of a ceramic aft heatshield (CAS) utilizing C/SiC panels as the capsule heatshield, a C/SiC deployable decelerator and several ablators. They additionally developed a health monitoring system, high temperature structures testing, and the insulation characterization. Though the task was pre-maturely cancelled, a significant quantity of work was accomplished.

Aerodynamic flight evaluation analysis and data base update

NASA Technical Reports Server (NTRS)

Boyle, W. W.; Miller, M. S.; Wilder, G. O.; Reheuser, R. D.; Sharp, R. S.; Bridges, G. I.

1989-01-01

Research was conducted to determine the feasibility of replacing the Solid Rocket Boosters on the existing Space Shuttle Launch Vehicle (SSLV) with Liquid Rocket Boosters (LRB). As a part of the LRB selection process, a series of wind tunnel tests were conducted along with aero studies to determine the effects of different LRB configurations on the SSLV. Final results were tabulated into increments and added to the existing SSLV data base. The research conducted in this study was taken from a series of wind tunnel tests conducted at Marshall's 14-inch Trisonic Wind Tunnel. The effects on the axial force (CAF), normal force (CNF), pitching moment (CMF), side force (CY), wing shear force (CSR), wing torque moment (CTR), and wing bending moment (CBR) coefficients were investigated for a number of candidate LRB configurations. The aero effects due to LRB protuberances, ET/LRB separation distance, and aft skirts were also gathered from the tests. Analysis was also conducted to investigate the base pressure and plume effects due to the new booster geometries. The test results found in Phases 1 and 2 of wind tunnel testing are discussed and compared. Preliminary LRB lateral/directional data results and trends are given. The protuberance and gap/skirt effects are discussed. The base pressure/plume effects study is discussed and results are given.

Nuclear reactor with low-level core coolant intake

DOEpatents

Challberg, Roy C.; Townsend, Harold E.

1993-01-01

A natural-circulation boiling-water reactor has skirts extending downward from control rod guide tubes to about 10 centimeters from the reactor vessel bottom. The skirts define annular channels about control rod drive housings that extend through the reactor vessel bottom. Recirculating water is forced in through the low-level entrances to these channels, sweeping bottom water into the channels in the process. The sweeping action prevents cooler water from accumulating at the bottom. This in turn minimizes thermal shock to bottom-dwelling components as would occur when accumulated cool water is swept away and suddenly replaced by warmer water.

Augmented Method to Improve Thermal Data for the Figure Drift Thermal Distortion Predictions of the JWST OTIS Cryogenic Vacuum Test

NASA Technical Reports Server (NTRS)

Park, Sang C.; Carnahan, Timothy M.; Cohen, Lester M.; Congedo, Cherie B.; Eisenhower, Michael J.; Ousley, Wes; Weaver, Andrew; Yang, Kan

2017-01-01

The JWST Optical Telescope Element (OTE) assembly is the largest optically stable infrared-optimized telescope currently being manufactured and assembled, and is scheduled for launch in 2018. The JWST OTE, including the 18 segment primary mirror, secondary mirror, and the Aft Optics Subsystem (AOS) are designed to be passively cooled and operate near 45K. These optical elements are supported by a complex composite backplane structure. As a part of the structural distortion model validation efforts, a series of tests are planned during the cryogenic vacuum test of the fully integrated flight hardware at NASA JSC Chamber A. The successful ends to the thermal-distortion phases are heavily dependent on the accurate temperature knowledge of the OTE structural members. However, the current temperature sensor allocations during the cryo-vac test may not have sufficient fidelity to provide accurate knowledge of the temperature distributions within the composite structure. A method based on an inverse distance relationship among the sensors and thermal model nodes was developed to improve the thermal data provided for the nanometer scale WaveFront Error (WFE) predictions. The Linear Distance Weighted Interpolation (LDWI) method was developed to augment the thermal model predictions based on the sparse sensor information. This paper will encompass the development of the LDWI method using the test data from the earlier pathfinder cryo-vac tests, and the results of the notional and as tested WFE predictions from the structural finite element model cases to characterize the accuracies of this LDWI method.

Thermal balance testing of MSAT 2 spacecraft

NASA Technical Reports Server (NTRS)

Samson, Serge; Choueiry, Elie

1994-01-01

The present work reports on the recently completed infrared thermal balance/thermal vacuum testing of a MSAT satellite, the first satellite to provide mobile communications service for all of continental North America. MSAT is a two spacecraft program, using a three-axis stabilized Hughes HS-601 series Bus as the vehicle for the Canadian designed Payload. The thermal tests which were performed at the Canadian Space Agency's David Florida Laboratory in Ottawa, Canada, lasted approximately 35 days. The infrared (IR) heating rig was designed to provide radiant heat inputs into seven spacecraft zones during Thermal Vacuum (TV) testing. The TV test was divided into multiple phases. It began with a thermal balance cold phase, followed by a thermal cold cycle and a hot balance phase, complemented by a thermal hot cycle to finish with a thermal cycle with continuous monitoring of the Bus and Payload. The spacecraft's external heat fluxes were provided by IR lamp sources. To ensure flux uniformity, highly reflective baffles and IR East and West faces; the Earth facing (Nadir); and the inside of the thrust cylinder. The aft-end panel heat fluxes were provided by a heated LN2 shroud. The radiation flux intensity on the spacecraft zones from the various rig elements was measured using Monitored Background Radiometers (MBR's) and compared with direct calculations and with pretest predictions. The temperature measurement system was based on Uniform Temperature References (UTR's) located inside the chamber such that all feedthroughs were copper-copper. This system was devised to achieve a temperature measurement accuracy of plus/minus 0.5 C for over 850 thermocouples used in the test. A PC-(QNX-based) based real-time data acquisition system was utilized to provide continuous monitoring of all channels based on a 30-second time scan. In addition, the data acquisition system was able to retrieve telemetry stream from the Satellite Test Equipments (STE) station for real-time data

Spacelab 3 flight experiment No. 3AFT23: Autogenic-feedback training as a preventive method for space adaptation syndrome

NASA Technical Reports Server (NTRS)

Cowings, Patricia S.; Toscano, William B.; Kamiya, Joe; Miller, Neal E.; Sharp, Joseph C.

1988-01-01

Space adaptation syndrome is a motion sickness-like disorder which affects up to 50 percent of all people exposed to microgravity in space. This experiment tested a physiological conditioning procedure (Autogenic-Feedback Training, AFT) as an alternative to pharmacological management. Four astronauts participated as subjects in this experiment. Crewmembers A and B served as treatment subjects. Both received preflight training for control of heart rate, respiration rate, peripheral blood volume, and skin conductance. Crewmembers C and D served as controls (i.e., did not receive training). Crewmember A showed reliable control of his own physiological responses, and a significant increase in motion sickness tolerance after training. Crewmember B, however, demonstrated much less control and only a moderate increase in motion sickness tolerance was observed after training. The inflight symptom reports and physiological data recordings revealed that Crewmember A did not experience any severe symptom episodes during the mission, while Crewmember B reported one severe symptom episode. Both control group subjects, C and D (who took antimotion sickness medication), reported multiple symptom episodes on mission day 0. Both inflight data and crew reports indicate that AFT may be an effective countermeasure. Additional data must be obtained inflight (a total of eight treatment and eight control subjects) before final evaluation of this treatment can be made.

Surrounded by work platforms, the full-scale Orion AFT crew module (center) is undergoing preparations for the first flight test of Orion's launch abort system.

NASA Image and Video Library

2008-05-20

Surrounded by work platforms, NASA's first full-scale Orion abort flight test (AFT) crew module (center) is undergoing preparations at the NASA Dryden Flight Research Center in California for the first flight test of Orion's launch abort system.

Analysis of pressure blips in aft-finocyl solid rocket motor

NASA Astrophysics Data System (ADS)

Di Giacinto, M.; Favini, B.; Cavallini, E.

2016-07-01

Ballistic anomalies have frequently occurred during the firing of several solid rocket motors (SRMs) (Inertial Upper Stage, Space Shuttle Redesigned SRM (RSRM) and Titan IV SRM Upgrade (SRMU)), producing even relevant and unexpected variations of the SRM pressure trace from its nominal profile. This paper has the purpose to provide a numerical analysis of the following possible causes of ballistic anomalies in SRMs: an inert object discharge, a slag ejection, and an unexpected increase in the propellant burning rate or in the combustion surface. The SRM configuration under investigation is an aft-finocyl SRM with a first-stage/small booster design. The numerical simulations are performed with a quasi-one-dimensional (Q1D) unsteady model of the SRM internal ballistics, properly tailored to model each possible cause of the ballistic anomalies. The results have shown that a classification based on the head-end pressure (HEP) signature, relating each other the HEP shape and the ballistic anomaly cause, can be made. For each cause of ballistic anomalies, a deepened discussion of the parameters driving the HEP signatures is provided, as well as qualitative and quantitative assessments of the resultant pressure signals.

KSC-2011-7767

NASA Image and Video Library

2011-11-10

VANDENBERG AIR FORCE BASE, Calif. -- At a Pegasus booster processing facility at Vandenberg Air Force Base in California, using a crane, technicians install a section of the aft skirt on the Pegasus XL rocket’s first stage. The Orbital Sciences Corp. Pegasus rocket will launch the Nuclear Spectroscopic Telescope Array (NuSTAR) into space. After the rocket and spacecraft are processed at Vandenberg, they will be flown on the Orbital Sciences’ L-1011 carrier aircraft to the Ronald Reagan Ballistic Missile Defense Test Site at the Pacific Ocean’s Kwajalein Atoll for launch. The high-energy x-ray telescope will conduct a census for black holes, map radioactive material in young supernovae remnants, and study the origins of cosmic rays and the extreme physics around collapsed stars. For more information, visit science.nasa.gov/missions/nustar/. Photo credit: NASA/Randy Beaudoin, VAFB

KSC-2012-5887

NASA Image and Video Library

2012-10-09

VANDENBERG AIR FORCE BASE, Calif. – At Vandenberg Air Force Base in California, technicians install the aft skirt on the Orbital Sciences Corp. Pegasus XL rocket which will launch the Interface Region Imaging Spectrograph, or IRIS, spacecraft. Scheduled for launch from Vandenberg Air Force Base no earlier than Feb. 27, 2013, IRIS will open a new window of discovery by tracing the flow of energy and plasma through the chromospheres and transition region into the sun’s corona using spectrometry and imaging. IRIS fills a crucial gap in our ability to advance studies of the sun-to-Earth connection by tracing the flow of energy and plasma through the foundation of the corona and the region around the sun known as the heliosphere. For more information, visit http://iris.gsfc.nasa.gov Photo credit: NASA/Randy Beaudoin

KSC-2012-5889

NASA Image and Video Library

2012-10-09

VANDENBERG AIR FORCE BASE, Calif. – At Vandenberg Air Force Base in California, technicians install the aft skirt on the Orbital Sciences Corp. Pegasus XL rocket which will launch the Interface Region Imaging Spectrograph, or IRIS, spacecraft. Scheduled for launch from Vandenberg Air Force Base no earlier than Feb. 27, 2013, IRIS will open a new window of discovery by tracing the flow of energy and plasma through the chromospheres and transition region into the sun’s corona using spectrometry and imaging. IRIS fills a crucial gap in our ability to advance studies of the sun-to-Earth connection by tracing the flow of energy and plasma through the foundation of the corona and the region around the sun known as the heliosphere. For more information, visit http://iris.gsfc.nasa.gov Photo credit: NASA/Randy Beaudoin

KSC-2012-5890

NASA Image and Video Library

2012-10-09

VANDENBERG AIR FORCE BASE, Calif. – At Vandenberg Air Force Base in California, technicians install the aft skirt on the Orbital Sciences Corp. Pegasus XL rocket which will launch the Interface Region Imaging Spectrograph, or IRIS, spacecraft. Scheduled for launch from Vandenberg Air Force Base no earlier than Feb. 27, 2013, IRIS will open a new window of discovery by tracing the flow of energy and plasma through the chromospheres and transition region into the sun’s corona using spectrometry and imaging. IRIS fills a crucial gap in our ability to advance studies of the sun-to-Earth connection by tracing the flow of energy and plasma through the foundation of the corona and the region around the sun known as the heliosphere. For more information, visit http://iris.gsfc.nasa.gov Photo credit: NASA/Randy Beaudoin

KSC-2014-1939

NASA Image and Video Library

2014-04-02

CAPE CANAVERAL, Fla. – Tom Engler, deputy director of the Center Planning and Development Directorate at Kennedy Space Center, speaks to members of the media during an Open House event at Hangar N at Cape Canaveral Air Force Station in Florida, to celebrate the one-year anniversary of PaR Systems' partnership with Kennedy. Under a 15-year lease agreement, PaR Systems is utilizing Hangar N and its unique nondestructive testing equipment. Behind Engler is the robotic inspection cell that contains an automated X-ray system once used to scan the aft skirts of the solid rocket boosters for the space shuttle. The partnership agreement was established by Kennedy's Center Planning and Development Directorate. The agreement is just one example of the types of partnerships that Kennedy is seeking to create a multi-user spaceport. Photo credit: NASA/Cory Huston

KSC-2011-7769

NASA Image and Video Library

2011-11-10

VANDENBERG AIR FORCE BASE, Calif. -- At a Pegasus booster processing facility at Vandenberg Air Force Base in California, using a crane, technicians install the second section of the aft skirt on the Pegasus XL rocket’s first stage. The Orbital Sciences Corp. Pegasus rocket will launch the Nuclear Spectroscopic Telescope Array (NuSTAR) into space. After the rocket and spacecraft are processed at Vandenberg, they will be flown on the Orbital Sciences’ L-1011 carrier aircraft to the Ronald Reagan Ballistic Missile Defense Test Site at the Pacific Ocean’s Kwajalein Atoll for launch. The high-energy x-ray telescope will conduct a census for black holes, map radioactive material in young supernovae remnants, and study the origins of cosmic rays and the extreme physics around collapsed stars. For more information, visit science.nasa.gov/missions/nustar/. Photo credit: NASA/Randy Beaudoin, VAFB

STS-99 workers move new Master Events Controller into aft compartment

NASA Technical Reports Server (NTRS)

2000-01-01

At Launch Pad 39A, workers move the replacement Enhanced Main Events Controller (E-MEC) into Shuttle Endeavour's aft compartment in the payload bay. The original E-MEC became suspect during the Jan. 31 launch countdown and mission STS-99 was delayed when NASA managers decided to replace it. Each Shuttle carries two enhanced master events controllers (E-MECs), which provide relays for onboard flight computers to send signals to arm and fire pyrotechnics that separate the solid rockets and external tank during assent. Both E-MECs are needed for the Shuttle to be cleared for flight. Currently Endeavour and Columbia are the only two orbiters with the E-MECs. Built by Rockwell's Satellite Space Electronics Division, Anaheim, Calif., each unit weighs 65 pounds and is approximately 20 inches long, 13 inches wide and 8 inches tall. Previously, three Shuttle flights have been scrubbed or delayed due to faulty MECs: STS-73, STS-49 and STS-41-D. The next scheduled date for launch of STS-99 is Feb. 11 at 12:30 p.m. EST.

The dominant allele Aft induces a shift from flavonol to anthocyanin production in response to UV-B radiation in tomato fruit.

PubMed

Catola, Stefano; Castagna, Antonella; Santin, Marco; Calvenzani, Valentina; Petroni, Katia; Mazzucato, Andrea; Ranieri, Annamaria

2017-08-01

The introgression of the A ft allele into domesticated tomato induced a shift from flavonol to anthocyanin production in response to UV-B radiation, while the hp - 1 allele negatively influenced the response of flavonoid biosynthesis to UV-B. Introgression of the dominant allele Anthocyanin fruit (Aft) from Solanum chilense induces anthocyanin accumulation in the peel of tomato (Solanum lycopersicum L.) fruit. UV-B radiation can influence plant secondary metabolism regulating the expression of several genes, among which those involved in flavonoid biosynthesis. Here, we investigated whether post-harvest UV-B treatment could up-regulate flavonoid production in tomato fruits and whether the Aft allele could affect flavonoid biosynthesis under UV-B radiation. Mature green fruits of an anthocyanin-rich tomato mutant line (SA206) and of its wild-type reference, cv. Roma, were daily subjected to post-harvest UV-B treatment until full ripening. Up-regulation of CHS and CHI transcription by UV-B treatment induced flavonoid accumulation in the peel of cv. Roma. Conversely, UV-B decreased the total flavonoid content and CHS transcript levels in the SA206 peel. SA206 being a double mutant containing also hp-1 allele, we investigated also the behavior of hp-1 fruit. The decreased peel flavonoid accumulation and gene transcription in response to UV-B suggest that hp-1 allele is involved in the marked down-regulation of the flavonoid biosynthesis observed in SA206 fruit. Interestingly, in SA206, UV-B radiation promoted the synthesis of delphinidin, petunidin, and malvidin by increasing F3'5'H and DFR transcription, but it decreased rutin production, suggesting a switch from flavonols to anthocyanins. Finally, although UV-B radiation does not reach the inner fruit tissues, it down-regulated flavonoid biosynthesis in the flesh of both genotypes. This study provides, for the first time, evidence that the presence of the functional Aft allele, under UV-B radiation, redirects

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, one of two orbital maneuvering system (OMS) pods removed from Endeavour is lowered toward a transporter. The OMS pods are attached to the upper aft fuselage left and right sides. Fabricated primarily of graphite epoxy composite and aluminum, each pod is 21.8 feet long and 11.37 feet wide at its aft end and 8.41 feet wide at its forward end, with a surface area of approximately 435 square feet. Each pod houses the Reaction Control System propulsion components used for inflight maneuvering and is attached to the aft fuselage with 11 bolts. OMS pods are removed during Orbiter Major Modifications. Once removed, the OMS pods undergo in-depth structural inspections, system checks and the thrusters are changed out.

NASA Image and Video Library

2003-09-05

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, one of two orbital maneuvering system (OMS) pods removed from Endeavour is lowered toward a transporter. The OMS pods are attached to the upper aft fuselage left and right sides. Fabricated primarily of graphite epoxy composite and aluminum, each pod is 21.8 feet long and 11.37 feet wide at its aft end and 8.41 feet wide at its forward end, with a surface area of approximately 435 square feet. Each pod houses the Reaction Control System propulsion components used for inflight maneuvering and is attached to the aft fuselage with 11 bolts. OMS pods are removed during Orbiter Major Modifications. Once removed, the OMS pods undergo in-depth structural inspections, system checks and the thrusters are changed out.

KENNEDY SPACE CENTER, FLA. - Technicians in the Orbiter Processing Facility oversee removal of one of two orbital maneuvering system (OMS) pods from Endeavour. The OMS pods are attached to the upper aft fuselage left and right sides. Fabricated primarily of graphite epoxy composite and aluminum, each pod is 21.8 feet long and 11.37 feet wide at its aft end and 8.41 feet wide at its forward end, with a surface area of approximately 435 square feet. Each pod houses the Reaction Control System propulsion components used for inflight maneuvering and is attached to the aft fuselage with 11 bolts. OMS pods are removed during Orbiter Major Modifications. Once removed, the OMS pods undergo in-depth structural inspections, system checks and the thrusters are changed out.

NASA Image and Video Library

2003-09-05

KENNEDY SPACE CENTER, FLA. - Technicians in the Orbiter Processing Facility oversee removal of one of two orbital maneuvering system (OMS) pods from Endeavour. The OMS pods are attached to the upper aft fuselage left and right sides. Fabricated primarily of graphite epoxy composite and aluminum, each pod is 21.8 feet long and 11.37 feet wide at its aft end and 8.41 feet wide at its forward end, with a surface area of approximately 435 square feet. Each pod houses the Reaction Control System propulsion components used for inflight maneuvering and is attached to the aft fuselage with 11 bolts. OMS pods are removed during Orbiter Major Modifications. Once removed, the OMS pods undergo in-depth structural inspections, system checks and the thrusters are changed out.

KENNEDY SPACE CENTER, FLA. - Workers in the Orbiter Processing Facility prepare to remove one of two orbital maneuvering system (OMS) pods from Endeavour. The OMS pods are attached to the upper aft fuselage left and right sides. Fabricated primarily of graphite epoxy composite and aluminum, each pod is 21.8 feet long and 11.37 feet wide at its aft end and 8.41 feet wide at its forward end, with a surface area of approximately 435 square feet. Each pod houses the Reaction Control System propulsion components used for inflight maneuvering and is attached to the aft fuselage with 11 bolts. OMS pods are removed during Orbiter Major Modifications. Once removed, the OMS pods undergo in-depth structural inspections, system checks and the thrusters are changed out.

NASA Image and Video Library

2003-09-05

KENNEDY SPACE CENTER, FLA. - Workers in the Orbiter Processing Facility prepare to remove one of two orbital maneuvering system (OMS) pods from Endeavour. The OMS pods are attached to the upper aft fuselage left and right sides. Fabricated primarily of graphite epoxy composite and aluminum, each pod is 21.8 feet long and 11.37 feet wide at its aft end and 8.41 feet wide at its forward end, with a surface area of approximately 435 square feet. Each pod houses the Reaction Control System propulsion components used for inflight maneuvering and is attached to the aft fuselage with 11 bolts. OMS pods are removed during Orbiter Major Modifications. Once removed, the OMS pods undergo in-depth structural inspections, system checks and the thrusters are changed out.

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, one of two orbital maneuvering system (OMS) pods removed from Endeavour is suspended overhead. The OMS pods are attached to the upper aft fuselage left and right sides. Fabricated primarily of graphite epoxy composite and aluminum, each pod is 21.8 feet long and 11.37 feet wide at its aft end and 8.41 feet wide at its forward end, with a surface area of approximately 435 square feet. Each pod houses the Reaction Control System propulsion components used for inflight maneuvering and is attached to the aft fuselage with 11 bolts. OMS pods are removed during Orbiter Major Modifications. Once removed, the OMS pods undergo in-depth structural inspections, system checks and the thrusters are changed out.

NASA Image and Video Library

2003-09-05

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, one of two orbital maneuvering system (OMS) pods removed from Endeavour is suspended overhead. The OMS pods are attached to the upper aft fuselage left and right sides. Fabricated primarily of graphite epoxy composite and aluminum, each pod is 21.8 feet long and 11.37 feet wide at its aft end and 8.41 feet wide at its forward end, with a surface area of approximately 435 square feet. Each pod houses the Reaction Control System propulsion components used for inflight maneuvering and is attached to the aft fuselage with 11 bolts. OMS pods are removed during Orbiter Major Modifications. Once removed, the OMS pods undergo in-depth structural inspections, system checks and the thrusters are changed out.

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, one of two orbital maneuvering system (OMS) pods removed from Endeavour is lowered onto a transporter. The OMS pods are attached to the upper aft fuselage left and right sides. Fabricated primarily of graphite epoxy composite and aluminum, each pod is 21.8 feet long and 11.37 feet wide at its aft end and 8.41 feet wide at its forward end, with a surface area of approximately 435 square feet. Each pod houses the Reaction Control System propulsion components used for inflight maneuvering and is attached to the aft fuselage with 11 bolts. OMS pods are removed during Orbiter Major Modifications. Once removed, the OMS pods undergo in-depth structural inspections, system checks and the thrusters are changed out.

NASA Image and Video Library

2003-09-05

KENNEDY SPACE CENTER, FLA. - In the Orbiter Processing Facility, one of two orbital maneuvering system (OMS) pods removed from Endeavour is lowered onto a transporter. The OMS pods are attached to the upper aft fuselage left and right sides. Fabricated primarily of graphite epoxy composite and aluminum, each pod is 21.8 feet long and 11.37 feet wide at its aft end and 8.41 feet wide at its forward end, with a surface area of approximately 435 square feet. Each pod houses the Reaction Control System propulsion components used for inflight maneuvering and is attached to the aft fuselage with 11 bolts. OMS pods are removed during Orbiter Major Modifications. Once removed, the OMS pods undergo in-depth structural inspections, system checks and the thrusters are changed out.

The Thermal Evolution of the Southeast Baffin Island Continental Margin: An Integrated Apatite Fission Track and Apatite (U-Th)/He Study

NASA Astrophysics Data System (ADS)

Jess, S.; Stephenson, R.; Brown, R. W.

2017-12-01

The elevated continental margins of the North Atlantic continue to be a focus of considerable geological and geomorphological debate, as the timing of major tectonic events and the age of topographic relief remain controversial. The West Greenland margin, on the eastern flank of Baffin Bay, is believed by some authors to have experienced tectonic rejuvenation and uplift during the Neogene. However, the opposing flank, Baffin Island, is considered to have experienced a protracted erosional regime with little tectonic activity since the Cretaceous. This work examines the thermal evolution of the Cumberland Peninsula, SE Baffin Island, using published apatite fission track (AFT) data with the addition of 103 apatite (U-Th)/He (AHe) ages. This expansion of available thermochronological data introduces a higher resolution of thermal modelling, whilst the application of the newly developed `Broken Crystals' technique provides a greater number of thermal constraints for an area dominated by AHe age dispersion. Results of joint thermal modelling of the AFT and AHe data exhibit two significant periods of cooling across the Cumberland Peninsula: Devonian/Carboniferous to the Triassic and Late Cretaceous to present. The earliest phase of cooling is interpreted as the result of major fluvial systems present throughout the Paleozoic that flowed across the Canadian Shield to basins in the north and south. The later stage of cooling is believed to result from rift controlled fluvial systems that flowed into Baffin Bay during the Mesozoic and Cenozoic during the early stages and culmination of rifting along the Labrador-Baffin margins. Glaciation in the Late Cenozoic has likely overprinted these later river systems creating a complex fjordal distribution that has shaped the modern elevated topography. This work demonstrates how surface processes, and not tectonism, can explain the formation of elevated continental margins and that recent methodological developments in the field of

Surrounded by work platforms, the full-scale Orion AFT crew module (center) is undergoing preparations for the first flight test of Orion's launch abort system.

NASA Image and Video Library

2008-05-20

Surrounded by work platforms, NASA's first full-scale Orion abort flight test (AFT) crew module (center) is undergoing preparations at the NASA Dryden Flight Research Center in California for the first flight test of Orion's launch abort system. To the left is a space shuttle orbiter purge vehicle sharing the hangar.

Altitude Effects on Thermal Ice Protection System Performance; a Study of an Alternative Approach

NASA Technical Reports Server (NTRS)

Addy, Harold E., Jr.; Orchard, David; Wright, William B.; Oleskiw, Myron

2016-01-01

Research has been conducted to better understand the phenomena involved during operation of an aircraft's thermal ice protection system under running wet icing conditions. In such situations, supercooled water striking a thermally ice-protected surface does not fully evaporate but runs aft to a location where it freezes. The effects of altitude, in terms of air pressure and density, on the processes involved were of particular interest. Initial study results showed that the altitude effects on heat energy transfer were accurately modeled using existing methods, but water mass transport was not. Based upon those results, a new method to account for altitude effects on thermal ice protection system operation was proposed. The method employs a two-step process where heat energy and mass transport are sequentially matched, linked by matched surface temperatures. While not providing exact matching of heat and mass transport to reference conditions, the method produces a better simulation than other methods. Moreover, it does not rely on the application of empirical correction factors, but instead relies on the straightforward application of the primary physics involved. This report describes the method, shows results of testing the method, and discusses its limitations.

STS-79 crew watches from aft flight deck during undocking from Mir

NASA Image and Video Library

1997-03-26

STS079-S-097 (16-26 Sept. 1996) --- Left to right, Terrence W. (Terry) Wilcutt, pilot; Shannon W. Lucid, mission specialist; and William F. Readdy, mission commander, are pictured on the space shuttle Atlantis' aft flight deck during undocking operations with Russia's Mir Space Station. Mir had served as both work and home for Lucid for over six months before greeting her American colleagues upon docking of Mir and Atlantis last week. Following her lengthy stay aboard Mir and several days on Atlantis, Lucid went on to spend 188 consecutive days in space before returning to Earth with the STS-79 crew. During the STS-79 mission, the crew used an IMAX camera to document activities aboard the Space Shuttle Atlantis and the various Mir modules. A hand-held version of the 65mm camera system accompanied the STS-79 crew into space in Atlantis' crew cabin. NASA has flown IMAX camera systems on many Shuttle missions, including a special cargo bay camera's coverage of other recent Shuttle-Mir rendezvous and/or docking missions.

STS-56 Commander Cameron uses SAREX on OV-103's aft flight deck

NASA Technical Reports Server (NTRS)

1993-01-01

STS-56 Commander Kenneth Cameron, wearing headset and headband equipped with penlight flashlight, uses the Shuttle Amateur Radio Experiment II (SAREX-II) on the aft flight deck of Discovery, Orbiter Vehicle (OV) 103. Cameron, positioned just behind the pilots seat, talks to amateur radio operators on Earth via the SAREX equipment. SAREX cables and the interface module freefloat in front of the pilots seat. The SAREX scan converter (a white box) is seen just above Cameron's head attached to overhead panel O9. SAREX was established by NASA, the American Radio League/Amateur Radio Satellite Corporation and the JSC Amateur Radio Club to encourage public participation in the space program through a program to demonstrate the effectiveness of conducting short-wave radio transmissions between the Shuttle and ground-based radio operators at low-cost ground stations with amateur and digital techniques. As on several previous missions, SAREX was used on this flight as an educational opportunity

KSC-2011-7766

NASA Image and Video Library

2011-11-10

VANDENBERG AIR FORCE BASE, Calif. -- At a Pegasus booster processing facility at Vandenberg Air Force Base in California, using a crane, technicians move a section of the aft skirt toward the Pegasus XL rocket for installation to the rocket’s first stage. The Orbital Sciences Corp. Pegasus rocket will launch the Nuclear Spectroscopic Telescope Array (NuSTAR) into space. After the rocket and spacecraft are processed at Vandenberg, they will be flown on the Orbital Sciences’ L-1011 carrier aircraft to the Ronald Reagan Ballistic Missile Defense Test Site at the Pacific Ocean’s Kwajalein Atoll for launch. The high-energy x-ray telescope will conduct a census for black holes, map radioactive material in young supernovae remnants, and study the origins of cosmic rays and the extreme physics around collapsed stars. For more information, visit science.nasa.gov/missions/nustar/. Photo credit: NASA/Randy Beaudoin, VAFB

KSC-2011-7764

NASA Image and Video Library

2011-11-10

VANDENBERG AIR FORCE BASE, Calif. -- At a Pegasus booster processing facility at Vandenberg Air Force Base in California, technicians unload one of the fins for the Pegasus XL rocket after its arrival. To the right is the aft skirt. The Orbital Sciences Corp. Pegasus rocket will launch the Nuclear Spectroscopic Telescope Array (NuSTAR) into space. After the rocket and spacecraft are processed at Vandenberg, they will be flown on the Orbital Sciences’ L-1011 carrier aircraft to the Ronald Reagan Ballistic Missile Defense Test Site at the Pacific Ocean’s Kwajalein Atoll for launch. The high-energy x-ray telescope will conduct a census for black holes, map radioactive material in young supernovae remnants, and study the origins of cosmic rays and the extreme physics around collapsed stars. For more information, visit science.nasa.gov/missions/nustar/. Photo credit: NASA/Randy Beaudoin, VAFB

Test Report for MSFC Test No. 83-2: Pressure scaled water impact test of a 12.5 inch diameter model of the Space Shuttle solid rocket booster filament wound case and external TVC PCD

NASA Technical Reports Server (NTRS)

1983-01-01

Water impact tests using a 12.5 inch diameter model representing a 8.56 percent scale of the Space Shuttle Solid Rocket Booster configuration were conducted. The two primary objectives of this SRB scale model water impact test program were: 1. Obtain cavity collapse applied pressure distributions for the 8.56 percent rigid body scale model FWC pressure magnitudes as a function of full-scale initial impact conditions at vertical velocities from 65 to 85 ft/sec, horizontal velocities from 0 to 45 ft/sec, and angles from -10 to +10 degrees. 2. Obtain rigid body applied pressures on the TVC pod and aft skirt internal stiffener rings at initial impact and cavity collapse loading events. In addition, nozzle loads were measured. Full scale vertical velocities of 65 to 85 ft/sec, horizontal velocities of 0 to 45 ft/sec, and impact angles from -10 to +10 degrees simulated.

Overview of the Orion Thermal Protection System

NASA Technical Reports Server (NTRS)

Kowal, T. John

2010-01-01

The Orion spacecraft is being developed as part of the Constellation Exploration Program and will serve as the United States crewed transportation system to the International Space Station after the retirement of the Space Shuttle in 2010 and as the eventual means to return U.S. astronauts to the Moon. Therefore, Orion is being designed for reentry missions from both low Earth orbit and from Lunar-return trajectories. This presentation will provide an overview of the development of the Orion TPS, a critical component in the development of the spacecraft. The thermal protection system (TPS) that protects the crew module from the extreme environments associated with Earth atmospheric reentry consists of a forward heatshield and an aft backshell. The requirements that drive the design of the TPS will be discussed, including several key requirements that establish a precedent for U.S. human-rated spacecraft. For the first time in U.S. human spaceflight, a vehicle s TPS is being designed with a specific, derived requirement for reliability. Also, due to the increased presence of spacecraft in Earth s orbit in recent decades, requirements for micro-meteoroid/orbital debris damage tolerance are also a driving requirement that has affected the selection of portions of the TPS. The efforts to select materials and to define a preliminary design for both the heatshield and the backshell will be described. This will include a discussion of the design challenges presented by the numerous penetrations on both the backshell and the heatshield. Finally, the verification and validation plan which is currently under development to certify the TPS for human-rated missions will be outlined. To support the execution of this plan, a ground test campaign for both thermal and structural performance is being designed. This test campaign will directly support thermal and thermal/structural analyses that also are fundamental to the certification effort.

Tectono-thermal evolution of north Kuqa Depression and South Tian Shan: constraints from apatite (U-Th)/He thermochronology

NASA Astrophysics Data System (ADS)

Xiao, Y.; Qiu, N.; Chang, J.

2017-12-01

The Kuqa Depression, located between Tarim Basin and South Tian Shan Orogen, is considered the most promising site for study the tectono-thermal evolution of the Central Asia Orogenic Belt (CAOB). (U-Th)/He is a new dating method and apatite He ages can record the cooling histories at low temperature between 40 ° 75°1. At present, the low temperature thermochronological data, especially the (U-Th)/He, from north Kuqa Depression are scarce, resulting in controversial issues regarding the cooling history of the upper crust and the latest uplift of South Tian Shan. We present new apatite (U-Th)/He (AHe) thermochronologic data from kuqa depression, aiming to provide insights into exhumation and thermal history of the north kuqa depression. In this study, we firstly present 43 apatite (U-Th)/He ages of 9 samples in north rim of Kuqa Depression. The (U-Th)/He ages range from 1.4±1.0Ma to 17.9±1.2Ma, which are obviously both younger than both the depositional ages and the corresponding AFT ages. To better understand the deformation evolution and thermal history of north Tarim Basin, we use these thermochronological data as inputs for HeFTy software implemented with radiation damage accumulation and annealing model (RDAAM) for time-temperature reconstruction1,2. The relationship between AHe or AFT ages and the relative stratigraphic ages shows that the AHe ages are young and almost about 10 Ma.Thermal modeling using apatite (U-Th)/He ages and geological background information in the same area allow us to obtain a cooling history. The sample T-03 suffered a cooling between 170 and 130Ma, they were re-heated at around 100° between 100 and 40Ma then rapidly cooled and exhumed to reach the surface temperature at around 5Ma. The thermal modeling results indicated the north Kuqa Depression experienced a Miocene rapid cooling event initialed at 12Ma and continued to 5Ma, resulting from far field effect of India-Asia collision. References1. Ketcham, R.A. Forward and reverse

SKIRT: The design of a suite of input models for Monte Carlo radiative transfer simulations

NASA Astrophysics Data System (ADS)

Baes, M.; Camps, P.

2015-09-01

The Monte Carlo method is the most popular technique to perform radiative transfer simulations in a general 3D geometry. The algorithms behind and acceleration techniques for Monte Carlo radiative transfer are discussed extensively in the literature, and many different Monte Carlo codes are publicly available. On the contrary, the design of a suite of components that can be used for the distribution of sources and sinks in radiative transfer codes has received very little attention. The availability of such models, with different degrees of complexity, has many benefits. For example, they can serve as toy models to test new physical ingredients, or as parameterised models for inverse radiative transfer fitting. For 3D Monte Carlo codes, this requires algorithms to efficiently generate random positions from 3D density distributions. We describe the design of a flexible suite of components for the Monte Carlo radiative transfer code SKIRT. The design is based on a combination of basic building blocks (which can be either analytical toy models or numerical models defined on grids or a set of particles) and the extensive use of decorators that combine and alter these building blocks to more complex structures. For a number of decorators, e.g. those that add spiral structure or clumpiness, we provide a detailed description of the algorithms that can be used to generate random positions. Advantages of this decorator-based design include code transparency, the avoidance of code duplication, and an increase in code maintainability. Moreover, since decorators can be chained without problems, very complex models can easily be constructed out of simple building blocks. Finally, based on a number of test simulations, we demonstrate that our design using customised random position generators is superior to a simpler design based on a generic black-box random position generator.

An investigation of the effects of aft blowing on a 3.0 caliber tangent ogive body at high angles of attack. M.S. Thesis

NASA Technical Reports Server (NTRS)

Gittner, Nathan M.

1992-01-01

An experimental investigation of the effects of aft blowing on the asymmetric vortex flow of a slender, axisymmetric body at high angles of attack was conducted. A 3.0 caliber tangent ogive body fitted with a cylindrical afterbody was tested in a wind tunnel under subsonic, laminar flow test conditions. Asymmetric blowing from both a single nozzle and a double nozzle configuration, positioned near the body apex, was investigated. Aft blowing was observed to alter the vortex asymmetry by moving the blowing-side vortex closer to the body surface while moving the non-blowing-side vortex further away from the body. The effect of increasing the blowing coefficient was to move the blowing-side vortex closer to the body surface at a more upstream location. The data also showed that blowing was more effective in altering the initial vortex asymmetry at the higher angles of attack than at the lower. The effects of changing the nozzle exit geometry were investigated and it was observed that blowing from a nozzle with a low, broad exit geometry was more effective in reducing the vortex asymmetry than blowing from a high, narrow exit geometry.

Fore-and-aft stiffness and damping characteristics of 30 x 11.5-14.5, Type VIII, bias-ply and radial-belted aircraft tires

NASA Technical Reports Server (NTRS)

Lopez, Mercedes C.; Davis, Pamela A.; Yeaton, Robert B.; Vogler, William A.

1988-01-01

Measurements of footprint geometrical properties and fore and aft stiffness and damping characteristics were obtained on 30 x 11.5-14.5 bias-ply and radial-belted aircraft tires. Significant differences in stiffness and damping characteristics were found between the two design types. The results show that footprint aspect ratio effects may interfere with the improved hydroplaning potential associated with the radial-belted tire operating at higher inflation pressures.

Investigation of Vapor Cooling Enhancements for Applications on Large Cryogenic Systems

NASA Technical Reports Server (NTRS)

Ameen, Lauren; Zoeckler, Joseph

2017-01-01

The need to demonstrate and evaluate the effectiveness of heat interception methods for use on a relevant cryogenic propulsion stage at a system level has been identified. Evolvable Cryogenics (eCryo) Structural Heat Intercept, Insulation and Vibration Evaluation Rig (SHIIVER) will be designed with vehicle specific geometries (SLS Exploration Upper Stage (EUS) as guidance) and will be subjected to simulated space environments. One method of reducing structure-born heat leak being investigated utilizes vapor-based heat interception. Vapor-based heat interception could potentially reduce heat leak into liquid hydrogen propulsion tanks, increasing potential mission length or payload capability. Due to the high number of unknowns associated with the heat transfer mechanism and integration of vapor-based heat interception on a realistic large-scale skirt design, a sub-scale investigation was developed. The sub-project effort is known as the Small-scale Laboratory Investigation of Cooling Enhancements (SLICE). The SLICE aims to study, design, and test sub-scale multiple attachments and flow configuration concepts for vapor-based heat interception of structural skirts. SLICE will focus on understanding the efficiency of the heat transfer mechanism to the boil-off hydrogen vapor by varying the fluid network designs and configurations. Various analyses were completed in MATLAB, Excel VBA, and COMSOL Multiphysics to understand the optimum flow pattern for heat transfer and fluid dynamics. Results from these analyses were used to design and fabricate test article subsections of a large forward skirt with vapor cooling applied. The SLICE testing is currently being performed to collect thermal mechanical performance data on multiple skirt heat removal designs while varying inlet vapor conditions necessary to intercept a specified amount of heat for a given system. Initial results suggest that applying vapor-cooling provides a 50 heat reduction in conductive heat transmission

STS-57 MS2 Sherlock operates RMS THC on OV-105's aft flight deck

NASA Technical Reports Server (NTRS)

1993-01-01

STS-57 Mission Specialist 2 (MS2) Nancy J. Sherlock operates the remote manipulator system (RMS) translation hand control (THC) while observing extravehicular activity (EVA) outside viewing window W10 on the aft flight deck of Endeavour, Orbiter Vehicle (OV) 105. Positioned at the onorbit station, Sherlock moved EVA astronauts in the payload bay (PLB). Payload Commander (PLC) G. David Low with his feet anchored to a special restraint device on the end of the RMS arm held MS3 Peter J.K. Wisoff during the RMS maneuvers. The activity represented an evaluation of techniques which might be used on planned future missions -- a 1993 servicing visit to the Hubble Space Telescope (HST) and later space station work -- which will require astronauts to frequently lift objects of similar sized bulk. Note: Just below Sherlock's left hand a 'GUMBY' toy watches the actvity.

Reverse Kinematic Analysis and Uncertainty Analysis of the Space Shuttle AFT Propulsion System (APS) POD Lifting Fixture

NASA Technical Reports Server (NTRS)

Brink, Jeffrey S.

2005-01-01

The space shuttle Aft Propulsion System (APS) pod requires precision alignment to be installed onto the orbiter deck. The Ground Support Equipment (GSE) used to perform this task cannot be manipulated along a single Cartesian axis without causing motion along the other Cartesian axes. As a result, manipulations required to achieve a desired motion are not intuitive. My study calculated the joint angles required to align the APS pod, using reverse kinematic analysis techniques. Knowledge of these joint angles will allow the ground support team to align the APS pod more safely and efficiently. An uncertainty analysis was also performed to estimate the accuracy associated with this approach and to determine whether any inexpensive modifications can be made to further improve accuracy.

Defect Characterization in a Thin Walled Composite RP-1 Tank: A Case Study

NASA Technical Reports Server (NTRS)

Langsing, Matthew D.; Walker, James L., II; Russell, Samual S.

2000-01-01

A full scale thin walled composite tank, designed and fabricated for the storage of pressurized RP- I rocket fuel, was fully inspected with digital infrared thermography (IR) during assembly and prior to proof testing. The tank featured a "pill capsule" design with the equatorial bondline being overwrapped on both the inner and outer surfaces. A composite skirt was bonded to the aft dome of the tank to serve as a structural support when the tank was stood on end in service. Numerous anomalies were detected and mapped prior to proof testing, some along bondlines and some scattered throughout the acreage. After the tank was intentionally burst, coupons were cut from the regions including thermographic anomalies. These coupons were again inspected thermographically to document the growth of any indications due to proof testing. Ultrasonic inspections (UT) were also performed on the coupons for comparison to thermography. Several coupons were dissected and micrographed. Relationships between IR and UT indications and the physical nature of the dissected material are presented.

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

KSC-08pd1859

NASA Image and Video Library

2008-07-01

CAPE CANAVERAL, Fla. – In the Assembly and Refurbishment Facility at NASA's Kennedy Space Center, a crane is lowered over the aft skirt for the Ares 1-X rocket. The segment is being lifted into a machine shop work stand for drilling modifications. The modifications will prepare it for the installation of the auxiliary power unit controller, the reduced-rate gyro unit, the booster decelerator motors and the booster tumble motors. Ares I is an in-line, two-stage rocket that will transport the Orion crew exploration vehicle to low-Earth orbit. Ares I-X is a test rocket. The Ares I first stage will be a five-segment solid rocket booster based on the four-segment design used for the shuttle. Ares I’s fifth booster segment allows the launch vehicle to lift more weight and reach a higher altitude before the first stage separates from the upper stage, which ignites in midflight to propel the Orion spacecraft to Earth orbit. Photo credit: NASA/Jim Grossmann

STS-55 Pilot Henricks uses CTE equipment mounted on SL-D2 aft end cone

NASA Technical Reports Server (NTRS)

1993-01-01

STS-55 Pilot Terence T. Henricks, positioned in front of an adjustable workstation mounted on the Spacelab Deutsche 2 (SL-D2) science module aft end cone, conducts Crew Telesupport Experiment (CTE). The STS-55 crew portrait (STS055(S)002) appears on the screen of the Macintosh portable computer. CTE will demonstrate real-time communication between the shuttle crew and the ground via a computer-based multimedia documentation file that includes text, graphics, and photos. CTE is expected to improve the effectiveness of on-orbit payload operations, returns from scientific investigations, crew interaction with the ground, and contingency maintenance tasks for systems and payloads. Also in the view and attached to the end cone are a fire extinguisher, a checklist, and an STS-37 extravehicular activity (EVA) photo of Mission Specialist (MS1) and Payload Commander (PLC) Jerry L. Ross (STS037-18-032).

GPACC program cost work breakdown structure-dictionary. General purpose aft cargo carrier study, volume 3

NASA Technical Reports Server (NTRS)

1985-01-01

The results of detailed cost estimates and economic analysis performed on the updated Model 101 configuration of the general purpose Aft Cargo Carrier (ACC) are given. The objective of this economic analysis is to provide the National Aeronautics and Space Administration (NASA) with information on the economics of using the ACC on the Space Transportation System (STS). The detailed cost estimates for the ACC are presented by a work breakdown structure (WBS) to ensure that all elements of cost are considered in the economic analysis and related subsystem trades. Costs reported by WBS provide NASA with a basis for comparing competing designs and provide detailed cost information that can be used to forecast phase C/D planning for new projects or programs derived from preliminary conceptual design studies. The scope covers all STS and STS/ACC launch vehicle cost impacts for delivering payloads to a 160 NM low Earth orbit (LEO).

Low-Temperature Thermochronology of Laramide Ranges in Montana and Wyoming Provides Information on Exhumation and Tectonics Associated with Flat-Slab Subduction

NASA Astrophysics Data System (ADS)

Armenta, M.; Carrapa, B.; DeCelles, P. G.

2014-12-01

Timing of exhumation of Laramide basement uplifts can be used as a proxy for tectonic processes associated with thick-skinned deformation resulting from flat-slab subduction. Despite its significance, the timing and pattern of Laramide deformation remains poorly constrained in Montana. Thermochronological data from Wyoming indicate exhumation of Laramide ranges during the late Cretaceous and Paleogene. Whereas a few data exist for the Bearthooth Range in Montana; the exhumation history of most of the Montana ranges remains unexplored preventing testing of current tectonic models. We report apatite fission track thermochronologic (AFT) data from modern river sands derived from Laramide ranges, bedrock basement samples, and synorogenic conglomerate clasts to determine the regional exhumation history of the Beartooth, Gravelly, Tobacco Root, Ruby, the Highland Mountains, and the Wind River Range. AFT permits reconstruction of thermal histories and rates of erosion of the upper few kilometers of the crust. In particular detrital AFT of river sands provides information on regional exhumation of the drainage area. AFT detrital ages derived from the southern end of the Beartooth Range are dominated by a 60-80 Ma signal, consistent with ages reported for bedrock basement samples in the Beartooth Range. A Cenozoic synorogenic conglomerate clast was obtained from the Highland Mountains, AFT results show a 69.56 +/- 5.45 Ma cooling age. In the Wind River Range, Wyoming AFT data from a Cenozoic synorogenic conglomerate clast from the Wind River Formation indicates a 59.32 +/- 4.83 Ma cooling age. This age is consistent with AFT ages from Gannett Peak indicating rapid cooling at ~60 Ma and ~50 Ma (Fan and Carrapa, 2014). Overall, samples from the easternmost ranges, the Beartooth and Bighorn, clearly preserve a Cretaceous signal; samples from Wind River Range and the rest of southwest Montana mainly record a Cenozoic signal. This suggests deeper and younger exhumation to the

Thermostructural Analysis of Unconventional Wing Structures of a Hyper-X Hypersonic Flight Research Vehicle for the Mach 7 Mission

NASA Technical Reports Server (NTRS)

Ko, William L.; Gong, Leslie

2001-01-01

Heat transfer, thermal stresses, and thermal buckling analyses were performed on the unconventional wing structures of a Hyper-X hypersonic flight research vehicle (designated as X-43) subjected to nominal Mach 7 aerodynamic heating. A wing midspan cross section was selected for the heat transfer and thermal stress analyses. Thermal buckling analysis was performed on three regions of the wing skin (lower or upper); 1) a fore wing panel, 2) an aft wing panel, and 3) a unit panel at the middle of the aft wing panel. A fourth thermal buckling analysis was performed on a midspan wing segment. The unit panel region is identified as the potential thermal buckling initiation zone. Therefore, thermal buckling analysis of the Hyper-X wing panels could be reduced to the thermal buckling analysis of that unit panel. "Buckling temperature magnification factors" were established. Structural temperature-time histories are presented. The results show that the concerns of shear failure at wing and spar welded sites, and of thermal buckling of Hyper-X wing panels, may not arise under Mach 7 conditions.

Remtech SSME nozzle design TPS

NASA Technical Reports Server (NTRS)

Bancroft, Steven A.; Engel, Carl D.; Pond, John E.

1990-01-01

Thermal damage to the Space Shuttle Main Engine (SSME) aft manifold Thermal Protection System (TPS) has been observed for flights STS-8 through STS-13. This damaged area is located on the ME2 and ME3 and extends over a region of approximately one square foot. Total failure or burn-through of the TPS could lead to severe thermal damage of the SSME manifold and loss of an engine nozzle necessitating nozzle replacement causing significant schedule delays and cost increases. Thermal damage to the manifold can be defined as a situation where the manifold temperature becomes greater than 1300 F; thereby causing loss of heat treatment in the nozzle. Results of Orbiter/nozzle wind tunnel tests and Hot Gas Facility tests of the TPS are presented. Aerothermal and thermal analysis models for the SSME aft manifold are discussed along with the flight predictions, design trajectory and design environment. Finally, the TPS design concept and TPS thermal response are addressed.

Thermal alteration in carbonaceous chondrites and implications for sublimation in rock comets

NASA Astrophysics Data System (ADS)

Springmann, Alessondra; Lauretta, Dante S.; Steckloff, Jordan K.

2015-11-01

Rock comets are small solar system bodies in Sun-skirting orbits (perihelion q < ~0.15 AU) that form comae rich in mineral sublimation products, but lack typical cometary ice sublimation products (H2O, CO2, etc.). B-class asteroid (3200) Phaethon, considered to be the parent body of the Geminid meteor shower, is the only rock comet currently known to periodically eject dust and form a coma. Thermal fracturing or thermal decomposition of surface materials may be driving Phaethon’s cometary activity (Li & Jewitt, 2013). Phaethon-like asteroids have dynamically unstable orbits, and their perihelia can change rapidly over their ~10 Myr lifetimes (de León et al., 2010), raising the possibility that other asteroids may have been rock comets in the past. Here, we propose using spectroscopic observations of mercury (Hg) as a tracer of an asteroid’s thermal metamorphic history, and therefore as a constraint on its minimum achieved perihelion distance.B-class asteroids such as Phaethon have an initial composition similar to aqueously altered primitive meteorites such as CI- or CM-type meteorites (Clark et al., 2010). Laboratory heating experiments of ~mm sized samples of carbonaceous chondrite meteorites from 300K to 1200K at a rate of 15K/minute show mobilization and volatilization of various labile elements at temperatures that could be reached by Mercury-crossing asteroids. Samples became rapidly depleted in labile elements and, in particular, lost ~75% of their Hg content when heated from ~500-700 K, which corresponds to heliocentric distances of ~0.15-0.3 au, consistent with our thermal models. Mercury has strong emission lines in the UV (~ 185 nm) and thus its presence (or absence) relative to carbonaceous chondrite abundances would indicate if these bodies had perihelia in their dynamical histories inside of 0.15 AU, and therefore may have previously been Phaethon-like rock comets. Future space telescopes or balloon-borne observing platforms equipped with a UV

STS-99 Technicians work in Endeavour's aft compartment of the payload bay

NASA Technical Reports Server (NTRS)

2000-01-01

Technicians work in the aft compartment of Shuttle Endeavour's payload bay, where a new Enhanced Main Events Controller (E-MEC) will be installed. The original E-MEC in Endeavour became suspect during the Jan. 31 launch countdown and mission STS-99 was delayed when NASA managers decided to replace it. Each Shuttle carries two enhanced master events controllers (E-MECs), which provide relays for onboard flight computers to send signals to arm and fire pyrotechnics that separate the solid rockets and external tank during assent. Both E-MECs are needed for the Shuttle to be cleared for flight. Currently Endeavour and Columbia are the only two orbiters with the E-MECs. Built by Rockwell's Satellite Space Electronics Division, Anaheim, Calif., each unit weighs 65 pounds and is approximately 20 inches long, 13 inches wide and 8 inches tall. Previously, three Shuttle flights have been scrubbed or delayed due to faulty MECs: STS-73, STS-49 and STS-41-D. Before workers can begin E-MEC replacement efforts at the launch pad, cryogenic reactants had to be offloaded from the orbiter and Space Shuttle ordnance disconnected. The next scheduled date for launch of STS-99 is Feb. 11 at 12:30 p.m. EST.

STS-37 Pilot Cameron and MS Godwin work on OV-104's aft flight deck

NASA Image and Video Library

1991-04-11

STS037-33-031 (5-11 April 1991) --- Astronauts Kenneth D. Cameron, STS-37 pilot, and Linda M. Godwin, mission specialist, take advantage of a well-lighted crew cabin to pose for an in-space portrait on the Space Shuttle Atlantis' aft flight deck. The two shared duties controlling the Remote Manipulator System (RMS) during operations involving the release of the Gamma Ray Observatory (GRO) and the Extravehicular Activity (EVA) of astronauts Jerry L. Ross and Jerome (Jay) Apt. The overhead window seen here and nearby eye-level windows (out of frame at left) are in a busy location on Shuttle missions, as they are used for payload surveys, Earth observation operations, astronomical studies and other purposes. Note the temporarily stowed large format still photo camera at lower right corner. This photo was made with a 35mm camera. This was one of the visuals used by the crew members during their April 19 Post Flight Press Conference (PFPC) at the Johnson Space Center (JSC).

A parametric shell analysis of the shuttle 51-L SRB AFT field joint

NASA Technical Reports Server (NTRS)

Davis, Randall C.; Bowman, Lynn M.; Hughes, Robert M., IV; Jackson, Brian J.

1990-01-01

Following the Shuttle 51-L accident, an investigation was conducted to determine the cause of the failure. Investigators at the Langley Research Center focused attention on the structural behavior of the field joints with O-ring seals in the steel solid rocket booster (SRB) cases. The shell-of-revolution computer program BOSOR4 was used to model the aft field joint of the solid rocket booster case. The shell model consisted of the SRB wall and joint geometry present during the Shuttle 51-L flight. A parametric study of the joint was performed on the geometry, including joint clearances, contact between the joint components, and on the loads, induced and applied. In addition combinations of geometry and loads were evaluated. The analytical results from the parametric study showed that contact between the joint components was a primary contributor to allowing hot gases to blow by the O-rings. Based upon understanding the original joint behavior, various proposed joint modifications are shown and analyzed in order to provide additional insight and information. Finally, experimental results from a hydro-static pressurization of a test rocket booster case to study joint motion are presented and verified analytically.

Masking of thresholds for the perception of fore-and-aft vibration of seat backrests.

PubMed

Morioka, Miyuki; Griffin, Michael J

2015-09-01

The detection of a vibration may be reduced by the presence of another vibration: a phenomenon known as 'masking'. This study investigated how the detection of one frequency of vibration is influenced by vibration at another frequency. With nine subjects, thresholds for detecting fore-and-aft backrest vibration were determined (for 4, 8, 16, and 31.5-Hz sinusoidal vibration) in the presence of a masker vibration (4-Hz random vibration, 1/3-octave bandwidth at six intensities). The masker vibration increased thresholds for perceiving vibration at each frequency by an amount that reduced with increasing difference between the frequency of the sinusoidal vibration and the frequency of the masker vibration. The 4-Hz random vibration almost completely masked 4-Hz sinusoidal vibration, partially masked 8- and 16-Hz vibration, and only slightly masked 31.5-Hz vibration. The findings might be explained by the involvement of different sensory systems and different body locations in the detection of different frequencies of vibration. Copyright © 2015 Elsevier Ltd and The Ergonomics Society. All rights reserved.

The telerobot workstation testbed for the shuttle aft flight deck: A project plan for integrating human factors into system design

NASA Technical Reports Server (NTRS)

Sauerwein, Timothy

1989-01-01

The human factors design process in developing a shuttle orbiter aft flight deck workstation testbed is described. In developing an operator workstation to control various laboratory telerobots, strong elements of human factors engineering and ergonomics are integrated into the design process. The integration of human factors is performed by incorporating user feedback at key stages in the project life-cycle. An operator centered design approach helps insure the system users are working with the system designer in the design and operation of the system. The design methodology is presented along with the results of the design and the solutions regarding human factors design principles.

DACC program cost and work breakdown structure-dictionary. General purpose aft cargo carrier study, volume 2

NASA Technical Reports Server (NTRS)

1985-01-01

Results of detailed cost estimates and economic analysis performed on the updated 201 configuration of the dedicated Aft Cargo Carrier (DACC) are given. The objective of this economic analysis is to provide the National Aeronautics and Space Administration (NASA) with information on the economics of using the DACC on the Space Transportation System (STS). The detailed cost estimates for the DACC are presented by a work breakdown structure (WBS) to ensure that all elements of cost are considered in the economic analysis and related subsystem trades. Costs reported by WBS provide NASA with a basis for comparing competing designs and provide detailed cost information that can be used to forecast phase C/D planning for new projects or programs derived from preliminary conceptual design studies. The scope covers all STS and STS/DACC launch vehicle cost impacts for delivering an orbital transfer vehicle to a 120 NM low Earth orbit (LEO).

Experimental investigation of the effects of aft blowing with various nozzle exit geometries on a 3.0 caliber tangent ogive at high angles of attack: Forebody pressure distributions

NASA Technical Reports Server (NTRS)

Chokani, Ndaona; Gittner, N. M.

1992-01-01

An experimental study of the effects of aft blowing on the asymmetric vortex flow of a slender, axisymmetric body at high angles of attack was conducted. A 3.0 caliber tangent ogive body fitted with a cylindrical afterbody was tested in a wind tunnel under subsonic, laminar flow test conditions. Asymmetric blowing from both a single nozzle and a double nozzle configuration, positioned near the body apex, was studied. Aft blowing was observed to alter the vortex asymmetry by moving the blowing-side vortex closer to the body surface while moving the non-blowing-side vortex further away from the body. The effect of increasing the blowing coefficient was to move the blowing-side vortex closer to the body surface at a more upstream location. The data also showed that blowing was more effective in altering the initial vortex asymmetry at the higher angles of attack than at the lower. The effects of changing the nozzle exit geometry were studied and it was observed that blowing from a nozzle with a low, broad exit geometry was more effective in reducing the vortex asymmetry than blowing from a high, narrow exit geometry.

Astronaut Thermal Exposure: Re-Entry After Low Earth Orbit Rescue Mission

NASA Technical Reports Server (NTRS)

Gillis, David B.; Hamilton, Douglas; Ilcus, Stana; Stepaniak, Phil; Son, Chang; Bue, Grant

2009-01-01

The STS-125 mission, launched May 11, 2009, is the final servicing mission to the Hubble Space Telescope. The repair mission's EVA tasks are described, including: installing a new wide field camera; installing the Cosmic Origins Spectrograph; repairing the Space Telescope Imaging Spectrograph; installing a new outer blanket layer; adding a Soft Capture and Rendezvous System for eventual controlled deorbit in about 2014; replacing the 'A' side Science Instrument Command and Data Handling module; repairing the Advanced Camera for surveys; and, replacing the rate sensor unit gyroscopes, fine guidance sensors and 3 batteries. Additionally, the Shuttle crew cabin thermal environment is described. A CFD model of per person CO2 demonstrates a discrepancy between crew breathing volume and general mid-deck levels of CO2. A follow-on CFD analysis of the mid-deck temperature distribution is provided. Procedural and engineering mitigation plans are presented to counteract thermal exposure upon reentry to the Earth atmosphere. Some of the procedures include: full cold soak the night prior to deorbit; modifying deck stowage to reduce interference with air flow; and early securing of avionics post-landing to reduce cabin thermal load prior to hatch opening. Engineering mitigation activities include modifying the location of the aft starboard ICUs, eliminating the X3 stack and eliminating ICU exhaust air directed onto astronauts; improved engineering data of ICU performance; and, verifying the adequacy of mid-deck temperature control using CFD models in addition to lumped parameter models. Post-mitigation CFD models of mid-deck temperature profiles and distribution are provided.

Perception of fore-and-aft whole-body vibration intensity measured by two methods.

PubMed

Forta, Nazım Gizem; Schust, Marianne

2015-01-01

This experimental study investigated the perception of fore-and-aft whole-body vibration intensity using cross-modality matching (CM) and magnitude estimation (ME) methods. Thirteen subjects were seated on a rigid seat without a backrest and exposed to sinusoidal stimuli from 0.8 to 12.5 Hz and 0.4 to 1.6 ms(-2) r.m.s. The Stevens exponents did not significantly depend on vibration frequency or the measurement method. The ME frequency weightings depended significantly on vibration frequency, but the CM weightings did not. Using the CM and ME weightings would result in higher weighted exposures than those calculated using the ISO (2631-1, 1997) Wd. Compared with ISO Wk, the CM and ME-weighted exposures would be greater at 1.6 Hz and lesser above that frequency. The CM and ME frequency weightings based on the median ratings for the reference vibration condition did not differ significantly. The lack of a method effect for weightings and for Stevens exponents suggests that the findings from the two methods are comparable. Frequency weighting curves for seated subjects for x-axis whole-body vibration were derived from an experiment using two different measurement methods and were compared with the Wd and Wk weighting curves in ISO 2631-1 (1997).

Cooling system for a bearing of a turbine rotor

DOEpatents

Schmidt, Mark Christopher

2002-01-01

In a gas turbine, a bore tube assembly radially inwardly of an aft bearing conveys cooling steam to the buckets of the turbine and returns the cooling steam to a return. To cool the bearing and thermally insulate the bearing from the cooling steam paths, a radiation shield is spaced from the bore tube assembly by a dead air gap. Additionally, an air passageway is provided between the radiation shield and the inner surface of an aft shaft forming part of the rotor. Air is supplied from an inlet for flow along the passage and radially outwardly through bores in the aft shaft disk to cool the bearing and insulate it from transfer of heat from the cooling steam.

STS-56 MS1 Foale and MS2 Cockrell on aft flight deck of Discovery, OV-103

NASA Technical Reports Server (NTRS)

1993-01-01

STS-56 Mission Specialist 1 (MS1) Michael Foale (left) and MS2 Kenneth D. Cockrell pose on aft flight deck of Discovery, Orbiter Vehicle (OV) 103, for this in-cabin electronic still camera (ESC) photograph. The two crewmembers are positioned in front of the onorbit station with a beam of sunlight shining through overhead window W8. The cable on the bottom right is part of the Hand-held, Earth-oriented, Real-time, Cooperative, User-friendly, Location-targeting and Environmental System (HERCULES), connecting the HERCULES Attitude Processor (HAP) to the Inertial Measurement Unit (IMU). In-cabin shots with the camera are for test purposes only. HERCULES is a device that makes it simple for Shuttle crewmembers to take pictures of Earth as they merely point and shoot any interesting feature, whose latitude and longitude are automatically determined in real time. Digital file name is ESC01008.TGA.

Atlas V Launch Incorporated NASA Glenn Thermal Barrier

NASA Technical Reports Server (NTRS)

Dunlap, Patrick H., Jr.; Steinetz, Bruce M.

2004-01-01

In the Spring of 2002, Aerojet experienced a major failure during a qualification test of the solid rocket motor that they were developing for the Atlas V Enhanced Expendable Launch Vehicle. In that test, hot combustion gas reached the O-rings in the nozzle-to-case joint and caused a structural failure that resulted in loss of the nozzle and aft dome sections of the motor. To improve the design of this joint, Aerojet decided to incorporate three braided carbon-fiber thermal barriers developed at the NASA Glenn Research Center. The thermal barriers were used to block the searing-hot 5500 F pressurized gases from reaching the temperature-sensitive O-rings that seal the joint. Glenn originally developed the thermal barriers for the nozzle joints of the space shuttle solid rocket motors, and Aerojet decided to use them on the basis of the results of several successful ground tests of the thermal barriers in the shuttle rockets. Aerojet undertook an aggressive schedule to redesign the rocket nozzle-to-case joint with the thermal barriers and to qualify it in time for a launch planned for the middle of 2003. They performed two successful qualification tests (Oct. and Dec. 2002) in which the Glenn thermal barriers effectively protected the O-rings. These qualification tests saved hundreds of thousands of dollars in development costs and put the Lockheed-Martin/Aerojet team back on schedule. On July 17, 2003, the first flight of an Atlas V boosted with solid rocket motors successfully launched a commercial satellite into orbit from Cape Canaveral Air Force Station. Aero-jet's two 67-ft solid rocket boosters performed flawlessly, with each providing thrust in excess of 250,000 lbf. Both motors incorporated three Glenn-developed thermal barriers in their nozzle-to-case joints. The Cablevision satellite launched on this mission will be used to provide direct-to-home satellite television programming for the U.S. market starting in late 2003. The Atlas V is a product of the

Qualification of the gritblast assembly and process for the inside diameter of the RSRM forward and aft domes

NASA Technical Reports Server (NTRS)

Nolan, Michael J.

1992-01-01

This gritblast assembly shall be used when refurbishing the Inside Diameter (ID) of RSRM forward and aft domes. Initial blasting is used to remove corrosion and adhesive not removed during the insulation washout. Final blasting is conducted just prior to part finalization in order to remove residual contamination and prepare the ID surface for bonding. The media used in this gritblaster is DuPont Zirclean Blasting Abrasive. It is possible to use other media in this gritblast assembly, however the only facility that has the control capability for this assembly is the Zirclean blast booth. This blast booth can not use other media without the occurrence of contamination. This automated process shall replace the manually controlled gritblasting that is currently in operation. Manual gritblasting does not provide the consistency, control, and safety that an automated process is capable of delivering.

Low-Temperature Thermochronology of Borehole and Surface Samples From the Wind River and Beartooth Laramide Ranges, Wyoming and Montana, USA

NASA Astrophysics Data System (ADS)

Peyton, S. L.; Reiners, P. W.

2007-12-01

We dated borehole and surface samples from the Wind River and Beartooth Laramide-age, basement-cored uplifts of the Rocky Mountain foreland using the apatite (U-Th)/He (AHe) system. Comparison of these results to previously published apatite fission-track (AFT) data along with the incorporation of new He diffusion models (Shuster et al., 2006), reveals several new insights into, and poses new interpretational challenges for, the shallow exhumation histories of these ranges. Deep (2.2-2.8 km below surface) borehole samples from the Wind River Range have AHe ages of 9-12 Ma, and suggest at least 600 m of rapid exhumation during the Miocene. Shallower samples range from 35-66 Ma and are consistent with exhumation of a fossil partial retention zone. Previously-published apatite fission track (AFT) data from the same borehole show at least 2 km of rapid exhumation at ~45-38 Ma at depths where AHe ages are 9-50 Ma. This contrasts with the AHe ages which show slow exhumation between 12-66 Ma and have a trend on an age-elevation plot that appears to cut across the AFT age trend. Forward modeling of the cooling ages of these data using well-constrained thermal histories and conventional Durango apatite He diffusion data cannot explain these coupled AFT-AHe age-elevation relationships. However, modeling using diffusion kinetics of the Shuster et al. radiation-damage trapping model can explain the observed age trends, including the apparent presence of a 45-38 Ma exhumation event in the AFT data and its absence in the AHe data. In the model the shallow samples do not reach high enough temperatures for annealing of accumulated radiation damage, so He is trapped and ages are much older than predicted by conventional diffusion models. Previously-published AFT data from the Beartooth Range also show a large Laramide-age exhumation event, dated at 57-52 Ma. Similar to our observations from the Wind River Range, this event is not represented in our AHe results from borehole samples

Pegasus XL CYGNSS

NASA Image and Video Library

2016-09-15

Inside Building 1555 at Vandenberg Air Force Base in California, technicians and engineers install the first stage aft skirt on the Orbital ATK Pegasus XL rocket which will launch eight NASA Cyclone Global Navigation Satellite System, or CYGNSS, spacecraft. When preparations are completed at Vandenberg, the rocket, with CYGNSS in its payload fairing, will be attached to the Orbital ATK L-1011 carrier aircraft and transported to NASA’s Kennedy Space Center in Florida. On Dec. 12, 2016, the carrier aircraft is scheduled to take off from the Skid Strip at Cape Canaveral Air Force Station and CYGNSS will launch on the Pegasus XL rocket with the L-1011 flying off shore. CYGNSS will make frequent and accurate measurements of ocean surface winds throughout the life cycle of tropical storms and hurricanes. The data that CYGNSS provides will enable scientists to probe key air-sea interaction processes that take place near the core of storms, which are rapidly changing and play a critical role in the beginning and intensification of hurricanes.

Space Launch System Booster Separation Aerodynamic Testing in the NASA Langley Unitary Plan Wind Tunnel

NASA Technical Reports Server (NTRS)

Wilcox, Floyd J., Jr.; Pinier, Jeremy T.; Chan, David T.; Crosby, William A.

2016-01-01

A wind-tunnel investigation of a 0.009 scale model of the Space Launch System (SLS) was conducted in the NASA Langley Unitary Plan Wind Tunnel to characterize the aerodynamics of the core and solid rocket boosters (SRBs) during booster separation. High-pressure air was used to simulate plumes from the booster separation motors (BSMs) located on the nose and aft skirt of the SRBs. Force and moment data were acquired on the core and SRBs. These data were used to corroborate computational fluid dynamics (CFD) calculations that were used in developing a booster separation database. The SRBs could be remotely positioned in the x-, y-, and z-direction relative to the core. Data were acquired continuously while the SRBs were moved in the axial direction. The primary parameters varied during the test were: core pitch angle; SRB pitch and yaw angles; SRB nose x-, y-, and z-position relative to the core; and BSM plenum pressure. The test was conducted at a free-stream Mach number of 4.25 and a unit Reynolds number of 1.5 million per foot.

Investigation of the transmission of fore and aft vibration through the human body.

PubMed

Demić, Miroslav; Lukić, Jovanka

2009-07-01

Understanding the behavior of human body under the influence of vibration is of great importance for the optimal motor vehicle system design. Therefore, great efforts are being done in order to discover as many information about the influence of vibration on human body as possible. So far the references show that the major scientific attention has been paid to vertical vibration, although intensive research has been performed lately on the other sorts of excitation. In this paper, the results of the investigation of behavior of human body, in seated position, under the influence of random fore and aft vibration are shown. The investigation is performed by the use of an electro-hydraulic simulator, on a group of 30 healthy male occupants. Experiments are performed in order to give results to improve human body modeling in driving conditions. Excitation amplitudes (1.75 and 2.25 m/s(2) rms) and seat backrest conditions (with and without inclination) were varied. Data results are analyzed by partial coherence and transfer functions. Analyses have been performed and results are given in detail. The results obtained have shown that the human body under the influence of random excitations behaves as a non-linear system and its response depends on spatial position. Obtained results give necessary data to define structure and parameters of human biodynamic model with respect to different excitation and seat backrest position.

Vertical drop test of a transport fuselage section located aft of the wing

NASA Technical Reports Server (NTRS)

Fasanella, E. L.; Alfaro-Bou, E.

1986-01-01

A 12-foot long Boeing 707 aft fuselage section with a tapering cross section was drop tested at the NASA Langley Research Center to measure structural, seat, and occupant response to vertical crash laods and to provide data for nonlinear finite element modeling. This was the final test in a series of three different transport fuselage sections tested under identical conditions. The test parameters at impact were: 20 ft/s velocity, and zero pitch, roll, and yaw. In addition, the test was an operational shock test of the data acquisition system used for the Controlled Impact Demonstration (CID) of a remotely piloted Boeing 720 that was crash tested at NASA Ames Dryden Flight Research Facility on December 1, 1984. Post-test measurements of the crush showed that the front of the section (with larger diameter) crushed vertically approximately 14 inches while the rear crushed 18 inches. Analysis of the data traces indicate the maximum peak normal (vertical) accelerations at the bottom of the frames were approximately 109 G at body station 1040 and 64 G at body station 1120. The peak floor acceleration varied from 14 G near the wall to 25 G near the center where high frequency oscillations of the floor were evident. The peak anthropomorphic dummy pelvis normal (vertical) acceleration was 19 G's.

Aircraft system aft telescope cavity configuration study for Stratospheric Observatory for Infrared Astronomy (SOFIA), phase 2

NASA Technical Reports Server (NTRS)

1994-01-01

The SOFIA Aircraft System (AS) Phase 1 Study was a broad-based study which addressed itself to satisfying technical and programmatic requirements by drawing from existing technology and applying cost-efficient commercial approaches to the aircraft modification. In this SOFIA AS Phase 2 Study, five critical areas of the aircraft were selected for more detailed investigation: forward pressure bulkhead, aft bulkhead, 'free' shell to bulkhead interface, shell cut-out to bulkhead interface, and flooring. The in-depth investigation of these areas upon a finite element model (FEM), with a fine grid model in areas of particular interest, is discussed. The FEM code used is called 'STRAP' and was developed by the engineering firm, Rasmussen and Associates. STRAP is NASTRAN compatible to within 1%. The loads applied to the model were approximated from known 747 envelope conditions. The areas of investigation, and a section through the fuselage is shown. The thrust of this investigation was to develop the design concepts conceived under phase 1 to the point where detailed design could be undertaken with a high level of confidence.

Thermal Analysis of a Carbon Fiber Rope Barrier for Use in the Reusable Solid Rocket Motor Nozzle Joint-2

NASA Technical Reports Server (NTRS)

Clayton, J. Louie

2002-01-01

This study provides development and verification of analysis methods used to assess performance of a carbon fiber rope (CFR) thermal barrier system that is currently being qualified for use in Reusable Solid Rocket Motor (RSRM) nozzle joint-2. Modeled geometry for flow calculations considers the joint to be vented with the porous CFR barriers placed in the 'open' assembly gap. Model development is based on a 1-D volume filling approach where flow resistances (assembly gap and CFRs) are defined by serially connected internal flow and the porous media 'Darcy' relationships. Combustion gas flow rates are computed using the volume filling code by assuming a lumped distribution total joint fill volume on a per linear circumferential inch basis. Gas compressibility, friction and heat transfer are included in the modeling. Gas-to-wall heat transfer is simulated by concurrent solution of the compressible flow equations and a large thermal 2-D finite element (FE) conduction grid. The derived numerical technique loosely couples the FE conduction matrix with the compressible gas flow equations. Free constants that appear in the governing equations are calibrated by parametric model comparison to hot fire subscale test results. The calibrated model is then used to make full-scale motor predictions using RSRM aft dome environments. Model results indicate that CFR thermal barrier systems will provide a thermally benign and controlled pressurization environment for the RSRM nozzle joint-2 primary seal activation.

Thermal Analysis of a Carbon Fiber Rope Barrier for Use in the Reusable Solid Rocket Motor Nozzle Joint-2

NASA Technical Reports Server (NTRS)

Clayton, J. Louie; Phelps, Lisa (Technical Monitor)

2001-01-01

This study provides for development and verification of analysis methods used to assess performance of a carbon fiber rope (CFR) thermal barrier system that is currently being qualified for use in Reusable Solid Rocket Motor (RSRM) nozzle joint-2. Modeled geometry for flow calculations considers the joint to be vented with the porous CFR barriers placed in the "open' assembly gap. Model development is based on a 1-D volume filling approach where flow resistances (assembly gap and CFRs) are defined by serially connected internal flow and the porous media "Darcy" relationships. Combustion gas flow rates are computed using the volume filling code by assuming a lumped distribution total joint fill volume on a per linear circumferential inch basis. Gas compressibility, friction and heat transfer are included in the modeling. Gas-to-wall heat transfer is simulated by concurrent solution of the compressible flow equations and a large thermal 2-D finite element (FE) conduction grid. The derived numerical technique loosely couples the FE conduction matrix with the compressible gas flow equations, Free constants that appear in the governing equations are calibrated by parametric model comparison to hot fire subscale test results. The calibrated model is then used to make full-scale motor predictions using RSRM aft dome environments. Model results indicate that CFR thermal barrier systems will provide a thermally benign and controlled pressurization environment for the RSRM nozzle joint-2 primary seal activation.

Development of A 2,000-10,000-Lb Improved Container Delivery System

DTIC Science & Technology

2010-04-01

System. The fourth airdrop system within the program is the Skirt Reefed G-12. The Skirt Reefed G-12 is intended to be a HV airdrop system...UNCLASSIFIED 5 D. Skirt Reefed G-12 System The Skirt Reefed G-12 System utilizes the G-12 parachute packed in accordance with Humanitarian Airdrop...Procedures2 with a slight variation in the reefing line material used. After several tests and many failures, the 9/16- inch tubular nylon and 2 turns of

Use of Several Thermal Analysis Techniques to Study the Cracking of a Nitrile Butadiene Rubber (NBR) Insulator on the Booster Separation Motor (BSM) of the Space Shuttle

NASA Technical Reports Server (NTRS)

Wingard, Charles D.

1999-01-01

Two different vendor rubber formulations have been used to produce the silica-filled NBR insulators for the BSM of each of the two Solid Rocket Boosters (SRBs) on the Space Shuttle. Each cured insulator is bonded to the BSM aluminum aft closure with an epoxy adhesive, and some of the curved areas in the rubber may have significant residual stresses. A number of recently bonded NBR insulators have shown fine surface cracks, and stressed insulator areas may be aging at a faster rate than unstressed areas, thus hastening the surface cracking. Thermal analysis data on both vendor insulators by Dynamic Mechanical Analysis (DMA) through a temperature/frequency sweep from 24 to 74 C have shown a higher flexural storage modulus and Arrhenius activation energy for the stressed area than for the unstressed area. Other thermal analysis techniques are being used to study the insulator surface vs. bulk interior for better understanding this anomaly.

VIBRATION DAMPING AND SHOCK MOUNT

DOEpatents

Stevens, D.J.; Forman, G.W.

1963-12-10

A shock absorbing mount in which vibrations are damped by an interference fit between relatively movable parts of the mount is described. A pair of generally cup-shaped parts or members have skirt portions disposed in an oppositely facing nesting relationship with the skirt of one member frictionally engaging the skirt of the other. The outermost skirt may be slotted to provide spring-like segments which embrace the inner skirt for effecting the interference fit. Belleville washers between the members provide yieldable support for a load carried by the mount. When a resonant frequency of vibration forces acting upon the moumt attains a certain level the kinetic energy of these forces is absorbed by sliding friction between the parts. (AEC)

Flow Structures and Noise Produced by a Heated Rectangular Nozzle with a Third Stream and Aft Deck

NASA Astrophysics Data System (ADS)

Ruscher, Christopher; Gogineni, Sivaram; Kiel, Barry

2015-11-01

Jet noise is a huge issue that affects both civilian and military aviation and is a two-fold problem. Near-field noise causes hearing damage and is of great concern to the Navy. Far-field noise is also a concern for military and civilian aircraft. For military jets, the trend has shown that newer and more advanced planes are louder than their predecessors. Most of these planes are designed keeping the performance as the main driver in mind while the jet noise becomes an afterthought. To remedy this and to aid the design process, we propose to create a joint noise and performance prediction tool. To create this tool, one must understand how the near-field flow structures generate noise and how they are related to far-field noise. In the current work, we considered rectangular, three-stream nozzle with an aft deck and investigated the flow structures such as corner vortices, shocks and their impact on the noise generation mechanism. We have also used state-of-the-art data analytical tools such as wavelets, POD, and stochastic estimations.

Using Pressure- and Temperature-Sensitive Paint for Global Surface Pressure and Temperature Measurements on the Aft-Body of a Capsule Reentry Vehicle

NASA Technical Reports Server (NTRS)

Watkins, A. Neal; Buck, Gregory M.; Leighty, Bradley D.; Lipford, William E.; Oglesby, Donald M.

2008-01-01

Pressure Sensitive Paint (PSP) and Temperature Sensitive Paint (TSP) were used to visualize and quantify the surface interactions of reaction control system (RCS) jets on the aft body of capsule reentry vehicle shapes. The first model tested was an Apollo-like configuration and was used to focus primarily on the effects of the forward facing roll and yaw jets. The second model tested was an early Orion Crew Module configuration blowing only out of its forward-most yaw jet, which was expected to have the most intense aerodynamic heating augmentation on the model surface. This paper will present the results from the experiments, which show that with proper system design, both PSP and TSP are effective tools for studying these types of interaction in hypersonic testing environments.

Piloting the use of indigenous methods to prevent Nipah virus infection by interrupting bats' access to date palm sap in Bangladesh.

PubMed

Nahar, Nazmun; Mondal, Utpal Kumar; Sultana, Rebeca; Hossain, M Jahangir; Khan, M Salah Uddin; Gurley, Emily S; Oliveras, Elizabeth; Luby, Stephen P

2013-09-01

People in Bangladesh frequently drink fresh date palm sap. Fruit bats (Pteropus giganteus) also drink raw sap and may contaminate the sap by shedding Nipah virus through saliva and urine. In a previous study we identified two indigenous methods to prevent bats accessing the sap, bamboo skirts and lime (calcium carbonate). We conducted a pilot study to assess the acceptability of these two methods among sap harvesters. We used interactive community meetings and group discussions to encourage all the sap harvesters (n = 12) from a village to use either bamboo skirts or lime smear that some of them (n = 4) prepared and applied. We measured the preparation and application time and calculated the cost of bamboo skirts. We conducted interviews after the use of each method. The sap harvesters found skirts effective in preventing bats from accessing sap. They were sceptical that lime would be effective as the lime was washed away by the sap flow. Preparation of the skirt took ∼105 min. The application of each method took ∼1 min. The cost of the bamboo skirt is minimal because bamboo is widely available and they made the skirts with pieces of used bamboo. The bamboo skirt method appeared practical and affordable to the sap harvesters. Further studies should explore its ability to prevent bats from accessing date palm sap and assess if its use produces more or better quality sap, which would provide further incentives to make it more acceptable for its regular use.

Debris/ice/TPS assessment and integrated photographic analysis for Shuttle Mission STS-62

NASA Technical Reports Server (NTRS)

Katnik, Gregory N.; Bowen, Barry C.; Davis, J. Bradley; Speece, Robert F.; Rivera, Jorge E.

1994-01-01

A pre-launch debris inspection of the pad and Shuttle vehicle was conducted on 2 March 1994. The detailed walkdown of Launch Pad 39B and MLP-1 also included the primary flight elements OV-102 Columbia (16th flight), ET-62 (LWT 55), and BI-064 SRB's. There were no significant facility or vehicle anomalies. After the launch on March 4th, a debris inspection of Pad 39B was performed. Damage to the pad overall was minimal. On-orbit photographs taken by the flight crew and two films from the ET/ORB umbilical cameras of the External Tank after separation from the Orbiter revealed no major damage or lost flight hardware that would have been a safety of flight concern. Orbiter performance on final approach appeared normal. Infrared imagery of landing gear deployment showed the loss of thermal barrier from the nose gear wheel well. The missing thermal barrier material was not recovered. The Solid Rocket Boosters were inspected at Hanger AF after retrieval. Both frustums had a combined total of 44 MSA-2 debonds over fasteners. Significant amounts of BTA had been applied to closeouts on the RH frustum, forward skirt, and aft skirt. Hypalon paint was blistered/missing over the areas were the BTA had been applied. The underlying BTA was not sooted (IFA STS-62-B-1). Investigation of this condition has concluded there was insufficient heat rates to cause blistering of the Hypalon until late in the ascent phase. A post landing inspection of OV-102 was conducted after the landing at KSC. The Orbiter TPS sustained a total of 97 hits, of which 16 had a major dimension of 1 inch or larger. The Orbiter lower surface had a total of 36 hits, of which 7 had a major dimension of 1 inch or larger. Based on these numbers and comparison to statistics from previous missions of similar configuration, both the total number of debris hits and the number of hits 1 inch or larger was less than average. Six thermal barriers, total size approximately 36 in. x 3 in. x 1.5 in., and one corner tile

Debris/ice/TPS assessment and integrated photographic analysis for Shuttle Mission STS-62

NASA Astrophysics Data System (ADS)

Katnik, Gregory N.; Bowen, Barry C.; Davis, J. Bradley; Speece, Robert F.; Rivera, Jorge E.

1994-05-01

A pre-launch debris inspection of the pad and Shuttle vehicle was conducted on 2 March 1994. The detailed walkdown of Launch Pad 39B and MLP-1 also included the primary flight elements OV-102 Columbia (16th flight), ET-62 (LWT 55), and BI-064 SRB's. There were no significant facility or vehicle anomalies. After the launch on March 4th, a debris inspection of Pad 39B was performed. Damage to the pad overall was minimal. On-orbit photographs taken by the flight crew and two films from the ET/ORB umbilical cameras of the External Tank after separation from the Orbiter revealed no major damage or lost flight hardware that would have been a safety of flight concern. Orbiter performance on final approach appeared normal. Infrared imagery of landing gear deployment showed the loss of thermal barrier from the nose gear wheel well. The missing thermal barrier material was not recovered. The Solid Rocket Boosters were inspected at Hanger AF after retrieval. Both frustums had a combined total of 44 MSA-2 debonds over fasteners. Significant amounts of BTA had been applied to closeouts on the RH frustum, forward skirt, and aft skirt. Hypalon paint was blistered/missing over the areas were the BTA had been applied. The underlying BTA was not sooted (IFA STS-62-B-1). Investigation of this condition has concluded there was insufficient heat rates to cause blistering of the Hypalon until late in the ascent phase. A post landing inspection of OV-102 was conducted after the landing at KSC. The Orbiter TPS sustained a total of 97 hits, of which 16 had a major dimension of 1 inch or larger. The Orbiter lower surface had a total of 36 hits, of which 7 had a major dimension of 1 inch or larger. thermal barriers, total size approximately 36 in. x 3 in. x 1.5 in., and one corner tile

Aeropropulsive characteristics of twin nonaxisymmetric vectoring nozzles installed with forward-swept and aft-swept wings. [in the Langley 16 Foot Transonic Tunnel

NASA Technical Reports Server (NTRS)

Capone, F. J.

1981-01-01

An investigation was conducted in the Langley 16 Foot Transonic Tunnel to determine the aeropropulsive characteristics of a single expansion ramp nozzle (SERN) and a two dimensional convergent divergent nozzle (2-D C-D) installed with both an aft swept and a forward swept wing. The SERN was tested in both an upright and an inverted position. The effects of thrust vectoring at nozzle vector angles from -5 deg to 20 deg were studied. This investigation was conducted at Mach numbers from 0.40 to 1.20 and angles of attack from -2.0 deg to 16 deg. Nozzle pressure ratio was varied from 1.0 (jet off) to about 9.0. Reynolds number based on the wing mean geometric chord varied from about 3 million to 4.8 million, depending upon free stream number.

A Randomized Controlled Trial of Interventions to Impede Date Palm Sap Contamination by Bats to Prevent Nipah Virus Transmission in Bangladesh

PubMed Central

Khan, Salah Uddin; Gurley, Emily S.; Hossain, M. Jahangir; Nahar, Nazmun; Sharker, M. A. Yushuf; Luby, Stephen P.

2012-01-01

Background Drinking raw date palm sap is a risk factor for human Nipah virus (NiV) infection. Fruit bats, the natural reservoir of NiV, commonly contaminate raw sap with saliva by licking date palm’s sap producing surface. We evaluated four types of physical barriers that may prevent bats from contacting sap. Methods During 2009, we used a crossover design and randomly selected 20 date palm sap producing trees and observed each tree for 2 nights: one night with a bamboo skirt intervention applied and one night without the intervention. During 2010, we selected 120 trees and randomly assigned four types of interventions to 15 trees each: bamboo, dhoincha (local plant), jute stick and polythene skirts covering the shaved part, sap stream, tap and collection pot. We enrolled the remaining 60 trees as controls. We used motion sensor activated infrared cameras to examine bat contact with sap. Results During 2009 bats contacted date palm sap in 85% of observation nights when no intervention was used compared with 35% of nights when the intervention was used [p<0.001]. Bats were able to contact the sap when the skirt did not entirely cover the sap producing surface. Therefore, in 2010 we requested the sap harvesters to use larger skirts. During 2010 bats contacted date palm sap [2% vs. 83%, p<0.001] less frequently in trees protected with skirts compared to control trees. No bats contacted sap in trees with bamboo (p<0.001 compared to control), dhoincha skirt (p<0.001) or polythene covering (p<0.001), but bats did contact sap during one night (7%) with the jute stick skirt (p<0.001). Conclusion Bamboo, dhoincha, jute stick and polythene skirts covering the sap producing areas of a tree effectively prevented bat-sap contact. Community interventions should promote applying these skirts to prevent occasional Nipah spillovers to human. PMID:22905160

Low-speed aerodynamic characteristics of a twin-engine general aviation configuration with aft-fuselage-mounted pusher propellers

NASA Technical Reports Server (NTRS)

Dunham, Dana Morris; Gentry, Garl L., Jr.; Manuel, Gregory S.; Applin, Zachary T.; Quinto, P. Frank

1987-01-01

An investigation was conducted to determine the aerodynamic characteristics of an advanced turboprop aircraft model with aft-pylon-mounted pusher propellers. Tests were conducted through an angle-of-attack range of -8 to 28 degrees, and an angle-of-sideslip range of -20 to 20 degrees at free-stream conditions corresponding to Reynolds numbers of 0.55 to 2.14 x 10 to the 6th power based on mean aerodynamic chord. Test results show that for the unpowered configurations the maximum lift coefficients for the cruise, takeoff, and landing configurations are 1.45, 1.90, and 2.10, respectively. Nacelle installation results in a drag coefficient increase of 0.01. Increasing propeller thrust results in a significant increase in lift for angles of attack above stall and improves the longitudinal stability. The cruise configuration remains longitudinally stable to an angle of attack 5 degrees beyond the stall angle, the takeoff configuration is stable 4 degrees beyond stall angle, and the landing configuration is stable 3 degrees beyond stall angle. The predominant effect of symmetric thrust on the lateral-directional aerodynamic characteristics is in the post-stall region, where additional rudder control is available with power on.