4. VIEW OF BOOSTER STATION 2, FACING NORTHWEST Nevada ...

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

4. VIEW OF BOOSTER STATION 2, FACING NORTHWEST - Nevada Test Site, Frenchman Flat Test Facility, Well Five Booster Stations, Intersection of 5-03 Road & Short Pole Line Road, Area 5, Frenchman Flat, Mercury, Nye County, NV

5. VIEW OF BOOSTER STATION 2, FACING SOUTHEAST Nevada ...

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

5. VIEW OF BOOSTER STATION 2, FACING SOUTHEAST - Nevada Test Site, Frenchman Flat Test Facility, Well Five Booster Stations, Intersection of 5-03 Road & Short Pole Line Road, Area 5, Frenchman Flat, Mercury, Nye County, NV

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.

9. VIEW OF BOOSTER STATION 3 INTERIOR, FACING NORTHEAST ...

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

9. VIEW OF BOOSTER STATION 3 INTERIOR, FACING NORTHEAST - Nevada Test Site, Frenchman Flat Test Facility, Well Five Booster Stations, Intersection of 5-03 Road & Short Pole Line Road, Area 5, Frenchman Flat, Mercury, Nye County, NV

6. VIEW OF BOOSTER STATION 2 INTERIOR, FACING WEST ...

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

6. VIEW OF BOOSTER STATION 2 INTERIOR, FACING WEST - Nevada Test Site, Frenchman Flat Test Facility, Well Five Booster Stations, Intersection of 5-03 Road & Short Pole Line Road, Area 5, Frenchman Flat, Mercury, Nye County, NV

12. VIEW OF BOOSTER STATION 4 INTERIOR, FACING SOUTHWEST ...

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

12. VIEW OF BOOSTER STATION 4 INTERIOR, FACING SOUTHWEST - Nevada Test Site, Frenchman Flat Test Facility, Well Five Booster Stations, Intersection of 5-03 Road & Short Pole Line Road, Area 5, Frenchman Flat, Mercury, Nye County, NV

3. VIEW OF BOOSTER STATION 1 INTERIOR, FACING EAST ...

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

3. VIEW OF BOOSTER STATION 1 INTERIOR, FACING EAST - Nevada Test Site, Frenchman Flat Test Facility, Well Five Booster Stations, Intersection of 5-03 Road & Short Pole Line Road, Area 5, Frenchman Flat, Mercury, Nye County, NV

Aerodynamic characteristics of a 142-inch diameter solid rocket booster, configuration 139 (SA2FA/SA2FB)

NASA Technical Reports Server (NTRS)

Radford, W. D.; Johnson, J. D.

1974-01-01

Tests of a 2.112 percent scale model of the space shuttle solid rocket booster model were conducted in a transonic pressure tunnel. Tests were conducted at Mach numbers ranging from 0.4 to 1.2, angles of attack from minus one degree to plus 181 degrees, and Reynolds numbers from 0.6 million to 6.1 million per foot. The model configurations investigated were as follows: (1) solid rocket booster without external protuberances, (2) solid rocket booster with an electrical tunnel and a solid rocket booster/external tank thrust attachment structure, and (3) solid rocket booster with two body strakes.

13. VIEW OF BOOSTER STATION 4 CHLORINATOR INTERIOR, FACING NORTH ...

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

13. VIEW OF BOOSTER STATION 4 CHLORINATOR INTERIOR, FACING NORTH - Nevada Test Site, Frenchman Flat Test Facility, Well Five Booster Stations, Intersection of 5-03 Road & Short Pole Line Road, Area 5, Frenchman Flat, Mercury, Nye County, NV

Aerodynamic stability and control characteristics of TBC shuttle booster AR-11981-3

NASA Technical Reports Server (NTRS)

Phelps, E. R.; Watts, L. L.; Ainsworth, R. W.

1972-01-01

A scale model of the Boeing Company space shuttle booster configuration 3 was tested in the MSFC 14-inch trisonic wind tunnel. This test was proposed to fill-in the original test run schedule as well as to investigate the aerodynamic stability and control characteristics of the booster with three wing configurations not previously tested. The configurations tested included: (1) a cylindrical booster body with an axisymmetric nose, (2) clipped delta canards that had variable incidence from 0 deg to -60 deg, (3) different aft body mounted wing configurations, (4) two vertical fin configurations, and (5) a Grumman G-3 orbiter configuration. Tests were conducted over a Mach range from 0.6 to 5.0.

Investigation of the McDonnell-Douglas orbiter and booster shuttle models in proximity at Mach numbers 2.0 to 6.0. Volume 7: Proximity data at Mach 4 and 6, interference free and launch vehicle data

NASA Technical Reports Server (NTRS)

Trimmer, L. L.; Love, D. A.; Decker, J. P.; Blackwell, K. L.; Strike, W. T.; Rampy, J. M.

1972-01-01

Aerodynamic data obtained from a space shuttle abort stage separation wind tunnel test are presented. The .00556 scale models of the orbiter and booster configuration were tested in close proximity using dual balances during the time period of April 21 to April 27 1971. Data were obtained for both booster and orbiter over an angle of attack range from -10 to 10 deg for zero degree sideslip angle. The models were tested at several relative incidence angles and separation distances and power conditions. Plug nozzles utilizing air were used to simulate booster and orbiter plumes at various altitudes along a nominal ascent trajectory. Powered conditions were 100, 50, 25 and 0 percent of full power for the orbiter and 100, 50 and 0 percent of full power for the booster. Pitch control effectiveness data were obtained for both booster and orbiter with power on and off. In addition, launch vehicle data with and without booster power were obtained utilizing a single balance in the booster model. Data were also obtained with the booster canard off in close proximity and for the launch configuration.

Evaluation of Safe Kids Week 2004: age 4 to 9? It's booster seat time!

PubMed

Howard, A; Beben, N; Rothman, L; Fiissel, D; MacArthur, C

2006-10-01

To assess the effectiveness of a national one week media campaign promoting booster seat use. Pre-test, post-test design based on nationally representative random digit dialing telephone survey, with control for exposure to campaign. Canada. Parents of children aged 4-9 years. During a one week campaign in May 2004, information on booster seat use was distributed via a national media campaign, retail stores, medical clinics, and community events. Information included pamphlets with guidelines for booster seat use, as well as a growth chart (designed by Safe Kids Canada) to assist parents in determining if their child should be using a booster seat. Assessing seat belt fit was described in detail on the growth chart. Knowledge, attitudes, and self-reported behaviors regarding booster seat use. Respondents in the group exposed to the campaign were twice as likely to report using a booster seat with lap and shoulder belt for their child (47%), compared to those in the pre-test (24%) and the unexposed (23%) groups (p<0.001). However, only small differences in general knowledge regarding booster seat use were found between the groups. A one week national media campaign substantially increased self-reported use of booster seats. Parents did not remember details of the campaign content, but did remember implications for their own child.

Standardization and Prevalence of the Booster Phenomenon: Evaluation Using a Two-Step Skin Test with 43 kDa Glycoprotein in Individuals from an Endemic Region of Paracoccidioidomycosis.

PubMed

Marques, Ana Paula C; Oliveira, Sandra Maria V L; Rezende, Grazielli R; Melo, Dayane A; Fernandes-Fitts, Sonia M; Pontes, Elenir Rose J C; Bonecini-Almeida, Maria da Glória; Camargo, Zoilo P; Mendes, Rinaldo P; Paniago, Anamaria M M

2017-10-01

We estimated the occurrence rate of the booster phenomenon by using an intradermal test with 43 kDa glycoprotein in an endemic area of paracoccidioidomycosis in the central-west region of Brazil. Individuals who had a negative result on a survey performed by using an intradermal test with 43 kDa glycoprotein in an endemic area of paracoccidioidomycosis underwent a second intradermal test after 10-15 days to determine the presence or absence of the booster phenomenon. Statistical analyses were performed using the Chi-square test, Chi-square for linear trend test, Student's t test, and binomial test; p < 0.05 was considered significant. For the first time, we reported the occurrence of the booster phenomenon to an intradermal reaction caused by 43 kDa glycoprotein at a rate of 5.8-8.4%, depending on the test's cutoff point. This suggests that a cutoff point should be considered for the booster phenomenon in intradermal tests with 43 kDa glycoprotein: a difference of 6-7 mm between readings according to the first and second tests, depending on the purpose of the evaluation. The results indicate that the prevalence of paracoccidioidal infection in endemic areas is underestimated, as the booster phenomenon has not been considered in epidemiological surveys for this infection.

Servo control booster system for minimizing following error

DOEpatents

Wise, W.L.

1979-07-26

A closed-loop feedback-controlled servo system is disclosed which reduces command-to-response error to the system's position feedback resolution least increment, ..delta..S/sub R/, on a continuous real-time basis, for all operational times of consequence and for all operating speeds. The servo system employs a second position feedback control loop on a by exception basis, when the command-to-response error greater than or equal to ..delta..S/sub R/, to produce precise position correction signals. When the command-to-response error is less than ..delta..S/sub R/, control automatically reverts to conventional control means as the second position feedback control loop is disconnected, becoming transparent to conventional servo control means. By operating the second unique position feedback control loop used herein at the appropriate clocking rate, command-to-response error may be reduced to the position feedback resolution least increment. The present system may be utilized in combination with a tachometer loop for increased stability.

Solid rocket booster thermal protection system materials development. [space shuttle boosters

NASA Technical Reports Server (NTRS)

Dean, W. G.

1978-01-01

A complete run log of all tests conducted in the NASA-MSFC hot gas test facility during the development of materials for the space shuttle solid rocket booster thermal protection system are presented. Lists of technical reports and drawings generated under the contract are included.

Space shuttle phase B wind tunnel model and test information. Volume 1: Booster configuration

NASA Technical Reports Server (NTRS)

Glynn, J. L.; Poucher, D. E.

1988-01-01

Archived wind tunnel test data are available for flyback booster or other alternative recoverable configurations as well as reusable orbiters studied during initial development (Phase B) of the Space Shuttle. Considerable wind tunnel data was acquired by the competing contractors and the NASA Centers for an extensive variety of configurations with an array of wing and body planforms. All contractor and NASA wind tunnel test data acquired in the Phase B development have been compiled into a database and are available for application to current winged flyback or recoverable booster aerodynamic studies. The Space Shuttle Phase B Wind Tunnel Database is structured by vehicle component and configuration type. Basic components include the booster, the orbiter, and the launch vehicle. Booster configuration types include straight and delta wings, canard, cylindrical, retroglide and twin body. Orbiter configuration types include straight and delta wings, lifting body, drop tanks and double delta wings. Launch configurations include booster and orbiter components in various stacked and tandem combinations. This is Volume 1 (Part 2) of the report -- Booster Configuration.

Space shuttle phase B wind tunnel model and test information. Volume 1: Booster configuration

NASA Technical Reports Server (NTRS)

Glynn, J. L.; Poucher, D. E.

1988-01-01

Archived wind tunnel test data are available for flyback booster or other alternative recoverable configurations as well as reusable orbiters studied during initial development (Phase B) of the Space Shuttle. Considerable wind tunnel data was acquired by the competing contractors and the NASA Centers for an extensive variety of configurations with an array of wing and body planforms. All contractor and NASA wind tunnel test data acquired in the Phase B development have been compiled into a database and are available for application to current winged flyback or recoverable booster aerodynamic studies. The Space Shuttle Phase B Wind Tunnel Database is structured by vehicle component and configuration type. Basic components include the booster, the orbiter and the launch vehicle. Booster configuration types include straight and delta wings, canard, cylindrical, retroglide and twin body. Orbiter configuration types include straight and delta wings, lifting body, drop tanks, and double delta wings. Launch configurations include booster and orbiter components in various stacked and tandem combinations. This is Volume 1 (Part 1) of the report -- Booster Configuration.

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.

Evaluation of Safe Kids Week 2004: Age 4 to 9? It's Booster Seat Time!

PubMed Central

Howard, A; Beben, N; Rothman, L; Fiissel, D; MacArthur, C

2006-01-01

Objective To assess the effectiveness of a national one week media campaign promoting booster seat use. Design Pre‐test, post‐test design based on nationally representative random digit dialing telephone survey, with control for exposure to campaign. Setting Canada. Subjects Parents of children aged 4–9 years. Interventions During a one week campaign in May 2004, information on booster seat use was distributed via a national media campaign, retail stores, medical clinics, and community events. Information included pamphlets with guidelines for booster seat use, as well as a growth chart (designed by Safe Kids Canada) to assist parents in determining if their child should be using a booster seat. Assessing seat belt fit was described in detail on the growth chart. Main outcome measures Knowledge, attitudes, and self‐reported behaviors regarding booster seat use. Results Respondents in the group exposed to the campaign were twice as likely to report using a booster seat with lap and shoulder belt for their child (47%), compared to those in the pre‐test (24%) and the unexposed (23%) groups (p<0.001). However, only small differences in general knowledge regarding booster seat use were found between the groups. Conclusions A one week national media campaign substantially increased self‐reported use of booster seats. Parents did not remember details of the campaign content, but did remember implications for their own child. PMID:17018673

Space shuttle: High angle of attack transition and low angle of attack launch phase aerodynamic stability and control of GD/C B-18E-2, B-18E-3 delta wing booster, and launch configuration of MSC-040A orbiter and twin pressure fed boosters

NASA Technical Reports Server (NTRS)

Debevoise, J. M.; Mcginnis, R. F.

1972-01-01

The test was a conventional stability and control test except for two aspects. One was the very high angles of attack at which the delta wing configurations were tested (up to 60 degrees) at Mach numbers of 3 and 4.96. The other was the installation of the orbiter and twin boosters in a manner that caused the support system to induce normal forces and side forces on the aft portion of the boosters at all Mach numbers; i.e., the support and the booster bodies were close together, side by side.

Design and prototype tests of a large-aperture 37-53 MHz ferrite-tuned booster synchrotron cavity

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

Mark S. Champion et al.

The Booster synchrotron at Fermilab employs eighteen 37-53 MHz ferrite-tuned double-gap coaxial radiofrequency cavities for acceleration of protons from 400 MeV to 8 GeV. The cavities have an aperture of 2.25 inches and operate at 55 kV per cavity. Future high duty factor operation of the Booster will be problematic due to unavoidable beam loss at the cavities resulting in excessive activation. The power amplifiers, high maintenance items, are mounted directly to the cavities in the tunnel. A proposed replacement for the Booster, the Proton Driver, will utilize the Booster radiofrequency cavities and requires not only a larger aperture, butmore » also higher voltage. A research and development program is underway at Fermilab to modify the Booster cavities to provide a 5-inch aperture and a 20% voltage increase. A prototype has been constructed and high power tests have bee completed. The cavity design and test results is presented.« less

Performance evaluation of Space Shuttle SRB parachutes from air drop and scaled model wind tunnel tests. [Solid Rocket Booster recovery system

NASA Technical Reports Server (NTRS)

Moog, R. D.; Bacchus, D. L.; Utreja, L. R.

1979-01-01

The aerodynamic performance characteristics have been determined for the Space Shuttle Solid Rocket Booster drogue, main, and pilot parachutes. The performance evaluation on the 20-degree conical ribbon parachutes is based primarily on air drop tests of full scale prototype parachutes. In addition, parametric wind tunnel tests were performed and used in parachute configuration development and preliminary performance assessments. The wind tunnel test data are compared to the drop test results and both sets of data are used to determine the predicted performance of the Solid Rocket Booster flight parachutes. Data from other drop tests of large ribbon parachutes are also compared with the Solid Rocket Booster parachute performance characteristics. Parameters assessed include full open terminal drag coefficients, reefed drag area, opening characteristics, clustering effects, and forebody interference.

KENNEDY SPACE CENTER, FLA. - Seen from below and through a solid rocket booster segment mockup, Jeff Thon, an SRB mechanic with United Space Alliance, tests the feasibility of a vertical solid rocket booster propellant grain inspection technique. The inspection of segments is required as part of safety analysis.

NASA Image and Video Library

2003-09-11

KENNEDY SPACE CENTER, FLA. - Seen from below and through a solid rocket booster segment mockup, Jeff Thon, an SRB mechanic with United Space Alliance, tests the feasibility of a vertical solid rocket booster propellant grain inspection technique. The inspection of segments is required as part of safety analysis.

Summary of Booster Development and Qualification Report

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

Francois, Elizabeth G.; Harry, Herbert H.; Hartline, Ernest L.

2012-06-21

This report outlines booster development work done at Los Alamos National Laboratory from 2007 to present. The booster is a critical link in the initiation train of explosive assemblies, from complex devices like nuclear weapons to conventional munitions. The booster bridges the gap from a small, relatively sensitive detonator to an insensitive, but massive, main charge. The movement throughout the explosives development community is to use more and more insensitive explosive components. With that, more energy is needed out of the booster. It has to initiate reliably, promptly, powerfully and safely. This report is divided into four sections. The firstmore » provides a summary of a collaborative effort between LANL, LLNL, and AWE to identify candidate materials and uniformly develop a testing plan for new boosters. Important parameters and the tests required to measure them were defined. The nature of the collaboration and the specific goals of the participating partners has changed over time, but the booster development plan stands on its own merit as a complete description of the test protocol necessary to compare and qualify booster materials, and is discussed in its entirety in this report. The second section describes a project, which began in 2009 with the Department of Defense to develop replacement booster formulations for PBXN-7. Replacement of PBXN-7 was necessary because it contained Triaminotrinitrobenzene (TATB), which was becoming unavailable to the DoD and because it contained Cyclotrimethylenetrinitramine (RDX), which was sensitive and toxic. A LANL-developed explosive, Diaminoazoxyfurazan (DAAF), was an important candidate. This project required any replacement formulation be a drop-in replacement in existing munitions. This project was timely, in that it made use of the collaborative booster development project, and had the additional constraint of matching shock sensitivity. Additionally it needed to be a safety improvement, and a performance improvement, especially at cold temperatures. The requirements of this project necessitated novel test development and a different approach to ranking booster qualities. Results of this project have been documented to the DoD and the relevant portions are included within. The third section of this booster report outlines testing related to main charge initiation merit. Initiability can be evaluated by looking at critical diameter, run distance, and shock sensitivity. Once a booster is initiated, it needs to be powerful enough to initiate the main charge symmetrically and evenly. Main charge initiability is evaluated directly by observing detonation wave symmetry, curvature, and first break out over the surface of a charge. Furthermore it must be insensitive to accidents and insults, and safe and reliable across a range of temperatures. These effects, tests, and results will be discussed individually in the context of DAAF and other explosives similarly tested. The last section provides a conclusion and summary of our experimental work and recommendations for the path forward. References and additional supporting documentation and results are provided in the appendices at the end of this report.« less

Saturn Apollo Program

NASA Image and Video Library

1960-01-01

The Saturn Project was approved on January 18, 1960 as a program of the highest national priority. The formal test program to prove out the clustered-booster concept was well underway at Redstone Arsenal. This photograph depicts a mockup of the Saturn booster (S-I stage) being transported to the Army Ballistic Missile Agency (ABMA) test stand, to check mating of the booster and stand and servicing methods.

Persistence of antibodies six years after booster vaccination with inactivated vaccine against Japanese encephalitis.

PubMed

Paulke-Korinek, Maria; Kollaritsch, Herwig; Kundi, Michael; Zwazl, Ines; Seidl-Friedrich, Claudia; Jelinek, Tomas

2015-07-09

Japanese Encephalitis (JE) virus occurs in wide regions of Asia with over 3 billion people living in areas at risk for JE. An estimated 68,000 clinical cases of JE occur every year, and vaccination is the most effective prophylactic measure. One internationally licensed vaccine containing the inactivated JE virus strain SA14-14-2 is Ixiaro (Valneva, Austria). According to recommendations, basic immunization consists of vaccinations on day 0, day 28, and a booster dose 12-24 months later. Protection in terms of neutralizing antibody titers has been assessed up to 12 months after the third dose of the vaccine. The current investigation was designed to evaluate antibody decline over time and to predict long-term duration of seroprotection after a booster dose. In a preceding trial, volunteers received basic immunization (day 0, day 28) and one booster dose against JE 15 months later. A follow up blood draw 6 years following their booster dose was carried out in 67 subjects. For antibody testing, a 50% plaque reduction neutralization test (PRNT50-test) was used. PRNT50 values of 10 and above are surrogate levels of protection according to WHO standards. Seventy-six months following the booster dose, 96% of the tested subjects had PRNT50 titers of 10 or higher. Geometric mean titer (GMT) was 148 (95% CI confidence interval: 107-207). Antibody titers were lower in volunteers 50 years of age and older. Vaccination history against other flaviviruses (yellow fever or tick borne encephalitis) did not significantly influence PRNT50 titers. A two-step log-linear decline model predicted protection against JE of approximately 14 years after the booster dose. Six years after a booster dose against JE, long-term protection could be demonstrated. According to our results, further booster doses should be scheduled 10 years following the first booster dose. Copyright © 2015 Elsevier Ltd. All rights reserved.

Blood Pressure Directed Booster Trainings Improve Intensive Care Unit Provider Retention of Excellent Cardiopulmonary Resuscitation Skills.

PubMed

Wolfe, Heather; Maltese, Matthew R; Niles, Dana E; Fischman, Elizabeth; Legkobitova, Veronika; Leffelman, Jessica; Berg, Robert A; Nadkarni, Vinay M; Sutton, Robert M

2015-11-01

Brief, intermittent cardiopulmonary resuscitation (CPR) training sessions, "Booster Trainings," improve CPR skill acquisition and short-term retention. The objective of this study was to incorporate arterial blood pressure (ABP) tracings into Booster Trainings to improve CPR skill retention. We hypothesized that ABP-directed CPR "Booster Trainings" would improve intensive care unit (ICU) provider 3-month retention of excellent CPR skills without need for interval retraining. A CPR manikin creating a realistic relationship between chest compression depth and ABP was used for training/testing. Thirty-six ICU providers were randomized to brief, bedside ABP-directed CPR manikin skill retrainings: (1) Booster Plus (ABP visible during training and testing) versus (2) Booster Alone (ABP visible only during training, not testing) versus (3) control (testing, no intervention). Subjects completed skill tests pretraining (baseline), immediately after training (acquisition), and then retention was assessed at 12 hours, 3 and 6 months. The primary outcome was retention of excellent CPR skills at 3 months. Excellent CPR was defined as systolic blood pressure of 100 mm Hg or higher and compression rate 100 to 120 per minute. Overall, 14 of 24 (58%) participants acquired excellent CPR skills after their initial training (Booster Plus 75% vs 50% Booster Alone, P = 0.21). Adjusted for age, ABP-trained providers were 5.2× more likely to perform excellent CPR after the initial training (95% confidence interval [95% CI], 1.3-21.2; P = 0.02), and to retain these skills at 12 hours (adjusted odds ratio, 4.4; 95% CI, 1.3-14.9; P = 0.018) and 3 months (adjusted odds ratio, 4.1; 95% CI, 1.2-13.9; P = 0.023) when compared to baseline performance. The ABP-directed CPR booster trainings improved ICU provider 3-month retention of excellent CPR skills without the need for interval retraining.

A new one-man submarine is tested as vehicle for solid rocket booster retrieval

NASA Technical Reports Server (NTRS)

2000-01-01

A mockup of a solid rocket booster nozzle is lowered into the waters of the Atlantic during a test of a new booster retrieval method. A one-man submarine known as DeepWorker 2000 is being tested on its ability to duplicate the sometimes hazardous job United Space Alliance (USA) divers perform to recover the expended boosters in the ocean after a launch. The boosters splash down in an impact area about 140 miles east of Jacksonville and after recovery are towed back to KSC for refurbishment by the specially rigged recovery ships. DeepWorker 2000 will be used in a demonstration during retrieval operations after the upcoming STS-101 launch. The submarine pilot will demonstrate capabilities to cut tangled parachute riser lines using a manipulator arm and attach a Diver Operator Plug to extract water and provide flotation for the booster. DeepWorker 2000 was built by Nuytco Research Ltd., North Vancouver, British Columbia. It is 8.25 feet long, 5.75 feet high, and weighs 3,800 pounds. USA is a prime contractor to NASA for the Space Shuttle program.

Feasibility demonstration of booster cross-over system for 3 1/2 inch SRB/MLP frangible nut system

NASA Technical Reports Server (NTRS)

1983-01-01

Recent testing of the SRB/MLP Frangible Nut System (SOS Part Number 114850-9/Boosters P/N 114848-3) at NASA indicated a need to reduce the function time between boosters (2) within a single frangible nut. These boosters are initiated separately by electrical impulse(s). Coupling the output of each detonator with an explosive cross-over would reduce the function time between boosters (independent of electrical impulse) while providing additional redundancy to the system. The objectives of this program were to: provide an explosive cross-over between boosters, reduce function time between boosters to less than one (1) millisecond within a given nut, reduce cost of boosters, be compatible with the existing frangible nut system, and meet requirements of USBI Spec's (nut 10SPC-0030, booster 10SPC-0031).

Space Launch System Booster Passes Major Ground Test

NASA Image and Video Library

2015-03-11

The largest, most powerful rocket booster ever built successfully fired up Wednesday for a major-milestone ground test in preparation for future missions to help propel NASA’s Space Launch System (SLS) rocket and Orion spacecraft to deep space destinations, including an asteroid and Mars. The booster fired for two minutes, the same amount of time it will fire when it lifts the SLS off the launch pad, and produced about 3.6 million pounds of thrust. The test was conducted at the Promontory, Utah test facility of commercial partner Orbital ATK.

Saturn Apollo Program

NASA Image and Video Library

1960-01-19

The Saturn Project was approved on January 18, 1960 as a program of the highest national priority. The formal test program, to prove out the clustered-booster concept, was well underway at Redstone Arsenal. This photograph depicts a mockup of the Saturn booster (S-I stage) being installed in the Army Ballistic Missile Agency (ABMA) test stand, on January 19, 1960, to check mating of the booster and stand and servicing methods.

Saturn Apollo Program

NASA Image and Video Library

1960-01-19

The Saturn Project was approved on January 18, 1960, as a program of the highest national priority. The formal test program to prove out the clustered-booster concept was well underway at Redstone Arsenal. This photograph depicts a mockup of the Saturn booster (S-I stage) being installed in the Army Ballistic Missile Agency (ABMA) test stand, on January 19, 1960, to check mating of the booster and stand and servicing methods.

Hybrid propulsion technology program. Volume 2: Technology definition package

NASA Technical Reports Server (NTRS)

Jensen, Gordon E.; Holzman, Allen L.; Leisch, Steven O.; Keilbach, Joseph; Parsley, Randy; Humphrey, John

1989-01-01

A concept design study was performed to configure two sizes of hybrid boosters; one which duplicates the advanced shuttle rocket motor vacuum thrust time curve and a smaller, quarter thrust level booster. Two sizes of hybrid boosters were configured for either pump-fed or pressure-fed oxygen feed systems. Performance analyses show improved payload capability relative to a solid propellant booster. Size optimization and fuel safety considerations resulted in a 4.57 m (180 inch) diameter large booster with an inert hydrocarbon fuel. The preferred diameter for the quarter thrust level booster is 2.53 m (96 inches). The demonstration plan would culminate with test firings of a 3.05 m (120 inch) diameter hybrid booster.

Field evaluation of a canine parvovirus vaccination program, using feline origin modified live virus vaccine.

PubMed

Gordon, J C; Rogers, W A

1982-06-15

Antibody titers measured by hemagglutination inhibition testing were determined in previously vaccinated dogs at the time of booster vaccination and 2 weeks later. All vaccines consisted of modified live panleukopenia virus. The booster injection was administered approximately 6 months after the initial parvovirus vaccination series was given. Fecal and serum specimens were collected immediately before and 2 weeks after administration of the booster vaccine for hemagglutination and hemagglutination inhibition testing, respectively. All dogs were privately owned and were from the Columbus, Ohio, area but were from environments with various exposure potentials to canine parvovirus. Results of hemagglutination (HA) testing on feces were negative in all dogs before and after booster vaccination. Therefore, these vaccinations did not interfere with interpretation of HA testing of feces. Results of serum hemagglutination inhibition (HI) testing indicated that 50% of the dogs had serum titers less than 1:80 prior to vaccination and that, of these dogs, 65.2% still had serum titers less than 1:80 2 weeks after the booster vaccination. Only 10.9% of all dogs had a marked increase in serum HI titer after the booster vaccination, indicating that overall serologic response to vaccination was poor. High HI titers (greater than or equal to 1:640) were associated with exposure to other dogs and cats in the neighborhood or to dogs suspected of having had parvovirus infection.

35. VIEW LOOKING NORTHWEST AT THE STATIC TEST TOWER. A ...

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

35. VIEW LOOKING NORTHWEST AT THE STATIC TEST TOWER. A 'DUMMY' SATURN I BOOSTER IS BEING HOISTED INTO THE TEST STAND TO TEST THE MATING OF THE BOOSTER AND THE TEST STAND. EARLY 1960, PHOTOGRAPHER UNKNOWN, MSFC PHOTO LAB. - Marshall Space Flight Center, Saturn Propulsion & Structural Test Facility, East Test Area, Huntsville, Madison County, AL

Space shuttle: Aerodynamic characteristics of a composite booster/040A orbiter launch configuration with fin and booster body configuration effect contribution

NASA Technical Reports Server (NTRS)

Ainsworth, R. W.; Johnson, J. C.; Watts, L. L.

1972-01-01

An investigation was made of the fin configuration and booster body configuration effects on a composite booster/040A orbiter launch configuration. Aerodynamic performance and stability characteristics in pitch and yaw were obtained. Configurations tested included two stepped cylindrical bodies of different lengths with a conical nose, four fin shapes of various sizes and aspect ratios mounted in different positions around the base of the bodies, two base flare angles and three 040A orbiter configurations. The orbiter variations included a tailless configuration and two tail sizes. A tailless booster launch configuration with deflected petals (expanded flare sectors) was also tested. The model scale was 0.003366. Data were converted to coefficient form in near real time, punched on cards, and tabulated. The cards used in conjunction with a Benson-Lehner plotter were used to provide plotted data. At the end of the test, tabulated input forms were completed for the SADSAC computer program to aid in publishing the final test data report.

Space shuttle phase B wind tunnel model and test information. Volume 3: Launch configuration

NASA Technical Reports Server (NTRS)

Glynn, J. L.; Poucher, D. E.

1988-01-01

Archived wind tunnel test data are available for flyback booster or other alternate recoverable configuration as well as reusable orbiters studied during initial development (Phase B) of the Space Shuttle, including contractor data for an extensive variety of configurations with an array of wing and body planforms. The test data have been compiled into a database and are available for application to current winged flyback or recoverable booster aerodynamic studies. The Space Shuttle Phase B Wind Tunnel Database is structured by vehicle component and configuration. Basic components include booster, orbiter, and launch vehicle. Booster configuration types include straight and delta wings, canard, cylindrical, retroglide and twin body. Orbiter configurations include straight and delta wings, lifting body, drop tanks and double delta wings. Launch configurations include booster and orbiter components in various stacked and tandem combinations. The digital database consists of 220 files containing basic tunnel data. Database structure is documented in a series of reports which include configuration sketches for the various planforms tested. This is Volume 3 -- launch configurations.

Space shuttle phase B wind tunnel model and test information. Volume 2: Orbiter configuration

NASA Technical Reports Server (NTRS)

Glynn, J. L.; Poucher, D. E.

1988-01-01

Archived wind tunnel test data are available for flyback booster or other alternative recoverable configurations as well as reusable orbiters studied during initial development (Phase B) of the Space Shuttle. Considerable wind tunnel data was acquired by the competing contractors and the NASA centers for an extensive variety of configurations with an array of wing and body planforms. All contractor and NASA wind tunnel test data acquired in the Phase B development have been compiled into a data base and are available for applying to current winged flyback or recoverable booster aerodynamic studies. The Space Shuttle Phase B Wind Tunnel Data Base is structured by vehicle component and configuration type. Basic components include the booster, the orbiter, and the launch vehicle. Booster configuration types include straight and delta wings, canard, cylindrical, retro-glide and twin body. Orbiter configuration types include straight and delta wings, lifting body, drop tanks, and double delta wings. Launch configuration types include booster and orbiter components in various stacked and tandem combinations.

Space shuttle abort separation pressure investigation. Volume 1, Part A: Booster data at Mach 5

NASA Technical Reports Server (NTRS)

Trimmer, L. L.; Love, D. A.; Rampy, J. M.; Decker, J. P.; Blackwell, K. L.; Strike, W. T.

1972-01-01

Pressure data obtained from a joint Langley Research Center (LaRC)/Marshall Space Flight Center (MSFC) Space Shuttle about stage separation wind tunnel test are presented. The .00556 scale models of the McDonnell-Douglas orbiter and booster configurations were tested in proximity in Tunnel A of the Von Karman Facility (VKF), Arnold Engineering Development Center (AEDC). Mach numbers were 5.0, 3.0, and 2.0 and nominal Reynolds numbers were 1.09, 1.60, and 1.74 million per foot, respectively. Pressure data were obtained for the booster upper surface and orbiter lower surface at angles of attack of -10 deg, -5, 0, 5, and 10 deg for zero degrees sideslip. The models were tested at incidence angles of 0 and 5 deg for several separation distances and power conditions. Plug nozzles utilizing air were used to simulate booster and orbiter plumes at various altitudes along a nominal ascent trajectory. Powered conditions were 100, 50, and 0 percent of full power for the orbiter and 100, 50 and 0 percent of full power for the booster. Data were also obtained with the booster canard off in close proximity.

Saturn Apollo Program

NASA Image and Video Library

1960-01-01

The Saturn Project was approved on January 18, 1960 as a program of the highest national priority. The formal test program to prove out the clustered-booster concept was well underway at Redstone Arsenal. This photograph depicts a mockup of the Saturn booster (S-I stage) being placed on a transporter and later being installed in the Army Ballistic Missile Agency (ABMA) test stand, on January 19, 1960, to check mating of the booster and stand and servicing methods.

A central solar domestic hot water system - Performance and economic analysis

NASA Astrophysics Data System (ADS)

Wolf, D.; Tamir, A.; Kudish, A. I.

1980-02-01

A solar-assisted central hot water system was retrofitted onto one of the student dormitory complexes. The system consisted of twenty commercial solar collectors, of the pipe and plate type, and central hot water tank connected to two dormitory buildings. The system has two loops: (1) a solar loop, in which the heated water circulates between the collector panels and the central hot water tank, and (2) a consumer loop, where the solar-heated water circulates between the central hot water tank and the dormitory. The solar-heated water circulates through the individual electric hot water tanks which serve as individual hot water storage and booster units, and the mains water is introduced at the bottom of the central tank to replace consumed water. The description of the system, the design and its performance, together with an economic analysis, are presented.

Space Shuttle: Static pressure distribution on Chrysler Corporation Space Division SERV booster configuration

NASA Technical Reports Server (NTRS)

Price, E. A.; Hull, J. J.; Rawls, E. A.

1971-01-01

A dual purpose test was conducted in the propulsion wind tunnel (PWT) to evaluate the performance of an aerospike engine, in the presence of a booster, and obtain forebody and base pressure distributions on the booster in which it is installed. The test item was a 2.5 percent scaled replica of the SERV booster employing a 5 percent spike length aerospike engine installed in the base region of the model. Cold flow air was used to simulate engine jet operation. Two booster configurations were investigated, one on which reentry aerospike engine thermal protection doors were installed, and another where the doors were removed. The data presented are representative of the latter configuration for a Mach number range of 0 to 1.25 at angles of attack of 0 and 8 degrees and 0 degrees angle of sideslip.

Booster Test for Space Launch System Rocket

NASA Image and Video Library

2016-06-26

The test area where the second and final qualification motor (QM-2) test for the Space Launch System’s booster is seen Sunday, June 26, 2016, at Orbital ATK Propulsion Systems test facilities in Promontory, Utah. The test is scheduled for Tuesday, June 28 at 10:05 a.m. EDT (8:05 a.m. MDT). Photo Credit: (NASA/Bill Ingalls)

Pegasus Rocket Booster Being Prepared for X-43A/Hyper-X Flight Test

NASA Image and Video Library

1999-08-25

Technicians prepare a Pegasus rocket booster for flight tests with the X-43A "Hypersonic Experimental Vehicle," or "Hyper-X." The X-43A, which will be attached to the Pegasus booster and drop launched from NASA's B-52 mothership, was developed to research dual-mode ramjet/scramjet propulsion system at speeds from Mach 7 up to Mach 10 (7 to 10 times the speed of sound, which varies with temperature and altitude).

The Unitary Plan Wind Tunnel(UPWT) Test 1891 Space Launch System

NASA Image and Video Library

2014-10-15

Stage Separation Test of the Space Launch System(SLS) in the Langley Unitary Plan Wind Tunnel (UPWT). The model used High Pressure air blown through the solid rocket boosters. (SRB) to simulate the booster separation motors (BSM) firing.

The Unitary Plan Wind Tunnel(UPWT) Test 1891 Space Launch System

NASA Image and Video Library

2014-10-14

Stage Separation Test of the Space Launch System(SLS) in the Langley Unitary Plan Wind Tunnel (UPWT). The model used High Pressure air blown through the solid rocket boosters. (SRB) to simulate the booster separation motors (BSM) firing.

Longitudinal Stability and Control Characteristics of a B-29 Airplane with a Booster Incorporated in the Elevator Control System to Provide Various Stick-Force and Control-Rate Characteristics

NASA Technical Reports Server (NTRS)

Mathews, Charles W.; Talmage, Donald B.; Whitten, James B.

1948-01-01

The longitudinal stability and control characteristics of a B-29 airplane have been measured with a booster incorporated in the elevator control system. Tests were made to determine the effects on the handling qualities of the test airplane of variations in pilots control-force gradients as well as the effects of variations in the maximum rate of control motion supplied by the booster system.

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.

Booster Test for Space Launch System Rocket

NASA Image and Video Library

2016-06-26

The test area where the second and final qualification motor (QM-2) test for the Space Launch System’s booster is seen through the window of a camera bunker, Sunday, June 26, 2016, at Orbital ATK Propulsion Systems test facilities in Promontory, Utah. The test is scheduled for Tuesday, June 28 at 10:05 a.m. EDT (8:05 a.m. MDT). Photo Credit: (NASA/Bill Ingalls)

KENNEDY SPACE CENTER, FLA. - Mobile Launcher Platform (MLP) number 3 and a set of twin solid rocket boosters, atop the crawler-transporter, inch along the crawlerway in support of the second engineering analysis vibration test on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A (framed between the boosters), and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

NASA Image and Video Library

2003-11-21

KENNEDY SPACE CENTER, FLA. - Mobile Launcher Platform (MLP) number 3 and a set of twin solid rocket boosters, atop the crawler-transporter, inch along the crawlerway in support of the second engineering analysis vibration test on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A (framed between the boosters), and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

Responses of the Q6/Q6s ATD Positioned in Booster Seats in the Far-Side Seat Location of Side Impact Passenger Car and Sled Tests.

PubMed

Tylko, Suzanne; Bohman, Katarina; Bussières, Alain

2015-11-01

Passenger car side impact crash tests and sled tests were conducted to investigate the influence of booster seats, near-side occupant characteristics and vehicle interiors on the responses of the Q6/Q6s child ATD positioned in the rear, far-side seating location. Data from nine side impact sled tests simulating a EuroNCAP AEMD barrier test were analyzed with data obtained from 44 side impact crash tests. The crash tests included: FMVSS 214 and IIHS MDB, moving car-to-stationary car and moving car-to-moving car. A Q6 or prototype Q6s ATD was seated on the far-side, using a variety of low and high back booster seats. Head and chest responses were recorded and ATD motions were tracked with high-speed videos. The vehicle lateral accelerations resulting from MDB tests were characterized by a much earlier and more rapid rise to peak than in tests where the bullet was another car. The near-side seating position was occupied by a Hybrid III 10-year-old ATD in the sled tests, and a rear or front facing child restraint or a 5th percentile side impact ATD in the crash tests. Head impacts occurred more frequently in vehicles where a forward facing child restraint was present behind the driver seat for both the low and high back booster seats. Pretensioners were found to reduce lateral head displacements in all sled test configurations but the greatest reduction in lateral excursion was obtained with a high back booster seat secured with LATCH and tested in combination with pretensioners.

Space shuttle: Heat transfer rate measurements on Convair booster (B-15B-2) and North American Rockwell orbiter (161B) at nominal Mach number of 8

NASA Technical Reports Server (NTRS)

Warmbrod, J. D.; Martindale, W. R.; Matthews, R. K.

1971-01-01

Plotted and tabulated data from the thin-skin thermocouple phase of an experimental test program are presented. These data are representative of three events of simulated flight and are described as booster-orbiter ascent heating data, booster reentry heating data, and orbiter reentry heating data. The test was conducted in a 50-inch hypersonic tunnel b at a nominal Mach number of 8 and free-stream Reynolds number range of 700,000 to 3,700,000 per foot. The model employed was a 0.009 scale replica of the Convair B-15B-2 booster and North American Rockwell 161B orbiter.

Effect on Longitudinal Stability and Control Characteristics of a Boeing B-29 Airplane of Variations in Stick-Force and Control-Rate Characteristics Obtained Through Use of a Booster in the Elevator-Control System

NASA Technical Reports Server (NTRS)

Mathews, Charles W; Talmage, Donald B; Whitten, James B

1952-01-01

A longitudinal stability and control characteristics of a Boeing B-29 airplane have been measured with a booster incorporated in the elevator-control system. Tests were made to determine the effects on the handling qualities of the test airplane of variations in the pilot's control-force gradients as well as the effects of variations in the maximum rate of control motion supplied by the booster. The results of the control-rate investigation indicate that large airplanes may have satisfactory handling qualities with the booster adjusted to give much lower rates of control motion than those normally used by pilots.

Space Shuttle Projects

NASA Image and Video Library

1977-12-01

The solid rocket booster (SRB) structural test article is being installed in the Solid Rocket Booster Test Facility for the structural and load verification test at the Marshall Space Flight Center (MSFC). The Shuttle's two SRB's are the largest solids ever built and the first designed for refurbishment and reuse. Standing nearly 150-feet high, the twin boosters provide the majority of thrust for the first two minutes of flight, about 5.8 million pounds, augmenting the Shuttle's main propulsion system during liftoff. The major design drivers for the solid rocket motors (SRM's) were high thrust and reuse. The desired thrust was achieved by using state-of-the-art solid propellant and by using a long cylindrical motor with a specific core design that allows the propellant to burn in a carefully controlled marner. At burnout, the boosters separate from the external tank and drop by parachute to the ocean for recovery and subsequent refurbishment.

Solid Rocket Booster Structural Test Article

NASA Technical Reports Server (NTRS)

1978-01-01

The structural test article to be used in the solid rocket booster (SRB) structural and load verification tests is being assembled in a high bay building of the Marshall Space Flight Center (MSFC). The Shuttle's two SRB's are the largest solids ever built and the first designed for refurbishment and reuse. Standing nearly 150-feet high, the twin boosters provide the majority of thrust for the first two minutes of flight, about 5.8 million pounds, augmenting the Shuttle's main propulsion system during liftoff. The major design drivers for the solid rocket motors (SRM's) were high thrust and reuse. The desired thrust was achieved by using state-of-the-art solid propellant and by using a long cylindrical motor with a specific core design that allows the propellant to burn in a carefully controlled marner. At burnout, the boosters separate from the external tank and drop by parachute to the ocean for recovery and subsequent refurbishment.

The aerodynamic challenges of SRB recovery

NASA Technical Reports Server (NTRS)

Bacchus, D. L.; Kross, D. A.; Moog, R. D.

1985-01-01

Recovery and reuse of the Space Shuttle solid rocket boosters was baselined to support the primary goal to develop a low cost space transportation system. The recovery system required for the 170,000-lb boosters was for the largest and heaviest object yet to be retrieved from exoatmospheric conditions. State-of-the-art design procedures were ground-ruled and development testing minimized to produce both a reliable and cost effective system. The ability to utilize the inherent drag of the boosters during the initial phase of reentry was a key factor in minimizing the parachute loads, size and weight. A wind tunnel test program was devised to enable the accurate prediction of booster aerodynamic characteristics. Concurrently, wind tunnel, rocket sled and air drop tests were performed to develop and verify the performance of the parachute decelerator subsystem. Aerodynamic problems encountered during the overall recovery system development and the respective solutions are emphasized.

Study of solid rocket motors for a space shuttle booster. Volume 3: Program acquisition planning

NASA Technical Reports Server (NTRS)

Vonderesch, A. H.

1972-01-01

Plans for conducting Phase C/D for a solid rocket motor booster vehicle are presented. Methods for conducting this program with details of scheduling, testing, and program management and control are included. The requirements of the space shuttle program to deliver a minimum cost/maximum reliability booster vehicle are examined.

Space shuttle: Aerodynamic heating tests of the MDAC delta wing orbiter and canard booster

NASA Technical Reports Server (NTRS)

Andresen, T. L.

1972-01-01

Design of an efficient thermal protection system for the space shuttle orbiter and booster is discussed, based on knowledge of the thermal environment to be experienced by the vehicles in all flight phases. The complex configurations of these vehicles limit the level of confidence which can be associated with purely analytical thermal environment predictions. Tests were conducted during April and May 1971 using an orbiter and booster model at a 96-in. hypersonic shock tunnel. Both models were tested separately as well as together. A sufficiently large range in Reynolds number was covered so that laminar, transitional, and turbulent data could be obtained.

Optimizing protection for rear seat occupants : assessing booster performance with realistic belt geometry using the hybrid III 6YO ATD.

DOT National Transportation Integrated Search

2011-11-01

A series of sled tests was conducted to examine the performance of booster seats under belt geometries representing the range found in the rear seats of current vehicles. Twelve tests were performed with the standard 6YO Hybrid III ATD and 29 tests w...

Vibration, acoustic, and shock design and test criteria for components on the Solid Rocket Boosters (SRB), Lightweight External Tank (LWT), and Space Shuttle Main Engines (SSME)

NASA Technical Reports Server (NTRS)

1984-01-01

The vibration, acoustics, and shock design and test criteria for components and subassemblies on the space shuttle solid rocket booster (SRB), lightweight tank (LWT), and main engines (SSME) are presented. Specifications for transportation, handling, and acceptance testing are also provided.

Aerodynamic characterisation and trajectory simulations for the Ariane-5 booster recovery system

NASA Astrophysics Data System (ADS)

Meiboom, F. P.

One of the most critical aspects of the early phases of the development of the Ariane-5 booster recovery system was the determination of the behavior of the booster during its atmospheric reentry, since this behavior determines the start conditions for the parachute system elements. A combination of wind-tunnel tests (subsonic and supersonic) and analytical methods was applied to define the aerodynamic characteristics of the booster. This aerodynamic characterization in combination with information of the ascent trajectory, atmospheric properties and booster mass and inertia were used as input for the 6-DOF trajectory simulations of the vehicle. Uncertainties in aerodynamic properties and deviations in atmospheric and booster properties were incorporated to define the range of initial conditions for the parachute system, utilizing stochastic (Monte-Carlo) methods.

Booster Test for Space Launch System Rocket

NASA Image and Video Library

2016-06-26

The quench system arm and nozzle are seen at the test area where the second and final qualification motor (QM-2) test for the Space Launch System’s booster will take place, Sunday, June 26, 2016, at Orbital ATK Propulsion Systems test facilities in Promontory, Utah. The test is scheduled for Tuesday, June 28 at 10:05 a.m. EDT (8:05 a.m. MDT). Photo Credit: (NASA/Bill Ingalls)

Pegasus Rocket Booster Being Prepared for X-43A/Hyper-X Flight Test

NASA Image and Video Library

1999-08-25

A close-up view of the front end of a Pegasus rocket booster being prepared by technicians at the Dryden Flight Research Center for flight tests with the X-43A "Hypersonic Experimental Vehicle," or "Hyper-X." The X-43A, which will be attached to the Pegasus booster and drop launched from NASA's B-52 mothership, was developed to research dual-mode ramjet/scramjet propulsion system at speeds from Mach 7 up to Mach 10 (7 to 10 times the speed of sound, which varies with temperature and altitude).

Assessing the Impact of an Emotion Regulation Booster Program for Elementary School-Aged Children

ERIC Educational Resources Information Center

Hammond, Angela; Westhues, Anne; Hanbidge, Alice Schmidt

2009-01-01

The purpose of this study was to determine whether children who participated in a booster program 3 years after completing an emotion regulation program show a greater increase between pretest and post-test in the development of emotion regulation skills than children in a comparison group. A booster program was implemented as a pilot project with…

An analysis of booster tone noise using a time-linearized Navier-Stokes solver

NASA Astrophysics Data System (ADS)

Wukie, Nathan A.

This thesis details a computational investigation of tone noise generated from a booster(low-pressure compressor) in a fan test rig. The computational study consisted of sets of time-linearized Navier-Stokes simulations in the booster region to investigate the blade-wake interactions that act as the primary noise-generating mechanism for the booster blade-passing frequency and harmonics. An acoustic test database existed with data at several operating points for the fan test rig that was used to compare against the predicted noise data from the computational study. It is shown that the computational methodology is able to capture trends in sound power for the 1st and 2nd booster tones along the operating line for the rig. It is also shown that the computational study underpredicts one of the tones at low power and is not able to capture a peak in the data at the Cutback condition. Further investigation of this type is warranted to quantify the source of discrepancies between the computational and experimental data as the reflected transmisison of sound off the fan through the bypass duct was not accounted for in this study.

Effects on Longitudinal Stability and Control Characteristics of a B-29 Airplane of Variations in Stick-force and Control-rate Characteristics Obtained Through Use of a Booster in the Elevator-control System

NASA Technical Reports Server (NTRS)

Mathews, Charles W; Talmage, Donald B; Whitten, James B

1951-01-01

The longitudinal stability and control characteristics of a B-29 airplane have been measured with a control surface booster incorporated in the elevator-control system. The measurements were obtained with the booster operating to provide various control-force gradients and various maximum rates of control motion. Results are presented which show the effect of these booster parameters on the handling qualities of the test airplane.

Qualitative investigation of booster recovery in open sea

NASA Technical Reports Server (NTRS)

Beck, P. E.

1973-01-01

Limited tests were conducted using 1/27 scale model of a Titan 3C booster plus 1/32.9 and 1/15.6 scale models of a solid rocket booster case to establish some of the characteristics that will effect recovery operations in open seas. This preliminary effort was designed to provide additional background information for conceptual development of a waterborne recovery system for space shuttle boosters, pending initiation of comprehensive studies. The models were not instrumented; therefore, all data are qualitative (approximations) and are based on observations plus photographic coverage.

KENNEDY SPACE CENTER, FLA. - The crawler transporter slowly moves the Mobile Launcher Platform (MLP), carrying a set of twin solid rocket boosters, away from the Vehicle Assembly Building (VAB) in support of engineering analysis vibration tests on the crawler and MLP. On either side of the boosters on the horizon can be seen the two launch pads. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

NASA Image and Video Library

2003-11-17

KENNEDY SPACE CENTER, FLA. - The crawler transporter slowly moves the Mobile Launcher Platform (MLP), carrying a set of twin solid rocket boosters, away from the Vehicle Assembly Building (VAB) in support of engineering analysis vibration tests on the crawler and MLP. On either side of the boosters on the horizon can be seen the two launch pads. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

StarBooster Demonstrator Cluster Configuration Analysis/Verification Program

NASA Technical Reports Server (NTRS)

DeTurris, Dianne J.

2003-01-01

In order to study the flight dynamics of the cluster configuration of two first stage boosters and upper-stage, flight-testing of subsonic sub-scale models has been undertaken using two glideback boosters launched on a center upper-stage. Three high power rockets clustered together were built and flown to demonstrate vertical launch, separation and horizontal recovery of the boosters. Although the boosters fly to conventional aircraft landing, the centerstage comes down separately under its own parachute. The goal of the project has been to collect data during separation and flight for comparison with a six degree of freedom simulation. The configuration for the delta wing canard boosters comes from a design by Starcraft Boosters, Inc. The subscale rockets were constructed of foam covered in carbon or fiberglass and were launched with commercially available solid rocket motors. The first set of boosters built were 3-ft tall with a 4-ft tall centerstage, and two additional sets of boosters were made that were each over 5-ft tall with a 7.5 ft centerstage. The rocket cluster is launched vertically, then after motor bum out the boosters are separated and flown to a horizontal landing under radio-control. An on-board data acquisition system recorded data during both the launch and glide phases of flight.

Evolution of solid rocket booster component testing

NASA Technical Reports Server (NTRS)

Lessey, Joseph A.

1989-01-01

The evolution of one of the new generation of test sets developed for the Solid Rocket Booster of the U.S. Space Transportation System. Requirements leading to factory checkout of the test set are explained, including the evolution from manual to semiautomated toward fully automated status. Individual improvements in the built-in test equipment, self-calibration, and software flexibility are addressed, and the insertion of fault detection to improve reliability is discussed.

SRB Processing Facilities Media Event

NASA Image and Video Library

2016-03-01

Members of the news media watch as two cranes are used to lift one of two pathfinders, or test versions, of solid rocket booster segments for NASA’s Space Launch System (SLS) rocket into the vertical position inside the Rotation, Processing and Surge Facility at NASA’s Kennedy Space Center in Florida. The pathfinder booster segment will be moved to the other end of the RPSF and secured on a test stand. The Ground Systems Development and Operations Program and Jacobs Engineering, on the Test and Operations Support Contract, will prepare the booster segments, which are inert, for a series of lifts, moves and stacking operations to prepare for Exploration Mission-1, deep-space missions and the journey to Mars.

Analysis of delayed TBE-vaccine booster after primary vaccination.

PubMed

Aerssens, Annelies; Cochez, Christel; Niedrig, Matthias; Heyman, Paul; Kühlmann-Rabens, Ilona; Soentjens, Patrick

2016-02-01

An open, uncontrolled single centre study was conducted in the Travel Clinic at the Military Hospital, Brussels. Eighty-eight subjects were recruited who had a primary series of tick-borne encephalitis (TBE) vaccine more than 5 years ago and who never received a booster dose afterwards. Response rate after booster vaccination was very high: 84 out of 88 subjects (95.5%) had neutralizing antibodies on plaque reduction neutralization test and all (100%) had IgG antibodies on ELISA, on Day 21-28 after booster vaccination. This study adds valuable information to the common situation of delayed booster interval. The results of our study indicate that in young healthy travellers (<50 years), one booster vaccination after a primary series of TBE vaccine in the past is sufficient to obtain protective antibodies, even if primary vaccination is much longer than the recommended booster interval of 5 years. © International Society of Travel Medicine, 2016. All rights reserved.For permissions, please e-mail: journals.permissions@oup.com.

Space shuttle: Static stability and control investigation of NR/GD delta wing booster (B-20) and delta wing orbiter (134D), volume 4

NASA Technical Reports Server (NTRS)

Allen, E. C., Jr.; Eder, F. W.

1972-01-01

Test results of booster and orbiter models of various component buildup configurations are reported. Dataset Collation Sheets, which give a complete summary of the configurations, are presented along with a description of the test facility. Data reduction procedures are described.

Development and evaluation of an ablative closeout material for solid rocket booster thermal protection system

NASA Technical Reports Server (NTRS)

Patterson, W. J.

1979-01-01

A trowellable closeout/repair material designated as MTA-2 was developed and evaluated for use on the Solid Rocket Booster. This material is composed of an epoxy-polysulfide binder and is highly filled with phenolic microballoons for density control and ablative performance. Mechanical property testing and thermal testing were performed in a wind tunnel to simulate the combined Solid Rocket Booster trajectory aeroshear and heating environments. The material is characterized by excellent thermal performance and was used extensively on the Space Shuttle STS-1 and STS-2 flight hardware.

Booster Interface Loads

NASA Technical Reports Server (NTRS)

Gentz, Steve; Wood, Bill; Nettles, Mindy

2015-01-01

The interaction between shock waves and the wake shed from the forward booster/core attach hardware results in unsteady pressure fluctuations, which can lead to large buffeting loads on the vehicle. This task investigates whether computational tools can adequately predict these flows, and whether alternative booster nose shapes can reduce these loads. Results from wind tunnel tests will be used to validate the computations and provide design information for future Space Launch System (SLS) configurations. The current work combines numerical simulations with wind tunnel testing to predict buffeting loads caused by the boosters. Variations in nosecone shape, similar to the Ariane 5 design (fig. 1), are being evaluated with regard to lowering the buffet loads. The task will provide design information for the mitigation of buffet loads for SLS, along with validated simulation tools to be used to assess future SLS designs.

A new one-man submarine is tested as vehicle for solid rocket booster retrieval

NASA Technical Reports Server (NTRS)

2000-01-01

The one-man submarine dubbed DeepWorker 2000 sits on the deck of Liberty Star, one of two KSC solid rocket booster recovery ships. The sub is being tested on its ability to duplicate the sometimes hazardous job United Space Alliance (USA) divers perform to recover the expended boosters in the ocean after a launch. The boosters splash down in an impact area about 140 miles east of Jacksonville and after recovery are towed back to KSC for refurbishment by the specially rigged recovery ships. DeepWorker 2000 will be used in a demonstration during retrieval operations after the upcoming STS-101 launch. The submarine pilot will demonstrate capabilities to cut tangled parachute riser lines using a manipulator arm and attach a Diver Operator Plug to extract water and provide flotation for the booster. DeepWorker 2000 was built by Nuytco Research Ltd., North Vancouver, British Columbia. It is 8.25 feet long, 5.75 feet high, and weighs 3,800 pounds. USA is a prime contractor to NASA for the Space Shuttle program.

A new one-man submarine is tested as vehicle for solid rocket booster retrieval

NASA Technical Reports Server (NTRS)

2000-01-01

From the deck of Liberty Star, one of two KSC solid rocket booster recovery ships, a crane lowers a one-man submarine into the ocean near Cape Canaveral, Fla. Called DeepWorker 2000, the sub is being tested on its ability to duplicate the sometimes hazardous job United Space Alliance (USA) divers perform to recover the expended boosters in the ocean after a launch. The boosters splash down in an impact area about 140 miles east of Jacksonville and after recovery are towed back to KSC for refurbishment by the specially rigged recovery ships. DeepWorker 2000 will be used in a demonstration during retrieval operations after the upcoming STS-101 launch. The submarine pilot will demonstrate capabilities to cut tangled parachute riser lines using a manipulator arm and attach a Diver Operator Plug to extract water and provide flotation for the booster. DeepWorker 2000 was built by Nuytco Research Ltd., North Vancouver, British Columbia. It is 8.25 feet long, 5.75 feet high, and weighs 3,800 pounds. USA is a prime contractor to NASA for the Space Shuttle program.

KSC-00padig011

NASA Image and Video Library

2000-04-22

KENNEDY SPACE CENTER, FLA. -- A mockup of a solid rocket booster nozzle is lowered into the waters of the Atlantic during a test of a new booster retrieval method. A one-man submarine known as DeepWorker 2000 is being tested on its ability to duplicate the sometimes hazardous job United Space Alliance (USA) divers perform to recover the expended boosters in the ocean after a launch. The boosters splash down in an impact area about 140 miles east of Jacksonville and after recovery are towed back to KSC for refurbishment by the specially rigged recovery ships. DeepWorker 2000 will be used in a demonstration during retrieval operations after the upcoming STS-101 launch. The submarine pilot will demonstrate capabilities to cut tangled parachute riser lines using a manipulator arm and attach a Diver Operator Plug to extract water and provide flotation for the booster. DeepWorker 2000 was built by Nuytco Research Ltd., North Vancouver, British Columbia. It is 8.25 feet long, 5.75 feet high, and weighs 3,800 pounds. USA is a prime contractor to NASA for the Space Shuttle program

Space Launch System Booster Test- Behind the Scenes

NASA Image and Video Library

2016-06-24

Get a sneak peek behind the scenes of how engineers and technicians at Orbital ATK in Promontory, Utah, are coming together to test the most powerful booster for NASA’s new rocket, the Space Launch System. SLS will make missions possible to an asteroid and the journey to Mars. For more information on SLS, visit www.nasa.gov/sls.

SRB Processing Facilities Media Event

NASA Image and Video Library

2016-03-01

Members of the news media view the high bay inside the Rotation, Processing and Surge Facility (RPSF) at NASA’s Kennedy Space Center in Florida. Kerry Chreist, with Jacobs Engineering on the Test and Operations Support Contract, explains the various test stands and how they will be used to prepare booster segments for NASA’s Space Launch System (SLS) rocket. In the far corner, in the vertical position, is one of two pathfinders, or test versions, of solid rocket booster segments for the SLS rocket. The Ground Systems Development and Operations Program and Jacobs are preparing the booster segments, which are inert, for a series of lifts, moves and stacking operations to prepare for Exploration Mission-1, deep-space missions and the journey to Mars.

Space shuttle solid rocket booster sting interference wind tunnel test analysis

NASA Technical Reports Server (NTRS)

Conine, B.; Boyle, W.

1981-01-01

Wind tunnel test results from shuttle solid rocket booster (SRB) sting interference tests were evaluated, yielding the general influence of the sting on the normal force and pitching moment coefficients and the side force and yawing moment coefficients. The procedures developed to determine the sting interference, the development of the corrected aerodynamic data, and the development of a new SRB aerodynamic mathematical model are documented.

Rabies Vaccine

MedlinePlus

... and booster doses should be given as needed. (Testing or booster doses are not recommended for travelers.) Ask your doctor for details. Vaccination After an Exposure:Anyone who has been bitten by an animal, or who otherwise may have been exposed to ...

Exercise, manual therapy, and use of booster sessions in physical therapy for knee osteoarthritis: a multi-center, factorial randomized clinical trial.

PubMed

Fitzgerald, G K; Fritz, J M; Childs, J D; Brennan, G P; Talisa, V; Gil, A B; Neilson, B D; Abbott, J H

2016-08-01

(1) Do treatment effects differ between participants receiving manual therapy (MT) with exercise compared to subjects who don't, (2) are treatment effects sustained better when participants receive booster sessions compared to those who don't over a one year period in subjects with knee osteoarthritis (KOA)? Multi-center, 2 × 2 factorial randomized clinical trial. 300 participants with knee OA were randomized to four groups: exercise-no boosters (Ex), exercise-with boosters (Ex+B), manual therapy+exercise-no boosters (MT+Ex), manual therapy+exercise-with boosters (MT+Ex+B). The primary outcome was the Western Ontario and McMaster osteoarthritis index (WOMAC) at 1 year. Secondary outcomes included knee pain, physical performance tests, and proportions of participants meeting treatment responder criteria. There were no differences between groups on the WOMAC at 1 year or on any performance-based measures. Secondary analyses indicated a) better scores on the WOMAC and greater odds of being a treatment responder at 9 weeks for participants receiving MT, b) greater odds of being a treatment responder at 1 year for participants receiving boosters. Exploratory interaction analysis suggested knee pain decreases for participants receiving boosters and increases for participants not receiving boosters from 9 weeks to 1 year. MT or use of boosters with exercise did not result in additive improvement in the primary outcome at 1 year. Secondary outcomes suggest MT may have some short term benefit, and booster sessions may improve responder status and knee pain at 1 year. However, the role of booster sessions remains unclear in sustaining treatment effects and warrants further study. gov (NCT01314183). Copyright © 2016 Osteoarthritis Research Society International. All rights reserved.

A concept of active mount for space applications

NASA Astrophysics Data System (ADS)

Souleille, A.; Lampert, T.; Lafarga, V.; Hellegouarch, S.; Rondineau, A.; Rodrigues, G.; Collette, C.

2018-06-01

Sensitive payloads mounted on top of launchers are subjected to many sources of disturbances during the flight. The most severe dynamic loads arise from the ignition of the motors, gusts, pressure fluctuations in the booster and from the separation of the boosters. The transmission of these dynamic forces can be reduced by mounting payloads on passive isolators, which comes at the expense of harmful amplifications of the motion at low frequency due to suspension resonances. To bypass this shortcoming, this paper presents a novel concept of active mount for aerospace payloads, which is easy to install, and meets two objectives. The first one is a high damping authority on both suspension resonances and flexible resonances without compromising the isolation and large stability margins of the closed loop system due to the collocation of the actuator and the sensor. The second one is a broadband reduction of the dynamic force transmitted to the payload, which was achieved in terms of 16 dB. The concept is presented in the first part of the paper and studied numerically and experimentally on a single degree of freedom isolator. A commercial isolator has been chosen for the purpose of the demonstration. The second part of the paper is dedicated to experimental validations on multi-degree of freedom scaled test benches. It is shown that the force feedback allows damping of both suspension and flexible modes (first and second modes, respectively), and significantly reducing the force transmitted in some broad frequency ranges.

KENNEDY SPACE CENTER, FLA. - Jeff Thon, an SRB mechanic with United Space Alliance, tests a technique for vertical solid rocket booster propellant grain inspection. The inspection of segments is required as part of safety analysis.

NASA Image and Video Library

2003-09-11

KENNEDY SPACE CENTER, FLA. - Jeff Thon, an SRB mechanic with United Space Alliance, tests a technique for vertical solid rocket booster propellant grain inspection. The inspection of segments is required as part of safety analysis.

The X-43A hypersonic research aircraft and its modified Pegasus booster rocket recently underwent c

NASA Technical Reports Server (NTRS)

2001-01-01

The first of three X-43A hypersonic research aircraft and its modified Pegasus booster rocket recently underwent combined systems testing while mounted to NASA's NB-52B carrier aircraft at the Dryden Flight Research Center, Edwards, Calif. The combined systems test was one of the last major milestones in the Hyper-X research program before the first X-43A flight. The X-43A flights will be the first actual flight tests of an aircraft powered by a revolutionary supersonic-combustion ramjet ('scramjet') engine capable of operating at hypersonic speeds (above Mach 5, or five times the speed of sound). The 12-foot, unpiloted research vehicle was developed and built by MicroCraft Inc., Tullahoma, Tenn., under NASA contract. The booster was built by Orbital Sciences Corp., Dulles, Va.,After being air-launched from NASA's venerable NB-52 mothership, the booster will accelerate the X-43A to test speed and altitude. The X-43A will then separate from the rocket and fly a pre-programmed trajectory, conducting aerodynamic and propulsion experiments until it descends into the Pacific Ocean. Three research flights are planned, two at Mach 7 and one at Mach 10.

The X-43A hypersonic research aircraft and its modified Pegasus booster rocket nestled under the wi

NASA Technical Reports Server (NTRS)

2001-01-01

The X-43A hypersonic research aircraft and its modified Pegasus booster rocket are nestled under the wing of NASA's NB-52B carrier aircraft during pre-flight systems testing at the Dryden Flight Research Center, Edwards, Calif. The combined systems test was one of the last major milestones in the Hyper-X research program before the first X-43A flight. The X-43A flights will be the first actual flight tests of an aircraft powered by a revolutionary supersonic-combustion ramjet ('scramjet') engine capable of operating at hypersonic speeds (above Mach 5, or five times the speed of sound). The 12-foot, unpiloted research vehicle was developed and built by MicroCraft Inc., Tullahoma, Tenn., under NASA contract. The booster was built by Orbital Sciences Corp., Dulles, Va. After being air-launched from NASA's venerable NB-52 mothership, the booster will accelerate the X-43A to test speed and altitude. The X-43A will then separate from the rocket and fly a pre-programmed trajectory, conducting aerodynamic and propulsion experiments until it descends into the Pacific Ocean. Three research flights are planned, two at Mach 7 and one at Mach 10.

Quality assurance and control in the production and static tests of the solid rocket boosters for the Space Shuttle

NASA Technical Reports Server (NTRS)

Cerny, O. F.

1979-01-01

The paper surveys the various aspects of design and overhaul of the solid rocket boosters. It is noted that quality control is an integral part of the design specifications. Attention is given to the production process which is optimized towards highest quality. Also discussed is the role of the DCA (Defense Contract Administration) in inspecting the products of subcontractors, noting that the USAF performs this role for prime contractors. Fabrication and construction of the booster is detailed with attention given to the lining of the booster cylinder and the mixing of the propellant and the subsequent X-ray inspection.

Saturn Apollo Program

NASA Image and Video Library

1961-02-04

The Saturn project was approved on January 18, 1960 as a program of the highest national priority. The formal test program to prove out the clustered-booster concept was well underway. A series of static tests of the Saturn I booster (S-I stage) began June 3, 1960 at the Marshall Space Flight Center (MSFC). This photograph depicts the Saturn I S-I stage equipped with eight H-1 engines, being successfully test-fired on February 4, 1961. A Juno rocket is visible on the right side of the test stand.

Pretest Plan for a Quarter Scale AFT Segment of the SRB Filament Wound Case in the NSWC Hydroballistics Facility. [space shuttle boosters

NASA Technical Reports Server (NTRS)

Adoue, J. A.

1984-01-01

In support of preflight design loads definition, preliminary water impact scale model are being conducted of space shuttle rocket boosters. The model to be used as well as the instrumentation, test facilities, and test procedures are described for water impact tests being conducted at test conditions to simulate full-scale initial impact at vertical velocities from 65 to 85 ft/sec. zero horizontal velocity, and angles of 0,5, and 10 degrees.

A new one-man submarine is tested as vehicle for solid rocket booster retrieval

NASA Technical Reports Server (NTRS)

2000-01-01

- The one-man submarine known as DeepWorker 2000 is tested in Atlantic waters near Cape Canaveral, Fla. Nearby are divers; inside the sub is the pilot, Anker Rasmussen. The sub is being tested on its ability to duplicate the sometimes hazardous job United Space Alliance (USA) divers perform to recover the expended boosters in the ocean after a launch. The boosters splash down in an impact area about 140 miles east of Jacksonville and after recovery are towed back to KSC for refurbishment by the specially rigged recovery ships. DeepWorker 2000 will be used in a demonstration during retrieval operations after the upcoming STS-101 launch. The submarine pilot will demonstrate capabilities to cut tangled parachute riser lines using a manipulator arm and attach a Diver Operator Plug to extract water and provide flotation for the booster. DeepWorker 2000 was built by Nuytco Research Ltd., North Vancouver, British Columbia. It is 8.25 feet long, 5.75 feet high, and weighs 3,800 pounds. USA is a prime contractor to NASA for the Space Shuttle program.

KSC-2009-6026

NASA Image and Video Library

2009-10-30

CAPE CANAVERAL, Fla. – The solid rocket booster recovery ship Freedom Star, towing the spent first stage of NASA's Ares I-X rocket through the Banana River, delivers the booster to Hangar AF at Cape Canaveral Air Force Station in Florida. Following the launch of the Ares I-X flight test, the booster splashed down in the Atlantic Ocean and was recovered. Liftoff of the 6-minute flight test was at 11:30 a.m. EDT Oct. 28. This was the first launch from Kennedy's pads of a vehicle other than the space shuttle since the Apollo Program's Saturn rockets were retired. The parts used to make the Ares I-X booster flew on 30 different shuttle missions ranging from STS-29 in 1989 to STS-106 in 2000. The data returned from more than 700 sensors throughout the rocket will be used to refine the design of future launch vehicles and bring NASA one step closer to reaching its exploration goals. For information on the Ares I-X vehicle and flight test, visit http://www.nasa.gov/aresIX. Photo credit: NASA/Kim Shiflett

The X-43A hypersonic research aircraft and its modified Pegasus® booster rocket recently underwent combined systems testing while mounted to NASA's NB-52B carrier aircraft

NASA Image and Video Library

2001-03-15

The first of three X-43A hypersonic research aircraft and its modified Pegasus® booster rocket recently underwent combined systems testing while mounted to NASA's NB-52B carrier aircraft at the Dryden Flight Research Center, Edwards, Calif. The combined systems test was one of the last major milestones in the Hyper-X research program before the first X-43A flight. The X-43A flights will be the first actual flight tests of an aircraft powered by a revolutionary supersonic-combustion ramjet ("scramjet") engine capable of operating at hypersonic speeds (above Mach 5, or five times the speed of sound). The 12-foot, unpiloted research vehicle was developed and built by MicroCraft Inc., Tullahoma, Tenn., under NASA contract. The booster was built by Orbital Sciences Corp., Dulles, Va.,After being air-launched from NASA's venerable NB-52 mothership, the booster will accelerate the X-43A to test speed and altitude. The X-43A will then separate from the rocket and fly a pre-programmed trajectory, conducting aerodynamic and propulsion experiments until it descends into the Pacific Ocean. Three research flights are planned, two at Mach 7 and one at Mach 10.

The X-43A hypersonic research aircraft and its modified Pegasus® booster rocket nestled under the wing of NASA's NB-52B carrier aircraft during pre-flight systems testing

NASA Image and Video Library

2001-03-15

The X-43A hypersonic research aircraft and its modified Pegasus® booster rocket are nestled under the wing of NASA's NB-52B carrier aircraft during pre-flight systems testing at the Dryden Flight Research Center, Edwards, Calif. The combined systems test was one of the last major milestones in the Hyper-X research program before the first X-43A flight. The X-43A flights will be the first actual flight tests of an aircraft powered by a revolutionary supersonic-combustion ramjet ("scramjet") engine capable of operating at hypersonic speeds (above Mach 5, or five times the speed of sound). The 12-foot, unpiloted research vehicle was developed and built by MicroCraft Inc., Tullahoma, Tenn., under NASA contract. The booster was built by Orbital Sciences Corp., Dulles, Va. After being air-launched from NASA's venerable NB-52 mothership, the booster will accelerate the X-43A to test speed and altitude. The X-43A will then separate from the rocket and fly a pre-programmed trajectory, conducting aerodynamic and propulsion experiments until it descends into the Pacific Ocean. Three research flights are planned, two at Mach 7 and one at Mach 10.

Space shuttle booster separation motor design

NASA Technical Reports Server (NTRS)

Smith, G. W.; Chase, C. A.

1976-01-01

The separation characteristics of the space shuttle solid rocket boosters (SRBs) are introduced along with the system level requirements for the booster separation motors (BSMs). These system requirements are then translated into specific motor requirements that control the design of the BSM. Each motor component is discussed including its geometry, material selection, and fabrication process. Also discussed is the propellant selection, grain design, and performance capabilities of the motor. The upcoming test program to develop and qualify the motor is outlined.

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.

Rabies Vaccine: What You Need to Know

MedlinePlus

... and booster doses should be given as needed. (Testing or booster doses are not recommended for travelers.) Ask your doctor for details. Vaccination after an exposure Anyone who has been bitten by an animal, or who otherwise may have been exposed to ...

Maintaining the potential of a psycho-educational program: efficacy of a booster session after an intervention offered family caregivers at disclosure of a relative's dementia diagnosis.

PubMed

Ducharme, Francine; Lachance, Lise; Lévesque, Louise; Zarit, Steven Howard; Kergoat, Marie-Jeanne

2015-01-01

Booster sessions as a means of maintaining the benefits of psycho-educational programs have received little attention in caregiving research. Caregivers were offered a booster session following participation in a program entitled Learning to Become a Family Caregiver (LBFC) intended to facilitate transition to the caregiver role after diagnostic disclosure of dementia in a relative. The 90-minute booster session served to review program content and afforded the opportunity to discuss and practice learned skills. This study sought to test the efficacy of the booster session in maintaining or recovering program effects at six months post-program. Participants in the program were randomly assigned to a group that received the booster session (n = 31) or a group that did not (n = 29). A third control group was also formed, which continued to receive only the usual care provided in memory clinics. Eligible participants - French-speaking primary caregivers of a relative diagnosed with Alzheimer's in the past nine months - were recruited in memory clinics in Quebec (Canada). Participants were blindly assessed before randomization and six months after the booster session on outcomes associated with a healthy role transition. Prediction analyses revealed one significant positive effect of the booster session: emergence of preparedness to provide care. Moreover, with or without the booster session, the program continued to have a positive effect on psychological distress and contributed to the emergence of self-efficacy in dealing with caregiving situations. The booster session had no significant effect on knowledge of services, planning for future care needs, use of reframing as a coping strategy, perceived informal support, and family conflicts. The limited effect observed is discussed in terms of the booster session's content and intensity. Recommendations are made for designing future research on the effect of booster sessions, including the importance of including a placebo booster group.

Saturn Apollo Program

NASA Image and Video Library

1960-06-15

The Saturn Project was approved on January 18, 1960 as a program of the highest national priority. The formal test program to prove out the clustered-booster concept was well underway. A series of static tests of the Saturn I booster (S-I stage) began June 3, 1960 at the Marshall Space Flight Center (MSFC). This photograph depicts the Saturn I S-I stage equipped with eight H-1 engines, being successfully test-fired for the duration of 121 seconds on June 15, 1960.

A new one-man submarine is tested as vehicle for solid rocket booster retrieval

NASA Technical Reports Server (NTRS)

2000-01-01

A Diver Operator Plug (DOP) is being pulled down into the ocean by a newly designed one-man submarine known as DeepWorker 2000. The activity is part of an operation to attach the plug to a mockup of a solid rocket booster nozzle. DeepWorker 2000 is being tested on its ability to duplicate the sometimes hazardous job United Space Alliance (USA) divers perform to recover the expended boosters in the ocean after a launch. The boosters splash down in an impact area about 140 miles east of Jacksonville and after recovery are towed back to KSC for refurbishment by the specially rigged recovery ships. DeepWorker 2000 will be used in a demonstration during retrieval operations after the upcoming STS-101 launch. The submarine pilot will demonstrate capabilities to cut tangled parachute riser lines using a manipulator arm and attach the DOP to extract water and provide flotation for the booster. DeepWorker 2000 was built by Nuytco Research Ltd., North Vancouver, British Columbia. It is 8.25 feet long, 5.75 feet high, and weighs 3,800 pounds. USA is a prime contractor to NASA for the Space Shuttle program.

A new one-man submarine is tested as vehicle for solid rocket booster retrieval

NASA Technical Reports Server (NTRS)

2000-01-01

After a successful dive, the one-man submarine known as DeepWorker 2000 is lifted from Atlantic waters near Cape Canaveral, Fla., onto the deck of the Liberty Star, one of two KSC solid rocket booster recovery ships. Inside the sub is the pilot, Anker Rasmussen. The sub is being tested on its ability to duplicate the sometimes hazardous job United Space Alliance (USA) divers perform to recover the expended boosters in the ocean after a launch. The boosters splash down in an impact area about 140 miles east of Jacksonville and after recovery are towed back to KSC for refurbishment by the specially rigged recovery ships. DeepWorker 2000 will be used in a demonstration during retrieval operations after the upcoming STS-101 launch. The submarine pilot will demonstrate capabilities to cut tangled parachute riser lines using a manipulator arm and attach a Diver Operator Plug to extract water and provide flotation for the booster. DeepWorker 2000 was built by Nuytco Research Ltd., North Vancouver, British Columbia. It is 8.25 feet long, 5.75 feet high, and weighs 3,800 pounds. USA is a prime contractor to NASA for the Space Shuttle program.

A new one-man submarine is tested as vehicle for solid rocket booster retrieval

NASA Technical Reports Server (NTRS)

2000-01-01

At left, a manipulator arm on a one-man submarine demonstrates its ability to cut tangled parachute riser lines and place a Diver Operator Plug (top right) inside a mock solid rocket booster nozzle (center). Known as DeepWorker 2000, the sub is being tested on its ability to duplicate the sometimes hazardous job United Space Alliance (USA) divers perform to recover the expended boosters in the ocean after a launch. The boosters splash down in an impact area about 140 miles east of Jacksonville and after recovery are towed back to KSC for refurbishment by the specially rigged recovery ships. DeepWorker 2000 will be used in a demonstration during retrieval operations after the upcoming STS-101 launch. The submarine pilot will demonstrate capabilities to cut tangled parachute riser lines using a manipulator arm and attach the DOP to extract water and provide flotation for the booster. DeepWorker 2000 was built by Nuytco Research Ltd., North Vancouver, British Columbia. It is 8.25 feet long, 5.75 feet high, and weighs 3,800 pounds. USA is a prime contractor to NASA for the Space Shuttle program.

Fallback level concepts for conventional and by-wire automotive brake systems

NASA Astrophysics Data System (ADS)

Retzer, H.; Mishra, R.; Ball, A.; Schmidt, K.

2012-05-01

Brake-by-wire represents the replacement of traditional brake components such as pumps, hoses, fluids, brake boosters, and master cylinders by electronic sensors and actuators. The different design of these brake concepts poses new challenges for the automotive industry with regard to availability and fallback levels in comparison to standard conventional brake systems. This contribution focuses on the development of appropriate fallback level concepts. Hardware-in-the-loop (HIL) techniques and field trials will be used to investigate the performance and the usability of such systems.

SRB Processing Facilities Media Event

NASA Image and Video Library

2016-03-01

Members of the news media view the high bay inside the Rotation, Processing and Surge Facility (RPSF) at NASA’s Kennedy Space Center in Florida. Kerry Chreist, with Jacobs Engineering on the Test and Operations Support Contract, talks with a reporter about the booster segments for NASA’s Space Launch System (SLS) rocket. In the far corner, in the vertical position, is one of two pathfinders, or test versions, of solid rocket booster segments for the SLS rocket. The Ground Systems Development and Operations Program and Jacobs are preparing the booster segments, which are inert, for a series of lifts, moves and stacking operations to prepare for Exploration Mission-1, deep-space missions and the journey to Mars.

Lithium cell tests at Marshall Space Flight Center. [batteries for range safety and frustrum location aid in the shuttle solid rocket booster

NASA Technical Reports Server (NTRS)

Paschal, L. E.

1977-01-01

Three 18 AH Li-CF batteries with a polypropylene separator and using dimethyl sulfite in Li as F6 for the electrolyte will be placed in each shuttle solid rocket booster for range safety and frustrum location aid. Mechanical vibration, acceleration, random and design vibration, and discharge evaluation tests are discussed.

Five year follow-up after a first booster vaccination against tick-borne encephalitis following different primary vaccination schedules demonstrates long-term antibody persistence and safety.

PubMed

Beran, Jiří; Xie, Fang; Zent, Olaf

2014-07-23

Long-term vaccination programs are recommended for individuals living in regions endemic for tick-borne encephalitis (TBE). Current recommendations suggest a first booster vaccine be administered 3 years after a conventional regimen or 12-18 months after a rapid regimen. However, the research supporting subsequent booster intervals is limited. The aim of this study was thus to evaluate the long-term persistence of TBE antibodies in adults and adolescents after a first booster dose with Encepur(®). A total of 323 subjects aged 15 years and over, who had received one of four different primary TBE vaccination series in a parent study, participated in this follow-up Phase IV trial. Immunogenicity and safety were assessed for up to five years after a first booster dose, which was administered three years after completion of the primary series. One subset of subjects was excluded from the booster vaccination since they had already received their booster prior to enrollment. For comparison, immune responses were still recorded for these subjects on Day 0 and on an annual basis until Year 5, but safety information was not collected. Following a booster vaccination, high antibody titers were recorded in all groups throughout the study. Neutralization test (NT) titers of ≥ 10 were noted in at least 94% of subjects at every time point post-booster (on Day 21 and through Years 1-5). These results demonstrated that a first booster vaccination following any primary immunization schedule results in high and long-lasting (>5 years) immune responses. These data lend support to the current belief that subsequent TBE booster intervals could be extended from the current recommendation. NCT00387634. Copyright © 2014 Elsevier Ltd. All rights reserved.

SPE5 Sub-Scale Test Series Summary Report

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

Vandersall, Kevin S.; Reeves, Robert V.; DeHaven, Martin R.

2016-01-14

A series of 2 SPE5 sub-scale tests were performed to experimentally confirm that a booster system designed and evaluated in prior tests would properly initiate the PBXN-110 case charge fill. To conduct the experiments, a canister was designed to contain the nominally 50 mm diameter booster tube with an outer fill of approximately 150 mm diameter by 150 mm in length. The canisters were filled with PBXN-110 at NAWS-China Lake and shipped back to LLNL for testing in the High Explosives Applications Facility (HEAF). Piezoelectric crystal pins were placed on the outside of the booster tube before filling, and amore » series of piezoelectric crystal pins along with Photonic Doppler Velocimetry (PDV) probes were placed on the outer surface of the canister to measure the relative timing and magnitude of the detonation. The 2 piezoelectric crystal pins integral to the booster design were also utilized along with a series of either piezoelectric crystal pins or piezoelectric polymer pads on the top of the canister or outside case that utilized direct contact, gaps, or different thicknesses of RTV cushions to obtain time of arrival data to evaluate the response in preparation for the large-scale SPE5 test. To further quantify the margin of the booster operation, the 1st test (SPE5SS1) was functioned with both detonators and the 2nd test (SPE5SS2) was functioned with only 1 detonator. A full detonation of the material was observed in both experiments as observed by the pin timing and PDV signals. The piezoelectric pads were found to provide a greater measured signal magnitude during the testing with an RTV layer present, and the improved response is due to the larger measurement surface area of the pad. This report will detail the experiment design, canister assembly for filling, final assembly, experiment firing, presentation of the diagnostic results, and a discussion of the results.« less

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.

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.

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.

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.

Space shuttle: Heat transfer rate measurements on Convair booster (B-15B-2) at nominal Mach number of 8

NASA Technical Reports Server (NTRS)

Warmbrod, J. D.; Martindale, W. R.; Matthews, R. K.

1971-01-01

Plotted and tabulated data on heat transfer from a thin-skin thermocouple are presented. The data is representative of the reentry event of the booster alone configuration. The data were generated during wind tunnel tests of the B-15B-2 delta wing booster at Mach 8. Thermocouple measurements are reduced to heat transfer coefficient ratio and the data are presented as plotted variations versus longitudinal, lateral, and vertical local model positions.

NASA's Space Launch System Advanced Booster Engineering Demonstration and/or Risk Reduction Efforts

NASA Technical Reports Server (NTRS)

Crumbly, Christopher M.; Dumbacher, Daniel L.; May, Todd A.

2012-01-01

The National Aeronautics and Space Administration (NASA) formally initiated the Space Launch System (SLS) development in September 2011, with the approval of the program s acquisition plan, which engages the current workforce and infrastructure to deliver an initial 70 metric ton (t) SLS capability in 2017, while using planned block upgrades to evolve to a full 130 t capability after 2021. A key component of the acquisition plan is a three-phased approach for the first stage boosters. The first phase is to complete the development of the Ares and Space Shuttle heritage 5-segment solid rocket boosters (SRBs) for initial exploration missions in 2017 and 2021. The second phase in the booster acquisition plan is the Advanced Booster Risk Reduction and/or Engineering Demonstration NASA Research Announcement (NRA), which was recently awarded after a full and open competition. The NRA was released to industry on February 9, 2012, with a stated intent to reduce risks leading to an affordable advanced booster and to enable competition. The third and final phase will be a full and open competition for Design, Development, Test, and Evaluation (DDT&E) of the advanced boosters. There are no existing boosters that can meet the performance requirements for the 130 t class SLS. The expected thrust class of the advanced boosters is potentially double the current 5-segment solid rocket booster capability. These new boosters will enable the flexible path approach to space exploration beyond Earth orbit (BEO), opening up vast opportunities including near-Earth asteroids, Lagrange Points, and Mars. This evolved capability offers large volume for science missions and payloads, will be modular and flexible, and will be right-sized for mission requirements. NASA developed the Advanced Booster Engineering Demonstration and/or Risk Reduction NRA to seek industry participation in reducing risks leading to an affordable advanced booster that meets the SLS performance requirements. Demonstrations and/or risk reduction efforts were required to be related to a proposed booster concept directly applicable to fielding an advanced booster. This paper will discuss, for the first time publicly, the contract awards and how NASA intends to use the data from these efforts to prepare for the planned advanced booster DDT&E acquisition as the SLS Program moves forward with competitively procured affordable performance enhancements.

NASA's Space Launch System Advanced Booster Engineering Demonstration and Risk Reduction Efforts

NASA Technical Reports Server (NTRS)

Crumbly, Christopher M.; May, Todd; Dumbacher, Daniel

2012-01-01

The National Aeronautics and Space Administration (NASA) formally initiated the Space Launch System (SLS) development in September 2011, with the approval of the program s acquisition plan, which engages the current workforce and infrastructure to deliver an initial 70 metric ton (t) SLS capability in 2017, while using planned block upgrades to evolve to a full 130 t capability after 2021. A key component of the acquisition plan is a three-phased approach for the first stage boosters. The first phase is to complete the development of the Ares and Space Shuttle heritage 5-segment solid rocket boosters for initial exploration missions in 2017 and 2021. The second phase in the booster acquisition plan is the Advanced Booster Risk Reduction and/or Engineering Demonstration NASA Research Announcement (NRA), which was recently awarded after a full and open competition. The NRA was released to industry on February 9, 2012, and its stated intent was to reduce risks leading to an affordable Advanced Booster and to enable competition. The third and final phase will be a full and open competition for Design, Development, Test, and Evaluation (DDT&E) of the Advanced Boosters. There are no existing boosters that can meet the performance requirements for the 130 t class SLS. The expected thrust class of the Advanced Boosters is potentially double the current 5-segment solid rocket booster capability. These new boosters will enable the flexible path approach to space exploration beyond Earth orbit, opening up vast opportunities including near-Earth asteroids, Lagrange Points, and Mars. This evolved capability offers large volume for science missions and payloads, will be modular and flexible, and will be right-sized for mission requirements. NASA developed the Advanced Booster Engineering Demonstration and/or Risk Reduction NRA to seek industry participation in reducing risks leading to an affordable Advanced Booster that meets the SLS performance requirements. Demonstrations and/or risk reduction efforts were required to be related to a proposed booster concept directly applicable to fielding an Advanced Booster. This paper will discuss, for the first time publicly, the contract awards and how NASA intends to use the data from these efforts to prepare for the planned Advanced Booster DDT&E acquisition as the SLS Program moves forward with competitively procured affordable performance enhancements.

KSC-2014-3685

NASA Image and Video Library

2014-08-04

CAPE CANAVERAL, Fla. – All three of the United Launch Alliance, or ULA, Delta IV boosters for Exploration Flight Test-1 are in view inside the Horizontal Integration Facility at Space Launch Complex 37 on Cape Canaveral Air Force Station in Florida. The port booster is being mated to the core booster. The ULA Delta IV Heavy rocket will launch an uncrewed Orion spacecraft on Exploration Flight Test-1. During the mission, Orion will travel farther into space than any human spacecraft has gone in more than 40 years. The data gathered during the flight will influence design decisions, validate existing computer models and innovative new approaches to space systems development, as well as reduce overall mission risks and costs for later Orion flights. Liftoff of Orion on the first flight test is planned for December 2014. Photo credit: NASA/Ben Smegelsky

KSC-2014-3686

NASA Image and Video Library

2014-08-04

CAPE CANAVERAL, Fla. – All three of the United Launch Alliance, or ULA, Delta IV boosters for Exploration Flight Test-1 are in view inside the Horizontal Integration Facility at Space Launch Complex 37 on Cape Canaveral Air Force Station in Florida. The port booster is being mated to the core booster. The ULA Delta IV Heavy rocket will launch an uncrewed Orion spacecraft on Exploration Flight Test-1. During the mission, Orion will travel farther into space than any human spacecraft has gone in more than 40 years. The data gathered during the flight will influence design decisions, validate existing computer models and innovative new approaches to space systems development, as well as reduce overall mission risks and costs for later Orion flights. Liftoff of Orion on the first flight test is planned for December 2014. Photo credit: NASA/Ben Smegelsky

KENNEDY SPACE CENTER, FLA. - The crawler-transporter carrying Mobile Launcher Platform (MLP) number 3, with a set of twin solid rocket boosters bolted atop, crawls to the intersection in the crawlerway in support of the second engineering analysis vibration test on the crawler and MLP. From this perspective, the Launch Control Center (left) and the 525-foot-tall Vehicle Assembly Building (right) in the background appear dwarfed by the 184-foot-tall boosters. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

NASA Image and Video Library

2003-11-21

KENNEDY SPACE CENTER, FLA. - The crawler-transporter carrying Mobile Launcher Platform (MLP) number 3, with a set of twin solid rocket boosters bolted atop, crawls to the intersection in the crawlerway in support of the second engineering analysis vibration test on the crawler and MLP. From this perspective, the Launch Control Center (left) and the 525-foot-tall Vehicle Assembly Building (right) in the background appear dwarfed by the 184-foot-tall boosters. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

KENNEDY SPACE CENTER, FLA. - A crawler-transporter carrying Mobile Launcher Platform (MLP) number 3, with a set of twin solid rocket boosters bolted atop, crawls to the intersection in the crawlerway in support of the second engineering analysis vibration test on the crawler and MLP. From this perspective, the Launch Control Center (left) and the 525-foot-tall Vehicle Assembly Building (right) in the background appear dwarfed by the 184-foot-tall boosters. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

NASA Image and Video Library

2003-11-21

KENNEDY SPACE CENTER, FLA. - A crawler-transporter carrying Mobile Launcher Platform (MLP) number 3, with a set of twin solid rocket boosters bolted atop, crawls to the intersection in the crawlerway in support of the second engineering analysis vibration test on the crawler and MLP. From this perspective, the Launch Control Center (left) and the 525-foot-tall Vehicle Assembly Building (right) in the background appear dwarfed by the 184-foot-tall boosters. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

Mercury Project

NASA Image and Video Library

1961-03-24

The Mercury-Redstone Booster Development vehicle (MR-BD) lifts off from Cape Canaveral March 24, 1961. This test flight evaluated changes incorporated in the booster designed to reduce vehicle oscillations and vibrations. The Mercury-Redstone launch vehicle was developed by Dr. Wernher von Braun and the rocket team in Huntsville, Alabama.

BERLinPro Booster Cavity Design, Fabrication and Test Plans

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

Burrill, Andrew; Anders, W; Frahm, A.

2014-12-01

The bERLinPro project, a 100 mA, 50 MeV superconducting RF (SRF) Energy Recovery Linac (ERL) is under construction at Helmholtz-Zentrum Berlin for the purpose of studying the technical challenges and physics of operating a high current, c.w., 1.3 GHz ERL. This machine will utilize three unique SRF cryomodules for the injector, booster and linac module respectively. The booster cryomodule will contain three 2-cell SRF cavities, based on the original design by Cornell University, and will be equipped with twin 115 kW RF power couplers in order to provide the appropriate acceleration to the high current electron beam. This paper willmore » review the status of the fabrication of the 4 booster cavities that have been built for this project by Jefferson Laboratory and look at the challenges presented by the incorporation of fundamental power couplers capable of delivering 115 kW. The test plan for the cavities and couplers will be given along with a brief overview of the cryomodule design.« less

The Use of Ion Vapor Deposited Aluminum (IVD) for the Space Shuttle Solid Rocket Booster (SRB)

NASA Technical Reports Server (NTRS)

Novak, Howard L.

2003-01-01

This viewgraph representation provides an overview of the use of ion vapor deposited aluminum (IVD) for use in the Space Shuttle Solid Rocket Booster (SRB). Topics considered include: schematics of ion vapor deposition system, production of ion vapor deposition system, IVD vs. cadmium coated drogue ratchets, corrosion exposure facilities and tests, seawater immersion facilities and tests and continued research and development issues.

KENNEDY SPACE CENTER, FLA. - The crawler transporter slowly moves the Mobile Launcher Platform (MLP), carrying a set of twin solid rocket boosters, along the crawlerway in support of engineering analysis vibration tests on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

NASA Image and Video Library

2003-11-17

KENNEDY SPACE CENTER, FLA. - The crawler transporter slowly moves the Mobile Launcher Platform (MLP), carrying a set of twin solid rocket boosters, along the crawlerway in support of engineering analysis vibration tests on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

Standardized error severity score (ESS) ratings to quantify risk associated with child restraint system (CRS) and booster seat misuse.

PubMed

Rudin-Brown, Christina M; Kramer, Chelsea; Langerak, Robin; Scipione, Andrea; Kelsey, Shelley

2017-11-17

Although numerous research studies have reported high levels of error and misuse of child restraint systems (CRS) and booster seats in experimental and real-world scenarios, conclusions are limited because they provide little information regarding which installation issues pose the highest risk and thus should be targeted for change. Beneficial to legislating bodies and researchers alike would be a standardized, globally relevant assessment of the potential injury risk associated with more common forms of CRS and booster seat misuse, which could be applied with observed error frequency-for example, in car seat clinics or during prototype user testing-to better identify and characterize the installation issues of greatest risk to safety. A group of 8 leading world experts in CRS and injury biomechanics, who were members of an international child safety project, estimated the potential injury severity associated with common forms of CRS and booster seat misuse. These injury risk error severity score (ESS) ratings were compiled and compared to scores from previous research that had used a similar procedure but with fewer respondents. To illustrate their application, and as part of a larger study examining CRS and booster seat labeling requirements, the new standardized ESS ratings were applied to objective installation performance data from 26 adult participants who installed a convertible (rear- vs. forward-facing) CRS and booster seat in a vehicle, and a child test dummy in the CRS and booster seat, using labels that only just met minimal regulatory requirements. The outcome measure, the risk priority number (RPN), represented the composite scores of injury risk and observed installation error frequency. Variability within the sample of ESS ratings in the present study was smaller than that generated in previous studies, indicating better agreement among experts on what constituted injury risk. Application of the new standardized ESS ratings to installation performance data revealed several areas of misuse of the CRS/booster seat associated with high potential injury risk. Collectively, findings indicate that standardized ESS ratings are useful for estimating injury risk potential associated with real-world CRS and booster seat installation errors.

SLS Pathfinder Segments Car Train Departure

NASA Image and Video Library

2016-03-02

An Iowa Northern locomotive, contracted by Goodloe Transportation of Chicago, departs from NASA’s Kennedy Space Center in Florida, with two containers on railcars for transport to the Jay Jay railroad yard. The containers held two pathfinders, or test versions, of solid rocket booster segments for NASA’s Space Launch System rocket that were delivered to the Rotation, Processing and Surge Facility (RPSF). Inside the RPSF, the Ground Systems Development and Operations Program and Jacobs Engineering, on the Test and Operations Support Contract, will conduct a series of lifts, moves and stacking operations using the booster segments, which are inert, to prepare for Exploration Mission-1, deep-space missions and the journey to Mars. The pathfinder booster segments are from Orbital ATK in Utah.

SLS Pathfinder Segments Car Train Departure

NASA Image and Video Library

2016-03-02

An Iowa Northern locomotive, contracted by Goodloe Transportation of Chicago, departs from the Rotation, Processing and Surge Facility (RPSF) at NASA’s Kennedy Space Center in Florida, with two containers on railcars for transport to the NASA Jay Jay railroad yard. The containers held two pathfinders, or test versions, of solid rocket booster segments for NASA’s Space Launch System rocket that were delivered to the RPSF. Inside the RPSF, the Ground Systems Development and Operations Program and Jacobs Engineering, on the Test and Operations Support Contract, will conduct a series of lifts, moves and stacking operations using the booster segments, which are inert, to prepare for Exploration Mission-1, deep-space missions and the journey to Mars. The pathfinder booster segments are from Orbital ATK in Utah.

NASA's Space Launch System Advanced Booster Development

NASA Technical Reports Server (NTRS)

Robinson, Kimberly F.; Crumbly, Christopher M.; May, Todd A.

2014-01-01

The National Aeronautics and Space Administration's (NASA's) Space Launch System (SLS) Program, managed at the Marshall Space Flight Center, is making progress toward delivering a new capability for human space flight and scientific missions beyond Earth orbit. NASA is executing this development within flat budgetary guidelines by using existing engines assets and heritage technology to ready an initial 70 metric ton (t) lift capability for launch in 2017, and then employing a block upgrade approach to evolve a 130-t capability after 2021. A key component of the SLS acquisition plan is a three-phased approach for the first-stage boosters. The first phase is to expedite the 70-t configuration by completing development of the Space Shuttle heritage 5-segment solid rocket boosters (SRBs) for the initial flights of SLS. Since no existing boosters can meet the performance requirements for the 130-t class SLS, the next phases of the strategy focus on the eventual development of advanced boosters with an expected thrust class potentially double the current 5-segment solid rocket booster capability of 3.88 million pounds of thrust each. The second phase in the booster acquisition plan is the Advanced Booster Engineering Demonstration and/or Risk Reduction (ABEDRR) effort, for which contracts were awarded beginning in 2012 after a full and open competition, with a stated intent to reduce risks leading to an affordable advanced booster. NASA has awarded ABEDRR contracts to four industry teams, which are looking into new options for liquid-fuel booster engines, solid-fuel-motor propellants, and composite booster structures. Demonstrations and/or risk reduction efforts were required to be related to a proposed booster concept directly applicable to fielding an advanced booster. This paper will discuss the status of this acquisition strategy and its results toward readying both the 70 t and 130 t configurations of SLS. The third and final phase will be a full and open competition for Design, Development, Test, and Evaluation (DDT&E) of the advanced boosters. These new boosters will enable the flexible path approach to deep space exploration, opening up vast opportunities for human missions to near-Earth asteroids and Mars. This evolved capability will offer large volume for science missions and payloads, will be modular and flexible, and will be right-sized for mission requirements.

Orion Core Stage & Booster Offload, Move to HIF

NASA Image and Video Library

2014-03-04

CAPE CANAVERAL, Fla. – The core booster for the United Launch Alliance Delta IV heavy for NASA’s upcoming Exploration Flight Test-1, or EFT-1, mission with the Orion spacecraft, was transported to the Horizontal Integration Facility, or HIF, at Space Launch Complex 37 on Cape Canaveral Air Force Station in Florida. The core booster and starboard booster arrived by barge at the U.S. Army Outpost wharf at Port Canaveral. The port booster and the upper stage are planned to be shipped to Cape Canaveral in April. At the HIF, all three boosters will be processed and checked out before being moved to the nearby launch pad and hoisted into position. During the EFT-1 mission, Orion will travel farther into space than any human spacecraft has gone in more than 40 years. The data gathered during the flight will influence design decisions, validate existing computer models and innovative new approaches to space systems development, as well as reduce overall mission risks and costs for later Orion flights. Liftoff of Orion on EFT-1 is planned for fall 2014. Photo credit: NASA/Kim Shiflett

Orion Core Stage & Booster Offload, Move to HIF

NASA Image and Video Library

2014-03-04

CAPE CANAVERAL, Fla. – A barge arrives at the U.S. Army Outpost wharf at Port Canaveral in Florida, carrying two of the three United Launch Alliance Delta IV heavy boosters for NASA’s upcoming Exploration Flight Test-1, or EFT-1, mission with the Orion spacecraft. The core booster and starboard booster will be offloaded and then transported to the Horizontal Integration Facility, or HIF, at Space Launch Complex 37 on Cape Canaveral Air Force Station. The port booster and the upper stage are planned to be shipped to Cape Canaveral in April. At the HIF, all three boosters will be processed and checked out before being moved to the nearby launch pad and hoisted into position. During the EFT-1 mission, Orion will travel farther into space than any human spacecraft has gone in more than 40 years. The data gathered during the flight will influence design decisions, validate existing computer models and innovative new approaches to space systems development, as well as reduce overall mission risks and costs for later Orion flights. Liftoff of Orion on EFT-1 is planned for fall 2014. Photo credit: NASA/Kim Shiflett

Orion Core Stage & Booster Offload, Move to HIF

NASA Image and Video Library

2014-03-04

CAPE CANAVERAL, Fla. – Two of the three United Launch Alliance Delta IV heavy boosters for NASA’s upcoming Exploration Flight Test-1, or EFT-1, mission with the Orion spacecraft, have arrived by barge at the U.S. Army Outpost wharf at Port Canaveral in Florida. The core booster and starboard booster will be offloaded and then transported to the Horizontal Integration Facility, or HIF, at Space Launch Complex 37 on Cape Canaveral Air Force Station. The port booster and the upper stage are planned to be shipped to Cape Canaveral in April. At the HIF, all three boosters will be processed and checked out before being moved to the nearby launch pad and hoisted into position. During the EFT-1 mission, Orion will travel farther into space than any human spacecraft has gone in more than 40 years. The data gathered during the flight will influence design decisions, validate existing computer models and innovative new approaches to space systems development, as well as reduce overall mission risks and costs for later Orion flights. Liftoff of Orion on EFT-1 is planned for fall 2014. Photo credit: NASA/Kim Shiflett

Orion Core Stage & Booster Offload, Move to HIF

NASA Image and Video Library

2014-03-04

CAPE CANAVERAL, Fla. – Two of the three United Launch Alliance Delta IV heavy boosters for NASA’s upcoming Exploration Flight Test-1, or EFT-1, mission with the Orion spacecraft, arrived by barge at the U.S. Army Outpost wharf at Port Canaveral in Florida. The core booster and starboard booster were offloaded and are being transported to the Horizontal Integration Facility, or HIF, at Space Launch Complex 37 on Cape Canaveral Air Force Station. The port booster and the upper stage are planned to be shipped to Cape Canaveral in April. At the HIF, all three boosters will be processed and checked out before being moved to the nearby launch pad and hoisted into position. During the EFT-1 mission, Orion will travel farther into space than any human spacecraft has gone in more than 40 years. The data gathered during the flight will influence design decisions, validate existing computer models and innovative new approaches to space systems development, as well as reduce overall mission risks and costs for later Orion flights. Liftoff of Orion on EFT-1 is planned for fall 2014. Photo credit: NASA/Kim Shiflett

Orion Core Stage & Booster Offload, Move to HIF

NASA Image and Video Library

2014-03-04

CAPE CANAVERAL, Fla. – Two of the three United Launch Alliance Delta IV heavy boosters for NASA’s upcoming Exploration Flight Test-1, or EFT-1, mission with the Orion spacecraft, arrived by barge at the U.S. Army Outpost wharf at Port Canaveral in Florida. The core booster and starboard booster have been offloaded and will be transported to the Horizontal Integration Facility, or HIF, at Space Launch Complex 37 on Cape Canaveral Air Force Station. The port booster and the upper stage are planned to be shipped to Cape Canaveral in April. At the HIF, all three boosters will be processed and checked out before being moved to the nearby launch pad and hoisted into position. During the EFT-1 mission, Orion will travel farther into space than any human spacecraft has gone in more than 40 years. The data gathered during the flight will influence design decisions, validate existing computer models and innovative new approaches to space systems development, as well as reduce overall mission risks and costs for later Orion flights. Liftoff of Orion on EFT-1 is planned for fall 2014. Photo credit: NASA/Kim Shiflett

Improved Testing Capability and Adaptability Through the Use of Wireless Sensors

NASA Technical Reports Server (NTRS)

Solano, Wanda M.

2003-01-01

From the first Saturn V rocket booster (S-II-T) testing in 1966 and the routine Space Shuttle Main Engine (SSME) testing beginning in 1975, to more recent test programs such as the X-33 Aerospike Engine, the Integrated Powerhead Development (IPD) program, and the Hybrid Sounding Rocket (HYSR), Stennis Space Center (SSC) continues to be a premier location for conducting large-scale testing. Central to each test program is the capability for sensor systems to deliver reliable measurements and high quality data, while also providing a means to monitor the test stand area to the highest degree of safety and sustainability. Sensor wiring is routed along piping and through cable trenches, making its way from the engine test area, through the test stand area and to the signal conditioning building before final transfer to the test control center. When sensor requirements lie outside the reach of the routine sensor cable routing, the use of wireless sensor networks becomes particularly attractive due to their versatility and ease of installation. As part of an on-going effort to enhance the testing capabilities of Stennis Space Center, the Test Technology and Development group has found numerous applications for its sensor-adaptable wireless sensor suite. While not intended for critical engine measurements or control loops, in-house hardware and software development of the sensor suite can provide improved testing capability for a range of applications including the safety monitoring of propellant storage barrels and as an experimental test-bed for embedded health monitoring paradigms.

Using Growth Curves To Determine the Timing of the Booster Sessions.

ERIC Educational Resources Information Center

Hennessy, Michael; Bolan, Gail A.; Hoxworth, Tamara; Iatesta, Michael; Rhodes, Fen; Zenilman, Jonathan M.

1999-01-01

Demonstrates an application of a method for using growth curves to determine the timing of booster sessions to reinforce the cognitive messages or behavior changes of interventions. Uses data from a multisite randomized experiment that compared three counseling and testing methods for preventing sexual disease transmission. Presents…

Study of solid rocket motors for a space shuttle booster. Appendix B: Prime item development specification

NASA Technical Reports Server (NTRS)

1972-01-01

The specifications for the performance, design, development, and test requirements of the P2-156, S3-156, and S6-120 space shuttle booster solid rocket motors are presented. The applicable documents which form a part of the specifications are listed.

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.

Surface pressure and inviscid flow field properties McDonnell-Douglas booster nominal Mach number of 8, volume 3

NASA Technical Reports Server (NTRS)

Matthews, R. K.; Martindale, W. R.; Warmbrod, J. D.

1972-01-01

The results are presented of a wind tunnel test program to determine surface pressures and flow field properties on the space shuttle booster configuration. The tests were conducted in September 1971. Data were obtained at a nominal Mach number of 8 at angles of attack of 40 and 50 deg and at a free stream unit Reynolds number of 3.7 million per foot.

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.

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.

The High Altitude Balloon Experiment demonstration of acquisition, tracking, and pointing technologies (HABE-ATP)

NASA Astrophysics Data System (ADS)

Dimiduk, D.; Caylor, M.; Williamson, D.; Larson, L.

1995-01-01

The High Altitude Balloon Experiment demonstration of Acquisition, Tracking, and Pointing (HABE-ATP) is a system built around balloon-borne payload which is carried to a nominal 26-km altitude. The goal is laser tracking thrusting theater and strategic missiles, and then pointing a surrogate laser weapon beam, with performance levels end a timeline traceable to operational laser weapon system requirements. This goal leads to an experiment system design which combines hardware from many technology areas: an optical telescope and IR sensors; an advanced angular inertial reference; a flexible multi-level of actuation digital control system; digital tracking processors which incorporate real-time image analysis and a pulsed, diode-pumped solid state tracking laser. The system components have been selected to meet the overall experiment goals of tracking unmodified boosters at 50- 200 km range. The ATP system on HABE must stabilize and control a relative line of sight between the platform and the unmodified target booster to a 1 microrad accuracy. The angular pointing reference system supports both open loop and closed loop track modes; GPS provides absolute position reference. The control system which positions the line of sight for the ATP system must sequence through accepting a state vector handoff, closed-loop passive IR acquisition, passive IR intermediate fine track, active fine track, and then finally aimpoint determination and maintenance modes. Line of sight stabilization to fine accuracy levels is accomplished by actuating wide bandwidth fast steering mirrors (FSM's). These control loops off-load large-amplitude errors to the outer gimbal in order to remain within the limited angular throw of the FSM's. The SWIR acquisition and MWIR intermediate fine track sensors (both PtSi focal planes) image the signature of the rocket plume. After Hard Body Handover (HBHO), active fine tracking is conducted with a visible focal plane viewing the laser-illuminated target rocket body. The track and fire control performance must be developed to the point that an aimpoint can be selected, maintained, and then track performance scored with a low-power 'surrogate' weapon beam. Extensive instrumentation monitors not only the optical sensors and the video data, but all aspects of each of the experiment subsystems such as the control system, the experiment flight vehicle, and the tracker. Because the system is balloon-borne and recoverable, it is expected to fly many times during its development program.

Launch Pad Activities

NASA Image and Video Library

1959-09-08

Big Joe Capsule Launch Pad Activities: This film covers both the Big Joe and a Little Joe Project Mercury flight test with a research and development version of the Mercury capsule. Big Joe was an Atlas missile that successfully launched a boilerplate model of the Mercury capsule on September 9, 1959. The lower half of the capsule was created at NASA Lewis. The scenes include coverage of the assembly and erection of the boosters, delivery of the capsules, mating of the capsules to the boosters, prelaunch views of the capsule and boosters on launchers, mission control, the launches, and recovery.

Liquid Rocket Booster (LRB) for the Space Transportation System (STS) systems study, volume 2

NASA Technical Reports Server (NTRS)

1989-01-01

The Liquid Rocket Booster (LRB) Systems Definition Handbook presents the analyses and design data developed during the study. The Systems Definition Handbook (SDH) contains three major parts: the LRB vehicles definition; the Pressure-Fed Booster Test Bed (PFBTB) study results; and the ALS/LRB study results. Included in this volume are the results of all trade studies; final configurations with supporting rationale and analyses; technology assessments; long lead requirements for facilities, materials, components, and subsystems; operational requirements and scenarios; and safety, reliability, and environmental analyses.

From orbital debris capture systems through internal combustion engines on Mars

NASA Technical Reports Server (NTRS)

1991-01-01

The investigation and conceptualization of an orbital debris collector was the primary area of design. In addition, an alternate structural design for Space Station Freedom and systems supporting resource utilization at Mars and the moon were studied. Hardware for production of oxygen from simulate Mars atmosphere was modified to permit more reliable operation at low pressures (down to 10 mb). An internal combustion engine was altered to study how Mars atmosphere could be used as a diluent to control combustion temperatures and avoid excess Mars propellant production requirements that would result from either methane-rich or oxygen-rich, methane-oxygen combustion. An elastic loop traction system that could be used for lunar construction vehicles was refined to permit testing. A parabolic heat rejection radiator system was designed and built to determine whether it was capable of increasing heat rejection rates during lunar daytime operation. In addition, an alternate space station truss design, utilizing a pre-integrated concept, was studied and found to reduce estimate extravehicular activity (EVA) time and increase the structural integrity when compared to the original Warren truss concept. An orbital-debris-capturing spacecraft design which could be mated with the Orbital Maneuvering Vehicle was studied. The design identified Soviet C-1B boosters as the best targets of opportunity in Earth orbits between an altitude of 900 km and 1100 km and at an inclination of 82.9 deg. A dual robot pallet, which could be spun to match the tumbling rate of the C-1B booster, was developed as the conceptual design.

Solid rocket booster performance evaluation model. Volume 1: Engineering description

NASA Technical Reports Server (NTRS)

1974-01-01

The space shuttle solid rocket booster performance evaluation model (SRB-II) is made up of analytical and functional simulation techniques linked together so that a single pass through the model will predict the performance of the propulsion elements of a space shuttle solid rocket booster. The available options allow the user to predict static test performance, predict nominal and off nominal flight performance, and reconstruct actual flight and static test performance. Options selected by the user are dependent on the data available. These can include data derived from theoretical analysis, small scale motor test data, large motor test data and motor configuration data. The user has several options for output format that include print, cards, tape and plots. Output includes all major performance parameters (Isp, thrust, flowrate, mass accounting and operating pressures) as a function of time as well as calculated single point performance data. The engineering description of SRB-II discusses the engineering and programming fundamentals used, the function of each module, and the limitations of each module.

First Test Results of the bERLinPro 2-cell Booster Cavities

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

Burrill, Andrew; Anders, W.; Frahm, A.

2015-09-01

The bERLinPro Energy Recovery Linac (ERL) is currently being built at Helmholtz-Zentrum Berlin in order to study the physics of operating a high-current, a 100 mA, 50 MeV ERL utilizing all SRF cavity technology. This machine will utilize three unique SRF cryomodules for the photoinjector, booster and linac cryomodules respectively. The focus of this paper will be on the cavities contained within the booster cryomodule. Here there will be three 2-cell SRF cavities, based on the original design by Cornell University, but optimized to meet the needs of the project. All of the cavity fabrication, processing and testing was carriedmore » out at Jefferson Laboratory, where 4 cavities were produced, and the 3 cavities with the best RF performance were fitted with helium vessels for installation in the cryomodule. This paper will report on the test results of the cavities as measured in the vertical testing dewar at JLab after fabrication and again after outfitting with the helium vessels.« less

Assessing immune competence in pigs by immunization with tetanus toxoid.

PubMed

Gimsa, U; Tuchscherer, A; Gimsa, J; Tuchscherer, M

2018-01-01

Immune competence can be tested by challenging organisms with a set of infectious agents. However, disease control requirements impose restrictions on the infliction of infections upon domestic pigs. Alternatively, vaccinations induce detectable immune responses that reflect immune competence. Here, we tested this approach with tetanus toxoid (TT) in young domestic pigs. To optimize the vaccination protocol, we immunized the pigs with a commercial TT vaccine at the age of 21 or 35 days. Booster immunizations were performed either 14 or 21 days later. TT-specific antibodies in plasma as well as lymphoproliferative responses were determined both 7 and 14 days after booster immunization using ELISA and lymphocyte transformation tests, respectively. In addition, general IgG and IgM plasma concentrations and mitogen-induced proliferation were measured. The highest TT-specific antibody responses were detected when blood samples were collected 1 week after a booster immunization conducted 21 days after primary immunization. The pigs' age at primary immunization did not have a significant influence on TT-specific antibody responses. Similarly, the TT-specific proliferative responses were highest when blood samples were collected 1 week after booster immunization, while age and time of primary and booster immunization were irrelevant in our setup. While general IgG and IgM plasma levels were highly age dependent, there were no significant age effects for TT-specific immune responses. In addition, mitogen-induced proliferation was independent of immunization as well as blood sampling protocols. In summary, our model of TT vaccination provides an interesting approach for the assessment of immune competence in young pigs. The detected vaccination effects were not biased by age, even though our data were acquired from immune systems that were under development during our tests.

Recession Curve Generation for the Space Shuttle Solid Rocket Booster Thermal Protection System Coatings

NASA Technical Reports Server (NTRS)

Kanner, Howard S.; Stuckey, C. Irvin; Davis, Darrell W.; Davis, Darrell (Technical Monitor)

2002-01-01

Ablatable Thermal Protection System (TPS) coatings are used on the Space Shuttle Vehicle Solid Rocket Boosters in order to protect the aluminum structure from experiencing excessive temperatures. The methodology used to characterize the recession of such materials is outlined. Details of the tests, including the facility, test articles and test article processing are also presented. The recession rates are collapsed into an empirical power-law relation. A design curve is defined using a 95-percentile student-t distribution. based on the nominal results. Actual test results are presented for the current acreage TPS material used.

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

NASA Technical Reports Server (NTRS)

Daileda, J. J.

1976-01-01

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

Hybrid Propulsion Demonstration Program 250K Hybrid Motor

NASA Technical Reports Server (NTRS)

Story, George; Zoladz, Tom; Arves, Joe; Kearney, Darren; Abel, Terry; Park, O.

2003-01-01

The Hybrid Propulsion Demonstration Program (HPDP) program was formed to mature hybrid propulsion technology to a readiness level sufficient to enable commercialization for various space launch applications. The goal of the HPDP was to develop and test a 250,000 pound vacuum thrust hybrid booster in order to demonstrate hybrid propulsion technology and enable manufacturing of large hybrid boosters for current and future space launch vehicles. The HPDP has successfully conducted four tests of the 250,000 pound thrust hybrid rocket motor at NASA's Stennis Space Center. This paper documents the test series.

Update on Risk Reduction Activities for a Liquid Advanced Booster for NASA's Space Launch System

NASA Technical Reports Server (NTRS)

Crocker, Andrew M.; Doering, Kimberly B; Meadows, Robert G.; Lariviere, Brian W.; Graham, Jerry B.

2015-01-01

The stated goals of NASA's Research Announcement for the Space Launch System (SLS) Advanced Booster Engineering Demonstration and/or Risk Reduction (ABEDRR) are to reduce risks leading to an affordable Advanced Booster that meets the evolved capabilities of SLS; and enable competition by mitigating targeted Advanced Booster risks to enhance SLS affordability. Dynetics, Inc. and Aerojet Rocketdyne (AR) formed a team to offer a wide-ranging set of risk reduction activities and full-scale, system-level demonstrations that support NASA's ABEDRR goals. For NASA's SLS ABEDRR procurement, Dynetics and AR formed a team to offer a series of full-scale risk mitigation hardware demonstrations for an affordable booster approach that meets the evolved capabilities of the SLS. To establish a basis for the risk reduction activities, the Dynetics Team developed a booster design that takes advantage of the flight-proven Apollo-Saturn F-1. Using NASA's vehicle assumptions for the SLS Block 2, a two-engine, F-1-based booster design delivers 150 mT (331 klbm) payload to LEO, 20 mT (44 klbm) above NASA's requirements. This enables a low-cost, robust approach to structural design. During the ABEDRR effort, the Dynetics Team has modified proven Apollo-Saturn components and subsystems to improve affordability and reliability (e.g., reduce parts counts, touch labor, or use lower cost manufacturing processes and materials). The team has built hardware to validate production costs and completed tests to demonstrate it can meet performance requirements. State-of-the-art manufacturing and processing techniques have been applied to the heritage F-1, resulting in a low recurring cost engine while retaining the benefits of Apollo-era experience. NASA test facilities have been used to perform low-cost risk-reduction engine testing. In early 2014, NASA and the Dynetics Team agreed to move additional large liquid oxygen/kerosene engine work under Dynetics' ABEDRR contract. Also led by AR, the objectives of this work are to demonstrate combustion stability and measure performance of a 500,000 lbf class Oxidizer-Rich Staged Combustion (ORSC) cycle main injector. A trade study was completed to investigate the feasibility, cost effectiveness, and technical maturity of a domestically produced Atlas V engine that could also potentially satisfy NASA SLS payload-to-orbit requirements via an advanced booster application. Engine physical dimensions and performance parameters resulting from this study provide the system level requirements for the ORSC risk reduction test article. The test article is scheduled to complete critical design review this fall and begin testing in 2017. Dynetics has also designed, developed, and built innovative tank and structure assemblies using friction stir welding to leverage recent NASA investments in manufacturing tools, facilities, and processes, significantly reducing development and recurring costs. The full-scale cryotank assembly was used to verify the structural design and prove affordable processes. Dynetics performed hydrostatic and cryothermal proof tests on the assembly to verify the assembly meets performance requirements. This paper will discuss the ABEDRR engine task and structures task achievements to date and the remaining effort through the end of the contract.

United Space Alliance waits to test its one-man submarine for SRB retrieval

NASA Technical Reports Server (NTRS)

2000-01-01

The one-man submarine dubbed DeepWorker 2000 sits on the deck of Liberty Star, one of two KSC solid rocket booster recovery ships. The sub is being tested on its ability to duplicate the sometimes hazardous job United Space Alliance (USA) divers perform to recover the expended boosters in the ocean after a launch. The boosters splash down in an impact area about 140 miles east of Jacksonville and after recovery are towed back to KSC for refurbishment by the specially rigged recovery ships. DeepWorker 2000 was built by Nuytco Research Ltd., North Vancouver, British Columbia. It is 8.25 feet long, 5.75 feet high, and weighs 3,800 pounds. USA is a prime contractor to NASA for the Space Shuttle program.

Space Shuttle Projects

NASA Image and Video Library

1979-07-13

This is a photograph of the solid rocket booster's (SRB's) Qualification Motor-1 (QM-1) being prepared for a static firing in a test stand at the Morton Thiokol Test Site in Wasatch, Utah, showing the aft end of the booster. The twin boosters provide the majority of thrust for the first two minutes of flight, about 5.8 million pounds, augmenting the Shuttle's main propulsion system during liftoff. The major design drivers for the solid rocket motors (SRM's) were high thrust and reuse. The desired thrust was achieved by using state-of-the-art solid propellant and by using a long cylindrical motor with a specific core design that allows the propellant to burn in a carefully controlled marner. Under the direction of the Marshall Space Flight Center, the SRM's are provided by the Morton Thiokol Corporation.

SLS Pathfinder Segments Car Train Departure

NASA Image and Video Library

2016-03-02

An Iowa Northern locomotive, contracted by Goodloe Transportation of Chicago, travels along the NASA railroad bridge over the Indian River north of Kennedy Space Center, carrying one of two containers on a railcar for transport to the NASA Jay Jay railroad yard. The containers held two pathfinders, or test versions, of solid rocket booster segments for NASA’s Space Launch System rocket that were delivered to the Rotation, Processing and Surge Facility (RPSF). Inside the RPSF, the Ground Systems Development and Operations Program and Jacobs Engineering, on the Test and Operations Support Contract, will conduct a series of lifts, moves and stacking operations using the booster segments, which are inert, to prepare for Exploration Mission-1, deep-space missions and the journey to Mars. The pathfinder booster segments are from Orbital ATK in Utah.

SLS Pathfinder Segments Car Train Departure

NASA Image and Video Library

2016-03-02

An Iowa Northern locomotive, conracted by Goodloe Transportation of Chicago, travels along the NASA railroad bridge over the Indian River north of Kennedy Space Center, with two containers on railcars for transport to the NASA Jay Jay railroad yard. The containers held two pathfinders, or test versions, of solid rocket booster segments for NASA’s Space Launch System rocket that were delivered to the Rotation, Processing and Surge Facility (RPSF). Inside the RPSF, the Ground Systems Development and Operations Program and Jacobs Engineering, on the Test and Operations Support Contract, will conduct a series of lifts, moves and stacking operations using the booster segments, which are inert, to prepare for Exploration Mission-1, deep-space missions and the journey to Mars. The pathfinder booster segments are from Orbital ATK in Utah.

SLS Pathfinder Segments Car Train Departure

NASA Image and Video Library

2016-03-02

An Iowa Northern locomotive, contracted by Goodloe Transportation of Chicago, approaches the raised span of the NASA railroad bridge to continue over the Indian River north of Kennedy Space Center with two containers on railcars for storage at the NASA Jay Jay railroad yard. The containers held two pathfinders, or test versions, of solid rocket booster segments for NASA’s Space Launch System rocket that were delivered to the Rotation, Processing and Surge Facility (RPSF). Inside the RPSF, the Ground Systems Development and Operations Program and Jacobs Engineering, on the Test and Operations Support Contract, will conduct a series of lifts, moves and stacking operations using the booster segments, which are inert, to prepare for Exploration Mission-1, deep-space missions and the journey to Mars. The pathfinder booster segments are from Orbital ATK in Utah.

SLS Pathfinder Segments Car Train Departure

NASA Image and Video Library

2016-03-02

An Iowa Northern locomotive, contracted by Goodloe Transportation of Chicago, travels along the NASA railroad bridge over the Indian River north of Kennedy Space Center, carrying one of two containers on a railcar for transport to the NASA Jay Jay railroad yard near the center. The containers held two pathfinders, or test versions, of solid rocket booster segments for NASA’s Space Launch System rocket that were delivered to the Rotation, Processing and Surge Facility (RPSF). Inside the RPSF, the Ground Systems Development and Operations Program and Jacobs Engineering, on the Test and Operations Support Contract, will conduct a series of lifts, moves and stacking operations using the booster segments, which are inert, to prepare for Exploration Mission-1, deep-space missions and the journey to Mars. The pathfinder booster segments are from Orbital ATK in Utah.

SLS Pathfinder Segments Car Train Departure

NASA Image and Video Library

2016-03-02

An Iowa Northern locomotive, contracted by Goodloe Transportation of Chicago, continues along the NASA railroad bridge over the Indian River north of Kennedy Space Center, carrying one of two containers on a railcar for transport to the NASA Jay Jay railroad yard. The containers held two pathfinders, or test versions, of solid rocket booster segments for NASA’s Space Launch System rocket that were delivered to the Rotation, Processing and Surge Facility (RPSF). Inside the RPSF, the Ground Systems Development and Operations Program and Jacobs Engineering, on the Test and Operations Support Contract, will conduct a series of lifts, moves and stacking operations using the booster segments, which are inert, to prepare for Exploration Mission-1, deep-space missions and the journey to Mars. The pathfinder booster segments are from Orbital ATK in Utah.

KENNEDY SPACE CENTER, FLA. - At the Rotation, Processing and Surge Facility stand a mockup of two segments of a solid rocket booster (SRB) being used to test the feasibility of a vertical SRB propellant grain inspection, required as part of safety analysis.

NASA Image and Video Library

2003-09-11

KENNEDY SPACE CENTER, FLA. - At the Rotation, Processing and Surge Facility stand a mockup of two segments of a solid rocket booster (SRB) being used to test the feasibility of a vertical SRB propellant grain inspection, required as part of safety analysis.

KENNEDY SPACE CENTER, FLA. - Framed between palm trees, solid rocket boosters loom above the Mobile Launcher Platform (MLP) as the crawler transporter slowly moves it along the crawlerway. The journey is in support of engineering analysis vibration tests on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

NASA Image and Video Library

2003-11-17

KENNEDY SPACE CENTER, FLA. - Framed between palm trees, solid rocket boosters loom above the Mobile Launcher Platform (MLP) as the crawler transporter slowly moves it along the crawlerway. The journey is in support of engineering analysis vibration tests on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

NASA's NB-52B carrier aircraft rolls down a taxiway with the X-43A hypersonic research aircraft and its modified Pegasus® booster rocket attached to a pylon under its right wing.

NASA Image and Video Library

2001-03-15

As part of a combined systems test conducted by NASA Dryden Flight Research Center, NASA's NB-52B carrier aircraft rolls down a taxiway at Edwards Air Force Base with the X-43A hypersonic research aircraft and its modified Pegasus® booster rocket attached to a pylon under its right wing. The taxi test was one of the last major milestones in the Hyper-X research program before the first X-43A flight. The X-43A flights will be the first actual flight tests of an aircraft powered by a revolutionary supersonic-combustion ramjet ("scramjet") engine capable of operating at hypersonic speeds (above Mach 5, or five times the speed of sound). The 12-foot, unpiloted research vehicle was developed and built by MicroCraft Inc., Tullahoma, Tenn., under NASA contract. The booster was built by Orbital Sciences Corp., Dulles, Va. After being air-launched from NASA's venerable NB-52 mothership, the booster will accelerate the X-43A to test speed and altitude. The X-43A will then separate from the rocket and fly a pre-programmed trajectory, conducting aerodynamic and propulsion experiments until it descends into the Pacific Ocean. Three research flights are planned, two at Mach 7 and one at Mach 10.

KENNEDY SPACE CENTER, FLA. - The crawler transporter slowly moves the Mobile Launcher Platform (MLP), carrying a set of twin solid rocket boosters, away from the Vehicle Assembly Building (VAB) in support of engineering analysis vibration tests on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

NASA Image and Video Library

2003-11-17

KENNEDY SPACE CENTER, FLA. - The crawler transporter slowly moves the Mobile Launcher Platform (MLP), carrying a set of twin solid rocket boosters, away from the Vehicle Assembly Building (VAB) in support of engineering analysis vibration tests on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

KENNEDY SPACE CENTER, FLA. - The crawler transporter has slowly moved the Mobile Launcher Platform (MLP), carrying a set of twin solid rocket boosters, out of the Vehicle Assembly Building (VAB) in support of engineering analysis vibration tests on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

NASA Image and Video Library

2003-11-17

KENNEDY SPACE CENTER, FLA. - The crawler transporter has slowly moved the Mobile Launcher Platform (MLP), carrying a set of twin solid rocket boosters, out of the Vehicle Assembly Building (VAB) in support of engineering analysis vibration tests on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

KENNEDY SPACE CENTER, FLA. - The crawler transporter is slowly moving the Mobile Launcher Platform (MLP), carrying a set of twin solid rocket boosters, out of the Vehicle Assembly Building (VAB) in support of engineering analysis vibration tests on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

NASA Image and Video Library

2003-11-17

KENNEDY SPACE CENTER, FLA. - The crawler transporter is slowly moving the Mobile Launcher Platform (MLP), carrying a set of twin solid rocket boosters, out of the Vehicle Assembly Building (VAB) in support of engineering analysis vibration tests on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

KENNEDY SPACE CENTER, FLA. - The crawler transporter slowly moves the Mobile Launcher Platform (MLP), carrying a set of twin solid rocket boosters, out of the Vehicle Assembly Building (VAB) in support of engineering analysis vibration tests on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

NASA Image and Video Library

2003-11-17

KENNEDY SPACE CENTER, FLA. - The crawler transporter slowly moves the Mobile Launcher Platform (MLP), carrying a set of twin solid rocket boosters, out of the Vehicle Assembly Building (VAB) in support of engineering analysis vibration tests on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

Space shuttle: Longitudinal and lateral aerodynamic characteristics of the 0.0035-scale GD/C aerospace booster (B-15B-1)

NASA Technical Reports Server (NTRS)

Debevoise, J. M.; Mcginnis, R. F.

1972-01-01

Force tests on a 0.0035-scale model of the General Dynamics/Convair space shuttle B-15B-1 booster were conducted in the MSFC trisonic wind tunnel during February and March 1971. Longitudinal and lateral characteristics were obtained at Mach numbers from 0.6 to 4.96. The configuration tested had a low delta wing, all-movable canard controls of delta planform, and a single vertical tail. Most of the test was devoted to obtaining data relevant to the transition from atmospheric reentry to subsonic cruise. In that portion of the test the angles of attack ranged from 6 degrees to 60 degrees, and yaw runs were made at angles of attack of 15 and 35 degrees. The rest of the test was devoted to obtaining booster-alone buildup data relevant to the launch phase. For the launch phase, the Mach number range was from 0.6 to 2.0, the angles of attack were from -10 to +10 degrees, and yaw runs were made at zero angle of attack.

Aerospace Plane Technology: Research and Development Efforts in Japan and Australia

DTIC Science & Technology

1991-10-01

However, only with the develop- Aerospace Planes ment of better test facility instruments and more trained personnel, together with the renovation and...necessary. Such a rocket booster (the H-IID) would be one of the largest launchers in the world after the Soviet Energia booster and U.S. Titan IV launch

Space shuttle: Static stability and control investigation of the NR-GD/C delta wing booster (B-15B-1) and a Reusable Nuclear Stage (RNS) M = 0.6 - 4.96

NASA Technical Reports Server (NTRS)

Allen, E. C.

1971-01-01

Experimental aerodynamic investigations were made in the NASA/MSFC 14 x 14 inch trisonic wind tunnel on a NR-GD/C 0.0031 scale model delta wing booster (B-15B-1) and reusable nuclear stage (RNS). Three basic configurations were tested: (1) the B-15B-1 booster alone, (2) the RNS alone, and (3) the booster with the RNS mounted piggyback. Six component force and moment data were recorded for each of these configurations over an angle of attack range from -16 deg to 4 deg at zero degrees sideslip, and over an angle of sideslip range from -10 deg to 10 deg at zero and -6 degrees angle of attack. The configurations were tested over a Mach number range of 0.6 to 5.0 with a nominal Reynolds number of 6.5 million per foot except for Mach 1.2 and 3.0 where the Reynolds number were 12.4 million and 4.4 million per foot respectively.

KENNEDY SPACE CENTER, FLA. - Like candles embedded in a sculptured “cake,” the Mobile Launcher Platform (MLP) number 3 with twin solid rocket boosters bolted to it inches along the crawlerway at various speeds up to 1 mph in an effort to achieve vibration data gathering goals. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

NASA Image and Video Library

2003-11-21

KENNEDY SPACE CENTER, FLA. - Like candles embedded in a sculptured “cake,” the Mobile Launcher Platform (MLP) number 3 with twin solid rocket boosters bolted to it inches along the crawlerway at various speeds up to 1 mph in an effort to achieve vibration data gathering goals. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

Economics of the solid rocket booster for space shuttle

NASA Technical Reports Server (NTRS)

Rice, W. C.

1979-01-01

The paper examines economics of the solid rocket booster for the Space Shuttle. Costs have been held down by adapting existing technology to the 146 in. SRB selected, with NASA reducing the cost of expendables and reusing the expensive nonexpendable hardware. Drop tests of Titan III motor cases and nozzles proved that boosters can survive water impact at vertical velocities of 100 ft/sec so that SRB components can be reused. The cost of expendables was minimized by selecting proven propellants, insulation, and nozzle ablatives of known costs; the propellant has the lowest available cost formulation, and low cost ablatives, such as pitch carbon fibers, will be used when available. Thus, the use of proven technology and low cost expendables will make the SRB an economical booster for the Space Shuttle.

Space shuttle phase B wind tunnel model and test information. Volume 3: Launch configuration

NASA Technical Reports Server (NTRS)

Glynn, J. L.; Poucher, D. E.

1988-01-01

Archived wind tunnel data are available for flyback booster or other alternative recoverable configurations as well as reusable orbiters studied during initial development (Phase B) of the Space Shuttle. Considerable wind tunnel data was acquired by the competing contractors and the NASA Centers for an extensive variety of configurations with an array of wing and body planforms. All contractor and NASA wind tunnel data acquired in the Phase B development have been compiled into a data base and are available for application to current winged flyback or recoverable booster aerodynamic studies. The Space Shuttle Phase B Wind Tunnel Database is structured by vehicle component and configuration type. Basic components include booster, orbiter and launch vehicle. Booster configuration types include straight and delta wings, canard, cylindrical, retroglide and twin body. Orbital configuration types include straight and delta wings, lifting body, drop tanks and double delta wings. This is Volume 3 (Part 2) of the report -- Launch Configuration -- which includes booster and orbiter components in various stacked and tandem combinations.

Test report for 120-inch-diameter Solid Rocket Booster (SRB) model tests. [floating and towing characteristics of space shuttle boosters

NASA Technical Reports Server (NTRS)

Jones, W. C.

1973-01-01

The space shuttle solid rocket boosters (SRB's) will be jettisoned to impact in the ocean within a 200-mile radius of the launch site. Tests were conducted at Long Beach, California, using a 12-inch diameter Titan 3C model to simulate the full-scale characteristics of the prototype SRB during retrieval operations. The objectives of the towing tests were to investigate and assess the following: (1) a floating and towing characteristics of the SRB; (2) need for plugging the SRB nozzle prior to tow; (3) attach point locations on the SRB; (4) effects of varying the SRB configuration; (5) towing hardware; and (6) difficulty of attaching a tow line to the SRB in the open sea. The model was towed in various sea states using four different types and varying lengths of tow line at various speeds. Three attach point locations were tested. Test data was recorded on magnetic tape for the tow line loads and for model pitch, roll, and yaw characteristics and was reduced by computer to tabular printouts and X-Y plots. Profile and movie photography provided documentary test data.

Orion Core Stage & Booster Offload, Move to HIF

NASA Image and Video Library

2014-03-04

CAPE CANAVERAL, Fla. – Two of the three United Launch Alliance Delta IV heavy boosters for NASA’s upcoming Exploration Flight Test-1, or EFT-1, mission with the Orion spacecraft, arrived by barge at the U.S. Army Outpost wharf at Port Canaveral in Florida. The core booster, shown in this photo, and starboard booster were offloaded and will be transported to the Horizontal Integration Facility, or HIF, at Space Launch Complex 37 on Cape Canaveral Air Force Station. The port booster and the upper stage are planned to be shipped to Cape Canaveral in April. At the HIF, all three boosters will be processed and checked out before being moved to the nearby launch pad and hoisted into position. During the EFT-1 mission, Orion will travel farther into space than any human spacecraft has gone in more than 40 years. The data gathered during the flight will influence design decisions, validate existing computer models and innovative new approaches to space systems development, as well as reduce overall mission risks and costs for later Orion flights. Liftoff of Orion on EFT-1 is planned for fall 2014. Photo credit: NASA/Kim Shiflett

Orion Core Stage & Booster Offload, Move to HIF

NASA Image and Video Library

2014-03-04

CAPE CANAVERAL, Fla. – Two of the three United Launch Alliance Delta IV heavy boosters for NASA’s upcoming Exploration Flight Test-1, or EFT-1, mission with the Orion spacecraft, have arrived by barge at the U.S. Army Outpost wharf at Port Canaveral in Florida. The core booster and starboard booster are being offloaded and will be transported to the Horizontal Integration Facility, or HIF, at Space Launch Complex 37 on Cape Canaveral Air Force Station. The port booster and the upper stage are planned to be shipped to Cape Canaveral in April. At the HIF, all three boosters will be processed and checked out before being moved to the nearby launch pad and hoisted into position. During the EFT-1 mission, Orion will travel farther into space than any human spacecraft has gone in more than 40 years. The data gathered during the flight will influence design decisions, validate existing computer models and innovative new approaches to space systems development, as well as reduce overall mission risks and costs for later Orion flights. Liftoff of Orion on EFT-1 is planned for fall 2014. Photo credit: NASA/Kim Shiflett

Orion Core Stage & Booster Offload, Move to HIF

NASA Image and Video Library

2014-03-04

CAPE CANAVERAL, Fla. – Two of the three United Launch Alliance Delta IV heavy boosters for NASA’s upcoming Exploration Flight Test-1, or EFT-1, mission with the Orion spacecraft, arrived by barge at the U.S. Army Outpost wharf at Port Canaveral in Florida. The core booster, shown in this photo, and starboard booster were offloaded and transported to the Horizontal Integration Facility, or HIF, at Space Launch Complex 37 on Cape Canaveral Air Force Station. The port booster and the upper stage are planned to be shipped to Cape Canaveral in April. At the HIF, all three boosters will be processed and checked out before being moved to the nearby launch pad and hoisted into position. During the EFT-1 mission, Orion will travel farther into space than any human spacecraft has gone in more than 40 years. The data gathered during the flight will influence design decisions, validate existing computer models and innovative new approaches to space systems development, as well as reduce overall mission risks and costs for later Orion flights. Liftoff of Orion on EFT-1 is planned for fall 2014. Photo credit: NASA/Kim Shiflett

The association between booster seat use and risk of death among motor vehicle occupants aged 4-8: a matched cohort study.

PubMed

Rice, T M; Anderson, C L; Lee, A S

2009-12-01

To estimate the effectiveness of booster seats and of seatbelts in reducing the risk of child death during traffic collisions and to examine possible effect modification by various collision and vehicle characteristics. A matched cohort study was conducted using data from the Fatality Analysis Reporting System. Death risk ratios were estimated with conditional Poisson regression, bootstrapped coefficient standard errors, and multiply imputed missing values using chained equations. Estimated death risk ratios for booster seats used with seatbelts were 0.33 (95% CI 0.28 to 0.40) for children age 4-5 years and 0.45 (0.31 to 0.63) for children aged 6-8 years (Wald test of homogeneity p<0.005). The estimated risk ratios for seatbelt used alone were similar for the two age groups, 0.37 (0.32 to 0.43) and 0.39 (0.34 to 0.44) for ages 4-5 and 6-8, respectively (Wald p = 0.61). Estimated booster seat effectiveness was significantly greater for inbound seating positions (Wald p = 0.05) and during rollovers collisions (Wald p = 0.01). Significant variability in risk ratio estimates was not observed across levels of calendar year, vehicle model year, vehicle type, or land use. Seatbelts, used with or without booster seats, are highly effective in preventing death among motor vehicle occupants aged 4-8 years. Booster seats do not appear to improve the performance of seatbelts with respect to preventing death (risk ratio 0.92, 95% CI 0.79 to 1.08, comparing seatbelts with boosters to seatbelts alone), but because several studies have found that booster seats reduce non-fatal injury severity, clinicians and injury prevention specialists should continue to recommend the use of boosters to parents of young children.

Space Shuttle Solid Rocket Booster Decelerator Subsystem Drop Test 3 - Anatomy of a failure

NASA Technical Reports Server (NTRS)

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

1979-01-01

A test failure dramatically points out a design weakness or the limits of the material in the test article. In a low budget test program, with a very limited number of tests, a test failure sparks supreme efforts to investigate, analyze, and/or explain the anomaly and to improve the design such that the failure will not recur. The third air drop of the Space Shuttle Solid Rocket Booster Recovery System experienced such a dramatic failure. On air drop 3, the 54-ft drogue parachute was totally destroyed 0.7 sec after deployment. The parachute failure investigation, based on analysis of drop test data and supporting ground element test results is presented. Drogue design modifications are also discussed.

Progress on the Design of a Perpendicularly Biased 2nd Harmonic Cavity for the Fermilab Booster

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

Madrak, R. L.; Dey, J. E.; Duel, K. L.

2016-10-01

perpendicularly biased 2nd harmonic cavity is being designed and built for the Fermilab Booster. Its purpose is to flatten the bucket at injection and thus change the longitudinal beam distribution to decrease space charge effects. It can also help at extraction. The cavity frequency range is 76 – 106 MHz. The power amplifier will be built using the Y567B tetrode, which is also used for the fundamental mode cavities in the Fermilab Booster. We discuss recent progress on the cavity, the biasing solenoid design and plans for testing the tuner's garnet material

Mercury Capsule Separation Tests

NASA Image and Video Library

1960-04-01

Mercury capsule separation from Redstone booster in the Altitude Wind Tunnel (AWT): NASA Lewis conducted full-scale separation tests of the posigrade rockets that were fired after the Redstone rockets burned out. The researchers studied the effect of the posigrade rockets firing on the Redstone booster and retrograde package. This film shows the Mercury capsule being mounted to the Redstone missile model in the Altitude Wind Tunnel. The capsule's engines are fired and it horizontally separates from the Atlas. After firing the capsule swings from an overhead crane.

Cross-protection elicited by primary and booster vaccinations against Japanese encephalitis: a two-year follow-up study.

PubMed

Erra, Elina O; Askling, Helena Hervius; Yoksan, Sutee; Rombo, Lars; Riutta, Jukka; Vene, Sirkka; Lindquist, Lars; Vapalahti, Olli; Kantele, Anu

2013-12-17

The inactivated Vero cell-derived vaccine (JE-VC, IXIARO) has replaced the traditional mouse brain-derived preparations (JE-MB) in travelers' vaccinations against Japanese encephalitis. We showed recently that a single JE-VC dose efficiently boosts immunity in JE-MB-primed vaccinees, and that JE-VC elicits cross-protective immunity against non-vaccine genotypes, including the emerging genotype I. While these studies only provided short-term data, the present investigation evaluates the longevity of seroprotection in the same volunteers. The study comprised 48 travelers who had received (1) JE-VC primary series, (2) JE-MB primary series followed by a single JE-VC booster dose, or (3) JE-MB primary series and a single JE-MB booster dose. Serum samples were collected two years after the last vaccine dose, and evaluated with the plaque-reduction neutralization test against seven Japanese encephalitis virus strains representing genotypes I-IV. PRNT50 titers ≥ 10 were considered protective. Two years after the primary series with JE-VC, 87-93% of the vaccinees proved to be cross-protected against test strains representing genotypes II-IV and 73% against those of genotype I. After a single homologous or heterologous booster dose to JE-MB-primed subjects, the two-year seroprotection rates against genotype I-IV strains were 89-100%. After JE-VC primary series, seroprotection appeared to wane first against genotype I. The first booster should not be delayed beyond two years. In JE-MB-primed subjects, a single JE-VC booster provided cross-protective immunity against genotype I-IV strains in almost all vaccinees, suggesting an interval of two years or even longer for the second booster. These data further support the use of a single JE-VC dose for boosting JE-MB immunity. Copyright © 2013 The Authors. Published by Elsevier Ltd.. All rights reserved.

SLS Test Stand Site Selection

NASA Technical Reports Server (NTRS)

Crowe, Kathryn; Williams, Michael

2015-01-01

Test site selection is a critical element of the design, development and production of a new system. With the advent of the new Space Launch System (SLS), the National Aeronautics and Space Administration (NASA) had a number of test site selection decisions that needed to be made early enough in the Program to support the planned Launch Readiness Date (LRD). This case study focuses on decisions that needed to be made in 2011 and 2012 in preparation for the April 2013 DPMC decision about where to execute the Main Propulsion Test that is commonly referred to as "Green Run." Those decisions relied upon cooperative analysis between the Program, the Test Lab and Center Operations. The SLS is a human spaceflight vehicle designed to carry a crew farther into space than humans have previously flown. The vehicle consists of four parts: the crew capsule, the upper stage, the core stage, and the first stage solid rocket boosters. The crew capsule carries the astronauts, while the upper stage, the core stage, and solid rocket boosters provide thrust for the vehicle. In other words, the stages provide the "lift" part of the lift vehicle. In conjunction with the solid rocket boosters, the core stage provides the initial "get-off-the-ground" thrust to the vehicle. The ignition of the four core stage engines and two solid rocket boosters is the first step in the launch portion of the mission. The solid rocket boosters burn out after about 2 minutes of flight, and are then jettisoned. The core stage provides thrust until the vehicle reaches a specific altitude and speed, at which point the core stage is shut off and jettisoned, and the upper stage provides vehicle thrust for subsequent mission trajectories. The integrated core stage primarily consists of a liquid oxygen tank, a liquid hydrogen tank, and the four core stage engines. For the SLS program, four RS-25 engines were selected as the four core stage engines. The RS-25 engine is the same engine that was used for Space Shuttle. The test plan for the integrated core stage was broken down into several segments: Component testing, system level testing, and element level testing. In this context, components are items such as valves, controllers, sensors, etc. Systems are items such as an entire engine, a tank, or the outer stage body. The core stage itself is considered to be an element. The rocket engines are also considered an element. At the program level, it was decided to perform a single green run test on the integrated core stage prior to shipment of it to Kennedy Space Center (KSC) for use in the EM-1 test flight of the SLS vehicle. A green run test is the first live fire of the new integrated core stage and engine elements - without boosters of course. The SLS Program had to decide where to perform SLS green run testing.

Study of solid rocket motor for space shuttle booster, Volume 3: Program acquisition planning

NASA Technical Reports Server (NTRS)

1972-01-01

The program planning acquisition functions for the development of the solid propellant rocket engine for the space shuttle booster is presented. The subjects discussed are: (1) program management, (2) contracts administration, (3) systems engineering, (4) configuration management, and (5) maintenance engineering. The plans for manufacturing, testing, and operations support are included.

United Space Alliance waits to test its one-man submarine for SRB retrieval

NASA Technical Reports Server (NTRS)

2000-01-01

The one-man submarine dubbed DeepWorker 2000 sits on the deck of Liberty Star, one of two KSC solid rocket booster recovery ships. Inside the sub is the pilot, Anker Rasmussen. The sub is being tested on its ability to duplicate the sometimes hazardous job United Space Alliance (USA) divers perform to recover the expended boosters in the ocean after a launch. The boosters splash down in an impact area about 140 miles east of Jacksonville and after recovery are towed back to KSC for refurbishment by the specially rigged recovery ships. DeepWorker 2000 was built by Nuytco Research Ltd., North Vancouver, British Columbia. It is 8.25 feet long, 5.75 feet high, and weighs 3,800 pounds. USA is a prime contractor to NASA for the Space Shuttle program.

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.

An Alternative Method Of Specifying Shock Test Criteria

NASA Technical Reports Server (NTRS)

Ferebee, R. C.; Clayton, J.; Alldredge, D.; Irvine, T.

2008-01-01

Shock testing of aerospace vehicle hardware has presented many challenges over the years due to the high magnitude and short duration of the specifications. Recently, component structural failures have occurred during testing that have not manifested themselves on over 200 Space Shuttle solid rocket booster (SRB) flights (two boosters per flight). It is suspected that the method of specifying shock test criteria may be leaving important information out of the test process. The traditional test criteria specification, the shock response spectrum, can be duplicated by any number of waveforms that may not resemble the actual flight test recorded time history. One method of overcoming this limitation is described herein, which may prove useful for qualifying hardware for the upcoming Constellation Program.

SRB Processing Facilities Media Event

NASA Image and Video Library

2016-03-01

Members of the news media watch as a crane is used to move one of two pathfinders, or test versions, of solid rocket booster segments for NASA’s Space Launch System rocket to a test stand in the Rotation, Processing and Surge Facility at NASA’s Kennedy Space Center in Florida. Inside the RPSF, the Ground Systems Development and Operations Program and Jacobs Engineering, on the Test and Operations Support Contract, will prepare the booster segments, which are inert, for a series of lifts, moves and stacking operations to prepare for Exploration Mission-1, deep-space missions and the journey to Mars.

KSC-2009-6029

NASA Image and Video Library

2009-10-30

CAPE CANAVERAL, Fla. – At Hangar AF on Cape Canaveral Air Force Station in Florida, the spent first stage of NASA's Ares I-X rocket is secured in a slip. The solid rocket booster recovery ship Freedom Star recovered the booster after it splashed down in the Atlantic Ocean following its flight test. Liftoff of the 6-minute flight test was at 11:30 a.m. EDT Oct. 28. This was the first launch from Kennedy's pads of a vehicle other than the space shuttle since the Apollo Program's Saturn rockets were retired. The parts used to make the Ares I-X booster flew on 30 different shuttle missions ranging from STS-29 in 1989 to STS-106 in 2000. The data returned from more than 700 sensors throughout the rocket will be used to refine the design of future launch vehicles and bring NASA one step closer to reaching its exploration goals. For information on the Ares I-X vehicle and flight test, visit http://www.nasa.gov/aresIX. Photo credit: NASA/Kim Shiflett

KSC-2009-6024

NASA Image and Video Library

2009-10-30

CAPE CANAVERAL, Fla. – The solid rocket booster recovery ship Freedom Star, towing the spent first stage of NASA's Ares I-X rocket, passes through Port Canaveral in Florida. Following the launch of the Ares I-X flight test, the booster splashed down in the Atlantic Ocean and was recovered. Liftoff of the 6-minute flight test was at 11:30 a.m. EDT Oct. 28. This was the first launch from Kennedy's pads of a vehicle other than the space shuttle since the Apollo Program's Saturn rockets were retired. The parts used to make the Ares I-X booster flew on 30 different shuttle missions ranging from STS-29 in 1989 to STS-106 in 2000. The data returned from more than 700 sensors throughout the rocket will be used to refine the design of future launch vehicles and bring NASA one step closer to reaching its exploration goals. For information on the Ares I-X vehicle and flight test, visit http://www.nasa.gov/aresIX. Photo credit: NASA/Kim Shiflett

KSC-2009-6032

NASA Image and Video Library

2009-10-31

CAPE CANAVERAL, Fla. – At Hangar AF on Cape Canaveral Air Force Station in Florida, the spent first stage of NASA's Ares I-X rocket, secured in a slip, awaits inspection. The booster was recovered by the solid rocket booster recovery ship Freedom Star after it splashed down in the Atlantic Ocean following its flight test. Liftoff of the 6-minute flight test was at 11:30 a.m. EDT Oct. 28. This was the first launch from Kennedy's pads of a vehicle other than the space shuttle since the Apollo Program's Saturn rockets were retired. The parts used to make the Ares I-X booster flew on 30 different shuttle missions ranging from STS-29 in 1989 to STS-106 in 2000. The data returned from more than 700 sensors throughout the rocket will be used to refine the design of future launch vehicles and bring NASA one step closer to reaching its exploration goals. For information on the Ares I-X vehicle and flight test, visit http://www.nasa.gov/aresIX. Photo credit: NASA/Kim Shiflett

KSC-2009-6027

NASA Image and Video Library

2009-10-30

CAPE CANAVERAL, Fla. – The solid rocket booster recovery ship Freedom Star delivers the spent first stage of NASA's Ares I-X rocket to Hangar AF at Cape Canaveral Air Force Station in Florida. Following the launch of the Ares I-X flight test, the booster splashed down in the Atlantic Ocean and was recovered. Liftoff of the 6-minute flight test was at 11:30 a.m. EDT Oct. 28. This was the first launch from Kennedy's pads of a vehicle other than the space shuttle since the Apollo Program's Saturn rockets were retired. The parts used to make the Ares I-X booster flew on 30 different shuttle missions ranging from STS-29 in 1989 to STS-106 in 2000. The data returned from more than 700 sensors throughout the rocket will be used to refine the design of future launch vehicles and bring NASA one step closer to reaching its exploration goals. For information on the Ares I-X vehicle and flight test, visit http://www.nasa.gov/aresIX. Photo credit: NASA/Kim Shiflett

KSC-2009-6028

NASA Image and Video Library

2009-10-30

CAPE CANAVERAL, Fla. – At Hangar AF on Cape Canaveral Air Force Station in Florida, workers guide the spent first stage of NASA's Ares I-X rocket into a slip. The solid rocket booster recovery ship Freedom Star, in the background, recovered the booster after it splashed down in the Atlantic Ocean following its flight test. Liftoff of the 6-minute flight test was at 11:30 a.m. EDT Oct. 28. This was the first launch from Kennedy's pads of a vehicle other than the space shuttle since the Apollo Program's Saturn rockets were retired. The parts used to make the Ares I-X booster flew on 30 different shuttle missions ranging from STS-29 in 1989 to STS-106 in 2000. The data returned from more than 700 sensors throughout the rocket will be used to refine the design of future launch vehicles and bring NASA one step closer to reaching its exploration goals. For information on the Ares I-X vehicle and flight test, visit http://www.nasa.gov/aresIX. Photo credit: NASA/Kim Shiflett

KSC-2009-6030

NASA Image and Video Library

2009-10-31

CAPE CANAVERAL, Fla. – At Hangar AF on Cape Canaveral Air Force Station in Florida, the spent first stage of NASA's Ares I-X rocket is secured in a slip. The solid rocket booster recovery ship Freedom Star recovered the booster after it splashed down in the Atlantic Ocean following its flight test. Liftoff of the 6-minute flight test was at 11:30 a.m. EDT Oct. 28. This was the first launch from Kennedy's pads of a vehicle other than the space shuttle since the Apollo Program's Saturn rockets were retired. The parts used to make the Ares I-X booster flew on 30 different shuttle missions ranging from STS-29 in 1989 to STS-106 in 2000. The data returned from more than 700 sensors throughout the rocket will be used to refine the design of future launch vehicles and bring NASA one step closer to reaching its exploration goals. For information on the Ares I-X vehicle and flight test, visit http://www.nasa.gov/aresIX. Photo credit: NASA/Kim Shiflett

Evaluation of boron-epoxy-reinforced titanium tubular truss for application to a space shuttle booster thrust structure

NASA Technical Reports Server (NTRS)

Corvelli, N.; Carri, R.

1972-01-01

Results of a study to demonstrate the applicability of boron-epoxy-composite-reinforced titanium tubular members to a space shuttle booster thrust structure are presented and discussed. The experimental results include local buckling of all-composite and composite-reinforced-metal cylinders with low values of diameter-thickness ratio, static tests on composite-to-metal bonded step joints, and a test to failure of a boron-epoxy-reinforced titanium demonstration truss. The demonstration truss failed at 118 percent of design ultimate load. Test results and analysis for all specimens and the truss are compared. Comparing an all-titanium design and a boron-epoxy-reinforced-titanium (75 percent B-E and 25 percent Ti) design for application to the space shuttle booster thrust structure indicates that the latter would weigh approximately 24 percent less. Experimental data on the local buckling strength of cylinders with a diameter-thickness ratio of approximately 50 are needed to insure that undue conservatism is not used in future designs.

Healthy Team Healthy U: A Prospective Validation of an Evidence-Based Worksite Health Promotion and Wellness Platform.

PubMed

Goldberg, Linn; Lockwood, Chondra; Garg, Bharti; Kuehl, Kerry S

2015-01-01

To evaluate the effects of a research-tested, team-based health promotion and wellness program combined with digital technologies and implemented in a diverse worksite setting among hospital, clinic, and university employees. A prospective cohort study of employees completing biometrics and questionnaires before and after the initial 12-session wellness program and its 12-session booster, 1 year later. After both the initial intervention and booster, blood pressure and weight were reduced, with greater reductions among employees with pre-hypertension and hypertension and those with a body mass index ≥25. After both the initial intervention and booster, there was a significant increase in (1) daily intake of fruit and vegetable servings, (2) days/week of ≥30 min of exercise, (3) days/week of strength training, and (4) levels of moderately vigorous and vigorous daily physical activity. Self-reported indices of both depression and work-related stress were reduced, while participants reported increased happiness. Post booster, average sleep quality, and sleep duration increased among higher risk employees reporting ≤6 h of daily sleep. Employees reported receiving encouragement from co-workers to engage in healthful diet and physical activities, and exercised together more, and indicated that they would recommend the program to other employees. Longitudinal analysis revealed the durability of the initial intervention outcomes with further beneficial effects after the booster. A research tested, comprehensive team-based health promotion and wellness program, combined with digital technologies, improved employee health behaviors, mood, sleep, elements of co-worker cohesion, and biometrics among a diverse multi-site workforce. Positive program effects were durable, with enhanced results after the booster.

Assessment of safety and efficacy against Bordetella pertussis of a new tetanus-reduced dose diphtheria-acellular pertussis vaccine in a murine model.

PubMed

Kwon, Hyo Jin; Han, Seung Beom; Kim, Bo Ram; Kang, Kyu Ri; Huh, Dong Ho; Choi, Gi Sub; Ahn, Dong Ho; Kang, Jin Han

2017-04-04

Tetanus-reduced dose diphtheria-acellular pertussis (Tdap) vaccination during adolescence was introduced in response to the resurgence of pertussis in various countries. A new Tdap vaccine was manufactured in Korea as a countermeasure against a predicted Tdap vaccine shortage. This study was performed to evaluate the immunogenicity, safety, and protection efficacy against Bordetella pertussis of the new Tdap vaccine in a murine model. Four-week-old BABL/c mice were used for assessment of immunogenicity and protection efficacy. A single dose of primary diphtheria-tetanus-acellular pertussis (DTaP) vaccine was administered, followed by a single dose of Tdap booster vaccine after a 12-week interval. Anti-pertussis toxin (PT), anti-filamentous hemagglutinin (FHA), and anti-pertactin (PRN) IgG titers were measured before primary vaccination, and before and after booster vaccination. An intranasal challenge test was performed after booster vaccination to determine protection efficacy. To assess safety, mouse weight gain test and leukocytosis promotion test were performed using 4-week-old ddY female mice. Anti-PT and anti-FHA IgG titers after booster vaccination were significantly higher than those before booster vaccination with either the new vaccine or a commercially available Tdap vaccine (P = 0.01 for all occasions). After booster vaccination, no significant difference was observed between the two vaccines in antibody titers against pertussis antigens (P = 0.53 for anti-PT IgG, P = 0.91 for anti-FHA IgG, P = 0.39 for anti-PRN IgG). In the intranasal challenge test, inoculated B. pertussis was eradicated 7 days after infection. On days 4 and 7 after infection, colony counts of B. pertussis were not significantly different between the new and positive control vaccine groups (P = 1.00). Mean body weight changes and leukocyte counts of the new vaccine, positive control, and negative control groups were not significantly different 7 days after vaccination (P = 0.87 and P = 0.37, respectively). All leukocyte counts in the new vaccine group were within a mean ± 3 standard deviations range. A murine model involving a single dose primary DTaP vaccination followed by a single dose Tdap booster vaccination can be used for non-clinical studies of Tdap vaccines. The new Tdap vaccine manufactured in Korea exhibited comparable immunogenicity, protection efficacy, and safety with a commercially available Tdap vaccine.

NASA's NB-52B carrier aircraft rolls down a taxiway with the X-43A hypersonic research aircraft and its modified Pegasus® booster rocket slung from a pylon under its right wing

NASA Image and Video Library

2001-03-15

NASA's NB-52B carrier aircraft rolls down a taxiway at Edwards Air Force Base with the X-43A hypersonic research aircraft and its modified Pegasus® booster rocket slung from a pylon under its right wing. Part of a combined systems test conducted by NASA's Dryden Flight Research Center at Edwards, the taxi test was one of the last major milestones in the Hyper-X research program before the first X-43A flight. The X-43A flights will be the first actual flight tests of an aircraft powered by a revolutionary supersonic-combustion ramjet ("scramjet") engine capable of operating at hypersonic speeds (above Mach 5, or five times the speed of sound). The 12-foot, unpiloted research vehicle was developed and built by MicroCraft Inc., Tullahoma, Tenn., under NASA contract. The booster was built by Orbital Sciences Corp., Dulles, Va.,After being air-launched from NASA's venerable NB-52 mothership, the booster will accelerate the X-43A to test speed and altitude. The X-43A will then separate from the rocket and fly a pre-programmed trajectory, conducting aerodynamic and propulsion experiments until it descends into the Pacific Ocean. Three research flights are planned, two at Mach 7 and one at Mach 10, with the first tentatively scheduled for late spring to early summer, 2001.

KENNEDY SPACE CENTER, FLA. - Mobile Launcher Platform (MLP) number 3 and a set of twin solid rocket boosters, atop the crawler-transporter, inch along the crawlerway in support of the second engineering analysis vibration test on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A (on the horizon) and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

NASA Image and Video Library

2003-11-21

KENNEDY SPACE CENTER, FLA. - Mobile Launcher Platform (MLP) number 3 and a set of twin solid rocket boosters, atop the crawler-transporter, inch along the crawlerway in support of the second engineering analysis vibration test on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A (on the horizon) and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

KENNEDY SPACE CENTER, FLA. - The crawler transporter slowly moves the Mobile Launcher Platform (MLP), carrying a set of twin solid rocket boosters, along the crawlerway in support of engineering analysis vibration tests on the crawler and MLP. In the distance, at left, is Launch Pad 39A. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

NASA Image and Video Library

2003-11-17

KENNEDY SPACE CENTER, FLA. - The crawler transporter slowly moves the Mobile Launcher Platform (MLP), carrying a set of twin solid rocket boosters, along the crawlerway in support of engineering analysis vibration tests on the crawler and MLP. In the distance, at left, is Launch Pad 39A. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

KENNEDY SPACE CENTER, FLA. - Mobile Launcher Platform (MLP) number 3 and a set of twin solid rocket boosters, atop the crawler-transporter, crawls away from the Vehicle Assembly Building in support of the second engineering analysis vibration test on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

NASA Image and Video Library

2003-11-21

KENNEDY SPACE CENTER, FLA. - Mobile Launcher Platform (MLP) number 3 and a set of twin solid rocket boosters, atop the crawler-transporter, crawls away from the Vehicle Assembly Building in support of the second engineering analysis vibration test on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

KENNEDY SPACE CENTER, FLA. - Mobile Launcher Platform (MLP) number 3 and a set of twin solid rocket boosters, atop the crawler-transporter, inch away from the Vehicle Assembly Building (VAB) in support of the second engineering analysis vibration test on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

NASA Image and Video Library

2003-11-21

KENNEDY SPACE CENTER, FLA. - Mobile Launcher Platform (MLP) number 3 and a set of twin solid rocket boosters, atop the crawler-transporter, inch away from the Vehicle Assembly Building (VAB) in support of the second engineering analysis vibration test on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

KENNEDY SPACE CENTER, FLA. - Carrying a set of twin solid rocket boosters, the crawler transporter slowly moves the Mobile Launcher Platform (MLP) past the NASA-KSC News Center where the U.S. flag flies daily. The journey is in support of engineering analysis vibration tests on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

NASA Image and Video Library

2003-11-17

KENNEDY SPACE CENTER, FLA. - Carrying a set of twin solid rocket boosters, the crawler transporter slowly moves the Mobile Launcher Platform (MLP) past the NASA-KSC News Center where the U.S. flag flies daily. The journey is in support of engineering analysis vibration tests on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

KENNEDY SPACE CENTER, FLA. - As the crawler transporter slowly moves the Mobile Launcher Platform (MLP) out of the Vehicle Assembly Building, the two solid rocket boosters on top are framed in the doorway. The move is in support of engineering analysis vibration tests on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

NASA Image and Video Library

2003-11-17

KENNEDY SPACE CENTER, FLA. - As the crawler transporter slowly moves the Mobile Launcher Platform (MLP) out of the Vehicle Assembly Building, the two solid rocket boosters on top are framed in the doorway. The move is in support of engineering analysis vibration tests on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

KENNEDY SPACE CENTER, FLA. - As the crawler transporter slowly moves the Mobile Launcher Platform (MLP) out of the Vehicle Assembly Building, the driver of the front control cab can be seen. The MLP is carrying two solid rocket boosters for engineering analysis vibration tests on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

NASA Image and Video Library

2003-11-17

KENNEDY SPACE CENTER, FLA. - As the crawler transporter slowly moves the Mobile Launcher Platform (MLP) out of the Vehicle Assembly Building, the driver of the front control cab can be seen. The MLP is carrying two solid rocket boosters for engineering analysis vibration tests on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

Saturn Apollo Program

NASA Image and Video Library

1966-01-01

Engineers and technicians at the Marshall Space Flight Center placed a Saturn V ground test booster (S-IC-D) into the dynamic test stand. The stand was constructed to test the integrity of the vehicle. Forces were applied to the tail of the vehicle to simulate the engines thrusting, and various other flight factors were fed to the vehicle to test reactions. The Saturn V launch vehicle, with the Apollo spacecraft, was subjected to more than 450 hours of shaking. The photograph shows the 300,000 pound S-IC stage being lifted from its transporter into place inside the 360-foot tall test stand. This dynamic test booster has one dummy F-1 engine and weight simulators are used at the other four engine positions.

Methods for data reduction and loads analysis of Space Shuttle Solid Rocket Booster model water impact tests

NASA Technical Reports Server (NTRS)

1976-01-01

The methodology used to predict full scale space shuttle solid rocket booster (SRB) water impact loads from scale model test data is described. Tests conducted included 12.5 inch and 120 inch diameter models of the SRB. Geometry and mass characteristics of the models were varied in each test series to reflect the current SRB baseline configuration. Nose first and tail first water entry modes were investigated with full-scale initial impact vertical velocities of 40 to 120 ft/sec, horizontal velocities of 0 to 60 ft/sec., and off-vertical angles of 0 to plus or minus 30 degrees. The test program included a series of tests with scaled atmospheric pressure.

Inviscid and Viscous CFD Analysis of Booster Separation for the Space Launch System Vehicle

NASA Technical Reports Server (NTRS)

Dalle, Derek J.; Rogers, Stuart E.; Chan, William M.; Lee, Henry C.

2016-01-01

This paper presents details of Computational Fluid Dynamic (CFD) simulations of the Space Launch System during solid-rocket booster separation using the Cart3D inviscid and Overflow viscous CFD codes. The discussion addresses the use of multiple data sources of computational aerodynamics, experimental aerodynamics, and trajectory simulations for this critical phase of flight. Comparisons are shown between Cart3D simulations and a wind tunnel test performed at NASA Langley Research Center's Unitary Plan Wind Tunnel, and further comparisons are shown between Cart3D and viscous Overflow solutions for the flight vehicle. The Space Launch System (SLS) is a new exploration-class launch vehicle currently in development that includes two Solid Rocket Boosters (SRBs) modified from Space Shuttle hardware. These SRBs must separate from the SLS core during a phase of flight where aerodynamic loads are nontrivial. The main challenges for creating a separation aerodynamic database are the large number of independent variables (including orientation of the core, relative position and orientation of the boosters, and rocket thrust levels) and the complex flow caused by exhaust plumes of the booster separation motors (BSMs), which are small rockets designed to push the boosters away from the core by firing partially in the direction opposite to the motion of the vehicle.

Persistence of rabies antibody 5 years after pre-exposure prophylaxis with human diploid cell antirabies vaccine and antibody response to a single booster dose.

PubMed Central

Rodrigues, F. M.; Mandke, V. B.; Roumiantzeff, M.; Rao, C. V.; Mehta, J. M.; Pavri, K. M.; Poonawalla, C.

1987-01-01

In 1978, 22 staff members of the National Institute of Virology, Pune, India, were given two doses of human diploid cell antirabies vaccine (HDCV) for primary pre-exposure prophylactic immunization; the interval between the two doses being approximately 4 weeks. Eighteen of these 22 vaccinees were given a booster dose 1 year later. All 18 vaccinees developed protective levels of antibody; most of them had antibody levels exceeding 10 IU/ml. In 1984, 5 years after the booster dose, 11 (79.0%) of 14 vaccinees tested still possessed neutralizing antibody levels ranging from 0.5 IU/ml to 10 IU/ml. Fourteen days after the administration of a booster dose, the antibody levels ranged from 10 to greater than or equal to 100 IU/ml for all except one vaccine (5.2 IU/ml). These findings demonstrate that the majority of vaccines retained detectable neutralizing antibody after pre-exposure prophylaxis for as long as 5 years and that a single booster dose thereafter evoked a good antibody response. PMID:3609177

Boosting the growth of the probiotic strain Lactobacillus paracasei ssp. paracasei F19.

PubMed

Brignone, Desideria; Radmann, Pia; Behr, Jürgen; Vogel, Rudi F

2017-08-01

Single so-called booster substances were added to the fermentation medium of the probiotic strain Lactobacillus (L.) paracasei ssp. paracasei F19 to enhance its growth. A wide screening was carried out in microtiter plates and a statistical analysis of the growth parameters was performed. CFU counts were used to correlate the increase in OD 590nm with the increase in viable cell number. Sodium ascorbate, sodium pyruvate, manganese sulfate and cysteine had a remarkable boosting effect on the growth of L. paracasei F19. Three of the boosters increased the growth rate of the strain and led to a higher cell density and biomass yield in laboratory conditions. Cysteine significantly shortened the lag phase, therefore reducing the fermentation times. The boosters were tested on four additional Lactobacillus species and their growth boosting activity was retained. To investigate whether the growth boosters could improve the tolerance of L. paracasei F19 to the adverse condition in the GI tract, additional tests were performed. Sodium ascorbate and sodium pyruvate exerted a certain antioxidant effect, as they improved the tolerance of L. paracasei F19 to H 2 O 2 . Sodium ascorbate enhanced the growth of the strain in low pH.

Output-Based Adaptive Meshing Applied to Space Launch System Booster Separation Analysis

NASA Technical Reports Server (NTRS)

Dalle, Derek J.; Rogers, Stuart E.

2015-01-01

This paper presents details of Computational Fluid Dynamic (CFD) simulations of the Space Launch System during solid-rocket booster separation using the Cart3D inviscid code with comparisons to Overflow viscous CFD results and a wind tunnel test performed at NASA Langley Research Center's Unitary PlanWind Tunnel. The Space Launch System (SLS) launch vehicle includes two solid-rocket boosters that burn out before the primary core stage and thus must be discarded during the ascent trajectory. The main challenges for creating an aerodynamic database for this separation event are the large number of basis variables (including orientation of the core, relative position and orientation of the boosters, and rocket thrust levels) and the complex flow caused by the booster separation motors. The solid-rocket boosters are modified from their form when used with the Space Shuttle Launch Vehicle, which has a rich flight history. However, the differences between the SLS core and the Space Shuttle External Tank result in the boosters separating with much narrower clearances, and so reducing aerodynamic uncertainty is necessary to clear the integrated system for flight. This paper discusses an approach that has been developed to analyze about 6000 wind tunnel simulations and 5000 flight vehicle simulations using Cart3D in adaptive-meshing mode. In addition, a discussion is presented of Overflow viscous CFD runs used for uncertainty quantification. Finally, the article presents lessons learned and improvements that will be implemented in future separation databases.

Space Shuttle Projects

NASA Image and Video Library

1978-11-01

The structural test article to be used in the solid rocket booster (SRB) structural and load verification tests is being assembled in a high bay building of the Marshall Space Flight Center (MSFC). The Shuttle's two SRB's are the largest solids ever built and the first designed for refurbishment and reuse. Standing nearly 150-feet high, the twin boosters provide the majority of thrust for the first two minutes of flight, about 5.8 million pounds, augmenting the Shuttle's main propulsion system during liftoff. The major design drivers for the solid rocket motors (SRM's) were high thrust and reuse. The desired thrust was achieved by using state-of-the-art solid propellant and by using a long cylindrical motor with a specific core design that allows the propellant to burn in a carefully controlled marner. At burnout, the boosters separate from the external tank and drop by parachute to the ocean for recovery and subsequent refurbishment.

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.

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.

Insulation Reformulation Development

NASA Technical Reports Server (NTRS)

Chapman, Cynthia; Bray, Mark

2015-01-01

The current Space Launch System (SLS) internal solid rocket motor insulation, polybenzimidazole acrylonitrile butadiene rubber (PBI-NBR), is a new insulation that replaced asbestos-based insulations found in Space Shuttle heritage solid rocket boosters. PBI-NBR has some outstanding characteristics such as an excellent thermal erosion resistance, low thermal conductivity, and low density. PBI-NBR also has some significant challenges associated with its use: Air entrainment/entrapment during manufacture and lay-up/cure and low mechanical properties such as tensile strength, modulus, and fracture toughness. This technology development attempted to overcome these challenges by testing various reformulated versions of booster insulation. The results suggest the SLS program should continue to investigate material alternatives for potential block upgrades or use an entirely new, more advanced booster. The experimental design was composed of a logic path that performs iterative formulation and testing in order to maximize the effort. A lab mixing baseline was developed and documented for the Rubber Laboratory in Bldg. 4602/Room 1178.

Reentry static stability characteristics of a (Model 471) .005479-scale 146-inch solid rocket booster tested in the NASA/MSFC 14 by 14 inch TWT (SA8F)

NASA Technical Reports Server (NTRS)

Johnson, J. D.; Braddock, W. F.; Praharaj, S. C.

1975-01-01

A force test of a scale model of the Space Shuttle Solid Rocket Booster was conducted in a trisonic wind tunnel. The model was tested with such protuberances as a camera capsule, electrical tunnel, attach rings, aft separation rockets, ET attachment structure, and hold-down struts. The model was also tested with the nozzle at gimbal angles of 0, 2.5, and 5 degrees. The influence of a unique heat shield configuration was also determined. Some photographs of model installations in the tunnel were taken and are included. Schlieren photography was utilized for several angles of attack.

Force test of a 0.88 percent scale 142-inch diameter solid rocket booster (MSFC model number 461) in the NASA/MSFC high Reynolds number wind tunnel (SA13F)

NASA Technical Reports Server (NTRS)

Johnson, J. D.; Winkler, G. W.

1976-01-01

The results are presented of a force test of a .88 percent scale model of the 142 inch solid rocket booster without protuberances, conducted in the MSFC high Reynolds number wind tunnel. The objective of this test was to obtain aerodynamic force data over a large range of Reynolds numbers. The test was conducted over a Mach number range from 0.4 to 3.5. Reynolds numbers based on model diameter (1.25 inches) ranged from .75 million to 13.5 million. The angle of attack range was from 35 to 145 degrees.

SRB Processing Facilities Media Event

NASA Image and Video Library

2016-03-01

At the Rotation, Processing and Surge Facility (RPSF) at NASA’s Kennedy Space Center in Florida, members of the news media photograph the process as cranes are used to lift one of two pathfinders, or test versions, of solid rocket booster segments for NASA’s Space Launch System rocket. The Ground Systems Development and Operations Program and Jacobs Engineering, on the Test and Operations Support Contract, are preparing the booster segments, which are inert, for a series of lifts, moves and stacking operations to prepare for Exploration Mission-1, deep-space missions and the journey to Mars.

SRB Processing Facilities Media Event

NASA Image and Video Library

2016-03-01

At the Rotation, Processing and Surge Facility (RPSF) at NASA’s Kennedy Space Center in Florida, members of the news media watch as cranes are used to lift one of two pathfinders, or test versions, of solid rocket booster segments for NASA’s Space Launch System rocket. The Ground Systems Development and Operations Program and Jacobs Engineering, on the Test and Operations Support Contract, are preparing the booster segments, which are inert, for a series of lifts, moves and stacking operations to prepare for Exploration Mission-1, deep-space missions and the journey to Mars.

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.

SRB Processing Facilities Media Event

NASA Image and Video Library

2016-03-01

Members of the news media view the high bay inside the Rotation, Processing and Surge Facility (RPSF) at NASA’s Kennedy Space Center in Florida. Inside the RPSF, engineers and technicians with Jacobs Engineering on the Test and Operations Support Contract, explain the various test stands. In the far corner is one of two pathfinders, or test versions, of solid rocket booster segments for NASA’s Space Launch System rocket. The Ground Systems Development and Operations Program and Jacobs are preparing the booster segments, which are inert, for a series of lifts, moves and stacking operations to prepare for Exploration Mission-1, deep-space missions and the journey to Mars.

[Influence of three booster doses hepatitis B vaccine on the persistence of immune-protection among infants with normal and high antibody response to primary vaccination: a matched case-control study].

PubMed

Feng, Yi; Lyu, Jingjing; Liu, Jiaye; Yan, Bingyu; Song, Lizhi; Liang, Xiaofeng; Li, Li; Zhang, Guomin; Wang, Fuzhen; Zhang, Li; Xu, Aiqiang

2016-04-01

To examine the influence of three-booster-doses hepatitis B vaccines on children with normal and high antibody response to primary vaccination. Antibody against hepatitis B surface antigen (anti-HBs) were detected after primary vaccination and children with normal or high response to hepatitis B primary vaccination at infancy, were identified. Children who were given three booster doses were selected to form the booster group and who were given no booster dose were 1∶1 matched with the same gender and residence to form the control group. Blood samples were obtained from all the participants and tested for anti-HBs and anti-HBc, 5 years after the primary vaccination. The positive rates of anti-HBs response to primary vaccination were 97.39% (224/230, 95% CI: 94.41%-99.04%) in the booster group and 53.91% (124/230, 95% CI: 47.24%-60.48%) in the control group (P<0.05), 5 years after the primary vaccination. Geometric mean concentration (GMC) of anti-HBs were 1 140.02 (887.46-1 464.46) mIU/ml in the booster group and 11.53 (8.73-15.23) mIU/ml in the control group (P<0.05). The prevalence rates of breakthrough HBV infection were 0.87% (2/230) in the booster group and 2.17%(5/230) in the control group (P>0.05). RESULTS from the multivariable analysis showed that the booster doses (OR=38.75, 95%CI: 16.23-92.54) and the level of anti-HBs after the primary vaccination (OR =3.06, 95%CI:1.51-6.17) were independently associated with the positive rates of anti-HBs, 5 years after the primary vaccination (P<0.05). Programs with three booster doses to children that showing normal and high antibody response to primary vaccination could improve the persistence of anti-HBs but possibly would not be able to prevent the HBV infection.

The Incremental Effects of Manual Therapy or Booster Sessions in Addition to Exercise Therapy for Knee Osteoarthritis: A Randomized Clinical Trial.

PubMed

Abbott, J Haxby; Chapple, Catherine M; Fitzgerald, G Kelley; Fritz, Julie M; Childs, John D; Harcombe, Helen; Stout, Kirsten

2015-12-01

A factorial randomized controlled trial. To investigate the addition of manual therapy to exercise therapy for the reduction of pain and increase of physical function in people with knee osteoarthritis (OA), and whether "booster sessions" compared to consecutive sessions may improve outcomes. The benefits of providing manual therapy in addition to exercise therapy, or of distributing treatment sessions over time using periodic booster sessions, in people with knee OA are not well established. All participants had knee OA and were provided 12 sessions of multimodal exercise therapy supervised by a physical therapist. Participants were randomly allocated to 1 of 4 groups: exercise therapy in consecutive sessions, exercise therapy distributed over a year using booster sessions, exercise therapy plus manual therapy without booster sessions, and exercise therapy plus manual therapy with booster sessions. The primary outcome measure was the Western Ontario and McMaster Universities Osteoarthritis Index (WOMAC score; 0-240 scale) at 1-year follow-up. Secondary outcome measures were the numeric pain-rating scale and physical performance tests. Of 75 participants recruited, 66 (88%) were retained at 1-year follow-up. Factorial analysis of covariance of the main effects showed significant benefit from booster sessions (P = .009) and manual therapy (P = .023) over exercise therapy alone. Group analysis showed that exercise therapy with booster sessions (WOMAC score, -46.0 points; 95% confidence interval [CI]: -80.0, -12.0) and exercise therapy plus manual therapy (WOMAC score, -37.5 points; 95% CI: -69.7, -5.5) had superior effects compared with exercise therapy alone. The combined strategy of exercise therapy plus manual therapy with booster sessions was not superior to exercise therapy alone. Distributing 12 sessions of exercise therapy over a year in the form of booster sessions was more effective than providing 12 consecutive exercise therapy sessions. Providing manual therapy in addition to exercise therapy improved treatment effectiveness compared to providing 12 consecutive exercise therapy sessions alone. Trial registered with the Australian New Zealand Clinical Trials Registry (ACTRN12612000460808).

Space Shuttle Solid Rocket Booster decelerator subsystem - Air drop test vehicle/B-52 design

NASA Technical Reports Server (NTRS)

Runkle, R. E.; Drobnik, R. F.

1979-01-01

The air drop development test program for the Space Shuttle Solid Rocket Booster Recovery System required the design of a large drop test vehicle that would meet all the stringent requirements placed on it by structural loads, safety considerations, flight recovery system interfaces, and sequence. The drop test vehicle had to have the capability to test the drogue and the three main parachutes both separately and in the total flight deployment sequence and still be low-cost to fit in a low-budget development program. The design to test large ribbon parachutes to loads of 300,000 pounds required the detailed investigation and integration of several parameters such as carrier aircraft mechanical interface, drop test vehicle ground transportability, impact point ground penetration, salvageability, drop test vehicle intelligence, flight design hardware interfaces, and packaging fidelity.

Update on Risk Reduction Activities for a Liquid Advanced Booster for NASA's Space Launch System

NASA Technical Reports Server (NTRS)

Crocker, Andrew M.; Greene, William D.

2017-01-01

The stated goals of NASA's Research Announcement for the Space Launch System (SLS) Advanced Booster Engineering Demonstration and/or Risk Reduction (ABEDRR) are to reduce risks leading to an affordable Advanced Booster that meets the evolved capabilities of SLS and enable competition by mitigating targeted Advanced Booster risks to enhance SLS affordability. Dynetics, Inc. and Aerojet Rocketdyne (AR) formed a team to offer a wide-ranging set of risk reduction activities and full-scale, system-level demonstrations that support NASA's ABEDRR goals. During the ABEDRR effort, the Dynetics Team has modified flight-proven Apollo-Saturn F-1 engine components and subsystems to improve affordability and reliability (e.g., reduce parts counts, touch labor, or use lower cost manufacturing processes and materials). The team has built hardware to validate production costs and completed tests to demonstrate it can meet performance requirements. State-of-the-art manufacturing and processing techniques have been applied to the heritage F-1, resulting in a low recurring cost engine while retaining the benefits of Apollo-era experience. NASA test facilities have been used to perform low-cost risk-reduction engine testing. In early 2014, NASA and the Dynetics Team agreed to move additional large liquid oxygen/kerosene engine work under Dynetics' ABEDRR contract. Also led by AR, the objectives of this work are to demonstrate combustion stability and measure performance of a 500,000 lbf class Oxidizer-Rich Staged Combustion (ORSC) cycle main injector. A trade study was completed to investigate the feasibility, cost effectiveness, and technical maturity of a domestically-produced engine that could potentially both replace the RD-180 on Atlas V and satisfy NASA SLS payload-to-orbit requirements via an advanced booster application. Engine physical dimensions and performance parameters resulting from this study provide the system level requirements for the ORSC risk reduction test article. The test article is scheduled to complete fabrication and assembly soon and continue testing through late 2019. Dynetics has also designed, developed, and built innovative tank and structure assemblies using friction stir welding to leverage recent NASA investments in manufacturing tools, facilities, and processes, significantly reducing development and recurring costs. The full-scale cryotank assembly was used to verify the structural design and prove affordable processes. Dynetics performed hydrostatic and cryothermal proof tests on the assembly to verify the assembly meets performance requirements..

Results of wind tunnel tests of an ASRM configured 0.03 scale Space Shuttle integrated vehicle model (47-OTS) in the AEDC 16-foot transonic wind tunnel, volume 2

NASA Technical Reports Server (NTRS)

Marroquin, J.; Lemoine, P.

1992-01-01

An experimental Aerodynamic and Aero-Acoustic loads data base was obtained at transonic Mach numbers for the Space Shuttle Launch Vehicle configured with the ASRM Solid Rocket Boosters as an increment to the current flight configuration (RSRB). These data were obtained during transonic wind tunnel tests (IA 613A) conducted in the Arnold Engineering Development Center 16-Foot transonic propulsion wind tunnel from March 27, 1991 through April 12, 1991. This test is the first of a series of two tests covering the Mach range from 0.6 to 3.5. Steady state surface static and fluctuating pressure distributions over the Orbiter, External Tank and Solid Rocket Boosters of the Shuttle Integrated Vehicle were measured. Total Orbiter forces, Wing forces and Elevon hinge moments were directly measured as well from force balances. Two configurations of Solid Rocket Boosters were tested, the Redesigned Solid Rocket Booster (RSRB) and the Advanced Solid Rocket Motor (ASRM). The effects of the position (i.e., top, bottom, top and bottom) of the Integrated Electronics Assembly (IEA) box, mounted on the SRB attach ring, were obtained on the ASRM configured model. These data were obtained with and without Solid Plume Simulators which, when used, matched as close as possible the flight derived pressures on the Orbiter and External Tank base. Data were obtained at Mach numbers ranging from 0.6 to 1.55 at a Unit Reynolds Number of 2.5 million per foot through model angles of attack from -8 to +4 degrees at sideslip angles of 0, +4 and -4 degrees.

Results of wind tunnel tests of an ASRM configured 0.03 scale Space Shuttle integrated vehicle model (47-OTS) in the AEDC 16-foot Transonic wind tunnel (IA613A), volume 1

NASA Technical Reports Server (NTRS)

Marroquin, J.; Lemoine, P.

1992-01-01

An experimental Aerodynamic and Aero-Acoustic loads data base was obtained at transonic Mach numbers for the Space Shuttle Launch Vehicle configured with the ASRM Solid Rocket Boosters as an increment to the current flight configuration (RSRB). These data were obtained during transonic wind tunnel tests (IA 613A) conducted in the Arnold Engineering Development Center 16-Foot transonic propulsion wind tunnel from March 27, 1991 through April 12, 1991. This test is the first of a series of two tests covering the Mach range from 0.6 to 3.5. Steady state surface static and fluctuating pressure distributions over the Orbiter, External Tank and Solid Rocket Boosters of the Shuttle Integrated Vehicle were measured. Total Orbiter forces, Wing forces and Elevon hinge moments were directly measured as well from force balances. Two configurations of Solid Rocket Boosters were tested, the Redesigned Solid Rocket Booster (RSRB) and the Advanced Solid Rocket Motor (ASRM). The effects of the position (i.e. top, bottom, top and bottom) of the Integrated Electronics Assembly (IEA) box, mounted on the SRB attach ring, were obtained on the ASRM configured model. These data were obtained with and without Solid Plume Simulators which, when used, matched as close as possible the flight derived pressures on the Orbiter and External Tank base. Data were obtained at Mach numbers ranging from 0.6 to 1.55 at a Unit Reynolds Number of 2.5 million per foot through model angles of attack from -8 to +4 degrees at sideslip angles of 0, +4 and -4 degrees.

KENNEDY SPACE CENTER, FLA. - Mobile Launcher Platform (MLP) number 3 and a set of twin solid rocket boosters, atop the crawler-transporter, crawl out of the Vehicle Assembly Building (VAB) in support of the second engineering analysis vibration test on the crawler and MLP. In the background is another MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

NASA Image and Video Library

2003-11-21

KENNEDY SPACE CENTER, FLA. - Mobile Launcher Platform (MLP) number 3 and a set of twin solid rocket boosters, atop the crawler-transporter, crawl out of the Vehicle Assembly Building (VAB) in support of the second engineering analysis vibration test on the crawler and MLP. In the background is another MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

KENNEDY SPACE CENTER, FLA. - A Kennedy Space Center technician monitors the performance of a crawler-transporter as it moves Mobile Launcher Platform (MLP) number 3, with a set of twin solid rocket boosters bolted atop, to the intersection in the crawlerway during the second engineering analysis vibration test on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A, and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

NASA Image and Video Library

2003-11-21

KENNEDY SPACE CENTER, FLA. - A Kennedy Space Center technician monitors the performance of a crawler-transporter as it moves Mobile Launcher Platform (MLP) number 3, with a set of twin solid rocket boosters bolted atop, to the intersection in the crawlerway during the second engineering analysis vibration test on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A, and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

KENNEDY SPACE CENTER, FLA. - Mobile Launcher Platform (MLP) number 3 and a set of twin solid rocket boosters bolted to it, atop the crawler-transporter, inches along the crawlerway in support of the second engineering analysis vibration test on the crawler and MLP. The MLP is viewed from the KSC News Center across the turn basin. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

NASA Image and Video Library

2003-11-21

KENNEDY SPACE CENTER, FLA. - Mobile Launcher Platform (MLP) number 3 and a set of twin solid rocket boosters bolted to it, atop the crawler-transporter, inches along the crawlerway in support of the second engineering analysis vibration test on the crawler and MLP. The MLP is viewed from the KSC News Center across the turn basin. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

KENNEDY SPACE CENTER, FLA. - A Kennedy Space Center technician walks towards the intersection of the crawlerway beside a crawler-transporter moving Mobile Launcher Platform (MLP) number 3, with a set of twin solid rocket boosters bolted atop, during the second engineering analysis vibration test on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A, and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

NASA Image and Video Library

2003-11-21

KENNEDY SPACE CENTER, FLA. - A Kennedy Space Center technician walks towards the intersection of the crawlerway beside a crawler-transporter moving Mobile Launcher Platform (MLP) number 3, with a set of twin solid rocket boosters bolted atop, during the second engineering analysis vibration test on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A, and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

KENNEDY SPACE CENTER, FLA. - Mobile Launcher Platform (MLP) number 3 and a set of twin solid rocket boosters, atop the crawler-transporter, inch along the crawlerway in support of the second engineering analysis vibration test on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A (on the horizon at right; Pad 39B is at far left), and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

NASA Image and Video Library

2003-11-21

KENNEDY SPACE CENTER, FLA. - Mobile Launcher Platform (MLP) number 3 and a set of twin solid rocket boosters, atop the crawler-transporter, inch along the crawlerway in support of the second engineering analysis vibration test on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A (on the horizon at right; Pad 39B is at far left), and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

International aerospaceplane efforts

NASA Technical Reports Server (NTRS)

Lindley, Charles A.

1992-01-01

Although the U.S. began the first reusable space booster effort in the late 1950's, it is no longer an exclusive field. All of the technologically advanced nations, and several groups of nations, have one or more reusable booster efforts in progress. A listing of the entries in the field is presented. The list is somewhat misleading, because it includes both fully reusable and partially reusable boosters, both manned and unmanned, and both flight test and operational proposals. Additionally, not all of the projects are funded, and only a few of the projects will survive. The most likely candidates are the following: France/ESA, Germany/ESA, Great Britain/ESA/(USSR), USSR(past), and Japan. A discussion of the preceding projects is provided.

KSC-2009-6031

NASA Image and Video Library

2009-10-31

CAPE CANAVERAL, Fla. – At Hangar AF on Cape Canaveral Air Force Station in Florida, workers prepare to inspect the spent first stage of NASA's Ares I-X rocket, secured in a slip. The booster was recovered by the solid rocket booster recovery ship Freedom Star after it splashed down in the Atlantic Ocean following its flight test. Liftoff of the 6-minute flight test was at 11:30 a.m. EDT Oct. 28. This was the first launch from Kennedy's pads of a vehicle other than the space shuttle since the Apollo Program's Saturn rockets were retired. The parts used to make the Ares I-X booster flew on 30 different shuttle missions ranging from STS-29 in 1989 to STS-106 in 2000. The data returned from more than 700 sensors throughout the rocket will be used to refine the design of future launch vehicles and bring NASA one step closer to reaching its exploration goals. For information on the Ares I-X vehicle and flight test, visit http://www.nasa.gov/aresIX. Photo credit: NASA/Kim Shiflett

Investigation of failure to separate an Inconel 718 frangible nut

NASA Technical Reports Server (NTRS)

Hoffman, William C., III; Hohmann, Carl

1994-01-01

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

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

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

Metzinger, K.E.

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

Garnet Ring Measurements for the Fermilab Booster 2nd Harmonic Cavity

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

Kuharik, J.; Dey, J.; Duel, K.

A perpendicularly biased tuneable 2nd harmonic cavity is being constructed for use in the Fermilab Booster. The cavity's tuner uses National Magnetics AL800 garnet as the tuning media. For quality control, the magnetic properties of the material and the uniformity of the properties within the tuner must be assessed. We describe two tests which are performed on the rings and on their corresponding witness samples.

Liquid Rocket Booster (LRB) for the Space Transportation System (STS) Systems Study. Amendment 13: Orientation meeting

NASA Technical Reports Server (NTRS)

1990-01-01

The topics are presented in viewgraph form and include the following: LRB study results summary -- Feb. 1989; LRB study results -- Jan. 1990; Shuttle configuration with booster options; LRB study results -- Sept. 1990; LRB statement of work tasks; ground rules and assumptions; study flow of design, manufacturing/production, and test program/certification; study products; study schedule; and candidate 1.5 stage engine arrangements.

Mercury: testing of the Little Joe booster

NASA Image and Video Library

1959-08-02

Testing of the Little Joe booster on its launcher. The launcher is positioned at its normal launch angle of 80 degrees. Joseph Shortal wrote (vol. 3, p. 33): The Little Joe booster was assembled at Wallops on its special launcher in a vertical attitude. It is shown in the on the left with the work platform in place. The launcher was located on a special concrete slab in Launching Area 1. The capsule was lowered onto the booster by crane.... After the assembly was completed, the scaffolding was disassembled and the launcher pitched over to its normal launch angle of 80 degrees.... Little Joe had a diameter of 80 inches and an overall length, including the capsule and escape tower of 48 feet. The total weight at launch was about 43,000 pounds. The overall span of the stabilizing fins was 21.3 feet. Although in comparison with the overall Mercury Project, Little Joe was a simple undertaking, the fact that an attempt was made to condense a normal two-year project into a 6-month one with in house labor turned it into a major undertaking for Langley. -- Published in Joseph A. Shortal, History of Wallops Station: Origins and Activities Through 1949, (Wallops Island, VA: National Aeronautics and Space Administration, Wallops Station, nd), Comment Edition.

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.

Electrets used in measuring rocket exhaust effluents from the space shuttle's solid rocket booster during static test firing, DM-3

NASA Technical Reports Server (NTRS)

Susko, M.

1979-01-01

The purpose of this experimental research was to compare Marshall Space Flight Center's electrets with Thiokol's fixed flow air samplers during the Space Shuttle Solid Rocket Booster Demonstration Model-3 static test firing on October 19, 1978. The measurement of rocket exhaust effluents by Thiokol's samplers and MSFC's electrets indicated that the firing of the Solid Rocket Booster had no significant effect on the quality of the air sampled. The highest measurement by Thiokol's samplers was obtained at Plant 3 (site 11) approximately 8 km at a 113 degree heading from the static test stand. At sites 11, 12, and 5, Thiokol's fixed flow air samplers measured 0.0048, 0.00016, and 0.00012 mg/m3 of CI. Alongside the fixed flow measurements, the electret counts from X-ray spectroscopy were 685, 894, and 719 counts. After background corrections, the counts were 334, 543, and 368, or an average of 415 counts. An additional electred, E20, which was the only measurement device at a site approximately 20 km northeast from the test site where no power was available, obtained 901 counts. After background correction, the count was 550. Again this data indicate there was no measurement of significant rocket exhaust effluents at the test site.

Preflight transient dynamic analyses of B-52 aircraft carrying Space Shuttle solid rocket booster drop-test vehicle

NASA Technical Reports Server (NTRS)

Ko, W. L.; Schuster, L. S.

1984-01-01

This paper concerns the transient dynamic analysis of the B-52 aircraft carrying the Space Shuttle solid rocket booster drop test vehicle (SRB/DTV). The NASA structural analysis (NASTRAN) finite element computer program was used in the analysis. The B-52 operating conditions considered for analysis were (1) landing and (2) braking on aborted takeoff runs. The transient loads for the B-52 pylon front and rear hooks were calculated. The results can be used to establish the safe maneuver envelopes for the B-52 carrying the SRB/DTV in landings and brakings.

KENNEDY SPACE CENTER, FLA. - Jeff Thon, an SRB mechanic with United Space Alliance, is fitted with a harness to test a vertical solid rocket booster propellant grain inspection technique. Thon will be lowered inside a mockup of two segments of the SRBs. The inspection of segments is required as part of safety analysis.

NASA Image and Video Library

2003-09-11

KENNEDY SPACE CENTER, FLA. - Jeff Thon, an SRB mechanic with United Space Alliance, is fitted with a harness to test a vertical solid rocket booster propellant grain inspection technique. Thon will be lowered inside a mockup of two segments of the SRBs. The inspection of segments is required as part of safety analysis.

Pre-flight transient dynamic analysis of B-52 carrying Space Shuttle solid rocket booster drop-test vehicle

NASA Technical Reports Server (NTRS)

Ko, W. L.; Schuster, L. S.

1983-01-01

This paper concerns the transient dynamic analysis of the B-52 aircraft carrying the Space Shuttle solid-rocket booster drop-test vehicle (SRB/DTV). The NASA structural analysis (NASTRAN) finite-element computer program was used in the analysis. The B-52 operating conditions considered for analysis were (1) landing and (2) braking on aborted takeoff runs. The transient loads for the B-52 pylon front and rear hooks were calculated. The results can be used to establish the safe maneuver envelopes for the B-52 carrying the SRB/DTV in landings and brakings.

Space shuttle: Effect of configuration changes on the directional characteristics of a GD/C booster Mach no. 1.2 - 4.96

NASA Technical Reports Server (NTRS)

Brickey, J.; Brice, T.; Marks, K. E.

1971-01-01

Force tests on a 0.0035-scale model of the General Dynamics/Convair aerospace space shuttle B-15B-1 booster were conducted in the MSFC trisonic wind tunnel. The configuration has a low delta wing, all-movable delta-planform canard controls, and a single vertical tail. The test was devoted to investigating the effects of various configuration variables upon lateral-directional characteristics. These variables included wing dihedral, rudder flare, and body flap deflection. Yaw runs were made at angles of attack of 6, 10, 15, 25, 30, and 35 degrees. The Mach number range for this test was 1.20 to 4.96.

A cohort study to evaluate persistence of hepatitis B immunogenicity after administration of hexavalent vaccines

PubMed Central

Giambi, Cristina; Bella, Antonino; Barale, Antonella; Montù, Domenico; Marchisio, Maria; Oddone, Maurizio; Zito, Salvatore; Rapicetta, Maria; Chionne, Paola; Madonna, Elisabetta; Atti, Marta L Ciofi degli

2008-01-01

Background In 2001, two hexavalent vaccines were licensed in Italy (Hexavac®, Infanrix Hexa®), and since 2002 were extensively used for primary immunization in the first year of life (at 3, 5, 11/12 months of age). In 2005, the market authorization of Hexavac® was precautionary suspended by EMEA, because of doubts on long-term protection against hepatitis B virus. The objectives of this study were to evaluate the persistence of antibodies to anti-HBs, in children in the third year of life, and to investigate the response to a booster dose of hepatitis B vaccine. Methods Participant children were enrolled concomitantly with the offering of anti-polio booster dose, in the third year of life. Anti-HBs titers were determined on capillary blood samples. A booster dose of hepatitis B vaccine was administered to children with anti-HBs titers < 10 mIU/ml, with the monovalent precursor product of the previously received hexavalent vaccine. HBsAb titers were tested again one month after the booster. Results Sera from 113 children previously vaccinated with Hexavac®, and from 124 vaccinated with Infanrix Hexa® were tested for anti-HBs. Titers were ≥ 10 mIU/ml in 69% and 96% (p < 0,0001) respectively. The proportion of children with titers ≥ 100 mIU/ml did also significantly differ among groups (27% and 78%; p < 0,0001). Post-booster, 93% of children achieved titers ≥ 10 mIU/ml, with no significant difference by vaccine group. Discussion Fifteen months after third dose administration, a significant difference in anti-HBs titers was noted in the two vaccine groups considered. Monovalent hepatitis B vaccine administration in 3-year old children induced a proper booster response, confirming that immunologic memory persists in children with anti-HBs titers < 10 mIU/ml. However, long-term persistence of HBV protection after hexavalent vaccines administration should be further evaluated over time. PMID:18662386

Prediction methodologies for target scene generation in the aerothermal targets analysis program (ATAP)

NASA Astrophysics Data System (ADS)

Hudson, Douglas J.; Torres, Manuel; Dougherty, Catherine; Rajendran, Natesan; Thompson, Rhoe A.

2003-09-01

The Air Force Research Laboratory (AFRL) Aerothermal Targets Analysis Program (ATAP) is a user-friendly, engineering-level computational tool that features integrated aerodynamics, six-degree-of-freedom (6-DoF) trajectory/motion, convective and radiative heat transfer, and thermal/material response to provide an optimal blend of accuracy and speed for design and analysis applications. ATAP is sponsored by the Kinetic Kill Vehicle Hardware-in-the-Loop Simulator (KHILS) facility at Eglin AFB, where it is used with the CHAMP (Composite Hardbody and Missile Plume) technique for rapid infrared (IR) signature and imagery predictions. ATAP capabilities include an integrated 1-D conduction model for up to 5 in-depth material layers (with options for gaps/voids with radiative heat transfer), fin modeling, several surface ablation modeling options, a materials library with over 250 materials, options for user-defined materials, selectable/definable atmosphere and earth models, multiple trajectory options, and an array of aerodynamic prediction methods. All major code modeling features have been validated with ground-test data from wind tunnels, shock tubes, and ballistics ranges, and flight-test data for both U.S. and foreign strategic and theater systems. Numerous applications include the design and analysis of interceptors, booster and shroud configurations, window environments, tactical missiles, and reentry vehicles.

Detonator Performance Characterization Using Multi-Frame Laser Schlieren Imaging

NASA Astrophysics Data System (ADS)

Clarke, S. A.; Landon, C. D.; Murphy, M. J.; Martinez, M. E.; Mason, T. A.; Thomas, K. A.

2009-12-01

Several experiments that are part of a phased plan to understand the evolution of detonation in a detonator from initiation shock through run to detonation to full detonation to transition to booster and booster detonation will be presented. High speed laser schlieren movies have been used to study several explosive initiation events, such as exploding bridgewires (EBW), exploding foil initiators (EFI) (or slappers), direct optical initiation (DOI), and electrostatic discharge (ESD). Additionally, a series of tests have been performed on "cut-back" detonators with varying initial pressing (IP) heights. We have also used this diagnostic to visualize a range of EBW, EFI, and DOI full-up detonators. Future applications to other explosive events such as boosters and IHE booster evaluation will be discussed. The EPIC hydrodynamic code has been used to analyze the shock fronts from the schlieren images to reverse calculate likely boundary or initial conditions to determine the temporal-spatial pressure profile across the output face of the detonator. LA-UR-05099

Using Schlieren Visualization to Track Detonator Performance

NASA Astrophysics Data System (ADS)

Clarke, S. A.; Bolme, C. A.; Murphy, M. J.; Landon, C. D.; Mason, T. A.; Adrian, R. J.; Akinci, A. A.; Martinez, M. E.; Thomas, K. A.

2007-12-01

Several experiments will be presented that are part of a phased plan to understand the evolution of detonation in a detonator from initiation shock through run to detonation, to full detonation, to transition, to booster and booster detonation. High-speed multiframe schlieren imagery has been used to study several explosive initiation events, such as exploding bridgewires (EBWs), exploding foil initiators (EFIs or "slappers"), direct optical initiation (DOI), and electrostatic discharge. Additionally, a series of tests has been performed on "cut-back" detonators with varying initial pressing heights. We have also used this diagnostic to visualize a range of EBW, EFI, and DOI full-up detonators. Future applications to other explosive events, such as boosters and insensitive high explosives booster evaluation, will be discussed. The EPIC finite element code has been used to analyze the shock fronts from the schlieren images to solve iteratively for consistent boundary or initial conditions to determine the temporal-spatial pressure profile across the output face of the detonator.

Using Schlieren Visualization to Track Detonator Performance

NASA Astrophysics Data System (ADS)

Clarke, Steven; Thomas, Keith; Martinez, Michael; Akinci, Adrian; Murphy, Michael; Adrian, Ronald

2007-06-01

Several experiments that are part of a phased plan to understand the evolution of detonation in a detonator from initiation shock through run to detonation to full detonation to transition to booster and booster detonation will be presented. High Speed Laser Schlieren Movies have been used to study several explosive initiation events, such as exploding bridgewires (EBW), Exploding Foil Initiators (EFI) (or slappers), Direct Optical Initiation (DOI), and ElectroStatic Discharge (ESD). Additionally, a series of tests have been performed on ``cut-back'' detonators with varying initial pressing (IP) heights. We have also used this diagnostic to visualize a range of EBW, EFI, and DOI full-up detonators. Future applications to other explosive events such as boosters and IHE booster evaluation will be discussed. EPIC Hydrodynamic code has been used to analyze the shock fronts from the Schlieren images to reverse calculate likely boundary or initial conditions to determine the temporal-spatial pressure profile across the output face of the detonator. LA-UR-07-1229

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

KSC-00padig010

NASA Image and Video Library

2000-04-22

KENNEDY SPACE CENTER, FLA. -- The one-man submarine dubbed DeepWorker 2000 sits on the deck of Liberty Star, one of two KSC solid rocket booster recovery ships. The sub is being tested on its ability to duplicate the sometimes hazardous job United Space Alliance (USA) divers perform to recover the expended boosters in the ocean after a launch. The boosters splash down in an impact area about 140 miles east of Jacksonville and after recovery are towed back to KSC for refurbishment by the specially rigged recovery ships. DeepWorker 2000 will be used in a demonstration during retrieval operations after the upcoming STS-101 launch. The submarine pilot will demonstrate capabilities to cut tangled parachute riser lines using a manipulator arm and attach a Diver Operator Plug to extract water and provide flotation for the booster. DeepWorker 2000 was built by Nuytco Research Ltd., North Vancouver, British Columbia. It is 8.25 feet long, 5.75 feet high, and weighs 3,800 pounds. USA is a prime contractor to NASA for the Space Shuttle program

AlGaN/GaN-on-Si monolithic power-switching device with integrated gate current booster

NASA Astrophysics Data System (ADS)

Han, Sang-Woo; Jo, Min-Gi; Kim, Hyungtak; Cho, Chun-Hyung; Cha, Ho-Young

2017-08-01

This study investigates the effects of a monolithic gate current booster integrated with an AlGaN/GaN-on-Si power-switching device. The integrated gate current booster was implemented by a single-stage inverter topology consisting of a recessed normally-off AlGaN/GaN MOS-HFET and a mesa resistor. The monolithically integrated gate current booster in a switching FET eliminated the parasitic elements caused by external interconnection and enabled fast switching operation. The gate charging and discharging currents were boosted by the integrated inverter, which significantly reduced both rise and fall times: the rise time was reduced from 626 to 41.26 ns, while the fall time was reduced from 554 to 42.19 ns by the single-stage inverter. When the packaged monolithic power chip was tested under 1 MHz hard-switching operation with VDD = 200 V, the switching loss was found to have been drastically reduced, from 5.27 to 0.55 W.

B-52/Pegasus with X-43A departing on first captive flight.

NASA Technical Reports Server (NTRS)

2001-01-01

The NASA X-43A hypersonic research vehicle and its Pegasus booster rocket, mounted beneath the wing of their B-52 mothership, had a successful first captive-carry flight on April 28, 2001, Basically a dress rehearsal for a subsequent free flight, the captive-carry flight kept the X-43A-and-Pegasus combination attached to the B-52's wing pylon throughout the almost two-hour mission from NASA's Dryden Flight Research Center, Edwards, Calif., over the Pacific Missile Test Range, and back to Dryden. The NASA X-43A hypersonic research vehicle and its Pegasus booster rocket, mounted beneath the wing of their B-52 mothership, had a successful first captive-carry flight on April 28, 2001, Basically a dress rehearsal for a subsequent free flight, the captive-carry flight kept the X-43A-and-Pegasus combination attached to the B-52's wing pylon throughout the almost two-hour mission from NASA's Dryden Flight Research Center, Edwards, Calif., over the Pacific Missile Test Range, and back to Dryden. After taking off from the Dryden Flight Research Center, Edwards, Calif., at 12:33 p.m. PDT, the B-52 soared off the California coast on the predetermined flight path, and returned to Dryden for a 2:19 p.m. PDT landing. Pending thorough evaluation of all flight data, this captive-carry test could lead to the first flight of the X-43A 'stack' as early as mid-May. The first free flight will be air-launched by NASA's B-52 at about 24,000 feet altitude. The booster will accelerate the X-43A to Mach 7 to approximately 95,000 feet altitude. At booster burnout, the X-43 will separate from the booster and fly under its own power on a preprogrammed flight path. The hydrogen-fueled aircraft has a wingspan of approximately 5 feet, measures 12 feet long and weighs about 2,800 pounds.

B-52/Pegasus with X-43A in flight over Pacific Ocean.

NASA Technical Reports Server (NTRS)

2001-01-01

The NASA X-43A hypersonic research vehicle and its Pegasus booster rocket, mounted beneath the wing of their B-52 mothership, had a successful first captive-carry flight on April 28, 2001, Basically a dress rehearsal for a subsequent free flight, the captive-carry flight kept the X-43A-and-Pegasus combination attached to the B-52's wing pylon throughout the almost two-hour mission from NASA's Dryden Flight Research Center, Edwards, Calif., over the Pacific Missile Test Range, and back to Dryden. The NASA X-43A hypersonic research vehicle and its Pegasus booster rocket, mounted beneath the wing of their B-52 mothership, had a successful first captive-carry flight on April 28, 2001, Basically a dress rehearsal for a subsequent free flight, the captive-carry flight kept the X-43A-and-Pegasus combination attached to the B-52's wing pylon throughout the almost two-hour mission from NASA's Dryden Flight Research Center, Edwards, Calif., over the Pacific Missile Test Range, and back to Dryden. After taking off from the Dryden Flight Research Center, Edwards, Calif., at 12:33 p.m. PDT, the B-52 soared off the California coast on the predetermined flight path, and returned to Dryden for a 2:19 p.m. PDT landing. Pending thorough evaluation of all flight data, this captive-carry test could lead to the first flight of the X-43A 'stack' as early as mid-May. The first free flight will be air-launched by NASA's B-52 at about 24,000 feet altitude. The booster will accelerate the X-43A to Mach 7 to approximately 95,000 feet altitude. At booster burnout, the X-43 will separate from the booster and fly under its own power on a preprogrammed flight path. The hydrogen-fueled aircraft has a wingspan of approximately 5 feet, measures 12 feet long and weighs about 2,800 pounds.

Close view of B-52/Pegasus with X-43A in flight.

NASA Technical Reports Server (NTRS)

2001-01-01

The NASA X-43A hypersonic research vehicle and its Pegasus booster rocket, mounted beneath the wing of their B-52 mothership, had a successful first captive-carry flight on April 28, 2001, Basically a dress rehearsal for a subsequent free flight, the captive-carry flight kept the X-43A-and-Pegasus combination attached to the B-52's wing pylon throughout the almost two-hour mission from NASA's Dryden Flight Research Center, Edwards, Calif., over the Pacific Missile Test Range, and back to Dryden. The NASA X-43A hypersonic research vehicle and its Pegasus booster rocket, mounted beneath the wing of their B-52 mothership, had a successful first captive-carry flight on April 28, 2001, Basically a dress rehearsal for a subsequent free flight, the captive-carry flight kept the X-43A-and-Pegasus combination attached to the B-52's wing pylon throughout the almost two-hour mission from NASA's Dryden Flight Research Center, Edwards, Calif., over the Pacific Missile Test Range, and back to Dryden. After taking off from the Dryden Flight Research Center, Edwards, Calif., at 12:33 p.m. PDT, the B-52 soared off the California coast on the predetermined flight path, and returned to Dryden for a 2:19 p.m. PDT landing. Pending thorough evaluation of all flight data, this captive-carry test could lead to the first flight of the X-43A 'stack' as early as mid-May. The first free flight will be air-launched by NASA's B-52 at about 24,000 feet altitude. The booster will accelerate the X-43A to Mach 7 to approximately 95,000 feet altitude. At booster burnout, the X-43 will separate from the booster and fly under its own power on a preprogrammed flight path. The hydrogen-fueled aircraft has a wingspan of approximately 5 feet, measures 12 feet long and weighs about 2,800 pounds.

B-52/Pegasus with X-43A landing after first captive carry flight.

NASA Technical Reports Server (NTRS)

2001-01-01

The NASA X-43A hypersonic research vehicle and its Pegasus booster rocket, mounted beneath the wing of their B-52 mothership, had a successful first captive-carry flight on April 28, 2001, Basically a dress rehearsal for a subsequent free flight, the captive-carry flight kept the X-43A-and-Pegasus combination attached to the B-52's wing pylon throughout the almost two-hour mission from NASA's Dryden Flight Research Center, Edwards, Calif., over the Pacific Missile Test Range, and back to Dryden. The NASA X-43A hypersonic research vehicle and its Pegasus booster rocket, mounted beneath the wing of their B-52 mothership, had a successful first captive-carry flight on April 28, 2001, Basically a dress rehearsal for a subsequent free flight, the captive-carry flight kept the X-43A-and-Pegasus combination attached to the B-52's wing pylon throughout the almost two-hour mission from NASA's Dryden Flight Research Center, Edwards, Calif., over the Pacific Missile Test Range, and back to Dryden. After taking off from the Dryden Flight Research Center, Edwards, Calif., at 12:33 p.m. PDT, the B-52 soared off the California coast on the predetermined flight path, and returned to Dryden for a 2:19 p.m. PDT landing. Pending thorough evaluation of all flight data, this captive-carry test could lead to the first flight of the X-43A 'stack' as early as mid-May. The first free flight will be air-launched by NASA's B-52 at about 24,000 feet altitude. The booster will accelerate the X-43A to Mach 7 to approximately 95,000 feet altitude. At booster burnout, the X-43 will separate from the booster and fly under its own power on a preprogrammed flight path. The hydrogen-fueled aircraft has a wingspan of approximately 5 feet, measures 12 feet long and weighs about 2,800 pounds.

Analytical Evaluation of a Method of Midcourse Guidance for Rendezvous with Earth Satellites

NASA Technical Reports Server (NTRS)

Eggleston, John M.; Dunning, Robert S.

1961-01-01

A digital-computer simulation was made of the midcourse or ascent phase of a rendezvous between a ferry vehicle and a space station. The simulation involved a closed-loop guidance system in which both the relative position and relative velocity between ferry and station are measured (by simulated radar) and the relative-velocity corrections required to null the miss distance are computed and applied. The results are used to study the effectiveness of a particular set of guidance equations and to study the effects of errors in the launch conditions and errors in the navigation data. A number of trajectories were investigated over a variety of initial conditions for cases in which the space station was in a circular orbit and also in an elliptic orbit. Trajectories are described in terms of a rotating coordinate system fixed in the station. As a result of this study the following conclusions are drawn. Successful rendezvous can be achieved even with launch conditions which are substantially less accurate than those obtained with present-day techniques. The average total-velocity correction required during the midcourse phase is directly proportional to the radar accuracy but the miss distance is not. Errors in the time of booster burnout or in the position of the ferry at booster burnout are less important than errors in the ferry velocity at booster burnout. The use of dead bands to account for errors in the navigational (radar) equipment appears to depend upon a compromise between the magnitude of the velocity corrections to be made and the allowable miss distance at the termination of the midcourse phase of the rendezvous. When approximate guidance equations are used, there are limits on their accuracy which are dependent on the angular distance about the earth to the expected point of rendezvous.

Delayed tuberculin reactivity in persons of Indochinese origin: implications for preventive therapy.

PubMed

Robertson, J M; Burtt, D S; Edmonds, K L; Molina, P L; Kiefe, C I; Ellner, J J

1996-05-01

To 1) study a variant delayed reaction to tuberculin testing as a way to enhance screening for tuberculosis among high-risk persons and 2) correlate the delayed reaction with lymphocyte blastogenesis. Cross-sectional study. 2 public health department clinics in North Carolina. 121 adults who had recently emigrated from Vietnam to North Carolina and who were ethnic Vietnamese and ethnic Dega, a minority population group from the central highlands region of Vietnam. Medical history, physical examination, laboratory evaluation, and standard purified protein derivative (PPD) testing (Mantoux method). Skin test results were read at 72 hours and again at 6 days. Variant reactivity was defined as induration of less than 10 mm at 72 hours that, when reassessed at 6 days, had increased in size to 10 mm or greater. Persons with negative (n=54) and variant (n=32) PPD results also had booster testing at 10 to 12 weeks. Serum samples were obtained from 57 participants for lymphocyte blastogenesis studies. 26% of participants had variant tuberculin reactivity. Variant reactivity was strongly associated with booster positivity: Sixty-five percent of persons with variant PPD results had booster positivity compared with 16% of persons with negative PPD results (P<0.001). The lymphocyte blastogenesis response of persons with variant PPD results was between the response of persons with negative PPD results and that of persons with positive PPD results. Variant reactivity in this high-risk group was a predictor of booster positivity. Together with the blastogenic response pattern, this association strongly suggests that variant reactivity has a high positive predictive value for tuberculous infection. Clinicians should incorporate these findings into their approach for choosing candidates for preventive therapy.

KENNEDY SPACE CENTER, FLA. - Mobile Launcher Platform (MLP) number 3 and a set of twin solid rocket boosters bolted to it, atop the crawler-transporter, crawl to the intersection in the crawlerway in support of the second engineering analysis vibration test on the crawler and MLP. In the background are Launch Pads 39A (right) and 39B (left). The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

NASA Image and Video Library

2003-11-21

KENNEDY SPACE CENTER, FLA. - Mobile Launcher Platform (MLP) number 3 and a set of twin solid rocket boosters bolted to it, atop the crawler-transporter, crawl to the intersection in the crawlerway in support of the second engineering analysis vibration test on the crawler and MLP. In the background are Launch Pads 39A (right) and 39B (left). The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

KENNEDY SPACE CENTER, FLA. - The crawler transporter slowly moves the Mobile Launcher Platform (MLP), carrying a set of twin solid rocket boosters, away from the Vehicle Assembly Building (VAB) in support of engineering analysis vibration tests on the crawler and MLP. In the distance, at left, is Launch Pad 39A. The water on the right of the crawlerway is the Banana River. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

NASA Image and Video Library

2003-11-17

KENNEDY SPACE CENTER, FLA. - The crawler transporter slowly moves the Mobile Launcher Platform (MLP), carrying a set of twin solid rocket boosters, away from the Vehicle Assembly Building (VAB) in support of engineering analysis vibration tests on the crawler and MLP. In the distance, at left, is Launch Pad 39A. The water on the right of the crawlerway is the Banana River. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

KENNEDY SPACE CENTER, FLA. - Seen across the water of the Launch Complex 39 turn basin, a crawler-transporter, carrying Mobile Launcher Platform (MLP) number 3 with a set of twin solid rocket boosters bolted atop, crawls out of the 525-foot-tall Vehicle Assembly Building during the second engineering analysis vibration test on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

NASA Image and Video Library

2003-11-21

KENNEDY SPACE CENTER, FLA. - Seen across the water of the Launch Complex 39 turn basin, a crawler-transporter, carrying Mobile Launcher Platform (MLP) number 3 with a set of twin solid rocket boosters bolted atop, crawls out of the 525-foot-tall Vehicle Assembly Building during the second engineering analysis vibration test on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

KENNEDY SPACE CENTER, FLA. - A Kennedy Space Center technician inspects the shoes on one of eight tracks of a crawler-transporter (CT). The CT is moving Mobile Launcher Platform (MLP) number 3 with a set of twin solid rocket boosters bolted on top to the intersection in the crawlerway in support of the second engineering analysis vibration test on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

NASA Image and Video Library

2003-11-21

KENNEDY SPACE CENTER, FLA. - A Kennedy Space Center technician inspects the shoes on one of eight tracks of a crawler-transporter (CT). The CT is moving Mobile Launcher Platform (MLP) number 3 with a set of twin solid rocket boosters bolted on top to the intersection in the crawlerway in support of the second engineering analysis vibration test on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

KENNEDY SPACE CENTER, FLA. - Mobile Launcher Platform (MLP) number 3 and a set of twin solid rocket boosters, atop the crawler-transporter, inch along the crawlerway in support of the second engineering analysis vibration test on the crawler and MLP. The view reveals the river gravel surface that is 4 inches thick on the straightaway sections and 8 inches thick on curves. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

NASA Image and Video Library

2003-11-21

KENNEDY SPACE CENTER, FLA. - Mobile Launcher Platform (MLP) number 3 and a set of twin solid rocket boosters, atop the crawler-transporter, inch along the crawlerway in support of the second engineering analysis vibration test on the crawler and MLP. The view reveals the river gravel surface that is 4 inches thick on the straightaway sections and 8 inches thick on curves. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

KENNEDY SPACE CENTER, FLA. - Viewed across the turn basin in the Launch Complex 39 Area, the crawler transporter slowly moves the Mobile Launcher Platform (MLP), carrying a set of twin solid rocket boosters, away from the Vehicle Assembly Building (VAB). The journey is in support of engineering analysis vibration tests on the crawler and MLP. The water on the right of the crawlerway is the Banana River. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

NASA Image and Video Library

2003-11-17

KENNEDY SPACE CENTER, FLA. - Viewed across the turn basin in the Launch Complex 39 Area, the crawler transporter slowly moves the Mobile Launcher Platform (MLP), carrying a set of twin solid rocket boosters, away from the Vehicle Assembly Building (VAB). The journey is in support of engineering analysis vibration tests on the crawler and MLP. The water on the right of the crawlerway is the Banana River. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

The X-43A hypersonic research aircraft and its modified Pegasus booster rocket mounted to NASA's NB

NASA Technical Reports Server (NTRS)

2001-01-01

The first of three X-43A hypersonic research aircraft and its modified Pegasus booster rocket recently underwent combined systems testing while mounted to NASA's NB-52B carrier aircraft at the Dryden Flight Research Center, Edwards, California. The combined systems test was one of the last major milestones in the Hyper-X research program before the first X-43A flight. One of the major goals of the Hyper-X program is flight validation of airframe-integrated, air-breathing propulsion system, which so far have only been tested in ground facilities, such as wind tunnels. The X-43A flights will be the first actual flight tests of an aircraft powered by a revolutionary supersonic-combustion ramjet ('scramjet') engine capable of operating at hypersonic speeds above Mach 5 (five times the speed of sound). The X-43A design uses the underbody of the aircraft to form critical elements of the engine. The forebody shape helps compress the intake airflow, while the aft section acts as a nozzle to direct thrust. The 12-foot, unpiloted research vehicle was developed and built by MicroCraft Inc., Tullahoma, Tenn., under NASA contract. The booster, built by Orbital Sciences Corp., Dulles, Va., will accelerate the X-43A after the X-43A/booster 'stack' is air-launched from NASA's venerable NB-52 mothership. The X-43A will separate from the rocket at a predetermined altitude and speed and fly a pre-programmed trajectory, conducting aerodynamic and propulsion experiments until it descends into the Pacific Ocean. Three research flights are planned, two at Mach 7 and one at Mach 10.

The X-43A hypersonic research aircraft and its modified Pegasus® booster rocket mounted to NASA's NB-52B carrier aircraft at the Dryden Flight Research Center, Edwards, California

NASA Image and Video Library

2001-03-13

The first of three X-43A hypersonic research aircraft and its modified Pegasus® booster rocket recently underwent combined systems testing while mounted to NASA's NB-52B carrier aircraft at the Dryden Flight Research Center, Edwards, California. The combined systems test was one of the last major milestones in the Hyper-X research program before the first X-43A flight. One of the major goals of the Hyper-X program is flight validation of airframe-integrated, air-breathing propulsion system, which so far have only been tested in ground facilities, such as wind tunnels. The X-43A flights will be the first actual flight tests of an aircraft powered by a revolutionary supersonic-combustion ramjet ("scramjet") engine capable of operating at hypersonic speeds above Mach 5 (five times the speed of sound). The X-43A design uses the underbody of the aircraft to form critical elements of the engine. The forebody shape helps compress the intake airflow, while the aft section acts as a nozzle to direct thrust. The 12-foot, unpiloted research vehicle was developed and built by MicroCraft Inc., Tullahoma, Tenn., under NASA contract. The booster, built by Orbital Sciences Corp., Dulles, Va., will accelerate the X-43A after the X-43A/booster "stack" is air-launched from NASA's venerable NB-52 mothership. The X-43A will separate from the rocket at a predetermined altitude and speed and fly a pre-programmed trajectory, conducting aerodynamic and propulsion experiments until it descends into the Pacific Ocean. Three research flights are planned, two at Mach 7 and one at Mach 10.

KSC00pp0596

NASA Image and Video Library

2000-04-27

The one-man submarine dubbed DeepWorker 2000 sits on the deck of Liberty Star, one of two KSC solid rocket booster recovery ships. The sub is being tested on its ability to duplicate the sometimes hazardous job United Space Alliance (USA) divers perform to recover the expended boosters in the ocean after a launch. The boosters splash down in an impact area about 140 miles east of Jacksonville and after recovery are towed back to KSC for refurbishment by the specially rigged recovery ships. DeepWorker 2000 was built by Nuytco Research Ltd., North Vancouver, British Columbia. It is 8.25 feet long, 5.75 feet high, and weighs 3,800 pounds. USA is a prime contractor to NASA for the Space Shuttle program

KSC-00pp0596

NASA Image and Video Library

2000-04-27

The one-man submarine dubbed DeepWorker 2000 sits on the deck of Liberty Star, one of two KSC solid rocket booster recovery ships. The sub is being tested on its ability to duplicate the sometimes hazardous job United Space Alliance (USA) divers perform to recover the expended boosters in the ocean after a launch. The boosters splash down in an impact area about 140 miles east of Jacksonville and after recovery are towed back to KSC for refurbishment by the specially rigged recovery ships. DeepWorker 2000 was built by Nuytco Research Ltd., North Vancouver, British Columbia. It is 8.25 feet long, 5.75 feet high, and weighs 3,800 pounds. USA is a prime contractor to NASA for the Space Shuttle program

KSC00pp0597

NASA Image and Video Library

2000-04-27

The one-man submarine dubbed DeepWorker 2000 sits on the deck of Liberty Star, one of two KSC solid rocket booster recovery ships. The sub is being tested on its ability to duplicate the sometimes hazardous job United Space Alliance (USA) divers perform to recover the expended boosters in the ocean after a launch. The boosters splash down in an impact area about 140 miles east of Jacksonville and after recovery are towed back to KSC for refurbishment by the specially rigged recovery ships. DeepWorker 2000 was built by Nuytco Research Ltd., North Vancouver, British Columbia. It is 8.25 feet long, 5.75 feet high, and weighs 3,800 pounds. USA is a prime contractor to NASA for the Space Shuttle program

KSC-00pp0597

NASA Image and Video Library

2000-04-27

The one-man submarine dubbed DeepWorker 2000 sits on the deck of Liberty Star, one of two KSC solid rocket booster recovery ships. The sub is being tested on its ability to duplicate the sometimes hazardous job United Space Alliance (USA) divers perform to recover the expended boosters in the ocean after a launch. The boosters splash down in an impact area about 140 miles east of Jacksonville and after recovery are towed back to KSC for refurbishment by the specially rigged recovery ships. DeepWorker 2000 was built by Nuytco Research Ltd., North Vancouver, British Columbia. It is 8.25 feet long, 5.75 feet high, and weighs 3,800 pounds. USA is a prime contractor to NASA for the Space Shuttle program

Subsonic Glideback Rocket Demonstrator Flight Testing

NASA Technical Reports Server (NTRS)

DeTurris, Dianne J.; Foster, Trevor J.; Barthel, Paul E.; Macy, Daniel J.; Droney, Christopher K.; Talay, Theodore A. (Technical Monitor)

2001-01-01

For the past two years, Cal Poly's rocket program has been aggressively exploring the concept of remotely controlled, fixed wing, flyable rocket boosters. This program, embodied by a group of student engineers known as Cal Poly Space Systems, has successfully demonstrated the idea of a rocket design that incorporates a vertical launch pattern followed by a horizontal return flight and landing. Though the design is meant for supersonic flight, CPSS demonstrators are deployed at a subsonic speed. Many steps have been taken by the club that allowed the evolution of the StarBooster prototype to reach its current size: a ten-foot tall, one-foot diameter, composite material rocket. Progress is currently being made that involves multiple boosters along with a second stage, third rocket.

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.

The Scent of the Future: Manned Space Travel and the Soviet Union.

DTIC Science & Technology

1981-06-01

AND ECONOMIC APPLICATIONS 56 GREENHOUSES , BOOSTERS, AND SPACE PLANES: SOVIET SPACE-RELATED RESEARCH AND DEVELOPMENT 72 R.U.R. REVISITED: MANNED VERSUS... greenhouse that was part of their 12-square-meter closed environment.9 6 The successful conclusion of this test demonstrated the feasibility of a manned...will probably be timed to coincide with the XXVI Party Congress which convenes in February 1981. 71 GREENHOUSES , BOOSTERS, AND SPACE PLANES: SOVIET

Immunogenicity and Safety of a Booster Dose of a Live Attenuated Japanese Encephalitis Chimeric Vaccine Given 1 Year After Primary Immunization in Healthy Children in the Republic of Korea.

PubMed

Kim, Dong Soo; Jang, Gwang Cheon; Cha, Sung-Ho; Choi, Soo-Han; Kim, Hwang Min; Kim, Ji Hong; Kang, Jin Han; Kim, Jong-Hyun; Kim, Ki Hwan; Bang, Joon; Naimi, Zulaikha; Bouckenooghe, Alain; Bosch-Castells, Valérie; Houillon, Guy

2016-02-01

This study evaluated the effect of a booster vaccination of a new, live attenuated, Japanese encephalitis chimeric vaccine (JE-CV). Previously this vaccine has been used as a booster 12 months after priming with an inactivated vaccine and at >24 months after priming with the same JE-CV. This study evaluates the immunogenicity and safety of the JE-CV given at 12-24 months after JE-CV priming. Phase III, open-label study in the Republic of Korea in which 119 children previously vaccinated with JE-CV at 12-24 months of age received a JE-CV booster at 12-24 months after primary vaccination. JE neutralizing antibody titers were measured using >50% plaque reduction neutralization test prebooster and 1 month postbooster vaccination. Seroprotection (SP) was defined as ≥10 (1/dil). Safety was assessed for 28 days postvaccination by parental reports. Serious adverse events were monitored for 6 months postvaccination. Antibody persistence was high prebooster (SP rate 93.5%). There was a strong anamnestic response postbooster vaccination, with an SP rate of 100% and a >50-fold increase in geometric mean titer from the prebooster level. Both antibody persistence and the booster response were independent of whether the booster was given at 12-17 or 18-24 months. The safety profile was good and comparable with the primary vaccination; there were no vaccine-related serious adverse events and no deaths. This study confirms the suitability of a JE-CV booster vaccination at 12-24 months after a primary dose of the same vaccine given at 12-24 months of age in children in the Republic of Korea.

Long-term Immunogenicity of a Single Dose of Japanese Encephalitis Chimeric Virus Vaccine in Toddlers and Booster Response 5 Years After Primary Immunization.

PubMed

Kosalaraksa, Pope; Watanaveeradej, Veerachai; Pancharoen, Chitsanu; Capeding, Maria Rosario; Feroldi, Emmanuel; Bouckenooghe, Alain

2017-04-01

Japanese encephalitis (JE) is an important mosquito-borne viral disease that is endemic in Asia, Western Pacific countries and Northern Australia. Although there is no antiviral treatment, vaccination is effective in preventing this disease. We followed a cohort of 596 children for 5 years after primary vaccination at 12-18 months of age with JE chimeric virus vaccine (JE-CV; IMOJEV) in a multicenter, phase III trial in Thailand and the Philippines to assess antibody persistence and safety. At the end of the 5 years, a subgroup of 85 participants, at 1 site in Thailand, was followed after administration of a JE-CV booster vaccination. JE antibody titers were measured annually after primary vaccination and 28 days after booster vaccination using a 50% plaque reduction neutralization test. Seroprotection was defined as a JE-CV neutralizing antibody titer ≥10 (1/dil). Kaplan-Meier survival analysis was used to estimate the proportion of participants maintaining protective JE-CV neutralizing antibody titers. At 1, 2, 3, 4 and 5 years after vaccination with JE-CV, 88.5%, 82.9%, 78.2%, 74.0% and 68.6% of the participants followed remained seroprotected. Geometric mean titers in the subgroup assessed after receipt of a booster dose increased from 61.2 (95% confidence interval: 43.8-85.7) pre-booster to 4951 (95% confidence interval: 3928-6241) 28 days post-booster, with all participants seroprotected. There were no safety concerns identified. Protective immune responses persisted for at least 5 years after a JE-CV primary immunization in the majority of participants. JE-CV booster induced a robust immune response even after a 5-year interval.

X-43A hypersonic research aircraft mated to its modified Pegasus booster rocket.

NASA Technical Reports Server (NTRS)

2001-01-01

The first of three X-43A hypersonic research aircraft was mated to its modified Pegasus booster rocket in late January at NASA's Dryden Flight Research Center, Edwards, Calif. FIRST X-43A MATED TO BOOSTER -- The first of three X-43A hypersonic research aircraft was mated to its modified Pegasus booster rocket in late January at NASA's Dryden Flight Research Center, Edwards, Calif. Mating of the X-43A and its specially-designed adapter to the first stage of the booster rocket marks a major milestone in the Hyper-X hypersonic research program. The 12-foot, unpiloted research vehicle was developed and built by MicroCraft Inc., Tullahoma, Tenn., for NASA. The booster, built by Orbital Sciences Corp., Dulles, Va., will accelerate the X-43A after the X-43A booster 'stack' is air-launched from NASA's venerable NB-52 mothership. The X-43A will separate from the rocket at a predetermined altitude and speed and fly a pre-programmed trajectory, conducting aerodynamic and propulsion experiments until it impacts into the Pacific Ocean. Three research flights are planned, two at Mach 7 and one at Mach 10 (seven and 10 times the speed of sound respectively) with the first tentatively scheduled for early summer of 2001. The X-43A is powered by a revolutionary supersonic-combustion ramjet ('scramjet') engine, and will use the underbody of the aircraft to form critical elements of the engine. The forebody shape helps compress the intake airflow, while the aft section acts as a nozzle to direct thrust. The X-43A flights will be the first actual flight tests of an aircraft powered by an air-breathing scramjet engine.

Developing the World's Most Powerful Solid Booster

NASA Technical Reports Server (NTRS)

Priskos, Alex S.; Frame, Kyle L.

2016-01-01

NASA's Journey to Mars has begun. Indicative of that challenge, this will be a multi-decadal effort requiring the development of technology, operational capability, and experience. The first steps are underway with more than 15 years of continuous human operations aboard the International Space Station (ISS) and development of commercial cargo and crew transportation capabilities. NASA is making progress on the transportation required for deep space exploration - the Orion crew spacecraft and the Space Launch System (SLS) heavy-lift rocket that will launch Orion and large components such as in-space stages, habitat modules, landers, and other hardware necessary for deep-space operations. SLS is a key enabling capability and is designed to evolve with mission requirements. The initial configuration of SLS - Block 1 - will be capable of launching more than 70 metric tons (t) of payload into low Earth orbit, greater mass than any other launch vehicle in existence. By enhancing the propulsion elements and larger payload fairings, future SLS variants will launch 130 t into space, an unprecedented capability that simplifies hardware design and in-space operations, reduces travel times, and enhances two solid propellant five-segment boosters, both based on space shuttle technologies. This paper will focus on development of the booster, which will provide more than 75 percent of total vehicle thrust at liftoff. Each booster is more than 17 stories tall, 3.6 meters (m) in diameter and weighs 725,000 kilograms (kg). While the SLS booster appears similar to the shuttle booster, it incorporates several changes. The additional propellant segment provides additional booster performance. Parachutes and other hardware associated with recovery operations have been deleted and the booster designated as expendable for affordability reasons. The new motor incorporates new avionics, new propellant grain, asbestos-free case insulation, a redesigned nozzle, streamlined manufacturing processes, and new inspection techniques. New materials and processes provide improved performance, safety, and affordability but also have led to challenges for the government/industry development team. The team completed its first full-size qualification motor test firing in early 2015. The second is scheduled for mid-2016. This paper will discuss booster accomplishments to date, as well as challenges and milestones ahead.

Innovative Comparison of Transient Ignition Temperature at the Booster Interface, New Stainless Steel Pyrovalve Primer Chamber Assembly "V" (PCA) Design Versus the Current Aluminum "Y" PCA Design

NASA Technical Reports Server (NTRS)

Saulsberry, Regor L.; McDougle, Stephen H.; Garcia,Roberto; Johnson, Kenneth L.; Sipes, William; Rickman, Steven; Hosangadi, Ashvin

2011-01-01

An assessment of four spacecraft pyrovalve anomalies that occurred during ground testing was conducted by the NASA Engineering & Safety Center (NESC) in 2008. In all four cases, a common aluminum (Al) primer chamber assembly (PCA) was used with dual NASA Standard Initiators (NSIs) and the nearly simultaneous (separated by less than 80 microseconds) firing of both initiators failed to ignite the booster charge. The results of the assessment and associated test program were reported in AIAA Paper AIAA-2008-4798, NESC Independent Assessment of Pyrovalve Ground Test Anomalies. As a result of the four Al PCA anomalies, and the test results and findings of the NESC assessment, the Mars Science Laboratory (MSL) project team decided to make changes to the PCA. The material for the PCA body was changed from aluminum (Al) to stainless steel (SS) to avoid melting, distortion, and potential leakage of the NSI flow passages when the device functioned. The flow passages, which were interconnected in a Y-shaped configuration (Y-PCA) in the original design, were changed to a V-shaped configuration (V-PCA). The V-shape was used to more efficiently transfer energy from the NSIs to the booster. Development and qualification testing of the new design clearly demonstrated faster booster ignition times compared to the legacy AL Y-PCA design. However, the final NESC assessment report recommended that the SS V-PCA be experimentally characterized and quantitatively compared to the Al Y-PCA design. This data was deemed important for properly evaluating the design options for future NASA projects. This test program has successfully quantified the improvement of the SS V-PCA over the Al Y-PCA. A phase B of the project was also conducted and evaluated the effect of firing command skew and enlargement of flame channels to further assist spacecraft applications.

Solid Rocket Booster (SRB) Flight System Integration at Its Best

NASA Technical Reports Server (NTRS)

Wood, T. David; Kanner, Howard S.; Freeland, Donna M.; Olson, Derek T.

2011-01-01

The Solid Rocket Booster (SRB) element integrates all the subsystems needed for ascent flight, entry, and recovery of the combined Booster and Motor system. These include the structures, avionics, thrust vector control, pyrotechnic, range safety, deceleration, thermal protection, and retrieval systems. This represents the only human-rated, recoverable and refurbishable solid rocket ever developed and flown. Challenges included subsystem integration, thermal environments and severe loads (including water impact), sometimes resulting in hardware attrition. Several of the subsystems evolved during the program through design changes. These included the thermal protection system, range safety system, parachute/recovery system, and others. Because the system was recovered, the SRB was ideal for data and imagery acquisition, which proved essential for understanding loads, environments and system response. The three main parachutes that lower the SRBs to the ocean are the largest parachutes ever designed, and the SRBs are the largest structures ever to be lowered by parachutes. SRB recovery from the ocean was a unique process and represented a significant operational challenge; requiring personnel, facilities, transportation, and ground support equipment. The SRB element achieved reliability via extensive system testing and checkout, redundancy management, and a thorough postflight assessment process. However, the in-flight data and postflight assessment process revealed the hardware was affected much more strongly than originally anticipated. Assembly and integration of the booster subsystems required acceptance testing of reused hardware components for each build. Extensive testing was done to assure hardware functionality at each level of stage integration. Because the booster element is recoverable, subsystems were available for inspection and testing postflight, unique to the Shuttle launch vehicle. Problems were noted and corrective actions were implemented as needed. The postflight assessment process was quite detailed and a significant portion of flight operations. The SRBs provided fully redundant critical systems including thrust vector control, mission critical pyrotechnics, avionics, and parachute recovery system. The design intent was to lift off with full redundancy. On occasion, the redundancy management scheme was needed during flight operations. This paper describes some of the design challenges and technical issues, how the design evolved with time, and key areas where hardware reusability contributed to improved system level understanding.

Solid Rocket Booster (SRB) - Evolution and Lessons Learned During the Shuttle Program

NASA Technical Reports Server (NTRS)

Kanner, Howard S.; Freeland, Donna M.; Olson, Derek T.; Wood, T. David; Vaccaro, Mark V.

2011-01-01

The Solid Rocket Booster (SRB) element integrates all the subsystems needed for ascent flight, entry, and recovery of the combined Booster and Motor system. These include the structures, avionics, thrust vector control, pyrotechnic, range safety, deceleration, thermal protection, and retrieval systems. This represents the only human-rated, recoverable and refurbishable solid rocket ever developed and flown. Challenges included subsystem integration, thermal environments and severe loads (including water impact), sometimes resulting in hardware attrition. Several of the subsystems evolved during the program through design changes. These included the thermal protection system, range safety system, parachute/recovery system, and others. Obsolescence issues occasionally required component recertification. Because the system was recovered, the SRB was ideal for data and imagery acquisition, which proved essential for understanding loads and system response. The three main parachutes that lower the SRBs to the ocean are the largest parachutes ever designed, and the SRBs are the largest structures ever to be lowered by parachutes. SRB recovery from the ocean was a unique process and represented a significant operational challenge; requiring personnel, facilities, transportation, and ground support equipment. The SRB element achieved reliability via extensive system testing and checkout, redundancy management, and a thorough postflight assessment process. Assembly and integration of the booster subsystems was a unique process and acceptance testing of reused hardware components was required for each build. Extensive testing was done to assure hardware functionality at each level of stage integration. Because the booster element is recoverable, subsystems were available for inspection and testing postflight, unique to the Shuttle launch vehicle. Problems were noted and corrective actions were implemented as needed. The postflight assessment process was quite detailed and a significant portion of flight operations. The SRBs provided fully redundant critical systems including thrust vector control, mission critical pyrotechnics, avionics, and parachute recovery system. The design intent was to lift off with full redundancy. On occasion, the redundancy management scheme was needed during flight operations. This paper describes some of the design challenges, how the design evolved with time, and key areas where hardware reusability contributed to improved system level understanding.

A comparison of self-report and direct observation of booster seat use in Latino families.

PubMed

Quistberg, D Alex; Lozano, Paula; Mack, Christopher D; Schwartz, Rachel; Ebel, Beth E

2010-08-01

To develop a reliable self-report tool for measuring child booster seat use among Latino families. Cross-sectional and observational survey of a convenience sample. Five retail stores in King County, Washington. 50 parents of children 4-8 years old that self-identified as Latino or Hispanic. Parent-reported measures of how often the child uses a booster seat, if the child used a booster seat on the last trip, how often the child complains about using a booster seat, how often the child asks to not use a booster seat, and how often other families they know use a booster seat. Observed booster seat use by child. 26 children (52%) were observed using a booster seat. Parent-reported booster seat use was a poor predictor of observed booster seat use. Although 34 parents reported that their child 'always' uses a booster seat, 8 (24%) of these children were not using a booster seat. A logistic model to predict booster seat use had a sensitivity of 81% and a specificity of 71%, and misclassified 24% of the participants' observed use. Reliance on parent-reported booster seat use significantly overstated observed booster seat use in the study. Among this study population, accurate determination of booster seat use required direct observation.

Design and Evaluation of a Clock Multiplexing Circuit for the SSRL Booster Accelerator Timing System - Oral Presentation

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

Araya, Million

2015-08-25

SPEAR3 is a 234 m circular storage ring at SLAC’s synchrotron radiation facility (SSRL) in which a 3 GeV electron beam is stored for user access. Typically the electron beam decays with a time constant of approximately 10hr due to electron lose. In order to replenish the lost electrons, a booster synchrotron is used to accelerate fresh electrons up to 3GeV for injection into SPEAR3. In order to maintain a constant electron beam current of 500mA, the injection process occurs at 5 minute intervals. At these times the booster synchrotron accelerates electrons for injection at a 10Hz rate. A 10Hzmore » 'injection ready' clock pulse train is generated when the booster synchrotron is operating. Between injection intervalswhere the booster is not running and hence the 10 Hz ‘injection ready’ signal is not present-a 10Hz clock is derived from the power line supplied by Pacific Gas and Electric (PG&E) to keep track of the injection timing. For this project I constructed a multiplexing circuit to 'switch' between the booster synchrotron 'injection ready' clock signal and PG&E based clock signal. The circuit uses digital IC components and is capable of making glitch-free transitions between the two clocks. This report details construction of a prototype multiplexing circuit including test results and suggests improvement opportunities for the final design.« less

Design and Evaluation of a Clock Multiplexing Circuit for the SSRL Booster Accelerator Timing System - Final Paper

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

Araya, Million

2015-08-21

SPEAR3 is a 234 m circular storage ring at SLAC’s synchrotron radiation facility (SSRL) in which a 3 GeV electron beam is stored for user access. Typically the electron beam decays with a time constant of approximately 10hr due to electron lose. In order to replenish the lost electrons, a booster synchrotron is used to accelerate fresh electrons up to 3GeV for injection into SPEAR3. In order to maintain a constant electron beam current of 500mA, the injection process occurs at 5 minute intervals. At these times the booster synchrotron accelerates electrons for injection at a 10Hz rate. A 10Hzmore » 'injection ready' clock pulse train is generated when the booster synchrotron is operating. Between injection intervals-where the booster is not running and hence the 10 Hz ‘injection ready’ signal is not present-a 10Hz clock is derived from the power line supplied by Pacific Gas and Electric (PG&E) to keep track of the injection timing. For this project I constructed a multiplexing circuit to 'switch' between the booster synchrotron 'injection ready' clock signal and PG&E based clock signal. The circuit uses digital IC components and is capable of making glitch-free transitions between the two clocks. This report details construction of a prototype multiplexing circuit including test results and suggests improvement opportunities for the final design.« less

Fracture Toughness, Mechanical Property, And Chemical Characterization Of A Critical Modification To The NASA SLS Solid Booster Internal Material System

NASA Technical Reports Server (NTRS)

Pancoast, Justin; Garrett, William; Moe, Gulia

2015-01-01

A modified propellant-liner-insulation (PLI) bondline in the Space Launch System (SLS) solid rocket booster required characterization for flight certification. The chemical changes to the PLI bondline and the required additional processing have been correlated to mechanical responses of the materials across the bondline. Mechanical properties testing and analyses included fracture toughness, tensile, and shear tests. Chemical properties testing and analyses included Fourier transform infrared (FTIR) spectroscopy, cross-link density, high-performance liquid chromatography (HPLC), gas chromatography (GC), gel permeation chromatography (GPC), and wave dispersion X-ray fluorescence (WDXRF). The testing identified the presence of the expected new materials and found the functional bondline performance of the new PLI system was not significantly changed from the old system.

Ascent heat transfer rate distribution on the North American Rockwell delta wing orbiter and the General Dynamics/Convair booster at a Mach number of 8 (mated)

NASA Technical Reports Server (NTRS)

Matthews, R. K.; Martindale, W. R.; Warmbrod, J. D.

1972-01-01

A wind tunnel test program to determine aerodynamic interference heating on the North American Rockwell orbiter mated with the General Dynamics Convair booster is discussed. The tests were conducted at the Arnold Engineering Development Center (AEDC) in Tunnel B of the von Karman Gas Dynamics Facility (VKF). The test period was June 1971. Heat-transfer rates were determined by the phase-change paint technique on 0.013-scale Stycast models using Tempilaq as the surface temperature indicator. The nominal test conditions were: Mach 8, free-stream unit length Reynolds numbers of 1.25 x one million and 2.55 x one million angles of attack of -5, 0, +5 deg. Model details, test conditions, phase-change paint photographs and reduced heat-transfer coefficients are presented.

Robust and novel two degree of freedom fractional controller based on two-loop topology for inverted pendulum.

PubMed

Dwivedi, Prakash; Pandey, Sandeep; Junghare, A S

2018-04-01

A rotary single inverted pendulum (RSIP) typically represents a space booster rocket, Segway and similar systems with unstable equilibrium. This paper proposes a novel two degree of freedom (2-DOF) fractional control strategy based on 2-loop topology for RSIP system which can be extended to control the systems with unstable equilibrium. It comprises feedback and feed-forward paths. Primary controller relates the perturbation attenuation while the secondary controller is accountable for set point tracking. To tune the parameters of proposed fractional controller a simple graphical tuning method based on frequency response is used. The study will serve the outstanding experimental results for both, stabilization and trajectory tracking tasks. The study will also serve to present a comparison of the performance of the proposed controller with the 1-DOF FOPID controller and sliding mode controller (SMC) for the RSIP system. Further to confirm the usability of the proposed controller and to avoid the random perturbations sensitivity, robustness, and stability analysis through fractional root-locus and Bode-plot is investigated. Copyright © 2018 ISA. Published by Elsevier Ltd. All rights reserved.

77 FR 11625 - Child Restraint Systems

Federal Register 2010, 2011, 2012, 2013, 2014

2012-02-27

...),'' Stammen; Vehicle Research and Test Center, National Highway Traffic Safety Administration (September 2004... exceeded. However, during extensive post-NPRM booster seat testing, inconsistencies in the test protocol... substantial rulemaking and research efforts to try to address test variability. NHTSA investigated the ATD's...

Aerodynamic characteristics of MSFC model 454 of the 142 inch solid rocket booster tested in the LeRC 10 foot SWT at Mach numbers of 2.0 and 2.7 (SA6F)

NASA Technical Reports Server (NTRS)

Johnson, J. D.; Burstadt, P. L.; Radford, W. D.

1975-01-01

A 2.112 percent scale Space Shuttle Solid Rocket Booster (SRB) was tested in a ten foot, supersonic wind tunnel. The test Mach numbers were 2.0 and 2.7. Test angles of attack were from minus 5 degrees to plus 185 degrees. The Reynolds numbers ranged from 0.514 to 2.81 million per foot. Test roll angles were 0, 22.5, 45, 90, and 135 degrees. The following configurations were tested: (1) SRB without external protuberances, (2) SRB with an electrical tunnel and a thrust attachment structure, (3) SRB with two engine shroud strakes, (4) SRB with eight engine shroud strakes, and (5) SRB with an electrical tunnel, thrust attachment structure, eight engine shroud strakes, and separation motors.

Thermal Analysis in Support of the Booster Separation Motor Crack Investigation

NASA Technical Reports Server (NTRS)

Davis, Darrell; Prickett, Terry; Turner, Larry D. (Technical Monitor)

2001-01-01

During a post-test inspection of a Booster Separation Motor (BSM) from a Lot Acceptance Test (LAT), a crack was noticed in the graphite throat. Since this was an out-of-family occurrence, an investigation team was formed to determine the cause of the crack. This paper will describe thermal analysis techniques used in support of this investigation. Models were generated to predict gradients in nominal motor conditions, as well as potentially anomalous conditions. Analysis was also performed on throats that were tested in the Laser Hardened Material Evaluation Laboratory (LHMEL). Some of these throats were pre-cracked, while others represented configurations designed to amplify effects of thermal stresses. Results from these analyses will be presented in this paper.

Thermal Analysis in Support of the Booster Separation Motor Crack Investigation

NASA Technical Reports Server (NTRS)

Davis, Darrell; Prickett, Terry

2002-01-01

During a post-test inspection of a Booster Separation Motor (BSM) from a Lot Acceptance Test (LAT), a crack was noticed in the graphite throat. Since this was an out-of-family occurrence, an investigation team was formed to determine the cause of the crack. This paper will describe thermal analysis techniques used in support of this investigation. Models were generated to predict gradients in nominal motor conditions, as well as potentially anomalous conditions. Analysis was also performed on throats that were tested in the Laser Hardened Material Evaluation Laboratory (LHMEL). Some of these throats were pre-cracked, while others represented configurations designed to amplify effects of thermal stresses. Results from these analyses will be presented in this paper.

An analysis of the booster plume impingement environment during the space shuttle nominal staging maneuver

NASA Technical Reports Server (NTRS)

Wojciechowski, C. J.; Penny, M. M.; Greenwood, T. F.; Fossler, I. H.

1972-01-01

An experimental study of the plume impingement heating on the space shuttle booster afterbody resulting from the space shuttle orbiter engine plumes was conducted. The 1/100-scale model tests consisted of one and two orbiter engine firings on a flat plate, a flat plate with a fin, and a cylinder model. The plume impingement heating rates on these surfaces were measured using thin film heat transfer gages. Results indicate the engine simulation is a reasonable approximation to the two engine configuration, but more tests are needed to verify the plume model of the main engine configuration. For impingment, results show models experienced laminar boundary layer convective heating. Therefore, tests at higher Reynolds numbers are needed to determine impingment heating.

KSC-2014-2560

NASA Image and Video Library

2014-05-07

CAPE CANAVERAL, Fla. -- A transporter for oversize loads carries the port booster for the United Launch Alliance Delta IV Heavy for Exploration Flight Test-1, or EFT-1, into the Horizontal Integration Facility, or HIF, at Space Launch Complex 37 on Cape Canaveral Air Force Station in Florida. The port booster joins the other two boosters of the Delta IV Heavy already in the HIF. The upper stage and spacecraft adapter arrived with the booster on a barge at the U.S. Army Outpost wharf at Port Canaveral, and were transported to the HIF on May 6. At the HIF, all three booster stages will be processed and checked out before being moved to the nearby launch pad and hoisted into position. The spacecraft adapter will connect Orion to the ULA Delta IV, and also will connect Orion to NASA's new rocket, the Space Launch System, on its first mission in 2017. During the EFT-1 mission, Orion will travel farther into space than any human spacecraft has gone in more than 40 years. The data gathered during the flight will influence design decisions, validate existing computer models and innovative new approaches to space systems development, as well as reduce overall mission risks and costs for later Orion flights. Liftoff of Orion on EFT-1 is planned for fall 2014. Photo credit: NASA/Kim Shiflett

KSC-2014-2558

NASA Image and Video Library

2014-05-07

CAPE CANAVERAL, Fla. -- A transporter for oversize loads carries the port booster for the United Launch Alliance Delta IV Heavy for Exploration Flight Test-1, or EFT-1, into the Horizontal Integration Facility, or HIF, at Space Launch Complex 37 on Cape Canaveral Air Force Station in Florida. The port booster joins the other two boosters of the Delta IV Heavy already in the HIF. The upper stage and spacecraft adapter arrived with the booster on a barge at the U.S. Army Outpost wharf at Port Canaveral, and were transported to the HIF on May 6. At the HIF, all three booster stages will be processed and checked out before being moved to the nearby launch pad and hoisted into position. The spacecraft adapter will connect Orion to the ULA Delta IV, and also will connect Orion to NASA's new rocket, the Space Launch System, on its first mission in 2017. During the EFT-1 mission, Orion will travel farther into space than any human spacecraft has gone in more than 40 years. The data gathered during the flight will influence design decisions, validate existing computer models and innovative new approaches to space systems development, as well as reduce overall mission risks and costs for later Orion flights. Liftoff of Orion on EFT-1 is planned for fall 2014. Photo credit: NASA/Kim Shiflett

KSC-2014-2559

NASA Image and Video Library

2014-05-07

CAPE CANAVERAL, Fla. -- A transporter for oversize loads carries the port booster for the United Launch Alliance Delta IV Heavy for Exploration Flight Test-1, or EFT-1, into the Horizontal Integration Facility, or HIF, at Space Launch Complex 37 on Cape Canaveral Air Force Station in Florida. The port booster joins the other two boosters of the Delta IV Heavy already in the HIF. The upper stage and spacecraft adapter arrived with the booster on a barge at the U.S. Army Outpost wharf at Port Canaveral, and were transported to the HIF on May 6. At the HIF, all three booster stages will be processed and checked out before being moved to the nearby launch pad and hoisted into position. The spacecraft adapter will connect Orion to the ULA Delta IV, and also will connect Orion to NASA's new rocket, the Space Launch System, on its first mission in 2017. During the EFT-1 mission, Orion will travel farther into space than any human spacecraft has gone in more than 40 years. The data gathered during the flight will influence design decisions, validate existing computer models and innovative new approaches to space systems development, as well as reduce overall mission risks and costs for later Orion flights. Liftoff of Orion on EFT-1 is planned for fall 2014. Photo credit: NASA/Kim Shiflett

Space shuttle: Aerodynamic characteristics of various MDAC space shuttle ascent configurations with parallel burn pressure-fed and SRM boosters. Volume 1: Tanks T1 and T2 ascent configurations

NASA Technical Reports Server (NTRS)

Jarrett, T. W.

1972-01-01

Various space shuttle ascent configurations were tested in a trisonic wind tunnel to determine the aerodynamic characteristics. The ascent configuration consisted of a NASA/MSC 040 orbiter in combination with various HO centerline tank and booster geometries. The aerodynamic interference between components of the space shuttle and the effect on the orbiter aerodynamics was determined. The various aerodynamic configurations tested were: (1) centerline HO tanks T1 and T2, (2) centerline HO tank T3, and (3) centerline HO tank H4.

The effects of solid rocket motor effluents on selected surfaces and solid particle size, distribution, and composition for simulated shuttle booster separation motors

NASA Technical Reports Server (NTRS)

Jex, D. W.; Linton, R. C.; Russell, W. M.; Trenkle, J. J.; Wilkes, D. R.

1976-01-01

A series of three tests was conducted using solid rocket propellants to determine the effects a solid rocket plume would have on thermal protective surfaces (TPS). The surfaces tested were those which are baselined for the shuttle vehicle. The propellants used were to simulate the separation solid rocket motors (SSRM) that separate the solid rocket boosters (SRB) from the shuttle launch vehicle. Data cover: (1) the optical effects of the plume environment on spacecraft related surfaces, and (2) the solid particle size, distribution, and composition at TPS sample locations.

Delta Mariner arrival with EFT-1 Booster

NASA Image and Video Library

2014-03-03

CAPE CANAVERAL, Fla. – The United Launch Alliance barge Delta Mariner enters Port Canaveral in Florida. The barge is carrying two of the booster stages for the Delta IV Heavy rocket slated for Orion's Exploration Flight Test-1, or EFT-1. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep-space return velocities. The first unpiloted test flight of Orion is scheduled to launch in September 2014 atop a Delta IV Heavy rocket and in 2017 on NASA’s Space Launch System

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.

KSC-2009-6025

NASA Image and Video Library

2009-10-30

CAPE CANAVERAL, Fla. – The solid rocket booster recovery ship Freedom Star, towing the spent first stage of NASA's Ares I-X rocket, traverses the Banana River along the shore of Cape Canaveral Air Force Station in Florida. Across the river, in the background, is the Vehicle Assembly Building at NASA's Kennedy Space Center. Following the launch of the Ares I-X flight test, the booster splashed down in the Atlantic Ocean and was recovered. Liftoff of the 6-minute flight test was at 11:30 a.m. EDT Oct. 28. This was the first launch from Kennedy's pads of a vehicle other than the space shuttle since the Apollo Program's Saturn rockets were retired. The parts used to make the Ares I-X booster flew on 30 different shuttle missions ranging from STS-29 in 1989 to STS-106 in 2000. The data returned from more than 700 sensors throughout the rocket will be used to refine the design of future launch vehicles and bring NASA one step closer to reaching its exploration goals. For information on the Ares I-X vehicle and flight test, visit http://www.nasa.gov/aresIX. Photo credit: NASA/Kim Shiflett

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

NASA Technical Reports Server (NTRS)

Mazurkivich, Pete; Chandler, Frank; Nguyen, Han

2005-01-01

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

Space Launch System Base Heating Test: Sub-Scale Rocket Engine/Motor Design, Development and Performance Analysis

NASA Technical Reports Server (NTRS)

Mehta, Manish; Seaford, Mark; Kovarik, Brian; Dufrene, Aaron; Solly, Nathan; Kirchner, Robert; Engel, Carl D.

2014-01-01

The Space Launch System (SLS) base heating test is broken down into two test programs: (1) Pathfinder and (2) Main Test. The Pathfinder Test Program focuses on the design, development, hot-fire test and performance analyses of the 2% sub-scale SLS core-stage and booster element propulsion systems. The core-stage propulsion system is composed of four gaseous oxygen/hydrogen RS-25D model engines and the booster element is composed of two aluminum-based model solid rocket motors (SRMs). The first section of the paper discusses the motivation and test facility specifications for the test program. The second section briefly investigates the internal flow path of the design. The third section briefly shows the performance of the model RS-25D engines and SRMs for the conducted short duration hot-fire tests. Good agreement is observed based on design prediction analysis and test data. This program is a challenging research and development effort that has not been attempted in 40+ years for a NASA vehicle.

KENNEDY SPACE CENTER, FLA. - A high-flying bird takes a closer look at the Mobile Launcher Platform (MLP) number 3 with twin solid rocket boosters bolted to it as it crawls toward Launch Pad 39A, in the background. The crawler is moving along the crawlerway at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

NASA Image and Video Library

2003-11-21

KENNEDY SPACE CENTER, FLA. - A high-flying bird takes a closer look at the Mobile Launcher Platform (MLP) number 3 with twin solid rocket boosters bolted to it as it crawls toward Launch Pad 39A, in the background. The crawler is moving along the crawlerway at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it travels toward Launch Pad 39A and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

Special Aspects of Flight Dynamics of a Reusable Cryogenic Booster Stage

NASA Astrophysics Data System (ADS)

Klevanski, J.; Sippel, M.

2005-02-01

The semi-reusable Space Transportation System (STS) investigated in the German ASTRA research program consists of two reusable winged liquid fly-back booster stages called LFBB attached to the expendable Ariane 5 core at an upgraded technology level. The focus of the presented study is the in-depth research of the special aspects of flight dynamics of a LFBB in all flight phases and especially the investigation of the trimmablity, stability and controllability. The LFBB-layout is developed under consideration of tight structural and geometrical constraints of using European cryogenic rocket engine technology [1]. These design conditions result in the special LFBB layout features, such as its large diameter fuselage and a forward position of the air-breathing engines. The great variation in the location of the center of pressure for different Mach numbers caused by large diameter fuselage and a wide range of center of gravity position demand canards for trim and control purposes. The aerodynamic investigation loop performed by the DLR Institute of Aerodynamics and Flow Technology in Braunschweig [2],[3] and in the DLR Wind Tunnel in Cologne [6] allowed optimizing the key features of the aerodynamical layout, such as the canards shape and the wing profile. The main task of this study is the investigation of the longitudinal flight dynamics of the LFBB using the obtained aerodynamic data within a closed loop simulation taking into account rigid body equations of motion, control law and actuators by realistic assumption. This paper discusses the controllability of the whole STS during the ascent phase until separation including wind gust influence, guaranteeing of the structural constraints during re-entry phase and the trimmablity and controllability of the LFBB during the cruise return flight. The flight dynamics behavior of the LFBB is investigated for different center of gravity positions with reasonable margins.

Space Shuttle Project

NASA Image and Video Library

1978-10-04

The Shuttle Orbiter Enterprise inside of Marshall Space Flight Center's Dynamic Test Stand for Mated Vertical Ground Vibration tests (MVGVT). The tests marked the first time ever that the entire shuttle complement including Orbiter, external tank, and solid rocket boosters were vertically mated.

Space shuttle: Aerodynamic characteristics of the Titan T 3 (1207-4)/GAC H-33 launch configuration

NASA Technical Reports Server (NTRS)

Sims, J. F.

1972-01-01

Aerodynamic data obtained in a 14-inch trisonic wind tunnel test on static stability and drag of 0.003366-scale models of the Grumman H-33 drop tank orbiter and the Titan T 3 (1207-4) expendable booster are presented. The orbiter was mounted to the booster both piggyback and tandem. Data were obtained over a Mach number range of 0.6 to 5.0. Angle of attack data were obtained from -16 deg to +4 deg at both 0 deg and -6 deg sideslip for the piggyback configuration, but were limited to -10 deg to +10 deg at 0 deg sideslip for the tandem configuration. Primary configuration variations, other than piggyback and tandem mount, were the number and location of solid propellant strap-on boosters.

KSC-00pp0598

NASA Image and Video Library

2000-04-27

The one-man submarine dubbed DeepWorker 2000 sits on the deck of Liberty Star, one of two KSC solid rocket booster recovery ships. Inside the sub is the pilot, Anker Rasmussen. The sub is being tested on its ability to duplicate the sometimes hazardous job United Space Alliance (USA) divers perform to recover the expended boosters in the ocean after a launch. The boosters splash down in an impact area about 140 miles east of Jacksonville and after recovery are towed back to KSC for refurbishment by the specially rigged recovery ships. DeepWorker 2000 was built by Nuytco Research Ltd., North Vancouver, British Columbia. It is 8.25 feet long, 5.75 feet high, and weighs 3,800 pounds. USA is a prime contractor to NASA for the Space Shuttle program

KSC00pp0598

NASA Image and Video Library

2000-04-27

The one-man submarine dubbed DeepWorker 2000 sits on the deck of Liberty Star, one of two KSC solid rocket booster recovery ships. Inside the sub is the pilot, Anker Rasmussen. The sub is being tested on its ability to duplicate the sometimes hazardous job United Space Alliance (USA) divers perform to recover the expended boosters in the ocean after a launch. The boosters splash down in an impact area about 140 miles east of Jacksonville and after recovery are towed back to KSC for refurbishment by the specially rigged recovery ships. DeepWorker 2000 was built by Nuytco Research Ltd., North Vancouver, British Columbia. It is 8.25 feet long, 5.75 feet high, and weighs 3,800 pounds. USA is a prime contractor to NASA for the Space Shuttle program

Effect of engine shroud configuration on the static aerodynamic characteristics of a 0.00563 scale 142-inch diameter solid rocket booster (SA10F)

NASA Technical Reports Server (NTRS)

Johnson, J. D.; Braddock, W. F.

1974-01-01

A test of a 0.563 percent scale space shuttle Solid Rocket Booster (SRB) model, MSFC Model 449, was conducted in a trisonic wind tunnel. Test Mach numbers were 0.4, 0.6, 0.9, 1.2, 1.96, 3.48, 4.0, 4.45, and 4.96. Test angles-of-attack ranged from minus 10 degrees to 190 degrees. Test Reynolds numbers ranged from 3.0 million per foot to 8.6 million per foot. Test roll angles were 0, 11.25, 22.5, 45, and 90 degrees. In addition to the static stability evaluation of the primary SRB configuration, five parametric investigations were made: (1) effect of Reynolds number, (2) effect of engine shroud flare angle, (3) effect of engine shroud length, (4) effect of engine shroud strakes, and (5) effect of engine shroud strakes and trust vector control bottles.

The safety of the H1N1 influenza A vaccine in egg allergic individuals.

PubMed

Greenhawt, Matthew J; Chernin, Anna S; Howe, Laura; Li, James T; Sanders, Georgiana

2010-11-01

The safety of H1N1 vaccine is unknown in egg allergic (EA) recipients. To establish the safety of administering H1N1 vaccine and to evaluate the predictability of H1N1 skin testing in EA patients. In a controlled, prospective trial, H1N1 skin testing and vaccination was compared between EA patients (n = 105) and non-EA controls (n = 19). Those with negative H1N1 skin test results received a full H1N1 dose; those with a positive skin test result received a graded challenge (10%, 90%). Booster vaccine, if required, was given as a single dose from a different lot without prior testing. Prick and intradermal test results were positive in 3 (2.4%) of 124 and 41 (33.1%) of 124 study participants, respectively. Forty-one individuals received a 2-step graded vaccine challenge, including 13 of 25 with a history of egg anaphylaxis. No significant allergic reactions resulted from either method of vaccination or from subsequent booster doses. All study participants received the H1N1 vaccine without significant allergic reactions. Skin testing is unnecessary and does not predict vaccine tolerance. All study participants who received a graded challenge tolerated a single dose booster from a different, untested lot, including 7 individuals with a history of egg-induced anaphylaxis. We recommend administration of H1N1 vaccine to EA children without prior skin testing or graded challenge dosing. Copyright © 2010 American College of Allergy, Asthma & Immunology. Published by Elsevier Inc. All rights reserved.

Misuse of Booster Cushions – An Observation Study of Children’s Performance during Buckling Up

PubMed Central

Osvalder, Anna-Lisa; Bohman, Katarina

2008-01-01

Booster cushions are effective tools to protect children from injuries in car crashes, but there remains a large amount of misuse. The aim of this study was to assess potential misuse of booster cushions in an observational laboratory study, and to identify whether booster cushion design, age or clothing had any effect. 130 Swedish children from the ages of 4–12 years participated. Each child buckled up on an integrated and on an aftermarket booster cushion in the rear seat. The older children also buckled up with seat belt only. Interviews, observations and body measurements were performed. Time to buckle up and amount of belt slack were registered. Photographs were taken to document misuse. Results showed that 77% failed to perform correct belt routing on the aftermarket cushion, independent of age, although they were familiar with this system. The misuse rate for the integrated cushion was only 4%. No misuse was found for seat belt only. Few children tightened the belt. The belt slack increased when wearing winter jackets. This indicates the importance of adding pretensioners to the rear seat. Sled tests with HIII&TNO 6y dummies were also performed for the most frequent misuse situations found. The main conclusion is that an integrated booster cushion has many advantages compared to an aftermarket cushion regarding both safety and comfort. It is easy and quick to handle, has few possibilities for misuse, has an intuitive design, the buckling up sequence is equal to buckling up with an ordinary seat belt, and younger children can buckle up correctly. PMID:19026222

Comparison of anamnestic responses to rabies vaccination in dogs and cats with current and out-of-date vaccination status.

PubMed

Moore, Michael C; Davis, Rolan D; Kang, Qing; Vahl, Christopher I; Wallace, Ryan M; Hanlon, Cathleen A; Mosier, Derek A

2015-01-15

To compare anamnestic antibody responses of dogs and cats with current versus out-of-date vaccination status. Cross-sectional study. 74 dogs and 33 cats. Serum samples were obtained from dogs and cats that had been exposed to rabies and brought to a veterinarian for proactive serologic monitoring or that had been brought to a veterinarian for booster rabies vaccination. Blood samples were collected on the day of initial evaluation (day 0) and then again 5 to 15 days later. On day 0, a rabies vaccine was administered according to label recommendations. Paired serum samples were analyzed for antirabies antibodies by means of a rapid fluorescent focus inhibition test. All animals had an antirabies antibody titer ≥ 0.5 IU/mL 5 to 15 days after booster vaccination. Dogs with an out-of-date vaccination status had a higher median increase in titer, higher median fold increase in titer, and higher median titer following booster vaccination, compared with dogs with current vaccination status. Most (26/33) cats, regardless of rabies vaccination status, had a titer ≥ 12 IU/mL 5 to 15 days after booster vaccination. Results indicated that dogs with out-of-date vaccination status were not inferior in their antibody response following booster rabies vaccination, compared with dogs with current vaccination status. Findings supported immediate booster vaccination followed by observation for 45 days of dogs and cats with an out-of-date vaccination status that are exposed to rabies, as is the current practice for dogs and cats with current vaccination status.

KSC00padig014

NASA Image and Video Library

2000-04-22

KENNEDY SPACE CENTER, FLA. -- From the deck of Liberty Star, one of two KSC solid rocket booster recovery ships, a crane lowers a one-man submarine into the ocean near Cape Canaveral, Fla. Called DeepWorker 2000, the sub is being tested on its ability to duplicate the sometimes hazardous job United Space Alliance (USA) divers perform to recover the expended boosters in the ocean after a launch. The boosters splash down in an impact area about 140 miles east of Jacksonville and after recovery are towed back to KSC for refurbishment by the specially rigged recovery ships. DeepWorker 2000 will be used in a demonstration during retrieval operations after the upcoming STS-101 launch. The submarine pilot will demonstrate capabilities to cut tangled parachute riser lines using a manipulator arm and attach a Diver Operator Plug to extract water and provide flotation for the booster. DeepWorker 2000 was built by Nuytco Research Ltd., North Vancouver, British Columbia. It is 8.25 feet long, 5.75 feet high, and weighs 3,800 pounds. USA is a prime contractor to NASA for the Space Shuttle program

KSC00padig013

NASA Image and Video Library

2000-04-22

KENNEDY SPACE CENTER, FLA. -- At left, a manipulator arm on a one-man submarine demonstrates its ability to cut tangled parachute riser lines and place a Diver Operator Plug (top right) inside a mock solid rocket booster nozzle (center). Known as DeepWorker 2000, the sub is being tested on its ability to duplicate the sometimes hazardous job United Space Alliance (USA) divers perform to recover the expended boosters in the ocean after a launch. The boosters splash down in an impact area about 140 miles east of Jacksonville and after recovery are towed back to KSC for refurbishment by the specially rigged recovery ships. DeepWorker 2000 will be used in a demonstration during retrieval operations after the upcoming STS-101 launch. The submarine pilot will demonstrate capabilities to cut tangled parachute riser lines using a manipulator arm and attach the DOP to extract water and provide flotation for the booster. DeepWorker 2000 was built by Nuytco Research Ltd., North Vancouver, British Columbia. It is 8.25 feet long, 5.75 feet high, and weighs 3,800 pounds. USA is a prime contractor to NASA for the Space Shuttle program

KSC-00padig014

NASA Image and Video Library

2000-04-22

KENNEDY SPACE CENTER, FLA. -- From the deck of Liberty Star, one of two KSC solid rocket booster recovery ships, a crane lowers a one-man submarine into the ocean near Cape Canaveral, Fla. Called DeepWorker 2000, the sub is being tested on its ability to duplicate the sometimes hazardous job United Space Alliance (USA) divers perform to recover the expended boosters in the ocean after a launch. The boosters splash down in an impact area about 140 miles east of Jacksonville and after recovery are towed back to KSC for refurbishment by the specially rigged recovery ships. DeepWorker 2000 will be used in a demonstration during retrieval operations after the upcoming STS-101 launch. The submarine pilot will demonstrate capabilities to cut tangled parachute riser lines using a manipulator arm and attach a Diver Operator Plug to extract water and provide flotation for the booster. DeepWorker 2000 was built by Nuytco Research Ltd., North Vancouver, British Columbia. It is 8.25 feet long, 5.75 feet high, and weighs 3,800 pounds. USA is a prime contractor to NASA for the Space Shuttle program

KSC-00padig013

NASA Image and Video Library

2000-04-22

KENNEDY SPACE CENTER, FLA. -- At left, a manipulator arm on a one-man submarine demonstrates its ability to cut tangled parachute riser lines and place a Diver Operator Plug (top right) inside a mock solid rocket booster nozzle (center). Known as DeepWorker 2000, the sub is being tested on its ability to duplicate the sometimes hazardous job United Space Alliance (USA) divers perform to recover the expended boosters in the ocean after a launch. The boosters splash down in an impact area about 140 miles east of Jacksonville and after recovery are towed back to KSC for refurbishment by the specially rigged recovery ships. DeepWorker 2000 will be used in a demonstration during retrieval operations after the upcoming STS-101 launch. The submarine pilot will demonstrate capabilities to cut tangled parachute riser lines using a manipulator arm and attach the DOP to extract water and provide flotation for the booster. DeepWorker 2000 was built by Nuytco Research Ltd., North Vancouver, British Columbia. It is 8.25 feet long, 5.75 feet high, and weighs 3,800 pounds. USA is a prime contractor to NASA for the Space Shuttle program

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.

A modified Pegasus rocket drops away after release from NASA's B-52B before accelerating the X-43A over a Pacific Ocean test range on Nov. 16, 2004

NASA Image and Video Library

2004-11-16

The third X-43A hypersonic research aircraft and its modified Pegasus booster rocket drop away from NASA's B-52B launch aircraft over the Pacific Ocean on November 16, 2004. The mission originated from the NASA Dryden Flight Research Center at Edwards Air Force Base, California. Moments later the Pegasus booster ignited to accelerate the X-43A to its intended speed of Mach 10.

KSC-00padig015

NASA Image and Video Library

2000-04-22

KENNEDY SPACE CENTER, FLA. -- The one-man submarine known as DeepWorker 2000 is tested in Atlantic waters near Cape Canaveral, Fla. Nearby are divers; inside the sub is the pilot, Anker Rasmussen. The sub is being tested on its ability to duplicate the sometimes hazardous job United Space Alliance (USA) divers perform to recover the expended boosters in the ocean after a launch. The boosters splash down in an impact area about 140 miles east of Jacksonville and after recovery are towed back to KSC for refurbishment by the specially rigged recovery ships. DeepWorker 2000 will be used in a demonstration during retrieval operations after the upcoming STS-101 launch. The submarine pilot will demonstrate capabilities to cut tangled parachute riser lines using a manipulator arm and attach a Diver Operator Plug to extract water and provide flotation for the booster. DeepWorker 2000 was built by Nuytco Research Ltd., North Vancouver, British Columbia. It is 8.25 feet long, 5.75 feet high, and weighs 3,800 pounds. USA is a prime contractor to NASA for the Space Shuttle program

KSC00padig015

NASA Image and Video Library

2000-04-22

KENNEDY SPACE CENTER, FLA. -- The one-man submarine known as DeepWorker 2000 is tested in Atlantic waters near Cape Canaveral, Fla. Nearby are divers; inside the sub is the pilot, Anker Rasmussen. The sub is being tested on its ability to duplicate the sometimes hazardous job United Space Alliance (USA) divers perform to recover the expended boosters in the ocean after a launch. The boosters splash down in an impact area about 140 miles east of Jacksonville and after recovery are towed back to KSC for refurbishment by the specially rigged recovery ships. DeepWorker 2000 will be used in a demonstration during retrieval operations after the upcoming STS-101 launch. The submarine pilot will demonstrate capabilities to cut tangled parachute riser lines using a manipulator arm and attach a Diver Operator Plug to extract water and provide flotation for the booster. DeepWorker 2000 was built by Nuytco Research Ltd., North Vancouver, British Columbia. It is 8.25 feet long, 5.75 feet high, and weighs 3,800 pounds. USA is a prime contractor to NASA for the Space Shuttle program

NASA's Space Launch System: Developing the World's Most Powerful Solid Booster

NASA Technical Reports Server (NTRS)

Priskos, Alex

2016-01-01

NASA's Journey to Mars has begun. Indicative of that challenge, this will be a multi-decadal effort requiring the development of technology, operational capability, and experience. The first steps are under way with more than 15 years of continuous human operations aboard the International Space Station (ISS) and development of commercial cargo and crew transportation capabilities. NASA is making progress on the transportation required for deep space exploration - the Orion crew spacecraft and the Space Launch System (SLS) heavy-lift rocket that will launch Orion and large components such as in-space stages, habitat modules, landers, and other hardware necessary for deep-space operations. SLS is a key enabling capability and is designed to evolve with mission requirements. The initial configuration of SLS - Block 1 - will be capable of launching more than 70 metric tons (t) of payload into low Earth orbit, greater mass than any other launch vehicle in existence. By enhancing the propulsion elements and larger payload fairings, future SLS variants will launch 130 t into space, an unprecedented capability that simplifies hardware design and in-space operations, reduces travel times, and enhances the odds of mission success. SLS will be powered by four liquid fuel RS-25 engines and two solid propellant five-segment boosters, both based on space shuttle technologies. This paper will focus on development of the booster, which will provide more than 75 percent of total vehicle thrust at liftoff. Each booster is more than 17 stories tall, 3.6 meters (m) in diameter and weighs 725,000 kilograms (kg). While the SLS booster appears similar to the shuttle booster, it incorporates several changes. The additional propellant segment provides additional booster performance. Parachutes and other hardware associated with recovery operations have been deleted and the booster designated as expendable for affordability reasons. The new motor incorporates new avionics, new propellant grain, asbestos-free case insulation, a redesigned nozzle, streamlined manufacturing processes, and new inspection techniques. New materials and processes provide improved performance, safety, and affordability but also have led to challenges for the government/industry development team. The team completed its first full-size qualification motor test firing in early 2015. The second is scheduled for mid-2016. This paper will discuss booster accomplishments to date, as well as challenges and milestones ahead.

Effects of cruise engine location and power on interference

NASA Technical Reports Server (NTRS)

Bradley, D.

1972-01-01

Data are presented, in plotted form, of tests for determining the interference effects of space shuttle booster cruise engine location for power-on and power-off conditions. The tests were conducted in a 7 x 10 foot transonic wind tunnel; the model was a 0.015-scale space shuttle booster specially equipped for propulsion effects testing. Data were obtained over a Mach number range of 0.4 to 1.13 at angles of attack from -4 deg to 20 deg at zero degrees sideslip and at angles of sideslip from -6 deg to +6 deg at constant angles of attack of 0 deg, 6 deg, 15 deg, and in some cases 10 deg. Additional parameters investigated were: elevon deflection, canard deflection, aileron deflection, rudder deflection, canard position, and mass flow rate.

Status of the Perpendicular Biased 2nd Harmonic Cavity for the Fermilab Booster

DOE PAGES

Tan, C. Y.; Dey, J. E.; Duel, K. L.; ...

2017-05-01

This is a status report on the 2nd harmonic cavity for the Fermilab Booster as part of the Proton Improvement Plan (PIP) for increasing beam transmission efficiency, and thus reducing losses. A set of tuner rings has been procured and is undergoing quality control tests. The Y567 tube for driving the cavity has been successfully tested at both injection and extraction frequencies. A cooling scheme for the tuner and cavity has been developed after a thorough thermal analysis of the system. RF windows have been procured and substantial progress has been made on the mechanical designs of the cavity andmore » the bias solenoid. Finally, the goal is to have a prototype cavity ready for testing by the end of 2017.« less

Status of the Perpendicular Biased 2nd Harmonic Cavity for the Fermilab Booster

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

Tan, C. Y.; Dey, J. E.; Duel, K. L.

This is a status report on the 2nd harmonic cavity for the Fermilab Booster as part of the Proton Improvement Plan (PIP) for increasing beam transmission efficiency, and thus reducing losses. A set of tuner rings has been procured and is undergoing quality control tests. The Y567 tube for driving the cavity has been successfully tested at both injection and extraction frequencies. A cooling scheme for the tuner and cavity has been developed after a thorough thermal analysis of the system. RF windows have been procured and substantial progress has been made on the mechanical designs of the cavity andmore » the bias solenoid. Finally, the goal is to have a prototype cavity ready for testing by the end of 2017.« less

Heat transfer rate distributions on McDonnell-Douglas booster determined by phase change technique for nominal Mach number of 8

NASA Technical Reports Server (NTRS)

Matthews, R. K.; Martindale, W. R.; Warmbrod, J. D.

1972-01-01

The results of a wind tunnel test program to determine aerodynamic heat transfer distributions on the McDonnell Douglas Booster configuration are presented. Heat-transfer rates were determined by the phase-change paint technique on 0.009-scale Stycast models using Tempilaq as the surface temperature indicator. The nominal test conditions were; Mach 8, length Reynolds numbers 5 million and 7.3 million, and angles of attack of 40, 50, and 60 deg. At the higher Reynolds number, data were obtained with and without boundary layer trips. Model details, test conditions, and reduced heat-transfer data are presented. Data reduction of the phase-change paint photographs was performed by utilizing a new technique which is described.

Low speed aerodynamic characteristics of the GD/C B-18E3 booster

NASA Technical Reports Server (NTRS)

Carter, W. V.; Gallaher, W. H.

1972-01-01

A 0.02 scale model of the B-18E3 space shuttle booster was tested in a low speed wind tunnel to evaluate the low speed aerodynamic charactersitics. The basic configuration, including build-up, was tested at a Mach number of 0.201 and Reynolds number per foot of 1.39 million. The normal angle-of-attack range was -4 to +24 degrees in 2 degree increments, at sideslip angles of 0 and 5 degrees. Some lateral data were obtained at the sideslip angle range of -6 to 10 degrees at angles-of attack of 0, 10, and 15 degrees. Data were obtained for canard, split elevon, and split rudder deflections.

Space shuttle: Determination of the aerodynamic interference between the space shuttle orbiter, external tank, and solid rocket booster on a 0.004 scale ascent configuration

NASA Technical Reports Server (NTRS)

Ramsey, P. E.; Buchholz, R.; Allen, E. C. JR.; Dehart, J.

1973-01-01

Wind tunnel tests were conducted to determine the aerodynamic interference between the space shuttle orbiter, external tank, and solid rocket booster on a 0.004 scale ascent configuration. Six component aerodynamic force and moment data were recorded over an angle of attack range from minus 10 to plus 10 degrees at zero degree sideslip. A sideslip range of minus 10 to plus 10 degrees at zero degree angle of attack was also tested. The Mach number range was varied from 0.6 to 4.96 with Reynolds number varying between 4.9 and 6.8 times one million per foot.

Space shuttle: Verification of transition reentry corridor at high angles of attack and determination of transition aerodynamic characteristics and subsonic aerodynamic characteristics at low angles of attack for the Boeing H-32 booster

NASA Technical Reports Server (NTRS)

Houser, J.; Johnson, L. J.; Oiye, M.; Runciman, W.

1972-01-01

Experimental aerodynamic investigations were made in a transonic wind tunnel on a 1/150-scale model of the Boeing H-32 space shuttle booster configuration. The purpose of the test was: (1) to verify the transonic reentry corridor at high angles of attack; (2) to determine the transonic aerodynamic characteristics; and (3) to determine the subsonic aerodynamic characteristics at low angles of attack. Test variables included configuration buildup, horizontal stabilizer settings of 0 and -20 deg, elevator deflections of 0 and -30 deg, and wing spoiler settings of 60 deg.

Workers in the VAB test SRB cables on STS-98 solid rocket boosters

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. -- United Space Alliance SRB technician Richard Bruns attaches a cable end cover to a cable pulled from the solid rocket booster on Space Shuttle Atlantis. The Shuttle was rolled back from Launch Pad 39A in order to conduct tests on the SRB cables. A prior extensive evaluation of NASA'''s SRB cable inventory on the shelf revealed conductor damage in four (of about 200) cables. Shuttle managers decided to prove the integrity of the system tunnel cables already on Atlantis before launching. Workers are conducting inspections, making continuity checks and conducting X-ray analysis on the cables. The launch has been rescheduled no earlier than Feb. 6.

Aerodynamic characteristics of the Grumman H-33 orbiter mated to a three segment solid propellant booster

NASA Technical Reports Server (NTRS)

Sims, F.; Olive, R.

1971-01-01

Experimental aerodynamic investigations were conducted on a .003366-scale model of the Grumman space shuttle configuration mounted to a three (3) segmented solid propellant booster. These tests were conducted in the MSFC 14-inch trisonic wind tunnel over a Mach number range of 0.6 to 4.96. The purpose of the test was to determine the aerodynamic characteristics of this configuration. Aerodynamic data was taken over a nominal angle of attack and angle of sideslip of -10 degrees to 10 degrees at zero degrees beta and alpha respectively. In addition, data was obtained for the H-33 orbiter alone to supplement data from TWT 502 and TWT 503.

Design of Test Loops for Forced Convection Heat Transfer Studies at Supercritical State

NASA Astrophysics Data System (ADS)

Balouch, Masih N.

Worldwide research is being conducted to improve the efficiency of nuclear power plants by using supercritical water (SCW) as the working fluid. One such SCW reactor considered for future development is the CANDU-Supercritical Water Reactor (CANDU-SCWR). For safe and accurate design of the CANDU-SCWR, a detailed knowledge of forced-convection heat transfer in SCW is required. For this purpose, two supercritical fluid loops, i.e. a SCW loop and an R-134a loop are developed at Carleton University. The SCW loop is designed to operate at pressures as high as 28 MPa, temperatures up to 600 °C and mass fluxes of up to 3000 kg/m2s. The R-134a loop is designed to operate at pressures as high as 6 MPa, temperatures up to 140 °C and mass fluxes in the range of 500-6000 kg/m2s. The test loops designs allow for up to 300 kW of heating power to be imparted to the fluid. Both test loops are of the closed-loop design, where flow circulation is achieved by a centrifugal pump in the SCW loop and three parallel-connected gear pumps in the R-134a loop, respectively. The test loops are pressurized using a high-pressure nitrogen cylinder and accumulator assembly, which allows independent control of the pressure, while simultaneously dampening pump induced pressure fluctuations. Heat exchangers located upstream of the pumps control the fluid temperature in the test loops. Strategically located measuring instrumentation provides information on the flow rate, pressure and temperature in the test loops. The test loops have been designed to accommodate a variety of test-section geometries, ranging from a straight circular tube to a seven-rod bundle, achieving heat fluxes up to 2.5 MW/m2 depending on the test-section geometry. The design of both test loops allows for easy reconfiguration of the test-section orientation relative to the gravitational direction. All the test sections are of the directly-heated design, where electric current passing through the pressure retaining walls of the test sections provides the Joule heating required to heat up the fluid to supercritical conditions. A high-temperature dielectric gasket isolates the current carrying parts of the test section from the rest of the assembly. Temperature and pressure drop data are collected at the inlet and outlet, and along the heated length of the test section. The test loops and test sections are designed according to American Society of Mechanical Engineers (ASME) Pressure Piping B31.1, and Boiler and Pressure Vessel Code, Section VIII-Division 1 rules. The final test loops and test sections assemblies are certified by Technical Standards and Safety Authority (TSSA). Every attempt is made to use off-the-shelf components where possible in order to streamline the design process and reduce costs. Following a rigorous selection process, stainless steel Types 316 and 316H are selected as the construction materials for the test loops, and Inconel 625 is selected as the construction material for the test sections. This thesis describes the design of the SCW and R-134a loops along with the three test-section geometries (i.e., tubular, annular and bundle designs).

Reentry aerodynamic characteristics of a space shuttle solid rocket booster (MSFC model 454) at high angles of attack and high Mach number in the NASA/Langley four-foot unitary plan wind tunnel (SA25F)

NASA Technical Reports Server (NTRS)

Johnson, J. D.; Braddock, W. F.

1975-01-01

A force test of a 2.112 percent scale Space Shuttle Solid Rocket Booster (SRB), MSFC Model 454, was conducted in test section no. 2 of the Unitary Plan Wind Tunnel. Sixteen (16) runs (pitch polars) were performed over an angle of attack range from 144 through 179 degrees. Test Mach numbers were 2.30, 2.70, 2.96, 3.48, 4.00 and 4.63. The first three Mach numbers had a test Reynolds number of 1.5 million per foot. The remaining three were at 2.0 million per foot. The model was tested in the following configurations: (1) SRB without external protuberances, and (2) SRB with an electrical tunnel and a SRB/ET thrust attachment structure. Schlieren photographs were taken during the testing of the first configuration. The second configuration was tested at roll angles of 45, 90, and 135 degrees.

Design study of the CEPC booster

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

Zhang, Chuang

2014-12-10

Design study of the CEPC booster is reported. The booster provides 120 GeV beams for the collider with topup injection frequency of 0.1 Hz. To save cost, energy of the linac injector for the booster is chosen as 6GeV, corresponding to the magnetic field of 30 Gs. In this paper, lattice of the booster is described; the low injection energy issues are studied; beam transfer from linac to booster and from booster to collider are discussed.

Space Shuttle Project

NASA Image and Video Library

1978-04-21

The Shuttle Orbiter Enterprise is lowered into the Dynamic Test Stand for Mated Vertical Ground Vibration tests (MVGVT) at the Marshall Space Flight Center. The tests marked the first time ever that the entire shuttle complement (including Orbiter, external tank, and solid rocket boosters) were mated vertically.

Space Shuttle Project

NASA Image and Video Library

1978-10-04

The Shuttle Orbiter Enterprise is being installed into liftoff configuration at Marshall Space Flight Center's Dynamic Test Stand for Mated Vertical Ground Vibration tests (MVGVT). The tests marked the first time ever that the entire shuttle complement (including Orbiter, external tank, and solid rocket boosters) were mated vertically.

CLV First Stage Design, Development, Test and Evaluation

NASA Technical Reports Server (NTRS)

Burt, Richard K.; Brasfield, F.

2006-01-01

The Crew Launch Vehicle (CLV) is an integral part of NASA's Exploration architecture that will provide crew and cargo access to the International Space Station as well as low earth orbit support for lunar missions. Currently in the system definition phase, the CLV is planned to replace the Space Shuttle for crew transport in the post 2010 time frame. It is comprised of a solid rocket booster first stage derived from the current Space Shuttle SRB, a LOX/hydrogen liquid fueled second stage utilizing a derivative of the Space Shuttle Main Engine (SSME) for propulsion, and a Crew Exploration Vehicle (GEV) composed of Command and Service Modules. This paper deals with current DDT&E planning for the CLV first stage solid rocket booster. Described are the current overall point-of-departure design and booster subsystems, systems engineering approach, and milestone schedule requirements.

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

NASA Technical Reports Server (NTRS)

Campbell, J. H., II

1975-01-01

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

Atmospheric reentry flight test of winged space vehicle

NASA Astrophysics Data System (ADS)

Inatani, Yoshifumi; Akiba, Ryojiro; Hinada, Motoki; Nagatomo, Makoto

A summary of the atmospheric reentry flight experiment of winged space vehicle is presented. The test was conducted and carried out by the Institute of Space and Astronautical Science (ISAS) in Feb. 1992 in Kagoshima Space Center. It is the first Japanese atmospheric reentry flight of the controlled lifting vehicle. A prime objective of the flight is to demonstrate a high speed atmospheric entry flight capability and high-angle-of-attack flight capability in terms of aerodynamics, flight dynamics and flight control of these kind of vehicles. The launch of the winged vehicle was made by balloon and solid propellant rocket booster which was also the first trial in Japan. The vehicle accomplishes the lfight from space-equivalent condition to the atmospheric flight condition where reaction control system (RCS) attitude stabilization and aerodynamic control was used, respectively. In the flight, the vehicle's attitude was measured by both an inertial measurement unit (IMU) and an air data sensor (ADS) which were employed into an auto-pilot flight control loop. After completion of the entry transient flight, the vehicle experienced unexpected instability during the atmospheric decelerating flight; however, it recovered the attitude orientation and completed the transonic flight after that. The latest analysis shows that it is due to the ADS measurement error and the flight control gain scheduling; what happened was all understood. Some details of the test and the brief summary of the current status of the post flight analysis are presented.

Evaluation of SRB phenolic TPS material made by an alternate vendor

NASA Technical Reports Server (NTRS)

Karu, Z. S.

1982-01-01

Tests conducted to evaluate the adequacy of solid rocket booster (SRB) phenolic thermal protection system (TPS) material supplied by an alternate vendor chosen by United Space Boosters, Inc. (USBI), to replace the current phenolic TPS sections used thus far on the first four Shuttle flights. The phenolic TPS is applied mainly to the attach and kick rings of the solid rocket booster (SRB). Full-scale sectional models of both the attach and kick ring structure were made up with 0.0265 in. thick stainless steel thin skin covers with thermocouples on them to determine the heating rates. Such models were made up for both the forward and rear faces of the kick ring which has a different configuration on each side. The thin skins were replaced with the alternate phenolic TPS sections cut from flight hardware configuration phenolic parts as supplied by the new vendor. Two tests were performed for each configuration of the attach and kick rings and the samples were exposed to the flow for a duration that gave a heat load equivalent to that obtained in the series of runs made for the current line of phenolic TPS. The samples performed very well with no loss of any phenolic layers. The post-test samples looked better than those used to verify the current phenolic TPS.

Space Launch System Accelerated Booster Development Cycle

NASA Technical Reports Server (NTRS)

Arockiam, Nicole; Whittecar, William; Edwards, Stephen

2012-01-01

With the retirement of the Space Shuttle, NASA is seeking to reinvigorate the national space program and recapture the public s interest in human space exploration by developing missions to the Moon, near-earth asteroids, Lagrange points, Mars, and beyond. The would-be successor to the Space Shuttle, NASA s Constellation Program, planned to take humans back to the Moon by 2020, but due to budgetary constraints was cancelled in 2010 in search of a more "affordable, sustainable, and realistic" concept2. Following a number of studies, the much anticipated Space Launch System (SLS) was unveiled in September of 2011. The SLS core architecture consists of a cryogenic first stage with five Space Shuttle Main Engines (SSMEs), and a cryogenic second stage using a new J-2X engine3. The baseline configuration employs two 5-segment solid rocket boosters to achieve a 70 metric ton payload capability, but a new, more capable booster system will be required to attain the goal of 130 metric tons to orbit. To this end, NASA s Marshall Space Flight Center recently released a NASA Research Announcement (NRA) entitled "Space Launch System (SLS) Advanced Booster Engineering Demonstration and/or Risk Reduction." The increased emphasis on affordability is evident in the language used in the NRA, which is focused on risk reduction "leading to an affordable Advanced Booster that meets the evolved capabilities of SLS" and "enabling competition" to "enhance SLS affordability. The purpose of the work presented in this paper is to perform an independent assessment of the elements that make up an affordable and realistic path forward for the SLS booster system, utilizing advanced design methods and technology evaluation techniques. The goal is to identify elements that will enable a more sustainable development program by exploring the trade space of heavy lift booster systems and focusing on affordability, operability, and reliability at the system and subsystem levels5. For this study, affordability is defined as lifecycle cost, which includes design, development, test, and engineering (DDT&E), production and operational costs (P&O). For this study, the system objectives include reducing DDT&E schedule by a factor of three, showing 99.9% reliability, flying up to four times per year, serving both crew and cargo missions, and evolving to a lift capability of 130 metric tons.3 After identifying gaps in the current system s capabilities, this study seeks to identify non-traditional and innovative technologies and processes that may improve performance in these areas and assess their impacts on booster system development. The DDT&E phase may be improved by incorporating incremental development testing and integrated demonstrations to mitigate risk. To further reduce DDT&E, this study will also consider how aspects of the booster system may have commonality with other users, such as the Department of Defense, commercial applications, or international partners; by sharing some of the risk and investment, the overall development cost may be reduced. Consideration is not limited to solid and liquid rocket boosters. A set of functional performance characteristics, such as engine thrust, specific impulse (Isp), mixture ratio, and throttle range are identified and their impacts on the system are evaluated. This study also identifies how such characteristics affect overall life cycle cost, including DDT&E and fixed and variable P&O.

Update on Risk Reduction Activities for a Liquid Advanced Booster for NASA's Space Launch System

NASA Technical Reports Server (NTRS)

Crocker, Andy; Greene, William D.

2017-01-01

Goals of NASA's Advanced Booster Engineering Demonstration and/or Risk Reduction (ABEDRR) are to: (1) Reduce risks leading to an affordable Advanced Booster that meets the evolved capabilities of SLS. (2) Enable competition by mitigating targeted Advanced Booster risks to enhance SLS affordability. SLS Block 1 vehicle is being designed to carry 70 mT to LEO: (1) Uses two five-segment solid rocket boosters (SRBs) similar to the boosters that helped power the space shuttle to orbit. Evolved 130 mT payload class rocket requires an advanced booster with more thrust than any existing U.S. liquid-or solid-fueled boosters

Proving the Space Transportation System: the Orbital Flight Test Program

NASA Technical Reports Server (NTRS)

Reichhardt, T.

1982-01-01

The main propulsion system, solid rocket boosters, external tank, orbital maneuvering system, spacecraft orbital operations (thermal tests, attitude control and remote manipulator), and return to Earth are outlined for the first four STS missions.

Workers in the VAB test SRB cables on STS-98 solid rocket boosters

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. -- Working near the top of a solid rocket booster, NASA and United Space Alliance SRB technicians hook up SRB cables to a CIRRUS computer for testing. From left are Jim Glass, with USA, performing a Flex test on the cable; Steve Swichkow, with NASA, and Jim Silviano, with USA, check the results on a computer. The SRB is part of Space Shuttle Atlantis, rolled back from Launch Pad 39A in order to conduct tests on the cables. A prior extensive evaluation of NASA'''s SRB cable inventory on the shelf revealed conductor damage in four (of about 200) cables. Shuttle managers decided to prove the integrity of the system tunnel cables already on Atlantis before launching. Workers are conducting inspections, making continuity checks and conducting X-ray analysis on the cables. The launch has been rescheduled no earlier than Feb. 6.

KENNEDY SPACE CENTER, FLA. - The red NASA engine hauls its cargo toward Titusville, Fla. The containers enclose segments of a solid rocket booster being returned to Utah for testing. The segments were part of the STS-114 stack. It is the first time actual flight segments that had been stacked for flight in the VAB are being returned for testing. They will undergo firing, which will enable inspectors to check the viability of the solid and verify the life expectancy for stacked segments.

NASA Image and Video Library

2004-01-30

KENNEDY SPACE CENTER, FLA. - The red NASA engine hauls its cargo toward Titusville, Fla. The containers enclose segments of a solid rocket booster being returned to Utah for testing. The segments were part of the STS-114 stack. It is the first time actual flight segments that had been stacked for flight in the VAB are being returned for testing. They will undergo firing, which will enable inspectors to check the viability of the solid and verify the life expectancy for stacked segments.

Kinematics of child volunteers and child anthropomorphic test devices during emergency braking events in real car environment.

PubMed

Stockman, Isabelle; Bohman, Katarina; Jakobsson, Lotta; Brolin, Karin

2013-01-01

The objective of this study was to present, compare, and discuss the kinematic response of children and child anthropomorphic test devices (ATDs) during emergency braking events in different restraint configurations in a passenger vehicle. A driving study was conducted on a closed-circuit test track comprising 16 children aged 4 to 12 years old and the Q3, Hybrid III (HIII) 3-year-old, 6-year-old, and 10-year-old ATDs restrained on the right rear seat of a modern passenger vehicle. The children were exposed to one braking event in each of the 2 restraint systems and the ATDs were exposed to 2 braking events in each restraint system. All events had a deceleration of 1.0 g. Short children (stature 107-123 cm) and the Q3, HIII 3-year-old, and 6-year-old were restrained on booster cushions as well as high-back booster seats. Tall children (stature 135-150 cm) and HIII 10-year-old were restrained on booster cushions or restrained by 3-point belts directly on the car seat. Vehicle data were collected and synchronized with video data. Forward trajectories for the forehead and external auditory canal (ear) were determined as well as head rotation and shoulder belt force. A total of 40 trials were analyzed. Child volunteers had greater maximum forward displacement of the head and greater head rotation compared to the ATDs. The average maximum displacement for children ranged from 165 to 210 mm and 155 to 195 mm for the forehead and ear target, respectively. Corresponding values for the ATDs were 55 to 165 mm and 50 to 160 mm. The change in head angle was greater for short children than for tall children. Shoulder belt force was within the same range for short children when restrained on booster cushions or high-back booster seats. For tall children, the shoulder belt force was greater when restrained on booster cushions compared to being restrained by seat belts directly on the car seat. The forward displacement was within the same range for all children regardless of stature and restraint system. However, the maximum forward position depended on the initial seated posture and shoulder belt position on the shoulder. Differences could also be seen in the curvature of the neck and spine. Short children exhibited a greater flexion motion of the head, whereas a more upright posture at maximum forward position was exhibited by the tall children. The ATDs displayed less forward displacement compared to the children.

47 CFR 27.9 - Operation of certificated signal boosters.

Code of Federal Regulations, 2013 CFR

2013-10-01

... 47 Telecommunication 2 2013-10-01 2013-10-01 false Operation of certificated signal boosters. 27.9... boosters. Individuals and non-individuals may operate certificated Consumer Signal Boosters on frequencies... operate a signal booster. [78 FR 21564, Apr. 11, 2013] ...

47 CFR 27.9 - Operation of certificated signal boosters.

Code of Federal Regulations, 2014 CFR

2014-10-01

... 47 Telecommunication 2 2014-10-01 2014-10-01 false Operation of certificated signal boosters. 27.9... boosters. Individuals and non-individuals may operate certificated Consumer Signal Boosters on frequencies... operate a signal booster. [78 FR 21564, Apr. 11, 2013] ...

Renewable Energy Generation and Storage Models | Grid Modernization | NREL

Science.gov Websites

-the-loop testing Projects Generator, Plant, and Storage Modeling, Simulation, and Validation NREL power plants. Power Hardware-in-the-Loop Testing NREL researchers are developing software-and-hardware -combined simulation testing methods known as power hardware-in-the-loop testing. Power hardware in the loop

[The tuberculin skin test in BCG-vaccinated individualse].

PubMed

Miret Cuadras, P; Pina Gutiérrez, J M

1998-10-01

The aim of this study was to evaluate the tuberculin skin test in individuals vaccinated with bacillus Calmette-Guérin (BCG) using 2 IU of RT-23. One hundred ninety-six individuals aged 22-40 years-old who had been vaccinated with BCG between 1965 and 1974 were enrolled along with 375 non-vaccinated individuals of the same age and with similar level of risk of infection. The positive predictive value of the test was assessed for three levels of response as indicated by areas of thickening in three diameters: 5, 10 and 15 mm. Vaccinated individuals with negative results were given a second skin test 7 days later to detect a booster effect. Positive diameters 5 mm were observed in 66% of the vaccinated individuals and 24% of the non-vaccinated subjects. Positive diameters 10 mm were observed in 51% of the vaccinated individuals and 19% of the non vaccinated ones. Positive diameters 15 mm were observed in 29% of the vaccinated subjects and in 13% of the non vaccinated ones. The differences were significant for all diameters. The positive predictive value of the test was 36.4% for a diameter 5 mm, 37.6% for diameter 10 mm and 44.8% for diameter 15 mm. The booster effect was detected in 25.8% of the vaccinated individuals who had tested negative at first. In vaccinated individuals, no guidelines can be established to guarantee that a positive reaction is due to infection by Mycobacterium tuberculosis infection, although the likelihood of infection (increased positive predictive value) increases with diameter. It is also impossible to fix a time limit. A second skin test is needed to detect a booster effect in all vaccinated individuals whose first test is negative.

Saturn Apollo Program

NASA Image and Video Library

1965-03-01

The S-IC-T stage was hoisted into the S-IC static test stand at the Marshall Space Flight Center. The S-IC-T stage was a static test vehicle not intended for flight. It was ground tested repeatedly over a period of many months to prove the vehicle's propulsion system. The 280,000-pound stage, 138 feet long and 33 feet in diameter, housed the fuel and liquid oxygen tanks that held a total of 4,400,000 pounds of liquid oxygen and kerosene. The two tanks are cornected by a 26-foot-long intertank section. Other parts of the booster included the forward skirt and the thrust structure, on which the engines were to be mounted. Five F-1 engines, each weighing 10 tons, gave the booster a total thrust of 7,500,000 pounds, roughly equivalent to 160 million horsepower.

Saturn Apollo Program

NASA Image and Video Library

1965-03-01

The S-IC-T stage is hoisted into the S-IC static test stand at the Marshall Space Flight Center. The S-IC-T stage is a static test vehicle not intended for flight. It was ground tested repeatedly over a period of many months proving the vehicle's propulsion system. The 280,000-pound stage, 138 feet long and 33 feet in diameter, houses the fuel and liquid oxygen tanks that hold a total of 4,400,000 pounds of liquid oxygen and kerosene. The two tanks are cornected by a 26-foot-long intertank section. Other parts of the booster included the forward skirt and the thrust structure, on which the engines were to be mounted. Five F-1 engines, each weighing 10 tons, gave the booster a total thrust of 7,500,000 pounds, roughly equivalent to 160 million horsepower.

Saturn Apollo Program

NASA Image and Video Library

1965-03-01

The S-IC-T stage was hoisted into the S-IC Static Test Stand at the Marshall Space Flight Center. The S-IC-T stage was a static test vehicle, not intended for flight. It was ground tested repeatedly over a period of many months to prove the vehicle's propulsion system. The 280,000-pound stage, 138 feet long and 33 feet in diameter, housed the fuel and liquid oxygen tanks that held a total of 4,400,000 pounds of liquid oxygen and kerosene. The two tanks were cornected by a 26-foot intertank section. Other parts of the booster included the forward skirt and the thrust structure, on which the engines were to be mounted. Five F-1 engines, each weighing 10 tons, gave the booster a total thrust of 7,500,000 pounds, roughly equivalent to 160 million horsepower.

Stennis Space Center Conducts Water Flow Test On The B-2 Test Stand

NASA Image and Video Library

2018-05-04

Stennis Space Center completed a water flow test of the refurbished B-2 Test Stand on May 4, 2018. This included both the deflector and the aspirator, individually and together. This test stand is being prepared for the testing of the Space Launch System's booster core, which will utilize four RS-25 rocket engines.

Compatibility of booster seats and vehicles in the U.S. market.

PubMed

Bing, Julie A; Agnew, Amanda M; Bolte, John H

2018-05-19

The objective of this study was to analyze booster and rear vehicle seat dimensions to identify the most frequent compatibility problems. Measurements were collected from 40 high-back and backless boosters and 95 left rear and center rear row seating positions in 50 modern vehicles. Dimensions were compared for 3,800 booster/vehicle seat combinations. For validation and estimation of tolerance and correction factors, 72 booster installations were physically completed and compared with measurement-based compatibility predictions. Dimensions were also compared to the International Organization for Standardization (ISO) volumetric envelopes of forward-facing child restraints and boosters. Seat belt buckles in outboard positions accommodated the width of boosters better than center positions (success rates of 85.4 and 34.7%, respectively). Adequate head restraint clearance occurred in 71.9 to 77.2% of combinations, depending on the booster's head support setting. Booster recline angles aligned properly with vehicle seat cushion angles in 71.5% of combinations. In cases of poor angle alignment, booster angles were more obtuse than the vehicle seat angles 97.7% of the time. Head restraint interference exacerbated angle alignment issues. Data indicate success rates above 90% for boosters being fully supported by the length of the seat cushion and for adequate height clearance with the vehicle roofline. Comparison to ISO envelopes indicates that most boosters on the U.S. market are taller and angled more obtusely than ISO target envelopes. This study quantifies some of the common interferences between boosters and vehicles that may complicate booster usage. Data are useful for design and to prioritize specific problem areas.

NASA's B-52B launch aircraft cruises to a test range over the Pacific Ocean carrying the third X-43A vehicle attached to a Pegasus rocket on November 16, 2004

NASA Image and Video Library

2004-11-16

The third X-43A hypersonic research aircraft, attached to a modified Pegasus booster rocket, was taken to launch altitude by NASA's B-52B launch aircraft from the NASA Dryden Flight Research Center at Edwards Air Force Base, California, on November 16, 2004. About an hour later the Pegasus booster was released from the B-52 to accelerate the X-43A to its intended speed of Mach 10.

Steel Primer Chamber Assemblies for Dual Initiated Pyrovalves

NASA Technical Reports Server (NTRS)

Guemsey, Carl S.; Mizukami, Masashi; Zenz, Zac; Pender, Adam A.

2009-01-01

A solution was developed to mitigate the potential risk of ignition failures and burn-through in aluminum primer chamber assemblies on pyrovalves. This was accomplished by changing the assembly material from aluminum to steel, and reconfiguration of flame channels to provide more direct paths from initiators to boosters. With the geometric configuration of the channels changed, energy is more efficiently transferred from the initiators to the boosters. With the alloy change to steel, the initiator flame channels do not erode upon firing, eliminating the possibility of burn-through. Flight qualification tests have been successfully passed.

Mercury Project

NASA Image and Video Library

1960-01-21

The launch of the Little Joe booster for the LJ1B mission on the launch pad from the wallops Flight Facility, Wallops Island, Virginia, on January 21, 1960. This mission achieved the suborbital Mercury capsule test, testing of the escape system, and biomedical tests by using a monkey, named Miss Sam.

47 CFR 74.1203 - Interference.

Code of Federal Regulations, 2014 CFR

2014-10-01

... FM Broadcast Booster Stations § 74.1203 Interference. (a) An authorized FM translator or booster..., TV booster, FM translator or FM booster station; or (3) The direct reception by the public of the off... FM booster stations. Interference will be considered to occur whenever reception of a regularly used...

47 CFR 74.1203 - Interference.

Code of Federal Regulations, 2013 CFR

2013-10-01

... FM Broadcast Booster Stations § 74.1203 Interference. (a) An authorized FM translator or booster..., TV booster, FM translator or FM booster station; or (3) The direct reception by the public of the off... FM booster stations. Interference will be considered to occur whenever reception of a regularly used...

47 CFR 74.1203 - Interference.

Code of Federal Regulations, 2011 CFR

2011-10-01

... FM Broadcast Booster Stations § 74.1203 Interference. (a) An authorized FM translator or booster..., TV booster, FM translator or FM booster station; or (3) The direct reception by the public of the off... FM booster stations. Interference will be considered to occur whenever reception of a regularly used...

47 CFR 74.1203 - Interference.

Code of Federal Regulations, 2012 CFR

2012-10-01

... FM Broadcast Booster Stations § 74.1203 Interference. (a) An authorized FM translator or booster..., TV booster, FM translator or FM booster station; or (3) The direct reception by the public of the off... FM booster stations. Interference will be considered to occur whenever reception of a regularly used...

Space shuttle booster multi-engine base flow analysis

NASA Technical Reports Server (NTRS)

Tang, H. H.; Gardiner, C. R.; Anderson, W. A.; Navickas, J.

1972-01-01

A comprehensive review of currently available techniques pertinent to several prominent aspects of the base thermal problem of the space shuttle booster is given along with a brief review of experimental results. A tractable engineering analysis, capable of predicting the power-on base pressure, base heating, and other base thermal environmental conditions, such as base gas temperature, is presented and used for an analysis of various space shuttle booster configurations. The analysis consists of a rational combination of theoretical treatments of the prominent flow interaction phenomena in the base region. These theories consider jet mixing, plume flow, axisymmetric flow effects, base injection, recirculating flow dynamics, and various modes of heat transfer. Such effects as initial boundary layer expansion at the nozzle lip, reattachment, recompression, choked vent flow, and nonisoenergetic mixing processes are included in the analysis. A unified method was developed and programmed to numerically obtain compatible solutions for the various flow field components in both flight and ground test conditions. Preliminary prediction for a 12-engine space shuttle booster base thermal environment was obtained for a typical trajectory history. Theoretical predictions were also obtained for some clustered-engine experimental conditions. Results indicate good agreement between the data and theoretical predicitons.

Boosting safety behaviour: Descriptive norms encourage child booster seat usage amongst low involvement parents.

PubMed

Jeffrey, Jennifer; Whelan, Jodie; Pirouz, Dante M; Snowdon, Anne W

2016-07-01

Campaigns advocating behavioural changes often employ social norms as a motivating technique, favouring injunctive norms (what is typically approved or disapproved) over descriptive norms (what is typically done). Here, we investigate an upside to including descriptive norms in health and safety appeals. Because descriptive norms are easy to process and understand, they should provide a heuristic to guide behaviour in those individuals who lack the interest or motivation to reflect on the advocated behaviour more deeply. When those descriptive norms are positive - suggesting that what is done is consistent with what ought to be done - including them in campaigns should be particularly beneficial at influencing this low-involvement segment. We test this proposition via research examining booster seat use amongst parents with children of booster seat age, and find that incorporating positive descriptive norms into a related campaign is particularly impactful for parents who report low involvement in the topic of booster seat safety. Descriptive norms are easy to state and easy to understand, and our research suggests that these norms resonate with low involvement individuals. As a result, we recommend incorporating descriptive norms when possible into health and safety campaigns. Copyright © 2016. Published by Elsevier Ltd.

KSC-00padig016

NASA Image and Video Library

2000-04-22

KENNEDY SPACE CENTER, FLA. -- After a successful dive, the one-man submarine known as DeepWorker 2000 is lifted from Atlantic waters near Cape Canaveral, Fla., onto the deck of the Liberty Star, one of two KSC solid rocket booster recovery ships. Inside the sub is the pilot, Anker Rasmussen. The sub is being tested on its ability to duplicate the sometimes hazardous job United Space Alliance (USA) divers perform to recover the expended boosters in the ocean after a launch. The boosters splash down in an impact area about 140 miles east of Jacksonville and after recovery are towed back to KSC for refurbishment by the specially rigged recovery ships. DeepWorker 2000 will be used in a demonstration during retrieval operations after the upcoming STS-101 launch. The submarine pilot will demonstrate capabilities to cut tangled parachute riser lines using a manipulator arm and attach a Diver Operator Plug to extract water and provide flotation for the booster. DeepWorker 2000 was built by Nuytco Research Ltd., North Vancouver, British Columbia. It is 8.25 feet long, 5.75 feet high, and weighs 3,800 pounds. USA is a prime contractor to NASA for the Space Shuttle program

KSC-00padig012

NASA Image and Video Library

2000-04-22

KENNEDY SPACE CENTER, FLA. -- A Diver Operator Plug (DOP) is being pulled down into the ocean by a newly designed one-man submarine known as DeepWorker 2000. The activity is part of an operation to attach the plug to a mockup of a solid rocket booster nozzle. DeepWorker 2000 is being tested on its ability to duplicate the sometimes hazardous job United Space Alliance (USA) divers perform to recover the expended boosters in the ocean after a launch. The boosters splash down in an impact area about 140 miles east of Jacksonville and after recovery are towed back to KSC for refurbishment by the specially rigged recovery ships. DeepWorker 2000 will be used in a demonstration during retrieval operations after the upcoming STS-101 launch. The submarine pilot will demonstrate capabilities to cut tangled parachute riser lines using a manipulator arm and attach the DOP to extract water and provide flotation for the booster. DeepWorker 2000 was built by Nuytco Research Ltd., North Vancouver, British Columbia. It is 8.25 feet long, 5.75 feet high, and weighs 3,800 pounds. USA is a prime contractor to NASA for the Space Shuttle program

KSC00padig016

NASA Image and Video Library

2000-04-22

KENNEDY SPACE CENTER, FLA. -- After a successful dive, the one-man submarine known as DeepWorker 2000 is lifted from Atlantic waters near Cape Canaveral, Fla., onto the deck of the Liberty Star, one of two KSC solid rocket booster recovery ships. Inside the sub is the pilot, Anker Rasmussen. The sub is being tested on its ability to duplicate the sometimes hazardous job United Space Alliance (USA) divers perform to recover the expended boosters in the ocean after a launch. The boosters splash down in an impact area about 140 miles east of Jacksonville and after recovery are towed back to KSC for refurbishment by the specially rigged recovery ships. DeepWorker 2000 will be used in a demonstration during retrieval operations after the upcoming STS-101 launch. The submarine pilot will demonstrate capabilities to cut tangled parachute riser lines using a manipulator arm and attach a Diver Operator Plug to extract water and provide flotation for the booster. DeepWorker 2000 was built by Nuytco Research Ltd., North Vancouver, British Columbia. It is 8.25 feet long, 5.75 feet high, and weighs 3,800 pounds. USA is a prime contractor to NASA for the Space Shuttle program

KSC00padig012

NASA Image and Video Library

2000-04-22

KENNEDY SPACE CENTER, FLA. -- A Diver Operator Plug (DOP) is being pulled down into the ocean by a newly designed one-man submarine known as DeepWorker 2000. The activity is part of an operation to attach the plug to a mockup of a solid rocket booster nozzle. DeepWorker 2000 is being tested on its ability to duplicate the sometimes hazardous job United Space Alliance (USA) divers perform to recover the expended boosters in the ocean after a launch. The boosters splash down in an impact area about 140 miles east of Jacksonville and after recovery are towed back to KSC for refurbishment by the specially rigged recovery ships. DeepWorker 2000 will be used in a demonstration during retrieval operations after the upcoming STS-101 launch. The submarine pilot will demonstrate capabilities to cut tangled parachute riser lines using a manipulator arm and attach the DOP to extract water and provide flotation for the booster. DeepWorker 2000 was built by Nuytco Research Ltd., North Vancouver, British Columbia. It is 8.25 feet long, 5.75 feet high, and weighs 3,800 pounds. USA is a prime contractor to NASA for the Space Shuttle program

KSC-2014-3675

NASA Image and Video Library

2014-08-04

CAPE CANAVERAL, Fla. – Preparations are underway to begin mating the United Launch Alliance Delta IV port booster to the core booster inside the Horizontal Integration Facility at Space Launch Complex 37 on Cape Canaveral Air Force Station in Florida. The Delta IV Heavy rocket will launch an uncrewed Orion spacecraft on Exploration Flight Test-1. During the mission, Orion will travel farther into space than any human spacecraft has gone in more than 40 years. The data gathered during the flight will influence design decisions, validate existing computer models and innovative new approaches to space systems development, as well as reduce overall mission risks and costs for later Orion flights. Liftoff of Orion on the first flight test is planned for December 2014. Photo credit: NASA/Ben Smegelsky

KSC-2014-3676

NASA Image and Video Library

2014-08-04

CAPE CANAVERAL, Fla. – In this close-up photograph, the United Launch Alliance Delta IV port booster is being mated to the core booster inside the Horizontal Integration Facility at Space Launch Complex 37 on Cape Canaveral Air Force Station in Florida. The Delta IV Heavy rocket will launch an uncrewed Orion spacecraft on Exploration Flight Test-1. During the mission, Orion will travel farther into space than any human spacecraft has gone in more than 40 years. The data gathered during the flight will influence design decisions, validate existing computer models and innovative new approaches to space systems development, as well as reduce overall mission risks and costs for later Orion flights. Liftoff of Orion on the first flight test is planned for December 2014. Photo credit: NASA/Ben Smegelsky

KSC-2014-3910

NASA Image and Video Library

2014-09-12

CAPE CANAVERAL, Fla. – Inside the Horizontal Integration Facility at Space Launch Complex 37 at Cape Canaveral Air Force Station in Florida, the second stage of the United Launch Alliance Delta IV Heavy rocket has been mated to the core booster of the three booster stages for the unpiloted Exploration Flight Test-1, or EFT-1. During the mission, Orion will travel farther into space than any human spacecraft has gone in more than 40 years. The data gathered during the flight will influence design decisions, validate existing computer models and innovative new approaches to space systems development, as well as reduce overall mission risks and costs for later Orion flights. Liftoff of Orion on the first flight test is planned for December 2014. Photo credit: NASA/Daniel Casper

KSC-2014-3902

NASA Image and Video Library

2014-09-12

CAPE CANAVERAL, Fla. – Inside the Horizontal Integration Facility at Space Launch Complex 37 at Cape Canaveral Air Force Station in Florida, preparations are underway to mate the second stage of a Delta IV Heavy rocket to the central core booster of the three booster stages for the unpiloted Exploration Flight Test-1, or EFT-1. During the mission, Orion will travel farther into space than any human spacecraft has gone in more than 40 years. The data gathered during the flight will influence design decisions, validate existing computer models and innovative new approaches to space systems development, as well as reduce overall mission risks and costs for later Orion flights. Liftoff of Orion on the first flight test is planned for December 2014. Photo credit: NASA/Daniel Casper

KSC-2014-3682

NASA Image and Video Library

2014-08-04

CAPE CANAVERAL, Fla. – The United Launch Alliance Delta IV port booster is being mated to the core booster inside the Horizontal Integration Facility at Space Launch Complex 37 on Cape Canaveral Air Force Station in Florida. The Delta IV Heavy rocket will launch an uncrewed Orion spacecraft on Exploration Flight Test-1. During the mission, Orion will travel farther into space than any human spacecraft has gone in more than 40 years. The data gathered during the flight will influence design decisions, validate existing computer models and innovative new approaches to space systems development, as well as reduce overall mission risks and costs for later Orion flights. Liftoff of Orion on the first flight test is planned for December 2014. Photo credit: NASA/Ben Smegelsky

Testing of Environmentally Preferable Aluminum Pretreatments and Coating Systems for Use on Space Shuttle Solid Rocket Boosters (SRB)

NASA Technical Reports Server (NTRS)

Clayton, C.; Raley, R.; Zook, L.

2001-01-01

The solid rocket booster (SRB) has historically used a chromate conversion coating prior to protective finish application. After conversion coating, an organic paint system consisting of a chromated epoxy primer and polyurethane topcoat is applied. An overall systems approach was selected to reduce waste generation from the coatings application and removal processes. While the most obvious waste reduction opportunity involved elimination of the chromate conversion coating, several other coating system configurations were explored in an attempt to reduce the total waste. This paper will briefly discuss the use of a systems view to reduce waste generation from the coating process and present the results of the qualification testing of nonchromated aluminum pretreatments and alternate coating systems configurations.

Delta Mariner arrival with EFT-1 Booster

NASA Image and Video Library

2014-03-03

CAPE CANAVERAL, Fla. – The United Launch Alliance barge Delta Mariner enters Port Canaveral in Florida. The barge is carrying two of the booster stages for the Delta IV Heavy rocket slated for Orion's Exploration Flight Test-1, or EFT-1. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep-space return velocities. The first unpiloted test flight of Orion is scheduled to launch in September 2014 atop a Delta IV Heavy rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: NASA/Frankie Martin

Delta Mariner arrival with EFT-1 Booster

NASA Image and Video Library

2014-03-03

CAPE CANAVERAL, Fla. – The United Launch Alliance barge Delta Mariner is secured to the dock in Port Canaveral in Florida. The barge is carrying two of the booster stages for the Delta IV Heavy rocket slated for Orion's Exploration Flight Test-1, or EFT-1. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep-space return velocities. The first unpiloted test flight of Orion is scheduled to launch in September 2014 atop a Delta IV Heavy rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: NASA/Frankie Martin

Delta Mariner arrival with EFT-1 Booster

NASA Image and Video Library

2014-03-03

CAPE CANAVERAL, Fla. – The United Launch Alliance barge Delta Mariner prepares to dock in Port Canaveral in Florida. The barge is carrying two of the booster stages for the Delta IV Heavy rocket slated for Orion's Exploration Flight Test-1, or EFT-1. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep-space return velocities. The first unpiloted test flight of Orion is scheduled to launch in September 2014 atop a Delta IV Heavy rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: NASA/Frankie Martin

Delta Mariner arrival with EFT-1 Booster

NASA Image and Video Library

2014-03-03

CAPE CANAVERAL, Fla. – The United Launch Alliance barge Delta Mariner approaches the mouth of Port Canaveral in Florida. The barge is carrying two of the booster stages for the Delta IV Heavy rocket slated for Orion's Exploration Flight Test-1, or EFT-1. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep-space return velocities. The first unpiloted test flight of Orion is scheduled to launch in September 2014 atop a Delta IV Heavy rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: NASA/Frankie Martin

Delta Mariner arrival with EFT-1 Booster

NASA Image and Video Library

2014-03-03

CAPE CANAVERAL, Fla. – The United Launch Alliance barge Delta Mariner nears the dock in Port Canaveral in Florida. The barge is carrying two of the booster stages for the Delta IV Heavy rocket slated for Orion's Exploration Flight Test-1, or EFT-1. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep-space return velocities. The first unpiloted test flight of Orion is scheduled to launch in September 2014 atop a Delta IV Heavy rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: NASA/Frankie Martin

Delta Mariner arrival with EFT-1 Booster

NASA Image and Video Library

2014-03-03

CAPE CANAVERAL, Fla. – The United Launch Alliance barge Delta Mariner glides past the jetties as it enters Port Canaveral in Florida. The barge is carrying two of the booster stages for the Delta IV Heavy rocket slated for Orion's Exploration Flight Test-1, or EFT-1. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep-space return velocities. The first unpiloted test flight of Orion is scheduled to launch in September 2014 atop a Delta IV Heavy rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: NASA/Frankie Martin

Delta Mariner arrival with EFT-1 Booster

NASA Image and Video Library

2014-03-03

CAPE CANAVERAL, Fla. – The United Launch Alliance barge Delta Mariner travels through Port Canaveral in Florida. The barge is carrying two of the booster stages for the Delta IV Heavy rocket slated for Orion's Exploration Flight Test-1, or EFT-1. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep-space return velocities. The first unpiloted test flight of Orion is scheduled to launch in September 2014 atop a Delta IV Heavy rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: NASA/Frankie Martin

Delta Mariner arrival with EFT-1 Booster

NASA Image and Video Library

2014-03-03

CAPE CANAVERAL, Fla. – The United Launch Alliance barge Delta Mariner docks in Port Canaveral in Florida. The barge is carrying two of the booster stages for the Delta IV Heavy rocket slated for Orion's Exploration Flight Test-1, or EFT-1. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep-space return velocities. The first unpiloted test flight of Orion is scheduled to launch in September 2014 atop a Delta IV Heavy rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: NASA/Frankie Martin

47 CFR 74.1233 - Processing FM translator and booster station applications.

Code of Federal Regulations, 2014 CFR

2014-10-01

... 47 Telecommunication 4 2014-10-01 2014-10-01 false Processing FM translator and booster station... SERVICES FM Broadcast Translator Stations and FM Broadcast Booster Stations § 74.1233 Processing FM translator and booster station applications. (a) Applications for FM translator and booster stations are...

47 CFR 74.1233 - Processing FM translator and booster station applications.

Code of Federal Regulations, 2012 CFR

2012-10-01

... 47 Telecommunication 4 2012-10-01 2012-10-01 false Processing FM translator and booster station... SERVICES FM Broadcast Translator Stations and FM Broadcast Booster Stations § 74.1233 Processing FM translator and booster station applications. (a) Applications for FM translator and booster stations are...

47 CFR 74.733 - UHF translator signal boosters.

Code of Federal Regulations, 2014 CFR

2014-10-01

... 47 Telecommunication 4 2014-10-01 2014-10-01 false UHF translator signal boosters. 74.733 Section... Translator, and TV Booster Stations § 74.733 UHF translator signal boosters. (a) The licensee of a UHF television broadcast translator station may be authorized to operate one or more signal boosters for the...

47 CFR 74.1233 - Processing FM translator and booster station applications.

Code of Federal Regulations, 2011 CFR

2011-10-01

... 47 Telecommunication 4 2011-10-01 2011-10-01 false Processing FM translator and booster station... SERVICES FM Broadcast Translator Stations and FM Broadcast Booster Stations § 74.1233 Processing FM translator and booster station applications. (a) Applications for FM translator and booster stations are...

47 CFR 74.733 - UHF translator signal boosters.

Code of Federal Regulations, 2013 CFR

2013-10-01

... 47 Telecommunication 4 2013-10-01 2013-10-01 false UHF translator signal boosters. 74.733 Section... Translator, and TV Booster Stations § 74.733 UHF translator signal boosters. (a) The licensee of a UHF television broadcast translator station may be authorized to operate one or more signal boosters for the...

47 CFR 74.1233 - Processing FM translator and booster station applications.

Code of Federal Regulations, 2013 CFR

2013-10-01

... 47 Telecommunication 4 2013-10-01 2013-10-01 false Processing FM translator and booster station... SERVICES FM Broadcast Translator Stations and FM Broadcast Booster Stations § 74.1233 Processing FM translator and booster station applications. (a) Applications for FM translator and booster stations are...

47 CFR 74.1233 - Processing FM translator and booster station applications.

Code of Federal Regulations, 2010 CFR

2010-10-01

... 47 Telecommunication 4 2010-10-01 2010-10-01 false Processing FM translator and booster station... SERVICES FM Broadcast Translator Stations and FM Broadcast Booster Stations § 74.1233 Processing FM translator and booster station applications. (a) Applications for FM translator and booster stations are...

47 CFR 74.733 - UHF translator signal boosters.

Code of Federal Regulations, 2010 CFR

2010-10-01

... 47 Telecommunication 4 2010-10-01 2010-10-01 false UHF translator signal boosters. 74.733 Section... Translator, and TV Booster Stations § 74.733 UHF translator signal boosters. (a) The licensee of a UHF television broadcast translator station may be authorized to operate one or more signal boosters for the...

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

NASA Technical Reports Server (NTRS)

Thorpe, Douglas G.

1991-01-01

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

Initiation Capacity of a Specially Shaped Booster Pellet and Numerical Simulation of Its Initiation Process

NASA Astrophysics Data System (ADS)

Hu, Li-Shuang; Hu, Shuang-Qi; Cao, Xiong; Zhang, Jian-Ren

2014-01-01

The insensitive main charge explosive is creating new requirements for the booster pellet of detonation trains. The traditional cylindrical booster pellet has insufficient energy output to reliably initiate the insensitive main charge explosive. In this research, a concave spherical booster pellet was designed. The initiation capacity of the concave spherical booster pellet was studied using varied composition and axial steel dent methods. The initiation process of the concave spherical booster pellet was also simulated by ANSYS/LS-DYNA. The results showed that using a concave spherical booster allows a 42% reduction in the amount of explosive needed to match the initiation capacity of a conventional cylindrical booster of the same dimensions. With the other parameters kept constant, the initiation capacity of the concave spherical booster pellet increases with decreased cone angle and concave radius. The numerical simulation results are in good agreement with the experimental data.

Tailored interventions for screening mammography among a sample of initially non-adherent women: when is a booster dose important?

PubMed

Skinner, Celette Sugg; Kobrin, Sarah C; Monahan, Patrick O; Daggy, Joanne; Menon, Usha; Todora, Helen Smith; Champion, Victoria L

2007-01-01

To assess added value of a booster dose of a tailored mammography intervention. Participants, non-adherent at baseline, were randomly assigned to usual care or one of three tailored interventions. Intervention group members (n=657) were further randomly assigned to receive/not receive a booster intervention dose. Electronic record mammography data were collected following initial intervention and at 6 and 15 months post-booster. Booster had no effect among women not screened after first intervention dose (n=337). Among women screened after initial dose (n=320), booster predicted re-screening at 6 but not 15 months. A boosterxrace interaction showed a booster effect at 6 months for African Americans (OR=4.66, p=.0005) but not Caucasians (OR=0.74, p=.44). Findings suggest if a first-dose intervention does not facilitate screening, neither will a booster dose. However, among women for whom a first dose is effective, boosters can facilitate timely repeat adherence, especially among African Americans. At 6 months booster recipients were less likely to be off-schedule but, by 15 months, the groups were similar. Boosters may effect when, but not whether, women continue screening.

Investigation of structural factors of safety for the space shuttle

NASA Technical Reports Server (NTRS)

1972-01-01

A study was made of the factors governing the structural design of the fully reusable space shuttle booster to establish a rational approach to select optimum structural factors of safety. The study included trade studies of structural factors of safety versus booster service life, weight, cost, and reliability. Similar trade studies can be made on other vehicles using the procedures developed. The major structural components of a selected baseline booster were studied in depth, each being examined to determine the fatigue life, safe-life, and fail-safe capabilities of the baseline design. Each component was further examined to determine its reliability and safety requirements, and the change of structural weight with factors of safety. The apparent factors of safety resulting from fatigue, safe-life, proof test, and fail-safe requirements were identified. The feasibility of reduced factors of safety for design loads such as engine thrust, which are well defined, was examined.

Aerodynamic Characteristics and Glide-Back Performance of Langley Glide-Back Booster

NASA Technical Reports Server (NTRS)

Pamadi, Bandu N.; Covell, Peter F.; Tartabini, Paul V.; Murphy, Kelly J.

2004-01-01

NASA-Langley Research Center is conducting system level studies on an-house concept of a small launch vehicle to address NASA's needs for rapid deployment of small payloads to Low Earth Orbit. The vehicle concept is a three-stage system with a reusable first stage and expendable upper stages. The reusable first stage booster, which glides back to launch site after staging around Mach 3 is named the Langley Glide-Back Booster (LGBB). This paper discusses the aerodynamic characteristics of the LGBB from subsonic to supersonic speeds, development of the aerodynamic database and application of this database to evaluate the glide back performance of the LGBB. The aerodynamic database was assembled using a combination of wind tunnel test data and engineering level analysis. The glide back performance of the LGBB was evaluated using a trajectory optimization code and subject to constraints on angle of attack, dynamic pressure and normal acceleration.

A real time status monitor for transistor bank driver power limit resistor in boost injection kicker power supply

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

Mi, J.; Tan, Y.; Zhang, W.

2011-03-28

For years suffering of Booster Injection Kicker transistor bank driver regulator troubleshooting, a new real time monitor system has been developed. A simple and floating circuit has been designed and tested. This circuit monitor system can monitor the driver regulator power limit resistor status in real time and warn machine operator if the power limit resistor changes values. This paper will mainly introduce the power supply and the new designed monitoring system. This real time resistor monitor circuit shows a useful method to monitor some critical parts in the booster pulse power supply. After two years accelerator operation, it showsmore » that this monitor works well. Previously, we spent a lot of time in booster machine trouble shooting. We will reinstall all 4 PCB into Euro Card Standard Chassis when the power supply system will be updated.« less

Creation of an Upper Stage Trajectory Capability Boundary to Enable Booster System Trade Space Exploration

NASA Technical Reports Server (NTRS)

Walsh, Ptrick; Coulon, Adam; Edwards, Stephen; Mavris, Dimitri N.

2012-01-01

The problem of trajectory optimization is important in all space missions. The solution of this problem enables one to specify the optimum thrust steering program which should be followed to achieve a specified mission objective, simultaneously satisfying the constraints.1 It is well known that whether or not the ascent trajectory is optimal can have a significant impact on propellant usage for a given payload, or on payload weight for the same gross vehicle weight.2 Consequently, ascent guidance commands are usually optimized in some fashion. Multi-stage vehicles add complexity to this analysis process as changes in vehicle properties in one stage propagate to the other stages through gear ratios and changes in the optimal trajectory. These effects can cause an increase in analysis time as more variables are added and convergence of the optimizer to system closure requires more analysis iterations. In this paper, an approach to simplifying this multi-stage problem through the creation of an upper stage capability boundary is presented. This work was completed as part of a larger study focused on trade space exploration for the advanced booster system that will eventually form a part of NASA s new Space Launch System.3 The approach developed leverages Design of Experiments and Surrogate Modeling4 techniques to create a predictive model of the SLS upper stage performance. The design of the SLS core stages is considered fixed for the purposes of this study, which results in trajectory parameters such as staging conditions being the only variables relevant to the upper stage. Through the creation of a surrogate model, which takes staging conditions as inputs and predicts the payload mass delivered by the SLS upper stage to a reference orbit as the response, it is possible to identify a "surface" of staging conditions which all satisfy the SLS requirement of placing 130 metric tons into low-Earth orbit (LEO).3 This identified surface represents the 130 metric ton capability boundary for the upper stage, such that if the combined first stage and boosters can achieve any one staging point on that surface, then the design is identified as feasible. With the surrogate model created, design and analysis of advanced booster concepts is streamlined, as optimization of the upper stage trajectory is no longer required in every design loop.

Executive Summary of Propulsion on the Orion Abort Flight-Test Vehicles

NASA Technical Reports Server (NTRS)

Jones, Daniel S.; Koelfgen, Syri J.; Barnes, Marvin W.; McCauley, Rachel J.; Wall, Terry M.; Reed, Brian D.; Duncan, C. Miguel

2012-01-01

The NASA Orion Flight Test Office was tasked with conducting a series of flight tests in several launch abort scenarios to certify that the Orion Launch Abort System is capable of delivering astronauts aboard the Orion Crew Module to a safe environment, away from a failed booster. The first of this series was the Orion Pad Abort 1 Flight-Test Vehicle, which was successfully flown on May 6, 2010 at the White Sands Missile Range in New Mexico. This paper provides a brief overview of the three propulsive subsystems used on the Pad Abort 1 Flight-Test Vehicle. An overview of the propulsive systems originally planned for future flight-test vehicles is also provided, which also includes the cold gas Reaction Control System within the Crew Module, and the Peacekeeper first stage rocket motor encased within the Abort Test Booster aeroshell. Although the Constellation program has been cancelled and the operational role of the Orion spacecraft has significantly evolved, lessons learned from Pad Abort 1 and the other flight-test vehicles could certainly contribute to the vehicle architecture of many future human-rated space launch vehicles.

Reentry aerodynamic characteristics of a space shuttle solid rocket booster model 449 tested in MSFC 14 by 14 inch TWT (SA26F)

NASA Technical Reports Server (NTRS)

Johnson, J. D.; Braddock, W. F.

1974-01-01

Force tests of a 0.563 percent scale space shuttle solid rocket booster (SRB) model, MSFC Model 449, were conducted at the Marshall Space Flight Center 14 x 14 inch Trisonic Wind Tunnel. There were a total of 134 runs (pitch polars) made. Test Mach numbers were 0.6, 0.9, 1.2, 1.96, 2.74, 3.48, 4.00, 4.45, and 4.96; test angles of attack ranged from minus 10 degrees to 190 degrees; test Reynolds numbers ranged from 4.9 million per foot to 7.1 million per foot; and test roll angles were 0, 45, 90, and 135 degrees. The model was tested with three different engine nozzle/skirts. Two of these engine configurations differed from each other in the magnitude of the volume inside the nozzle and skirt. The third engine configuration had part of the nozzle removed. The model was tested with an electrical tunnel in combination with separation rockets of two different heights.

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.

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

NASA Technical Reports Server (NTRS)

Tejnil, Edward; Rogers, Stuart E.

2012-01-01

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

Dynamic testing of a single-degree-of-freedom strapdown gyroscope

NASA Technical Reports Server (NTRS)

Lory, C. B.; Feldman, J.; Sinkiewicz, J. S., Jr.

1971-01-01

Test methods and results are presented for the equivalent average input rate of a single-degree-of-freedom gyroscope operated both open loop and with a ternary-logic pulse-torque-to-balance loop during multiaxis angular oscillation. For the open-loop tests, good agreement was obtained with theoretical results. Two-axis testing was performed for oscillations about the Input-Output axes, the Input-Spin axes, and the Spin-Output axes. These tests run in the torque-to-balance mode revealed significant departures from open-loop results in the induced drift rate. An analysis is developed explaining much of the closed-loop data presented. Test data for the gryoscope in a ternary torque-to-balance loop with constant input rates is presented. The tests demonstrate that the instrument rate linearity does not change with interrogation frequency from 3,600 to 14,400 Hz if the torque coil is tuned to offer a resistive load to the current switch. Analysis cited shows that gyroscope lag compensation eliminates multiple pulsing and other equivalent forms of degraded resolution in a wide variety of quantizing loops. This result is test verified for the ternary delta-modulator loop.

Liquid Rocket Booster (LRB) for the Space Transportation System (STS) systems study. Appendix E: Pressure-fed booster test bed for the liquid rocket booster study

NASA Technical Reports Server (NTRS)

1989-01-01

The stress analysis/structural design of the Pressure-Fed Booster Engine Test Bed using the existing F-1 Test Facility Test Stand at Huntsville, Alabama is described. The analysis has been coded and set up for solution on NASTRAN. A separate stress program was established to take the NASTRAN output and perform stress checks on the members. Joint checks and other necessary additional checks were performed by hand. The notes include a brief description of other programs which assist in reproducing and reviewing the NASTRAN results. The redesign of the test stand members and the stress analysis was performed per the A.I.S.C. Code. Loads on the stand consist of the loaded run tanks; wind loads; seismic loads; live loads consisting of snow and ice: live and dead loads of steel; and loaded pressurant bottle. In combining loads, wind loads and seismic loads were each combined with full live loads. Wind and seismic loads were not combined. No one third increase in allowables was taken for the environmental loads except at decks 147 and 214, where the increase was used when considering the stay rods, brackets and stay beams. Wind and seismic loads were considered from each of the four coordinate directions (i.e. N,S,E,W) to give eight basic conditions. The analysis was run with the pressurant tank mounted at level 125. One seismic condition was also run with the tank mounted at levels 169 and 214. No failures were noted with mounting at level 169, but extensive deck failure with mounting at level 214 (the loadsets used are included on the tape, but no detailed results are included in the package). Decking support beams at levels 147 and 214 are not included in the model. The stress program thus does not reduce strut lengths to the length between support beams (the struts are attached to the beams at intersection points) and gives stress ratios larger than one for some of the struts. The affected members were therefore checked by hand.

Space shuttle phase B. Volume 2: Technical summary, addendum A

NASA Technical Reports Server (NTRS)

1971-01-01

A study was conducted to analyze the characteristics and performance data for the booster vehicles to be used with the space shuttle operations. It was determined that the single pressure-fed booster offered the lowest program cost per flight of the pressure-fed booster arrangements studied. The fly back booster required the highest peak annual funding and highest program cost. It was recommended that the pressure-fed booster, series burn with liquid oxygen phase, be continued for further study. The flyback booster study was discontinued. Both solid and liquid propelled booster vehicles with 14 by 45 foot and 15 by 60 foot payload orbiters were considered.

Five-Segment Reusable Solid Rocket Booster Upgrade

NASA Technical Reports Server (NTRS)

Sauvageau, Don

1999-01-01

The Five Segment Reusable Solid Rocket Booster (RSRB) feasibility status is presented in viewgraph form. The Five Segment Booster (FSB) objective is to provide a low cost, low risk approach to increase reliability and safety of the Shuttle system. Topics include: booster upgrade requirements; design summary; reliability issues; booster trajectories; launch site assessment; and enhanced abort modes.

30 CFR 57.8518 - Main and booster fans.

Code of Federal Regulations, 2013 CFR

2013-07-01

... 30 Mineral Resources 1 2013-07-01 2013-07-01 false Main and booster fans. 57.8518 Section 57.8518... and Underground § 57.8518 Main and booster fans. (a) All mine main and booster fans installed and used..., or adjustments. (b) In the event of main or booster fan failure due to a malfunction, accident, power...

30 CFR 57.8518 - Main and booster fans.

Code of Federal Regulations, 2014 CFR

2014-07-01

... 30 Mineral Resources 1 2014-07-01 2014-07-01 false Main and booster fans. 57.8518 Section 57.8518... and Underground § 57.8518 Main and booster fans. (a) All mine main and booster fans installed and used..., or adjustments. (b) In the event of main or booster fan failure due to a malfunction, accident, power...

30 CFR 57.8518 - Main and booster fans.

Code of Federal Regulations, 2010 CFR

2010-07-01

... 30 Mineral Resources 1 2010-07-01 2010-07-01 false Main and booster fans. 57.8518 Section 57.8518... and Underground § 57.8518 Main and booster fans. (a) All mine main and booster fans installed and used..., or adjustments. (b) In the event of main or booster fan failure due to a malfunction, accident, power...

30 CFR 57.8518 - Main and booster fans.

Code of Federal Regulations, 2012 CFR

2012-07-01

... 30 Mineral Resources 1 2012-07-01 2012-07-01 false Main and booster fans. 57.8518 Section 57.8518... and Underground § 57.8518 Main and booster fans. (a) All mine main and booster fans installed and used..., or adjustments. (b) In the event of main or booster fan failure due to a malfunction, accident, power...

30 CFR 57.8518 - Main and booster fans.

Code of Federal Regulations, 2011 CFR

2011-07-01

... 30 Mineral Resources 1 2011-07-01 2011-07-01 false Main and booster fans. 57.8518 Section 57.8518... and Underground § 57.8518 Main and booster fans. (a) All mine main and booster fans installed and used..., or adjustments. (b) In the event of main or booster fan failure due to a malfunction, accident, power...

Emulsion based cast booster - a priming system

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

Gupta, R.N.; Mishra, A.K.

2005-07-01

This paper explores the potential of emulsion based cast booster to be used as primer to initiate bulk delivered emulsion explosives used in mines. An attempt has been made for comparative study between conventional cast booster and emulsion based cast booster in terms of the initiation process developed and their capability to develop and maintain the stable detonation process in the column explosives. The study has been conducted using a continuous velocity of detonation (VOD) measuring instrument. During this study three blasts have been monitored. In each blast two holes have been selected for study, the first hole being initiatedmore » with conventional cast booster while the other one with emulsion based cast booster. The findings of the study advocates that emulsion based cast booster is capable of efficient priming of bulk delivered column explosive with stable detonation process in the column. Further, the booster had advantages over the conventional PETN/TNT based cast booster. 5 refs., 2 figs., 1 tab., 1 photo.« less

Space Shuttle Project

NASA Image and Video Library

1998-03-24

The roman candle effect as seen in this picture represents the testing of a solid rocket booster (SRB) for unexplained corrosion conditions (EUCC) which have occurred on the nozzles of redesigned solid rocket motors (RSRM). The motor being tested in this photo is a 48 M-NASA motor.

47 CFR 74.15 - Station license period.

Code of Federal Regulations, 2011 CFR

2011-10-01

... broadcast booster station or a TV broadcast booster station will be issued for a period running concurrently... broadcast station, FM translator or FM broadcast booster, TV translator or TV broadcast booster, or low...

47 CFR 74.15 - Station license period.

Code of Federal Regulations, 2012 CFR

2012-10-01

... broadcast booster station or a TV broadcast booster station will be issued for a period running concurrently... broadcast station, FM translator or FM broadcast booster, TV translator or TV broadcast booster, or low...

Lightning tests and analyses of tunnel bond straps and shielded cables on the Space Shuttle solid rocket booster

NASA Technical Reports Server (NTRS)

Druen, William M.

1993-01-01

The purposes of the tests and analyses described in this report are as follows: (1) determine the lightning current survivability of five alternative changed designs of the bond straps which electrically bond the solid rocket booster (SRB) systems tunnel to the solid rocket motor (SRM) case; (2) determine the amount of reduction in induced voltages on operational flight (OF) tunnel cables obtained by a modified design of tunnel bond straps (both tunnel cover-to-cover and cover-to-motor case); (3) determine the contribution of coupling to the OF tunnel cables by ground electrical and instrumentation (GEI) cables which enter the systems tunnel from unshielded areas on the surfaces of the motor case; and (4) develop a model (based on test data) and calculate the voltage levels at electronic 'black boxes' connected to the OF cables that run in the systems tunnel.

Technologies for Future Precision Strike Missile Systems (les Technologies des futurs systemes de missiles pour frappe de precision)

DTIC Science & Technology

2001-07-01

hardware - in - loop (HWL) simulation is also developed...Firings / Engine Tests Structure Test Hardware In - Loop Simulation Subsystem Test Lab Tests Seeker Actuators Sensors Electronics Propulsion Model Aero Model...Structure Test Hardware In - Loop Simulation Subsystem Test Lab Tests Seeker Actuators Sensors Electronics Propulsion Model Aero Model Model

How securely is the testicular artery occluded in the spermatic cord by using a ligature?

PubMed

Rijkenhuizen, A B M; Sommerauer, S; Fasching, M; Velde, K; Peham, C

2013-09-01

There are no studies on the ideal ligature technique for the spermatic cord. To compare the maximal resistance pressure in the testicular artery and the maximal tensile forces to produce failure of 2 different ligature techniques used for ligation of the equine spermatic cord. The capabilities of 2 types of ligatures, single knot loop and double knot loop, were assessed using a pressure-resistance test in testicular arteries and with an in vitro mechanical evaluation of the tensile strength by single cycle-to-failure testing. In the pressure-resistance test, the mean ± s.d. peak force at failure of the single knot loop was 354.4 ± 91.7 mmHg and for the double knot loop 303.2 ± 62.0 mmHg. There was no significant difference between the maximal load to failure of the single knot loop and double knot loop technique. The pressure needed for rupture was significantly higher (P = 0.001) than for leakage. The maximal tensile force at failure of the single knot loop was significantly higher than the double knot loop (P = 0.028). There was no significant difference in load elongation properties to failure between the single knot loop and double knot loop. Although no significant differences were obtained in the pressure-resistance test, the single knot loop sustained significantly greater load to failure than the double knot loop in single cycle-to-failure testing. Based on these findings, it would appear that the performance of the single knot loop should be superior to the double knot loop. Both ligature techniques are able to withstand the normal physiological intravascular pressure. The single knot loop has the greater breaking strength of the 2 ligatures tested and is less time consuming to perform and may therefore have advantages during equine castration. © 2012 EVJ Ltd.

Ares I First Stage Booster Deceleration System: An Overview

NASA Technical Reports Server (NTRS)

King, Ron; Hengel, John E.; Wolf, Dean

2009-01-01

In 2005, the Congressional NASA Authorization Act enacted a new space exploration program, the "Vision for Space Exploratien". The Constellation Program was formed to oversee the implementation of this new mission. With an intent not simply to support the International Space Station, but to build a permanent outpost on the Moon and then travel on to explore ever more distant terrains, the Constellation Program is supervising the development of a brand new fleet of launch vehicles, the Ares. The Ares lineup will include two new launch vehicles: the Ares I Crew Launch Vehicle and the Ares V Cargo Launch Vehicle. A crew exploration vehicle, Orion, will be launched on the Ares I. It will be capable of docking with the Space Station, the lunar lander, Altair, and the Earth Departure Stage of Ares V. The Ares V will be capable of lifting both large-scale hardware and the Altair into space. The Ares First Stage Team is tasked with developing the propulsion system necessary to liftoff from the Earth and loft the entire Ares vehicle stack toward low Earth orbit. The Ares I First Stage booster is a 12-foot diameter, five-segment, reusable solid rocket booster derived from the Space Shuttle's four segment reusable solid rocket booster (SRB). It is separated from the Upper Stage through the use of a Deceleration Subsystem (DSS). Booster Tumble Motors are used to induce the pitch tumble following separation from the Upper Stage. The spent Ares I booster must be recoverable using a parachute deceleration system similar to that of the Shuttle SRB heritage system. Since Ares I is much heavier and reenters the Earth's atmosphere from a higher altitude at a much higher velocity than the SRB, all of the parachutes must be redesigned to reliably meet the operational requisites of the new launch vehicles. This paper presents an overview of this new booster deceleration system. It includes comprehensive detail of the parachute deceleration system, its design and deployment sequences, including how and why it is being developed, the requirements it must meet, and the testing involved in its implementation.

47 CFR 73.3500 - Application and report forms.

Code of Federal Regulations, 2014 CFR

2014-10-01

..., TV Translator or TV Booster Station. 347 Application for a Low Power TV, TV Translator or TV Booster... Booster Station. 350 Application for an FM Translator or FM Booster Station License. 395-B Annual...

47 CFR 73.3500 - Application and report forms.

Code of Federal Regulations, 2012 CFR

2012-10-01

..., TV Translator or TV Booster Station. 347 Application for a Low Power TV, TV Translator or TV Booster... Booster Station. 350 Application for an FM Translator or FM Booster Station License. 395-B Annual...

47 CFR 73.3500 - Application and report forms.

Code of Federal Regulations, 2011 CFR

2011-10-01

..., TV Translator or TV Booster Station. 347 Application for a Low Power TV, TV Translator or TV Booster... Booster Station. 350 Application for an FM Translator or FM Booster Station License. 395-B Annual...

47 CFR 73.3500 - Application and report forms.

Code of Federal Regulations, 2013 CFR

2013-10-01

..., TV Translator or TV Booster Station. 347 Application for a Low Power TV, TV Translator or TV Booster... Booster Station. 350 Application for an FM Translator or FM Booster Station License. 395-B Annual...

Closed-loop thrust and pressure profile throttling of a nitrous oxide/hydroxyl-terminated polybutadiene hybrid rocket motor

NASA Astrophysics Data System (ADS)

Peterson, Zachary W.

Hybrid motors that employ non-toxic, non-explosive components with a liquid oxidizer and a solid hydrocarbon fuel grain have inherently safe operating characteristics. The inherent safety of hybrid rocket motors offers the potential to greatly reduce overall operating costs. Another key advantage of hybrid rocket motors is the potential for in-flight shutdown, restart, and throttle by controlling the pressure drop between the oxidizer tank and the injector. This research designed, developed, and ground tested a closed-loop throttle controller for a hybrid rocket motor using nitrous oxide and hydroxyl-terminated polybutadiene as propellants. The research simultaneously developed closed-loop throttle algorithms and lab scale motor hardware to evaluate the fidelity of the throttle simulations and algorithms. Initial open-loop motor tests were performed to better classify system parameters and to validate motor performance values. Deep-throttle open-loop tests evaluated limits of stable thrust that can be achieved on the test hardware. Open-loop tests demonstrated the ability to throttle the motor to less than 10% of maximum thrust with little reduction in effective specific impulse and acoustical stability. Following the open-loop development, closed-loop, hardware-in-the-loop tests were performed. The closed-loop controller successfully tracked prescribed step and ramp command profiles with a high degree of fidelity. Steady-state accuracy was greatly improved over uncontrolled thrust.

Thermal Management Coating As Thermal Protection System for Space Transportation System

NASA Technical Reports Server (NTRS)

Kaul, Raj; Stuckey, C. Irvin

2003-01-01

This paper presents viewgraphs on the development of a non-ablative thermal management coating used as the thermal protection system material for space shuttle rocket boosters and other launch vehicles. The topics include: 1) Coating Study; 2) Aerothermal Testing; 3) Preconditioning Environments; 4) Test Observations; 5) Lightning Strike Test Panel; 6) Test Panel After Impact Testing; 7) Thermal Testing; and 8) Mechanical Testing.

KSC-2009-2144

NASA Image and Video Library

2009-03-18

CAPE CANAVERAL, Fla. – The Solid Rocket Booster Retrieval Ship Liberty Star tows a booster to the dock at Hangar AF at Cape Canaveral Air Force Station in Florida. The booster was used during space shuttle Discovery's launch from NASA's Kennedy Space Center in Florida March 15 on mission STS-119. The space shuttle’s solid rocket booster casings and associated flight hardware are recovered at sea after a launch. The spent rockets were recovered by NASA's Solid Rocket Booster Retrieval Ships Freedom Star and Liberty Star. The boosters impact the Atlantic Ocean approximately seven minutes after liftoff. The splashdown area is a square of about six by nine nautical miles located about 140 nautical miles downrange from the launch pad. The retrieval ships are stationed approximately 8 to 10 nautical miles from the impact area at the time of splashdown. As soon as the boosters enter the water, the ships accelerate to a speed of 15 knots and quickly close on the boosters. The pilot chutes and main parachutes are the first items to be brought on board. With the chutes and frustum recovered, attention turns to the boosters. The ship’s tow line is connected and the booster is returned to the Port and, after transfer to a position alongside the ship, to Hangar AF. There, the expended boosters are disassembled, refurbished and reloaded with solid propellant for reuse. Photo credit: NASA/Jack Pfaller

KSC-2009-2141

NASA Image and Video Library

2009-03-18

CAPE CANAVERAL, Fla. – The Solid Rocket Booster Retrieval Ship Liberty Star tows a booster to the dock at Hangar AF at Cape Canaveral Air Force Station in Florida. The booster was used during space shuttle Discovery's launch from NASA's Kennedy Space Center in Florida March 15 on mission STS-119. The space shuttle’s solid rocket booster casings and associated flight hardware are recovered at sea after a launch. The spent rockets were recovered by NASA's Solid Rocket Booster Retrieval Ships Freedom Star and Liberty Star. The boosters impact the Atlantic Ocean approximately seven minutes after liftoff. The splashdown area is a square of about six by nine nautical miles located about 140 nautical miles downrange from the launch pad. The retrieval ships are stationed approximately 8 to 10 nautical miles from the impact area at the time of splashdown. As soon as the boosters enter the water, the ships accelerate to a speed of 15 knots and quickly close on the boosters. The pilot chutes and main parachutes are the first items to be brought on board. With the chutes and frustum recovered, attention turns to the boosters. The ship’s tow line is connected and the booster is returned to the Port and, after transfer to a position alongside the ship, to Hangar AF. There, the expended boosters are disassembled, refurbished and reloaded with solid propellant for reuse. Photo credit: NASA/Jack Pfaller

KSC-2014-3688

NASA Image and Video Library

2014-08-04

CAPE CANAVERAL, Fla. – A United Launch Alliance, or ULA, technician monitors the progress as the Delta IV port booster is mated to the core booster inside the Horizontal Integration Facility at Space Launch Complex 37 on Cape Canaveral Air Force Station in Florida. The ULA Delta IV Heavy rocket will launch an uncrewed Orion spacecraft on Exploration Flight Test-1. During the mission, Orion will travel farther into space than any human spacecraft has gone in more than 40 years. The data gathered during the flight will influence design decisions, validate existing computer models and innovative new approaches to space systems development, as well as reduce overall mission risks and costs for later Orion flights. Liftoff of Orion on the first flight test is planned for December 2014. Photo credit: NASA/Ben Smegelsky

KSC-2014-3680

NASA Image and Video Library

2014-08-04

CAPE CANAVERAL, Fla. – United Launch Alliance, or ULA, technicians monitor the progress as the Delta IV port booster is mated to the core booster inside the Horizontal Integration Facility at Space Launch Complex 37 on Cape Canaveral Air Force Station in Florida. The ULA Delta IV Heavy rocket will launch an uncrewed Orion spacecraft on Exploration Flight Test-1. During the mission, Orion will travel farther into space than any human spacecraft has gone in more than 40 years. The data gathered during the flight will influence design decisions, validate existing computer models and innovative new approaches to space systems development, as well as reduce overall mission risks and costs for later Orion flights. Liftoff of Orion on the first flight test is planned for December 2014. Photo credit: NASA/Ben Smegelsky

KSC-2014-3683

NASA Image and Video Library

2014-08-04

CAPE CANAVERAL, Fla. – United Launch Alliance, or ULA, technicians monitor the progress as the Delta IV port booster is mated to the core booster inside the Horizontal Integration Facility at Space Launch Complex 37 on Cape Canaveral Air Force Station in Florida. The ULA Delta IV Heavy rocket will launch an uncrewed Orion spacecraft on Exploration Flight Test-1. During the mission, Orion will travel farther into space than any human spacecraft has gone in more than 40 years. The data gathered during the flight will influence design decisions, validate existing computer models and innovative new approaches to space systems development, as well as reduce overall mission risks and costs for later Orion flights. Liftoff of Orion on the first flight test is planned for December 2014. Photo credit: NASA/Ben Smegelsky

KSC-2014-3908

NASA Image and Video Library

2014-09-12

CAPE CANAVERAL, Fla. – Inside the Horizontal Integration Facility at Space Launch Complex 37 at Cape Canaveral Air Force Station in Florida, a United Launch Alliance technician on a scissor lift monitors the progress as the second stage of a Delta IV Heavy rocket is mated to the central core booster of the three booster stages for the unpiloted Exploration Flight Test-1, or EFT-1. During the mission, Orion will travel farther into space than any human spacecraft has gone in more than 40 years. The data gathered during the flight will influence design decisions, validate existing computer models and innovative new approaches to space systems development, as well as reduce overall mission risks and costs for later Orion flights. Liftoff of Orion on the first flight test is planned for December 2014. Photo credit: NASA/Daniel Casper

KSC-2014-3678

NASA Image and Video Library

2014-08-04

CAPE CANAVERAL, Fla. – United Launch Alliance, or ULA, technicians monitor the progress as the Delta IV port booster is mated to the core booster inside the Horizontal Integration Facility at Space Launch Complex 37 on Cape Canaveral Air Force Station in Florida. The ULA Delta IV Heavy rocket will launch an uncrewed Orion spacecraft on Exploration Flight Test-1. During the mission, Orion will travel farther into space than any human spacecraft has gone in more than 40 years. The data gathered during the flight will influence design decisions, validate existing computer models and innovative new approaches to space systems development, as well as reduce overall mission risks and costs for later Orion flights. Liftoff of Orion on the first flight test is planned for December 2014. Photo credit: NASA/Ben Smegelsky

KSC-2014-3681

NASA Image and Video Library

2014-08-04

CAPE CANAVERAL, Fla. – United Launch Alliance, or ULA, technicians monitor the progress as the Delta IV port booster is mated to the core booster inside the Horizontal Integration Facility at Space Launch Complex 37 on Cape Canaveral Air Force Station in Florida. The ULA Delta IV Heavy rocket will launch an uncrewed Orion spacecraft on Exploration Flight Test-1. During the mission, Orion will travel farther into space than any human spacecraft has gone in more than 40 years. The data gathered during the flight will influence design decisions, validate existing computer models and innovative new approaches to space systems development, as well as reduce overall mission risks and costs for later Orion flights. Liftoff of Orion on the first flight test is planned for December 2014. Photo credit: NASA/Ben Smegelsky

KSC-2014-3677

NASA Image and Video Library

2014-08-04

CAPE CANAVERAL, Fla. – United Launch Alliance, or ULA, technicians monitor the progress as the Delta IV port booster is mated to the core booster inside the Horizontal Integration Facility at Space Launch Complex 37 on Cape Canaveral Air Force Station in Florida. The ULA Delta IV Heavy rocket will launch an uncrewed Orion spacecraft on Exploration Flight Test-1. During the mission, Orion will travel farther into space than any human spacecraft has gone in more than 40 years. The data gathered during the flight will influence design decisions, validate existing computer models and innovative new approaches to space systems development, as well as reduce overall mission risks and costs for later Orion flights. Liftoff of Orion on the first flight test is planned for December 2014. Photo credit: NASA/Ben Smegelsky

KSC-2014-3679

NASA Image and Video Library

2014-08-04

CAPE CANAVERAL, Fla. – United Launch Alliance, or ULA, technicians monitor the progress as the Delta IV port booster is mated to the core booster inside the Horizontal Integration Facility at Space Launch Complex 37 on Cape Canaveral Air Force Station in Florida. The ULA Delta IV Heavy rocket will launch an uncrewed Orion spacecraft on Exploration Flight Test-1. During the mission, Orion will travel farther into space than any human spacecraft has gone in more than 40 years. The data gathered during the flight will influence design decisions, validate existing computer models and innovative new approaches to space systems development, as well as reduce overall mission risks and costs for later Orion flights. Liftoff of Orion on the first flight test is planned for December 2014. Photo credit: NASA/Ben Smegelsky

KSC-2014-3906

NASA Image and Video Library

2014-09-12

CAPE CANAVERAL, Fla. – Inside the Horizontal Integration Facility at Space Launch Complex 37 at Cape Canaveral Air Force Station in Florida, United Launch Alliance technicians monitor the progress as the second stage of a Delta IV Heavy rocket is mated to the central core booster of the three booster stages for the unpiloted Exploration Flight Test-1, or EFT-1. During the mission, Orion will travel farther into space than any human spacecraft has gone in more than 40 years. The data gathered during the flight will influence design decisions, validate existing computer models and innovative new approaches to space systems development, as well as reduce overall mission risks and costs for later Orion flights. Liftoff of Orion on the first flight test is planned for December 2014. Photo credit: NASA/Daniel Casper

KSC-2014-3907

NASA Image and Video Library

2014-09-12

CAPE CANAVERAL, Fla. – Inside the Horizontal Integration Facility at Space Launch Complex 37 at Cape Canaveral Air Force Station in Florida, a United Launch Alliance technician on a scissor lift monitors the progress as the second stage of a Delta IV Heavy rocket is mated to the central core booster of the three booster stages for the unpiloted Exploration Flight Test-1, or EFT-1. During the mission, Orion will travel farther into space than any human spacecraft has gone in more than 40 years. The data gathered during the flight will influence design decisions, validate existing computer models and innovative new approaches to space systems development, as well as reduce overall mission risks and costs for later Orion flights. Liftoff of Orion on the first flight test is planned for December 2014. Photo credit: NASA/Daniel Casper

KSC-2014-3684

NASA Image and Video Library

2014-08-04

CAPE CANAVERAL, Fla. – United Launch Alliance, or ULA, technicians monitor the progress as the Delta IV port booster is mated to the core booster inside the Horizontal Integration Facility at Space Launch Complex 37 on Cape Canaveral Air Force Station in Florida. The ULA Delta IV Heavy rocket will launch an uncrewed Orion spacecraft on Exploration Flight Test-1. During the mission, Orion will travel farther into space than any human spacecraft has gone in more than 40 years. The data gathered during the flight will influence design decisions, validate existing computer models and innovative new approaches to space systems development, as well as reduce overall mission risks and costs for later Orion flights. Liftoff of Orion on the first flight test is planned for December 2014. Photo credit: NASA/Ben Smegelsky

KSC-2014-3687

NASA Image and Video Library

2014-08-04

CAPE CANAVERAL, Fla. – United Launch Alliance, or ULA, technicians monitor the progress as the Delta IV port booster is mated to the core booster inside the Horizontal Integration Facility at Space Launch Complex 37 on Cape Canaveral Air Force Station in Florida. The ULA Delta IV Heavy rocket will launch an uncrewed Orion spacecraft on Exploration Flight Test-1. During the mission, Orion will travel farther into space than any human spacecraft has gone in more than 40 years. The data gathered during the flight will influence design decisions, validate existing computer models and innovative new approaches to space systems development, as well as reduce overall mission risks and costs for later Orion flights. Liftoff of Orion on the first flight test is planned for December 2014. Photo credit: NASA/Ben Smegelsky

KSC-2009-2212

NASA Image and Video Library

2009-03-19

CAPE CANAVERAL, Fla. – The NASA Railroad makes the exchange with the Florida East Coast Railway cars carrying the booster segments for the Ares I-X test rocket. The four reusable motor segments and the nozzle exit cone, manufactured by the Ares I first-stage prime contractor Alliant Techsystems Inc., or ATK, departed Utah March 12 on the seven-day, cross-country trip to Florida. The segments will be delivered to the Rotation, Processing and Surge Facility for final processing and integration. The booster used for the Ares I-X launch is being modified by adding new forward structures and a fifth segment simulator. The motor is the final hardware needed for the rocket's upcoming test flight this summer. The stacking operations are scheduled to begin in the Vehicle Assembly Building in April. Photo credit: NASA/Kim Shiflett

Workers in the VAB test SRB cables on STS-98 solid rocket boosters

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. -- NASA and United Space Alliance SRB technicians hook up solid rocket booster cables to a Cirris Signature Touch 1 cable tester. From left are Loren Atkinson and Steve Swichkow, with NASA, and Jeff Suter, with USA. The SRB is part of Space Shuttle Atlantis, rolled back from Launch Pad 39A in order to conduct tests on the cables. A prior extensive evaluation of NASA'''s SRB cable inventory on the shelf revealed conductor damage in four (of about 200) cables. Shuttle managers decided to prove the integrity of the system tunnel cables already on Atlantis before launching. Workers are conducting inspections, making continuity checks and conducting X-ray analysis on the cables. The launch has been rescheduled no earlier than Feb. 6.

Workers in the VAB test SRB cables on STS-98 solid rocket boosters

NASA Technical Reports Server (NTRS)

2001-01-01

KENNEDY SPACE CENTER, Fla. -- In the Vehicle Assembly Building, United Space Alliance SRB technician Frank Meyer pulls cables out of the solid rocket booster system tunnel. Cable end covers are in a box near his feet. The SRB is part of Space Shuttle Atlantis, rolled back from Launch Pad 39A in order to conduct tests on the cables. A prior extensive evaluation of NASA'''s SRB cable inventory on the shelf revealed conductor damage in four (of about 200) cables. Shuttle managers decided to prove the integrity of the system tunnel cables already on Atlantis before launching. Workers are conducting inspections, making continuity checks and conducting X-ray analysis on the cables. The launch has been rescheduled no earlier than Feb. 6.

KSC-03PD-3163

NASA Technical Reports Server (NTRS)

2003-01-01

KENNEDY SPACE CENTER, FLA. A Kennedy Space Center technician walks towards the intersection of the crawlerway beside a crawler-transporter moving Mobile Launcher Platform (MLP) number 3, with a set of twin solid rocket boosters bolted atop, during the second engineering analysis vibration test on the crawler and MLP. The crawler is moving at various speeds up to 1 mph in an effort to achieve vibration data gathering goals as it leaves the VAB, travels toward Launch Pad 39A, and then returns. The boosters are braced at the top for stability. The primary purpose of these rollout tests is to gather data to develop future maintenance requirements on the transport equipment and the flight hardware. Various parts of the MLP and crawler transporter have been instrumented with vibration data collection equipment.

SRB/SLEEC (Solid Rocket Booster/Shingle Lap Extendible Exit Cone) feasibility study, volume 1

NASA Technical Reports Server (NTRS)

Baker, William H., Jr.

1986-01-01

A preliminary design and analysis was completed for a SLEEC (Shingle Lap Extendible Exit Cone) which could be incorporated on the Space Transportation System (STS) Solid Rocket Booster (SRB). Studies were completed which predicted weights and performance increases and development plans were prepared for the full-scale bench and static test of SLEEC. In conjunction with the design studies, a series of supporting analyses were performed to assure the validity and feasibility of performance, fabrication, cost, and reliability for the selected design. The feasibility and required amounts of bench, static firing, and flight tests considered necessary for the successful incorporation of SLEEC on the Shuttle SRBs were determined. Preliminary plans were completed which define both a follow on study effort and a development program.

Pressure-Equalizing Cradle for Booster Rocket Mounting

NASA Technical Reports Server (NTRS)

Rutan, Elbert L. (Inventor)

2015-01-01

A launch system and method improve the launch efficiency of a booster rocket and payload. A launch aircraft atop which the booster rocket is mounted in a cradle, is flown or towed to an elevation at which the booster rocket is released. The cradle provides for reduced structural requirements for the booster rocket by including a compressible layer, that may be provided by a plurality of gas or liquid-filled flexible chambers. The compressible layer contacts the booster rocket along most of the length of the booster rocket to distribute applied pressure, nearly eliminating bending loads. Distributing the pressure eliminates point loading conditions and bending moments that would otherwise be generated in the booster rocket structure during carrying. The chambers may be balloons distributed in rows and columns within the cradle or cylindrical chambers extending along a length of the cradle. The cradle may include a manifold communicating gas between chambers.

Factors Affecting Booster Seat Use.

PubMed

Aita-Levy, Jerussa; Henderson, Lauren

2016-10-01

Objective To identify general awareness of booster seats as well as reasons for use and nonuse in an urban pediatric emergency room. Methods A total of 100 questionnaires were completed consisting of 24 questions each. Questions included knowledge of booster seat guidelines, source of knowledge, awareness of risks, and confidence in booster seats. Afterward, participants were provided an educational handout. Results Majority of parents reported currently using or having used a booster seat. The most popular reason was to protect from injury (78%), and reason for nonuse was size (44%). Majority of parents agreed that motor vehicle crashes were the leading cause of death in children. However, 56% of parents prematurely transitioned child out of a booster seat. Only 20% reported learning about booster seats from their pediatrician. Conclusion Parents continue to transition their children prematurely from booster seats. Current state laws need revision as well as further education using simplified illustrated guidelines. © The Author(s) 2015.

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.

Pegasus Mated to B-52 Mothership - First Flight

NASA Image and Video Library

1989-11-09

The Pegasus air-launched space booster is carried aloft under the right wing of NASA's B-52 carrier aircraft on its first captive flight from the Dryden Flight Research Center, Edwards, California. The first of two scheduled captive flights was completed on November 9, 1989. Pegasus is used to launch satellites into low-earth orbits cheaply. In 1997, a Pegasus rocket booster was also modified to test a hypersonic experiment (PHYSX). An experimental "glove," installed on a section of its wing, housed hundreds of temperature and pressure sensors that sent hypersonic flight data to ground tracking facilities during the experiment’s flight.

Long-term antibody response and immunologic memory in children immunized with hepatitis B vaccine at birth.

PubMed

Saffar, M J; Rezai, M S

2004-12-01

Four hundred and fifty three healthy children immunized with a course of hepatitis B vaccine beginning at birth were tested at 10-11 years of age for persistence of anti-hepatitis B-S antigen antibody (anti-HBs); and responses of children without protective antibody to different doses of hepatitis B vaccine booster were evaluated. Although nearly 42% of them were not seroprotected, but most of boosted subjects (87.3%) retained robust immunologic memory and rapidly retained a protective anti-HBs antibody titer of at least 10 IU/L after booster vaccination.

SRB Environment Evaluation and Analysis. Volume 3: ASRB Plume Induced Environments

NASA Technical Reports Server (NTRS)

Bender, R. L.; Brown, J. R.; Reardon, J. E.; Everson, J.; Coons, L. W.; Stuckey, C. I.; Fulton, M. S.

1991-01-01

Contract NAS8-37891 was expanded in late 1989 to initiate analysis of Shuttle plume induced environments as a result of the substitution of the Advanced Solid Rocket Booster (ASRB) for the Redesigned Solid Rocket Booster (RSRB). To support this analysis, REMTECH became involved in subscale and full-scale solid rocket motor test programs which further expanded the scope of work. Later contract modifications included additional tasks to produce initial design cycle environments and to specify development flight instrumentation. Volume 3 of the final report describes these analyses and contains a summary of reports resulting from various studies.

Design, analysis, fabrication and test of the Space Shuttle solid rocket booster motor case

NASA Technical Reports Server (NTRS)

Kapp, J. R.

1978-01-01

The motor case used in the solid propellant booster for the Space Shuttle is unique in many respects, most of which are indigenous to size and special design requirements. The evolution of the case design from initial requirements to finished product is discussed, with increased emphasis of reuse capability, special design features, fracture mechanics and corrosion control. Case fabrication history and the resulting procedure are briefly reviewed with respect to material development, processing techniques and special problem areas. Case assembly, behavior and performance during the DM-1 static firing are reviewed, with appropriate comments and conclusions.

High explosive corner turning performance and the LANL Mushroom test

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

Hill, L.G.; Seitz, W.L.; Forest, C.A.

1997-09-01

The Mushroom test is designed to characterize the corner turning performance of a new generation of less insensitive booster explosives. The test is described in detail, and three corner turning figures-of-merit are examined using pure TATB (both Livermore`s Ultrafine and a Los Alamos research blend) and PBX9504 as examples.

Space Shuttle Project

NASA Image and Video Library

1978-04-21

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

KENNEDY SPACE CENTER, FLA. - Workers ride the rails along with a container enclosing a segment of a solid rocket booster being moved to the main track. Several segments are being returned to Utah for testing. The segments were part of the STS-114 stack. It is the first time actual flight segments that had been stacked for flight in the VAB are being returned for testing. They will undergo firing, which will enable inspectors to check the viability of the solid and verify the life expectancy for stacked segments.

NASA Image and Video Library

2004-01-30

KENNEDY SPACE CENTER, FLA. - Workers ride the rails along with a container enclosing a segment of a solid rocket booster being moved to the main track. Several segments are being returned to Utah for testing. The segments were part of the STS-114 stack. It is the first time actual flight segments that had been stacked for flight in the VAB are being returned for testing. They will undergo firing, which will enable inspectors to check the viability of the solid and verify the life expectancy for stacked segments.

KENNEDY SPACE CENTER, FLA. - The red NASA engine backs up with its cargo of containers in order to change tracks. The containers enclose segments of a solid rocket booster being returned to Utah for testing. The segments were part of the STS-114 stack. It is the first time actual flight segments that had been stacked for flight in the VAB are being returned for testing. They will undergo firing, which will enable inspectors to check the viability of the solid and verify the life expectancy for stacked segments.

NASA Image and Video Library

2004-01-30

KENNEDY SPACE CENTER, FLA. - The red NASA engine backs up with its cargo of containers in order to change tracks. The containers enclose segments of a solid rocket booster being returned to Utah for testing. The segments were part of the STS-114 stack. It is the first time actual flight segments that had been stacked for flight in the VAB are being returned for testing. They will undergo firing, which will enable inspectors to check the viability of the solid and verify the life expectancy for stacked segments.

KENNEDY SPACE CENTER, FLA. - The red NASA engine moves forward past the Vehicle Assembly Building with its cargo of containers enclosing segments of a solid rocket booster being returned to Utah for testing. The segments were part of the STS-114 stack. It is the first time actual flight segments that had been stacked for flight in the VAB are being returned for testing. They will undergo firing, which will enable inspectors to check the viability of the solid and verify the life expectancy for stacked segments.

NASA Image and Video Library

2004-01-30

KENNEDY SPACE CENTER, FLA. - The red NASA engine moves forward past the Vehicle Assembly Building with its cargo of containers enclosing segments of a solid rocket booster being returned to Utah for testing. The segments were part of the STS-114 stack. It is the first time actual flight segments that had been stacked for flight in the VAB are being returned for testing. They will undergo firing, which will enable inspectors to check the viability of the solid and verify the life expectancy for stacked segments.

Stress Corrosion Cracking and Fatigue Crack Growth Studies Pertinent to Spacecraft and Booster Pressure Vessels

NASA Technical Reports Server (NTRS)

Hall, L. R.; Finger, R. W.

1972-01-01

This experimental program was divided into two parts. The first part evaluated stress corrosion cracking in 2219-T87 aluminum and 5Al-2.5Sn (ELI) titanium alloy plate and weld metal. Both uniform height double cantilever beam and surface flawed specimens were tested in environments normally encountered during the fabrication and operation of pressure vessels in spacecraft and booster systems. The second part studied compatibility of material-environment combinations suitable for high energy upper stage propulsion systems. Surface flawed specimens having thicknesses representative of minimum gage fuel and oxidizer tanks were tested. Titanium alloys 5Al-2.5Sn (ELI), 6Al-4V annealed, and 6Al-4V STA were tested in both liquid and gaseous methane. Aluminum alloy 2219 in the T87 and T6E46 condition was tested in fluorine, a fluorine-oxygen mixture, and methane. Results were evaluated using modified linear elastic fracture mechanics parameters.

Long-term immunogenicity of an initial booster dose of an inactivated, Vero cell culture-derived Japanese encephalitis vaccine (JE-VC) and the safety and immunogenicity of a second JE-VC booster dose in children previously vaccinated with an inactivated, mouse brain-derived Japanese encephalitis vaccine.

PubMed

Yun, Ki Wook; Lee, Hoan Jong; Park, Ji Young; Cho, Hye-Kyung; Kim, Yae-Jean; Kim, Kyung-Hyo; Kim, Nam Hee; Hong, Young Jin; Kim, Dong Ho; Kim, Hwang Min; Cha, Sung-Ho

2018-03-07

This study was performed with the aim of determining the long-term immunogenicity of an inactivated, Vero cell culture-derived Japanese encephalitis (JE) vaccine (JE-VC) and an inactivated, mouse brain-derived JE vaccine (JE-MB) after the 1st booster dose at 2 years of age, as well as the safety and immunogenicity of the 2nd booster dose of JE-VC at 6 years of age, in children primed and given a 1st booster dose of either JE-VC or JE-MB. In this multicenter, open-label clinical trial, the study population consisted of healthy Korean children (aged 6 years) who participated in the previous JE vaccine trial. All subjects were subcutaneously vaccinated once for the booster immunization with Boryung Cell Culture Japanese Encephalitis Vaccine® (JE-VC). Approximately 4 years after the 1st booster dose of JE-VC, the seroprotection rate (SPR) and geometric mean titer (GMT) of the neutralizing antibody were 100% and 1113.8, respectively. In children primed and given a 1st booster dose of JE-MB, the SPR and GMT were 88.5% and 56.3, respectively. After the 2nd booster dose of JE-VC, all participants primed and given a 1st booster dose of either JE-MB or JE-VC were seroprotective against JE virus. The GMT of the neutralizing antibody was higher in children primed and given a 1st booster dose of JE-VC (8144.1) than in those primed and given a 1st booster dose of JE-MB (942.5) after the vaccination (p < 0.001). In addition, the 2nd booster dose of JE-VC showed a good safety profile with no serious vaccine-related adverse events. The 1st booster dose of JE-VC and JE-MB showed long-term immunogenicity of at least 4 years, and the 2nd booster dose of JE-VC showed a good safety and immunogenicity profile in children primed and given a 1st booster dose of either JE-VC or JE-MB. ClinicalTtrials.gov Identifier: NCT02532569. Copyright © 2018 Elsevier Ltd. All rights reserved.

KSC-08pd0736

NASA Image and Video Library

2008-03-12

KENNEDY SPACE CENTER, FLA. -- The Freedom Star, one of NASA's solid rocket booster retrieval ships, motors through Port Canaveral with a solid rocket booster alongside. The booster is from space shuttle Endeavour, which launched the STS-123 mission on March 11. The space shuttle’s solid rocket booster casings and associated flight hardware are recovered at sea. The boosters impact the Atlantic Ocean approximately seven minutes after liftoff. The splashdown area is a square of about 6 by 9 nautical miles located about 140 nautical miles downrange from the launch pad. The retrieval ships are stationed approximately 8 to 10 nautical miles from the impact area at the time of splashdown. As soon as the boosters enter the water, the ships accelerate to a speed of 15 knots and quickly close on the boosters, which they tow back to port. After transfer to a position alongside the ship, the booster will be towed to Hangar AF at Cape Canaveral Air Force Station. There, the expended boosters are disassembled, refurbished and reloaded with solid propellant for reuse. Photo credit: NASA/Jack Pfaller

KSC-08pd0741

NASA Image and Video Library

2008-03-12

KENNEDY SPACE CENTER, FLA. -- The Freedom Star, one of NASA's solid rocket booster retrieval ships, nears Hangar AF at Cape Canaveral Air Force Station with a solid rocket booster alongside. The booster is from space shuttle Endeavour, which launched the STS-123 mission on March 11. The space shuttle’s solid rocket booster casings and associated flight hardware are recovered at sea. The boosters impact the Atlantic Ocean approximately seven minutes after liftoff. The splashdown area is a square of about 6 by 9 nautical miles located about 140 nautical miles downrange from the launch pad. The retrieval ships are stationed approximately 8 to 10 nautical miles from the impact area at the time of splashdown. As soon as the boosters enter the water, the ships accelerate to a speed of 15 knots and quickly close on the boosters, which they tow back to port. After transfer to a position alongside the ship, the booster will be towed to Hangar AF at Cape Canaveral Air Force Station. There, the expended boosters are disassembled, refurbished and reloaded with solid propellant for reuse. Photo credit: NASA/Jack Pfaller

KSC-08pd0738

NASA Image and Video Library

2008-03-12

KENNEDY SPACE CENTER, FLA. -- The Freedom Star, one of NASA's solid rocket booster retrieval ships, crosses through the drawbridge over the Haulover Canal into the Banana River. The ship is towing a solid rocket booster alongside. The booster is from space shuttle Endeavour, which launched the STS-123 mission on March 11. The space shuttle’s solid rocket booster casings and associated flight hardware are recovered at sea. The boosters impact the Atlantic Ocean approximately seven minutes after liftoff. The splashdown area is a square of about 6 by 9 nautical miles located about 140 nautical miles downrange from the launch pad. The retrieval ships are stationed approximately 8 to 10 nautical miles from the impact area at the time of splashdown. As soon as the boosters enter the water, the ships accelerate to a speed of 15 knots and quickly close on the boosters, which they tow back to port. After transfer to a position alongside the ship, the booster will be towed to Hangar AF at Cape Canaveral Air Force Station. There, the expended boosters are disassembled, refurbished and reloaded with solid propellant for reuse. Photo credit: NASA/Jack Pfaller

KSC-08pd0740

NASA Image and Video Library

2008-03-12

KENNEDY SPACE CENTER, FLA. -- The Freedom Star, one of NASA's solid rocket booster retrieval ships, tows a solid rocket booster alongside, heading for Hangar AF at Cape Canaveral Air Force Station. The booster is from space shuttle Endeavour, which launched the STS-123 mission on March 11. The space shuttle’s solid rocket booster casings and associated flight hardware are recovered at sea. The boosters impact the Atlantic Ocean approximately seven minutes after liftoff. The splashdown area is a square of about 6 by 9 nautical miles located about 140 nautical miles downrange from the launch pad. The retrieval ships are stationed approximately 8 to 10 nautical miles from the impact area at the time of splashdown. As soon as the boosters enter the water, the ships accelerate to a speed of 15 knots and quickly close on the boosters, which they tow back to port. After transfer to a position alongside the ship, the booster will be towed to Hangar AF at Cape Canaveral Air Force Station. There, the expended boosters are disassembled, refurbished and reloaded with solid propellant for reuse. Photo credit: NASA/Jack Pfaller

KSC-08pd0737

NASA Image and Video Library

2008-03-12

KENNEDY SPACE CENTER, FLA. -- The Freedom Star, one of NASA's solid rocket booster retrieval ships, motors through Port Canaveral with a solid rocket booster alongside. The booster is from space shuttle Endeavour, which launched the STS-123 mission on March 11. The space shuttle’s solid rocket booster casings and associated flight hardware are recovered at sea. The boosters impact the Atlantic Ocean approximately seven minutes after liftoff. The splashdown area is a square of about 6 by 9 nautical miles located about 140 nautical miles downrange from the launch pad. The retrieval ships are stationed approximately 8 to 10 nautical miles from the impact area at the time of splashdown. As soon as the boosters enter the water, the ships accelerate to a speed of 15 knots and quickly close on the boosters, which they tow back to port. After transfer to a position alongside the ship, the booster will be towed to Hangar AF at Cape Canaveral Air Force Station. There, the expended boosters are disassembled, refurbished and reloaded with solid propellant for reuse. Photo credit: NASA/Jack Pfaller

Internal Flow Simulation of Enhanced Performance Solid Rocket Booster for the Space Transportation System

NASA Technical Reports Server (NTRS)

Ahmad, Rashid A.; McCool, Alex (Technical Monitor)

2001-01-01

An enhanced performance solid rocket booster concept for the space shuttle system has been proposed. The concept booster will have strong commonality with the existing, proven, reliable four-segment Space Shuttle Reusable Solid Rocket Motors (RSRM) with individual component design (nozzle, insulator, etc.) optimized for a five-segment configuration. Increased performance is desirable to further enhance safety/reliability and/or increase payload capability. Performance increase will be achieved by adding a fifth propellant segment to the current four-segment booster and opening the throat to accommodate the increased mass flow while maintaining current pressure levels. One development concept under consideration is the static test of a "standard" RSRM with a fifth propellant segment inserted and appropriate minimum motor modifications. Feasibility studies are being conducted to assess the potential for any significant departure in component performance/loading from the well-characterized RSRM. An area of concern is the aft motor (submerged nozzle inlet, aft dome, etc.) where the altered internal flow resulting from the performance enhancing features (25% increase in mass flow rate, higher Mach numbers, modified subsonic nozzle contour) may result in increased component erosion and char. To assess this issue and to define the minimum design changes required to successfully static test a fifth segment RSRM engineering test motor, internal flow studies have been initiated. Internal aero-thermal environments were quantified in terms of conventional convective heating and discrete phase alumina particle impact/concentration and accretion calculations via Computational Fluid Dynamics (CFD) simulation. Two sets of comparative CFD simulations of the RSRM and the five-segment (IBM) concept motor were conducted with CFD commercial code FLUENT. The first simulation involved a two-dimensional axi-symmetric model of the full motor, initial grain RSRM. The second set of analyses included three-dimensional models of the RSRM and FSM aft motors with four-degree vectored nozzles.

Finite element analysis of the Space Shuttle 2.5-inch frangible nut

NASA Technical Reports Server (NTRS)

McKinnis, Darin N.

1994-01-01

Finite element analysis of the Space Shuttle 2.5-inch frangible nut was conducted to improve understanding of the current design and proposed design changes to this explosively-actuated nut. The 2.5-inch frangible nut is used in two places to attach the aft end of the Space Shuttle Orbiter to the External Tank. Both 2.5-inch frangible nuts must function to complete safe separation. The 2.5-inch frangible nut contains two explosive boosters containing RDX explosive each capable of splitting the nut in half, on command from the Orbiter computers. To ensure separation, the boosters are designed to be redundant. The detonation of one booster is sufficient to split the nut in half. However, beginning in 1987 some production lots of 2.5-inch frangible nuts have demonstrated an inability to separate using only a single booster. The cause of the failure has been attributed to differences in the material properties and response of the Inconel 718 from which the 2.5-inch frangible nut is manufactured. Subsequent tests have resulted in design modifications of the boosters and frangible nut. Model development and initial analysis was conducted by Sandia National Laboratories (SNL) under funding from NASA Lyndon B. Johnson Space Center (NASA-JSC) starting in 1992. Modeling codes previously developed by SNL were transferred to NASA-JSC for further analysis on this and other devices. An explosive bolt with NASA Standard Detonator (NSD) charge, a 3/4-inch frangible nut, and the Super*Zip linear separation system are being modeled by NASA-JSC.

Kinematics and Shoulder Belt Position of Child Rear Seat Passengers during Vehicle Maneuvers

PubMed Central

Bohman, Katarina; Stockman, Isabelle; Jakobsson, Lotta; Osvalder, Anna-Lisa; Bostrom, Ola; Arbogast, Kristy B.

2011-01-01

Head impact to the seat back has been identified as one important injury causation scenario for seat belt restrained, head-injured children and previous research highlighted vehicle maneuvers prior to impact as possible contributing factors. The aim was to quantify kinematics of child occupants during swerving maneuvers focusing on the child’s lateral movement and seat belt position relative to the child’s shoulder. A study was conducted on a closed-circuit test track with 16 children aged 4–12, restrained in the rear seat of a modern passenger vehicle. A professional driving instructor drove at 50 km/h making sharp turns in a repeatable fashion, resulting in inboard motion of the children. The children were exposed to two turns in each of two restraint systems. Shorter children were on a booster or highback booster cushion. The taller children were seated on a booster cushion or with only a lap and shoulder seat belt. Four film cameras were fixed in the vehicle monitoring the child. Vehicle data were also collected. The seat belt slipped off the shoulder in 1 of 5 turns, varying by age and restraint type. Among shorter children, the belt slipped off in a majority of turns when seated on a booster cushion while the belt remained on the shoulder when seated on the highback booster cushion. Among taller children, the shoulder belt moved far laterally on the shoulder in half of the turns. This data provides valuable knowledge on possible pre-impact postures of children as a result of vehicle swerving maneuvers for a variety of restraint systems. PMID:22105379

KSC-2014-2552

NASA Image and Video Library

2014-05-07

CAPE CANAVERAL, Fla. -- A transporter for oversize loads carries the port booster for the United Launch Alliance Delta IV Heavy for Exploration Flight Test-1, or EFT-1, to Space Launch Complex 37 on Cape Canaveral Air Force Station after it was offloaded from the barge at the U.S. Army Outpost wharf at Port Canaveral in Florida. The booster will be transported to the Horizontal Integration Facility, or HIF, at the launch complex. The upper stage and spacecraft adapter arrived with the booster and were transported to the HIF on May 6. At the HIF, all three booster stages will be processed and checked out before being moved to the nearby launch pad and hoisted into position. The spacecraft adapter will connect Orion to the ULA Delta IV, and also will connect Orion to NASA's new rocket, the Space Launch System, on its first mission in 2017. During the EFT-1 mission, Orion will travel farther into space than any human spacecraft has gone in more than 40 years. The data gathered during the flight will influence design decisions, validate existing computer models and innovative new approaches to space systems development, as well as reduce overall mission risks and costs for later Orion flights. Liftoff of Orion on EFT-1 is planned for fall 2014. Photo credit: NASA/Kim Shiflett

KSC-2014-2554

NASA Image and Video Library

2014-05-07

CAPE CANAVERAL, Fla. -- A transporter for oversize loads carries the port booster for the United Launch Alliance Delta IV Heavy for Exploration Flight Test-1, or EFT-1, to Space Launch Complex 37 on Cape Canaveral Air Force Station after it was offloaded from the barge at the U.S. Army Outpost wharf at Port Canaveral in Florida. The booster will be transported to the Horizontal Integration Facility, or HIF, at the launch complex. The upper stage and spacecraft adapter arrived with the booster and were transported to the HIF on May 6. At the HIF, all three booster stages will be processed and checked out before being moved to the nearby launch pad and hoisted into position. The spacecraft adapter will connect Orion to the ULA Delta IV, and also will connect Orion to NASA's new rocket, the Space Launch System, on its first mission in 2017. During the EFT-1 mission, Orion will travel farther into space than any human spacecraft has gone in more than 40 years. The data gathered during the flight will influence design decisions, validate existing computer models and innovative new approaches to space systems development, as well as reduce overall mission risks and costs for later Orion flights. Liftoff of Orion on EFT-1 is planned for fall 2014. Photo credit: NASA/Kim Shiflett

KSC-2014-2434

NASA Image and Video Library

2014-05-06

CAPE CANAVERAL, Fla. -- The second stage, port booster and spacecraft adapter, the remaining stages for the United Launch Alliance Delta IV Heavy boosters for NASA’s upcoming Exploration Flight Test-1, or EFT-1, mission with the Orion spacecraft, have been transported in their containers to the Horizontal Integration Facility, or HIF, at Space Launch Complex 37 on Cape Canaveral Air Force Station in Florida. Inside the facility, technicians uncrate the port booster. The segments arrived by barge at the U.S. Army Outpost wharf at Port Canaveral. At the HIF, all three booster stages will be processed and checked out before being moved to the nearby launch pad and hoisted into position. The spacecraft adapter will connect Orion to the ULA Delta IV, and also will connect Orion to NASA's new rocket, the Space Launch System, on its first mission in 2017. During the EFT-1 mission, Orion will travel farther into space than any human spacecraft has gone in more than 40 years. The data gathered during the flight will influence design decisions, validate existing computer models and innovative new approaches to space systems development, as well as reduce overall mission risks and costs for later Orion flights. Liftoff of Orion on EFT-1 is planned for fall 2014. Photo credit: NASA/Kim Shiflett

KSC-2014-2553

NASA Image and Video Library

2014-05-07

CAPE CANAVERAL, Fla. -- A transporter for oversize loads carries the port booster for the United Launch Alliance Delta IV Heavy for Exploration Flight Test-1, or EFT-1, to Space Launch Complex 37 on Cape Canaveral Air Force Station after it was offloaded from the barge at the U.S. Army Outpost wharf at Port Canaveral in Florida. The booster will be transported to the Horizontal Integration Facility, or HIF, at the launch complex. The upper stage and spacecraft adapter arrived with the booster and were transported to the HIF on May 6. At the HIF, all three booster stages will be processed and checked out before being moved to the nearby launch pad and hoisted into position. The spacecraft adapter will connect Orion to the ULA Delta IV, and also will connect Orion to NASA's new rocket, the Space Launch System, on its first mission in 2017. During the EFT-1 mission, Orion will travel farther into space than any human spacecraft has gone in more than 40 years. The data gathered during the flight will influence design decisions, validate existing computer models and innovative new approaches to space systems development, as well as reduce overall mission risks and costs for later Orion flights. Liftoff of Orion on EFT-1 is planned for fall 2014. Photo credit: NASA/Kim Shiflett

KSC-2014-2555

NASA Image and Video Library

2014-05-07

CAPE CANAVERAL, Fla. -- A transporter for oversize loads carries the port booster for the United Launch Alliance Delta IV Heavy for Exploration Flight Test-1, or EFT-1, to Space Launch Complex 37 on Cape Canaveral Air Force Station after it was offloaded from the barge at the U.S. Army Outpost wharf at Port Canaveral in Florida. The booster will be transported to the Horizontal Integration Facility, or HIF, at the launch complex. The upper stage and spacecraft adapter arrived with the booster and were transported to the HIF on May 6. At the HIF, all three booster stages will be processed and checked out before being moved to the nearby launch pad and hoisted into position. The spacecraft adapter will connect Orion to the ULA Delta IV, and also will connect Orion to NASA's new rocket, the Space Launch System, on its first mission in 2017. During the EFT-1 mission, Orion will travel farther into space than any human spacecraft has gone in more than 40 years. The data gathered during the flight will influence design decisions, validate existing computer models and innovative new approaches to space systems development, as well as reduce overall mission risks and costs for later Orion flights. Liftoff of Orion on EFT-1 is planned for fall 2014. Photo credit: NASA/Kim Shiflett

Space Launch System NASA Research Announcement Advanced Booster Engineering Demonstration and/or Risk Reduction

NASA Technical Reports Server (NTRS)

Crumbly, Christopher M.; Craig, Kellie D.

2011-01-01

The intent of the Advanced Booster Engineering Demonstration and/or Risk Reduction (ABEDRR) effort is to: (1) Reduce risks leading to an affordable Advanced Booster that meets the evolved capabilities of SLS (2) Enable competition by mitigating targeted Advanced Booster risks to enhance SLS affordability. Key Concepts (1) Offerors must propose an Advanced Booster concept that meets SLS Program requirements (2) Engineering Demonstration and/or Risk Reduction must relate to the Offeror s Advanced Booster concept (3) NASA Research Announcement (NRA) will not be prescriptive in defining Engineering Demonstration and/or Risk Reduction

KSC-08pd3731

NASA Image and Video Library

2008-11-19

CAPE CANAVERAL, Fla. – NASA's Solid Rocket Booster Retrieval Ship Freedom Star arrives at the dock at Hangar AF, Cape Canaveral Air Force Station in Florida, with a spent solid rocket booster alongside. The booster is from space shuttle Endeavour's launch Nov. 14 on mission STS-126. The space shuttle’s solid rocket booster casings and associated flight hardware are recovered at sea. The boosters impact the Atlantic Ocean approximately seven minutes after liftoff. The splashdown area is a square of about six by nine nautical miles located about 140 nautical miles downrange from the launch pad. The retrieval ships are stationed approximately 8 to 10 nautical miles from the impact area at the time of splashdown. As soon as the boosters enter the water, the ships accelerate to a speed of 15 knots and quickly close on the boosters. The pilot chutes and main parachutes are the first items to be brought on board. With the chutes and frustum recovered, attention turns to the boosters. The ship’s tow line is connected and the booster is returned to the Port and, after transfer to a position alongside the ship, to Hangar AF. There, the expended boosters are disassembled, refurbished and reloaded with solid propellant for reuse. Photo credit: NASA/Kim Shiflett

KSC-08pd0263

NASA Image and Video Library

2008-02-10

KENNEDY SPACE CENTER, FLA. -- The solid rocket booster retrieval ship Freedom Star is temporarily docked at Port Canaveral while the booster it was towing is moved alongside for the remainder of the trip upriver to Cape Canaveral Air Force Station. Freedom Star retrieved the booster after the launch of space shuttle Atlantis' STS-122 mission. The space shuttle's solid rocket booster casings and associated flight hardware are recovered at sea. The boosters impact the Atlantic Ocean approximately seven minutes after liftoff. The splashdown area is a square of about 6 by 9 nautical miles located about 140 nautical miles downrange from the launch pad. The retrieval ships are stationed approximately 8 to 10 nautical miles from the impact area at the time of splashdown. As soon as the boosters enter the water, the ships accelerate to a speed of 15 knots and quickly close on the boosters. The pilot chutes and main parachutes are the first items to be brought on board. With the chutes and frustum recovered, attention turns to the boosters. The ship's tow line is connected and the booster is returned to the Port and, after transfer to a position alongside the ship, to Hangar AF at Cape Canaveral Air Force Station. There, the expended boosters are disassembled, refurbished and reloaded with solid propellant for reuse. Photo credit: NASA/Jack Pfaller

KSC-08pd0262

NASA Image and Video Library

2008-02-10

KENNEDY SPACE CENTER, FLA. -- The solid rocket booster retrieval ship Freedom Star is temporarily docked at Port Canaveral while the booster it was towing is moved alongside for the remainder of the trip upriver to Cape Canaveral Air Force Station. Freedom Star retrieved the booster after the launch of space shuttle Atlantis' STS-122 mission. The space shuttle's solid rocket booster casings and associated flight hardware are recovered at sea. The boosters impact the Atlantic Ocean approximately seven minutes after liftoff. The splashdown area is a square of about 6 by 9 nautical miles located about 140 nautical miles downrange from the launch pad. The retrieval ships are stationed approximately 8 to 10 nautical miles from the impact area at the time of splashdown. As soon as the boosters enter the water, the ships accelerate to a speed of 15 knots and quickly close on the boosters. The pilot chutes and main parachutes are the first items to be brought on board. With the chutes and frustum recovered, attention turns to the boosters. The ship's tow line is connected and the booster is returned to the Port and, after transfer to a position alongside the ship, to Hangar AF at Cape Canaveral Air Force Station. There, the expended boosters are disassembled, refurbished and reloaded with solid propellant for reuse. Photo credit: NASA/Jack Pfaller

Immunogenicity and Safety of Primary and Booster Vaccinations of a Fully Liquid DTaP-IPV-HB-PRP-T Hexavalent Vaccine in Healthy Infants and Toddlers in Germany and the Czech Republic.

PubMed

Prymula, Roman; Kieninger, Dorothee; Feroldi, Emmanuel; Jordanov, Emilia; B'Chir, Siham; DaCosta, Xavier

2018-05-14

To support a fully liquid, diphtheria (D)-tetanus (T)-acellular pertussis (aP)-inactivated poliovirus (IPV)-hepatitis B (HB)-Haemophilus influenzae b (PRP-T) vaccine in Europe using a 2, 3, 4 month primary series and a booster at 11 to 15 months of age. Phase III, randomized, observer-blind studies in Germany and the Czech Republic. Participants who had not received HB vaccine were randomized to a 2, 3, 4 month primary series of DTaP-IPV-HB-PRP-T (Group 1; N=266) or a reconstituted DTaPHB-IPV//PRP-T comparator (Group 2; N=263) and a booster of the same vaccine. Pneumococcal vaccine (PCV13) and rotavirus vaccine (RV) were coadministered at 2, 3, 4 months and the booster was coadministered with PCV13. Non-inferiority (Group 1 versus Group 2) was tested post-primary series for seroprotection rates (anti-HB and anti-PRP) and vaccine response rates (anti-PT and anti-FHA). Safety was assessed by parental reports. Non-inferiority was demonstrated with the lower bound of the 95% CI for the difference (Group 1-Group 2) being >-10% for each comparison. Primary series immune responses were high for all antigens and similar in each group. Pre-booster antibody persistence was good and there was a strong anamnestic response, both being similar for the investigational and control vaccines. Responses to PCV13 and RV were similar in each group. There were no safety concerns. These data support the use of the DTaP-IPV-HB-PRP-T vaccine in a 2, 3, 4 month schedule without a birth dose of HB vaccine, with a booster dose in the second year of life administered with routine childhood vaccines.

[Current status of hepatitis B immunization and strengthened immune memory among first-year middle school students in Tianjin].

PubMed

Shan, Ai-lan; Li, Chao; Wu, Wei-shen; He, Hai-yan; Liu, Yong; Liu, Peng; Xie, Xiao-hua

2010-06-01

To investigate the immunization status of hepatitis B vaccine who were inoculated at birth, HBV infections and the vaccine booster effect in the first-year middle school students (12 - 14 years old). A cluster, stratified simplified random sampling method was administrated. The sample size was at least 218, which was calculated by Epi Info 3.3.2 software at 53% the minimum acceptable anti-HBs positive rate and 95% confidence level. A total of 250 and 236 students participated in the infection status and booster immunization effects investigation. The HBsAg, anti-HBs and anti-HBc IgG were detected by Enzyme-linked immunosorbent assay (ELISA). HBV DNA was detected by fluorescence quantitative PCR, and the diagnostic test kit were produced respectively by ABBOTT, Diasorin and Beijing Wantai Biological Pharmacy Enterprise Co. For the immunization status before booster: the positive rate of anti-HBs was 62.80% (157/250), the GMT was 73.79 IU/L; the currently HBV infection rate (HBsAg and anti-HBc positive) was 2.80% (7/250). After injection, the anti-HBs positive rate was 94.92% (224/236). Compared with the before booster results, the significant difference was observed (χ(2) = 73.92, P = 0.00). The GMT was 521.15 IU/L, comparing with the before booster results, there was significant difference (t = 15.98, P = 0.00). The anti-HBs conversion rate (from negative to positive) was 91.86% (79/86) after immune-enhancement; of which, 11 students got the second dose of booster vaccine who are no-responders after first injection, in addition 8 students got the anti-HBs. It is an effective method to put the first-year middle school students into the immune-enhancement program, so as to improve the immunization memory effect and avoid the loss of protective antibodies.

Long-term efficacy of Internet-based cognitive behavior therapy for obsessive-compulsive disorder with or without booster: a randomized controlled trial.

PubMed

Andersson, E; Steneby, S; Karlsson, K; Ljótsson, B; Hedman, E; Enander, J; Kaldo, V; Andersson, G; Lindefors, N; Rück, C

2014-10-01

As relapse after completed cognitive behavior therapy (CBT) for obsessive-compulsive disorder (OCD) is common, many treatment protocols include booster programs to improve the long-term effects. However, the effects of booster programs are not well studied. In this study, we investigated the long-term efficacy of Internet-based CBT (ICBT) with therapist support for OCD with or without an Internet-based booster program. A total of 101 participants were included in the long-term follow-up analysis of ICBT. Of these, 93 were randomized to a booster program or no booster program. Outcome assessments were collected at 4, 7, 12 and 24 months after receiving ICBT. The entire sample had sustained long-term effects from pre-treatment to all follow-up assessments, with large within-group effect sizes (Cohen's d = 1.58-2.09). The booster group had a significant mean reduction in OCD symptoms compared to the control condition from booster baseline (4 months) to 7 months, but not at 12 or 24 months. Participants in the booster group improved significantly in terms of general functioning at 7, 12 and 24 months, and had fewer relapses. Kaplan-Meier analysis also indicated a significantly slower relapse rate in the booster group. The results suggest that ICBT has sustained long-term effects and that adding an Internet-based booster program can further improve long-term outcome and prevent relapse for some OCD patients.

Space Shuttle Projects

NASA Image and Video Library

1975-01-01

As early as September 1972, the Marshall Space Flight Center arnounced plans for a series of 20 water-entry simulation tests with a solid-fueled rocket casing assembly. The tests would provide valuable data for assessment of solid rocket booster parachute water recovery and aid in preliminary solid rocket motor design.

Space Shuttle Propulsion System Reliability

NASA Technical Reports Server (NTRS)

Welzyn, Ken; VanHooser, Katherine; Moore, Dennis; Wood, David

2011-01-01

This session includes the following sessions: (1) External Tank (ET) System Reliability and Lessons, (2) Space Shuttle Main Engine (SSME), Reliability Validated by a Million Seconds of Testing, (3) Reusable Solid Rocket Motor (RSRM) Reliability via Process Control, and (4) Solid Rocket Booster (SRB) Reliability via Acceptance and Testing.

Design of the transfer line from booster to storage ring at 3 GeV

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

Bayar, C., E-mail: cafer.bayar@cern.ch; Ciftci, A. K., E-mail: abbas.kenan.ciftci@cern.ch

The Synchrotron Booster Ring accelerates the e-beam up to 3 GeV and particles are transported from booster to storage ring by transfer line. In this study, two options are considered, the first one is a long booster which shares the same tunnel with storage ring and the second one is a compact booster. As a result, two transfer line are designed based on booster options. The optical design is constrained by the e-beam Twiss parameters entering and leaving the transfer line. Twiss parameters in the extraction point of booster are used for the entrance of transfer line and are matchedmore » in the exit of transfer line to the injection point of the storage ring.« less

Expendable second stage reusable space shuttle booster. Volume 2: Technical summary. Book 3: Booster vehicle modifications and ground systems definition

NASA Technical Reports Server (NTRS)

1972-01-01

A definition of the expendable second stage and space shuttle booster separation system is presented. Modifications required on the reusable booster for expendable second stage/payload flight and the ground systems needed to operate the expendable second stage in conjuction with the space shuttle booster are described. The safety, reliability, and quality assurance program is explained. Launch complex operations and services are analyzed.

Space Shuttle Project

NASA Image and Video Library

1988-01-01

Marshall Space Flight Center workers install Structural Test Article Number Three (STA-3) into a Center test facility. From December 1987 to April 1988, STA-3 (a test model of the Redesigned Solid Rocket Motor) underwent a series of six tests at the Marshall Center designed to demonstrate the structural strength of the Space Shuttle's Solid Rocket Booster, redesigned after the January 1986 Challenger accident.

Executive Summary of Propulsion on the Orion Abort Flight-Test Vehicles

NASA Technical Reports Server (NTRS)

Jones, Daniel S.; Brooks, Syri J.; Barnes, Marvin W.; McCauley, Rachel J.; Wall, Terry M.; Reed, Brian D.; Duncan, C. Miguel

2012-01-01

The National Aeronautics and Space Administration Orion Flight Test Office was tasked with conducting a series of flight tests in several launch abort scenarios to certify that the Orion Launch Abort System is capable of delivering astronauts aboard the Orion Crew Module to a safe environment, away from a failed booster. The first of this series was the Orion Pad Abort 1 Flight-Test Vehicle, which was successfully flown on May 6, 2010 at the White Sands Missile Range in New Mexico. This report provides a brief overview of the three propulsive subsystems used on the Pad Abort 1 Flight-Test Vehicle. An overview of the propulsive systems originally planned for future flight-test vehicles is also provided, which also includes the cold gas Reaction Control System within the Crew Module, and the Peacekeeper first stage rocket motor encased within the Abort Test Booster aeroshell. Although the Constellation program has been cancelled and the operational role of the Orion spacecraft has significantly evolved, lessons learned from Pad Abort 1 and the other flight-test vehicles could certainly contribute to the vehicle architecture of many future human-rated space launch vehicles