Megasite Management Tool (mmt): a Decision Support System Built Using Mapwindow Activex Control

NASA Astrophysics Data System (ADS)

Pulsani, B. R.

2017-11-01

Megasite Management Tool (MMT) is planning and evaluation software for contaminated sites. Using different statistical modules, MMT produces maps which help decision makers in rehabilitating contaminated sites. The input data used by MMT is of geographic nature and exists as shapefile and raster format. As MMT is built using simple windows forms application, the objective of the study was to find a way to visualize geographic data and to allow the user to edit its attribute information. Therefore, the application requirement was to find GIS libraries which offer capabilities such as (1) map viewer with navigation tools (2) library to read/write geographic data and (3) software which allows free distribution of the developed components. A research on these requirements led to the discovery of MapWindow ActiveX components which not only offered these capabilities but also provided free and open source licensing options for redistribution. Although considerable amount of reports and publications exist on MMT, the major contribution provided by MapWindow libraries have been under played. The current study emphasises upon the contribution and advantages MapWindow ActiveX provides for incorporating GIS functionality to an already existing application. Similar components for other languages have also been reviewed.

Making Metadata Better with CMR and MMT

NASA Technical Reports Server (NTRS)

Gilman, Jason Arthur; Shum, Dana

2016-01-01

Ensuring complete, consistent and high quality metadata is a challenge for metadata providers and curators. The CMR and MMT systems provide providers and curators options to build in metadata quality from the start and also assess and improve the quality of already existing metadata.

Validation of Manual Muscle Testing and a Subset of Eight Muscles (MMT8) for Adult and Juvenile Idiopathic Inflammatory Myopathies

PubMed Central

Rider, Lisa G.; Koziol, Deloris; Giannini, Edward H.; Jain, Minal S.; Smith, Michaele R.; Whitney-Mahoney, Kristi; Feldman, Brian M.; Wright, Susan J.; Lindsley, Carol B.; Pachman, Lauren M.; Villalba, Maria L.; Lovell, Daniel J.; Bowyer, Suzanne L.; Plotz, Paul H.; Miller, Frederick W.; Hicks, Jeanne E.

2010-01-01

Objective To validate manual muscle testing (MMT) for strength assessment in juvenile and adult dermatomyositis (DM) and polymyositis (PM). Methods Seventy-three children and 45 adult DM/PM patients were assessed at baseline and reevaluated 6–9 months later. We compared Total MMT (a group of 24 proximal, distal, and axial muscles) and Proximal MMT (7 proximal muscle groups) tested bilaterally on a 0–10 scale with 144 subsets of six and 96 subsets of eight muscle groups tested unilaterally. Expert consensus was used to rank the best abbreviated MMT subsets for face validity and ease of assessment. Results The Total, Proximal and best MMT subsets had excellent internal reliability (rs:Total MMT 0.91–0.98), and consistency (Cronbach’s α 0.78–0.97). Inter- and intra-rater reliability were acceptable (Kendall’s W 0.68–0.76; rs 0.84–0.95). MMT subset scores correlated highly with Total and Proximal MMT scores and with the Childhood Myositis Assessment Scale, and correlated moderately with physician global activity, functional disability, magnetic resonance imaging, axial and distal MMT scores and, in adults, with creatine kinase. The standardized response mean for Total MMT was 0.56 in juveniles and 0.75 in adults. Consensus was reached to use a subset of eight muscles (neck flexors, deltoids, biceps, wrist extensors, gluteus maximus and medius, quadriceps and ankle dorsiflexors) that performed as well as the Total and Proximal MMT, and had good face validity and ease of assessment. Conclusions These findings aid in standardizing the use of MMT for assessing strength as an outcome measure for myositis. PMID:20391500

Cancellations of (helicopter-transported) mobile medical team dispatches in the Netherlands.

PubMed

Giannakopoulos, Georgios F; Lubbers, Wouter D; Christiaans, Herman M T; van Exter, Pieternel; Bet, Piet; Hugen, Paul J C; Innemee, Gerard; Schubert, Edo; de Lange-Klerk, Elly S M; Goslings, J Carel; Jukema, Gerrolt N

2010-08-01

The trauma centre of the Trauma Center Region North-West Netherlands (TRNWN) has consensus criteria for Mobile Medical Team (MMT) scene dispatch. The MMT can be dispatched by the EMS-dispatch centre or by the on-scene ambulance crew and is transported by helicopter or ground transport. Although much attention has been paid to improve the dispatch criteria, the MMT is often cancelled after being dispatched. The aim of this study was to assess the cancellation rate and the noncompliant dispatches of our MMT and to identify factors associated with this form of primary overtriage. By retrospective analysis of all MMT dispatches in the period from 1 July 2006 till 31 December 2006 using chart review, we conducted a consecutive case review of 605 dispatches. Four hundred and sixty seven of these were included for our study, collecting data related to prehospital triage, patient's condition on-scene and hospital course. Average age was 35.9 years; the majority of the patients were male (65.3%). Four hundred and thirty patients were victims of trauma, sustaining injuries in most cases from blunt trauma (89.3%). After being dispatched, the MMT was cancelled 203 times (43.5%). Statistically significant differences between assists and cancellations were found for overall mortality, mean RTS, GCS and ISS, mean hospitalization, length and amount of ICU admissions (p < 0.001). All dispatches were evaluated by using the MMT-dispatch criteria and mission appropriateness criteria. Almost 26% of all dispatches were neither appropriate, nor met the dispatch criteria. Fourteen missions were appropriate, but did not meet the dispatch criteria. The remaining 318 dispatches had met the dispatch criteria, of which 135 (30.3%) were also appropriate. The calculated additional costs of the cancelled dispatches summed up to a total of 34,448 euro, amounting to 2.2% of the total MMT costs during the study period. In our trauma system, the MMT dispatches are involved with high rates of

The U.S. Women's World Cup Soccer Team arrives to view the STS-93 launch

NASA Technical Reports Server (NTRS)

1999-01-01

Members of the U.S. Women's World Cup Soccer Team are greeted by NASA Administrator Daniel S. Goldin as they disembark from a plane at the Skid Strip at Cape Canaveral Air Station. They arrived with First Lady Hillary Rodham Clinton to view the launch of Space Shuttle mission STS-93 scheduled for 12:36 a.m. EDT July 20. Much attention has been generated over the launch due to Commander Eileen M. Collins, the first woman to serve as commander of a Shuttle mission. The primary payload of the five- day mission is the release of the Chandra X-ray Observatory, which will allow scientists from around the world to study some of the most distant, powerful and dynamic objects in the universe.

Mars Pathfinder Status at Launch

NASA Technical Reports Server (NTRS)

Spear, A. J.; Freeman, Delma C., Jr.; Braun, Robert D.

1996-01-01

The Mars Pathfinder Flight System is in final test, assembly and launch preparations at the Kennedy Space Center in Florida. Launch is scheduled for 2 Dec. 1996. The Flight System development, in particular the Entry, Descent, and Landing (EDL) system, was a major team effort involving JPL, other NASA centers and industry. This paper provides a summary Mars Pathfinder description and status at launch. In addition, a section by NASA's Langley Research Center, a key EDL contributor, is provided on their support to Mars Pathfinder. This section is included as an example of the work performed by Pathfinder team members outside JPL.

Toward first light for the 6.5-m MMT Telescope

NASA Astrophysics Data System (ADS)

West, Steve C.; Callahan, Shawn; Chaffee, Frederic H.; Davison, Warren B.; Derigne, S. T.; Fabricant, Daniel G.; Foltz, Craig B.; Hill, John M.; Nagel, Robert H.; Poyner, Anthony D.; Williams, Joseph T.

1997-03-01

Operated by the Multiple Mirror Telescope Observatory (MMTO), the multiple mirror telescope (MMT) is funded jointly by the Smithsonian Institution (SAO) and the University of Arizona (UA). The two organizations equally share observing time on the telescope. The MMT was dedicated in May 1979, and is located on the summit of Mt. Hopkins (at an altitude of 2.6 km), 64 km south of Tucson, Arizona, at the Smithsonian Institution's Fred Lawrence Whipple Observatory (FLWO). As a result of advances in the technology at the Steward Observatory Mirror Laboratory for the casting of large and fast borosilicate honeycomb astronomical primary mirrors, in 1987 it was decided to convert the MMT from its six 1.8 m mirror array (effective aperture of 4.5 m) to a single 6.5 m diameter primary mirror telescope. This conversion will more than double the light gathering capacity, and will by design, increase the angular field of view by a factor of 15. Because the site is already developed and the existing building and mount will be used with some modification, the conversion will be accomplished for only about $20 million. During 1995, several major technical milestones were reached: (1) the existing building was modified, (2) the major steel telescope structures were fabricated, and (3) the mirror blank was diamond wheel ground (generated). All major mechanical hardware required to affect the conversion is now nearly in hand. Once the primary mirror is polished and lab-tested on its support system, the six-mirror MMT will be taken out of service and the conversion process begun. We anticipate that a 6 - 12 month period will be required to rebuild the telescope, install its optics and achieve f/9 first light, now projected to occur in early 1998. The f/5.4 and f/15 implementation will then follow. We provide a qualitative and brief update of project progress.

Launch Vehicle Operations Simulator

NASA Technical Reports Server (NTRS)

Blackledge, J. W.

1974-01-01

The Saturn Launch Vehicle Operations Simulator (LVOS) was developed for NASA at Kennedy Space Center. LVOS simulates the Saturn launch vehicle and its ground support equipment. The simulator was intended primarily to be used as a launch crew trainer but it is also being used for test procedure and software validation. A NASA/contractor team of engineers and programmers implemented the simulator after the Apollo XI lunar landing during the low activity periods between launches.

STS-135 Atlantis Launch

NASA Image and Video Library

2011-07-07

NASA Photographer Kim Shiflett, left, and Videographer Glenn Benson capture a group photo of the launch team in Firing Room Four of the NASA Kennedy Space Center Launch Control Center (LCC) shortly after the space shuttle Atlantis, STS-135, launched on Friday, July 8, 2011, in Cape Canaveral, Fla. The launch of Atlantis is the final flight of the shuttle program, a 12-day mission to the International Space Station. Photo Credit: (NASA/Bill Ingalls)

SLI Artist `s Launch Concept

NASA Technical Reports Server (NTRS)

2002-01-01

NASA's Marshall Space Flight Center in Huntsville, Alabama, manages the Space Launch Initiative (SLI), NASA's priority developmental program focused on empowering America's leadership in space. SLI includes commercial, higher education and defense partnerships and contracts to offer widespread participation in both the risk and success of developing our nation's next-generation reusable launch vehicle. This photo depicts an artist's concept of a future second-generation launch vehicle during launch. For SLI, architecture definition includes all components of the next-generation reusable launch system: Earth-to-orbit vehicles (the Space Shuttle is the first generation earth-to-orbit vehicle), crew transfer vehicles, transfer stages, ground processing systems, flight operations systems, and development of business case strategies. Three contractor teams have each been funded to develop potential second generation reusable launch system architectures: The Boeing Company of Seal Beach, California; Lockheed Martin Corporation of Denver, Colorado along with a team including Northrop Grumman of El Segundo, California; and Orbital Sciences Corporation of Dulles, Virginia.

Students Participate in Rocket Launch Project

NASA Technical Reports Server (NTRS)

2002-01-01

Filled with anticipation, students from two local universities, the University of Alabama in Huntsville (UAH), and Alabama Agricultural Mechanical University (AM), counted down to launch the rockets they designed and built at the Army test site on Redstone Arsenal in Huntsville, Alabama. The projected two-mile high launch culminated more than a year's work and demonstrated the student team's ability to meet the challenge set by the Marshall Space Flight Center's (MSFC) Student Launch Initiative (SLI) program to apply science and math to experience, judgment, and common sense, and proved to NASA officials that they have successfully built reusable launch vehicles (RLVs), another challenge set by NASA's SLI program. MSFC's SLI program is an educational effort that aims to motivate students to pursue careers in science, math, and engineering. It provides the students with hands-on, practical aerospace experience. In this picture, a student from AM and his mentor install their payload into the launch vehicle which was built by the team of UAH students. The scientific payload, developed and built by the team of AM students, measured the amount of hydrogen produced during electroplating with nickel in a brief period of micrgravity.

Fabrication of durable fluorine-free superhydrophobic polyethersulfone (PES) composite coating enhanced by assembled MMT-SiO2 nanoparticles

NASA Astrophysics Data System (ADS)

Zhang, Xiguang; Wang, Huaiyuan; Liu, Zhanjian; Zhu, Yixing; Wu, Shiqi; Wang, Chijia; Zhu, Yanji

2017-02-01

A durable fluorine-free polyethersulfone (PES) superhydrophobic composite coating with excellent wear-resistant and anti-corrosion properties has been successfully fabricated by combining sol-gel and spray technology. The robust micro/nano-structures of the prepared surface were established by introducing binary montmorillonite-silica (MMT-SiO2) assembled composite particles, which were formed by in-situ growth of SiO2 on MMT surfaces via sol-gel. Combined with the low surface energy of amino silicon oil (APDMS), the fluorine-free superhydrophoic PES coating was obtained with high water contact angle 156.1 ± 1.1° and low sliding angle 4.8 ± 0.7°. The anti-wear of the final PES/APDMS/MMT-SiO2 superhydrophobic coating can reach up to 60,100 cycles, which is outdistancing the pure PES coating (6800 cycles) and the PES/MMT/SiO2 coating prepared by simple physical mixture (18,200 cycles). The enhanced wear resistance property can be mainly attributed to the lubrication performance of APDMS and stable interface bonding force between the MMT surface and SiO2. Simultaneously, potentiodynamic polarization curves and electrochemical impedance spectroscopy exhibited the outstanding anti-corrosion property of PES/APDMS/MMT-SiO2 composite coating, with low corrosion current (1.6 × 10-10 A/cm2) and high protection efficiency (99.999%) even after 30 d immersion process. These test results show that this durable superhydrophobic PES composite coating can be hopefully to provide the possibility of industrial application.

Comparison of In Situ Polymerization and Solution-Dispersion Techniques in the Preparation of Polyimide/Montmorillonite (MMT) Nanocomposites

PubMed Central

Ahmad, Mansor Bin; Gharayebi, Yadollah; Salit, Mohd. Sapuan; Hussein, Mohd. Zobir; Shameli, Kamyar

2011-01-01

In this paper, Polyimide/Montmorillonite Nanocomposites (PI/MMT NCs), based on aromatic diamine (4-Aminophenyl sulfone) (APS) and aromatic dianhydride (3,3′,4,4′-benzophenonetetracarboxylic dianhydride) (BTDA) were prepared using in situ polymerization and solution-dispersion techniques. The prepared PI/MMT NCs films were characterized by X-ray diffraction (XRD), Fourier transform infrared spectroscopy (FT-IR), transmission electron microscopy (TEM) and thermogravimetric analysis (TGA). The XRD results showed that at the content of 1.0 wt % Organo Montmorillonite (OMMT) for two techniques and 3.0 wt % OMMT for the in situ polymerization technique, the OMMT was well-intercalated, exfoliated and dispersed into polyimide matrix. The OMMT agglomerated when its amount exceeded 10 wt % and 3.0 wt % for solution-dispersion and in situ polymerization techniques respectively. These results were confirmed by the TEM images of the prepared PI/MMT NCs. The TGA thermograms indicated that thermal stability of prepared PI/MMT NCs were increased with the increase of loading that, the effect is higher for the samples prepared by in situ polymerization technique. PMID:22016643

Comparison of in situ polymerization and solution-dispersion techniques in the preparation of Polyimide/Montmorillonite (MMT) Nanocomposites.

PubMed

Ahmad, Mansor Bin; Gharayebi, Yadollah; Salit, Mohd Sapuan; Hussein, Mohd Zobir; Shameli, Kamyar

2011-01-01

In this paper, Polyimide/Montmorillonite Nanocomposites (PI/MMT NCs), based on aromatic diamine (4-Aminophenyl sulfone) (APS) and aromatic dianhydride (3,3',4,4'-benzophenonetetracarboxylic dianhydride) (BTDA) were prepared using in situ polymerization and solution-dispersion techniques. The prepared PI/MMT NCs films were characterized by X-ray diffraction (XRD), Fourier transform infrared spectroscopy (FT-IR), transmission electron microscopy (TEM) and thermogravimetric analysis (TGA). The XRD results showed that at the content of 1.0 wt % Organo Montmorillonite (OMMT) for two techniques and 3.0 wt % OMMT for the in situ polymerization technique, the OMMT was well-intercalated, exfoliated and dispersed into polyimide matrix. The OMMT agglomerated when its amount exceeded 10 wt % and 3.0 wt % for solution-dispersion and in situ polymerization techniques respectively. These results were confirmed by the TEM images of the prepared PI/MMT NCs. The TGA thermograms indicated that thermal stability of prepared PI/MMT NCs were increased with the increase of loading that, the effect is higher for the samples prepared by in situ polymerization technique.

Intelsat satellite scheduled for launch

NASA Technical Reports Server (NTRS)

1981-01-01

The launch schedule for Intelsat 5-B, the prime Intelsat satellite to provide communications services between the Americas, Europe, the Middle East, and Africa, is presented. The planned placement of the satellite into an elliptical transfer orbit, and circularization of the orbit at geosynchronous altitude over the equator are described. Characteristics of the Atlas Centaur launch vehicle, AC-56, are given. The launch operation is summarized and the launch sequence presented. The Intelsat team and contractors are listed.

U.S. Secretary of State addresses launch team

NASA Technical Reports Server (NTRS)

1998-01-01

In a firing room of the Launch Control Center,U.S. Secretary of State Madeleine Albright waves to the personnel after her speech about the successful launch of Space Shuttle Endeavour. At her right is NASA Administrator Daniel Goldin. During the nearly 12- day mission of STS-88, the six-member crew will mate in space the first two elements of the International Space Station -- the already-orbiting Zarya control module and the Unity connecting module carried by Endeavour.

The impact of ultra-low amounts of amino-modified MMT on dynamics and properties of densely cross-linked cyanate ester resins

NASA Astrophysics Data System (ADS)

Bershtein, Vladimir; Fainleib, Alexander; Egorova, Larisa; Gusakova, Kristina; Grigoryeva, Olga; Kirilenko, Demid; Konnikov, Semen; Ryzhov, Valery; Yakushev, Pavel; Lavrenyuk, Natalia

2015-04-01

Thermostable nanocomposites based on densely cross-linked cyanate ester resins (CER), derived from bisphenol E and doped by 0.01 to 5 wt. % amino-functionalized 2D montmorillonite (MMT) nanoparticles, were synthesized and characterized using Fourier transform infrared (FTIR), transmission electron microscopy (TEM), energy dispersive X-ray spectroscopy (EDXS), wide-angle X-ray diffraction (WAXD), dynamic mechanical analysis (DMA), differential scanning calorimetry (DSC), thermogravimetric analysis (TGA), far-infrared (Far-IR), and creep rate spectroscopy (CRS) techniques. It was revealed that ultra-low additives, e.g., 0.025 to 0.1 wt. %, of amino-MMT nanolayers covalently embedded into CER network exerted an anomalously large impact on its dynamics and properties resulting, in particular, in some suppression of dynamics, increasing the onset of glass transition temperature by 30° to 40° and twofold rise of modulus in temperature range from 20°C to 200°C. Contrarily, the effects became negligibly small or even negative at increased amino-MMT contents, especially at 2 and 5 wt. %. That could be explained by TEM/EDXS data displaying predominance of individual amino-MMT nanolayers and their thin (2 to 3 nanolayers) stacks over more thick tactoids (5 to 10 nanolayers) and the large amino-MMT aggregates (100 to 500 nm in thickness) reversing the composite structure produced with increasing of amino-MMT content within CER matrix. The revealed effect of ultra-low amino-MMT content testifies in favor of the idea about the extraordinarily enhanced long-range action of the `constrained dynamics' effect in the case of densely cross-linked polymer networks.

Preparation and photo-catalytic activities of FeOOH/ZnO/MMT composite

NASA Astrophysics Data System (ADS)

Zhou, Yao; Liu, Fusheng; Yu, Shitao

2015-11-01

Montmorillonite (MMT) was used as the carrier for synthesis of FeOOH and FeOOH/ZnO nano-material. FeOOH and FeOOH/ZnO were synthesized by the aqueous solutions of Fe(NO3)3-HNO3 and Zn(NO3)2-NaOH/Fe(NO3)3-HNO3 with the carrier of montmorillonite respectively. Transmission electron-microscopy (TEM) and X-ray diffraction (XRD) were used to study the morphology form and structure of the nano-materials. TEM was also used to demonstrate that FeOOH/ZnO can be formed with the appropriate interface. According to UV-vis absorption spectra, FeOOH/ZnO has a better response to visible light than FeOOH and ZnO, which indicates there is some coupling effect between FeOOH and ZnO. Pentachlorophenol (PCP) was used as a representative organic pollutant to evaluate the photo-catalytic efficiency of the FeOOH/ZnO and FeOOH catalysts in visible light (λ > 400 nm). The photo-catalytic efficiency of FeOOH/ZnO/MMT is better than FeOOH/MMT. According to FTIR, changes of pH and TOC, the degradation mechanism was also discussed. PCP was degraded to aromatic ketone and chloro-hydrocarbon compounds and then to H2O, CO2 and HCl.

Improved NOAA weather satellite scheduled for NASA launch

NASA Technical Reports Server (NTRS)

1981-01-01

A description of the GOES-E mission is presented and includes the instrumentation of the satellite, data acquisition, spacecraft description, and Delta Launch Vehicle description. The launch operations are presented and include major launch events, post-launch events, and a review of the Delta/GOES-E team.

STS-121: Discovery Post Launch Press Briefing

NASA Technical Reports Server (NTRS)

2006-01-01

The briefing begins with Dean Acousta (NASA Press Secretary) introducing Michael Griffin (NASA Administrator), Bill Gerstenmaier (Associate Administrator for Space Operations) Wayne Hale (Space Shuttle Program Manager), John Shannon (Chairman, Mission Management Team, JSC), and Mike Leinbach (NASA Launch Director). The teams effort and dedication paid off in the form of a perfect launch and the weather cooperated. The Mission Management Team no problems during inspection. Debris assessment at 2 min. 47 sec. and 4 min. 50 sec. will be discussed when that information becomes available.The floor was then open for questions from the press.

Ares Launch Vehicles Lean Practices Case Study

NASA Technical Reports Server (NTRS)

Doreswamy, Rajiv; Self, Timothy A.

2007-01-01

The Ares launch vehicles team, managed by the Ares Projects Office (APO) at NASA Marshall Space Flight Center, has completed the Ares I Crew Launch Vehicle System Requirements Review and System Definition Review and early design work for the Ares V Cargo Launch Vehicle. This paper provides examples of how Lean Manufacturing, Kaizen events, and Six Sigma practices are helping APO deliver a new space transportation capability on time and within budget, while still meeting stringent technical requirements. For example, Lean philosophies have been applied to numerous process definition efforts and existing process improvement activities, including the Ares I-X test flight Certificate of Flight Readiness (CoFR) process, risk management process, and review board organization and processes. Ares executives learned Lean practices firsthand, making the team "smart buyers" during proposal reviews and instilling the team with a sense of what is meant by "value-added" activities. Since the goal of the APO is to field launch vehicles at a reasonable cost and on an ambitious schedule, adopting Lean philosophies and practices will be crucial to the Ares Project's long-term SUCCESS.

Ceremony celebrates 50 years of rocket launches

NASA Technical Reports Server (NTRS)

2000-01-01

Ceremony celebrates 50 years of rocket launches PL00C-10364.12 At the 50th anniversary ceremony celebrating the first rocket launch from pad 3 on what is now Cape Canaveral Air Force Station, Norris Gray waves to the audience. Gray was part of the team who successfully launched the first rocket, known as Bumper 8. The ceremony was hosted by the Air Force Space & Missile Museum Foundation, Inc. , and included launch of a Bumper 8 model rocket, presentation of a Bumper Award to Florida Sen. George Kirkpatrick by the National Space Club; plus remarks by Sen. Kirkpatrick, KSC's Center Director Roy Bridges, and the Commander of the 45th Space Wing, Brig. Gen. Donald Pettit. Also attending the ceremony were other members of the original Bumper 8 team. A reception followed at Hangar C. Since 1950 there have been a total of 3,245 launches from Cape Canaveral.

The KSC Simulation Team practices for contingencies in Firing Room 1

NASA Technical Reports Server (NTRS)

1998-01-01

In Firing Room 1 at KSC, Shuttle launch team members put the Shuttle system through an integrated simulation. The control room is set up with software used to simulate flight and ground systems in the launch configuration. A Simulation Team, comprised of KSC engineers, introduce 12 or more major problems to prepare the launch team for worst-case scenarios. Such tests and simulations keep the Shuttle launch team sharp and ready for liftoff. The next liftoff is targeted for Oct. 29.

NPP After Launch: Characterizing ATMS Performance

NASA Technical Reports Server (NTRS)

Lambrigtsen, Bjorn

2011-01-01

The NPOESS Preparatory Project (NPP) mission is scheduled to launch in the fall of 2011. Although several teams from the government and the instrument contractor will be assessing and characterizing the performance of the Advanced Technology Microwave Sounder (ATMS) and the Cross-track Infrared Sounder (CrIS) sounding suite, the NASA NPP Science Team will be paying particular attention to the aspects of these sensors that affect their utility for atmospheric and climate research. In this talk we discuss relevant aspects of ATMS and our post launch analysis approach.

STS-121: Discovery Mission Management Team Briefing

NASA Technical Reports Server (NTRS)

2006-01-01

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

STS-135 Launch Day

NASA Image and Video Library

2011-07-07

Warren Hinson, a NASA Emergency Response Team (ERT) member, keeps an eye out while flying near the Vehicle Assembly Building (VAB) prior to the launch of space shuttle Atlantis, STS-135, Friday, July 8, 2011, at Kennedy Space Center in Cape Canaveral, Fla. The launch of Atlantis, is the final flight of the shuttle program, a 12-day mission to the International Space Station. Photo Credit: (NASA/Bill Ingalls)

Launch Vehicle Control Center Architectures

NASA Technical Reports Server (NTRS)

Watson, Michael D.; Epps, Amy; Woodruff, Van; Vachon, Michael Jacob; Monreal, Julio; Williams, Randall; McLaughlin, Tom

2014-01-01

This analysis is a survey of control center architectures of the NASA Space Launch System (SLS), United Launch Alliance (ULA) Atlas V and Delta IV, and the European Space Agency (ESA) Ariane 5. Each of these control center architectures have similarities in basic structure, and differences in functional distribution of responsibilities for the phases of operations: (a) Launch vehicles in the international community vary greatly in configuration and process; (b) Each launch site has a unique processing flow based on the specific configurations; (c) Launch and flight operations are managed through a set of control centers associated with each launch site, however the flight operations may be a different control center than the launch center; and (d) The engineering support centers are primarily located at the design center with a small engineering support team at the launch site.

Implementation and on-sky results of an optimal wavefront controller for the MMT NGS adaptive optics system

NASA Astrophysics Data System (ADS)

Powell, Keith B.; Vaitheeswaran, Vidhya

2010-07-01

The MMT observatory has recently implemented and tested an optimal wavefront controller for the NGS adaptive optics system. Open loop atmospheric data collected at the telescope is used as the input to a MATLAB based analytical model. The model uses nonlinear constrained minimization to determine controller gains and optimize the system performance. The real-time controller performing the adaptive optics close loop operation is implemented on a dedicated high performance PC based quad core server. The controller algorithm is written in C and uses the GNU scientific library for linear algebra. Tests at the MMT confirmed the optimal controller significantly reduced the residual RMS wavefront compared with the previous controller. Significant reductions in image FWHM and increased peak intensities were obtained in J, H and K-bands. The optimal PID controller is now operating as the baseline wavefront controller for the MMT NGS-AO system.

Launch of Space Shuttle Atlantis / STS-129 Mission

NASA Image and Video Library

2009-11-16

STS129-S-058 (16 Nov. 2009) --- In Firing Room 4 of NASA Kennedy Space Center's Launch Control Center, shuttle launch director Michael Leinbach (standing), assistant launch director Peter Nickolenko and Atlantis flow director Angie Brewer (both seated), applaud the launch team upon the successful launch of Space Shuttle Atlantis. Liftoff of Atlantis from Launch Pad 39A on its STS-129 mission to the International Space Station came at 2:28 p.m. (EST) Nov. 16, 2009.

The 6.5-m MMT Telescope: status and plans for the future

NASA Astrophysics Data System (ADS)

Williams, G. Grant; Ortiz, R.; Goble, W.; Gibson, J. D.

2016-08-01

The MMT Observatory, a joint venture of the Smithsonian Institution and the University of Arizona, operates the 6.5-m MMT telescope on the summit of Mount Hopkins approximately 45 miles south of Tucson, AZ. The upgraded telescope has been in routine operation for nearly fifteen years and, as such, is a very reliable and productive general purpose astronomical instrument. The telescope can be configured with one of three secondary mirrors that feed more than ten instruments at the Cassegrain focus. In this paper we provide an overview of the the telescope, its current capabilities, and its performance. We will review the existing suite of instruments and their different modes of operation. We will describe some of the general operations challenges and strategies for the Observatory. Finally, we will discuss plans for the near-term future including technical upgrades, new instrumentation and routine queue operation of MMIRS and Binospec.

Life Cycle Analysis of Dedicated Nano-Launch Technologies

NASA Technical Reports Server (NTRS)

Zapata, Edgar; McCleskey, Carey; Martin, John; Lepsch, Roger; Hernani, Tosoc

2014-01-01

Recent technology advancements have enabled the development of small cheap satellites that can perform useful functions in the space environment. Currently, the only low cost option for getting these payloads into orbit is through ride share programs. As a result, these launch opportunities await primary payload launches and a backlog exists. An alternative option would be dedicated nano-launch systems built and operated to provide more flexible launch services, higher availability, and affordable prices. The potential customer base that would drive requirements or support a business case includes commercial, academia, civil government and defense. Further, NASA technology investments could enable these alternative game changing options.With this context, in 2013 the Game Changing Development (GCD) program funded a NASA team to investigate the feasibility of dedicated nano-satellite launch systems with a recurring cost of less than $2 million per launch for a 5 kg payload to low Earth orbit. The team products would include potential concepts, technologies and factors for enabling the ambitious cost goal, exploring the nature of the goal itself, and informing the GCD program technology investment decision making process. This paper provides an overview of the life cycle analysis effort that was conducted in 2013 by an inter-center NASA team. This effort included the development of reference nano-launch system concepts, developing analysis processes and models, establishing a basis for cost estimates (development, manufacturing and launch) suitable to the scale of the systems, and especially, understanding the relationship of potential game changing technologies to life cycle costs, as well as other factors, such as flights per year.

Launch of Space Shuttle Atlantis / STS-129 Mission

NASA Image and Video Library

2009-11-16

STS129-S-059 (16 Nov. 2009) --- In Firing Room 4 of NASA Kennedy Space Center's Launch Control Center, Kennedy Director Bob Cabana congratulates the launch team upon the successful launch of Space Shuttle Atlantis. Liftoff of Atlantis from Launch Pad 39A on its STS-129 mission to the International Space Station came at 2:28 p.m. (EST) Nov. 16, 2009.

Imagery Integration Team

NASA Technical Reports Server (NTRS)

Calhoun, Tracy; Melendrez, Dave

2014-01-01

The Human Exploration Science Office (KX) provides leadership for NASA's Imagery Integration (Integration 2) Team, an affiliation of experts in the use of engineering-class imagery intended to monitor the performance of launch vehicles and crewed spacecraft in flight. Typical engineering imagery assessments include studying and characterizing the liftoff and ascent debris environments; launch vehicle and propulsion element performance; in-flight activities; and entry, landing, and recovery operations. Integration 2 support has been provided not only for U.S. Government spaceflight (e.g., Space Shuttle, Ares I-X) but also for commercial launch providers, such as Space Exploration Technologies Corporation (SpaceX) and Orbital Sciences Corporation, servicing the International Space Station. The NASA Integration 2 Team is composed of imagery integration specialists from JSC, the Marshall Space Flight Center (MSFC), and the Kennedy Space Center (KSC), who have access to a vast pool of experience and capabilities related to program integration, deployment and management of imagery assets, imagery data management, and photogrammetric analysis. The Integration 2 team is currently providing integration services to commercial demonstration flights, Exploration Flight Test-1 (EFT-1), and the Space Launch System (SLS)-based Exploration Missions (EM)-1 and EM-2. EM-2 will be the first attempt to fly a piloted mission with the Orion spacecraft. The Integration 2 Team provides the customer (both commercial and Government) with access to a wide array of imagery options - ground-based, airborne, seaborne, or vehicle-based - that are available through the Government and commercial vendors. The team guides the customer in assembling the appropriate complement of imagery acquisition assets at the customer's facilities, minimizing costs associated with market research and the risk of purchasing inadequate assets. The NASA Integration 2 capability simplifies the process of securing one

Synthesis of the very acid-sensitive Fmoc-Cys(Mmt)-OH and its application in solid-phase peptide synthesis.

PubMed

Barlos, K; Gatos, D; Hatzi, O; Koch, N; Koutsogianni, S

1996-03-01

S-4-methoxytrityl cysteine was synthesized and converted into the corresponding Fmoc-Cys(Mmt)-OH by its reaction with Fmoc-OSu. As compared to the corresponding Fmoc-Cys(Trt)-OH, the S-Mmt-function was found to be considerably more acid labile. Quantitative S-Mmt-removal occurs selectively in the presence of groups of the tert butyl type and S-Trt by treatment with 0.5-1.0% TFA. The new derivative was successfully utilized in the SPPS of Tyr1-somatostatin on 2-chlorotrityl resin. In this synthesis groups of the Trt-type were exclusively used for amino acid side-chain protection. Quantitative cleavage from the resin and complete deprotection was performed by treatment with 3% TFA in DCM-TES (95:5) for 30 min at RT. We observed no reduction of tryptophan under these conditions.

Launch Vehicles

NASA Image and Video Library

2007-09-09

Under the goals of the Vision for Space Exploration, Ares I is a chief component of the cost-effective space transportation infrastructure being developed by NASA's Constellation Program. This transportation system will safely and reliably carry human explorers back to the moon, and then onward to Mars and other destinations in the solar system. The Ares I effort includes multiple project element teams at NASA centers and contract organizations around the nation, and is managed by the Exploration Launch Projects Office at NASA's Marshall Space Flight Center (MFSC). ATK Launch Systems near Brigham City, Utah, is the prime contractor for the first stage booster. ATK's subcontractor, United Space Alliance of Houston, is designing, developing and testing the parachutes at its facilities at NASA's Kennedy Space Center in Florida. NASA's Johnson Space Center in Houston hosts the Constellation Program and Orion Crew Capsule Project Office and provides test instrumentation and support personnel. Together, these teams are developing vehicle hardware, evolving proven technologies, and testing components and systems. Their work builds on powerful, reliable space shuttle propulsion elements and nearly a half-century of NASA space flight experience and technological advances. Ares I is an inline, two-stage rocket configuration topped by the Crew Exploration Vehicle, its service module, and a launch abort system. In this HD video image, the first stage reentry 1/2% model is undergoing pressure measurements inside the wind tunnel testing facility at MSFC. (Highest resolution available)

Launch of Space Shuttle Atlantis / STS-129 Mission

NASA Image and Video Library

2009-11-16

STS129-S-056 (16 Nov. 2009) --- Members of the space shuttle launch team watch Space Shuttle Atlantis' launch through the newly installed windows of Firing Room 4 in the Launch Control Center at NASA's Kennedy Space Center in Florida. Liftoff of Atlantis from Launch Pad 39A on its STS-129 mission to the International Space Station came at 2:28 p.m. (EST) Nov. 16, 2009.

Launch Vehicles

NASA Image and Video Library

2007-09-09

Under the goals of the Vision for Space Exploration, Ares I is a chief component of the cost-effective space transportation infrastructure being developed by NASA's Constellation Program. This transportation system will safely and reliably carry human explorers back to the moon, and then onward to Mars and other destinations in the solar system. The Ares I effort includes multiple project element teams at NASA centers and contract organizations around the nation, and is managed by the Exploration Launch Projects Office at NASA's Marshall Space Flight Center (MFSC). ATK Launch Systems near Brigham City, Utah, is the prime contractor for the first stage booster. ATK's subcontractor, United Space Alliance of Houston, is designing, developing and testing the parachutes at its facilities at NASA's Kennedy Space Center in Florida. NASA's Johnson Space Center in Houston hosts the Constellation Program and Orion Crew Capsule Project Office and provides test instrumentation and support personnel. Together, these teams are developing vehicle hardware, evolving proven technologies, and testing components and systems. Their work builds on powerful, reliable space shuttle propulsion elements and nearly a half-century of NASA space flight experience and technological advances. Ares I is an inline, two-stage rocket configuration topped by the Crew Exploration Vehicle, its service module, and a launch abort system. The launch vehicle's first stage is a single, five-segment reusable solid rocket booster derived from the Space Shuttle Program's reusable solid rocket motor that burns a specially formulated and shaped solid propellant called polybutadiene acrylonitrile (PBAN). The second or upper stage will be propelled by a J-2X main engine fueled with liquid oxygen and liquid hydrogen. This HD video image depicts a test firing of a 40k subscale J2X injector at MSFC's test stand 115. (Highest resolution available)

Functional copolymer/organo-MMT nanoarchitectures. VI. Synthesis and characterization of novel nanocomposites by interlamellar controlled/living radical copolymerization via preintercalated RAFT-agent/organoclay complexes.

PubMed

Rzayev, Zakir M O; Söylemez, A Ernur

2011-04-01

We have developed a new approach for the synthesis of polymer nanocomposites using a bifunctional reversible addition-fragmentation chain transfer (RAFT) agent, two types of organo-montmorillonites, such as a non-reactive dimethyldodecyl ammonium (DMDA)-MMT and a reactive octadecylamine (ODA)-MMT organoclays, and a radical initiator. The method includes the following stages: (1) synthesis of RAFT intercalated O-MMTs by a physical or chemical interaction of the RAFT agent having two pendant carboxylic groups [S,S-bis(alpha,alpha'-dimethyl-alpha"-acetic acid)trithiocarbonate] with surface alkyl amines of O-MMT containing tertiary ammonium cation or primary amine groups through strong H-bonding and complexing/amidization reactions, respectively, and (2) utilization of these well-dispersed and intercalated RAFT ... O-MMT complexes and their amide derivatives as new modified RAFT agents in radical-initiated interlamellar controlled/living copolymerization of itaconic acid (IA)-n-butylmethacrylate (BMA) monomer pair. The structure and compositions of the synthesized RAFT ... O-MMT complexes and functional copolymer/O-MMT hybrids were confirmed by FTIR, XRD, thermal (DSC-TGA), SEM and TEM morphology analyses. It was demonstrated that the degree of interaction/exfoliation, morphology and thermal behavior of nanocomposites significantly depended on the type of organoclay and in situ interaction, as well as on the content of flexible butyl-ester linkages as a internal plasticizer. The results of the comparative analysis of the nanocomposites structure-composition-property relations show that the functional copolymer-organoclay hybrids prepared with reactive RAFT ... ODA-MMT complex and containing a combination of partially intercalated and predominantly exfoliated nano-structures exhibit relatively higher thermal stability and fine dispersed morphology. These effects were explained by in situ interfacial chemical reactions through amidization of RAFT with surface alkyl amine

KSC-07pd3599

NASA Image and Video Library

2007-12-09

KENNEDY SPACE CENTER, FLA. -- Doug Lyons, STS-122 launch director, participates in a news briefing following the conclusion of a Mission Management Team, or MMT, meeting. The meeting followed the morning's launch scrub of the space shuttle Atlantis STS-122 mission caused by problems experienced with the external tank's engine cutoff sensor system during tanking for the second launch attempt. An announcement was made during the briefing that the STS-122 launch is postponed to no earlier than Jan. 2, 2008, to give the team time to resolve the system's problems. Atlantis will carry the Columbus Laboratory, the European Space Agency's largest contribution to the construction of the International Space Station. It will support scientific and technological research in a microgravity environment. Permanently attached to the Harmony node of the space station, the laboratory will carry out experiments in materials science, fluid physics and biosciences, as well as perform a number of technological applications. Photo credit: NASA/Kim Shiflett

Life Cycle Analysis of Dedicated Nano-Launch Technologies

NASA Technical Reports Server (NTRS)

Zapata, Edgar; McCleskey, Carey (Editor); Martin, John; Lepsch, Roger; Ternani, Tosoc

2014-01-01

Recent technology advancements have enabled the development of small cheap satellites that can perform useful functions in the space environment. Currently, the only low cost option for getting these payloads into orbit is through ride share programs - small satellites awaiting the launch of a larger satellite, and then riding along on the same launcher. As a result, these small satellite customers await primary payload launches and a backlog exists. An alternative option would be dedicated nano-launch systems built and operated to provide more flexible launch services, higher availability, and affordable prices. The potential customer base that would drive requirements or support a business case includes commercial, academia, civil government and defense. Further, NASA technology investments could enable these alternative game changing options. With this context, in 2013 the Game Changing Development (GCD) program funded a NASA team to investigate the feasibility of dedicated nano-satellite launch systems with a recurring cost of less than $2 million per launch for a 5 kg payload to low Earth orbit. The team products would include potential concepts, technologies and factors for enabling the ambitious cost goal, exploring the nature of the goal itself, and informing the GCD program technology investment decision making process. This paper provides an overview of the life cycle analysis effort that was conducted in 2013 by an inter-center NASA team. This effort included the development of reference nano-launch system concepts, developing analysis processes and models, establishing a basis for cost estimates (development, manufacturing and launch) suitable to the scale of the systems, and especially, understanding the relationship of potential game changing technologies to life cycle costs, as well as other factors, such as flights per year.

Launch of Space Shuttle Atlantis / STS-129 Mission

NASA Image and Video Library

2009-11-16

STS129-S-055 (16 Nov. 2009) --- The space shuttle launch team monitors the progress of Space Shuttle Atlantis' countdown from consoles on the main floor of Firing Room 4 in Kennedy's Launch Control Center. Liftoff of Atlantis from Launch Pad 39A on its STS-129 mission to the International Space Station came at 2:28 p.m. (EST) Nov. 16, 2009.

Launch Vehicles

NASA Image and Video Library

2007-08-09

Under the goals of the Vision for Space Exploration, Ares I is a chief component of the cost-effective space transportation infrastructure being developed by NASA's Constellation Program. This transportation system will safely and reliably carry human explorers back to the moon, and then onward to Mars and other destinations in the solar system. The Ares I effort includes multiple project element teams at NASA centers and contract organizations around the nation, and is managed by the Exploration Launch Projects Office at NASA's Marshall Space Flight Center (MFSC). ATK Launch Systems near Brigham City, Utah, is the prime contractor for the first stage booster. ATK's subcontractor, United Space Alliance of Houston, is designing, developing and testing the parachutes at its facilities at NASA's Kennedy Space Center in Florida. NASA's Johnson Space Center in Houston hosts the Constellation Program and Orion Crew Capsule Project Office and provides test instrumentation and support personnel. Together, these teams are developing vehicle hardware, evolving proven technologies, and testing components and systems. Their work builds on powerful, reliable space shuttle propulsion elements and nearly a half-century of NASA space flight experience and technological advances. Ares I is an inline, two-stage rocket configuration topped by the Crew Exploration Vehicle, its service module, and a launch abort system. This HD video image depicts confidence testing of a manufactured aluminum panel that will fabricate the Ares I upper stage barrel. In this test, bent aluminum is stressed to breaking point and thoroughly examined. The panels are manufactured by AMRO Manufacturing located in El Monte, California. (Highest resolution available)

Launch Vehicles

NASA Image and Video Library

2006-08-09

Under the goals of the Vision for Space Exploration, Ares I is a chief component of the cost-effective space transportation infrastructure being developed by NASA's Constellation Program. This transportation system will safely and reliably carry human explorers back to the moon, and then onward to Mars and other destinations in the solar system. The Ares I effort includes multiple project element teams at NASA centers and contract organizations around the nation, and is managed by the Exploration Launch Projects Office at NASA's Marshall Space Flight Center (MFSC). ATK Launch Systems near Brigham City, Utah, is the prime contractor for the first stage booster. ATK's subcontractor, United Space Alliance of Houston, is designing, developing and testing the parachutes at its facilities at NASA's Kennedy Space Center in Florida. NASA's Johnson Space Center in Houston hosts the Constellation Program and Orion Crew Capsule Project Office and provides test instrumentation and support personnel. Together, these teams are developing vehicle hardware, evolving proven technologies, and testing components and systems. Their work builds on powerful, reliable space shuttle propulsion elements and nearly a half-century of NASA space flight experience and technological advances. Ares I is an inline, two-stage rocket configuration topped by the Crew Exploration Vehicle, its service module, and a launch abort system. This HD video image depicts a manufactured aluminum panel, that will fabricate the Ares I upper stage barrel, undergoing a confidence panel test. In this test, bent aluminum is stressed to breaking point and thoroughly examined. The panels are manufactured by AMRO Manufacturing located in El Monte, California. (Highest resolution available)

Launch Vehicles

NASA Image and Video Library

2007-07-09

Under the goals of the Vision for Space Exploration, Ares I is a chief component of the cost-effective space transportation infrastructure being developed by NASA's Constellation Program. This transportation system will safely and reliably carry human explorers back to the moon, and then onward to Mars and other destinations in the solar system. The Ares I effort includes multiple project element teams at NASA centers and contract organizations around the nation, and is managed by the Exploration Launch Projects Office at NASA's Marshall Space Flight Center (MFSC). ATK Launch Systems near Brigham City, Utah, is the prime contractor for the first stage booster. ATK's subcontractor, United Space Alliance of Houston, is designing, developing and testing the parachutes at its facilities at NASA's Kennedy Space Center in Florida. NASA's Johnson Space Center in Houston hosts the Constellation Program and Orion Crew Capsule Project Office and provides test instrumentation and support personnel. Together, these teams are developing vehicle hardware, evolving proven technologies, and testing components and systems. Their work builds on powerful, reliable space shuttle propulsion elements and nearly a half-century of NASA space flight experience and technological advances. Ares I is an inline, two-stage rocket configuration topped by the Crew Exploration Vehicle, its service module, and a launch abort system. In this HD video image, an Ares I x-test involves the upper stage separating from the first stage. This particular test was conducted at the NASA Langley Research Center in July 2007. (Highest resolution available)

Launch Vehicles

NASA Image and Video Library

2007-08-09

Under the goals of the Vision for Space Exploration, Ares I is a chief component of the cost-effective space transportation infrastructure being developed by NASA's Constellation Program. This transportation system will safely and reliably carry human explorers back to the moon, and then onward to Mars and other destinations in the solar system. The Ares I effort includes multiple project element teams at NASA centers and contract organizations around the nation, and is managed by the Exploration Launch Projects Office at NASA's Marshall Space Flight Center (MFSC). ATK Launch Systems near Brigham City, Utah, is the prime contractor for the first stage booster. ATK's subcontractor, United Space Alliance of Houston, is designing, developing and testing the parachutes at its facilities at NASA's Kennedy Space Center in Florida. NASA's Johnson Space Center in Houston hosts the Constellation Program and Orion Crew Capsule Project Office and provides test instrumentation and support personnel. Together, these teams are developing vehicle hardware, evolving proven technologies, and testing components and systems. Their work builds on powerful, reliable space shuttle propulsion elements and nearly a half-century of NASA space flight experience and technological advances. Ares I is an inline, two-stage rocket configuration topped by the Crew Exploration Vehicle, its service module, and a launch abort system. In this HD video image, processes for upper stage barrel fabrication are talking place. Aluminum panels are manufacturing process demonstration articles that will undergo testing until perfected. The panels are built by AMRO Manufacturing located in El Monte, California. (Largest resolution available)

Launch Vehicles

NASA Image and Video Library

2007-08-09

Under the goals of the Vision for Space Exploration, Ares I is a chief component of the cost-effective space transportation infrastructure being developed by NASA's Constellation Program. This transportation system will safely and reliably carry human explorers back to the moon, and then onward to Mars and other destinations in the solar system. The Ares I effort includes multiple project element teams at NASA centers and contract organizations around the nation, and is managed by the Exploration Launch Projects Office at NASA's Marshall Space Flight Center (MFSC). ATK Launch Systems near Brigham City, Utah, is the prime contractor for the first stage booster. ATK's subcontractor, United Space Alliance of Houston, is designing, developing and testing the parachutes at its facilities at NASA's Kennedy Space Center in Florida. NASA's Johnson Space Center in Houston hosts the Constellation Program and Orion Crew Capsule Project Office and provides test instrumentation and support personnel. Together, these teams are developing vehicle hardware, evolving proven technologies, and testing components and systems. Their work builds on powerful, reliable space shuttle propulsion elements and nearly a half-century of NASA space flight experience and technological advances. Ares I is an inline, two-stage rocket configuration topped by the Crew Exploration Vehicle, its service module, and a launch abort system. This HD video image depicts the manufacturing of aluminum panels that will be used to form the Ares I barrel. The panels are manufacturing process demonstration articles that will undergo testing until perfected. The panels are built by AMRO Manufacturing located in El Monte, California. (Highest resolution available)

[Impacts of antiretroviral treatment on drug use and high risk sexual behaviors among HIV-positive MMT clients].

PubMed

Qian, Xiaoai; Cao, Xiaobin; Zhao, Yan; Wang, Changhe; Luo, Wei; Rou, Keming; Zhang, Bo; Min, Xiangdong; Duan, Song; Tang, Renhai; Wu, Zunyou

2015-06-01

To explore the impacts of antiretroviral treatment on drug use and high risk sexual behaviors among HIV-positive MMT clients. A cross-sectional study was conducted in patients undergoing ART (ART-experienced) and patients not undergoing ART (ART-naive) attending MMT in 5 clinics in Yunnan Honghe and Dehong prefectures in 2014. A questionnaire was designed to collect socio-demographic characteristics, ART and MMT information and sexual and drug use behaviors within 3 months before the investigation was conducted. Logistic regression analysis was conducted to identify the predictors for drug use and risky sexual behaviors. A total of 328 cases were included in the analysis, among which 202 were ART-experienced and 126 were ART-naÏve. Among 152 respondents who were sexually active, 61 (40.1%) reported having unprotected sex (UPS) with their regular partners in the prior 3 months. A total of 57.6% (189/328) of the respondents used drugs in the prior 3 months. Multiple logistic regression analysis revealed that younger than 35 years old (OR = 3.57, 95% CI: 1.23-10.37), fertility desire (OR = 4.47, 95% CI: 1.49-13.41), partner being HIV-positive (OR = 4.62, 95% CI: 1.80-11.86), length of MMT attendance less than 5 years (OR = 2.92, 95% CI: 1.14-7.53), agreed that it was necessary to use condom no matter the viral load is high or low (OR = 0.14, 95% CI: 0.04-0.51) were protective factors of UPS in the prior 3 months. Multiple logistic regression analysis revealed that being Han (OR = 0.46, 95% CI: 0.24-0.89), feeling having good health status (OR = 0.39, 95% CI: 0.18-0.85), being enrolled in ART (OR = 0.32, 95% CI: 0.17-0.60) were protective factors for drug use in the prior three months, having contact with drug using friends (OR = 4.41, 95% CI: 2.31-8.29), having experience of missing an MMT dose (OR = 3.47, 95% CI: 1.92-6.29), and not satisfied with current MMT dose (OR = 13.92, 95% CI: 3.24-59.93) were risk factors for drug use during the prior three months. ART was

NASA's Launch Propulsion Systems Technology Roadmap

NASA Technical Reports Server (NTRS)

McConnaughey, Paul K.; Femminineo, Mark G.; Koelfgen, Syri J.; Lepsch, Roger A; Ryan, Richard M.; Taylor, Steven A.

2012-01-01

Safe, reliable, and affordable access to low-Earth (LEO) orbit is necessary for all of the United States (US) space endeavors. In 2010, NASA s Office of the Chief Technologist commissioned 14 teams to develop technology roadmaps that could be used to guide the Agency s and US technology investment decisions for the next few decades. The Launch Propulsion Systems Technology Area (LPSTA) team was tasked to address the propulsion technology challenges for access to LEO. The developed LPSTA roadmap addresses technologies that enhance existing solid or liquid propulsion technologies and their related ancillary systems or significantly advance the technology readiness level (TRL) of less mature systems like airbreathing, unconventional, and other launch technologies. In developing this roadmap, the LPSTA team consulted previous NASA, military, and industry studies as well as subject matter experts to develop their assessment of this field, which has fundamental technological and strategic impacts for US space capabilities.

Launch system development in the Pacific Rim

NASA Technical Reports Server (NTRS)

Stone, Barbara A.; Page, John R.

1993-01-01

Several Western Pacific Rim nations are beginning to challenge the domination of the United States, Europe, and the former Soviet Union in the international market for commercial launch sevices. This paper examines the current development of launch systems in China, Japan, and Australia. China began commercial launch services with their Long March-3 in April 1990, and is making enhancements to vehicles in this family. Japan is developing the H-2 rocket which will be marketed on a commercial basis. In Australia, British Aerospace Ltd. is leading a team conducting a project definition study for an Australian Launch Vehicle, aimed at launching the new generation of satellites into low Earth orbit.

NASA Scientific Balloon Team Hopes to Break Flight Duration Record with New Zealand Launch

NASA Image and Video Library

2017-12-08

After years of tests and development, NASA’s Balloon Program team is on the cusp of expanding the envelope in high-altitude, heavy-lift ballooning with its super pressure balloon (SPB) technology. NASA’s scientific balloon experts are in Wanaka, New Zealand, prepping for the fourth flight of an 18.8 million-cubic-foot (532,000 cubic-meter) balloon, with the ambitious goal of achieving an ultra-long-duration flight of up to 100 days at mid-latitudes. Launch of the pumpkin-shaped, football stadium-size balloon is scheduled for sometime after April 1, 2016, from Wanaka Airport, pending final checkouts and flight readiness of the balloon and supporting systems. Once launched, the SPB, which is made from 22-acres of polyethylene film – similar to a sandwich bag, but stronger and more durable – will ascend to a nearly constant float altitude of 110,000 feet (33.5 km). The balloon will travel eastward carrying a 2,260-pound (1,025 kg) payload consisting of tracking, communications and scientific instruments. NASA expects the SPB to circumnavigate the globe once every one to three weeks, depending on wind speeds in the stratosphere. Read more: go.nasa.gov/1p56xKR NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors: Earth Science, Heliophysics, Solar System Exploration, and Astrophysics. Goddard plays a leading role in NASA’s accomplishments by contributing compelling scientific knowledge to advance the Agency’s mission. Follow us on Twitter Like us on Facebook Find us on Instagram

The effect of recycled Natural Rubber Glove (rRG) Plasticizers to Deflection and Flexural Strength Properties of PP/MMt/rRG Smart Composites and Its Inflammability

NASA Astrophysics Data System (ADS)

Suharty, N. S.; Ismail, H.; Diharjo, K.; Handayani, D. S.; Saputri, L. N. M. Z.; Ariesta, N.

2018-03-01

Had been synthesized PP/rRG/MMt+ZB smart material composite in solution reactive processes with various rRG concentration. The addition of rRG plasticizers will improve the deflection properties and increase the filler capacity MMt loading to reach the optimum concentration. The addition of 3% rRG is capable of loading filler capacity MMt to 23% as the optimum condition. At the optimum conditions it can increase the deflection (Defl) and flexural strength (FS) up to 16% and 15% respectively compared to that of the composites without rRG. The rRG plasticizer serves as a bio-compatibilizer that can reduce surface tension of the mixture and leads to decrease the Defl., follow by the increase of loading filler capacity and well interaction finally can increase the FS properties. The increase of loading filler MMt up to 23% can also improve the inflammability of the composites. Time to Ignition (TTI) increase by 5% and Burning Rate (BR) decrease by 4.5% compared to that of the composites which is containing MMt 20% without rRG.

Development of novel composite membranes using quaternized chitosan and Na+-MMT clay for the pervaporation dehydration of isopropanol.

PubMed

Choudhari, Santosh K; Kariduraganavar, Mahadevappa Y

2009-10-01

Novel polymer-clay-based composite membranes were prepared by incorporating sodium montmorillonite (Na(+)-MMT) clay into quaternized chitosan. The resulting membranes were characterized by Fourier transform infrared spectroscopy (FTIR), wide-angle X-ray diffraction (WXAD), and thermogravimetric analysis (TGA). The effect of membrane swelling was studied by varying the water concentration in the feed. The membranes were employed for the pervaporation dehydration of isopropanol in terms of feed composition and Na(+)-MMT clay loading. The experimental results demonstrated that membrane containing 10 mass% of Na(+)-MMT clay showed the highest separation selectivity of 14,992 with a flux of 14.23x10(-2) kg/m(2) h at 30 degrees C for 10 mass% of water in the feed. The total flux and flux of water are found to be overlapping each other particularly for clay-incorporated membranes, signifying that the composite membranes developed in the present study involving quaternized chitosan and Na(+)-MMT clay are highly selective toward water. From the temperature-dependent diffusion and permeation values, the Arrhenius activation parameters were estimated. The resulting activation energy values obtained for water permeation (E(pw)) are much lower than those of isopropanol permeation (E(pIPA)), suggesting that the developed composite membranes have higher separation efficiency for the water-isopropanol system. The estimated E(p) and E(D) values ranged between 8.97 and 11.89, and 7.56 and 9.88 kJ/mol, respectively. The positive heat of sorption (DeltaH(s)) values were obtained for all the membranes, suggesting that Henry's mode of sorption is predominant in the process.

Making Interoperability Easier with NASA's Metadata Management Tool (MMT)

NASA Technical Reports Server (NTRS)

Shum, Dana; Reese, Mark; Pilone, Dan; Baynes, Katie

2016-01-01

While the ISO-19115 collection level metadata format meets many users' needs for interoperable metadata, it can be cumbersome to create it correctly. Through the MMT's simple UI experience, metadata curators can create and edit collections which are compliant with ISO-19115 without full knowledge of the NASA Best Practices implementation of ISO-19115 format. Users are guided through the metadata creation process through a forms-based editor, complete with field information, validation hints and picklists. Once a record is completed, users can download the metadata in any of the supported formats with just 2 clicks.

Assessing Upper-Level Winds on Day-of-Launch

NASA Technical Reports Server (NTRS)

Bauman, William H., III; Wheeler, Mark M.

2012-01-01

On the day-or-launch. the 45th Weather Squadron Launch Weather Officers (LWOS) monitor the upper-level winds for their launch customers to include NASA's Launch Services Program (LSP). During launch operations, the payload launch team sometimes asks the LWO if they expect the upper level winds to change during the countdown but the LWOs did not have the capability to quickly retrieve or display the upper-level observations and compare them to the numerical weather prediction model point forecasts. The LWOs requested the Applied Meteorology Unit (AMU) develop a capability in the form of a graphical user interface (GUI) that would allow them to plot upper-level wind speed and direction observations from the Kennedy Space Center Doppler Radar Wind Profilers and Cape Canaveral Air Force Station rawinsondes and then overlay model point forecast profiles on the observation profiles to assess the performance of these models and graphically display them to the launch team. The AMU developed an Excel-based capability for the LWOs to assess the model forecast upper-level winds and compare them to observations. They did so by creating a GUI in Excel that allows the LWOs to first initialize the models by comparing the O-hour model forecasts to the observations and then to display model forecasts in 3-hour intervals from the current time through 12 hours.

Launch Vehicles

NASA Image and Video Library

2007-08-09

Under the goals of the Vision for Space Exploration, Ares I is a chief component of the cost-effective space transportation infrastructure being developed by NASA's Constellation Program. This transportation system will safely and reliably carry human explorers back to the moon, and then onward to Mars and other destinations in the solar system. The Ares I effort includes multiple project element teams at NASA centers and contract organizations around the nation, and is managed by the Exploration Launch Projects Office at NASA's Marshall Space Flight Center (MFSC). ATK Launch Systems near Brigham City, Utah, is the prime contractor for the first stage booster. ATK's subcontractor, United Space Alliance of Houston, is designing, developing and testing the parachutes at its facilities at NASA's Kennedy Space Center in Florida. NASA's Johnson Space Center in Houston hosts the Constellation Program and Orion Crew Capsule Project Office and provides test instrumentation and support personnel. Together, these teams are developing vehicle hardware, evolving proven technologies, and testing components and systems. Their work builds on powerful, reliable space shuttle propulsion elements and nearly a half-century of NASA space flight experience and technological advances. Ares I is an inline, two-stage rocket configuration topped by the Crew Exploration Vehicle, its service module, and a launch abort system. This HD video image depicts friction stir welding used in manufacturing aluminum panels that will fabricate the Ares I upper stage barrel. The panels are subjected to confidence tests in which the bent aluminum is stressed to breaking point and thoroughly examined. The panels are manufactured by AMRO Manufacturing located in El Monte, California. (Highest resolution available)

Launch Vehicles

NASA Image and Video Library

2007-08-09

Under the goals of the Vision for Space Exploration, Ares I is a chief component of the cost-effective space transportation infrastructure being developed by NASA's Constellation Program. This transportation system will safely and reliably carry human explorers back to the moon, and then onward to Mars and other destinations in the solar system. The Ares I effort includes multiple project element teams at NASA centers and contract organizations around the nation, and is managed by the Exploration Launch Projects Office at NASA's Marshall Space Flight Center (MFSC). ATK Launch Systems near Brigham City, Utah, is the prime contractor for the first stage booster. ATK's subcontractor, United Space Alliance of Houston, is designing, developing and testing the parachutes at its facilities at NASA's Kennedy Space Center in Florida. NASA's Johnson Space Center in Houston hosts the Constellation Program and Orion Crew Capsule Project Office and provides test instrumentation and support personnel. Together, these teams are developing vehicle hardware, evolving proven technologies, and testing components and systems. Their work builds on powerful, reliable space shuttle propulsion elements and nearly a half-century of NASA space flight experience and technological advances. Ares I is an inline, two-stage rocket configuration topped by the Crew Exploration Vehicle, its service module, and a launch abort system. This HD video image, depicts a manufactured aluminum panel, that will be used to fabricate the Ares I upper stage barrel, undergoing a confidence panel test. In this test, the bent aluminum is stressed to breaking point and thoroughly examined. The panels are manufactured by AMRO Manufacturing located in El Monte, California. (Highest resolution available)

Launch Vehicles

NASA Image and Video Library

2007-08-09

Under the goals of the Vision for Space Exploration, Ares I is a chief component of the cost-effective space transportation infrastructure being developed by NASA's Constellation Program. This transportation system will safely and reliably carry human explorers back to the moon, and then onward to Mars and other destinations in the solar system. The Ares I effort includes multiple project element teams at NASA centers and contract organizations around the nation, and is managed by the Exploration Launch Projects Office at NASA's Marshall Space Flight Center (MFSC). ATK Launch Systems near Brigham City, Utah, is the prime contractor for the first stage booster. ATK's subcontractor, United Space Alliance of Houston, is designing, developing and testing the parachutes at its facilities at NASA's Kennedy Space Center in Florida. NASA's Johnson Space Center in Houston hosts the Constellation Program and Orion Crew Capsule Project Office and provides test instrumentation and support personnel. Together, these teams are developing vehicle hardware, evolving proven technologies, and testing components and systems. Their work builds on powerful, reliable space shuttle propulsion elements and nearly a half-century of NASA space flight experience and technological advances. Ares I is an inline, two-stage rocket configuration topped by the Crew Exploration Vehicle, its service module, and a launch abort system. This HD video image depicts a manufactured aluminum panel, that will fabricate the Ares I upper stage barrel, undergoing a confidence panel test. In this test, the bent aluminum is stressed to breaking point and thoroughly examined. The panels are manufactured by AMRO Manufacturing located in El Monte, California. (Highest resolution available)

Launch Vehicles

NASA Image and Video Library

2006-08-08

Under the goals of the Vision for Space Exploration, Ares I is a chief component of the cost-effective space transportation infrastructure being developed by NASA's Constellation Program. This transportation system will safely and reliably carry human explorers back to the moon, and then onward to Mars and other destinations in the solar system. The Ares I effort includes multiple project element teams at NASA centers and contract organizations around the nation, and is managed by the Exploration Launch Projects Office at NASA's Marshall Space Flight Center (MFSC). ATK Launch Systems near Brigham City, Utah, is the prime contractor for the first stage booster. ATK's subcontractor, United Space Alliance of Houston, is designing, developing and testing the parachutes at its facilities at NASA's Kennedy Space Center in Florida. NASA's Johnson Space Center in Houston hosts the Constellation Program and Orion Crew Capsule Project Office and provides test instrumentation and support personnel. Together, these teams are developing vehicle hardware, evolving proven technologies, and testing components and systems. Their work builds on powerful, reliable space shuttle propulsion elements and nearly a half-century of NASA space flight experience and technological advances. Ares I is an inline, two-stage rocket configuration topped by the Crew Exploration Vehicle, its service module, and a launch abort system. This HD video image depicts a manufactured aluminum panel that will be used to fabricate the Ares I upper stage barrel, undergoing a confidence panel test. In this test, the bent aluminum is stressed to breaking point and thoroughly examined. The panels are manufactured by AMRO Manufacturing located in El Monte, California. (Highest resolution available)

Report of the Horizontal Launch Study

NASA Technical Reports Server (NTRS)

Wilhite, Alan W.; Bartolotta, Paul A.

2011-01-01

A study of horizontal launch concepts has been conducted. This study, jointly sponsored by the Defense Advanced Research Projects Agency (DARPA) and the National Aeronautics and Space Administration (NASA) was tasked to estimate the economic and technical viability of horizontal launch approaches. The study team identified the key parameters and critical technologies which determine mission viability and reported on the state of the art of critical technologies, along with objectives for technology development.

SPIDER Readied for Launch

NASA Image and Video Library

2015-01-22

Prior to launch, the team laid out the parachute and hang lines in front of SPIDER, seen in the distance. The long-duration balloon that would carry SPIDER into the sky is attached to the end of the parachute shown here in the foreground. http://photojournal.jpl.nasa.gov/catalog/PIA19177

Use of Smoothed Measured Winds to Predict and Assess Launch Environments

NASA Technical Reports Server (NTRS)

Cordova, Henry S.; Leahy, Frank; Adelfang, Stanley; Roberts, Barry; Starr, Brett; Duffin, Paul; Pueri, Daniel

2011-01-01

Since many of the larger launch vehicles are operated near their design limits during the ascent phase of flight to optimize payload to orbit, it often becomes necessary to verify that the vehicle will remain within certification limits during the ascent phase as part of the go/no-go review made prior to launch. This paper describes the approach used to predict Ares I-X launch vehicle structural air loads and controllability prior to launch which represents a distinct departure from the methodology of the Space Shuttle and Evolved Expendable Launch Vehicle (EELV) programs. Protection for uncertainty of key environment and trajectory parameters is added to the nominal assessment of launch capability to ensure that critical launch trajectory variables would be within the integrated vehicle certification envelopes. This process was applied by the launch team as a key element of the launch day go/no-go recommendation. Pre-launch assessments of vehicle launch capability for NASA's Space Shuttle and the EELV heavy lift versions require the use of a high-resolution wind profile measurements, which have relatively small sample size compared with low-resolution profile databases (which include low-resolution balloons and radar wind profilers). The approach described in this paper has the potential to allow the pre-launch assessment team to use larger samples of wind measurements from low-resolution wind profile databases that will improve the accuracy of pre-launch assessments of launch availability with no degradation of mission assurance or launch safety.

Students Compete in NASA's Student Launch Competition

NASA Image and Video Library

2018-03-30

NASA's Student Launch competition challenges middle school, high school and college teams to design, build, test and fly a high-powered, reusable rocket to an altitude of one mile above ground level while carrying a payload. During the eight-month process, the selected teams will go through a series of design, test and readiness reviews that resemble the real-world process of rocket development. In addition to building and preparing their rocket and payload, the teams must also create and execute an education and outreach program that will share their work with their communities and help inspire the next generation of scientists, engineers and explorers. Student Launch is hosted by NASA's Marshall Space Flight Center in Huntsville, Alabama, and is managed by Marshall's Academic Affairs Office to further NASA’s major education goal of attracting and encouraging students to pursue degrees and careers in the STEM fields of science, technology, engineering and mathematics.

Ceremony celebrates 50 years of rocket launches

NASA Technical Reports Server (NTRS)

2000-01-01

Ceremony celebrates 50 years of rocket launches PL00C-10364.16 At the 50th anniversary ceremony celebrating the first rocket launch from what is now Cape Canaveral Air Force Station, Brig. Gen. Donald Pettit addresses an audience that included members of the team who successfully launched the first rocket, known as Bumper 8. The ceremony was hosted by the Air Force Space & Missile Museum Foundation, Inc. , and included launch of a Bumper 8 model rocket, presentation of a Bumper Award to Florida Sen. George Kirkpatrick by the National Space Club; plus remarks by Sen. Kirkpatrick, KSC's Center Director Roy Bridges, and Pettit. A reception followed at Hangar C. Since 1950 there have been a total of 3,245 launches from Cape Canaveral.

KSC-07pd3597

NASA Image and Video Library

2007-12-09

KENNEDY SPACE CENTER, FLA. -- Bill Gerstenmaier, associate administrator for Space Operations, participates in a news briefing following the conclusion of a Mission Management Team, or MMT, meeting. The meeting followed the morning's launch scrub of the space shuttle Atlantis STS-122 mission caused by problems experienced with the external tank's engine cutoff sensor system during tanking for the second launch attempt. An announcement was made during the briefing that the STS-122 launch is postponed to no earlier than Jan. 2, 2008, to give the team time to resolve the system's problems. Atlantis will carry the Columbus Laboratory, the European Space Agency's largest contribution to the construction of the International Space Station. It will support scientific and technological research in a microgravity environment. Permanently attached to the Harmony node of the space station, the laboratory will carry out experiments in materials science, fluid physics and biosciences, as well as perform a number of technological applications. Photo credit: NASA/Kim Shiflett

Improving Care Teams' Functioning: Recommendations from Team Science.

PubMed

Fiscella, Kevin; Mauksch, Larry; Bodenheimer, Thomas; Salas, Eduardo

2017-07-01

Team science has been applied to many sectors including health care. Yet there has been relatively little attention paid to the application of team science to developing and sustaining primary care teams. Application of team science to primary care requires adaptation of core team elements to different types of primary care teams. Six elements of teams are particularly relevant to primary care: practice conditions that support or hinder effective teamwork; team cognition, including shared understanding of team goals, roles, and how members will work together as a team; leadership and coaching, including mutual feedback among members that promotes teamwork and moves the team closer to achieving its goals; cooperation supported by an emotionally safe climate that supports expression and resolution of conflict and builds team trust and cohesion; coordination, including adoption of processes that optimize efficient performance of interdependent activities among team members; and communication, particularly regular, recursive team cycles involving planning, action, and debriefing. These six core elements are adapted to three prototypical primary care teams: teamlets, health coaching, and complex care coordination. Implementation of effective team-based models in primary care requires adaptation of core team science elements coupled with relevant, practical training and organizational support, including adequate time to train, plan, and debrief. Training should be based on assessment of needs and tasks and the use of simulations and feedback, and it should extend to live action. Teamlets represent a potential launch point for team development and diffusion of teamwork principles within primary care practices. Copyright © 2017 The Joint Commission. Published by Elsevier Inc. All rights reserved.

Launch Vehicles

NASA Image and Video Library

2007-08-09

Under the goals of the Vision for Space Exploration, Ares I is a chief component of the cost-effective space transportation infrastructure being developed by NASA's Constellation Program. This transportation system will safely and reliably carry human explorers back to the moon, and then onward to Mars and other destinations in the solar system. The Ares I effort includes multiple project element teams at NASA centers and contract organizations around the nation, and is managed by the Exploration Launch Projects Office at NASA's Marshall Space Flight Center (MFSC). ATK Launch Systems near Brigham City, Utah, is the prime contractor for the first stage booster. ATK's subcontractor, United Space Alliance of Houston, is designing, developing and testing the parachutes at its facilities at NASA's Kennedy Space Center in Florida. NASA's Johnson Space Center in Houston hosts the Constellation Program and Orion Crew Capsule Project Office and provides test instrumentation and support personnel. Together, these teams are developing vehicle hardware, evolving proven technologies, and testing components and systems. Their work builds on powerful, reliable space shuttle propulsion elements and nearly a half-century of NASA space flight experience and technological advances. Ares I is an inline, two-stage rocket configuration topped by the Crew Exploration Vehicle, its service module, and a launch abort system. This HD video image depicts the preparation and placement of a confidence ring for friction stir welding used in manufacturing aluminum panels that will fabricate the Ares I upper stage barrel. The aluminum panels are manufactured and subjected to confidence tests during which the bent aluminum is stressed to breaking point and thoroughly examined. The panels are manufactured by AMRO Manufacturing located in El Monte, California. (Highest resolution available)

Launch Vehicles

NASA Image and Video Library

2007-09-09

Under the goals of the Vision for Space Exploration, Ares I is a chief component of the cost-effective space transportation infrastructure being developed by NASA's Constellation Program. This transportation system will safely and reliably carry human explorers back to the moon, and then onward to Mars and other destinations in the solar system. The Ares I effort includes multiple project element teams at NASA centers and contract organizations around the nation, and is managed by the Exploration Launch Projects Office at NASA's Marshall Space Flight Center (MFSC). ATK Launch Systems near Brigham City, Utah, is the prime contractor for the first stage booster. ATK's subcontractor, United Space Alliance of Houston, is designing, developing and testing the parachutes at its facilities at NASA's Kennedy Space Center in Florida. NASA's Johnson Space Center in Houston hosts the Constellation Program and Orion Crew Capsule Project Office and provides test instrumentation and support personnel. Together, these teams are developing vehicle hardware, evolving proven technologies, and testing components and systems. Their work builds on powerful, reliable space shuttle propulsion elements and nearly a half-century of NASA space flight experience and technological advances. Ares I is an inline, two-stage rocket configuration topped by the Crew Exploration Vehicle, its service module, and a launch abort system. In this HD video image, the first stage reentry parachute drop test is conducted at the Yuma, Arizona proving ground. The parachute tests demonstrated a three-stage deployment sequence that included the use of an Orbiter drag chute to properly stage the unfurling of the main chute. The parachute recovery system for Orion will be similar to the system used for Apollo command module landings and include two drogue, three pilot, and three main parachutes. (Highest resolution available)

Launch Vehicles

NASA Image and Video Library

2006-09-09

Under the goals of the Vision for Space Exploration, Ares I is a chief component of the cost-effective space transportation infrastructure being developed by NASA's Constellation Program. This transportation system will safely and reliably carry human explorers back to the moon, and then onward to Mars and other destinations in the solar system. The Ares I effort includes multiple project element teams at NASA centers and contract organizations around the nation, and is managed by the Exploration Launch Projects Office at NASA's Marshall Space Flight Center (MFSC). ATK Launch Systems near Brigham City, Utah, is the prime contractor for the first stage booster. ATK's subcontractor, United Space Alliance of Houston, is designing, developing and testing the parachutes at its facilities at NASA's Kennedy Space Center in Florida. NASA's Johnson Space Center in Houston hosts the Constellation Program and Orion Crew Capsule Project Office and provides test instrumentation and support personnel. Together, these teams are developing vehicle hardware, evolving proven technologies, and testing components and systems. Their work builds on powerful, reliable space shuttle propulsion elements and nearly a half-century of NASA space flight experience and technological advances. Ares I is an inline, two-stage rocket configuration topped by the Crew Exploration Vehicle, its service module, and a launch abort system. In this HD video image, the first stage reentry parachute drop test is conducted at the Yuma, Arizona proving ground. The parachute tests demonstrated a three-stage deployment sequence that included the use of an Orbiter drag chute to properly stage the unfurling of the main chute. The parachute recovery system for Orion will be similar to the system used for Apollo command module landings and include two drogue, three pilot, and three main parachutes. (Highest resolution available)

Next Generation Heavy-Lift Launch Vehicle: Large Diameter, Hydrocarbon-Fueled Concepts

NASA Technical Reports Server (NTRS)

Holliday, Jon; Monk, Timothy; Adams, Charles; Campbell, Ricky

2012-01-01

With the passage of the 2010 NASA Authorization Act, NASA was directed to begin the development of the Space Launch System (SLS) as a follow-on to the Space Shuttle Program. The SLS is envisioned as a heavy lift launch vehicle that will provide the foundation for future large-scale, beyond low Earth orbit (LEO) missions. Supporting the Mission Concept Review (MCR) milestone, several teams were formed to conduct an initial Requirements Analysis Cycle (RAC). These teams identified several vehicle concept candidates capable of meeting the preliminary system requirements. One such team, dubbed RAC Team 2, was tasked with identifying launch vehicles that are based on large stage diameters (up to the Saturn V S-IC and S-II stage diameters of 33 ft) and utilize high-thrust liquid oxygen (LOX)/RP engines as a First Stage propulsion system. While the trade space for this class of LOX/RP vehicles is relatively large, recent NASA activities (namely the Heavy Lift Launch Vehicle Study in late 2009 and the Heavy Lift Propulsion Technology Study of 2010) examined specific families within this trade space. Although the findings from these studies were incorporated in the Team 2 activity, additional branches of the trade space were examined and alternative approaches to vehicle development were considered. Furthermore, Team 2 set out to define a highly functional, flexible, and cost-effective launch vehicle concept. Utilizing this approach, a versatile two-stage launch vehicle concept was chosen as a preferred option. The preferred vehicle option has the capability to fly in several different configurations (e.g. engine arrangements) that gives this concept an inherent operational flexibility which allows the vehicle to meet a wide range of performance requirements without the need for costly block upgrades. Even still, this concept preserves the option for evolvability should the need arise in future mission scenarios. The foundation of this conceptual design is a focus on low

Students Participate in Rocket Launch Project

NASA Technical Reports Server (NTRS)

2002-01-01

Filled with anticipation, students from three Huntsville area high schools: Randolph, Sparkman, and Johnson High Schools, counted down to launch the rockets they designed and built at the Army test site on Redstone Arsenal in Huntsville, Alabama. The projected two-mile high launch culminated more than a year's work and demonstrated the student team's ability to meet the challenge set by the Marshall Space Flight Center's (MSFC) Student Launch Initiative (SLI) program to apply science and math to experience, judgment, and common sense, and proved to NASA officials that they have successfully built reusable launch vehicles (RLVs), another challenge set by NASA's SLI program. MSFC's SLI program is an educational effort that aims to motivate students to pursue careers in science, math, and engineering. It provides hands-on, practical aerospace experience. In this picture, Randolph High School students are assembling their rocket in preparation for launch.

Ceremony celebrates 50 years of rocket launches

NASA Technical Reports Server (NTRS)

2000-01-01

Ceremony celebrates 50 years of rocket launches PL00C-10364.21 At the 50th anniversary ceremony celebrating the first rocket launch from pad 3 on what is now Cape Canaveral Air Force Station, KSC's Center Director Roy Bridges Jr. addresses an audience that included members of the team who successfully launched the first rocket, known as Bumper 8. The original launch occurred July 24, 1950. The anniversary ceremony was hosted by the Air Force Space & Missile Museum Foundation, Inc., and included launch of a Bumper 8 model rocket, presentation of a Bumper Award to Florida Sen. George Kirkpatrick by the National Space Club; plus remarks by Sen. Kirkpatrick, Bridges, and the Commander of the 45th Space Wing, Brig. Gen. Donald Pettit. A reception followed at Hangar C. Since 1950 there have been a total of 3,245 launches from Cape Canaveral.

Lunar launch and landing facilities and operations

NASA Technical Reports Server (NTRS)

1987-01-01

The Florida Institute of Technology established an Interdisciplinary Design Team to design a lunar based facility whose primary function involves launch and landing operations for future moon missions. Both manned and unmanned flight operations were considered in the study with particular design emphasis on the utilization (or reutilization) of all materials available on the moon. This resource availability includes man-made materials which might arrive in the form of expendable landing vehicles as well as in situ lunar minerals. From an engineering standpoint, all such materials are considered as to their suitability for constructing new lunar facilities and/or repairing or expanding existing structures. Also considered in this design study was a determination of the feasibility of using naturally occurring lunar materials to provide fuel components to support lunar launch operations. Conventional launch and landing operations similar to those used during the Apollo Program were investigated as well as less conventional techniques such as rail guns and electromagnetic mass drivers. The Advanced Space Design team consisted of students majoring in Physics and Space Science as well as Electrical, Mechanical, Chemical and Ocean Engineering.

2018 NASA Student Launch event, Bragg Farms, Toney, Al

NASA Image and Video Library

2018-04-10

After eight months of designing, building and testing, the middle school, high school and college and university teams launched their rockets as part of NASA Student Launch on Sunday, April 8. The rockets and their payloads are designed to fly to 1-mile in altitude before deploying recovery systems that brings them safely to the ground.

2018 NASA Student Launch event, Bragg Farms, Toney, Al

NASA Image and Video Library

2018-04-09

After eight months of designing, building and testing, the middle school, high school and college and university teams launched their rockets as part of NASA Student Launch on Sunday, April 8. The rockets and their payloads are designed to fly to 1-mile in altitude before deploying recovery systems that brings them safely to the ground.

Pegasus XL CYGNSS Second Launch Attempt

NASA Image and Video Library

2016-12-15

In the Mission Director's Center at Cape Canaveral Air Force Station, members of the launch team monitor the progress of preparations to launch eight Cyclone Global Navigation Satellite System, or CYGNSS, spacecraft. The CYGNSS satellites will make frequent and accurate measurements of ocean surface winds throughout the life cycle of tropical storms and hurricanes. The data that CYGNSS provides will enable scientists to probe key air-sea interaction processes that take place near the core of storms, which are rapidly changing and play a crucial role in the beginning and intensification of hurricanes.

Aerials of Orion on Launch Pad 37 from Helicopter

NASA Image and Video Library

2014-12-04

This helicopter view of the Kennedy Space Center Visitor Complex shows the thousands of vehicles parked where guests gather to see the launch of the Orion Flight Test. The liftoff was postponed because of an issue related to fill and drain valves on the Delta IV Heavy rocket that teams could not troubleshoot by the time the launch window expired.

HISTORY AND ACCOMPLISHMENTS OF THE US EPA'S SUPERFUND INNOVATIVE TECHNOLOGY EVALUATION (SITE) MONITORING AND MEASUREMENT (MMT) PROGRAM

EPA Science Inventory

This manuscript presents the history and evolution of the U.S. Environmental Protection Agency's (EPA) Superfund Innovative Technology Evaluation (SITE) Monitoring and Measurement Technology (MMT) Program. This includes a discussion of how the fundamental concepts of a performanc...

Students Participate in Rocket Launch Project

NASA Technical Reports Server (NTRS)

2002-01-01

Filled with anticipation, students from three Huntsville area high schools: Randolph, Sparkman, and Johnson High Schools, counted down to launch the rockets they designed and built at the Army test site on Redstone Arsenal in Huntsville, Alabama. The projected two-mile high launch culminated more than a year's work and demonstrated the student team's ability to meet the challenge set by the Marshall Space Flight Center's (MSFC) Student Launch Initiative (SLI) program to apply science and math to experience, judgment, and common sense, and proved to NASA officials that they have successfully built reusable launch vehicles (RLVs), another challenge set by NASA's SLI program. MSFC's SLI program is an educational effort that aims to motivate students to pursue careers in science, math, and engineering. It provides them with hands-on, practical aerospace experience. In this picture, three Sparkman High School students pose with their rocket.

Students Participate in Rocket Launch Project

NASA Technical Reports Server (NTRS)

2002-01-01

Filled with anticipation, students from three Huntsville area high schools: Randolph, Sparkman and Johnson High Schools, counted down to launch the rockets they designed and built at the Army test site on Redstone Arsenal in Huntsville, Alabama. The projected two-mile high launch culminated more than a year's work and demonstrated the student team's ability to meet the challenge set by the Marshall Space Flight Center's (MSFC) Student Launch Initiative (SLI) program to apply science and math to experience, judgment, and common sense, and proved to NASA officials that they have successfully built reusable launch vehicles (RLVs), another challenge set by NASA's SLI program. MSFC's SLI program is an educational effort that aims to motivate students to pursue careers in science, math, and engineering. It provides them with hands-on, practical aerospace experience. In this picture, two Johnson High School students pose with their rocket.

Students Participate in Rocket Launch Project

NASA Technical Reports Server (NTRS)

2002-01-01

Filled with anticipation, students from three Huntsville area high schools: Randolph, Sparkman, and Johnson High Schools, counted down to launch the rockets they designed and built at the Army test site on Redstone Arsenal in Huntsville, Alabama. The projected two-mile high launch culminated more than a year's work and demonstrated the student team's ability to meet the challenge set by the Marshall Space Flight Center's (MSFC) Student Launch Initiative program to apply science and math to experience, judgment, and common sense, and proved to NASA officials that they have successfully built reusable launch vehicles (RLVs), another challenge set by NASA's SLI program. MSFC's SLI program is an educational effort that aims to motivate students to pursue careers in science, math, and engineering. It provides hands-on, practical aerospace experience. In this picture, a rocket built by Johnson High School students soars to it projected designation.

NASA's Space Launch System: Momentum Builds Towards First Launch

NASA Technical Reports Server (NTRS)

May, Todd; Lyles, Garry

2014-01-01

of economic challenges, the nationwide SLS team continues to meet ambitious budget and schedule targets through the studied use of hardware, infrastructure, and workforce investments the United States has already made in the last half century, while selectively using new technologies for design, manufacturing, and testing, as well as streamlined management approaches that have increased decision velocity and reduced associated costs. This paper will summarize recent SLS Program technical accomplishments, as well as the challenges and opportunities ahead for the most powerful and capable launch vehicle in history.

Students Participate in Rocket Launch Project

NASA Technical Reports Server (NTRS)

2002-01-01

Filled with anticipation, students from two local universities, the University of Alabama in Huntsville (UAH), and Alabama Agricultural Mechanical University (AM), counted down to launch the rockets they designed and built at the Army test site on Redstone Arsenal in Huntsville, Alabama. The projected two-mile high launch culminated more than a year's work and demonstrated the student team's ability to meet the challenge set by the Marshall Space Flight Center's (MSFC) Student Launch Initiative (SLI) program to apply science and math to experience, judgment, and common sense, and proved to NASA officials that they have successfully built reusable launch vehicles (RLVs), another challenge set by NASA's SLI program. MSFC's SLI program is an educational effort that aims to motivate students to pursue careers in science, math, and engineering. It provides the students with hands-on, practical aerospace experience. UAH students designed and built the rocket and AM students designed the payload. In this picture, AM students prepare their payload, an experiment that measures the amount of hydrogen produced during electroplating with nickel in a brief period of micrgravity, prior to launch.

Students Participate in Rocket Launch Project

NASA Technical Reports Server (NTRS)

2002-01-01

Filled with anticipation, students from two local universities, the University of Alabama in Huntsville (UAH), and Alabama Agricultural Mechanical University (AM), counted down to launch the rockets they designed and built at the Army test site on Redstone Arsenal in Huntsville, Alabama. The projected two-mile high launch culminated more than a year's work and demonstrated the student team's ability to meet the challenge set by the Marshall Space Flight Center's (MSFC) Student Launch Initiative (SLI) program to apply science and math to experience, judgment, and common sense, and proved to NASA officials that they have successfully built reusable launch vehicles (RLVs), another challenge set by NASA's SLI program. MSFC's SLI program is an educational effort that aims to motivate students to pursue careers in science, math, and engineering. It provides the students with hands-on, practical aerospace experience. In this picture, the University students prepare their rocket for launch. Students at UAH built the rocket and AM students developed its scientific payload, an experiment that measures the amount of hydrogen produced during electroplating with nickel in a brief period of micrgravity.

Launching a world-class joint venture.

PubMed

Bamford, James; Ernst, David; Fubini, David G

2004-02-01

More than 5,000 joint ventures, and many more contractual alliances, have been launched worldwide in the past five years. Companies are realizing that JVs and alliances can be lucrative vehicles for developing new products, moving into new markets, and increasing revenues. The problem is, the success rate for JVs and alliances is on a par with that for mergers and acquisitions--which is to say not very good. The authors, all McKinsey consultants, argue that JV success remains elusive for most companies because they don't pay enough attention to launch planning and execution. Most companies are highly disciplined about integrating the companies they target through M&A, but they rarely commit sufficient resources to launching similarly sized joint ventures or alliances. As a result, the parent companies experience strategic conflicts, governance gridlock, and missed operational synergies. Often, they walk away from the deal. The launch phase begins with the parent companies' signing of a memorandum of understanding and continues through the first 100 days of the JV or alliance's operation. During this period, it's critical for the parents to convene a team dedicated to exposing inherent tensions early. Specifically, the launch team must tackle four basic challenges. First, build and maintain strategic alignment across the separate corporate entities, each of which has its own goals, market pressures, and shareholders. Second, create a shared governance system for the two parent companies. Third, manage the economic interdependencies between the corporate parents and the JV. And fourth, build a cohesive, high-performing organization (the JV or alliance)--not a simple task, since most managers come from, will want to return to, and may even hold simultaneous positions in the parent companies. Using real-world examples, the authors offer their suggestions for meeting these challenges.

NASA's Space Launch System: Momentum Builds Toward First Launch

NASA Technical Reports Server (NTRS)

May, Todd A.; Lyles, Garry M.

2014-01-01

NASA's Space Launch System (SLS) is gaining momentum toward the first launch of a new exploration-class heavy lift launch vehicle for international exploration and science initiatives. The SLS comprises an architecture that begins with a vehicle capable of launching 70 metric tons (t) into low Earth orbit. It will launch the Orion Multi-Purpose Crew Vehicle (MPCV) on its first autonomous flight beyond the Moon and back in December 2017. Its first crewed flight follows in 2021. SLS can evolve to a130-t lift capability and serve as a baseline for numerous robotic and human missions ranging from a Mars sample return to delivering the first astronauts to explore another planet. The SLS Program formally transitioned from the formulation phase to implementation with the successful completion of the rigorous Key Decision Point C review in 2014. As a result, the Agency authorized the Program to move forward to Critical Design Review, scheduled for 2015. In the NASA project life cycle process, SLS has completed 50 percent of its major milestones toward first flight. Every SLS element manufactured development hardware for testing over the past year. Accomplishments during 2013/2014 included manufacture of core stage test articles, preparations for qualification testing the solid rocket boosters and the RS-25 main engines, and shipment of the first flight hardware in preparation for the Exploration Flight Test-1 (EFT-1) in 2014. SLS was conceived with the goals of safety, affordability, and sustainability, while also providing unprecedented capability for human exploration and scientific discovery beyond Earth orbit. In an environment of economic challenges, the SLS team continues to meet ambitious budget and schedule targets through the studied use of hardware, infrastructure, and workforce investments the United States made in the last half century, while selectively using new technologies for design, manufacturing, and testing, as well as streamlined management approaches

Use of DES Modeling for Determining Launch Availability for SLS

NASA Technical Reports Server (NTRS)

Watson, Michael; Staton, Eric; Cates, Grant; Finn, Ronald; Altino, Karen M.; Burns, K. Lee

2014-01-01

(1) NASA is developing a new heavy lift launch system for human and scientific exploration beyond Earth orbit comprising of the Space Launch System (SLS), Orion Multi-Purpose Crew Vehicle (MPCV), and Ground Systems Development and Operations (GSDO); (2) The desire of the system is to ensure a high confidence of successfully launching the exploration missions, especially those that require multiple launches, have a narrow Earth departure window, and high investment costs; and (3) This presentation discusses the process used by a Cross-Program team to develop the Exploration Systems Development (ESD) Launch Availability (LA) Technical Performance Measure (TPM) and allocate it to each of the Programs through the use of Discrete Event Simulations (DES).

NASA’s BARREL Mission Launches 20 Balloons

NASA Image and Video Library

2017-12-08

The BARREL team at the SANAE IV research station celebrates their final launch in the Antarctica sun. Credit: NASA --- In Antarctica in January, 2013 – the summer at the South Pole – scientists launched 20 balloons up into the air to study an enduring mystery of space weather: when the giant radiation belts surrounding Earth lose material, where do the extra particles actually go? The mission is called BARREL (Balloon Array for Radiation belt Relativistic Electron Losses) and it is led by physicist Robyn Millan of Dartmouth College in Hanover, NH. Millan provided photographs from the team’s time in Antarctica. The team launched a balloon every day or two into the circumpolar winds that circulate around the pole. Each balloon floated for anywhere from 3 to 40 days, measuring X-rays produced by fast-moving electrons high up in the atmosphere. BARREL works hand in hand with another NASA mission called the Van Allen Probes, which travels through the Van Allen radiation belts surrounding Earth. The belts wax and wane over time in response to incoming energy and material from the sun, sometimes intensifying the radiation through which satellites must travel. Scientists wish to understand this process better, and even provide forecasts of this space weather, in order to protect our spacecraft. As the Van Allen Probes were observing what was happening in the belts, BARREL tracked electrons that precipitated out of the belts and hurtled down Earth’s magnetic field lines toward the poles. By comparing data, scientists will be able to track how what’s happening in the belts correlates to the loss of particles – information that can help us understand this mysterious, dynamic region that can impact spacecraft. Having launched balloons in early 2013, the team is back at home building the next set of payloads. They will launch 20 more balloons in 2014. NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors

Launch Control Network Engineer

NASA Technical Reports Server (NTRS)

Medeiros, Samantha

2017-01-01

The Spaceport Command and Control System (SCCS) is being built at the Kennedy Space Center in order to successfully launch NASA’s revolutionary vehicle that allows humans to explore further into space than ever before. During my internship, I worked with the Network, Firewall, and Hardware teams that are all contributing to the huge SCCS network project effort. I learned the SCCS network design and the several concepts that are running in the background. I also updated and designed documentation for physical networks that are part of SCCS. This includes being able to assist and build physical installations as well as configurations. I worked with the network design for vehicle telemetry interfaces to the Launch Control System (LCS); this allows the interface to interact with other systems at other NASA locations. This network design includes the Space Launch System (SLS), Interim Cryogenic Propulsion Stage (ICPS), and the Orion Multipurpose Crew Vehicle (MPCV). I worked on the network design and implementation in the Customer Avionics Interface Development and Analysis (CAIDA) lab.

NASA’s First Nations Launch Bolsters Skills, Broadens Horizons For Tribal Students

NASA Image and Video Library

2017-04-20

Fifteen teams of STEM-minded students from 14 tribal and other U.S. colleges and universities competed in NASA’s Eighth Annual First Nations Launch Competition, or FNL, hosted at Carthage College in Kenosha, Wisconsin, on April 20 – 22, 2017. The three-day event, featuring technical workshops, design-sharing and a spirit of collaboration, culminated on Saturday, April 22, at the Richard Bong Recreation Area in nearby Kansasville, Wisconsin, where teams gathered to launch the high-powered rockets they’d designed and built this school year. FNL empowers Native American college students to pursue academic and professional opportunities in STEM and other fields. First Nations Launch is a STEM Education and Accountability Project (SEAP) managed at the Kennedy Space Center through the Wisconsin Space Grant Consortium located at Carthage College in Kenosha, Wisconsin.

Students Participate in Rocket Launch Project

NASA Technical Reports Server (NTRS)

2002-01-01

Filled with anticipation, students from two local universities, the University of Alabama in Huntsville (UAH), and Alabama Agricultural Mechanical University (AM), counted down to launch the rockets they designed and built at the Army test site on Redstone Arsenal in Huntsville, Alabama. The projected two-mile high launch culminated more than a year's work and demonstrated the student team's ability to meet the challenge set by the Marshall Space Flight Center's (MSFC) Student Launch Initiative (SLI) Program to apply science and math to experience, judgment, and common sense, and proved to NASA officials that they have successfully built reusable launch vehicles (RLVs), another challenge set by NASA's SLI program. MSFC's SLI program is an educational effort that aims to motivate students to pursue careers in science, math, and engineering. It provides the students with hands-on, practical aerospace experience. In this picture, the university students prepare their rocket for flight on the launch pad. Students at UAH built the rocket and AM students developed its scientific payload, an experiment that measures the amount of hydrogen produced during electroplating with nickel in a brief period of micrgravity.

Hunting for extremely metal-poor emission-line galaxies in the Sloan Digital Sky Survey: MMT and 3.5 m APO observations

NASA Astrophysics Data System (ADS)

Izotov, Y. I.; Thuan, T. X.; Guseva, N. G.

2012-10-01

We present 6.5-m MMT and 3.5 m APO spectrophotometry of 69 H ii regions in 42 low-metallicity emission-line galaxies, selected from the data release 7 of the Sloan Digital Sky Survey to have mostly [O iii]λ4959/Hβ ≲ 1 and [N ii]λ6583/Hβ ≲ 0.1. The electron temperature-sensitive emission line [O iii] λ4363 is detected in 53 H ii regions allowing a direct abundance determination. The oxygen abundance in the remaining 16 H ii regions is derived using a semi-empirical method. The oxygen abundance of the galaxies in our sample ranges from 12 + log O/H ~ 7.1 to ~7.9, with 14 H ii regions in 7 galaxies with 12 + log O/H ≤ 7.35. In 5 of the latter galaxies, the oxygen abundance is derived here for the first time. Including other known extremely metal-deficient emission-line galaxies from the literature, e.g. SBS 0335-052W, SBS 0335-052E and I Zw 18, we have compiled a sample of the 17 most metal-deficient (with 12 + log O/H ≤ 7.35) emission-line galaxies known in the local universe. There appears to be a metallicity floor at 12 + log O/H ~ 6.9, suggesting that the matter from which dwarf emission-line galaxies formed was pre-enriched to that level by e.g. Population III stars. Based on observations with the Multiple Mirror telescope (MMT) and the 3.5 m Apache Point Observatory (APO). The MMT is operated by the MMT Observatory (MMTO), a joint venture of the Smithsonian Institution and the University of Arizona. The Apache Point Observatory 3.5-m telescope is owned and operated by the Astrophysical Research Consortium.Figures 1-3 and Tables 2-8 are available in electronic form at http://www.aanda.org

Use of a Fourier transform spectrometer on a balloon-borne telescope and at the multiple mirror telescope (MMT)

NASA Technical Reports Server (NTRS)

Traub, W. A.; Chance, K. V.; Brasunas, J. C.; Vrtilek, J. M.; Carleton, N. P.

1982-01-01

The design and use of an infrared Fourier transform spectrometer which has been used for observations of laboratory, stratospheric, and astronomical spectra are described. The spectrometer has a spectral resolution of 0.032/cm and has operated in the mid-infrared (12 to 13 microns) as well as the far-infrared (40 to 140 microns), using both bolometer and photoconductor cryogenic detectors. The spectrometer is optically sized to accept an f/9 beam from the multi-mirror telescope (MMT). The optical and electronic design are discussed, including remote operation of the spectrometer on a balloon-borne 102-cm telescope. The performance of the laser-controlled, screw-driven moving cat's-eye mirror is discussed. Segments of typical far-infrared balloon flight spectra, lab spectra, and mid-infrared MMT spectra are presented. Data reduction, interferogram processing, artifact removal, wavelength calibration, and intensity calibration methods are discussed. Future use of the spectrometer is outlined.

The Launch Systems Operations Cost Model

NASA Technical Reports Server (NTRS)

Prince, Frank A.; Hamaker, Joseph W. (Technical Monitor)

2001-01-01

One of NASA's primary missions is to reduce the cost of access to space while simultaneously increasing safety. A key component, and one of the least understood, is the recurring operations and support cost for reusable launch systems. In order to predict these costs, NASA, under the leadership of the Independent Program Assessment Office (IPAO), has commissioned the development of a Launch Systems Operations Cost Model (LSOCM). LSOCM is a tool to predict the operations & support (O&S) cost of new and modified reusable (and partially reusable) launch systems. The requirements are to predict the non-recurring cost for the ground infrastructure and the recurring cost of maintaining that infrastructure, performing vehicle logistics, and performing the O&S actions to return the vehicle to flight. In addition, the model must estimate the time required to cycle the vehicle through all of the ground processing activities. The current version of LSOCM is an amalgamation of existing tools, leveraging our understanding of shuttle operations cost with a means of predicting how the maintenance burden will change as the vehicle becomes more aircraft like. The use of the Conceptual Operations Manpower Estimating Tool/Operations Cost Model (COMET/OCM) provides a solid point of departure based on shuttle and expendable launch vehicle (ELV) experience. The incorporation of the Reliability and Maintainability Analysis Tool (RMAT) as expressed by a set of response surface model equations gives a method for estimating how changing launch system characteristics affects cost and cycle time as compared to today's shuttle system. Plans are being made to improve the model. The development team will be spending the next few months devising a structured methodology that will enable verified and validated algorithms to give accurate cost estimates. To assist in this endeavor the LSOCM team is part of an Agency wide effort to combine resources with other cost and operations professionals to

STS-121: Discovery Pre-Launch Mission Management Team Press Briefing

NASA Technical Reports Server (NTRS)

2006-01-01

The briefing began with Allard Buetel (NASA Public Affairs) introducing Bill Gerstenmaier (Associate Administrator for Space Operations) who provided an update of the Mission Management team meeting. The 3 criteria reviewed by the team were: a) ascent heating; b) ice formation and c) remaining foam still intact. The ascent heating had a safety factor of 5 and posed no concern. Ice formation was not a concern. In order to insure there was no damage to the remaining foam, an 8ft. pipe with a camera attached was used to provide pictures. The boroscope pictures showed there was no damage to the brackets or foam. The inspection went very well and the foam was acceptable and ready to fly. Then the floor was open to questions from the press.

NASA's Decadal Planning Team Mars Mission Analysis Summary

NASA Astrophysics Data System (ADS)

Drake, Bret G.

2007-02-01

In June 1999 the NASA Administrator chartered an internal NASA task force, termed the Decadal Planning Team, to create new integrated vision and strategy for space exploration. The efforts of the Decadal Planning Team evolved into the Agency-wide team known as the NASA Exploration Team (NEXT). This team was also instructed to identify technology roadmaps to enable the science-driven exploration vision, established a cross-Enterprise, cross-Center systems engineering team with emphasis focused on revolutionary not evolutionary approaches. The strategy of the DPT and NEXT teams was to "Go Anywhere, Anytime" by conquering key exploration hurdles of space transportation, crew health and safety, human/robotic partnerships, affordable abundant power, and advanced space systems performance. Early emphasis was placed on revolutionary exploration concepts such as rail gun and electromagnetic launchers, propellant depots, retrograde trajectories, nano structures, and gas core nuclear rockets to name a few. Many of these revolutionary concepts turned out to be either not feasible for human exploration missions or well beyond expected technology readiness for near-term implementation. During the DPT and NEXT study cycles, several architectures were analyzed including missions to the Earth-Sun Libration Point (L2), the Earth-Moon Gateway and L1, the lunar surface, Mars (both short and long stays), one-year round trip Mars, and near-Earth asteroids. Common emphasis of these studies included utilization of the Earth-Moon Libration Point (L1) as a staging point for exploration activities, current (Shuttle) and near-term launch capabilities (EELV), advanced propulsion, and robust space power. Although there was much emphasis placed on utilization of existing launch capabilities, the team concluded that missions in near-Earth space are only marginally feasible and human missions to Mars were not feasible without a heavy lift launch capability. In addition, the team concluded that

NASA's Decadal Planning Team Mars Mission Analysis Summary

NASA Technical Reports Server (NTRS)

Drake, Bret G. (Editor)

2007-01-01

In June 1999 the NASA Administrator chartered an internal NASA task force, termed the Decadal Planning Team, to create new integrated vision and strategy for space exploration. The efforts of the Decadal Planning Team evolved into the Agency-wide team known as the NASA Exploration Team (NEXT). This team was also instructed to identify technology roadmaps to enable the science-driven exploration vision, established a cross-Enterprise, cross-Center systems engineering team with emphasis focused on revolutionary not evolutionary approaches. The strategy of the DPT and NEXT teams was to "Go Anywhere, Anytime" by conquering key exploration hurdles of space transportation, crew health and safety, human/robotic partnerships, affordable abundant power, and advanced space systems performance. Early emphasis was placed on revolutionary exploration concepts such as rail gun and electromagnetic launchers, propellant depots, retrograde trajectories, nano structures, and gas core nuclear rockets to name a few. Many of these revolutionary concepts turned out to be either not feasible for human exploration missions or well beyond expected technology readiness for near-term implementation. During the DPT and NEXT study cycles, several architectures were analyzed including missions to the Earth-Sun Libration Point (L2), the Earth-Moon Gateway and L1, the lunar surface, Mars (both short and long stays), one-year round trip Mars, and near-Earth asteroids. Common emphasis of these studies included utilization of the Earth-Moon Libration Point (L1) as a staging point for exploration activities, current (Shuttle) and near-term launch capabilities (EELV), advanced propulsion, and robust space power. Although there was much emphasis placed on utilization of existing launch capabilities, the team concluded that missions in near-Earth space are only marginally feasible and human missions to Mars were not feasible without a heavy lift launch capability. In addition, the team concluded that

NASA’s Wallops Flight Facility Completes Initial Assessment after Orbital Launch Mishap

NASA Image and Video Library

2017-12-08

An aerial view of the Wallops Island launch facilities taken by the Wallops Incident Response Team Oct. 29 following the failed launch attempt of Orbital Science Corp.'s Antares rocket Oct. 28. Credit: NASA/Terry Zaperach --- The Wallops Incident Response Team completed today an initial assessment of Wallops Island, Virginia, following the catastrophic failure of Orbital Science Corp.’s Antares rocket shortly after liftoff at 6:22 p.m. EDT Tuesday, Oct. 28, from Pad 0A of the Mid-Atlantic Regional Spaceport at NASA’s Wallops Flight Facility in Virginia. “I want to praise the launch team, range safety, all of our emergency responders and those who provided mutual aid and support on a highly-professional response that ensured the safety of our most important resource -- our people,” said Bill Wrobel, Wallops director. “In the coming days and weeks ahead, we'll continue to assess the damage on the island and begin the process of moving forward to restore our space launch capabilities. There's no doubt in my mind that we will rebound stronger than ever.” The initial assessment is a cursory look; it will take many more weeks to further understand and analyze the full extent of the effects of the event. A number of support buildings in the immediate area have broken windows and imploded doors. A sounding rocket launcher adjacent to the pad, and buildings nearest the pad, suffered the most severe damage. At Pad 0A the initial assessment showed damage to the transporter erector launcher and lightning suppression rods, as well as debris around the pad. The Wallops team also met with a group of state and local officials, including the Virginia Department of Environmental Quality, the Virginia Department of Emergency Management, the Virginia Marine Police, and the U.S. Coast Guard. The Wallops environmental team also is conducting assessments at the site. Preliminary observations are that the environmental effects of the launch failure were largely contained

VizieR Online Data Catalog: The quasars MMT-BOSS pilot survey (Ross+, 2012)

NASA Astrophysics Data System (ADS)

Ross, N. P.; Myers, A. D.; Sheldon, E. S.; Yeche, C.; Strauss, M. A.; Bovy, J.; Kirkpatrick, J. A.; Richards, G. T.; Aubourg, E.; Blanton, M. R.; Brandt, W. N.; Carithers, W. C.; Croft, R. A. C.; da Silva, R.; Dawson, K.; Eisenstein, D. J.; Hennawi, J. F.; Ho, S.; Hogg, D. W.; Lee, K.-G.; Lundgren, B.; McMahon, R. G.; Miralda-Escude, J.; Palanque-Delabrouille, N.; Paris, I.; Petitjean, P.; Pieri, M. M.; Rich, J.; Roe, N. A.; Schiminovich, D.; Schlegel, D. J.; Schneider, D. P.; Slosar, A. Z.; Suzuki, N.; Tinker, J. L.; Weinberg, D. H.; Weyant, A.; White, M.; Wood-Vasey, W. M.

2012-03-01

The Sloan Digital Sky Survey is now in its third phase (SDSS-III; Eisenstein et al. 2011AJ....142...72E) and is carrying out a combination of four interleaved surveys that will continue until the summer of 2014. One of those surveys, the Baryon Oscillation Spectroscopic Survey (BOSS), commenced operations in late 2009 and is using essentially all the dark time for SDSS-III. BOSS uses the same 2.5m Sloan Foundation telescope that was used in SDSS-I/II, but since BOSS will observe fainter targets, the fiber-fed spectrographs have been significantly upgraded. These upgrades include: new CCDs with improved blue and red response; 1000 2" instead of 640 3" optical diameter fibers; higher throughput gratings over a spectral range of 3600-10000Å at a resolution of about 2000, and improved optics. Prior to the commencement of BOSS spectroscopy, we carried out spectroscopy of quasar candidates selected from co-added photometry in SDSS Stripe 82. Observations of these candidates were carried out in queue mode between 2008 September and 2009 January using the Hectospec multi-fiber spectrograph on the 6.5m Multiple Mirror Telescope (MMT). In Tables 14 and 15, we provide positions, PSF photometry (as observed, uncorrected for Galactic extinction), and redshifts for confirmed quasars from the MMT survey. Objects that are not flagged Primary in the CAS are listed separately (table 15). (2 data files).

2017 First Nations Launch Competition Winners visit Kennedy Spac

NASA Image and Video Library

2017-08-02

A group of 19 college students recently visited NASA's Kennedy Space Center as winners of the First Nations Launch competition in Wisconsin. They were part of teams that successfully flew high-powered rockets, earning them an opportunity to visit the Florida spaceport. During their visit, they toured the Vehicle Assembly Building, Launch Control Center and the Kennedy visitor complex. The competition is supported by NASA and the Wisconsin Space Grant Consortium. It provides an opportunity for students attending tribal colleges or universities, or who are members of a campus American Indian Science and Engineering Society, or AISES, chapter to design, build and launch a rocket at a competition in Kansasville, Wisconsin.

Optical design of infrared pyramid wavefront sensor for the MMT

NASA Astrophysics Data System (ADS)

Chen, Shaojie; Sivanandam, Suresh; Liu, Siqi; Veran, Jean-Pierre; Hinz, Phil; Mieda, Etsuko; Hardy, Tim; Lardiere, Olivier

2017-09-01

We report the optical design of an infrared (0.85-1.8 μm) pyramid wavefront sensor (IRPWFS) that is designed for the 6.5m MMT on telescope adaptive optics system using the latest developments in low-noise infrared avalanche photodiode arrays. The comparison between the pyramid and the double-roof prism based wavefront sensors and the evaluation of their micro pupils' quality are presented. According to our analysis, the use of two double-roof prisms with achromatic materials produces the competitive performance when compared to the traditional pyramid prism, which is difficult to manufacture. The final micro pupils on the image plane have the residual errors of pupil position, chromatism, and distortion within 1/10 pixel over the 2×2 arcsecond field of view, which meet the original design goals.

Launch Vehicle Demonstrator Using Shuttle Assets

NASA Technical Reports Server (NTRS)

Threet, Grady E., Jr.; Creech, Dennis M.; Philips, Alan D.; Water, Eric D.

2011-01-01

The Marshall Space Flight Center Advanced Concepts Office (ACO) has the leading role for NASA s preliminary conceptual launch vehicle design and performance analysis. Over the past several years the ACO Earth-to-Orbit Team has evaluated thousands of launch vehicle concept variations for a multitude of studies including agency-wide efforts such as the Exploration Systems Architecture Study (ESAS), Constellation, Heavy Lift Launch Vehicle (HLLV), Heavy Lift Propulsion Technology (HLPT), Human Exploration Framework Team (HEFT), and Space Launch System (SLS). NASA plans to continue human space exploration and space station utilization. Launch vehicles used for heavy lift cargo and crew will be needed. One of the current leading concepts for future heavy lift capability is an inline one and a half stage concept using solid rocket boosters (SRB) and based on current Shuttle technology and elements. Potentially, the quickest and most cost-effective path towards an operational vehicle of this configuration is to make use of a demonstrator vehicle fabricated from existing shuttle assets and relying upon the existing STS launch infrastructure. Such a demonstrator would yield valuable proof-of-concept data and would provide a working test platform allowing for validated systems integration. Using shuttle hardware such as existing RS-25D engines and partial MPS, propellant tanks derived from the External Tank (ET) design and tooling, and four-segment SRB s could reduce the associated upfront development costs and schedule when compared to a concept that would rely on new propulsion technology and engine designs. There are potentially several other additional benefits to this demonstrator concept. Since a concept of this type would be based on man-rated flight proven hardware components, this demonstrator has the potential to evolve into the first iteration of heavy lift crew or cargo and serve as a baseline for block upgrades. This vehicle could also serve as a demonstration

STS-112 Pilot Melroy inspects cables prior to launch

NASA Technical Reports Server (NTRS)

2002-01-01

KENNEDY SPACE CENTER, FLA. - STS-112 Pilot Pamela Ann Melroy (left) conducts a last-minute inspection of some cables inside Space Shuttle Atlantis at Launch Pad 39B prior to the launch of her mission. The STS-112 crew also includes Commander Jeffrey S. Ashby and Mission Specialists David A. Wolf, Sandra H. Magnus, Piers J. Sellers, and Fyodor N. Yurchikhin of the Russian Space Agency. Launch of the mission was postponed today to no earlier than Thursday, Oct. 3, while weather forecasters and the mission management team assess the possible effect Hurricane Lili may have on the Mission Control Center located at the Lyndon B. Johnson Space Center in Houston, Texas.

Students Participate in Rocket Launch Project

NASA Technical Reports Server (NTRS)

2002-01-01

Filled with anticipation, students from two local universities, the University of Alabama in Huntsville (UAH), and Alabama Agricultural Mechanical University (AM), counted down to launch the rockets they designed and built at the Army test site on Redstone Arsenal in Huntsville, Alabama. The projected two-mile high launch culminated more than a year's work and demonstrated the student team's ability to meet the challenge set by the Marshall Space Flight Center's (MSFC) Student Launch Initiative (SLI) program to apply science and math to experience, judgment, and common sense, and proved to NASA officials that they have successfully built reusable launch vehicles (RLVs), another challenge set by NASA's SLI program. MSFC's SLI program is an educational effort that aims to motivate students to pursue careers in science, math, and engineering. It provides the students with hands-on, practical aerospace experience. In this picture, the combined efforts of students from UAH and AM sent this rocket soaring into flight. Students at UAH built the rocket and AM students developed its scientific payload, an experiment that measures the amount of hydrogen produced during electroplating with nickel in a brief period of micrgravity.

NASA’s BARREL Mission Launches 20 Balloons

NASA Image and Video Library

2017-12-08

BARREL team members run under the payload as the balloon first takes flight at the SANAE IV research station in Antarctica. Credit: NASA --- In Antarctica in January, 2013 – the summer at the South Pole – scientists launched 20 balloons up into the air to study an enduring mystery of space weather: when the giant radiation belts surrounding Earth lose material, where do the extra particles actually go? The mission is called BARREL (Balloon Array for Radiation belt Relativistic Electron Losses) and it is led by physicist Robyn Millan of Dartmouth College in Hanover, NH. Millan provided photographs from the team’s time in Antarctica. The team launched a balloon every day or two into the circumpolar winds that circulate around the pole. Each balloon floated for anywhere from 3 to 40 days, measuring X-rays produced by fast-moving electrons high up in the atmosphere. BARREL works hand in hand with another NASA mission called the Van Allen Probes, which travels through the Van Allen radiation belts surrounding Earth. The belts wax and wane over time in response to incoming energy and material from the sun, sometimes intensifying the radiation through which satellites must travel. Scientists wish to understand this process better, and even provide forecasts of this space weather, in order to protect our spacecraft. As the Van Allen Probes were observing what was happening in the belts, BARREL tracked electrons that precipitated out of the belts and hurtled down Earth’s magnetic field lines toward the poles. By comparing data, scientists will be able to track how what’s happening in the belts correlates to the loss of particles – information that can help us understand this mysterious, dynamic region that can impact spacecraft. Having launched balloons in early 2013, the team is back at home building the next set of payloads. They will launch 20 more balloons in 2014. NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four

NASA’s BARREL Mission Launches 20 Balloons

NASA Image and Video Library

2017-12-08

An emperor penguin waddles away on Christmas morning in Antarctica. On Christmas day, the BARREL team visited a penguin colony. Credit: NASA --- In Antarctica in January, 2013 – the summer at the South Pole – scientists launched 20 balloons up into the air to study an enduring mystery of space weather: when the giant radiation belts surrounding Earth lose material, where do the extra particles actually go? The mission is called BARREL (Balloon Array for Radiation belt Relativistic Electron Losses) and it is led by physicist Robyn Millan of Dartmouth College in Hanover, NH. Millan provided photographs from the team’s time in Antarctica. The team launched a balloon every day or two into the circumpolar winds that circulate around the pole. Each balloon floated for anywhere from 3 to 40 days, measuring X-rays produced by fast-moving electrons high up in the atmosphere. BARREL works hand in hand with another NASA mission called the Van Allen Probes, which travels through the Van Allen radiation belts surrounding Earth. The belts wax and wane over time in response to incoming energy and material from the sun, sometimes intensifying the radiation through which satellites must travel. Scientists wish to understand this process better, and even provide forecasts of this space weather, in order to protect our spacecraft. As the Van Allen Probes were observing what was happening in the belts, BARREL tracked electrons that precipitated out of the belts and hurtled down Earth’s magnetic field lines toward the poles. By comparing data, scientists will be able to track how what’s happening in the belts correlates to the loss of particles – information that can help us understand this mysterious, dynamic region that can impact spacecraft. Having launched balloons in early 2013, the team is back at home building the next set of payloads. They will launch 20 more balloons in 2014. NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through

Landsat Science Team meeting: Winter 2015

USGS Publications Warehouse

Schroeder, Todd A.; Loveland, Thomas; Wulder, Michael A.; Irons, James R.

2015-01-01

The summer meeting of the joint U.S. Geological Survey (USGS)–NASA Landsat Science Team (LST) was held at the USGS’s Earth Resources Observation and Science (EROS) Center July 7-9, 2015, in Sioux Falls, SD. The LST co-chairs, Tom Loveland [EROS—Senior Scientist] and Jim Irons [NASA’s Goddard Space Flight Center (GSFC)—Landsat 8 Project Scientist], opened the three-day meeting on an upbeat note following the recent successful launch of the European Space Agency’s Sentinel-2 mission on June 23, 2015 (see image on page 14), and the news that work on Landsat 9 has begun, with a projected launch date of 2023.With over 60 participants in attendance, this was the largest LST meeting ever held. Meeting topics on the first day included Sustainable Land Imaging and Landsat 9 development, Landsat 7 and 8 operations and data archiving, the Landsat 8 Thermal Infrared Sensor (TIRS) stray-light issue, and the successful Sentinel-2 launch. In addition, on days two and three the LST members presented updates on their Landsat science and applications research. All presentations are available at landsat.usgs.gov/science_LST_Team_ Meetings.php.

Launch Vehicle Directorate and Centaur Rocket Model

NASA Image and Video Library

1979-05-21

The National Aeronautics and Space Administration (NASA) Lewis Research Center’s Launch Vehicle Directorate in front of a full-scale model of the Centaur second-stage rocket. The photograph was taken to mark Centaur’s fiftieth launch. NASA Lewis managed the Centaur Program since 1962. At that time, the only prior launch attempt ended in failure. Lewis improved the spacecraft and tested it extensively throughout the early 1960s. In May 1966 an Atlas-Centaur sent the Surveyor spacecraft to the moon. It was the first successful soft landing on another planet. The Launch Vehicles Division was formed in 1969 to handle the increasing number of Centaur launches. The Lewis team became experts at integrating the payload with the Centaur and calculating proper trajectories for the missions. Centaur’s first 50 missions included Orbiting Astronomical Observatories, the Mariner 6 and 7 flybys of Mars, Mariner 9 which was the first spacecraft to orbit around another planet, the Pioneer 10 and 11 missions to the outer solar system, the Mariner 10 flyby of Venus and Mercury, the Viking 1 and 2 Mars landers, Voyagers 1 and 2 missions to Jupiter, Saturn, Uranus, and Neptune, and the Pioneer 12 and 13 flights to Venus.

JSC Astronaut corps, STS-3 vehicle integration test team and others

NASA Technical Reports Server (NTRS)

1982-01-01

Members of the JSC astronaut corps, STS-3 vehicle integration test (VIT) team and other personnel pose for photograph at the completion of a countdown demonstration test (CDDT) and safety briefings at Launch Pad 39A, Kennedy Space Center. Participants are, from the left, Wilbur J. Etbauer, engineer with the VIT team; George W.S. Abbey, Director of Flight Operations at JSC; Astronaut John H. Young, Chief of the Astronaut Office at JSC; Jack Fleming of Rockwell International; Mission Specialist-Astronaut John M. Lounge; Astronaut Daniel C. Brandenstein; Mission Specialist-Astronaut James D. Van Hoften; Astronauts C. Gordon Fullerton and Jack Lousma, prime crew for STS-3; Olan J. Bertrand, VIT team member; Mission Specialist-Astronaut Kathryn D. Sullivan; Richard W. Nygren, head of the VIT team; and Astronaut Donald E. Williams. The Columbia is obscured by its service structure on Launch Pad 39A in the background. Part of slide-wire emergency escape system is visible in the picture.

Launch vehicle systems design analysis

NASA Technical Reports Server (NTRS)

Ryan, Robert; Verderaime, V.

1993-01-01

Current launch vehicle design emphasis is on low life-cycle cost. This paper applies total quality management (TQM) principles to a conventional systems design analysis process to provide low-cost, high-reliability designs. Suggested TQM techniques include Steward's systems information flow matrix method, quality leverage principle, quality through robustness and function deployment, Pareto's principle, Pugh's selection and enhancement criteria, and other design process procedures. TQM quality performance at least-cost can be realized through competent concurrent engineering teams and brilliance of their technical leadership.

NASA’s BARREL Mission Launches 20 Balloons

NASA Image and Video Library

2017-12-08

An iceberg as viewed from the bow of the RRS Ernest Shackleton a few days before the BARREL team reached Halley Research Station in Antarctica. This research vessel regularly carries scientists and supplies to Halley. Credit: NASA --- In Antarctica in January, 2013 – the summer at the South Pole – scientists launched 20 balloons up into the air to study an enduring mystery of space weather: when the giant radiation belts surrounding Earth lose material, where do the extra particles actually go? The mission is called BARREL (Balloon Array for Radiation belt Relativistic Electron Losses) and it is led by physicist Robyn Millan of Dartmouth College in Hanover, NH. Millan provided photographs from the team’s time in Antarctica. The team launched a balloon every day or two into the circumpolar winds that circulate around the pole. Each balloon floated for anywhere from 3 to 40 days, measuring X-rays produced by fast-moving electrons high up in the atmosphere. BARREL works hand in hand with another NASA mission called the Van Allen Probes, which travels through the Van Allen radiation belts surrounding Earth. The belts wax and wane over time in response to incoming energy and material from the sun, sometimes intensifying the radiation through which satellites must travel. Scientists wish to understand this process better, and even provide forecasts of this space weather, in order to protect our spacecraft. As the Van Allen Probes were observing what was happening in the belts, BARREL tracked electrons that precipitated out of the belts and hurtled down Earth’s magnetic field lines toward the poles. By comparing data, scientists will be able to track how what’s happening in the belts correlates to the loss of particles – information that can help us understand this mysterious, dynamic region that can impact spacecraft. Having launched balloons in early 2013, the team is back at home building the next set of payloads. They will launch 20 more balloons in 2014

NASA’s BARREL Mission Launches 20 Balloons

NASA Image and Video Library

2017-12-08

Arrival of the RRS Ernest Shackleton near Halley Research Station in Antarctica. The Shackleton is the regular resupply ship for the station and it also brought in some of the BARREL team scientists. The long tether is for the ship’s mooring. Credit: NASA --- In Antarctica in January, 2013 – the summer at the South Pole – scientists launched 20 balloons up into the air to study an enduring mystery of space weather: when the giant radiation belts surrounding Earth lose material, where do the extra particles actually go? The mission is called BARREL (Balloon Array for Radiation belt Relativistic Electron Losses) and it is led by physicist Robyn Millan of Dartmouth College in Hanover, NH. Millan provided photographs from the team’s time in Antarctica. The team launched a balloon every day or two into the circumpolar winds that circulate around the pole. Each balloon floated for anywhere from 3 to 40 days, measuring X-rays produced by fast-moving electrons high up in the atmosphere. BARREL works hand in hand with another NASA mission called the Van Allen Probes, which travels through the Van Allen radiation belts surrounding Earth. The belts wax and wane over time in response to incoming energy and material from the sun, sometimes intensifying the radiation through which satellites must travel. Scientists wish to understand this process better, and even provide forecasts of this space weather, in order to protect our spacecraft. As the Van Allen Probes were observing what was happening in the belts, BARREL tracked electrons that precipitated out of the belts and hurtled down Earth’s magnetic field lines toward the poles. By comparing data, scientists will be able to track how what’s happening in the belts correlates to the loss of particles – information that can help us understand this mysterious, dynamic region that can impact spacecraft. Having launched balloons in early 2013, the team is back at home building the next set of payloads. They will launch

NASA's Space Launch System: Progress Report

NASA Technical Reports Server (NTRS)

Cook, Jerry; Lyles, Garry

2017-01-01

NASA and its commercial industry team achieved significant progress in 2016 in manufacturing and testing of the Block 1 vehicle for the first launch of the Space Launch System (SLS). Test and flight article hardware for the liquid hydrogen fuel tank as well as the engine section for the core stage were completed at Michoud Assembly Facility (MAF) in New Orleans. Test stands neared completion at Marshall Space Flight Center for the propellant tanks, engine section, intertank and payload section. Stennis Space Center completed major structural renovations on the B2 test stand, where the core stage "green run" test program will be conducted. The SLS team completed a hotfire test series at Stennis to successfully demonstrate the ability of the RS-25 engine to operate under SLS environments and performance conditions. The team also test fired the second qualification five-segment solid rocket motor and cast the first six motor segments for the first SLS mission. The Interim Cryogenic Propulsion Stage (ICPS) test article was delivered to Marshall for structural tests, and work is nearly finished on the flight stage. Flight software testing completed at Marshall included power quality and command and data handling. In 2017, that work continues. SLS completed Preliminary Design Review (PDR) on the Exploration Upper Stage (EUS), a powerful, human-rated spacecraft that will propel explorers to cis-lunar space. In 2017, hardware will continue to be integrated at MAF for core stage structural test articles and the first two operational flights. RS-25 hotfire testing will continue to explore engine performance, as well as test flight-like software and four new Engine Controller Units (ECUs) for the first mission. Production of development components for a more affordable RS-25 design is underway. Core stage structural test articles have begun arriving at Marshall. While engineering challenges typical of a new development are possible, SLS is working toward launch readiness in

JPSS-1 VIIRS Pre-Launch Radiometric Performance

NASA Technical Reports Server (NTRS)

Oudrari, Hassan; McIntire, Jeff; Xiong, Xiaoxiong; Butler, James; Efremova, Boryana; Ji, Jack; Lee, Shihyan; Schwarting, Tom

2015-01-01

The Visible Infrared Imaging Radiometer Suite (VIIRS) on-board the first Joint Polar Satellite System (JPSS) completed its sensor level testing on December 2014. The JPSS-1 (J1) mission is scheduled to launch in December 2016, and will be very similar to the Suomi-National Polar-orbiting Partnership (SNPP) mission. VIIRS instrument was designed to provide measurements of the globe twice daily. It is a wide-swath (3,040 kilometers) cross-track scanning radiometer with spatial resolutions of 370 and 740 meters at nadir for imaging and moderate bands, respectively. It covers the wavelength spectrum from reflective to long-wave infrared through 22 spectral bands [0.412 microns to 12.01 microns]. VIIRS observations are used to generate 22 environmental data products (EDRs). This paper will briefly describe J1 VIIRS characterization and calibration performance and methodologies executed during the pre-launch testing phases by the independent government team, to generate the at-launch baseline radiometric performance, and the metrics needed to populate the sensor data record (SDR) Look-Up-Tables (LUTs). This paper will also provide an assessment of the sensor pre-launch radiometric performance, such as the sensor signal to noise ratios (SNRs), dynamic range, reflective and emissive bands calibration performance, polarization sensitivity, bands spectral performance, response-vs-scan (RVS), near field and stray light responses. A set of performance metrics generated during the pre-launch testing program will be compared to the SNPP VIIRS pre-launch performance.

Large Scale Composite Manufacturing for Heavy Lift Launch Vehicles

NASA Technical Reports Server (NTRS)

Stavana, Jacob; Cohen, Leslie J.; Houseal, Keth; Pelham, Larry; Lort, Richard; Zimmerman, Thomas; Sutter, James; Western, Mike; Harper, Robert; Stuart, Michael

2012-01-01

Risk reduction for the large scale composite manufacturing is an important goal to produce light weight components for heavy lift launch vehicles. NASA and an industry team successfully employed a building block approach using low-cost Automated Tape Layup (ATL) of autoclave and Out-of-Autoclave (OoA) prepregs. Several large, curved sandwich panels were fabricated at HITCO Carbon Composites. The aluminum honeycomb core sandwich panels are segments of a 1/16th arc from a 10 meter cylindrical barrel. Lessons learned highlight the manufacturing challenges required to produce light weight composite structures such as fairings for heavy lift launch vehicles.

Pre-dispersed organo-montmorillonite (organo-MMT) nanofiller: Morphology, cytocompatibility and impact on flexibility, toughness and biostability of biomedical ethyl vinyl acetate (EVA) copolymer.

PubMed

Osman, Azlin F; M Fitri, Tuty Fareyhynn; Rakibuddin, Md; Hashim, Fatimah; Tuan Johari, Syed Ahmad Tajudin; Ananthakrishnan, Rajakumar; Ramli, Rafiza

2017-05-01

Polymer-clay based nanocomposites are among the attractive materials to be applied for various applications, including biomedical. The incorporation of the nano sized clay (nanoclay) into polymer matrices can result in their remarkable improvement in mechanical, thermal and barrier properties as long as the nanofillers are well exfoliated and dispersed throughout the matrix. In this work, exfoliation strategy through pre-dispersing process of the organically modified montmorillonite (organo-MMT) nanofiller was done to obtain ethyl vinyl acetate (EVA) nanocomposite with improved flexibility, toughness, thermal stability and biostability. Our results indicated that the degree of organo-MMT exfoliation affects its cytotoxicity level and the properties of the resulting EVA nanocomposite. The pre-dispersed organo-MMT by ultrasonication in water possesses higher degree of exfoliation as compared to its origin condition and significantly performed reduced cytotoxicity level. Beneficially, this nanofiller also enhanced the EVA flexibility, thermal stability and biostability upon the in vitro exposure. We postulated that these were due to plasticizing effect and enhanced EVA-nanofiller interactions contributing to more stable chemical bonds in the main copolymer chains. Improvement in copolymer flexibility is beneficial for close contact with human soft tissue, while enhancement in toughness and biostability is crucial to extend its life expectancy as insulation material for implantable device. Copyright © 2016 Elsevier B.V. All rights reserved.

NASA's Space Launch System Progress Report

NASA Technical Reports Server (NTRS)

Singer, Joan A.; Cook, Jerry R.; Lyles, Garry M.; Beaman, David E.

2011-01-01

centers across the country will provide their unique expertise to the Space Launch System endeavor. Unique infrastructure to be used includes the Michoud Assembly Facility for tank manufacturing, Stennis Space Center for engine testing, and Kennedy Space Center for processing and launch. As this panel will discuss, the SLS team is dedicated to doing things differently-from applying lean oversight/insight models to smartly using legacy hardware and existing facilities. Building on the foundation laid by over 50 years of human and scientific space flight--and on the lessons learned from the Apollo, Space Shuttle, and Constellation Programs-the SLS team has delivered both technical trade studies and business case analyses to ensure that the SLS architecture will be safe, affordable, reliable, and sustainable.

NASA's Space Launch System: Moving Toward the Launch Pad

NASA Technical Reports Server (NTRS)

Creech, Stephen D.; May, Todd A.

2013-01-01

The National Aeronautics and Space Administration's (NASA's) Space Launch System (SLS) Program, managed at the Marshall Space Flight Center (MSFC), is making progress toward delivering a new capability for human space flight and scientific missions beyond Earth orbit. Designed with the goals of safety, affordability, and sustainability in mind, the SLS rocket will launch the Orion Multi-Purpose Crew Vehicle (MPCV), equipment, supplies, and major science missions for exploration and discovery. Supporting Orion's first autonomous flight to lunar orbit and back in 2017 and its first crewed flight in 2021, the SLS will evolve into the most powerful launch vehicle ever flown via an upgrade approach that will provide building blocks for future space exploration. NASA is working to deliver this new capability in an austere economic climate, a fact that has inspired the SLS team to find innovative solutions to the challenges of designing, developing, fielding, and operating the largest rocket in history. This paper will summarize the planned capabilities of the vehicle, the progress the SLS Program has made in the 2 years since the Agency formally announced its architecture in September 2011, the path it is following to reach the launch pad in 2017 and then to evolve the 70 metric ton (t) initial lift capability to 130-t lift capability after 2021. The paper will explain how, to meet the challenge of a flat funding curve, an architecture was chosen that combines the use and enhancement of legacy systems and technology with strategic new developments that will evolve the launch vehicle's capabilities. This approach reduces the time and cost of delivering the initial 70 t Block 1 vehicle, and reduces the number of parallel development investments required to deliver the evolved 130 t Block 2 vehicle. The paper will outline the milestones the program has already reached, from developmental milestones such as the manufacture of the first flight hardware, to life

[Involvement of medical representatives in team medical care].

PubMed

Hirotsu, Misaki; Sohma, Michiro; Takagi, Hidehiko

2009-04-01

In recent years, chemotherapies have been further advanced because of successive launch of new drugs, introduction of molecular targeting, etc., and the concept of so-called Team Medical Care ,the idea of sharing interdisciplinary expertise for collaborative treatment, has steadily penetrated in the Japanese medical society. Dr. Naoto Ueno is a medical oncologist at US MD Anderson Cancer Center, the birthplace of the Team Medical Care. He has advocated the concept of ABC of Team Oncology by positioning pharmaceutical companies as Team C. Under such team practice, we believe that medical representatives of a pharmaceutical company should also play a role as a member of the Team Medical Care by providing appropriate drug use information to healthcare professionals, supporting post-marketing surveillance of treated patients, facilitating drug information sharing among healthcare professionals at medical institutions, etc.

Effect of film multi-scale structure on the water vapor permeability in hydroxypropyl starch (HPS)/Na-MMT nanocomposites.

PubMed

Liu, Siyuan; Cai, Panfu; Li, Xiaoxi; Chen, Ling; Li, Lin; Li, Bing

2016-12-10

To improve the water vapor resistance of starch-based films, Na-MMT (Na-montmorillonite) as nanofillers were fabricated into hydroxypropyl starch and the multi-scale structural changes (including intermolecular interaction, short-range conformation, long-range ordered structure and the aggregated structure of the film) were revealed. The elongation of the water vapor molecule pathway by tortuous path is generally recognized as the main reason for the improvement of water resistance. However this study observed the lowest water vapor permeability (WVP) was at the 3% Na-MMT/hydroxypropyl starch (HPS) ratio instead of 5% even nanofillers were partially exfoliated at both ratio. Except for the "tortuous path" caused by nanofillers, this observation proposed that the short-range conformation of HPS chains, long-range ordered structure and the aggregated structure likely influenced the water barrier property. The relationship between WVP and multi-scale structure of the film was investigated. The results suggested that a good balance of short-range conformationin the amorphous region, long-range ordered structure and the aggregated structure of the film was required for the improvement of water vapor barrier property. Copyright © 2016 Elsevier Ltd. All rights reserved.

NASA’s BARREL Mission Launches 20 Balloons

NASA Image and Video Library

2017-12-08

Pumping helium into the first BARREL balloon to launch from Halley Research Satation. Credit: NASA --- In Antarctica in January, 2013 – the summer at the South Pole – scientists launched 20 balloons up into the air to study an enduring mystery of space weather: when the giant radiation belts surrounding Earth lose material, where do the extra particles actually go? The mission is called BARREL (Balloon Array for Radiation belt Relativistic Electron Losses) and it is led by physicist Robyn Millan of Dartmouth College in Hanover, NH. Millan provided photographs from the team’s time in Antarctica. The team launched a balloon every day or two into the circumpolar winds that circulate around the pole. Each balloon floated for anywhere from 3 to 40 days, measuring X-rays produced by fast-moving electrons high up in the atmosphere. BARREL works hand in hand with another NASA mission called the Van Allen Probes, which travels through the Van Allen radiation belts surrounding Earth. The belts wax and wane over time in response to incoming energy and material from the sun, sometimes intensifying the radiation through which satellites must travel. Scientists wish to understand this process better, and even provide forecasts of this space weather, in order to protect our spacecraft. As the Van Allen Probes were observing what was happening in the belts, BARREL tracked electrons that precipitated out of the belts and hurtled down Earth’s magnetic field lines toward the poles. By comparing data, scientists will be able to track how what’s happening in the belts correlates to the loss of particles – information that can help us understand this mysterious, dynamic region that can impact spacecraft. Having launched balloons in early 2013, the team is back at home building the next set of payloads. They will launch 20 more balloons in 2014. NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors: Earth Science

A status of the Turbine Technology Team activities

NASA Technical Reports Server (NTRS)

Griffin, Lisa W.

1992-01-01

The recent activities of the Turbine Technology Team of the Consortium for Computational Fluid Dynamics (CFD) Application in Propulsion Technology is presented. The team consists of members from the government, industry, and universities. The goal of this team is to demonstrate the benefits to the turbine design process attainable through the application of CFD. This goal is to be achieved by enhancing and validating turbine design tools for improved loading and flowfield definition and loss prediction, and transferring the advanced technology to the turbine design process. In order to demonstrate the advantages of using CFD early in the design phase, the Space Transportation Main Engine (STME) turbines for the National Launch System (NLS) were chosen on which to focus the team's efforts. The Turbine Team activities run parallel to the STME design work.

Ares Launch Vehicles Overview: Space Access Society

NASA Technical Reports Server (NTRS)

Cook, Steve

2007-01-01

America is returning to the Moon in preparation for the first human footprint on Mars, guided by the U.S. Vision for Space Exploration. This presentation will discuss NASA's mission, the reasons for returning to the Moon and going to Mars, and how NASA will accomplish that mission in ways that promote leadership in space and economic expansion on the new frontier. The primary goals of the Vision for Space Exploration are to finish the International Space Station, retire the Space Shuttle, and build the new spacecraft needed to return people to the Moon and go to Mars. The Vision commits NASA and the nation to an agenda of exploration that also includes robotic exploration and technology development, while building on lessons learned over 50 years of hard-won experience. NASA is building on common hardware, shared knowledge, and unique experience derived from the Apollo Saturn, Space Shuttle, and contemporary commercial launch vehicle programs. The journeys to the Moon and Mars will require a variety of vehicles, including the Ares I Crew Launch Vehicle, which transports the Orion Crew Exploration Vehicle, and the Ares V Cargo Launch Vehicle, which transports the Lunar Surface Access Module. The architecture for the lunar missions will use one launch to ferry the crew into orbit, where it will rendezvous with the Lunar Module in the Earth Departure Stage, which will then propel the combination into lunar orbit. The imperative to explore space with the combination of astronauts and robots will be the impetus for inventions such as solar power and water and waste recycling. This next chapter in NASA's history promises to write the next chapter in American history, as well. It will require this nation to provide the talent to develop tools, machines, materials, processes, technologies, and capabilities that can benefit nearly all aspects of life on Earth. Roles and responsibilities are shared between a nationwide Government and industry team. The Exploration Launch

SLS launched missions concept studies for LUVOIR mission

NASA Astrophysics Data System (ADS)

Stahl, H. Philip; Hopkins, Randall C.

2015-09-01

NASA's "Enduring Quests Daring Visions" report calls for an 8- to 16-m Large UV-Optical-IR (LUVOIR) Surveyor mission to enable ultra-high-contrast spectroscopy and coronagraphy. AURA's "From Cosmic Birth to Living Earth" report calls for a 12-m class High-Definition Space Telescope to pursue transformational scientific discoveries. The multi-center ATLAST Team is working to meet these needs. The MSFC Team is examining potential concepts that leverage the advantages of the SLS (Space Launch System). A key challenge is how to affordably get a large telescope into space. The JWST design was severely constrained by the mass and volume capacities of its launch vehicle. This problem is solved by using an SLS Block II-B rocket with its 10-m diameter x 30-m tall fairing and estimated 45 mt payload to SE-L2. Previously, two development study cycles produced a detailed concept called ATLAST-8. Using ATLAST-8 as a point of departure, this paper reports on a new ATLAST-12 concept. ATLAST-12 is a 12-m class segmented aperture LUVOIR with an 8-m class center segment. Thus, ATLAST-8 is now a de-scope option.

SLS Launched Missions Concept Studies for LUVOIR Mission

NASA Technical Reports Server (NTRS)

Stahl, H. Philip; Hopkins, Randall C.

2015-01-01

NASA's "Enduring Quests Daring Visions" report calls for an 8- to 16-meter Large UV-Optical-IR (LUVOIR) Surveyor mission to enable ultra-high-contrast spectroscopy and coronagraphy. AURA's "From Cosmic Birth to Living Earth" report calls for a 12-meter class High-Definition Space Telescope to pursue transformational scientific discoveries. The multi-center ATLAST Team is working to meet these needs. The MSFC Team is examining potential concepts that leverage the advantages of the SLS (Space Launch System). A key challenge is how to affordably get a large telescope into space. The JWST design was severely constrained by the mass and volume capacities of its launch vehicle. This problem is solved by using an SLS Block II-B rocket with its 10-m diameter x 30-m tall fairing and 45 mt payload to SE-L2. Previously, two development study cycles produced a detailed concept called ATLAST-8. Using ATLAST-8 as a point of departure, this paper reports on a new ATLAST-12 concept. ATLAST-12 is a 12-meter class segmented aperture LUVOIR with an 8-m class center segment. Thus, ATLAST-8 is now a de-scope option.

Cassini launch contingency effort

NASA Astrophysics Data System (ADS)

Chang, Yale; O'Neil, John M.; McGrath, Brian E.; Heyler, Gene A.; Brenza, Pete T.

2002-01-01

On 15 October 1997 at 4:43 AM EDT, the Cassini spacecraft was successfully launched on a Titan IVB/Centaur on a mission to explore the Saturnian system. It carried three Radioisotope Thermoelectric Generators (RTGs) and 117 Light Weight Radioisotope Heater Units (LWRHUs). As part of the joint National Aeronautics and Space Administration (NASA)/U.S. Department of Energy (DoE) safety effort, a contingency plan was prepared to address the unlikely events of an accidental suborbital reentry or out-of-orbital reentry. The objective of the plan was to develop procedures to predict, within hours, the Earth impact footprints (EIFs) for the nuclear heat sources released during the atmospheric reentry. The footprint predictions would be used in subsequent notification and recovery efforts. As part of a multi-agency team, The Johns Hopkins University Applied Physics Laboratory (JHU/APL) had the responsibility to predict the EIFs of the heat sources after a reentry, given the heat sources' release conditions from the main spacecraft. (No ablation burn-through of the heat sources' aeroshells was expected, as a result of earlier testing.) JHU/APL's other role was to predict the time of reentry from a potential orbital decay. The tools used were a three degree-of-freedom trajectory code, a database of aerodynamic coefficients for the heat sources, secure links to obtain tracking data, and a high fidelity special perturbation orbit integrator code to predict time of spacecraft reentry from orbital decay. In the weeks and days prior to launch, all the codes and procedures were exercised. Notional EIFs were derived from hypothetical reentry conditions. EIFs predicted by JHU/APL were compared to those by JPL and US SPACECOM, and were found to be in good agreement. The reentry time from orbital decay for a booster rocket for the Russian Progress M-36 freighter, a cargo ship for the Mir space station, was predicted to within 5 minutes more than two hours before reentry. For the

Space Technology 5 Launch and Operations

NASA Technical Reports Server (NTRS)

O'Donnell, James R.; Concha, Marco A.; Morrissey, James R.; Placanica, Samuel J.; Russo, Angela M.; Tsai, Dean C.

2007-01-01

The three spacecraft that made up the Space Technology 5 (ST5) mission were successfully launched and deployed from their Pegasus launch vehicle on March 22, 2006. Final contact with the spacecraft occurred on June 30, 2006, with all Level 1 requirements met. By the end of the mission, all ST5 technologies had been validated, all on-board attitude control system (ACS) modes had been successfully demonstrated, and the desired constellation configurations had been achieved to demonstrate the ability of small spacecraft to take quality science measurements, However, during those 100 days (ST5 was planned to be a 90-day mission), there were a number of anomalies that made achieving the mission goals very challenging. This paper will discuss: the chronology of the ST5 launch and early operations, work performed to diagnose and work-around a sun sensor anomaly, spacecraft tests devised to demonstrate correct operation of all onboard ACS modes, the maneuver plan performed to achieve the desired constellation, investigations performed by members of the ST5 GN&C and Science teams of an anomalous spin down condition, and the end-of-life orbit and passivating operations performed on the three spacecraft.

Kennedy Space Center (KSC) Launch Pad Avian Abatement Efforts Including Related KSC Road Kill Reduction Effort

NASA Technical Reports Server (NTRS)

Schlierf, Roland; Hight, Ron; Payne, Stephen J.; Shaffer, John P.; Missimer, Brad; Willis, Christopher

2007-01-01

While birds might seem harmless, there's a good reason for the concern. During the July 2005 launch of Discovery on mission STS-1 14, a vulture soaring around the launch pad impacted the shuttle's external tank just after liftoff. With a vulture's average weight ranging from 3 to 5 pounds. a strike at a critical point on the Shuttle -- like the nose or wing leading thermal protection panels -- could cause catastrophic damage to the vehicle. The foam chunk that fatefully struck Columbia's wing in 2003 weighed only 1.7 pounds. (Cheryl L. Mansfield "Bye Bye Birdies" 2006) To address this issue, NASA formed an "Avian Abatement Team". The team goal is to have safer Shuttle missions by reducing the vulture population at KSC near the pad area thereby reducing the probability of another vulture strike during a Shuttle launch.

Information Flow in the Launch Vehicle Design/Analysis Process

NASA Technical Reports Server (NTRS)

Humphries, W. R., Sr.; Holland, W.; Bishop, R.

1999-01-01

This paper describes the results of a team effort aimed at defining the information flow between disciplines at the Marshall Space Flight Center (MSFC) engaged in the design of space launch vehicles. The information flow is modeled at a first level and is described using three types of templates: an N x N diagram, discipline flow diagrams, and discipline task descriptions. It is intended to provide engineers with an understanding of the connections between what they do and where it fits in the overall design process of the project. It is also intended to provide design managers with a better understanding of information flow in the launch vehicle design cycle.

President Clinton's Arrival at CCAS and Visit to KSC for Launch of STS-95

NASA Technical Reports Server (NTRS)

1998-01-01

Live footage shows President Bill Clinton and First Lady Hillary Rodham Clinton arriving in Airforce 1 on the Skid Strip, viewing the launch, and tracking the plume of Space Shuttle Discovery, on mission STS-95. The viewing takes place on the roof of the Launch Control Center (LCC). Also present on the roof to watch this event are Astronaut Robert Cabana and Eileen Collins (both in flight suit), and the NASA Administrator Daniel Goldin. The President is shown giving a speech to the Launch Team and shaking hands with employees in the LCC.

Zero Launch Mass Three Dimensional Print Head

NASA Technical Reports Server (NTRS)

Mueller, Robert P.; Gelino, Nathan J.; Smith, Jonathan D.; Buckles, Brad C.; Lippitt, Thomas; Schuler, Jason M.; Nick, Andrew J.; Nugent, Matt W.; Townsend, Ivan I.

2018-01-01

NASA's strategic goal is to put humans on Mars in the 2030's. The NASA Human Spaceflight Architecture Team (HAT) and NASA Mars Design Reference Architecture (DRA) 5.0 has determined that in-situ resource utilization (ISRU) is an essential technology to accomplish this mission. Additive construction technology using in-situ materials from planetary surfaces will reduce launch mass, allow structures to be three dimensionally (3D) printed on demand, and will allow building designs to be transmitted digitally from Earth and printed in space. This will ultimately lead to elimination of reliance on structural materials launched from Earth (zero launch mass of construction consumables). The zero launch mass (ZLM) 3D print head project addressed this need by developing a system that 3D prints using a mixture of in-situ regolith and polymer as feedstock, determining the optimum mixture ratio and regolith particle size distribution, developing software to convert g-code into motion instructions for a FANUC robotic arm, printing test samples, performing materials testing, and printing a reduced scale habitable structure concept. This paper will focus on the ZLM 3D Print Head design, materials selection, software development, and lessons learned from operating the system in the NASA KSC Swamp Works Granular Mechanics & Regolith Operations (GMRO) Laboratory.

Preparation and Launch of the JEM ISS Elements - A NASA Mission Manager's Perspective

NASA Technical Reports Server (NTRS)

Higginbotham, Scott A.

2016-01-01

The pre-flight launch site preparations and launch of the Japanese Experiment Module (JEM) elements of the International Space Station required an intense multi-year, international collaborative effort between US and Japanese personnel at the Kennedy Space Center (KSC). This presentation will provide a brief overview of KSC, a brief overview of the ISS, and a summary of authors experience managing the NASA team responsible that supported and conducted the JEM element operations.

Manufacturing Methods and Technology (MM&T) program. 10.6 micrometer carbon dioxide TEA (Transverely Excited Atmospheric) lasers

NASA Astrophysics Data System (ADS)

Luck, C. F.

1983-06-01

This report documents the efforts of Raytheon Company to conduct a manufacturing methods and technology (MM&T) program for 10.6 micrometer carbon dioxide TEA lasers. A set of laser parameters is given and a conforming tube design is described. Results of thermal and mechanical stress analyses are detailed along with a procedure for assembling and testing the laser tube. Also provided are purchase specifications for optics and process specifications for some of the essential operations.

Ties That Bind International Research Teams: A Network Multilevel Model of Interdisciplinary Collaboration

ERIC Educational Resources Information Center

Kollasch, Aurelia Wiktoria

2012-01-01

Today large research projects require substantial involvement of researchers from different organizations, disciplines, or cultures working in groups or teams to accomplish a common goal of producing, sharing, and disseminating scientific knowledge. This study focuses on the international research team that was launched in response to pressing…

NASA's Space Launch System: Moving Toward the Launch Pad

NASA Technical Reports Server (NTRS)

Creech, Stephen D.; May, Todd

2013-01-01

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. Developed with the goals of safety, affordability, and sustainability in mind, the SLS rocket will launch the Orion Multi-Purpose Crew Vehicle (MPCV), equipment, supplies, and major science missions for exploration and discovery. Supporting Orion's first autonomous flight to lunar orbit and back in 2017 and its first crewed flight in 2021, the SLS will evolve into the most powerful launch vehicle ever flown, via an upgrade approach that will provide building blocks for future space exploration and development. NASA is working to develop this new capability in an austere economic climate, a fact which has inspired the SLS team to find innovative solutions to the challenges of designing, developing, fielding, and operating the largest rocket in history. This paper will summarize the planned capabilities of the vehicle, the progress the SLS program has made in the 2 years since the Agency formally announced its architecture in September 2011, and the path the program is following to reach the launch pad in 2017 and then to evolve the 70 metric ton (t) initial lift capability to 130-t lift capability. The paper will explain how, to meet the challenge of a flat funding curve, an architecture was chosen which combines the use and enhancement of legacy systems and technology with strategic new development projects that will evolve the capabilities of the launch vehicle. This approach reduces the time and cost of delivering the initial 70 t Block 1 vehicle, and reduces the number of parallel development investments required to deliver the evolved version of the vehicle. The paper will outline the milestones the program has already reached, from developmental milestones such as the manufacture of the first flight

Flight Force Measurements on a Spacecraft to Launch Vehicle Interface

NASA Astrophysics Data System (ADS)

Kaufman, Daniel S.; Gordon, Scott A.

2012-07-01

For several years we had wanted to measure interface forces between a launch vehicle and the Payload. Finally in July 2006 a proposal was made and funded to evaluate the use of flight force measurements (FFM) to improve the loads process of a Spacecraft in its design and test cycle. A NASA/Industry team was formed, the core Team consisted of 20 people. The proposal identified two questions that this assessment would attempt to address by obtaining the flight forces. These questions were: 1) Is flight correlation and reconstruction with acceleration methods sufficient? 2) How much can the loads and therefore the design and qualification be reduced by having force measurements? The objective was to predict the six interface driving forces between the Spacecraft and the Launch Vehicle throughout the boost phase. Then these forces would be compared with reconstructed loads analyses for evaluation in an attempt to answer them. The paper will present the development of a strain based force measurement system and also an acceleration method, actual flight results, post flight evaluations and lessons learned.

Orbital transfer vehicle launch operations study. Volume 1: Executive summary

NASA Technical Reports Server (NTRS)

1986-01-01

The purpose was to use the operational experience at the launch site to identify, describe and quantify the operational impacts of the various configurations on the Kennedy Space Center (KSC) and/or space station launch sites. Orbital Transfer Vehicle (OTV) configurations are being developed/defined by contractor teams. Lacking an approved configuration, the KSC Study Team defined a Reference Configuration to be used for this study. This configuration then become the baseline for the identification of the facilities, personnel and crew skills required for processing the OTV in a realistic manner that would help NASA achieve the lowest possible OTV life cycle costs. As the study progressed, researchers' initial apraisal that the vehicle, when delivered, would be a sophisticated, state-of-the-art vehicle was reinforced. It would be recovered and reused many times so the primary savings to be gained would be in the recurring-cycle of the vehicle operations--even to the point where it would be beneficial to break from tradition and make a significant expenditure in the development of processing facilities at the beginning of the program.

NASA’s BARREL Mission Launches 20 Balloons

NASA Image and Video Library

2017-12-08

Some of the BARREL balloon launches took place at the South African National Antarctic Expedition Research base, called SANAE IV, the others at Halley Research Station. This balloon is taking flight at SANAE IV. Credit: NASA --- In Antarctica in January, 2013 – the summer at the South Pole – scientists launched 20 balloons up into the air to study an enduring mystery of space weather: when the giant radiation belts surrounding Earth lose material, where do the extra particles actually go? The mission is called BARREL (Balloon Array for Radiation belt Relativistic Electron Losses) and it is led by physicist Robyn Millan of Dartmouth College in Hanover, NH. Millan provided photographs from the team’s time in Antarctica. The team launched a balloon every day or two into the circumpolar winds that circulate around the pole. Each balloon floated for anywhere from 3 to 40 days, measuring X-rays produced by fast-moving electrons high up in the atmosphere. BARREL works hand in hand with another NASA mission called the Van Allen Probes, which travels through the Van Allen radiation belts surrounding Earth. The belts wax and wane over time in response to incoming energy and material from the sun, sometimes intensifying the radiation through which satellites must travel. Scientists wish to understand this process better, and even provide forecasts of this space weather, in order to protect our spacecraft. As the Van Allen Probes were observing what was happening in the belts, BARREL tracked electrons that precipitated out of the belts and hurtled down Earth’s magnetic field lines toward the poles. By comparing data, scientists will be able to track how what’s happening in the belts correlates to the loss of particles – information that can help us understand this mysterious, dynamic region that can impact spacecraft. Having launched balloons in early 2013, the team is back at home building the next set of payloads. They will launch 20 more balloons in 2014. NASA

NASA Advanced Concepts Office, Earth-To-Orbit Team Design Process and Tools

NASA Technical Reports Server (NTRS)

Waters, Eric D.; Creech, Dennis M.; Garcia, Jessica; Threet, Grady E., Jr.; Phillips, Alan

2012-01-01

The Earth-to-Orbit Team (ETO) of the Advanced Concepts Office (ACO) at NASA Marshall Space Flight Center (MSFC) is considered the pre-eminent go-to group for pre-phase A and phase A concept definition. Over the past several years the ETO team has evaluated thousands of launch vehicle concept variations for a significant number of studies including agency-wide efforts such as the Exploration Systems Architecture Study (ESAS), Constellation, Heavy Lift Launch Vehicle (HLLV), Augustine Report, Heavy Lift Propulsion Technology (HLPT), Human Exploration Framework Team (HEFT), and Space Launch System (SLS). The ACO ETO Team is called upon to address many needs in NASA s design community; some of these are defining extremely large trade-spaces, evaluating advanced technology concepts which have not been addressed by a large majority of the aerospace community, and the rapid turn-around of highly time critical actions. It is the time critical actions, those often limited by schedule or little advanced warning, that have forced the five member ETO team to develop a design process robust enough to handle their current output level in order to meet their customer s needs. Based on the number of vehicle concepts evaluated over the past year this output level averages to four completed vehicle concepts per day. Each of these completed vehicle concepts includes a full mass breakdown of the vehicle to a tertiary level of subsystem components and a vehicle trajectory analysis to determine optimized payload delivery to specified orbital parameters, flight environments, and delta v capability. A structural analysis of the vehicle to determine flight loads based on the trajectory output, material properties, and geometry of the concept is also performed. Due to working in this fast-paced and sometimes rapidly changing environment, the ETO Team has developed a finely tuned process to maximize their delivery capabilities. The objective of this paper is to describe the interfaces

NASA Advanced Concepts Office, Earth-To-Orbit Team Design Process and Tools

NASA Technical Reports Server (NTRS)

Waters, Eric D.; Garcia, Jessica; Threet, Grady E., Jr.; Phillips, Alan

2013-01-01

The Earth-to-Orbit Team (ETO) of the Advanced Concepts Office (ACO) at NASA Marshall Space Flight Center (MSFC) is considered the pre-eminent "go-to" group for pre-phase A and phase A concept definition. Over the past several years the ETO team has evaluated thousands of launch vehicle concept variations for a significant number of studies including agency-wide efforts such as the Exploration Systems Architecture Study (ESAS), Constellation, Heavy Lift Launch Vehicle (HLLV), Augustine Report, Heavy Lift Propulsion Technology (HLPT), Human Exploration Framework Team (HEFT), and Space Launch System (SLS). The ACO ETO Team is called upon to address many needs in NASA's design community; some of these are defining extremely large trade-spaces, evaluating advanced technology concepts which have not been addressed by a large majority of the aerospace community, and the rapid turn-around of highly time critical actions. It is the time critical actions, those often limited by schedule or little advanced warning, that have forced the five member ETO team to develop a design process robust enough to handle their current output level in order to meet their customer's needs. Based on the number of vehicle concepts evaluated over the past year this output level averages to four completed vehicle concepts per day. Each of these completed vehicle concepts includes a full mass breakdown of the vehicle to a tertiary level of subsystem components and a vehicle trajectory analysis to determine optimized payload delivery to specified orbital parameters, flight environments, and delta v capability. A structural analysis of the vehicle to determine flight loads based on the trajectory output, material properties, and geometry of the concept is also performed. Due to working in this fast-paced and sometimes rapidly changing environment, the ETO Team has developed a finely tuned process to maximize their delivery capabilities. The objective of this paper is to describe the interfaces

Building and Leading the Next Generation of Exploration Launch Vehicles

NASA Technical Reports Server (NTRS)

Cook, Stephen A.; Vanhooser, Teresa

2010-01-01

NASA s Constellation Program is depending on the Ares Projects to deliver the crew and cargo launch capabilities needed to send human explorers to the Moon and beyond. Ares I and V will provide the core space launch capabilities needed to continue providing crew and cargo access to the International Space Station (ISS), and to build upon the U.S. history of human spaceflight to the Moon and beyond. Since 2005, Ares has made substantial progress on designing, developing, and testing the Ares I crew launch vehicle and has continued its in-depth studies of the Ares V cargo launch vehicle. In 2009, the Ares Projects plan to: conduct the first flight test of Ares I, test-fire the Ares I first stage solid rocket motor; build the first integrated Ares I upper stage; continue testing hardware for the J-2X upper stage engine, and continue refining the design of the Ares V cargo launch vehicle. These efforts come with serious challenges for the project leadership team as it continues to foster a culture of ownership and accountability, operate with limited funding, and works to maintain effective internal and external communications under intense external scrutiny.

Synthesis of block copolymers consists on vinylidene chloride and α- Methylstyrene by cationic polymerization using an acid exchanged motmorillonite clay as heterogeneous catalyst (Algerian MMT)

NASA Astrophysics Data System (ADS)

Ayat, Moulkheir; Belbachir, Mohamed; Rahmouni, Abdelkader

2017-07-01

The aim of this study was to develop the efficient and versatile method for the synthesis of block copolymers consists by cationic polymerization vinylidene chloride (VDC) and alpha-methylstyrene (alpha-MS) in the presence of a natural Algerian montmorillonite clay modified by 0.05-0.35 M H2SO4 (Algerian MMT-H+). It was found that H2SO4 concentration allows controlling the chemical composition, the porous structure of the acid-activated clays and their catalytic performance. The maximal yield of polymer is observed in the presence of Algerian MMT modified by 0.25 M H2SO4. Effects of VDC/MS molar ration, catalyst concentration, reaction time, reaction temperature and polarity medium on yield and molecular weight of polymer were revealed in the presence of the most active sample.

SLS Trade Study 0058: Day of Launch (DOL) Wind Biasing

NASA Technical Reports Server (NTRS)

Decker, Ryan K.; Duffin, Paul; Hill, Ashley; Beck, Roger; Dukeman, Greg

2014-01-01

SLS heritage hardware and legacy designs have shown load exceedances at several locations during Design Analysis Cycles (DAC): MPCV Z bending moments; ICPS Electro-Mechanical Actuator (EMA) loads; Core Stage loads just downstream of Booster forward interface. SLS Buffet Loads Mitigation Task Team (BLMTT) tasked to study issue. Identified low frequency buffet load responses are a function of the vehicle's total angle of attack (AlphaTotal). SLS DOL Wind Biasing Trade team to analyze DOL wind biasing methods to limit maximum AlphaTotal in the M0.8 - 2.0 altitude region for EM-1 and EM-2 missions through investigating: Trajectory design process; Wind wavelength filtering options; Launch availability; DOL process to achieve shorter processing/uplink timeline. Trade Team consisted of personnel supporting SLS, MPCV, GSDO programs.

NASA's Space Launch System (SLS): A New National Capability

NASA Technical Reports Server (NTRS)

May, Todd A.

2012-01-01

The National Aeronautics and Space Administration's (NASA's) Space Launch System (SLS) will contribute a new national capability for human space flight and scientific missions to low- Earth orbit (LEO) and beyond. Exploration beyond Earth orbit will be an enduring legacy to future generations, confirming America s desire to explore, learn, and progress. The SLS Program, managed at NASA s Marshall Space Fight Center, will develop the heavy lift vehicle that will launch the Orion Multi-Purpose Crew Vehicle (MPCV), equipment, supplies, and science experiments for missions beyond Earth s orbit. This paper gives an overview of the SLS design and management approach against a backdrop of the missions it will empower. It will detail the plan to move from the computerized drawing board to the launch pad in the near term, as well as summarize the innovative approaches the SLS team is applying to deliver a safe, affordable, and sustainable long-range national capability.

Integrated Safety Analysis Teams

NASA Technical Reports Server (NTRS)

Wetherholt, Jonathan C.

2008-01-01

Today's complex systems require understanding beyond one person s capability to comprehend. Each system requires a team to divide the system into understandable subsystems which can then be analyzed with an Integrated Hazard Analysis. The team must have both specific experiences and diversity of experience. Safety experience and system understanding are not always manifested in one individual. Group dynamics make the difference between success and failure as well as the difference between a difficult task and a rewarding experience. There are examples in the news which demonstrate the need to connect the pieces of a system into a complete picture. The Columbia disaster is now a standard example of a low consequence hazard in one part of the system; the External Tank is a catastrophic hazard cause for a companion subsystem, the Space Shuttle Orbiter. The interaction between the hardware, the manufacturing process, the handling, and the operations contributed to the problem. Each of these had analysis performed, but who constituted the team which integrated this analysis together? This paper will explore some of the methods used for dividing up a complex system; and how one integration team has analyzed the parts. How this analysis has been documented in one particular launch space vehicle case will also be discussed.

NASA Exploration Launch Projects Overview: The Crew Launch Vehicle and the Cargo Launch Vehicle Systems

NASA Technical Reports Server (NTRS)

Snoddy, Jimmy R.; Dumbacher, Daniel L.; Cook, Stephen A.

2006-01-01

The U.S. Vision for Space Exploration (January 2004) serves as the foundation for the National Aeronautics and Space Administration's (NASA) strategic goals and objectives. As the NASA Administrator outlined during his confirmation hearing in April 2005, these include: 1) Flying the Space Shuttle as safely as possible until its retirement, not later than 2010. 2) Bringing a new Crew Exploration Vehicle (CEV) into service as soon as possible after Shuttle retirement. 3) Developing a balanced overall program of science, exploration, and aeronautics at NASA, consistent with the redirection of the human space flight program to focus on exploration. 4) Completing the International Space Station (ISS) in a manner consistent with international partner commitments and the needs of human exploration. 5) Encouraging the pursuit of appropriate partnerships with the emerging commercial space sector. 6) Establishing a lunar return program having the maximum possible utility for later missions to Mars and other destinations. In spring 2005, the Agency commissioned a team of aerospace subject matter experts to perform the Exploration Systems Architecture Study (ESAS). The ESAS team performed in-depth evaluations of a number of space transportation architectures and provided recommendations based on their findings? The ESAS analysis focused on a human-rated Crew Launch Vehicle (CLV) for astronaut transport and a heavy lift Cargo Launch Vehicle (CaLV) to carry equipment, materials, and supplies for lunar missions and, later, the first human journeys to Mars. After several months of intense study utilizing safety and reliability, technical performance, budget, and schedule figures of merit in relation to design reference missions, the ESAS design options were unveiled in summer 2005. As part of NASA's systems engineering approach, these point of departure architectures have been refined through trade studies during the ongoing design phase leading to the development phase that

Completion of Launch Director Console Project and Other Support Work

NASA Technical Reports Server (NTRS)

Steinrock, Joshua G.

2018-01-01

There were four projects that I was a part of working on during the spring semester of 2018. This included the completion of the Launch Director Console (LDC) project and the completion and submission of a Concept of Operations (ConOps) document for the Record and Playback System (RPS) at the Launch Control Center (LCC), as well as supporting the implementation of a unit in RPS known as the CDP (Communication Data Processor). Also included was my support and mentorship of a High School robotics team that is sponsored by Kennedy Space Center. The LDC project is an innovative workstation to be used by the launch director for the future Space Launch System program. I worked on the fabrication and assembly of the final console. The ConOps on RPS is a technical document for which I produced supporting information and notes. All of this was done in the support of the IT Project Management Office (IT-F). The CDP is a subsystem that will eventually be installed in and operated by RPS.

NASA’s BARREL Mission Launches 20 Balloons

NASA Image and Video Library

2017-12-08

A crane lowers two BARREL balloon payloads onto the platform at Halley Research Station in Antarctica. Credit: NASA --- In Antarctica in January, 2013 – the summer at the South Pole – scientists launched 20 balloons up into the air to study an enduring mystery of space weather: when the giant radiation belts surrounding Earth lose material, where do the extra particles actually go? The mission is called BARREL (Balloon Array for Radiation belt Relativistic Electron Losses) and it is led by physicist Robyn Millan of Dartmouth College in Hanover, NH. Millan provided photographs from the team’s time in Antarctica. The team launched a balloon every day or two into the circumpolar winds that circulate around the pole. Each balloon floated for anywhere from 3 to 40 days, measuring X-rays produced by fast-moving electrons high up in the atmosphere. BARREL works hand in hand with another NASA mission called the Van Allen Probes, which travels through the Van Allen radiation belts surrounding Earth. The belts wax and wane over time in response to incoming energy and material from the sun, sometimes intensifying the radiation through which satellites must travel. Scientists wish to understand this process better, and even provide forecasts of this space weather, in order to protect our spacecraft. As the Van Allen Probes were observing what was happening in the belts, BARREL tracked electrons that precipitated out of the belts and hurtled down Earth’s magnetic field lines toward the poles. By comparing data, scientists will be able to track how what’s happening in the belts correlates to the loss of particles – information that can help us understand this mysterious, dynamic region that can impact spacecraft. Having launched balloons in early 2013, the team is back at home building the next set of payloads. They will launch 20 more balloons in 2014. NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors

NASA’s BARREL Mission Launches 20 Balloons

NASA Image and Video Library

2017-12-08

The BARREL cargo on its four-hour journey from the supply ship to the research station. Credit: NASA --- In Antarctica in January, 2013 – the summer at the South Pole – scientists launched 20 balloons up into the air to study an enduring mystery of space weather: when the giant radiation belts surrounding Earth lose material, where do the extra particles actually go? The mission is called BARREL (Balloon Array for Radiation belt Relativistic Electron Losses) and it is led by physicist Robyn Millan of Dartmouth College in Hanover, NH. Millan provided photographs from the team’s time in Antarctica. The team launched a balloon every day or two into the circumpolar winds that circulate around the pole. Each balloon floated for anywhere from 3 to 40 days, measuring X-rays produced by fast-moving electrons high up in the atmosphere. BARREL works hand in hand with another NASA mission called the Van Allen Probes, which travels through the Van Allen radiation belts surrounding Earth. The belts wax and wane over time in response to incoming energy and material from the sun, sometimes intensifying the radiation through which satellites must travel. Scientists wish to understand this process better, and even provide forecasts of this space weather, in order to protect our spacecraft. As the Van Allen Probes were observing what was happening in the belts, BARREL tracked electrons that precipitated out of the belts and hurtled down Earth’s magnetic field lines toward the poles. By comparing data, scientists will be able to track how what’s happening in the belts correlates to the loss of particles – information that can help us understand this mysterious, dynamic region that can impact spacecraft. Having launched balloons in early 2013, the team is back at home building the next set of payloads. They will launch 20 more balloons in 2014. NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors: Earth Science

NASA’s BARREL Mission Launches 20 Balloons

NASA Image and Video Library

2017-12-08

Liftoff! A balloon begins to rise over the brand new Halley VI Research Station, which had its grand opening in February 2013. Credit: NASA --- In Antarctica in January, 2013 – the summer at the South Pole – scientists launched 20 balloons up into the air to study an enduring mystery of space weather: when the giant radiation belts surrounding Earth lose material, where do the extra particles actually go? The mission is called BARREL (Balloon Array for Radiation belt Relativistic Electron Losses) and it is led by physicist Robyn Millan of Dartmouth College in Hanover, NH. Millan provided photographs from the team’s time in Antarctica. The team launched a balloon every day or two into the circumpolar winds that circulate around the pole. Each balloon floated for anywhere from 3 to 40 days, measuring X-rays produced by fast-moving electrons high up in the atmosphere. BARREL works hand in hand with another NASA mission called the Van Allen Probes, which travels through the Van Allen radiation belts surrounding Earth. The belts wax and wane over time in response to incoming energy and material from the sun, sometimes intensifying the radiation through which satellites must travel. Scientists wish to understand this process better, and even provide forecasts of this space weather, in order to protect our spacecraft. As the Van Allen Probes were observing what was happening in the belts, BARREL tracked electrons that precipitated out of the belts and hurtled down Earth’s magnetic field lines toward the poles. By comparing data, scientists will be able to track how what’s happening in the belts correlates to the loss of particles – information that can help us understand this mysterious, dynamic region that can impact spacecraft. Having launched balloons in early 2013, the team is back at home building the next set of payloads. They will launch 20 more balloons in 2014. NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through

NASA’s BARREL Mission Launches 20 Balloons

NASA Image and Video Library

2017-12-08

Watching a BARREL balloon – and the instruments dangling below – float up over the SANAE IV research base in Antarctica. Credit: NASA --- In Antarctica in January, 2013 – the summer at the South Pole – scientists launched 20 balloons up into the air to study an enduring mystery of space weather: when the giant radiation belts surrounding Earth lose material, where do the extra particles actually go? The mission is called BARREL (Balloon Array for Radiation belt Relativistic Electron Losses) and it is led by physicist Robyn Millan of Dartmouth College in Hanover, NH. Millan provided photographs from the team’s time in Antarctica. The team launched a balloon every day or two into the circumpolar winds that circulate around the pole. Each balloon floated for anywhere from 3 to 40 days, measuring X-rays produced by fast-moving electrons high up in the atmosphere. BARREL works hand in hand with another NASA mission called the Van Allen Probes, which travels through the Van Allen radiation belts surrounding Earth. The belts wax and wane over time in response to incoming energy and material from the sun, sometimes intensifying the radiation through which satellites must travel. Scientists wish to understand this process better, and even provide forecasts of this space weather, in order to protect our spacecraft. As the Van Allen Probes were observing what was happening in the belts, BARREL tracked electrons that precipitated out of the belts and hurtled down Earth’s magnetic field lines toward the poles. By comparing data, scientists will be able to track how what’s happening in the belts correlates to the loss of particles – information that can help us understand this mysterious, dynamic region that can impact spacecraft. Having launched balloons in early 2013, the team is back at home building the next set of payloads. They will launch 20 more balloons in 2014. NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four

Comprehensive Software Simulation on Ground Power Supply for Launch Pads and Processing Facilities at NASA Kennedy Space Center

NASA Technical Reports Server (NTRS)

Dominguez, Jesus A.; Victor, Elias; Vasquez, Angel L.; Urbina, Alfredo R.

2017-01-01

A multi-threaded software application has been developed in-house by the Ground Special Power (GSP) team at NASA Kennedy Space Center (KSC) to separately simulate and fully emulate all units that supply VDC power and battery-based power backup to multiple KSC launch ground support systems for NASA Space Launch Systems (SLS) rocket.

Ares I Crew Launch Vehicle Upper Stage Element Overview

NASA Technical Reports Server (NTRS)

McArthur, J. Craig

2008-01-01

This viewgraph presentation gives an overview of NASA's Ares I Crew Launch Vehicle Upper Stage Element. The topics include: 1) What is NASA s Mission?; 2) NASA s Exploration Roadmap What is our time line?; 3) Building on a Foundation of Proven Technologies Launch Vehicle Comparisons; 4) Ares I Upper Stage; 5) Upper Stage Primary Products; 6) Ares I Upper Stage Development Approach; 7) What progress have we made?; 8) Upper Stage Subsystem Highlights; 9) Structural Testing; 10) Common Bulkhead Processing; 11) Stage Installation at Stennis Space Center; 12) Boeing Producibility Team; 13) Upper Stage Low Cost Strategy; 14) Ares I and V Production at Michoud Assembly Facility (MAF); 15) Merged Manufacturing Flow; and 16) Manufacturing and Assembly Weld Tools.

Launch and Commissioning of the Deep Space Climate Observatory

NASA Technical Reports Server (NTRS)

Frey, Nicholas P.; Davis, Edward P.

2016-01-01

The Deep Space Climate Observatory (DSCOVR), formerly known as Triana, successfully launched on February 11th, 2015. To date, each of the five space-craft attitude control system (ACS) modes have been operating as expected and meeting all guidance, navigation, and control (GN&C) requirements, although since launch, several anomalies were encountered. While unplanned, these anomalies have proven to be invaluable in developing a deeper understanding of the ACS, and drove the design of three alterations to the ACS task of the flight software (FSW). An overview of the GN&C subsystem hardware, including re-furbishment, and ACS architecture are introduced, followed by a chronological discussion of key events, flight performance, as well as anomalies encountered by the GN&C team.

Microwave Anisotrophy Probe Launch and Early Operations

NASA Technical Reports Server (NTRS)

ODonnell, James R., Jr.; Andrews, Stephen F.; Starin, Scott R.; Ward, David K.; Bauer, Frank H. (Technical Monitor)

2002-01-01

The Microwave Anisotropy Probe (MAP), a follow-on to the Differential Microwave Radiometer (DMR) instrument on the Cosmic Background Explorer (COBE), was launched from the Kennedy Space Center at 19:46:46 UTC on June 30, 2001. The powered flight and separation from the Delta II appeared to go as designed, with the launch placing MAP well within sigma launch dispersion and with less than 7 Nms of tip-off momentum. Because of this relatively low momentum, MAP was able to acquire the sun within only 15 minutes with a battery state of charge of 94%. After MAP's successful launch, a six week period of in-orbit checkout and orbit maneuvers followed. The dual purpose of the in-orbit checkout period was to validate the correct performance of all of MAP's systems and, from the attitude control system (ACS) point of view, to calibrate the performance of the spacecraft ACS sensors and actuators to maximize system performance. In addition to the checkout activities performed by the MAP team, the other critical activity taking place during the first six weeks after launch were a series of orbit maneuvers necessary to get the spacecraft from its launch orbit out to its desired orbit about L2, the second Earth-Sun Lagrange point. As MAP continues its standard operations, its ACS design is meeting all of its requirements to successfully complete the mission. This paper will describe the launch and early operations summarized above in greater detail, and show the performance of the attitude control and attitude determination system versus its requirements. Additionally, some of the unexpected events that occurred during this period will be discussed, including two events which dropped the spacecraft into its Safehold Mode and the presence of an "anomalous force" observed during each of the perigee orbit maneuvers that had the potential to cause these critical maneuvers to be prematurely aborted.

New Product Launching Ideas

NASA Astrophysics Data System (ADS)

Kiruthika, E.

2012-09-01

Launching a new product can be a tense time for a small or large business. There are those moments when you wonder if all of the work done to develop the product will pay off in revenue, but there are many things are can do to help increase the likelihood of a successful product launch. An open-minded consumer-oriented approach is imperative in todayís diverse global marketplace so a firm can identify and serve its target market, minimize dissatisfaction, and stay ahead of competitors. Final consumers purchase for personal, family, or household use. Finally, the kind of information that the marketing team needs to provide customers in different buying situations. In high-involvement decisions, the marketer needs to provide a good deal of information about the positive consequences of buying. The sales force may need to stress the important attributes of the product, the advantages compared with the competition; and maybe even encourage ìtrialî or ìsamplingî of the product in the hope of securing the sale. The final stage is the post-purchase evaluation of the decision. It is common for customers to experience concerns after making a purchase decision. This arises from a concept that is known as ìcognitive dissonance

50 Years of Electronic Check Out and Launch Systems at Kennedy Space Center

NASA Technical Reports Server (NTRS)

Starr, Stanley O.

2007-01-01

When NASA was created in 1958 one of the elements incorporated into this new agency was the Army Ballistic Missile Agency (ABMA) in Huntsville, AL and its subordinate Missile Firing Laboratory (MFL) in Cape Canaveral. Under NASA, the MFL became the Launch Operations Directorate of the George C. Marshall Space Flight Center in Huntsville, but expanding operations in the build up to Apollo dictated that it be given the status of a full fledged Center in July, 1 962[ 1]. The next year it was renamed the John F. Kennedy Space Center (KS C) after the president whose vision transformed its first decade of operation. The ABMA was under the technical leadership of Dr. Werner Von Braun. The MEL was run by his deputy Dr. Kurt Debus, an electrical engineer whose experience in the field began in the early days of V-2 testing in war time Germany. In 1952 a group led by Debus arrived in Cape Canaveral to begin test launches of the new Redstone missile [2]. During the 50's, The MFL built several launch complexes and tested the Redstone, Jupiter and Jupiter C missiles. This small experienced team of engineers and technicians formed the seed from which has grown the KSC team of today. This article briefly reviews the evolution of the KSC electronic technologies for integration, check-out and launch of space vehicles and payloads during NASA's first 50 years.

NASA’s BARREL Mission Launches 20 Balloons

NASA Image and Video Library

2017-12-08

A BARREL balloon floats into the sky as it is partially filled. When fully inflated, each balloon is 90 feet in diameter and carries an instrument suite that weighs 50 pounds. This is small for an Antarctica balloon launch, which can have balloons Typical balloons l the size of a football field with payloads of some 3,000 pounds. Credit: NASA --- In Antarctica in January, 2013 – the summer at the South Pole – scientists launched 20 balloons up into the air to study an enduring mystery of space weather: when the giant radiation belts surrounding Earth lose material, where do the extra particles actually go? The mission is called BARREL (Balloon Array for Radiation belt Relativistic Electron Losses) and it is led by physicist Robyn Millan of Dartmouth College in Hanover, NH. Millan provided photographs from the team’s time in Antarctica. The team launched a balloon every day or two into the circumpolar winds that circulate around the pole. Each balloon floated for anywhere from 3 to 40 days, measuring X-rays produced by fast-moving electrons high up in the atmosphere. BARREL works hand in hand with another NASA mission called the Van Allen Probes, which travels through the Van Allen radiation belts surrounding Earth. The belts wax and wane over time in response to incoming energy and material from the sun, sometimes intensifying the radiation through which satellites must travel. Scientists wish to understand this process better, and even provide forecasts of this space weather, in order to protect our spacecraft. As the Van Allen Probes were observing what was happening in the belts, BARREL tracked electrons that precipitated out of the belts and hurtled down Earth’s magnetic field lines toward the poles. By comparing data, scientists will be able to track how what’s happening in the belts correlates to the loss of particles – information that can help us understand this mysterious, dynamic region that can impact spacecraft. Having launched balloons in

Managed Development Environment Successes for MSFC's VIPA Team

NASA Technical Reports Server (NTRS)

Finckenor, Jeff; Corder, Gary; Owens, James; Meehan, Jim; Tidwell, Paul H.

2005-01-01

This paper outlines the best practices of the Vehicle Design Team for VIPA. The functions of the VIPA Vehicle Design (VVD) discipline team are to maintain the controlled reference geometry and provide linked, simplified geometry for each of the other discipline analyses. The core of the VVD work, and the approach for VVD s first task of controlling the reference geometry, involves systems engineering, top-down, layout-based CAD modeling within a Product Data Manager (PDM) development environment. The top- down approach allows for simple control of very large, integrated assemblies and greatly enhances the ability to generate trade configurations and reuse data. The second VVD task, model simplification for analysis, is handled within the managed environment through application of the master model concept. In this approach, there is a single controlling, or master, product definition dataset. Connected to this master model are reference datasets with live geometric and expression links. The referenced models can be for drawings, manufacturing, visualization, embedded analysis, or analysis simplification. A discussion of web based interaction, including visualization, between the design and other disciplines is included. Demonstrated examples are cited, including the Space Launch Initiative development cycle, the Saturn V systems integration and verification cycle, an Orbital Space Plane study, and NASA Exploration Office studies of Shuttle derived and clean sheet launch vehicles. The VIPA Team has brought an immense amount of detailed data to bear on program issues. A central piece of that success has been the Managed Development Environment and the VVD Team approach to modeling.

Deep Impact Delta II Launch Vehicle Cracked Thick Film Coating on Electronic Packages Technical Consultation Report

NASA Technical Reports Server (NTRS)

Cameron, Kenneth D.; Kichak, Robert A.; Piascik, Robert S.; Leidecker, Henning W.; Wilson, Timmy R.

2009-01-01

The Deep Impact spacecraft was launched on a Boeing Delta II rocket from Cape Canaveral Air Force Station (CCAFS) on January 12, 2005. Prior to the launch, the Director of the Office of Safety and Mission Assurance (OS&MA) requested the NASA Engineering and Safety Center (NESC) lead a team to render an independent opinion on the rationale for flight and the risk code assignments for the hazard of cracked Thick Film Assemblies (TFAs) in the E-packages of the Delta II launch vehicle for the Deep Impact Mission. The results of the evaluation are contained in this report.

eLaunch Hypersonics: An Advanced Launch System

NASA Technical Reports Server (NTRS)

Starr, Stanley

2010-01-01

This presentation describes a new space launch system that NASA can and should develop. This approach can significantly reduce ground processing and launch costs, improve reliability, and broaden the scope of what we do in near earth orbit. The concept (not new) is to launch a re-usable air-breathing hypersonic vehicle from a ground based electric track. This vehicle launches a final rocket stage at high altitude/velocity for the final leg to orbit. The proposal here differs from past studies in that we will launch above Mach 1.5 (above transonic pinch point) which further improves the efficiency of air breathing, horizontal take-off launch systems. The approach described here significantly reduces cost per kilogram to orbit, increases safety and reliability of the boost systems, and reduces ground costs due to horizontal-processing. Finally, this approach provides significant technology transfer benefits for our national infrastructure.

Resolving the Dusty Circumstellar Structure of the Enigmatic Symbiotic Star CH Cygni with the MMT Adaptive Optics System

NASA Astrophysics Data System (ADS)

Biller, Beth A.; Close, Laird M.; Li, Aigen; Marengo, Massimo; Bieging, John H.; Hinz, Phil M.; Hoffmann, William F.; Brusa, Guido; Miller, Doug

2006-08-01

We imaged the symbiotic star CH Cyg and two PSF calibration stars using the unique 6.5 m MMT deformable secondary adaptive optics system. Our high-resolution (FWHM = 0.3"), very high Strehl (98%+/-2%), mid-infrared (9.8 and 11.7 μm) images of CH Cyg allow us to probe finer length scales than ever before for this object. CH Cyg is significantly extended compared to our unresolved PSF calibration stars (μ UMa and α Her) at 9.8 and 11.7 μm. We estimated the size of the extension by convolving a number of simple Gaussian models with the μ UMa PSF and determining which model provided the best fit to the data. Adopting the Hipparcos distance for this object of 270 pc, we found a nearly Gaussian extension with a FWHM at 9.8 μm of ~40.5+/-2.7 AU (0.15"+/-0.01") and a FWHM at 11.7 μm of 45.9+/-2.7 AU (0.17"+/-0.01"). After subtracting out the Gaussian component of the emission (convolved with our PSF), we found a faint ~ 0.7" asymmetric extension, which peaks in flux ~0.5" north of the stars. This extension is roughly coincident with the northern knotlike feature seen in HST WFPC2 images obtained in 1999. The results presented here made use of the of MMT Observatory, a facility jointly operated by the University of Arizona and the Smithsonian Institution.

Space Launch System Development Status

NASA Technical Reports Server (NTRS)

Lyles, Garry

2014-01-01

Development of NASA's Space Launch System (SLS) heavy lift rocket is shifting from the formulation phase into the implementation phase in 2014, a little more than three years after formal program approval. Current development is focused on delivering a vehicle capable of launching 70 metric tons (t) into low Earth orbit. This "Block 1" configuration will launch the Orion Multi-Purpose Crew Vehicle (MPCV) on its first autonomous flight beyond the Moon and back in December 2017, followed by its first crewed flight in 2021. SLS can evolve to a130-t lift capability and serve as a baseline for numerous robotic and human missions ranging from a Mars sample return to delivering the first astronauts to explore another planet. Benefits associated with its unprecedented mass and volume include reduced trip times and simplified payload design. Every SLS element achieved significant, tangible progress over the past year. Among the Program's many accomplishments are: manufacture of Core Stage test panels; testing of Solid Rocket Booster development hardware including thrust vector controls and avionics; planning for testing the RS-25 Core Stage engine; and more than 4,000 wind tunnel runs to refine vehicle configuration, trajectory, and guidance. The Program shipped its first flight hardware - the Multi-Purpose Crew Vehicle Stage Adapter (MSA) - to the United Launch Alliance for integration with the Delta IV heavy rocket that will launch an Orion test article in 2014 from NASA's Kennedy Space Center. Objectives of this Earth-orbit flight include validating the performance of Orion's heat shield and the MSA design, which will be manufactured again for SLS missions to deep space. The Program successfully completed Preliminary Design Review in 2013 and Key Decision Point C in early 2014. NASA has authorized the Program to move forward to Critical Design Review, scheduled for 2015 and a December 2017 first launch. The Program's success to date is due to prudent use of proven

NASA'S Space Launch System Mission Capabilities for Exploration

NASA Technical Reports Server (NTRS)

Creech, Stephen D.; Crumbly, Christopher M.; Robinson, Kimberly F.

2015-01-01

Designed to enable human space exploration missions, including eventual landings on Mars, NASA’s Space Launch System (SLS) represents a unique launch capability with a wide range of utilization opportunities, from delivering habitation systems into the lunar vicinity to high-energy transits through the outer solar system. Developed with the goals of safety, affordability and sustainability in mind, SLS is a foundational capability for NASA’s future plans for exploration, along with the Orion crew vehicle and upgraded ground systems at the agency’s Kennedy Space Center. Substantial progress has been made toward the first launch of the initial configuration of SLS, which will be able to deliver more than 70 metric tons of payload into low Earth orbit (LEO), greater mass-to-orbit capability than any contemporary launch vehicle. The vehicle will then be evolved into more powerful configurations, culminating with the capability to deliver more than 130 metric tons to LEO, greater even than the Saturn V rocket that enabled human landings on the moon. SLS will also be able to carry larger payload fairings than any contemporary launch vehicle, and will offer opportunities for co-manifested and secondary payloads. Because of its substantial mass-lift capability, SLS will also offer unrivaled departure energy, enabling mission profiles currently not possible. Early collaboration with science teams planning future decadal-class missions have contributed to a greater understanding of the vehicle’s potential range of utilization. This presentation will discuss the potential opportunities this vehicle poses for the planetary sciences community, relating the vehicle’s evolution to practical implications for mission capture. As this paper will explain, SLS will be a global launch infrastructure asset, employing sustainable solutions and technological innovations to deliver capabilities for space exploration to power human and robotic systems beyond our Moon and in to

NASA's Space Launch System Mission Capabilities for Exploration

NASA Technical Reports Server (NTRS)

Creech, Stephen D.; Crumbly, Christopher M.; Robinson, Kimberly F.

2015-01-01

Designed to enable human space exploration missions, including eventual landings on Mars, NASA's Space Launch System (SLS) represents a unique launch capability with a wide range of utilization opportunities, from delivering habitation systems into the lunar vicinity to high-energy transits through the outer solar system. Developed with the goals of safety, affordability and sustainability in mind, SLS is a foundational capability for NASA's future plans for exploration, along with the Orion crew vehicle and upgraded ground systems at the agency's Kennedy Space Center. Substantial progress has been made toward the first launch of the initial configuration of SLS, which will be able to deliver more than 70 metric tons of payload into low Earth orbit (LEO), greater mass-to-orbit capability than any contemporary launch vehicle. The vehicle will then be evolved into more powerful configurations, culminating with the capability to deliver more than 130 metric tons to LEO, greater even than the Saturn V rocket that enabled human landings on the moon. SLS will also be able to carry larger payload fairings than any contemporary launch vehicle, and will offer opportunities for co-manifested and secondary payloads. Because of its substantial mass-lift capability, SLS will also offer unrivaled departure energy, enabling mission profiles currently not possible. Early collaboration with science teams planning future decadal-class missions have contributed to a greater understanding of the vehicle's potential range of utilization. This presentation will discuss the potential opportunities this vehicle poses for the planetary sciences community, relating the vehicle's evolution to practical implications for mission capture. As this paper will explain, SLS will be a global launch infrastructure asset, employing sustainable solutions and technological innovations to deliver capabilities for space exploration to power human and robotic systems beyond our Moon and in to deep space.

Shuttle-Derived Launch Vehicles' Capablities: An Overview

NASA Technical Reports Server (NTRS)

Rothschild, William J.; Bailey, Debra A.; Henderson, Edward M.; Crumbly, Chris

2005-01-01

Shuttle-Derived Launch Vehicle (SDLV) concepts have been developed by a collaborative team comprising the Johnson Space Center, Marshall Space Flight Center, Kennedy Space Center, ATK-Thiokol, Lockheed Martin Space Systems Company, The Boeing Company, and United Space Alliance. The purpose of this study was to provide timely information on a full spectrum of low-risk, cost-effective options for STS-Derived Launch Vehicle concepts to support the definition of crew and cargo launch requirements for the Space Exploration Vision. Since the SDLV options use high-reliability hardware, existing facilities, and proven processes, they can provide relatively low-risk capabilities to launch extremely large payloads to low Earth orbit. This capability to reliably lift very large, high-dollar-value payloads could reduce mission operational risks by minimizing the number of complex on-orbit operations compared to architectures based on multiple smaller launchers. The SDLV options also offer several logical spiral development paths for larger exploration payloads. All of these development paths make practical and cost-effective use of existing Space Shuttle Program (SSP) hardware, infrastructure, and launch and flight operations systems. By utilizing these existing assets, the SDLV project could support the safe and orderly transition of the current SSP through the planned end of life in 2010. The SDLV concept definition work during 2004 focused on three main configuration alternatives: a side-mount heavy lifter (approximately 77 MT payload), an in-line medium lifter (approximately 22 MT Crew Exploration Vehicle payload), and an in-line heavy lifter (greater than 100 MT payload). This paper provides an overview of the configuration, performance capabilities, reliability estimates, concept of operations, and development plans for each of the various SDLV alternatives. While development, production, and operations costs have been estimated for each of the SDLV configuration

Global Precipitation Measurement Mission Launch and Commissioning

NASA Technical Reports Server (NTRS)

Davis, Nikesha; DeWeese, Keith; Vess, Melissa; O'Donnell, James R., Jr.; Welter, Gary

2015-01-01

During launch and early operation of the Global Precipitation Measurement (GPM) Mission, the Guidance, Navigation, and Control (GN&C) analysis team encountered four main on-orbit anomalies. These include: (1) unexpected shock from Solar Array deployment, (2) momentum buildup from the Magnetic Torquer Bars (MTBs) phasing errors, (3) transition into Safehold due to albedo induced Course Sun Sensor (CSS) anomaly, and (4) a flight software error that could cause a Safehold transition due to a Star Tracker occultation. This paper will discuss ways GN&C engineers identified the anomalies and tracked down the root causes. Flight data and GN&C on-board models will be shown to illustrate how each of these anomalies were investigated and mitigated before causing any harm to the spacecraft. On May 29, 2014, GPM was handed over to the Mission Flight Operations Team after a successful commissioning period. Currently, GPM is operating nominally on orbit, collecting meaningful scientific data that will significantly improve our understanding of the Earth's climate and water cycle.

Aerodynamic Characterization of a Modern Launch Vehicle

NASA Technical Reports Server (NTRS)

Hall, Robert M.; Holland, Scott D.; Blevins, John A.

2011-01-01

A modern launch vehicle is by necessity an extremely integrated design. The accurate characterization of its aerodynamic characteristics is essential to determine design loads, to design flight control laws, and to establish performance. The NASA Ares Aerodynamics Panel has been responsible for technical planning, execution, and vetting of the aerodynamic characterization of the Ares I vehicle. An aerodynamics team supporting the Panel consists of wind tunnel engineers, computational engineers, database engineers, and other analysts that address topics such as uncertainty quantification. The team resides at three NASA centers: Langley Research Center, Marshall Space Flight Center, and Ames Research Center. The Panel has developed strategies to synergistically combine both the wind tunnel efforts and the computational efforts with the goal of validating the computations. Selected examples highlight key flow physics and, where possible, the fidelity of the comparisons between wind tunnel results and the computations. Lessons learned summarize what has been gleaned during the project and can be useful for other vehicle development projects.

Global Precipitation Measurement Mission Launch and Commissioning

NASA Technical Reports Server (NTRS)

Davis, Nikesha; Deweese, Keith; Vess, Missie; Welter, Gary; O'Donnell, James R., Jr.

2015-01-01

During launch and early operation of the Global Precipitation Measurement (GPM) Mission, the Guidance, Navigation and Control (GNC) analysis team encountered four main on orbit anomalies. These include: (1) unexpected shock from Solar Array deployment, (2) momentum buildup from the Magnetic Torquer Bars (MTBs) phasing errors, (3) transition into Safehold due to albedo-induced Course Sun Sensor (CSS) anomaly, and (4) a flight software error that could cause a Safehold transition due to a Star Tracker occultation. This paper will discuss ways GNC engineers identified and tracked down the root causes. Flight data and GNC on board models will be shown to illustrate how each of these anomalies were investigated and mitigated before causing any harm to the spacecraft. On May 29, 2014, GPM was handed over to the Mission Flight Operations Team after a successful commissioning period. Currently, GPM is operating nominally on orbit, collecting meaningful scientific data that will significantly improve our understanding of the Earth's climate and water cycle.

Launch Order, Launch Separation, and Loiter in the Constellation 1 1/2-Launch Solution

NASA Technical Reports Server (NTRS)

Stromgren, Chel; Cates, Grant; Cirillo, William

2009-01-01

The NASA Constellation Program (CxP) is developing a two-element Earth-to-Orbit launch system to enable human exploration of the Moon. The first element, Ares I, is a human-rated system that consists of a first stage based on the Space Shuttle Program's solid rocket booster (SRB) and an upper stage that consists of a four-crew Orion capsule, a service module, and a Launch Escape System. The second element, Ares V, is a Saturn V-plus category launch system that consists of the core stage with a cluster of six RS-68B engines and augmented with two 5.5-segment SRBs, a Saturn-derived J-2X engine powering an Earth Departure Stage (EDS), and the lunar-lander vehicle payload, Altair. Initial plans called for the Ares V to be launched first, followed the next day by the Ares I. After the EDS performs the final portion of ascent and subsequent orbit circularization, the Orion spacecraft then performs a rendezvous and docks with the EDS and its Altair payload. Following checkout, the integrated stack loiters in low Earth orbit (LEO) until the appropriate Trans-Lunar Injection (TLI) window opportunity opens, at which time the EDS propels the integrated Orion Altair to the Moon. Successful completion of this 1 1/2-launch solution carries risks related to both the orbital lifetime of the assets and the probability of achieving the launch of the second vehicle within the orbital lifetime of the first. These risks, which are significant in terms of overall system design choices and probability of mission success, dictated a thorough reevaluation of the launch strategy, including the order of vehicle launch and the planned time period between launches. The goal of the effort described in this paper was to select a launch strategy that would result in the greatest possible expected system performance, while accounting for launch risks and the cost of increased orbital lifetime. Discrete Event Simulation (DES) model of the launch strategies was created to determine the probability

STS-90 Mission Commander Richard Searfoss is suited up for launch

NASA Technical Reports Server (NTRS)

1998-01-01

STS-90 Mission Specialist Kathryn (Kay) Hire prepares for launch during suitup activities in the Operations and Checkout Building as Astronaut Support Personnel team member Heidi Piper braids Hire's hair. Hire and the rest of the STS-90 crew will shortly depart for Launch Pad 39B, where the Space Shuttle Columbia awaits a second liftoff attempt at 2:19 p.m. EDT. Her first trip into space, Hire is participating in this life sciences research flight that will focus on the most complex and least understood part of the human body -- the nervous system. Neurolab will examine the effects of spaceflight on the brain, spinal cord, peripheral nerves and sensory organs in the human body.

66. DETAIL OF LAUNCH CONDUCTOR AND ASSISTANT LAUNCH CONDUCTOR PANELS ...

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

66. DETAIL OF LAUNCH CONDUCTOR AND ASSISTANT LAUNCH CONDUCTOR PANELS IN CONSOLE LOCATED CENTRALLY IN SLC-3E CONTROL ROOM. FROM LEFT TO RIGHT IN BACKGROUND: LAUNCH OPERATOR, LAUNCH ANALYST, AND FACILITIES PANELS. - Vandenberg Air Force Base, Space Launch Complex 3, Launch Operations Building, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

The U.S. Women's World Cup Soccer Team poses with astronauts and Dan Goldin

NASA Technical Reports Server (NTRS)

1999-01-01

Members of the U.S. World Cup Soccer Team pose with Astronauts Scott Parazynski, Heidemarie M. Stefanyshyn-Piper, Steven W. Lindsey, and Nancy Jane Currie and NASA Administrator Daniel Goldin after the team's arrival at the Skid Strip at Cape Canaveral Air Station. The team arrived with First Lady Hillary Rodham Clinton to view the launch of Space Shuttle mission STS- 93. Liftoff is scheduled for 12:36 a.m. EDT July 20. Much attention has been generated over the launch due to Commander Eileen M. Collins, the first woman to serve as commander of a Shuttle mission. The primary payload of the five-day mission is the Chandra X-ray Observatory, which will allow scientists from around the world to study some of the most distant, powerful and dynamic objects in the universe. The new telescope is 20 to 50 times more sensitive than any previous X-ray telescope and is expected to unlock the secrets of supernovae, quasars and black holes.

Marshall Team Complete Testing for Lunar Atmosphere and Dust Environment Explorer

NASA Technical Reports Server (NTRS)

Swofford, Philip

2013-01-01

Dr. Huu Trinh and his team with the Propulsion Systems and Test Departments at Marshall Space Flight Center in Huntsville, Ala. successfully complete a simulated cold-flow test series on the propulsion system used for the Lunar Atmosphere and Dust Environment Explorer (LADEE) spacecraft. NASA Ames Research Center, Moffett Field, Calif., is leading NASA s work on the development of the LADEE spacecraft, and the Marshall center is the program office for the project. The spacecraft, scheduled for launch this fall, will orbit the Moon and gather information about the lunar atmosphere, conditions near the surface of the Moon, and collect samples of lunar dust. A thorough understanding of these characteristics will address long-standing unknowns, and help scientists understand other planetary bodies as well. The test team at the Marshall center conducted the cold flow test to identify how the fluid flows through the propulsion system feed lines, especially during critical operation modes. The test data will be used to assist the LADEE team in identifying any potential flow issues in the propulsion system, and allow them to address and correct them in advance of the launch.

Pre-Launch Tasks Proposed in our Contract of December 1991

NASA Technical Reports Server (NTRS)

1998-01-01

We propose, during the pre-EOS phase to: (1) develop, with other MODIS Team Members, a means of discriminating different major biome types with NDVI and other AVHRR-based data; (2) develop a simple ecosystem process model for each of these biomes, BIOME-BGC; (3) relate the seasonal trend of weekly composite NDVI to vegetation phenology and temperature limits to develop a satellite defined growing season for vegetation; and (4) define physiologically based energy to mass conversion factors for carbon and water for each biome. Our final core at-launch product will be simplified, completely satellite driven biome specific models for net primary production. We will build these biome specific satellite driven algorithms using a family of simple ecosystem process models as calibration models, collectively called BIOME-BGC, and establish coordination with an existing network of ecological study sites in order to test and validate these products. Field datasets will then be available for both BIOME-BGC development and testing, use for algorithm developments of other MODIS Team Members, and ultimately be our first test point for MODIS land vegetation products upon launch. We will use field sites from the National Science Foundation Long-Term Ecological Research network, and develop Glacier National Park as a major site for intensive validation.

Pre-Launch Tasks Proposed in our Contract of December 1991

NASA Technical Reports Server (NTRS)

Running, Steven W.; Nemani, Ramakrishna R.; Glassy, Joseph

1997-01-01

We propose, during the pre-EOS phase to: (1) develop, with other MODIS Team Members, a means of discriminating different major biome types with NDVI and other AVHRR-based data. (2) develop a simple ecosystem process model for each of these biomes, BIOME-BGC (3) relate the seasonal trend of weekly composite NDVI to vegetation phenology and temperature limits to develop a satellite defined growing season for vegetation; and (4) define physiologically based energy to mass conversion factors for carbon and water for each biome. Our final core at-launch product will be simplified, completely satellite driven biome specific models for net primary production. We will build these biome specific satellite driven algorithms using a family of simple ecosystem process models as calibration models, collectively called BIOME-BGC, and establish coordination with an existing network of ecological study sites in order to test and validate these products. Field datasets will then be available for both BIOME-BGC development and testing, use for algorithm developments of other MODIS Team Members, and ultimately be our first test point for MODIS land vegetation products upon launch. We will use field sites from the National Science Foundation Long-Term Ecological Research network, and develop Glacier National Park as a major site for intensive validation.

Rockot Launch Vehicle Commercial Operations for Grace and Iridium Program

NASA Astrophysics Data System (ADS)

Viertel, Y.; Kinnersley, M.; Schumacher, I.

2002-01-01

The GRACE mission and the IRIDIUM mission on ROCKOT launch vehicle are presented. Two identical GRACE satellites to measure in tandem the gravitational field of the earth with previously unattainable accuracy - it's called the Gravity Research and Climate Experiment, or and is a joint project of the U.S. space agency, NASA and the German Centre for Aeronautics and Space Flight, DLR. In order to send the GRACE twins into a 500x500 km , 89deg. orbit, the Rockot launch vehicle was selected. A dual launch of two Iridium satellites was scheduled for June 2002 using the ROCKOT launch vehicle from Plesetsk Cosmodrome in Northern Russia. This launch will inject two replacement satellites into a low earth orbit (LEO) to support the maintenance of the Iridium constellation. In September 2001, Eurockot successfully carried out a "Pathfinder Campaign" to simulate the entire Iridium mission cycle at Plesetsk. The campaign comprised the transport of simulators and related equipment to the Russian port-of-entry and launch site and also included the integration and encapsulation of the simulators with the actual Rockot launch vehicle at Eurockot's dedicated launch facilities at Plesetsk Cosmodrome. The pathfinder campaign lasted four weeks and was carried out by a joint team that also included Khrunichev, Russian Space Forces and Eurockot personnel on the contractors' side. The pathfinder mission confirmed the capability of Eurockot Launch Services to perform the Iridium launch on cost and on schedule at Plesetsk following Eurockot's major investment in international standard preparation, integration and launch facilities including customer facilities and a new hotel. In 2003, Eurockot will also launch the Japanese SERVI'S-1 satellite for USEF. The ROCKOT launch vehicle is a 3 stage liquid fuel rocket whose first 2 stages have been adapted from the Russian SS-19. A third stage, called "Breeze", can be repeatedly ignited and is extraordinarily capable of manoeuvre. Rockot can place

Expendable launch vehicle studies

NASA Technical Reports Server (NTRS)

Bainum, Peter M.; Reiss, Robert

1995-01-01

Analytical support studies of expendable launch vehicles concentrate on the stability of the dynamics during launch especially during or near the region of maximum dynamic pressure. The in-plane dynamic equations of a generic launch vehicle with multiple flexible bending and fuel sloshing modes are developed and linearized. The information from LeRC about the grids, masses, and modes is incorporated into the model. The eigenvalues of the plant are analyzed for several modeling factors: utilizing diagonal mass matrix, uniform beam assumption, inclusion of aerodynamics, and the interaction between the aerodynamics and the flexible bending motion. Preliminary PID, LQR, and LQG control designs with sensor and actuator dynamics for this system and simulations are also conducted. The initial analysis for comparison of PD (proportional-derivative) and full state feedback LQR Linear quadratic regulator) shows that the split weighted LQR controller has better performance than that of the PD. In order to meet both the performance and robustness requirements, the H(sub infinity) robust controller for the expendable launch vehicle is developed. The simulation indicates that both the performance and robustness of the H(sub infinity) controller are better than that for the PID and LQG controllers. The modelling and analysis support studies team has continued development of methodology, using eigensensitivity analysis, to solve three classes of discrete eigenvalue equations. In the first class, the matrix elements are non-linear functions of the eigenvector. All non-linear periodic motion can be cast in this form. Here the eigenvector is comprised of the coefficients of complete basis functions spanning the response space and the eigenvalue is the frequency. The second class of eigenvalue problems studied is the quadratic eigenvalue problem. Solutions for linear viscously damped structures or viscoelastic structures can be reduced to this form. Particular attention is paid to

NASA team hosts STEM-Ulate actvities

NASA Image and Video Library

2010-07-13

Young visitors to NASA's John C. Stennis Space Center prepare to launch 'stomp rockets' during STEM-Ulate to Innovate activities at the facility July 13. The NASA Foundations of Influence, Relationships, Success and Teamwork (FIRST) Team sponsored STEM-Ulate to Innovate for more than 100 children ages 9-11. Children from area Boys & Girls Clubs participated in hands-on activities, presentations and demonstrations by professional engineers, all designed to promote the relevance of science, technology, engineering and mathematics (STEM).

78 FR 52560 - Hurricane Sandy Rebuilding Task Force-Rebuild-by-Design; Announcement of Selection of Design Teams

Federal Register 2010, 2011, 2012, 2013, 2014

2013-08-23

... launch Rebuild by Design and select the 10 teams. NEA has a history of supporting and facilitating design... design teams selected are the following: Interboro Partners with the New Jersey Institute of Technology.... Massachusetts Institute of Technology Center for Advanced Urbanism and the Dutch Delta Collaborative by ZUS...

The James Webb Space Telescope: Observatory Status and the Path to Launch

NASA Technical Reports Server (NTRS)

McElwain, Michael; Bowers, Chuck; Clampin, Mark; Niedner, Mal

2016-01-01

JWST will carry out transformative science from the very early universe and across cosmic time. JWST OTE and ISIM have been combined to form OTIS, which will commence environmental testing. The full JWST team has made tremendous progress since the last AT+I meeting in 2014.JWST on track following 2011 replan and remains on schedule to launch in October 2018.

Canadian Space Launch: Exploiting Northern Latitudes For Efficient Space Launch

DTIC Science & Technology

2015-04-01

9  Peoples’ Republic of China .........................................................................................11  USA Launch... taxation and legislation that make Canada an attractive destination for commercial space companies.3 General Definitions Highly Inclined Orbit...launches from sites north of the 35th parallel.33 USA Launch Facilities There are 3 US based launch facilities that conduct launch operations north

65. DETAIL OF ASSISTANT LAUNCH CONTROLLER AND LAUNCH CONTROLLER PANELS ...

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

65. DETAIL OF ASSISTANT LAUNCH CONTROLLER AND LAUNCH CONTROLLER PANELS LOCATED NEAR CENTER OF SLC-3E CONTROL ROOM. NOTE 30-CHANNEL COMMUNICATIONS PANELS. PAYLOAD ENVIRONMENTAL CONTROL AND MONITORING PANELS (LEFT) AND LAUNCH OPERATORS PANEL (RIGHT) IN BACKGROUND. - Vandenberg Air Force Base, Space Launch Complex 3, Launch Operations Building, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

High-Altitude Balloon Launches for Effective Education, Inspiration and Research

NASA Astrophysics Data System (ADS)

Voss, H. D.; Dailey, J.; Patterson, D.; Krueger, J.

2006-12-01

Over a three-year period the Taylor University Science Research Training Program (SRTP) has successfully launched and recovered 33 sophisticated payloads to altitudes between 20-33 km (100% success with rapid recovery). All of the payloads included two GPS tracking systems, cameras and monitors, a 110 kbit down link, and uplink command capability for educational experiments (K-12 and undergrad) and nanosatellite subsystem testing. Launches were conducted both day and night, with multiple balloons, with up to 10 experiment boxes, and under varying weather and upper atmospheric conditions. The many launches in a short period of time allowed the payload bus design to evolve toward increased performance, reliability, standardization, simplicity, and modularity for low-cost launch services. The current design uses a Zigbee wireless connection (50 kbaud rate) for each of the payload experiment boxes for rapid assembly and checkout with a common interface board for gathering analog and digital data and for commanding. Common data from each box is processed and displayed using modular LabView software. The use of balloons for active research (ozone, aerosols, cosmic rays. UV, IR, remote sensing, energy, propulsion) significantly invigorates and motivates student development, drives team schedule, uncovers unexpected problems, permits end-to-end closure, and forces calibration and validation of real data. The SRTP has helped to spin off a student company called StratoStar Systems for providing an affordable low-cost balloon launch service capability, insurance plan, and other technical assistance for scientific, industrial and STEM educational use.

Suomi Npp and Jpss Pre-Launch Test Data Collection and Archive

NASA Astrophysics Data System (ADS)

Denning, M.; Ullman, R.; Guenther, B.; Kilcoyne, H.; Chandler, C.; Adameck, J.

2012-12-01

During the development of each Suomi National Polar-orbiting Partnership (Suomi NPP) instrument, significant testing was performed, both in ambient and simulated orbital (thermal-vacuum) conditions, at the instrument factory, and again after integration with the spacecraft. The NPOESS Integrated Program Office (IPO), and later the NASA Joint Polar Satellite System (JPSS) Program Office, defined two primary objectives with respect to capturing instrument and spacecraft test data during these test events. The first objective was to disseminate test data and auxiliary documentation to an often distributed network of scientists to permit timely production of independent assessments of instrument performance, calibration, data quality, and test progress. The second goal was to preserve the data and documentation in a catalogued government archive for the life of the mission, to aid in the resolution of anomalies and to facilitate the comparison of on-orbit instrument operating characteristics to those observed prior to launch. In order to meet these objectives, Suomi NPP pre-launch test data collection, distribution, processing, and archive methods included adaptable support infrastructures to quickly and completely transfer test data and documentation from the instrument and spacecraft factories to sensor scientist teams on-site at the factory and around the country. These methods were unique, effective, and low in cost. These efforts supporting pre-launch instrument calibration permitted timely data quality assessments and technical feedback from contributing organizations within the government, academia, and industry, and were critical in supporting timely sensor development. Second, in parallel to data distribution to the sensor science teams, pre-launch test data were transferred and ingested into the central Suomi NPP calibration and validation (cal/val) system, known as the Government Resource for Algorithm Verification, Independent Testing, and Evaluation

Launch Vehicles

NASA Image and Video Library

2007-09-09

Under the goals of the Vision for Space Exploration, Ares I is a chief component of the cost-effective space transportation infrastructure being developed by NASA's Constellation Program. This transportation system will safely and reliably carry human explorers back to the moon, and then onward to Mars and other destinations in the solar system. Launch Pad 39B of the Kennedy Space Flight Center (KSC), currently used for Space Shuttle launches, will be revised to host the Ares launch vehicles. The fixed and rotating service structures standing at the pad will be dismantled sometime after the Ares I-X test flight. A new launch tower for Ares I will be built onto a new mobile launch platform. The gantry for the shuttle doesn't reach much higher than the top of the four segments of the solid rocket booster. Pad access above the current shuttle launch pad structure will not be required for Ares I-X because the stages above the solid rocket booster are inert. For the test scheduled in 2012 or for the crewed flights, workers and astronauts will need access to the highest levels of the rocket and capsule. When the Ares I rocket rolls out to the launch pad on the back of the same crawler-transporters used now, its launch gantry will be with it. The mobile launchers will nestle under three lightning protection towers to be erected around the pad area. Ares time at the launch pad will be significantly less than the three weeks or more the shuttle requires. This “clean pad” approach minimizes equipment and servicing at the launch pad. It is the same plan NASA used with the Saturn V rockets and industry employs it with more modern launchers. The launch pad will also get a new emergency escape system for astronauts, one that looks very much like a roller coaster. Cars riding on a rail will replace the familiar baskets hanging from steel cables. This artist's concept illustrates the Ares I on launch pad 39B.

NASA's Space Launch System: An Evolving Capability for Exploration

NASA Technical Reports Server (NTRS)

Robinson, Kimberly F.; Hefner, Keith; Hitt, David

2015-01-01

Designed to enable human space exploration missions, including eventually landings on Mars, NASA's Space Launch System (SLS) represents a unique launch capability with a wide range of utilization opportunities, from delivering habitation systems into the "proving ground" of lunar-vicinity space to enabling high-energy transits through the outer solar system. Substantial progress has been made toward the first launch of the initial configuration of SLS, which will be able to deliver more than 70 metric tons of payload into low Earth orbit (LEO). Preparations are also underway to evolve the vehicle into more powerful configurations, culminating with the capability to deliver more than 130 metric tons to LEO. Even the initial configuration of SLS will be able to deliver greater mass to orbit than any contemporary launch vehicle, and the evolved configuration will have greater performance than the Saturn V rocket that enabled human landings on the moon. SLS will also be able to carry larger payload fairings than any contemporary launch vehicle, and will offer opportunities for co-manifested and secondary payloads. Because of its substantial mass-lift capability, SLS will also offer unrivaled departure energy, enabling mission profiles currently not possible. The basic capabilities of SLS have been driven by studies on the requirements of human deep-space exploration missions, and continue to be validated by maturing analysis of Mars mission options, including the Global Exploration Roadmap. Early collaboration with science teams planning future decadal-class missions have contributed to a greater understanding of the vehicle's potential range of utilization. As SLS draws closer to its first launch, the Program is maturing concepts for future capability upgrades, which could begin being available within a decade. These upgrades, from multiple unique payload accommodations to an upper stage providing more power for inspace propulsion, have ramifications for a variety of

STS-90 Mission Specialist Kathryn (Kay) Hire is suited up for launch

NASA Technical Reports Server (NTRS)

1998-01-01

STS-90 Mission Specialist Kathryn (Kay) Hire prepares for launch during suitup activities in the Operations and Checkout Building as Astronaut Support Personnel team member Heidi Piper braids Hire's hair. Hire and the rest of the STS-90 crew will shortly depart for Launch Pad 39B, where the Space Shuttle Columbia awaits a second liftoff attempt at 2:19 p.m. EDT. Her first trip into space, Hire is participating in this life sciences research flight that will focus on the most complex and least understood part of the human body -- the nervous system. Neurolab will examine the effects of spaceflight on the brain, spinal cord, peripheral nerves and sensory organs in the human body.

The Challenges of Integrating NASA's Human, Budget, and Data Capital within the Constellation Program's Exploration Launch Projects Office

NASA Technical Reports Server (NTRS)

Kidd, Luanne; Morris, Kenneth B.; Self, Tim

2006-01-01

The U.S. Vision for Space Exploration directs NASA to retire the Space Shuttle in 2010 and replace it with safe, reliable, and cost-effective space transportation systems for crew and cargo travel to the Moon, Mars, and beyond. Such emerging space transportation initiatives face massive organizational challenges, including building and nurturing an experienced, dedicated team with the right skills for the required tasks; allocating and tracking the fiscal capital invested in achieving technical progress against an integrated master schedule; and turning generated data into usehl knowledge that equips the team to design and develop superior products for customers and stakeholders. This paper discusses how NASA's Exploration Launch Projects Office, which is responsible for delivering these new launch vehicles, integrates these resources to create an engineering business environment that promotes mission success.

Occupational and environmental exposure of automobile mechanics and nonautomotive workers to airborne manganese arising from the combustion of methylcyclopentadienyl manganese tricarbonyl (MMT).

PubMed

Sierra, P; Loranger, S; Kennedy, G; Zayed, J

1995-07-01

Inhalation exposure to manganese (Mn) was measured for a group of garage mechanics and a control group of nonautomotive workers. The airborne Mn exposure of 35 garage mechanics suspected of being relatively highly exposed to Mn from MMT was measured at the workplace over one-week period. It also was measured for 30 nonautomotive workers at the University of Montreal. The environmental exposure also was measured for the two groups, as was the exposure to three other metals, aluminum (Al), iron (Fe), and zinc (Zn). At work the mechanics were exposed to Mn concentrations varying from 0.010 to 6.673 micrograms m-3 with a mean of 0.45 microgram m-5, while the control group was exposed to concentrations varying from 0.011 to 1.862 microgram m-3 with a mean of 0.04 microgram m-3. The mean environmental exposure for the two groups was similar to the Mn concentrations gathered in Montreal in 1992. Workplace concentrations of Al, Fe, and Zn also were higher for the garage mechanics. The results suggest that less than 10% of the Mn exposure of the garage mechanics was due to MMT. The levels of the metals measured were below the established limits for industrial and even environmental exposure.

NASA's Space Launch System Development Status

NASA Technical Reports Server (NTRS)

Lyles, Garry

2014-01-01

Development of the National Aeronautics and Space Administration's (NASA's) Space Launch System (SLS) heavy lift rocket is shifting from the formulation phase into the implementation phase in 2014, a little more than 3 years after formal program establishment. Current development is focused on delivering a vehicle capable of launching 70 metric tons (t) into low Earth orbit. This "Block 1" configuration will launch the Orion Multi-Purpose Crew Vehicle (MPCV) on its first autonomous flight beyond the Moon and back in December 2017, followed by its first crewed flight in 2021. SLS can evolve to a130t lift capability and serve as a baseline for numerous robotic and human missions ranging from a Mars sample return to delivering the first astronauts to explore another planet. Benefits associated with its unprecedented mass and volume include reduced trip times and simplified payload design. Every SLS element achieved significant, tangible progress over the past year. Among the Program's many accomplishments are: manufacture of core stage test barrels and domes; testing of Solid Rocket Booster development hardware including thrust vector controls and avionics; planning for RS- 25 core stage engine testing; and more than 4,000 wind tunnel runs to refine vehicle configuration, trajectory, and guidance. The Program shipped its first flight hardware - the Multi-Purpose Crew Vehicle Stage Adapter (MSA) - to the United Launch Alliance for integration with the Delta IV heavy rocket that will launch an Orion test article in 2014 from NASA's Kennedy Space Center. The Program successfully completed Preliminary Design Review in 2013 and will complete Key Decision Point C in 2014. NASA has authorized the Program to move forward to Critical Design Review, scheduled for 2015 and a December 2017 first launch. The Program's success to date is due to prudent use of proven technology, infrastructure, and workforce from the Saturn and Space Shuttle programs, a streamlined management

NASA's Space Launch System: Building a New Capability for Discovery

NASA Technical Reports Server (NTRS)

Creech, Stephen D.; Robinson, Kimberly F.

2015-01-01

Designed to enable human space exploration missions, including eventually landings on Mars, NASA's Space Launch System (SLS) represents a unique launch capability with a wide range of utilization opportunities, from delivering habitation systems into the lunar vicinity to high-energy transits through the outer solar system. Substantial progress has been made toward the first launch of the initial configuration of SLS, which will be able to deliver more than 70 metric tons of payload into low Earth orbit (LEO). The vehicle will then be evolved into more powerful configurations, culminating with the capability to deliver more than 130 metric tons to LEO. The initial configuration will be able to deliver greater mass to orbit than any contemporary launch vehicle, and the evolved configuration will have greater performance than the Saturn V rocket that enabled human landings on the moon. SLS will also be able to carry larger payload fairings than any contemporary launch vehicle, and will offer opportunities for co-manifested and secondary payloads. Because of its substantial mass-lift capability, SLS will also offer unrivaled departure energy, enabling mission profiles currently not possible. The basic capabilities of SLS have been driven by studies on the requirements of human deep-space exploration missions, and continue to be validated by maturing analysis of Mars mission options. Early collaboration with science teams planning future decadal-class missions have contributed to a greater understanding of the vehicle's potential range of utilization. As this paper will explain, SLS is making measurable progress toward becoming a global infrastructure asset for robotic and human scouts of all nations by providing the robust space launch capability to deliver sustainable solutions for exploration.

First night launch of a Saturn I launch vehicle

NASA Image and Video Library

1965-05-25

First night time launching of a Saturn I launch vehicle took place at 2:35 a.m., May 25, 1965, with the launch of the second Pegasus meteoroid detection satellite from Complex 37, Cape Kennedy, Florida.

Launch Services, a Proven Model

NASA Astrophysics Data System (ADS)

Trafton, W. C.; Simpson, J.

2002-01-01

From a commercial perspective, the ability to justify "leap frog" technology such as reusable systems has been difficult to justify because the estimated 5B to 10B investment is not supported in the current flat commercial market coupled with an oversupply of launch service suppliers. The market simply does not justify investment of that magnitude. Currently, next generation Expendable Launch Systems, including Boeing's Delta IV, Lockheed Martin's Atlas 5, Ariane V ESCA and RSC's H-IIA are being introduced into operations signifying that only upgrades to proven systems are planned to meet the changes in anticipated satellite demand (larger satellites, more lifetime, larger volumes, etc.) in the foreseeable future. We do not see a new fleet of ELVs emerging beyond that which is currently being introduced, only continuous upgrades of the fleet to meet the demands. To induce a radical change in the provision of launch services, a Multinational Government investment must be made and justified by World requirements. The commercial market alone cannot justify such an investment. And if an investment is made, we cannot afford to repeat previous mistakes by relying on one system such as shuttle for commercial deployment without having any back-up capability. Other issues that need to be considered are national science and security requirements, which to a large extent fuels the Japanese, Chinese, Indian, Former Soviet Union, European and United States space transportation entries. Additionally, this system must support or replace current Space Transportation Economies with across-the-board benefits. For the next 10 to 20 years, Multinational cooperation will be in the form of piecing together launch components and infrastructure to supplement existing launch systems and reducing the amount of non-recurring investment while meeting the future requirements of the End-User. Virtually all of the current systems have some form of multinational participation: Sea Launch

AXONOMETRIC, LAUNCH DOOR AND DOOR CYLINDER, LAUNCH PLATFORM ROLLER GUIDE, ...

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

AXONOMETRIC, LAUNCH DOOR AND DOOR CYLINDER, LAUNCH PLATFORM ROLLER GUIDE, CRIB SUSPENSION SHOCK STRUT, LAUNCH PLATFORM - Dyess Air Force Base, Atlas F Missle Site S-8, Launch Facility, Approximately 3 miles east of Winters, 500 feet southwest of Highway 1770, center of complex, Winters, Runnels County, TX

Ensuring Safe Exploration: Ares Launch Vehicle Integrated Vehicle Ground Vibration Testing

NASA Technical Reports Server (NTRS)

Tuma, M. L.; Chenevert, D. J.

2010-01-01

upgraded. Two new cranes will help move test articles at the test stand and at the Redstone Arsenal railhead where first stage segments will be received in 2011. The Hydrodynamic Support systems (HDSs) used for Saturn and Shuttle have been disassembled and evaluated for use during IVGVT. Analyses indicate that the 45-year-old HDSs can be refurbished to support the Ares I IVGVT. An alternate concept for a pneumatic suspension system is also being explored. A decision on which suspension system configuration to use for IVGVT will be made in 2010. In the next three years, the team will complete the updates to TS 4550, upgrade the test and data collection equipment, and finalize the configurations of the test articles to be used in the IVGVT. With NASA's GVT capabilities reestablished, the FITO team will be well positioned to perform similar work on Ares V, the largest exploration launch vehicle NASA has ever built. The GVT effort continues NASA's 50-year commitment to using testing and data analysis for safer, more reliable launch vehicles.

Marshall Team Fires Recreated Goddard Rocket

NASA Technical Reports Server (NTRS)

2003-01-01

In honor of the Centernial of Flight Celebration and commissioned by the American Institute of Aeronautics and Astronautics (AIAA), a team of engineers from Marshall Space Flight Center (MSFC) built a replica of the first liquid-fueled rocket. The original rocket, designed and built by rocket engineering pioneer Robert H. Goddard in 1926, opened the door to modern rocketry. Goddard's rocket reached an altitude of 41 feet while its flight lasted only 2.5 seconds. The Marshall design team's plan was to stay as close as possible to an authentic reconstruction of Goddard's rocket. The same propellants were used - liquid oxygen and gasoline - as available during Goddard's initial testing and firing. The team also tried to construct the replica using the original materials and design to the greatest extent possible. By purposely using less advanced techniques and materials than many that are available today, the team encountered numerous technical challenges in testing the functional hardware. There were no original blueprints or drawings, only photographs and notes. However, this faithful adherence to historical accuracy has allowed the team to experience many of the same challenges Goddard faced 77 years ago, and more fully appreciate the genius of this extraordinary man. In this photo, the replica is shown firing in the A-frame launch stand in near-flight configuration at MSFC's Test Area 116 during the American Institute of Aeronautics and Astronautics 39th Joint Propulsion Conference on July 23, 2003.

Landsat science team meeting: Summer 2015

USGS Publications Warehouse

Schroeder, Todd; Loveland, Thomas; Wulder, Michael A.; Irons, James R.

2015-01-01

With over 60 participants in attendance, this was the largest LST meeting ever held. Meeting topics on the first day included Sustainable Land Imaging and Landsat 9 development, Landsat 7 and 8 operations and data archiving, the Landsat 8 Thermal Infrared Sensor (TIRS) stray-light issue, and the successful Sentinel-2 launch. In addition, on days two and three the LST members presented updates on their Landsat science and applications research. All presentations are available at landsat.usgs.gov/science_LST_Team_ Meetings.php.

The Next Giant Leap: NASA's Ares Launch Vehicles Overview

NASA Technical Reports Server (NTRS)

Cook, Stephen A.; Vanhooser, Teresa

2008-01-01

The next chapter in NASA's history also promises to write the next chapter in America's history, as the Agency makes measurable strides toward developing new space transportation capabilities that wi!! put astronauts on course to explore the Moon as the next giant leap toward the first human footprint on Mars. This paper will present top-level plans and progress being made toward fielding the Ares I crew launch vehicle in the 2013 timeframe and the Ares V cargo launch vehicle in the 2018 timeframe. It also gives insight into the objectives for the first test flight, known as the Ares I-X, which is scheduled for April 2009. The U.S. strategy to scientifically explore space will fuel innovations such as solar power and water recycling, as well as yield new knowledge that directly benefits life on Earth. For the Ares launch vehicles, NASA is building on heritage hardware and unique capabilities; as well as almost 50 years of lessons learned from the Apollo Saturn, Space Shuttle, and commercial launch vehicle programs. In the Ares I Project's inaugural year, extensive trade studies and evaluations were conducted to improve upon the designs initially recommended by the Exploration Systems Architecture Study, resulting in significant reduction of near-term and long-range technical and programmatic risks; conceptual designs were analyzed for fitness against requirements; and the contractual framework was assembled to enable a development effort unparalleled in American space flight since the Space Shuttle. The Exploration Launch Projects team completed the Ares I System Requirements Review (SRR) at the end of 2006--the first such engineering milestone for a human-rated space transportation system in over 30 years.

AMBIENT AIR CONCENTRATIONS OF FINE (PM2.5) MANGANESE IN U.S. NATIONAL PARKS AND IN CALIFORNIA AND CANADIAN CITIES: THE POSSIBLE IMPACT OF ADDING MMT TO UNLEADED GASOLINE

EPA Science Inventory

The October 1995 court decision allowing Ethyl Corporation to offer methylcylopentadienyl manganese tricarbonyl (MMT) for sale to refiners for introduction into unleaded gasoline as an octane enhancer is likely to result in increased fine (PM2.5) manganese (Mn) concentrations in ...

Google Mercury: The Launch of a New Planet

NASA Astrophysics Data System (ADS)

Hirshon, B.; Chapman, C. R.; Edmonds, J.; Goldstein, J.; Hallau, K. G.; Solomon, S. C.; Vanhala, H.; Weir, H. M.; Messenger Education; Public Outreach Epo Team

2010-12-01

The NASA MESSENGER mission’s Education and Public Outreach (EPO) Team, in cooperation with Google, Inc., has launched Google Mercury, an immersive new environment on the Google Earth platform. Google Mercury features hundreds of surface features, most of them newly revealed by the three flybys of the innermost planet by the MESSENGER spacecraft. As with Google Earth, Google Mercury is available on line at no cost. This presentation will demonstrate how our team worked with Google staff, features we incorporated, how games can be developed within the Google Earth platform, and how others can add tours, games, and other educational features. Finally, we will detail new enhancements to be added once MESSENGER enters into orbit about Mercury in March 2011 and begins sending back compelling images and other global data sets on a daily basis. The MESSENGER EPO Team comprises individuals from the American Association for the Advancement of Science (AAAS); Carnegie Academy for Science Education (CASE); Center for Educational Resources (CERES) at Montana State University (MSU) - Bozeman; National Center for Earth and Space Science Education (NCESSE); Johns Hopkins University Applied Physics Laboratory (JHU/APL); National Air and Space Museum (NASM); Science Systems and Applications, Inc. (SSAI); and Southwest Research Institute (SwRI). Screen shot of Google Mercury as a work in progress

Launch Preparation and Rocket Launching

DTIC Science & Technology

1991-05-23

which do not exceed several hundred kilometers. In the USA MBR and heavy rocket carriers to distant distances are transported predominantly on air or...Balloon for transportation of MBR "Minuteman" (drawing): - balloon; 2 - rocket. DOC = 91032701 PAGE 34 Page 20. Thus, for the protection from the axial g...launching is suitable for rockets, launched from surface of the earth (water), or from silo (submarine in submerged state). The selection of

STS-82 Discovery Launch

NASA Technical Reports Server (NTRS)

1997-01-01

The Space Shuttle Discovery cuts a bright swath through the early-morning darkness as it lifts off from Launch Pad 39A on a scheduled 10-day flight to service the Hubble Space Telescope (HST). Liftoff of Mission STS-82 occurred on-time at 3:55:17 a.m. EST, Feb. 11, 1997. Leading the veteran crew is Mission Commander Kenneth D. Bowersox. Scott J. 'Doc' Horowitz is the pilot. Mark C. Lee is the payload commander. Rounding out the seven-member crew are Mission Specialists Steven L. Smith, Gregory J. Harbaugh, Joseph R. 'Joe' Tanner and Steven A. Hawley. Four of the astronauts will be divided into two teams to perform the scheduled four back-to-back extravehicular activities (EVAs) or spacewalks. Lee and Smith will team up for EVAs 1 and 3 on flight days 4 and 6; Harbaugh and Tanner will perform EVAs 2 and 4 on flight days 5 and 7. Among the tasks will be to replace two outdated scientific instruments with two new instruments the Space Telescope Imaging Spectrograph (STIS) and the Near Infrared Camera and Multi-Object Spectrometer (NICMOS). This is the second servicing mission for HST, which was originally deployed in 1990 and designed to be serviced on-orbit about every three years. Hubble was first serviced in 1993. STS-82 is the second of eight planned flights in 1997. It is the 22nd flight of Discovery and the 82nd Shuttle mission.

The Launch of an Atlas/Centaur Launch Vehicle

NASA Technical Reports Server (NTRS)

1978-01-01

The launch of an Atlas/Centaur launch vehicle is shown in this photograph. The Atlas/Centaur, launched on November 13, 1978, carried the High Energy Astronomy Observatory (HEAO)-2 into the required orbit. The second observatory, the HEAO-2 (nicknamed the Einstein Observatory in honor of the centernial of the birth of Albert Einstein) carried the first telescope capable of producing actual photographs of x-ray objects.

COSMOS Launch Services

NASA Astrophysics Data System (ADS)

Kalnins, Indulis

2002-01-01

COSMOS-3M is a two stage launcher with liquid propellant rocket engines. Since 1960's COSMOS has launched satellites of up to 1.500kg in both circular low Earth and elliptical orbits with high inclination. The direct SSO ascent is available from Plesetsk launch site. The very high number of 759 launches and the achieved success rate of 97,4% makes this space transportation system one of the most reliable and successful launchers in the world. The German small satellite company OHB System co-operates since 1994 with the COSMOS manufacturer POLYOT, Omsk, in Russia. They have created the joint venture COSMOS International and successfully launched five German and Italian satellites in 1999 and 2000. The next commercial launches are contracted for 2002 and 2003. In 2005 -2007 COSMOS will be also used for the new German reconnaissance satellite launches. This paper provides an overview of COSMOS-3M launcher: its heritage and performance, examples of scientific and commercial primary and piggyback payload launches, the launch service organization and international cooperation. The COSMOS launch service business strategy main points are depicted. The current and future position of COSMOS in the worldwide market of launch services is outlined.

Advances in thermal control and performance of the MMT M1 mirror

NASA Astrophysics Data System (ADS)

Gibson, J. D.; Williams, G. G.; Callahan, S.; Comisso, B.; Ortiz, R.; Williams, J. T.

2010-07-01

Strategies for thermal control of the 6.5-meter diameter borosilicate honeycomb primary (M1) mirror at the MMT Observatory have included: 1) direct control of ventilation system chiller setpoints by the telescope operator, 2) semiautomated control of chiller setpoints, using a fixed offset from the ambient temperature, and 3) most recently, an automated temperature controller for conditioned air. Details of this automated controller, including the integration of multiple chillers, heat exchangers, and temperature/dew point sensors, are presented here. Constraints and sanity checks for thermal control are also discussed, including: 1) mirror and hardware safety, 2) aluminum coating preservation, and 3) optimization of M1 thermal conditions for science acquisition by minimizing both air-to-glass temperature differences, which cause mirror seeing, and internal glass temperature gradients, which cause wavefront errors. Consideration is given to special operating conditions, such as high dew and frost points. Precise temperature control of conditioned ventilation air as delivered to the M1 mirror cell is also discussed. The performance of the new automated controller is assessed and compared to previous control strategies. Finally, suggestions are made for further refinement of the M1 mirror thermal control system and related algorithms.

U.S. & international small launch vehicles : Quarterly Launch Report : special report

DOT National Transportation Integrated Search

1998-01-01

Since the 1980s, there have been expectations that a substantial commercial market for launch services using small launch vehicles would develop. In fact, commercial launches of small launch vehicles have, in theory, been available since the mid-1980...

Technology Transfer External Metrics, Research, Success Stories, and Participation on Evaluation Team for the Reusable Launch Vehicle (RLV)

NASA Technical Reports Server (NTRS)

Trivoli, George W.

1996-01-01

This research report is divided into four sections. The first section is related to participation on the team that evaluated the proposals for the X-33 project and the Reusable Launch Vehicle (RLV) during mid-May; prior to beginning the 1996 Summer Faculty Fellowship. The second section discusses the various meetings attended related to the technology evaluation process. The third section is related to various research and evaluation activities engaged in by this researcher. The final section discusses several success stories this researcher aided in preparing. Despite the fact that this researcher is not an engineer or science faculty, invaluable knowledge and experience have been gained at MSFC. Although related to the previous summer's research, the research has been new, varied, and challenging. This researcher was fortunate to have had maximum interaction with NASA colleague, David Cockrell. It would be a privilege and honor to continue a relationship with the Technology Transfer Office. In addition, we will attempt to aid in the establishment of a continuous formalized relationship between MSFC and Jacksonville State University. Dr. David Watts, Vice President for Academic Affairs, J.S.U., is interested in having the Technology Division cooperating with MSFC in sharing information and working tech transfer inquiries. The principal benefits gained by this researcher include the opportunity to conduct research in a non-academic, real world environment. In addition, the opportunity to be involved in aiding with the decision process for the choice of the next generation of space transportation system was a once in a lifetime experience. This researcher has gained enhanced respect and understanding of MSFC/NASA staff and facilities.

Decentralized Formation Flying Control in a Multiple-Team Hierarchy

NASA Technical Reports Server (NTRS)

Mueller, Joseph .; Thomas, Stephanie J.

2005-01-01

This paper presents the prototype of a system that addresses these objectives-a decentralized guidance and control system that is distributed across spacecraft using a multiple-team framework. The objective is to divide large clusters into teams of manageable size, so that the communication and computational demands driven by N decentralized units are related to the number of satellites in a team rather than the entire cluster. The system is designed to provide a high-level of autonomy, to support clusters with large numbers of satellites, to enable the number of spacecraft in the cluster to change post-launch, and to provide for on-orbit software modification. The distributed guidance and control system will be implemented in an object-oriented style using MANTA (Messaging Architecture for Networking and Threaded Applications). In this architecture, tasks may be remotely added, removed or replaced post-launch to increase mission flexibility and robustness. This built-in adaptability will allow software modifications to be made on-orbit in a robust manner. The prototype system, which is implemented in MATLAB, emulates the object-oriented and message-passing features of the MANTA software. In this paper, the multiple-team organization of the cluster is described, and the modular software architecture is presented. The relative dynamics in eccentric reference orbits is reviewed, and families of periodic, relative trajectories are identified, expressed as sets of static geometric parameters. The guidance law design is presented, and an example reconfiguration scenario is used to illustrate the distributed process of assigning geometric goals to the cluster. Next, a decentralized maneuver planning approach is presented that utilizes linear-programming methods to enact reconfiguration and coarse formation keeping maneuvers. Finally, a method for performing online collision avoidance is discussed, and an example is provided to gauge its performance.

4. GENERAL VIEW OF LAUNCH PAD B FROM LAUNCH PAD ...

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

4. GENERAL VIEW OF LAUNCH PAD B FROM LAUNCH PAD A MOBILE SERVICE STRUCTURE; VIEW TO SOUTH. - Cape Canaveral Air Station, Launch Complex 17, Facility 28402, East end of Lighthouse Road, Cape Canaveral, Brevard County, FL

73. VIEW OF LAUNCH OPERATOR AND LAUNCH ANAYLST PANELS LOCATED ...

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

73. VIEW OF LAUNCH OPERATOR AND LAUNCH ANAYLST PANELS LOCATED NEAR CENTER OF SOUTH WALL OF SLC-3E CONTROL ROOM. FROM LEFT TO RIGHT ON WALL IN BACKGROUND: COMMUNICATIONS HEADSET AND FOOT PEDAL IN FORGROUND. ACCIDENT REPORTING EMERGENCY NOTIFICATION SYSTEM TELEPHONE, ATLAS H FUEL COUNTER, AND DIGITAL COUNTDOWN CLOCK. - Vandenberg Air Force Base, Space Launch Complex 3, Launch Operations Building, Napa & Alden Roads, Lompoc, Santa Barbara County, CA

14 CFR 420.29 - Launch site location review for unproven launch vehicles.

Code of Federal Regulations, 2011 CFR

2011-01-01

... AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION LICENSING LICENSE TO OPERATE A LAUNCH SITE Criteria and Information Requirements for Obtaining a License § 420.29 Launch site location review for unproven launch vehicles. An applicant for a license to operate a launch site for an unproven launch vehicle shall...

14 CFR 420.29 - Launch site location review for unproven launch vehicles.

Code of Federal Regulations, 2010 CFR

2010-01-01

... AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION LICENSING LICENSE TO OPERATE A LAUNCH SITE Criteria and Information Requirements for Obtaining a License § 420.29 Launch site location review for unproven launch vehicles. An applicant for a license to operate a launch site for an unproven launch vehicle shall...

Conceptual Launch Vehicle and Spacecraft Design for Risk Assessment

NASA Technical Reports Server (NTRS)

Motiwala, Samira A.; Mathias, Donovan L.; Mattenberger, Christopher J.

2014-01-01

One of the most challenging aspects of developing human space launch and exploration systems is minimizing and mitigating the many potential risk factors to ensure the safest possible design while also meeting the required cost, weight, and performance criteria. In order to accomplish this, effective risk analyses and trade studies are needed to identify key risk drivers, dependencies, and sensitivities as the design evolves. The Engineering Risk Assessment (ERA) team at NASA Ames Research Center (ARC) develops advanced risk analysis approaches, models, and tools to provide such meaningful risk and reliability data throughout vehicle development. The goal of the project presented in this memorandum is to design a generic launch 7 vehicle and spacecraft architecture that can be used to develop and demonstrate these new risk analysis techniques without relying on other proprietary or sensitive vehicle designs. To accomplish this, initial spacecraft and launch vehicle (LV) designs were established using historical sizing relationships for a mission delivering four crewmembers and equipment to the International Space Station (ISS). Mass-estimating relationships (MERs) were used to size the crew capsule and launch vehicle, and a combination of optimization techniques and iterative design processes were employed to determine a possible two-stage-to-orbit (TSTO) launch trajectory into a 350-kilometer orbit. Primary subsystems were also designed for the crewed capsule architecture, based on a 24-hour on-orbit mission with a 7-day contingency. Safety analysis was also performed to identify major risks to crew survivability and assess the system's overall reliability. These procedures and analyses validate that the architecture's basic design and performance are reasonable to be used for risk trade studies. While the vehicle designs presented are not intended to represent a viable architecture, they will provide a valuable initial platform for developing and demonstrating

Licensing of commercial launch sites : Quarterly Launch Report : special report :

DOT National Transportation Integrated Search

2000-01-01

The Commercial Space Launch Act of 1984 as recodified at 49 U.S.C. Subtitle IX--Commercial Space Transportation, ch. 701, Commercial Space Launch Activities, 49 U.S.C. '' 70101- authorizes the Secretary of Transportation to license launches or the op...

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

U.S. small launch vehicles : Quarterly Launch Report : special report

DOT National Transportation Integrated Search

1996-01-01

1995 was an ambitious and difficult year for the United States small launch vehicle market. A total of five small launch vehicles were launched from the United States, two of which were successful (Atlas : E and Pegasus 1) and three of which resulted...

Launch of Agena Target Docking Vehicle atop Atlas launch vehicle

NASA Technical Reports Server (NTRS)

1966-01-01

An Agena Target Docking Vehicle atop its Atlas launch vehicle was launched fromt the Kennedy Space Center's Launch Complex 14 at 6:05 a.m., September 12, 1966. The Agena served as a rendezvous and docking vehicle for the Gemini 11 spacecraft.

Saving Lives through visual health communication: a multidisciplinary team approach.

PubMed

Wressell, Adrian; Twaites, Heidi; Taylor, Stephen; Hartland, Dan; Gove-Humphries, Theo

2014-10-01

Saving Lives is a public health awareness charity that aims to educate the UK public about HIV and encourage testing for the virus. In May 2011 Saving Lives contacted the Medical Illustration department at Heart of England NHS Foundation Trust to discuss the idea of working together to develop a national HIV awareness campaign. A number of local sporting celebrities were invited to a studio photography session. All the sports stars and celebrities were photographed on a Mamiya 645 AFDII camera, with PhaseOne P30 + digital back, using prime 35 mm, 55 mm and 80 mm lenses. During the photography sessions, the team's film maker captured video footage of the subjects being photographed. Once the final avengers' graphical composition had been created, it was applied to the posters, billboards and public transport signs for the campaign. In the three-month period following the campaign launch, survey research was carried out, the initial data being recorded by a questionnaire which was provided to each of the 1800 patients attending the Heartlands Hospital sexual health clinic for HIV testing. Following the launch of the initial campaign, the Saving Lives team continues to produce material to assist in the promotion of the charity and its message. Its success has led to it becoming an on-going long-term project, and to date the team have photographed and filmed 33 sporting stars and visited numerous sporting institutes.

STS-120 launch

NASA Image and Video Library

2007-10-23

STS120-S-026 (23 Oct. 2007) --- In the firing room of the Kennedy Space Center in Florida, NASA Shuttle Launch Director Michael Leinbach (second right) and launch managers watch the 11:38 a.m. (EDT) launch of Space Shuttle Discovery. Discovery launched Oct. 23 on a 14-day construction mission to the International Space Station. Photo credit: NASA/Bill Ingalls

An Overview of the Characterization of the Space Launch Vehicle Aerodynamic Environments

NASA Technical Reports Server (NTRS)

Blevins, John A.; Campbell, John R., Jr.; Bennett, David W.; Rausch, Russ D.; Gomez, Reynaldo J.; Kiris, Cetin C.

2014-01-01

Aerodynamic environments are some of the rst engineering data products that are needed to design a space launch vehicle. These products are used in performance predic- tions, vehicle control algorithm design, as well as determing loads on primary and secondary structures in multiple discipline areas. When the National Aeronautics and Space Admin- istration (NASA) Space Launch System (SLS) Program was established with the goal of designing a new, heavy-lift launch vehicle rst capable of lifting the Orion Program Multi- Purpose Crew Vehicle (MPCV) to low-earth orbit and preserving the potential to evolve the design to a 200 metric ton cargo launcher, the data needs were no di erent. Upon commencement of the new program, a characterization of aerodynamic environments were immediately initiated. In the time since, the SLS Aerodynamics Team has produced data describing the majority of the aerodynamic environment de nitions needed for structural design and vehicle control under nominal ight conditions. This paper provides an overview of select SLS aerodynamic environments completed to date.

Research activities on Antarctic middle atmosphere by JARE 25th team

NASA Technical Reports Server (NTRS)

Hirasawa, T.; Eiwasaka, Y. AFTANAKA, M. agfujii, r.0 typ; Eiwasaka, Y. AFTANAKA, M. agfujii, r.0 typ

1985-01-01

The Antarctic Middle Atmosphere (AMA)-Japan research project was set about by the JARE (Japan Antarctic Research Expedition) 23rd team in 1982, and since then the JARE-24th and JARE-25th teams have been continuing reseach on the Antarctic Middle Atmosphere. Results gained by JARE-25th team members who are now working at Syowa Station (69.99 deg S, 39.35 deg E), Antarctica are presented. In their activities satellite measurements (Exos-C) and rocket soundings are used. Three rockets of the S310 type were launched at Syowa Station (Geomagnetic Latitude = 69.9 deg S) for the purpose of directly observing the electron density, ionospheric temperature, auroral patterns and luminosity in situ. Vertical profiles of electron density and auroral emission 4278A measured by three rockets are compared.

Atlas V Launch Incorporated NASA Glenn Thermal Barrier

NASA Technical Reports Server (NTRS)

Dunlap, Patrick H., Jr.; Steinetz, Bruce M.

2004-01-01

In the Spring of 2002, Aerojet experienced a major failure during a qualification test of the solid rocket motor that they were developing for the Atlas V Enhanced Expendable Launch Vehicle. In that test, hot combustion gas reached the O-rings in the nozzle-to-case joint and caused a structural failure that resulted in loss of the nozzle and aft dome sections of the motor. To improve the design of this joint, Aerojet decided to incorporate three braided carbon-fiber thermal barriers developed at the NASA Glenn Research Center. The thermal barriers were used to block the searing-hot 5500 F pressurized gases from reaching the temperature-sensitive O-rings that seal the joint. Glenn originally developed the thermal barriers for the nozzle joints of the space shuttle solid rocket motors, and Aerojet decided to use them on the basis of the results of several successful ground tests of the thermal barriers in the shuttle rockets. Aerojet undertook an aggressive schedule to redesign the rocket nozzle-to-case joint with the thermal barriers and to qualify it in time for a launch planned for the middle of 2003. They performed two successful qualification tests (Oct. and Dec. 2002) in which the Glenn thermal barriers effectively protected the O-rings. These qualification tests saved hundreds of thousands of dollars in development costs and put the Lockheed-Martin/Aerojet team back on schedule. On July 17, 2003, the first flight of an Atlas V boosted with solid rocket motors successfully launched a commercial satellite into orbit from Cape Canaveral Air Force Station. Aero-jet's two 67-ft solid rocket boosters performed flawlessly, with each providing thrust in excess of 250,000 lbf. Both motors incorporated three Glenn-developed thermal barriers in their nozzle-to-case joints. The Cablevision satellite launched on this mission will be used to provide direct-to-home satellite television programming for the U.S. market starting in late 2003. The Atlas V is a product of the

Capabilities of the Materials Contamination Team at Marshall Space Flight Center

NASA Technical Reports Server (NTRS)

Burns, H. D.; Finckenor, M. M.; Boothe, R. E.; Albyn, K. C.; Finchum, C. A.

2003-01-01

The Materials Contamination Team of the Environmental Effects Group, Materials, Processes, and Manufacturing Department, has been recognized for its contribution to space flight, including space transportation, space science and flight projects, such as the reusable solid rocket motor, Chandra X-Ray Observatory, and the International Space Station. The Materials Contamination Team s realm of responsibility encompasses all phases of hardware development including design, manufacturing, assembly, test, transportation, launch-site processing, on-orbit exposure, return, and refurbishment if required. Contamination is a concern in the Space Shuttle with sensitivity bondlines and reactive fluid (liquid oxygen) compatibility as well as for sensitive optics, particularly spacecraft such as Hubble Space Telescope and Chandra X-Ray Observatory. The Materials Contamination Team has a variety of facilities and instrumentation capable of contaminant detection identification, and monitoring. The team addresses material applications dealing with environments, including production facilities, clean rooms, and on-orbit exposure. The team of engineers and technicians also develop and evaluates new surface cleanliness inspection technologies. Databases are maintained by the team for proces! materials as well as outgassing and optical compatibility test results for specific environments.

CSUNSat-1 Team working on their CubeSat at California State University Northridge

NASA Image and Video Library

2015-03-02

CSUNSat-1 Team (Adam Kaplan, James Flynn, Donald Eckels) working on their CubeSat at California State University Northridge. The primary mission of CSUNSat1 is to space test an innovative low temperature capable energy storage system developed by the Jet Propulsion Laboratory, raising its TRL level to 7 from 4 to 5. The success of this energy storage system will enable future missions, especially those in deep space to do more science while requiring less energy, mass and volume. This CubeSat was designed, built, programmed, and tested by a team of over 70 engineering and computer science students at CSUN.  The primary source of funding for CSUNSat1 comes from NASA’s Smallest Technology Partnership program. Launched by NASA’s CubeSat Launch Initiative NET April 18, 2017 ELaNa XVII mission on the seventh Orbital-ATK Cygnus Commercial Resupply Services (OA-7) to the International Space Station and deployed on tbd.

Astronauts greet the U.S. Women's World Cup Soccer Team at the Skid Strip

NASA Technical Reports Server (NTRS)

1999-01-01

Members of the U.S. Women's World Cup Soccer Team were greeted upon their arrival at the Skid Strip at Cape Canaveral Air Station by Astronauts (right) Steven W. Lindsey, Heidemarie M. Stefanyshyn-Piper and Scott E. Parzynski. The team are here to view the launch of Space Shuttle mission STS-93, scheduled for 12:36 a.m. EDT July 20. Much attention has been generated over the launch due to Commander Eileen M. Collins, the first woman to serve as commander of a Shuttle mission. The primary payload of the five-day mission is the Chandra X-ray Observatory, which will allow scientists from around the world to study some of the most distant, powerful and dynamic objects in the universe. The new telescope is 20 to 50 times more sensitive than any previous X- ray telescope and is expected to unlock the secrets of supernovae, quasars and black holes.

Support to X-33/Reusable Launch Vehicle Technology Program

NASA Technical Reports Server (NTRS)

2000-01-01

The Primary activities of Lee & Associates for the referenced Purchase Order has been in direct support of the X-33/Reusable Launch Vehicle Technology Program. An independent review to evaluate the X-33 liquid hydrogen fuel tank failure, which recently occurred after-test of the starboard tank has been provided. The purpose of the Investigation team was to assess the tank design modifications, provide an assessment of the testing approach used by MSFC (Marshall Space Flight Center) in determining the flight worthiness of the tank, assessing the structural integrity, and determining the cause of the failure of the tank. The approach taken to satisfy the objectives has been for Lee & Associates to provide the expertise of Mr. Frank Key and Mr. Wayne Burton who have relevant experience from past programs and a strong background of experience in the fields critical to the success of the program. Mr. Key and Mr. Burton participated in the NASA established Failure Investigation Review Team to review the development and process data and to identify any design, testing or manufacturing weaknesses and potential problem areas. This approach worked well in satisfying the objectives and providing the Review Team with valuable information including the development of a Fault Tree. The detailed inputs were made orally in real time in the Review Team daily meetings. The results of the investigation were presented to the MSFC Center Director by the team on February 15, 2000. Attached are four charts taken from that presentation which includes 1) An executive summary, 2) The most probable cause, 3) Technology assessment, and 4) Technology Recommendations for Cryogenic tanks.

Small Launch Vehicle Design Approaches: Clustered Cores Compared with Multi-Stage Inline Concepts

NASA Technical Reports Server (NTRS)

Waters, Eric D.; Beers, Benjamin; Esther, Elizabeth; Philips, Alan; Threet, Grady E., Jr.

2013-01-01

In an effort to better define small launch vehicle design options two approaches were investigated from the small launch vehicle trade space. The primary focus was to evaluate a clustered common core design against a purpose built inline vehicle. Both designs focused on liquid oxygen (LOX) and rocket propellant grade kerosene (RP-1) stages with the terminal stage later evaluated as a LOX/methane (CH4) stage. A series of performance optimization runs were done in order to minimize gross liftoff weight (GLOW) including alternative thrust levels, delivery altitude for payload, vehicle length to diameter ratio, alternative engine feed systems, re-evaluation of mass growth allowances, passive versus active guidance systems, and rail and tower launch methods. Additionally manufacturability, cost, and operations also play a large role in the benefits and detriments for each design. Presented here is the Advanced Concepts Office's Earth to Orbit Launch Team methodology and high level discussion of the performance trades and trends of both small launch vehicle solutions along with design philosophies that shaped both concepts. Without putting forth a decree stating one approach is better than the other; this discussion is meant to educate the community at large and let the reader determine which architecture is truly the most economical; since each path has such a unique set of limitations and potential payoffs.

NASA Space Environments Technical Discipline Team Space Weather Activities

NASA Astrophysics Data System (ADS)

Minow, J. I.; Nicholas, A. C.; Parker, L. N.; Xapsos, M.; Walker, P. W.; Stauffer, C.

2017-12-01

The Space Environment Technical Discipline Team (TDT) is a technical organization led by NASA's Technical Fellow for Space Environments that supports NASA's Office of the Chief Engineer through the NASA Engineering and Safety Center. The Space Environments TDT conducts independent technical assessments related to the space environment and space weather impacts on spacecraft for NASA programs and provides technical expertise to NASA management and programs where required. This presentation will highlight the status of applied space weather activities within the Space Environment TDT that support development of operational space weather applications and a better understanding of the impacts of space weather on space systems. We will first discuss a tool that has been developed for evaluating space weather launch constraints that are used to protect launch vehicles from hazardous space weather. We then describe an effort to better characterize three-dimensional radiation transport for CubeSat spacecraft and processing of micro-dosimeter data from the International Space Station which the team plans to make available to the space science community. Finally, we will conclude with a quick description of an effort to maintain access to the real-time solar wind data provided by the Advanced Composition Explorer satellite at the Sun-Earth L1 point.

Space Launch System Co-Manifested Payload Options for Habitation

NASA Technical Reports Server (NTRS)

Smitherman, David

2015-01-01

The Space Launch System (SLS) has a co-manifested payload capability that will grow over time as the launch vehicle matures and planned upgrades are implemented. The final configuration is planned to be capable of inserting a payload greater than 10 metric tons (mt) into a trans-lunar injection trajectory along with the crew in the Orion capsule and its service module. The co-manifested payload is located below the Orion and its service module in a 10 m high fairing similar to the way the Saturn launch vehicle carried the lunar lander below the Apollo command and service modules. Various approaches that utilize this comanifested payload capability to build up infrastructure in deep space have been explored in support of future asteroid, lunar, and Mars mission scenarios. This paper reports on the findings of the Advanced Concepts Office study team at NASA Marshall Space Flight Center (MSFC) working with the Advanced Exploration Systems Program on the Exploration Augmentation Module Project. It includes some of the possible options for habitation in the co-manifested payload volume of the SLS. Findings include a set of module designs that can be developed in 10 mt increments to support these co-manifested payload missions along with a comparison of this approach to a large-module payload flight configuration for the SLS.

Integrated Launch Operations Applications Remote Display Developer

NASA Technical Reports Server (NTRS)

Flemming, Cedric M., II

2014-01-01

This internship provides the opportunity to support the creation and use of Firing Room Displays and Firing Room Applications that use an abstraction layer called the Application Control Language (ACL). Required training included video watching, reading assignments, face-to-face instruction and job shadowing other Firing Room software developers as they completed their daily duties. During the training period various computer and access rights needed for creating the applications were obtained. The specific ground subsystems supported are the Cryogenics Subsystems, Liquid Hydrogen (LH2) and Liquid Oxygen (LO2). The cryogenics team is given the task of finding the best way to handle these very volatile liquids that are used to fuel the Space Launch System (SLS) and the Orion flight vehicles safely.

Submillimeter Wave Astronomy Satellite (SWAS) Launch and Early Orbit Support Experiences

NASA Technical Reports Server (NTRS)

Kirschner, S.; Sedlak, J.; Challa, M.; Nicholson, A.; Sande, C.; Rohrbaugh, D.

1999-01-01

The Submillimeter Wave Astronomy Satellite (SWAS) was successfully launched on December 6, 1998 at 00:58 UTC. The two year mission is the fourth in the series of Small Explorer (SMEX) missions. SWAS is dedicated to the study of star formation and interstellar chemistry. SWAS was injected into a 635 km by 650 km orbit with an inclination of nearly 70 deg by an Orbital Sciences Corporation Pegasus XL launch vehicle. The Flight Dynamics attitude and navigation teams supported all phases of the early mission. This support included orbit determination, attitude determination, real-time monitoring, and sensor calibration. This paper reports the main results and lessons learned concerning navigation, support software, star tracker performance, magnetometer and gyroscope calibrations, and anomaly resolution. This includes information on spacecraft tip-off rates, first-day navigation problems, target acquisition anomalies, star tracker anomalies, and significant sensor improvements due to calibration efforts.

Agena Target Vehicle atop Atlas Launch vehicle launched from KSC

NASA Technical Reports Server (NTRS)

1966-01-01

An Agena Target Vehicle atop its Atlas Launch vehicle is launched from the Kennedy Space Center (KSC) Launch Complex 14 at 10:15 am.m., May 17, 1966. The Agena was intended as a rendezvous and docking vehicle for the Gemini 9 spacecraft. However, since the Agena failed to achieve orbit, the Gemini 9 mission was postponed.

Team Learning in Teacher Teams: Team Entitativity as a Bridge between Teams-in-Theory and Teams-in-Practice

ERIC Educational Resources Information Center

Vangrieken, Katrien; Dochy, Filip; Raes, Elisabeth

2016-01-01

This study aimed to investigate team learning in the context of teacher teams in higher vocational education. As teacher teams often do not meet all criteria included in theoretical team definitions, the construct "team entitativity" was introduced. Defined as the degree to which a group of individuals possesses the quality of being a…

Launch Vehicles

NASA Image and Video Library

1990-06-01

The Delta II expendable launch vehicle with the ROSAT (Roentgen Satellite), cooperative space X-ray astronomy mission between NASA, Germany and United Kingdom, was launched from the Cape Canaveral Air Force Station on June 1, 1990.

Ensuring Safe Exploration: Ares Launch Vehicle Integrated Vehicle Ground Vibration Testing

NASA Technical Reports Server (NTRS)

Tuma, M. L.; Chenevert, D. J.

2009-01-01

team expects to collect important information about the new launch vehicles, greatly increasing astronaut safety as NASA prepares to explore the Moon and beyond.

Team Leader Structuring for Team Effectiveness and Team Learning in Command-and-Control Teams.

PubMed

van der Haar, Selma; Koeslag-Kreunen, Mieke; Euwe, Eline; Segers, Mien

2017-04-01

Due to their crucial and highly consequential task, it is of utmost importance to understand the levers leading to effectiveness of multidisciplinary emergency management command-and-control (EMCC) teams. We argue that the formal EMCC team leader needs to initiate structure in the team meetings to support organizing the work as well as facilitate team learning, especially the team learning process of constructive conflict. In a sample of 17 EMCC teams performing a realistic EMCC exercise, including one or two team meetings (28 in sum), we coded the team leader's verbal structuring behaviors (1,704 events), rated constructive conflict by external experts, and rated team effectiveness by field experts. Results show that leaders of effective teams use structuring behaviors more often (except asking procedural questions) but decreasingly over time. They support constructive conflict by clarifying and by making summaries that conclude in a command or decision in a decreasing frequency over time.

Team Leader Structuring for Team Effectiveness and Team Learning in Command-and-Control Teams

PubMed Central

van der Haar, Selma; Koeslag-Kreunen, Mieke; Euwe, Eline; Segers, Mien

2017-01-01

Due to their crucial and highly consequential task, it is of utmost importance to understand the levers leading to effectiveness of multidisciplinary emergency management command-and-control (EMCC) teams. We argue that the formal EMCC team leader needs to initiate structure in the team meetings to support organizing the work as well as facilitate team learning, especially the team learning process of constructive conflict. In a sample of 17 EMCC teams performing a realistic EMCC exercise, including one or two team meetings (28 in sum), we coded the team leader’s verbal structuring behaviors (1,704 events), rated constructive conflict by external experts, and rated team effectiveness by field experts. Results show that leaders of effective teams use structuring behaviors more often (except asking procedural questions) but decreasingly over time. They support constructive conflict by clarifying and by making summaries that conclude in a command or decision in a decreasing frequency over time. PMID:28490856

Status of NASA's Space Launch System

NASA Technical Reports Server (NTRS)

Honeycutt, John; Lyles, Garry

2016-01-01

NASA's Space Launch System (SLS) continued to make significant progress in 2015 and 2016, completing hardware and testing that brings NASA closer to a new era of deep space exploration. Programmatically, SLS completed Critical Design Review (CDR) in 2015. A team of independent reviewers concluded that the vehicle design is technically and programmatically ready to move to Design Certification Review (DCR) and launch readiness in 2018. Just five years after program start, every major element has amassed development and flight hardware and completed key tests that will lead to an accelerated pace of manufacturing and testing in 2016 and 2017. Key to SLS' rapid progress has been the use of existing technologies adapted to the new launch vehicle. The existing fleet of RS-25 engines is undergoing adaptation tests to prove it can meet SLS requirements and environments with minimal change. The four-segment shuttle-era booster has been modified and updated with a fifth propellant segment, new insulation, and new avionics. The Interim Cryogenic Upper Stage is a modified version of an existing upper stage. The first Block I SLS configuration will launch a minimum of 70 metric tons (t) of payload to low Earth orbit (LEO). The vehicle architecture has a clear evolutionary path to more than 100t and, ultimately, to 130t. Among the program's major 2015-2016 accomplishments were two booster qualification hotfire tests, a series of RS-25 adaptation hotfire tests, manufacturing of most of the major components for both core stage test articles and first flight tank, delivery of the Pegasus core stage barge, and the upper stage simulator. Renovations to the B-2 test stand for stage green run testing was completed at NASA Stennis Space Center. This year will see the completion of welding for all qualification and flight EM-1 core stage components and testing of flight avionics, completion of core stage structural test stands, casting of the EM-1 solid rocket motors, additional testing

Status of NASA's Space Launch System

NASA Technical Reports Server (NTRS)

Honeycutt, John; Cook, Jerry; Lyles, Garry

2016-01-01

NASA's Space Launch System (SLS) continued to make significant progress in 2015, completing hardware and testing that brings NASA closer to a new era of deep space exploration. The most significant program milestone of the year was completion of Critical Design Review (CDR). A team of independent reviewers concluded that the vehicle design is technically and programmatically ready to move to Design Certification Review (DCR) and launch readiness in 2018. Just four years after program start, every major element has amassed development and flight hardware and completed key tests that will set the stage for a growing schedule of manufacturing and testing in 2016. Key to SLS' rapid progress has been the use of existing technologies adapted to the new launch vehicle. The space shuttle-heritage RS-25 engine is undergoing adaptation tests to prove it can meet SLS requirements and environments with minimal change. The four-segment shuttle-era booster has been modified and updated with an additional propellant segment, new insulation, and new avionics. The Interim Cryogenic Upper Stage is a modified version of an existing upper stage. The first Block I SLS configuration will launch a minimum of 70 metric tons of payload to low Earth orbit (LEO). The vehicle architecture has a clear evolutionary path to more than 100 metric tons and, ultimately, to 130 metric tons. Among the program's major accomplishments in 2015 were the first booster qualification hotfire test, a series of seven RS-25 adaptation hotfire tests, manufacturing of most of the major components for both core stage test articles and first flight tank, delivery of the Pegasus core stage barge, and the upper stage simulator. Renovations to the B-2 test stand for stage green run testing was completed at NASA Stennis Space Center. This year will see the second booster qualification motor hotfire, flight and additional development RS-25 engine tests, and completion of core stage test articles and test stands and

Status of NASA's Space Launch System

NASA Technical Reports Server (NTRS)

Lyles, Garry

2016-01-01

NASA's Space Launch System (SLS) continued to make significant progress in 2015, completing hardware and testing that brings NASA closer to a new era of deep space exploration. The most significant program milestone of the year was completion of Critical Design Review (CDR). A team of independent reviewers concluded that the vehicle design is technically and programmatically ready to move to Design Certification Review (DCR) and launch readiness in 2018. Just four years after program start, every major element has amassed development and flight hardware and completed key tests that will set the stage for a growing schedule of manufacturing and testing in 2016. Key to SLS' rapid progress has been the use of existing technologies adapted to the new launch vehicle. The space shuttle-heritage RS-25 engine is undergoing adaptation tests to prove it can meet SLS requirements and environments with minimal change. The four-segment shuttle-era booster has been modified and updated with an additional propellant segment, new insulation, and new avionics. The Interim Cryogenic Upper Stage is a modified version of an existing upper stage. The first Block I SLS configuration will launch a minimum of 70 metric tons (t) of payload to low Earth orbit (LEO). The vehicle architecture has a clear evolutionary path to more than 100t and, ultimately, to 130t. Among the program's major accomplishments in 2015 were the first booster qualification hotfire test, a series of seven RS-25 adaptation hotfire tests, manufacturing of most of the major components for both core stage test articles and first flight tank, delivery of the Pegasus core stage barge, and the upper stage simulator. Renovations to the B-2 test stand for stage green run testing was completed at NASA Stennis Space Center. This year will see the second booster qualification motor hotfire, flight and additional development RS-25 engine tests, and completion of core stage test articles and test stands and several flight article

Vented Launch Vehicle Adaptor for a Manned Spacecraft with "Pusher" Launch Abort System

NASA Technical Reports Server (NTRS)

Vandervort, Robert E. (Inventor)

2017-01-01

A system, method, and apparatus for a vented launch vehicle adaptor (LVA) for a manned spacecraft with a "pusher" launch abort system are disclosed. The disclosed LVA provides a structural interface between a commercial crew vehicle (CCV) crew module/service module (CM/SM) spacecraft and an expendable launch vehicle. The LVA provides structural attachment of the module to the launch vehicle. It also provides a means to control the exhaust plume from a pusher-type launch abort system that is integrated into the module. In case of an on-pad or ascent abort, which requires the module to jettison away from the launch vehicle, the launch abort system exhaust plume must be safely directed away from critical and dangerous portions of the launch vehicle in order to achieve a safe and successful jettison.

GREECE Mission Launching Into Aurora

NASA Image and Video Library

2014-03-04

Caption: A NASA-funded sounding rocket launches into an aurora in the early morning of March 3, 2014, over Venetie, Alaska. The GREECE mission studies how certain structures – classic curls like swirls of cream in coffee -- form in the aurora. Credit: NASA/Christopher Perry More info: On March 3, 2014, at 6:09 a.m. EST, a NASA-funded sounding rocket launched straight into an aurora over Venetie, Alaska. The Ground-to-Rocket Electrodynamics – Electron Correlative Experiment, or GREECE, sounding rocket mission, which launched from Poker Flat Research Range in Poker Flat, Alaska, will study classic curls in the aurora in the night sky. The GREECE instruments travel on a sounding rocket that launches for a ten-minute ride right through the heart of the aurora reaching its zenith over the native village of Venetie, Alaska. To study the curl structures, GREECE consists of two parts: ground-based imagers located in Venetie to track the aurora from the ground and the rocket to take measurements from the middle of the aurora itself. At their simplest, auroras are caused when particles from the sun funnel over to Earth's night side, generate electric currents, and trigger a shower of particles that strike oxygen and nitrogen some 60 to 200 miles up in Earth's atmosphere, releasing a flash of light. But the details are always more complicated, of course. Researchers wish to understand the aurora, and movement of plasma in general, at much smaller scales including such things as how different structures are formed there. This is a piece of information, which in turn, helps paint a picture of the sun-Earth connection and how energy and particles from the sun interact with Earth's own magnetic system, the magnetosphere. GREECE is a collaborative effort between SWRI, which developed particle instruments and the ground-based imaging, and the University of California, Berkeley, measuring the electric and magnetic fields. The launch is supported by a sounding rocket team from

Launch Collision Probability

NASA Technical Reports Server (NTRS)

Bollenbacher, Gary; Guptill, James D.

1999-01-01

This report analyzes the probability of a launch vehicle colliding with one of the nearly 10,000 tracked objects orbiting the Earth, given that an object on a near-collision course with the launch vehicle has been identified. Knowledge of the probability of collision throughout the launch window can be used to avoid launching at times when the probability of collision is unacceptably high. The analysis in this report assumes that the positions of the orbiting objects and the launch vehicle can be predicted as a function of time and therefore that any tracked object which comes close to the launch vehicle can be identified. The analysis further assumes that the position uncertainty of the launch vehicle and the approaching space object can be described with position covariance matrices. With these and some additional simplifying assumptions, a closed-form solution is developed using two approaches. The solution shows that the probability of collision is a function of position uncertainties, the size of the two potentially colliding objects, and the nominal separation distance at the point of closest approach. ne impact of the simplifying assumptions on the accuracy of the final result is assessed and the application of the results to the Cassini mission, launched in October 1997, is described. Other factors that affect the probability of collision are also discussed. Finally, the report offers alternative approaches that can be used to evaluate the probability of collision.

Launch Control System Software Development System Automation Testing

NASA Technical Reports Server (NTRS)

Hwang, Andrew

2017-01-01

The Spaceport Command and Control System (SCCS) is the National Aeronautics and Space Administration's (NASA) launch control system for the Orion capsule and Space Launch System, the next generation manned rocket currently in development. This system requires high quality testing that will measure and test the capabilities of the system. For the past two years, the Exploration and Operations Division at Kennedy Space Center (KSC) has assigned a group including interns and full-time engineers to develop automated tests to save the project time and money. The team worked on automating the testing process for the SCCS GUI that would use streamed simulated data from the testing servers to produce data, plots, statuses, etc. to the GUI. The software used to develop automated tests included an automated testing framework and an automation library. The automated testing framework has a tabular-style syntax, which means the functionality of a line of code must have the appropriate number of tabs for the line to function as intended. The header section contains either paths to custom resources or the names of libraries being used. The automation library contains functionality to automate anything that appears on a desired screen with the use of image recognition software to detect and control GUI components. The data section contains any data values strictly created for the current testing file. The body section holds the tests that are being run. The function section can include any number of functions that may be used by the current testing file or any other file that resources it. The resources and body section are required for all test files; the data and function sections can be left empty if the data values and functions being used are from a resourced library or another file. To help equip the automation team with better tools, the Project Lead of the Automated Testing Team, Jason Kapusta, assigned the task to install and train an optical character recognition (OCR

Electron launching voltage monitor

DOEpatents

Mendel, Clifford W.; Savage, Mark E.

1992-01-01

An electron launching voltage monitor measures MITL voltage using a relationship between anode electric field and electron current launched from a cathode-mounted perturbation. An electron launching probe extends through and is spaced from the edge of an opening in a first MITL conductor, one end of the launching probe being in the gap between the MITL conductor, the other end being adjacent a first side of the first conductor away from the second conductor. A housing surrounds the launching probe and electrically connects the first side of the first conductor to the other end of the launching probe. A detector detects the current passing through the housing to the launching probe, the detected current being representative of the voltage between the conductors.

Electron launching voltage monitor

DOEpatents

Mendel, C.W.; Savage, M.E.

1992-03-17

An electron launching voltage monitor measures MITL voltage using a relationship between anode electric field and electron current launched from a cathode-mounted perturbation. An electron launching probe extends through and is spaced from the edge of an opening in a first MITL conductor, one end of the launching probe being in the gap between the MITL conductor, the other end being adjacent a first side of the first conductor away from the second conductor. A housing surrounds the launching probe and electrically connects the first side of the first conductor to the other end of the launching probe. A detector detects the current passing through the housing to the launching probe, the detected current being representative of the voltage between the conductors. 5 figs.

Design of an airborne launch vehicle for an air launched space booster

NASA Technical Reports Server (NTRS)

Chao, Chin; Choi, Rich; Cohen, Scott; Dumont, Brian; Gibin, Mauricius; Jorden, Rob; Poth, Stefan

1993-01-01

A conceptual design is presented for a carrier vehicle for an air launched space booster. This airplane is capable of carrying a 500,000 pound satellite launch system to an altitude over 40,000 feet for launch. The airplane features a twin fuselage configuration for improved payload and landing gear integration, a high aspect ratio wing for maneuverability at altitude, and is powered by six General Electric GE-90 engines. The analysis methods used and the systems employed in the airplane are discussed. Launch costs are expected to be competitive with existing launch systems.

Design of an airborne launch vehicle for an air launched space booster

NASA Astrophysics Data System (ADS)

Chao, Chin; Choi, Rich; Cohen, Scott; Dumont, Brian; Gibin, Mauricius; Jorden, Rob; Poth, Stefan

1993-12-01

A conceptual design is presented for a carrier vehicle for an air launched space booster. This airplane is capable of carrying a 500,000 pound satellite launch system to an altitude over 40,000 feet for launch. The airplane features a twin fuselage configuration for improved payload and landing gear integration, a high aspect ratio wing for maneuverability at altitude, and is powered by six General Electric GE-90 engines. The analysis methods used and the systems employed in the airplane are discussed. Launch costs are expected to be competitive with existing launch systems.

TeamXchange: A Team Project Experience Involving Virtual Teams and Fluid Team Membership

ERIC Educational Resources Information Center

Dineen, Brian R.

2005-01-01

TeamXchange, an online team-based exercise, is described. TeamXchange is consistent with the collaborative model of learning and provides a means of fostering enhanced student learning and engagement through collaboration in virtual teams experiencing periodic membership changes. It was administered in an undergraduate Organizational Behavior…

14 CFR 420.21 - Launch site location review-launch site boundary.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 14 Aeronautics and Space 4 2011-01-01 2011-01-01 false Launch site location review-launch site boundary. 420.21 Section 420.21 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION... the debris dispersion radius of the largest launch vehicle type and weight class proposed for the...

14 CFR 420.21 - Launch site location review-launch site boundary.

Code of Federal Regulations, 2013 CFR

2013-01-01

... 14 Aeronautics and Space 4 2013-01-01 2013-01-01 false Launch site location review-launch site boundary. 420.21 Section 420.21 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION... the debris dispersion radius of the largest launch vehicle type and weight class proposed for the...

14 CFR 420.21 - Launch site location review-launch site boundary.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 14 Aeronautics and Space 4 2012-01-01 2012-01-01 false Launch site location review-launch site boundary. 420.21 Section 420.21 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION... the debris dispersion radius of the largest launch vehicle type and weight class proposed for the...

14 CFR 420.21 - Launch site location review-launch site boundary.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 14 Aeronautics and Space 4 2014-01-01 2014-01-01 false Launch site location review-launch site boundary. 420.21 Section 420.21 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION... the debris dispersion radius of the largest launch vehicle type and weight class proposed for the...

14 CFR 420.21 - Launch site location review-launch site boundary.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Launch site location review-launch site boundary. 420.21 Section 420.21 Aeronautics and Space COMMERCIAL SPACE TRANSPORTATION, FEDERAL AVIATION... the debris dispersion radius of the largest launch vehicle type and weight class proposed for the...

14 CFR 417.17 - Launch reporting requirements and launch specific updates.

Code of Federal Regulations, 2010 CFR

2010-01-01

... by the terms of the launch operator's license. A launch operator must file any change to the... information: (i) Payload information required by § 415.59 of this chapter; and (ii) Flight information, including the launch vehicle, planned flight path, staging and impact locations, and any on-orbit activity...

14 CFR 417.17 - Launch reporting requirements and launch specific updates.

Code of Federal Regulations, 2014 CFR

2014-01-01

... by the terms of the launch operator's license. A launch operator must file any change to the... information: (i) Payload information required by § 415.59 of this chapter; and (ii) Flight information, including the launch vehicle, planned flight path, staging and impact locations, and any on-orbit activity...

14 CFR 417.17 - Launch reporting requirements and launch specific updates.

Code of Federal Regulations, 2013 CFR

2013-01-01

... by the terms of the launch operator's license. A launch operator must file any change to the... information: (i) Payload information required by § 415.59 of this chapter; and (ii) Flight information, including the launch vehicle, planned flight path, staging and impact locations, and any on-orbit activity...

14 CFR 417.17 - Launch reporting requirements and launch specific updates.

Code of Federal Regulations, 2011 CFR

2011-01-01

... by the terms of the launch operator's license. A launch operator must file any change to the... information: (i) Payload information required by § 415.59 of this chapter; and (ii) Flight information, including the launch vehicle, planned flight path, staging and impact locations, and any on-orbit activity...

14 CFR 417.17 - Launch reporting requirements and launch specific updates.

Code of Federal Regulations, 2012 CFR

2012-01-01

... by the terms of the launch operator's license. A launch operator must file any change to the... information: (i) Payload information required by § 415.59 of this chapter; and (ii) Flight information, including the launch vehicle, planned flight path, staging and impact locations, and any on-orbit activity...

The Next Giant Leap: NASA's Ares Launch Vehicles Overview

NASA Technical Reports Server (NTRS)

Cook, Stephen A.; Vanhooser, Teresa

2007-01-01

The National Aeronautics and Space Administration (NASA)'s Constellation Program is developing new launch vehicles (Ares) and spacecraft (Orion) to send astronauts to the Moon, Mars, and beyond. This paper presents plans, projections, and progress toward fielding the Ares I and Ares V vehicles, and the Ares I-X test flight in 2009. NASA is building on both new research and aeronautical capabilities, as well as lessons learned from almost 50 years of aerospace experience. The Ares Projects Office (APO) completed the Ares I System Requirements Review (SRR) in 2006 and the System Definition Review in autumn 2007; and will focus on the Preliminary Design Review in 2008. Ares I is currently being refined to meet safety, operability, reliability, and affordability goals. The Ares team is simultaneously testing Ares I elements and building hardware for Ares I-X, while the Ares V is in the early design stage, with the team validating requirements and ensuring commonality with Ares I. Ares I and V are key to opening the space frontier for peaceful endeavors.

Why Major Programs Need Innovation Support Labs: An Example from the Space Shuttle Launch Program at KSC

NASA Technical Reports Server (NTRS)

Youngquist, Robert C.; Starr, Stanley O.; Stevenson, G.; Rivera, Jorge E.; Sullivan, Steven J.

2011-01-01

For over 30 years the Kennedy Space Center (KSC) has processed the Space Shuttle; handling all hands-on aspects from receiving the Orbiter, External Tanks, Solid Rocket Booster Segments, and Payloads, through certification, check-out, and assembly, and ending with fueling, count-down, and launch. A team of thousands have worked this highly complicated, yet supremely organized, process and have, as a consequence, generated an exceptional amount of technology to solve a host of problems. This paper describes the contributions of one team that formed with the express purpose to help solve some of these diverse Shuttle ground processing problems.

The Interstellar Boundary Explorer (IBEX) - Time to Launch!

NASA Astrophysics Data System (ADS)

McComas, David

The Interstellar Boundary Explorer (IBEX) mission is scheduled to launch in mid-July 2008, right around the time of this COSPAR meeting. IBEX will make the first global observations of the heliosphere's interaction with the interstellar medium. IBEX achieves these breakthrough observations by traveling outside of the Earth's magnetosphere in a highly elliptical orbit and taking global Energetic Neutral Atoms (ENA) images with two very large aperture single pixel ENA cameras. IBEX-Lo makes measurements in 8 contiguous energy pass bands covering from ˜10 eV to 2 keV; IBEX-Hi similarly covers from ˜300 eV to 6 keV in 6 contiguous pass bands. IBEX's high-apogee (˜50RE ) orbit enables heliospheric ENA measurements by providing viewing from far outside the earth's relatively bright magnetospheric ENA emissions. The IBEX cameras view perpendicular to the spacecraft's sun-pointed spin axis. Each six months, the spacecraft spin and progression of the sun-pointing spin axis as the Earth moves around the Sun lead naturally to global, all-sky images. IBEX is the first mission to achieve a high altitude from a standard Pegasus launch vehicle. We accomplish this by adding the propulsion from an IBEX-supplied solid rocket motor and the spacecraft's hydrazine propulsion system. Additional information on IBEX is available at www.ibex.swri.edu. This talk, on behalf of the IBEX science and engineering teams, will summarize the IBEX science and mission and will provide an up-to-the-minute update on the status of the mission, including any new information on the launch and commissioning status.

LAUNCH Health Forum

NASA Image and Video Library

2010-10-30

Tom Kalil, Deputy Director of the White House Office of Science and Technology Policy, opens the LAUNCH: Health forum at NASA's Kennedy Space Center in Florida on Saturday, Oct. 30, 2010. LAUNCH: Health provides a forum to discuss accelerating innovation for a sustainable future. LAUNCH: Health partners include NASA, USAID and Nike. Photo Credit: (NASA/Bill Ingalls)

Turbine Technology Team - An overview of current and planned activities relevant to the National Launch System (NLS)

NASA Technical Reports Server (NTRS)

Griffin, Lisa W.; Huber, Frank W.

1992-01-01

The current status of the activities and future plans of the Turbine Technology Team of the Consortium for Computational Fluid Dynamics is reviewed. The activities of the Turbine Team focus on developing and enhancing codes and models, obtaining data for code validation and general understanding of flows through turbines, and developing and analyzing the aerodynamic designs of turbines suitable for use in the Space Transportation Main Engine fuel and oxidizer turbopumps. Future work will include the experimental evaluation of the oxidizer turbine configuration, the development, analysis, and experimental verification of concepts to control secondary and tip losses, and the aerodynamic design, analysis, and experimental evaluation of turbine volutes.

Space Shuttle Discovery Launch

NASA Image and Video Library

2008-05-31

NASA Shuttle Launch Director Michael Leinbach, left, STS-124 Assistant Launch Director Ed Mango, center, and Flow Director for Space Shuttle Discovery Stephanie Stilson clap in the the Launch Control Center after the main engine cut off and successful launch of the Space Shuttle Discovery (STS-124) Saturday, May 31, 2008, at the Kennedy Space Center in Cape Canaveral, Fla. The Shuttle lifted off from launch pad 39A at 5:02 p.m. EDT. Photo Credit: (NASA/Bill Ingalls)

STS-97 ascent team in WFCR

NASA Image and Video Library

2000-11-20

JSC2000-07294 (20 November 2000) --- The 40-odd flight controllers assigned to the STS-97 ascent team and some special guests pose for a group portrait in the shuttle flight control room in Houston's Mission Control Center (JSC). The five guests attired in the blue and white shirts are the flight crew members for the STS-97 crew, scheduled to be launched from Florida on the last day of this month. The astronauts are, from the left, Joseph R. Tanner, Carlos I. Noriega, Brent W. Jett, Jr., Michael J. Bloomfield and Marc Garneau, who represents the Canadian Space Agency (CSA). Ascent shift flight director Wayne Hale stands next to Tanner.

Sentinel-5 Precursor: First Copernicus Atmospheric Mission Ready for Launch

NASA Astrophysics Data System (ADS)

McMullan, Kevin; Nett, Herbert; Fehr, Thorsten; Ingmann, Paul

2016-08-01

Sentinel-5 Precursor (S-5P) will be the first of a series of atmospheric missions to be launched within the European Commission's Copernicus (former GMES) Programme. With the current launch window mid October - mid November 2016 and a nominal lifetime of 7 years S-5P is expected to provide continuity in the availability of global atmospheric data products between its predecessor missions SCIAMACHY (Envisat) and OMI (AURA) and the future Sentinel-4 and -5 series.S-5P will deliver unique data regarding the sources and sinks of trace gases with a focus on the lower Troposphere including the planet boundary layer. Due to its enhanced spatial, temporal and spectral sampling capabilities, as compared to its predecessors.The S-5P satellite will carry a single payload, TROPOMI (TROPOspheric Monitoring Instrument) which is jointly developed by The Netherlands and ESA. Covering spectral channels in the UV, visible, near- and short-wave infrared it will measure various key species including tropospheric/stratospheric ozone, NO2, SO2, CO, CH4, CH2O as well as cloud and aerosol parameters.The S-5P Project has successfully passed the Ground Segment Acceptance Review (GS-AR) and the satellite level Qualification Acceptance Review (QAR) in March and April 2016, respectively. Remaining pre-launch tasks focus on the detailed planning of Phase E1 activities and the training of the operations teams.

14 CFR 1214.117 - Launch and orbit parameters for a standard launch.

Code of Federal Regulations, 2010 CFR

2010-01-01

...) Launch at a time, selected by NASA, from a launch window of not less than 1 hour (a more restrictive launch window may be provided as an optional service). (b) For shared flights from KSC to the standard...

Mobile Launch Platform Vehicle Assembly Area (SWMU 056) Biosparge Expansion Interim Measures Work Plan

NASA Technical Reports Server (NTRS)

Burcham, Michael S.; Daprato, Rebecca C.

2016-01-01

This document presents the design details for an Interim Measure (IM) Work Plan (IMWP) for the Mobile Launch Platform/Vehicle Assembly Building (MLPV) Area, located at the John F. Kennedy Space Center (KSC), Florida. The MLPV Area has been designated Solid Waste Management Unit Number 056 (SWMU 056) under KSC's Resource Conservation and Recovery Act (RCRA) Corrective Action Program. This report was prepared by Geosyntec Consultants (Geosyntec) for the National Aeronautics and Space Administration (NASA) under contract number NNK09CA02B and NNK12CA13B, project control number ENV1642. The Advanced Data Package (ADP) presentation covering the elements of this IMWP report received KSC Remediation Team (KSCRT) approval at the December 2015 Team Meeting; the meeting minutes are included in Appendix A.

Development of a large scale Chimera grid system for the Space Shuttle Launch Vehicle

NASA Technical Reports Server (NTRS)

Pearce, Daniel G.; Stanley, Scott A.; Martin, Fred W., Jr.; Gomez, Ray J.; Le Beau, Gerald J.; Buning, Pieter G.; Chan, William M.; Chiu, Ing-Tsau; Wulf, Armin; Akdag, Vedat

1993-01-01

The application of CFD techniques to large problems has dictated the need for large team efforts. This paper offers an opportunity to examine the motivations, goals, needs, problems, as well as the methods, tools, and constraints that defined NASA's development of a 111 grid/16 million point grid system model for the Space Shuttle Launch Vehicle. The Chimera approach used for domain decomposition encouraged separation of the complex geometry into several major components each of which was modeled by an autonomous team. ICEM-CFD, a CAD based grid generation package, simplified the geometry and grid topology definition by provoding mature CAD tools and patch independent meshing. The resulting grid system has, on average, a four inch resolution along the surface.

Fifth FLTSATCOM to be launched

NASA Technical Reports Server (NTRS)

1981-01-01

Launch of the FLTSATOOM-E, into an elliptical orbit by the Atlas Centaur launch vehicle is announced. The launch and relevant launch operations are described. A chart of the launch sequence for FLTSATCOM-E communication satellite is given.

Enhancing the Cassini Mission Through FP Applications After Launch

NASA Technical Reports Server (NTRS)

Morgan, Paula S.

2016-01-01

Although rigorous pre-emptive measures are taken to preclude failures and anomalous conditions from occurring in JPL spacecraft missions prior to launch, unforeseeable problems can still surface after liftoff. In the case of the Cassini/Huygens Mission-to-Saturn spacecraft, several problems were observed post-launch: 1) immediately after takeoff, the collected engineering/science data stored on the Solid State Recorders (SSR) contained a significantly higher number of corrupted bits than was expected (considerably over spec) due to human error in the memory mapping of these devices, 2) numerous Solid State Power Switches (SSPS) sporadically tripped off throughout the mission due to cosmic ray bombardment from the unique space environment, and 3) false assumptions in the pressure regulator design in combination with missing heritage test data led to inaccurate design conclusions, causing the issuance of two waivers for the regulator to close properly (a potentially mission catastrophic single-point failure which occurred 24 days after launch) - amongst other problems. For Cassini, some of these anomalies led to arduous work-arounds or required continuous monitoring of telemetry variables by the ground-based Spacecraft Operations Flight Support (SOFS) team in order to detect and fix fault occurrences as they happened. Fortunately, sufficient funding and schedule margin allowed several Fault Protection (FP) solutions to be implemented into post-launch Flight Software (FSW) uploads to help resolve these issues autonomously, reducing SOFS ground support efforts while improving anomaly recovery time in order to preserve maximum science capture. This paper details the FP applications used to resolve the above issues as well as to optimize solutions for several other problems experienced by the Cassini spacecraft during its fight, in order to enhance the spacecraft's overall mission success throughout the 18 years of its 20 year expedition to and within the Saturnian

A member of the U.S. Women's World Cup Soccer Team is greeted by Parazynski

NASA Technical Reports Server (NTRS)

1999-01-01

A member of the U.S. Women's World Cup Soccer Team is greeted by NASA Astronaut Scott E. Parazynski (left) upon her arrival at the Skid Strip at Cape Canaveral Air Station as her teammates look on. The team is at KSC to view the launch of Space Shuttle mission STS-93 scheduled for liftoff at 12:36 a.m. EDT July 20. Much attention has been generated over the launch due to Commander Eileen M. Collins, the first woman to serve as commander of a Shuttle mission. The primary payload of the five- day mission is the Chandra X-ray Observatory, which will allow scientists from around the world to study some of the most distant, powerful and dynamic objects in the universe. The new telescope is 20 to 50 times more sensitive than any previous X- ray telescope and is expected to unlock the secrets of supernovae, quasars and black holes.

Launch summary for 1978

NASA Technical Reports Server (NTRS)

Vostreys, R. W.

1978-01-01

Sounding rocket, satellite, and space probe launchings are presented. Time, date, and location of the launches are provided. The sponsoring countries and the institutions responsible for the launch are listed.

Launch Vehicle Control Center Architectures

NASA Technical Reports Server (NTRS)

Watson, Michael D.; Epps, Amy; Woodruff, Van; Vachon, Michael Jacob; Monreal, Julio; Levesque, Marl; Williams, Randall; Mclaughlin, Tom

2014-01-01

Launch vehicles within the international community vary greatly in their configuration and processing. Each launch site has a unique processing flow based on the specific launch vehicle configuration. Launch and flight operations are managed through a set of control centers associated with each launch site. Each launch site has a control center for launch operations; however flight operations support varies from being co-located with the launch site to being shared with the space vehicle control center. There is also a nuance of some having an engineering support center which may be co-located with either the launch or flight control center, or in a separate geographical location altogether. A survey of control center architectures is presented for various launch vehicles including the NASA Space Launch System (SLS), United Launch Alliance (ULA) Atlas V and Delta IV, and the European Space Agency (ESA) Ariane 5. Each of these control center architectures shares some similarities in basic structure while differences in functional distribution also exist. The driving functions which lead to these factors are considered and a model of control center architectures is proposed which supports these commonalities and variations.

Report on Mars Odyssey Independent Assessment Team Activities

NASA Technical Reports Server (NTRS)

Barto, R.; Day, John H. (Technical Monitor)

2001-01-01

During the week of March 26, 2001, I was asked by Rich Katz, NASA-GSFC, to participate on the Mars Odyssey Independent Assessment Team (IAT) that would investigate the implications of the failure of an Actel RP 1280 Field Programmable Gate Array (FPGA), which occurred on the Space Infrared Telescope Facility (SIRTF) spacecraft, on the Mars Odyssey spacecraft that was set to launch on April 7, 2001. We were provided with review materials from JPL and Lockheed Martin (LMA) that would be discussed at a meeting on April 2, 2001.

Sensitivity of the Asteroid Redirect Robotic Mission (ARRM) to Launch Date and Asteroid Stay Time

NASA Technical Reports Server (NTRS)

Mcguire, Melissa L.; Burke, Laura M.; McCarty, Steven L.; Strange, Nathan J.; Qu, Min; Shen, Haijun; Vavrina, Matthew A.

2017-01-01

National Aeronautics and Space Administrations (NASAs) proposed Asteroid Redirect Mission (ARM) is being designed to robotically capture and then redirect an asteroidal boulder into a stable orbit in the vicinity of the moon, where astronauts would be able to visit and study it. The current reference trajectory for the robotic portion, ARRM, assumes a launch on a Delta-IV H in the end of the calendar year 2021, with a return for astronaut operations in cislunar space in 2026. The current baseline design allocates 245 days of stay time at the asteroid for operations and boulder collection. This paper outlines analysis completed by the ARRM mission design team to understand the sensitivity of the reference trajectory to launch date and asteroid stay time.

Sensitivity of the Asteroid Redirect Robotic Mission (ARRM) to Launch Date and Asteroid Stay Time

NASA Technical Reports Server (NTRS)

Mcguire, Melissa L.; Burke, Laura M.; McCarty, Steven L.; Strange, Nathan J.; Qu, Min; Shen, Haijun; Vavrina, Matthew A.

2017-01-01

National Aeronautics and Space Administrations (NASAs) proposed Asteroid Redirect Mission (ARM) is being designed to robotically capture and then redirect an asteroidal boulder mass into a stable orbit in the vicinity of the moon, where astronauts would be able to visit and study it. The current reference trajectory for the robotic portion, ARRM, assumes a launch on a Delta IV H in the end of the calendar year 2021, with a return for astronaut operations in cislunar space in 2026. The current baseline design allocates 245 days of stay time at the asteroid for operations and boulder collection. This paper outlines analysis completed by the ARRM mission design team to understand the sensitivity of the reference trajectory to launch date and asteroid stay time.

Voices from Team-Teaching Classrooms: A Case Study in Junior High Schools in Japan

ERIC Educational Resources Information Center

Fujimoto-Adamson, Naoki

2010-01-01

Team-teaching between a Japanese teacher of language (JTL) and a native-English speaker assistant language teacher (ALT) has been widely implemented in English-language classrooms in Japanese schools for more than 20 years under the Japan Exchange Teaching Program (JET) launched in 1987. This study focuses on the classroom roles and…

Preparing NASA's Next Solar Satellite for Launch

NASA Image and Video Library

2017-12-08

Orbital Sciences team members move the second half of the payload fairing before it is placed over NASA's IRIS (Interface Region Imaging Spectrograph) spacecraft. The fairing connects to the nose of the Orbital Sciences Pegasus XL rocket that will lift the solar observatory into orbit. The work is taking place in a hangar at Vandenberg Air Force Base, where IRIS is being prepared for launch on a Pegasus XL rocket. Scheduled for launch from Vandenberg on June 26, 2013, IRIS will open a new window of discovery by tracing the flow of energy and plasma through the chromospheres and transition region into the sun's corona using spectrometry and imaging. IRIS fills a crucial gap in our ability to advance studies of the sun-to-Earth connection by tracing the flow of energy and plasma through the foundation of the corona and the region around the sun known as the heliosphere. High res file available here: 1.usa.gov/11yal3w Photo Credit: NASA/Tony Vauclin NASA image use policy. NASA Goddard Space Flight Center enables NASA’s mission through four scientific endeavors: Earth Science, Heliophysics, Solar System Exploration, and Astrophysics. Goddard plays a leading role in NASA’s accomplishments by contributing compelling scientific knowledge to advance the Agency’s mission. Follow us on Twitter Like us on Facebook Find us on Instagram

The IRSC Baccalaureate Transition Team: Leading Change in a Culture of Communication, Collaboration, and Creativity

ERIC Educational Resources Information Center

Massey, Edwin R.; Locke, Mary G.; Neuhard, Ian P.

2009-01-01

No other Florida community college has successfully developed and launched nine baccalaureate degree programs at one time. Indian River State College accomplished this goal--and gained Southern Association of Colleges and Schools (SACS) Level II accreditation--in 12 months by establishing a college-wide Baccalaureate Transition Team within a…

Launch summary for 1980

NASA Technical Reports Server (NTRS)

Vostreys, R. W.

1981-01-01

Sounding rockets, artificial Earth satellites, and space probes launched betweeen January 1 and December 31, 1980 are listed. Data tabulated for the rocket launchings show launching site, instruments carried, date of launch, agency rocket identification, sponsoring country, experiment discipline, peak altitude, and the experimenter or institution responsible. Tables for satellites and space probes show COSPAR designation, spacecraft name, country, launch date, epoch date, orbit type, apoapsis, periapsis and inclination period. The functions and responsibilities of the World Data Center and the areas of scientific interest at the seven subcenters are defined. An alphabetical listing of experimenters using the sounding rockets is also provided.

Pegasus air-launched space booster flight test program

NASA Astrophysics Data System (ADS)

Elias, Antonio L.; Knutson, Martin A.

1995-03-01

Pegasus is a satellite-launching space rocket dropped from a B52 carrier aircraft instead of launching vertically from a ground pad. Its three-year, privately-funded accelerated development was carried out under a demanding design-to-nonrecurring cost methodology, which imposed unique requirements on its flight test program, such as the decision not to drop an inert model from the carrier aircraft; the number and type of captive and free-flight tests; the extent of envelope exploration; and the decision to combine test and operational orbital flights. The authors believe that Pegasus may be the first vehicle where constraints in the number and type of flight tests to be carried out actually influenced the design of the vehicle. During the period November 1989 to February of 1990 a total of three captive flight tests were conducted, starting with a flutter clearing flight and culminating in a complete drop rehearsal. Starting on April 5, 1990, two combination test/operational flights were conducted. A unique aspect of the program was the degree of involvement of flight test personnel in the early design of the vehicle and, conversely, of the design team in flight testing and early flight operations. Various lessons learned as a result of this process are discussed throughout this paper.

Computational fluid dynamic modeling of the summit of Mt. Hopkins for the MMT Observatory

NASA Astrophysics Data System (ADS)

Callahan, S.

2010-07-01

Over the past three decades, the staff of the MMT observatory used a variety of techniques to predict the summit wind characteristics including wind tunnel modeling and the release of smoke bombs. With the planned addition of a new instrument repair facility to be constructed on the summit of Mt. Hopkins, new computational fluid dynamic (CFD) models were made to determine the building's influence on the thermal environment around the telescope. The models compared the wind profiles and density contours above the telescope enclosure with and without the new building. The results show the steeply-sided Mount Hopkins dominates the summit wind profiles. In typical winds, the height of the telescope remains above the ground layer and is sufficiently separated from the new facility to insure the heat from the new building does not interfere with the telescope. The results also confirmed the observatories waste heat exhaust duct location needs to be relocated to prevent heat from being trapped in the wind shadow of the new building and lofting above the telescope. These useful models provide many insights into understanding the thermal environment of the summit.

Software framework for the upcoming MMT Observatory primary mirror re-aluminization

NASA Astrophysics Data System (ADS)

Gibson, J. Duane; Clark, Dusty; Porter, Dallan

2014-07-01

Details of the software framework for the upcoming in-situ re-aluminization of the 6.5m MMT Observatory (MMTO) primary mirror are presented. This framework includes: 1) a centralized key-value store and data structure server for data exchange between software modules, 2) a newly developed hardware-software interface for faster data sampling and better hardware control, 3) automated control algorithms that are based upon empirical testing, modeling, and simulation of the aluminization process, 4) re-engineered graphical user interfaces (GUI's) that use state-of-the-art web technologies, and 5) redundant relational databases for data logging. Redesign of the software framework has several objectives: 1) automated process control to provide more consistent and uniform mirror coatings, 2) optional manual control of the aluminization process, 3) modular design to allow flexibility in process control and software implementation, 4) faster data sampling and logging rates to better characterize the approximately 100-second aluminization event, and 5) synchronized "real-time" web application GUI's to provide all users with exactly the same data. The framework has been implemented as four modules interconnected by a data store/server. The four modules are integrated into two Linux system services that start automatically at boot-time and remain running at all times. Performance of the software framework is assessed through extensive testing within 2.0 meter and smaller coating chambers at the Sunnyside Test Facility. The redesigned software framework helps ensure that a better performing and longer lasting coating will be achieved during the re-aluminization of the MMTO primary mirror.

STS-135 Atlantis Launch

NASA Image and Video Library

2011-07-07

NASA Administrator Charles Bolden, right, participates in the post launch traditional beans and cornbread at the NASA Kennedy Space Center, Launch Control Center (LCC) shortly after the space shuttle Atlantis, STS-135, launched on Friday, July 8, 2011, in Cape Canaveral, Fla. The launch of Atlantis is the final flight of the shuttle program, a 12-day mission to the International Space Station. Photo Credit: (NASA/Bill Ingalls)

14 CFR 1214.117 - Launch and orbit parameters for a standard launch.

Code of Federal Regulations, 2013 CFR

2013-01-01

...) Launch from Kennedy Space Center (KSC) into the customer's choice of two standard mission orbits: 160 NM... 14 Aeronautics and Space 5 2013-01-01 2013-01-01 false Launch and orbit parameters for a standard launch. 1214.117 Section 1214.117 Aeronautics and Space NATIONAL AERONAUTICS AND SPACE ADMINISTRATION...

14 CFR 1214.117 - Launch and orbit parameters for a standard launch.

Code of Federal Regulations, 2012 CFR

2012-01-01

...) Launch from Kennedy Space Center (KSC) into the customer's choice of two standard mission orbits: 160 NM... 14 Aeronautics and Space 5 2012-01-01 2012-01-01 false Launch and orbit parameters for a standard launch. 1214.117 Section 1214.117 Aeronautics and Space NATIONAL AERONAUTICS AND SPACE ADMINISTRATION...

14 CFR 1214.117 - Launch and orbit parameters for a standard launch.

Code of Federal Regulations, 2011 CFR

2011-01-01

...) Launch from Kennedy Space Center (KSC) into the customer's choice of two standard mission orbits: 160 NM... 14 Aeronautics and Space 5 2011-01-01 2010-01-01 true Launch and orbit parameters for a standard launch. 1214.117 Section 1214.117 Aeronautics and Space NATIONAL AERONAUTICS AND SPACE ADMINISTRATION...

Venture Class Launch Services

NASA Technical Reports Server (NTRS)

Wiese, Mark

2016-01-01

Provide an introduction to the Launch Services Program, and specifically the strategic initiative that drove the Venture Class Launch Services contracts. Provide information from the VCLS request for proposals, as well as the Agency's CubeSat Launch Initiative.

Foreign launch competition growing

NASA Astrophysics Data System (ADS)

Brodsky, R. F.; Wolfe, M. G.; Pryke, I. W.

1986-07-01

A survey is given of progress made by other nations in providing or preparing to provide satellite launch services. The European Space Agency has four generations of Ariane vehicles, with a fifth recently approved; a second launch facility in French Guiana that has become operational has raised the possible Ariane launch rate to 10 per year, although a May failure of an Ariane 2 put launches on hold. The French Hermes spaceplane and the British HOTOL are discussed. Under the auspices of the Italian National Space Plane, the Iris orbital transfer vehicle is developed and China's Long March vehicles and the Soviet Protons and SL-4 vehicles are discussed; the Soviets moreover are apparently developing not only a Saturn V-class heavy lift vehicle with a 150,000-kg capacity (about five times the largest U.S. capacity) but also a space shuttle and a spaceplane. Four Japanese launch vehicles and some vehicles in an Indian program are also ready to provide launch services. In this new, tough market for launch services, the customers barely outnumber the suppliers. The competition develops just as the Challenger and Titan disasters place the U.S. at a disadvantage and underline the hard work ahead to recoup its heretofore leading position in launch services.

Hail Disrometer Array for Launch Systems Support

NASA Technical Reports Server (NTRS)

Lane, John E.; Sharp, David W.; Kasparis, Takis C.; Doesken, Nolan J.

2008-01-01

vehicle is on the launch pad, with special attention after any storm suspected of containing hail. If no hail is recorded by the HMS, the vehicle and pad inspection team has no need to conduct a thorough inspection of the vehicle immediately following a storm. On the afternoon of July 13, 2007, hail on the ground was reported by observers at the VAB, about three miles west of Pad 39A, as well as at several other locations around Kennedy Space Center. The HMS showed no impact detections, indicating that the shuttle had not been damaged by any of the numerous hail events which occurred that day.

Pegasus air-launched space booster

NASA Astrophysics Data System (ADS)

Lindberg, Robert E.; Mosier, Marty R.

The launching of small satellites with the mother- aircraft-launched Pegasus booster yields substantial cost improvements over ground launching and enhances operational flexibility, since it allows launches to be conducted into any orbital inclination. The Pegasus launch vehicle is a three-stage solid-rocket-propelled system with delta-winged first stage. The major components of airborne support equipment, located on the mother aircraft, encompass a launch panel operator console, an electronic pallet, and a pylon adapter. Alternatives to the currently employed B-52 launch platform aircraft have been identified for future use. Attention is given to the dynamic, thermal, and acoustic environments experienced by the payload.

STS-114: Discovery Post MMT Press Conference

NASA Technical Reports Server (NTRS)

2005-01-01

George Diller, NASA Public Affairs, introduces the panel who consist of: Bill Parsons, Space Shuttle Program Manager; Wayne Hale, Space Shuttle Deputy Program Manager; Ed Mango, Deputy Manager JSC Orbiter Project Office; and Mike Wetmore, Director of Shuttle Processing. Bill Parsons begins by expressing that he is still searching for the problem with the low level fuel sensor inside the external tank. Hale talks about more ambient tests that will be performed to fix this problem. Mango expresses his findings from tests in the aft engine compartment, point sensor box, orbiter wiring, and wire resistance. He also talks about looking in detail into the circuit analysis of the point sensor box. Questions from the news media about tanking tests and extending the launch window are addressed.

Flight and Integrated Vehicle Testing: Laying the Groundwork for the Next Generation of Space Exploration Launch Vehicles

NASA Technical Reports Server (NTRS)

Taylor, J. L.; Cockrell, C. E.

2009-01-01

Integrated vehicle testing will be critical to ensuring proper vehicle integration of the Ares I crew launch vehicle and Ares V cargo launch vehicle. The Ares Projects, based at Marshall Space Flight Center in Alabama, created the Flight and Integrated Test Office (FITO) as a separate team to ensure that testing is an integral part of the vehicle development process. As its name indicates, FITO is responsible for managing flight testing for the Ares vehicles. FITO personnel are well on the way toward assembling and flying the first flight test vehicle of Ares I, the Ares I-X. This suborbital development flight will evaluate the performance of Ares I from liftoff to first stage separation, testing flight control algorithms, vehicle roll control, separation and recovery systems, and ground operations. Ares I-X is now scheduled to fly in summer 2009. The follow-on flight, Ares I-Y, will test a full five-segment first stage booster and will include cryogenic propellants in the upper stage, an upper stage engine simulator, and an active launch abort system. The following flight, Orion 1, will be the first flight of an active upper stage and upper stage engine, as well as the first uncrewed flight of an Orion spacecraft into orbit. The Ares Projects are using an incremental buildup of flight capabilities prior to the first operational crewed flight of Ares I and the Orion crew exploration vehicle in 2015. In addition to flight testing, the FITO team will be responsible for conducting hardware, software, and ground vibration tests of the integrated launch vehicle. These efforts will include verifying hardware, software, and ground handling interfaces. Through flight and integrated testing, the Ares Projects will identify and mitigate risks early as the United States prepares to take its next giant leaps to the Moon and beyond.

Earth Observing System (EOS) Aqua Launch and Early Mission Attitude Support Experiences

NASA Technical Reports Server (NTRS)

Tracewell, D.; Glickman, J.; Hashmall, J.; Natanson, G.; Sedlak, J.

2003-01-01

The Earth Observing System (EOS) Aqua satellite was successfully launched on May 4,2002. Aqua is the second in the series of EOS satellites. EOS is part of NASA s Earth Science Enterprise Program, whose goals are to advance the scientific understanding of the Earth system. Aqua is a three-axis stabilized, Earth-pointing spacecraft in a nearly circular, sun-synchronous orbit at an altitude of 705 km. The Goddard Space Flight Center (GSFC) Flight Dynamics attitude team supported all phases of the launch and early mission. This paper presents the main results and lessons learned during this period, including: real-time attitude mode transition support, sensor calibration, onboard computer attitude validation, response to spacecraft emergencies, postlaunch attitude analyses, and anomaly resolution. In particular, Flight Dynamics support proved to be invaluable for successful Earth acquisition, fine-point mode transition, and recognition and correction of several anomalies, including support for the resolution of problems observed with the MODIS instrument.

Combustion devices technology team - An overview and status of STME-related activities

NASA Technical Reports Server (NTRS)

Tucker, P. K.; Croteau-Gillespie, Margie

1992-01-01

The Consortium for CFD applications in propulsion technology has been formed at NASA/Marshall Space Flight Center. The combustion devices technology team is one of the three teams that constitute the Consortium. While generally aiming to advance combustion devices technology for rocket propulsion, the team's efforts for the last 1 and 1/2 years have been focused on issues relating to the Space Transportation Main Engine (STME) nozzle. The nozzle design uses hydrogen-rich turbine exhaust to cool the wall in a film/dump scheme. This method of cooling presents challenges and associated risks for the nozzle designers and the engine/vehicle integrators. Within the nozzle itself, a key concern is the ability to effectively and efficiently film cool the wall. From the National Launch System vehicle base standpoint, there are concerns with dumping combustible gases at the nozzle exit and their potential adverse effects on the base thermal environment. The Combustion Team has developed and is implementing plans to use validated CFD tools to aid in risk mitigation for both areas.

Proposal of New Triggered Lightning Launch Commit Criteria for Japan's Safety Rocket Launch

NASA Astrophysics Data System (ADS)

Saito, Yasuhiro; Saito, Toshiya; Okita, Koichi

2013-09-01

Triggered lightning for rocket launch can cause the failure.The current Japanese criteria to postpone the launch opportunity is the thickness of cloud 1.8km with 0 -20 degrees Celsius. Of all H2A launches during these ten years, slipping launches have occurred over half of its flights. So, we have initiated a research on Triggered Lightning Launch Commit Criteria, two years ago.We present the overall activities with the observation campaign (RAIJIN*) in Feb/2012 and Jan-Feb/2013, by means of air-born field mill with airplane, X-band dual polarization radar, ground based field mill and Videosonde. Also, the analytical results and proposal of the new criteria will be shown.*) Raijin is originally a name for Thunder god in Japanese and here it stands for Rocket launch Atmospheric electricity Investigation by Jaxa IN cooperation with academia.

When Teams Fail to Self-Regulate: Predictors and Outcomes of Team Procrastination Among Debating Teams.

PubMed

Van Hooft, Edwin A J; Van Mierlo, Heleen

2018-01-01

Models of team development have indicated that teams typically engage in task delay during the first stages of the team's life cycle. An important question is to what extent this equally applies to all teams, or whether there is variation across teams in the amount of task delay. The present study introduces the concept of team procrastination as a lens through which we can examine whether teams collectively engage in unplanned, voluntary, and irrational delay of team tasks. Based on theory and research on self-regulation, team processes, and team motivation we developed a conceptual multilevel model of predictors and outcomes of team procrastination. In a sample of 209 student debating teams, we investigated whether and why teams engage in collective procrastination as a team, and what consequences team procrastination has in terms of team member well-being and team performance. The results supported the existence of team procrastination as a team-level construct that has some stability over time. The teams' composition in terms of individual-level trait procrastination, as well as the teams' motivational states (i.e., team learning goal orientation, team performance-approach goal orientation in interaction with team efficacy) predicted team procrastination. Team procrastination related positively to team members' stress levels, especially for those low on trait procrastination. Furthermore, team procrastination had an indirect negative relationship with team performance, through teams' collective stress levels. These findings add to the theoretical understanding of self-regulatory processes of teams, and highlight the practical importance of paying attention to team-level states and processes such as team goal orientation and team procrastination.

X-33 Reusable Launch Vehicle Demonstrator, Spaceport and Range

NASA Technical Reports Server (NTRS)

Letchworth, Gary F.

2011-01-01

The X-33 was a suborbital reusable spaceplane demonstrator, in development from 1996 to early 2001. The intent of the demonstrator was to lower the risk of building and operating a full-scale reusable vehicle fleet. Reusable spaceplanes offered the potential to lower the cost of access to space by an order of magnitude, compared with conventional expendable launch vehicles. Although a cryogenic tank failure during testing ultimately led to the end of the effort, the X-33 team celebrated many successes during the development. This paper summarizes some of the accomplishments and milestones of this X-vehicle program, from the perspective of an engineer who was a member of the team throughout the development. X-33 Program accomplishments include rapid, flight hardware design, subsystem testing and fabrication, aerospike engine development and testing, Flight Operations Center and Operations Control Center ground systems design and construction, rapid Environmental Impact Statement NEPA process approval, Range development and flight plan approval for test flights, and full-scale system concept design and refinement. Lessons from the X-33 Program may have potential application to new RLV and other aerospace systems being developed a decade later.

SKYLAB IV - LAUNCH

NASA Image and Video Library

1973-11-27

S73-37285 (16 Nov. 1973) --- The Skylab 4/Saturn 1B space vehicle is launched from Pad B, Launch Complex 39, Kennedy Space Center, Florida, at 9:01:23 a.m. (EST), Friday, Nov. 16, 1973. Skylab 4 is the third and last of three scheduled manned Skylab missions. Aboard the Skylab 4 Command/Service Module were astronauts Gerald P. Carr, Edward G. Gibson and William R. Pogue. In addition to the CSM and its launch escape system, the Skylab 4 space vehicle consisted of the Saturn 1B first (S-1B) stage and the Saturn 1B second (S-IVB) stage. (The Skylab 1/Saturn V unmanned space vehicle with the space station payload was launched from Pad A on May 14, 1973). Photo credit: NASA

SKYLAB IV - LAUNCH

NASA Image and Video Library

1973-11-27

S73-37286 (16 Nov. 1973) --- The Skylab 4/Saturn 1B space vehicle is launched from Pad B, Launch Complex 39, Kennedy Space Center, Florida, at 9:01:23 a.m. (EST), Friday, Nov. 16, 1973. Skylab 4 is the third and last of three scheduled manned Skylab missions. Aboard the Skylab 4 Command/Service Module were astronauts Gerald P. Carr, Edward G. Gibson and William R. Pogue. In addition to the CSM and its launch escape system, the Skylab 4 space vehicle consisted of the Saturn 1B first (S-1B) stage and the Saturn 1B second (S-IVB) stage. (The Skylab 1/Saturn V unmanned space vehicle with the space station payload was launched from Pad A on May 14, 1973). Photo credit: NASA

Magnetic Launch Assist System Demonstration

NASA Technical Reports Server (NTRS)

1999-01-01

This Quick Time movie demonstrates the Magnetic Launch Assist system, previously referred to as the Magnetic Levitation (Maglev) system, for space launch using a 5 foot model of a reusable Bantam Class launch vehicle on a 50 foot track that provided 6-g acceleration and 6-g de-acceleration. Overcoming the grip of Earth's gravity is a supreme challenge for engineers who design rockets that leave the planet. Engineers at the Marshall Space Flight Center have developed and tested Magnetic Launch Assist technologies that could levitate and accelerate a launch vehicle along a track at high speeds before it leaves the ground. Using electricity and magnetic fields, a Magnetic Launch Assist system would drive a spacecraft along a horizontal track until it reaches desired speeds. A full-scale, operational track would be about 1.5-miles long and capable of accelerating a vehicle to 600 mph in 9.5 seconds. The major advantages of launch assist for NASA launch vehicles is that it reduces the weight of the takeoff, the landing gear, the wing size, and less propellant resulting in significant cost savings. The US Navy and the British MOD (Ministry of Defense) are planning to use magnetic launch assist for their next generation aircraft carriers as the aircraft launch system. The US Army is considering using this technology for launching target drones for anti-aircraft training.

Engine-Out Capabilities Assessment of Heavy Lift Launch Vehicles

NASA Technical Reports Server (NTRS)

Holladay, Jon; Baggett, Keithe; Thrasher, Chad; Bellamy, K. Scott; Feldman, Stuart

2012-01-01

Engine-out (EO) is a condition that might occur during flight due to the failure of one or more engines. Protection against this occurrence can be called engine-out capability (EOC) whereupon significantly improved loss of mission may occur, in addition to reduction in performance and increased cost. A standardized engine-out capability has not been studied exhaustively as it pertains to space launch systems. This work presents results for a specific vehicle design with specific engines, but also uniquely provides an approach to realizing the necessity of EOC for any launch vehicle system design. A derived top-level approach to engine-out philosophy for a heavy lift launch vehicle is given herein, based on an historical assessment of launch vehicle capabilities. The methodology itself is not intended to present a best path forward, but instead provides three parameters for assessment of a particular vehicle. Of the several parameters affected by this EOC, the three parameters of interest in this research are reliability (Loss of Mission (LOM) and Loss of Crew (LOC)), vehicle performance, and cost. The intent of this effort is to provide insight into the impacts of EO capability on these parameters. The effects of EOC on reliability, performance and cost are detailed, including how these important launch vehicle metrics can be combined to assess what could be considered overall launch vehicle affordability. In support of achieving the first critical milestone (Mission Concept Review) in the development of the Space Launch System (SLS), a team assessed two-stage, large-diameter vehicles that utilized liquid oxygen (LOX)-RP propellants in the First Stage and LOX/LH2 propellant in the Upper Stage. With multiple large thrust-class engines employed on the stages, engine-out capability could be a significant driver to mission success. It was determined that LOM results improve by a factor of five when assuming EOC for both Core Stage (CS) (first stage) and Upper Stage (US

NASA's Space Launch System Progress Report

NASA Technical Reports Server (NTRS)

May, Todd A.; Singer, Joan A.; Cook, Jerry R.; Lyles, Garry M.; Beaman, David E.

2012-01-01

Exploration beyond Earth orbit will be an enduring legacy for future generations, as it provides a platform for science and exploration that will define new knowledge and redefine known boundaries. NASA s Space Launch System (SLS) Program, managed at the Marshall Space Flight Center, is responsible for designing and developing the first exploration-class rocket since the Apollo Program s Saturn V that sent Americans to the Moon in the 1960s and 1970s. The SLS offers a flexible design that may be configured for the Orion Multi-Purpose Crew Vehicle with associated life-support equipment and provisions for long journeys or may be outfitted with a payload fairing that will accommodate flagship science instruments and a variety of high-priority experiments. Building on legacy systems, facilities, and expertise, the SLS will have an initial lift capability of 70 tonnes (t) in 2017 and will be evolvable to 130 t after 2021. While commercial launch vehicle providers service the International Space Station market, this capability will surpass all vehicles, past and present, providing the means to do entirely new missions, such as human exploration of Mars. Building on the foundation laid by over 50 years of human and scientific space flight and on the lessons learned from the Apollo, Space Shuttle, and Constellation Programs the SLS team is delivering both technical trade studies and business case analyses to ensure that the SLS architecture will be safe, affordable, reliable, and sustainable. This panel will address the planning and progress being made by NASA s SLS Program.

Launch Summary for 1979

NASA Technical Reports Server (NTRS)

Vostreys, R. W.

1980-01-01

Spacecraft launching for 1979 are identified and listed under the categories of (1) sounding rockets, and (2) artificial Earth satellites and space probes. The sounding rockets section includes a listing of the experiments, index of launch sites and tables of the meanings and codes used in the launch listing.

APOLLO VIII - LAUNCH - KSC

NASA Image and Video Library

1968-12-21

S68-56002 (21 Dec. 1968) --- The Apollo 8 (Spacecraft 103/Saturn 503) space vehicle is launched from Pad A, Launch Complex 39, Kennedy Space Center (KSC), at 7:51 a.m. (EST), Dec. 21, 1968. The crew of the Apollo 8 lunar orbit mission is astronauts Frank Borman, commander; James A. Lovell Jr., command module pilot; and William A. Anders, lunar module pilot. Apollo 8 was the first manned Saturn V launch. (F-ls 1/3 way from top of mobile launch tower.)

Russian Soyuz in Launch Position

NASA Technical Reports Server (NTRS)

2000-01-01

The Soyuz TM-31 launch vehicle is shown in the vertical position for its launch from Baikonur, carrying the first resident crew to the International Space Station. The Russian Soyuz launch vehicle is an expendable spacecraft that evolved out of the original Class A (Sputnik). From the early 1960s until today, the Soyuz launch vehicle has been the backbone of Russia's marned and unmanned space launch fleet. Today, the Soyuz launch vehicle is marketed internationally by a joint Russian/French consortium called STARSEM. As of August 2001, there have been ten Soyuz missions under the STARSEM banner.

Advanced transportation system studies. Technical area 2: Heavy lift launch vehicle development. Volume 2; Technical Results

NASA Technical Reports Server (NTRS)

1995-01-01

Sections 10 to 13 of the Advanced Transportation System Studies final report are included in this volume. Section 10 contains a copy of an executive summary that was prepared by Lockheed Space Operations Company (LSOC) to document their support to the TA-2 contract during the first-year period of performance of the contract, May 1992 through May 1993. LSOC participated on the TA-2 contract as part of the concurrent engineering launch system definition team, and provided outstanding heavy lift launch vehicle (HLLV) ground operations requirements and concept assessments for Lockheed Missiles and Space Company (LMSC) through an intercompany work transfer as well as providing specific HLLV ground operations assessments at the direction of NASA KSC through KSC funding that was routed to the TA-2 contract. Section 11 contains a copy of a vehicle-independent, launch system health management requirements assessment. The purpose of the assessment was to define both health management requirements and the associated interfaces between a generic advanced transportation system launch vehicle and all related elements of the entire transportation system, including the ground segment. Section 12 presents the major TA-2 presentations provided to summarize the significant results and conclusions that were developed over the course of the contract. Finally, Section 13 presents the design and assessment report on the first lunar outpost heavy lift launch vehicle.

STS-111/Endeavour/ISS UF2 Pre-Launch Activities: Launch with Playbacks

NASA Technical Reports Server (NTRS)

2002-01-01

This video of the preflight preparations for and launch of Space Shuttle Endeavour on STS-111 begins with a view of Endeavour on the launch pad. Additional launch pad views leading up to liftoff are interspersed with footage from the Firing Room at Kennedy Space Center, the crew's prelaunch activities, and inspection of the crew members in the White Room before boarding Endeavour. The crew is introduced by a narrator during the preflight banquet and suiting up, and a later clip shows them departing to the launch site. The crew consists of Commander Kenneth Cockrell, Pilot Paul Lockhart, Mission Specialists Philippe Perrin and Franklin Chang-Diaz, and the Expedition 5 crew of the International Space Station (ISS) (Commander Valery Korzun and Flight Engineers Peggy Whitsun and Sergei Treschev). The nozzles on Endeavour's Space Shuttle Main Engine (SSME) are swiveled before liftoff, and the launch is shown past the separation of the solid rocket boosters. After a brief clip from the Mission Control Center at Johnson Space Center, the following launch replays are shown: Beach Tracker, VAB, Pad A, Tower 1, UCS-15, Grandstand, Cocoa Beach DOAMS, Playalinda DOAMS, UCS-23, and OTV-070.

When Teams Fail to Self-Regulate: Predictors and Outcomes of Team Procrastination Among Debating Teams

PubMed Central

Van Hooft, Edwin A. J.; Van Mierlo, Heleen

2018-01-01

Models of team development have indicated that teams typically engage in task delay during the first stages of the team’s life cycle. An important question is to what extent this equally applies to all teams, or whether there is variation across teams in the amount of task delay. The present study introduces the concept of team procrastination as a lens through which we can examine whether teams collectively engage in unplanned, voluntary, and irrational delay of team tasks. Based on theory and research on self-regulation, team processes, and team motivation we developed a conceptual multilevel model of predictors and outcomes of team procrastination. In a sample of 209 student debating teams, we investigated whether and why teams engage in collective procrastination as a team, and what consequences team procrastination has in terms of team member well-being and team performance. The results supported the existence of team procrastination as a team-level construct that has some stability over time. The teams’ composition in terms of individual-level trait procrastination, as well as the teams’ motivational states (i.e., team learning goal orientation, team performance-approach goal orientation in interaction with team efficacy) predicted team procrastination. Team procrastination related positively to team members’ stress levels, especially for those low on trait procrastination. Furthermore, team procrastination had an indirect negative relationship with team performance, through teams’ collective stress levels. These findings add to the theoretical understanding of self-regulatory processes of teams, and highlight the practical importance of paying attention to team-level states and processes such as team goal orientation and team procrastination. PMID:29674991

Team Learning and Team Composition in Nursing

ERIC Educational Resources Information Center

Timmermans, Olaf; Van Linge, Roland; Van Petegem, Peter; Elseviers, Monique; Denekens, Joke

2011-01-01

Purpose: This study aims to explore team learning activities in nursing teams and to test the effect of team composition on team learning to extend conceptually an initial model of team learning and to examine empirically a new model of ambidextrous team learning in nursing. Design/methodology/approach: Quantitative research utilising exploratory…

Evolution of the Florida Launch Site Architecture: Embracing Multiple Customers, Enhancing Launch Opportunities

NASA Technical Reports Server (NTRS)

Colloredo, Scott; Gray, James A.

2011-01-01

The impending conclusion of the Space Shuttle Program and the Constellation Program cancellation unveiled in the FY2011 President's budget created a large void for human spaceflight capability and specifically launch activity from the Florida launch Site (FlS). This void created an opportunity to re-architect the launch site to be more accommodating to the future NASA heavy lift and commercial space industry. The goal is to evolve the heritage capabilities into a more affordable and flexible launch complex. This case study will discuss the FlS architecture evolution from the trade studies to select primary launch site locations for future customers, to improving infrastructure; promoting environmental remediation/compliance; improving offline processing, manufacturing, & recovery; developing range interface and control services with the US Air Force, and developing modernization efforts for the launch Pad, Vehicle Assembly Building, Mobile launcher, and supporting infrastructure. The architecture studies will steer how to best invest limited modernization funding from initiatives like the 21 st elSe and other potential funding.

Launch Services Safety Overview

NASA Technical Reports Server (NTRS)

Loftin, Charles E.

2008-01-01

NASA/KSC Launch Services Division Safety (SA-D) services include: (1) Assessing the safety of the launch vehicle (2) Assessing the safety of NASA ELV spacecraft (S/C) / launch vehicle (LV) interfaces (3) Assessing the safety of spacecraft processing to ensure resource protection of: - KSC facilities - KSC VAFB facilities - KSC controlled property - Other NASA assets (4) NASA personnel safety (5) Interfacing with payload organizations to review spacecraft for adequate safety implementation and compliance for integrated activities (6) Assisting in the integration of safety activities between the payload, launch vehicle, and processing facilities

Orion Launch

NASA Image and Video Library

2014-12-05

A Delta IV Heavy rocket lifts off from Space Launch Complex 37 at Cape Canaveral Air Force Station in Florida carrying NASA's Orion spacecraft on an unpiloted flight test to Earth orbit. Liftoff was at 7:05 a.m. EST. During the two-orbit, four-and-a-half hour mission, engineers will evaluate the systems critical to crew safety, the launch abort system, the heat shield and the parachute system.

Space Shuttle Discovery Launch

NASA Image and Video Library

2008-05-31

NASA Administrator, Michael Griffin watches the launch of the Space Shuttle Discovery (STS-124) from the Launch Control Center Saturday, May 31, 2008, at the Kennedy Space Center in Cape Canaveral, Fla. The Shuttle lifted off from launch pad 39A at 5:02 p.m. EDT. Photo Credit: (NASA/Bill Ingalls)

A member of the U.S. Women's World Cup Soccer Team poses with Lindsey, Currie and Clark

NASA Technical Reports Server (NTRS)

1999-01-01

A member of the U.S. Women's World Cup Soccer Team poses with Astronauts (from left) Steven W. Lindsey, Nancy Jane Currie and Laurel B. Clark. The team arrived at the Skid Strip at Cape Canaveral Air Station with First Lady Hillary Rodham Clinton to view the launch of Space Shuttle mission STS-93. Liftoff is scheduled for 12:36 a.m. EDT July 20. Much attention has been generated over the launch due to Commander Eileen M. Collins, the first woman to serve as commander of a Shuttle mission. The primary payload of the five-day mission is the Chandra X-ray Observatory, which will allow scientists from around the world to study some of the most distant, powerful and dynamic objects in the universe. The new telescope is 20 to 50 times more sensitive than any previous X-ray telescope and is expected to unlock the secrets of supernovae, quasars and black holes.

The Ceres S'COOL Project: Two Years After First Launch

NASA Technical Reports Server (NTRS)

Chambers, Lin H.; Young, David F.; Green, Carolyn J.; Haberer, Susan J.; Racel, Anne M.

2000-01-01

The idea for the Students' Cloud Observations OnLine (S'COOL) project as an outreach and education element of NASA's Clouds and the Earth's Radiant Energy System (CERES) research program was conceived in late 1996 during a conversation with a middle school science teacher. S'COOL was implemented in a series of increasingly developed test phases during 1997, as the launch of the first CERES instrument approached. Even before launch, the reception of the project in schools far exceeded expectations. After several delays the first instrument, on the Tropical Rainfall Measuring Mission (TRMM) spacecraft, was launched on Thanksgiving Day, 1997. Since the first launch, development and expansion of the project has continued with expectations for launch of Terra carrying two CERES instruments into a polar orbit in mid-1998. That launch is now expected in fall 1999, and will finally provide overflight of all participating schools. In two years, the project has grown from three initial test participants to over 300 schools now participating in 23 countries on five continents. Students from first grade through university level are involved (most participants are ages 10-15). S'COOL is also being used by a few education professors to teach about Internet use in the classroom. The project continues to grow through word of mouth, presentations at teacher workshops, and now increasingly through teachers who find it during web searches. Participants in the S'COOL project are part of the CERES validation team. They provide ground truth measurements at the time the CERES instrument flies over their location, to be compared with the retrieval of cloud properties by remote sensing from CERES. Quantities reported include cloud type, height, fraction and opacity; information on contrails; surface temperature, pressure and relative humidity; and ground cover (snow/ice, wet, dry; leaves on trees or not). in addition, a comment field on the report form serves as a catch-all for all kinds

KSC Vertical Launch Site Evaluation

NASA Technical Reports Server (NTRS)

Phillips, Lynne V.

2007-01-01

RS&H was tasked to evaluate the potential available launch sites for a combined two user launch pad. The Launch sites were to be contained entirely within current Kennedy Space Center property lines. The user launch vehicles to be used for evaluation are in the one million pounds of first stage thrust range. Additionally a second evaluation criterion was added early on in the study. A single user launch site was to be evaluated for a two million pound first stage thrust vehicle. Both scenarios were to be included in the report. To provide fidelity to the study criteria, a specific launch vehicle in the one million pound thrust range was chosen as a guide post or straw-man launch vehicle. The RpK K-1 vehicle is a current Commercial Orbital Transportation System (COTS), contract awardee along with the SpaceX Falcon 9 vehicle. SpaceX, at the time of writing, is planning to launch COTS and possibly other payloads from Cx-40 on Cape Canaveral Air Force Station property. RpK has yet to declare a specific launch site as their east coast US launch location. As such it was deemed appropriate that RpK's vehicle requirements be used as conceptual criteria. For the purposes of this study those criteria were marginally generalized to make them less specifiC.

Voyager 1's Launch Vehicle

NASA Image and Video Library

1977-09-05

The Titan/Centaur-6 launch vehicle was moved to Launch Complex 41 at Kennedy Space Center in Florida to complete checkout procedures in preparation for launch. The photo is dated January 1977. This launch vehicle carried Voyager 1 into space on September 5, 1977. https://photojournal.jpl.nasa.gov/catalog/PIA21739

14 CFR § 1214.117 - Launch and orbit parameters for a standard launch.

Code of Federal Regulations, 2014 CFR

2014-01-01

... flights: (1) Launch from Kennedy Space Center (KSC) into the customer's choice of two standard mission... 14 Aeronautics and Space 5 2014-01-01 2014-01-01 false Launch and orbit parameters for a standard launch. § 1214.117 Section § 1214.117 Aeronautics and Space NATIONAL AERONAUTICS AND SPACE...

ARES I-X Launch

NASA Image and Video Library

2009-10-27

NASA Ares I-X Launch Director Ed Mango, left, laughs as NASA Ares I-X Assistant Launch Director Pete Nickolenko looks out the window of Firing Room One of the Launch Control Center (LCC) at the Kennedy Space Center prior to the launch of the Ares I-X rocket from pad 39b at the Kennedy Space Center in Cape Canaveral, Fla., Wednesday, Oct. 28, 2009. The flight test of Ares I-X will provide NASA with an early opportunity to test and prove flight characteristics, hardware, facilities and ground operations associated with the Ares I. Photo Credit: (NASA/Bill Ingalls)

Perspective: a business school view of medical interprofessional rounds: transforming rounding groups into rounding teams.

PubMed

Bharwani, Aleem M; Harris, G Chad; Southwick, Frederick S

2012-12-01

An effective interprofessional medical team can efficiently coordinate health care providers to achieve the collective outcome of improving each patient's health. To determine how current teams function, four groups of business students independently observed interprofessional work rounds on four different internal medicine services in a typical academic hospital and also interviewed the participants. In all instances, caregivers had formed working groups rather than working teams. Participants consistently exhibited parallel interdependence (individuals working alone and assuming their work would be coordinated with other caregivers) rather than reciprocal interdependence (individuals working together to actively coordinate patient care), the hallmark of effective teams. With one exception, the organization was hierarchical, with the senior attending physician possessing the authority. The interns exclusively communicated with the attending physician in one-on-one conversations that excluded all other members of the team. Although nurses and pharmacists were often present, they never contributed their ideas and rarely spoke.The authors draw on these observations to form recommendations for enhancing interprofessional rounding teams. These are to include the bedside nurse, pharmacist, and case manager as team members, begin with a formal team launch that encourages active participation by all team members, use succinct communication protocols, conduct work rounds in a quiet, distraction-free environment, have teams remain together for longer durations, and receive teamwork training and periodic coaching. High-performing businesses have effectively used teams for decades to achieve their goals, and health care professionals should follow this example.

Small Space Launch: Origins & Challenges

NASA Astrophysics Data System (ADS)

Freeman, T.; Delarosa, J.

2010-09-01

The United States Space Situational Awareness capability continues to be a key element in obtaining and maintaining the high ground in space. Space Situational Awareness satellites are critical enablers for integrated air, ground and sea operations, and play an essential role in fighting and winning conflicts. The United States leads the world space community in spacecraft payload systems from the component level into spacecraft, and in the development of constellations of spacecraft. In the area of launch systems that support Space Situational Awareness, despite the recent development of small launch vehicles, the United States launch capability is dominated by an old, unresponsive and relatively expensive set of launchers in the Expandable, Expendable Launch Vehicles (EELV) platforms; Delta IV and Atlas V. The United States directed Air Force Space Command to develop the capability for operationally responsive access to space and use of space to support national security, including the ability to provide critical space capabilities in the event of a failure of launch or on-orbit capabilities. On 1 Aug 06, Air Force Space Command activated the Space Development & Test Wing (SDTW) to perform development, test and evaluation of Air Force space systems and to execute advanced space deployment and demonstration projects to exploit new concepts and technologies, and rapidly migrate capabilities to the warfighter. The SDTW charged the Launch Test Squadron (LTS) with the mission to develop the capability of small space launch, supporting government research and development space launches and missile defense target missions, with operationally responsive spacelift for Low-Earth-Orbit Space Situational Awareness assets as a future mission. This new mission created new challenges for LTS. The LTS mission tenets of developing space launches and missile defense target vehicles were an evolution from the squadrons previous mission of providing sounding rockets under the Rocket

Better team management--better team care?

PubMed

Shelley, P; Powney, B

1994-01-01

Team building should not be a 'bolt-on' extra, it should be a well planned, integrated part of developing teams and assisting their leaders. When asked to facilitate team building by a group of NHS managers we developed a framework which enabled individual members of staff to become more effective in the way they communicated with each other, their teams and in turn within the organization. Facing the challenge posed by complex organizational changes, staff were able to use 3 training days to increase and develop their awareness of the principles of teamwork, better team management, and how a process of leadership and team building could help yield better patient care.

14 CFR 420.30 - Launch site location review for permitted launch vehicles.

Code of Federal Regulations, 2010 CFR

2010-01-01

... AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION LICENSING LICENSE TO OPERATE A LAUNCH SITE Criteria and Information Requirements for Obtaining a License § 420.30 Launch site location review for...

14 CFR 420.30 - Launch site location review for permitted launch vehicles.

Code of Federal Regulations, 2011 CFR

2011-01-01

... AVIATION ADMINISTRATION, DEPARTMENT OF TRANSPORTATION LICENSING LICENSE TO OPERATE A LAUNCH SITE Criteria and Information Requirements for Obtaining a License § 420.30 Launch site location review for...

Reduction of Martian Sample Return Mission Launch Mass with Solar Sail Propulsion

NASA Technical Reports Server (NTRS)

Russell, Tiffany E.; Heaton, Andy F.; Young, Roy; Baysinger, Mike; Schnell, Andrew R.

2013-01-01

Solar sails have the potential to provide mass and cost savings for spacecraft traveling within the innter solar system. Companies like L'Garde have demonstrated sail manufacturability and various i-space development methods. The purpose of this study was to evaluate a current Mars sample return architecture and to determine how cost and mass would be reduced by incorporating a solar sail propulsion system. The team validated the design proposed by L'Garde, and scaled the design based on a trajectory analysis. Using the solar sail design reduced the required mass, eliminating one of the three launches required in the original architecture.

Reduction of Martian Sample Return Mission Launch Mass with Solar Sail Propulsion

NASA Technical Reports Server (NTRS)

Russell, Tiffany E.; Heaton, Andrew; Thomas, Scott; Thomas, Dan; Young, Roy; Baysinger, Mike; Capizzo, Pete; Fabisinski, Leo; Hornsby, Linda; Maples, Dauphne;

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.

Powering Exploration: The Ares I Crew Launch Vehicle and Ares V Cargo Launch Vehicle

NASA Technical Reports Server (NTRS)

Cook, Stephen A.

2008-01-01

The National Aeronautics and Space Administration (NASA)'s Constellation Program is depending on the Ares Projects to deliver the crew and cargo launch capabilities needed to send human explorers to the Moon and beyond. The Ares Projects continue to make progress toward design, component testing, and early flight testing of the Ares I crew launch vehicle, as well as early design work for Ares V cargo launch vehicle. Ares I and Ares V will form the core space launch capabilities the United States needs to continue its pioneering tradition as a spacefaring nation. This paper will discuss programmatic, design, fabrication, and testing progress toward building these new launch vehicles.

Team-Based Development of Medical Devices: An Engineering–Business Collaborative

PubMed Central

Eberhardt, Alan W.; Johnson, Ophelia L.; Kirkland, William B.; Dobbs, Joel H.; Moradi, Lee G.

2016-01-01

There is a global shift in the teaching methodology of science and engineering toward multidisciplinary, team-based processes. To meet the demands of an evolving technical industry and lead the way in engineering education, innovative curricula are essential. This paper describes the development of multidisciplinary, team-based learning environments in undergraduate and graduate engineering curricula focused on medical device design. In these programs, students actively collaborate with clinicians, professional engineers, business professionals, and their peers to develop innovative solutions to real-world problems. In the undergraduate senior capstone courses, teams of biomedical engineering (BME) and business students have produced and delivered numerous functional prototypes to satisfied clients. Pursuit of commercialization of devices has led to intellectual property (IP) disclosures and patents. Assessments have indicated high levels of success in attainment of student learning outcomes and student satisfaction with their undergraduate design experience. To advance these projects toward commercialization and further promote innovative team-based learning, a Master of Engineering (MEng) in Design and Commercialization was recently launched. The MEng facilitates teams of graduate students in engineering, life sciences, and business who engage in innovation-commercialization (IC) projects and coursework that take innovative ideas through research and development (R&D) to create marketable devices. The activities are structured with students working together as a “virtual company,” with targeted outcomes of commercialization (license agreements and new start-ups), competitive job placement, and/or career advancement. PMID:26902869

Team-Based Development of Medical Devices: An Engineering-Business Collaborative.

PubMed

Eberhardt, Alan W; Johnson, Ophelia L; Kirkland, William B; Dobbs, Joel H; Moradi, Lee G

2016-07-01

There is a global shift in the teaching methodology of science and engineering toward multidisciplinary, team-based processes. To meet the demands of an evolving technical industry and lead the way in engineering education, innovative curricula are essential. This paper describes the development of multidisciplinary, team-based learning environments in undergraduate and graduate engineering curricula focused on medical device design. In these programs, students actively collaborate with clinicians, professional engineers, business professionals, and their peers to develop innovative solutions to real-world problems. In the undergraduate senior capstone courses, teams of biomedical engineering (BME) and business students have produced and delivered numerous functional prototypes to satisfied clients. Pursuit of commercialization of devices has led to intellectual property (IP) disclosures and patents. Assessments have indicated high levels of success in attainment of student learning outcomes and student satisfaction with their undergraduate design experience. To advance these projects toward commercialization and further promote innovative team-based learning, a Master of Engineering (MEng) in Design and Commercialization was recently launched. The MEng facilitates teams of graduate students in engineering, life sciences, and business who engage in innovation-commercialization (IC) projects and coursework that take innovative ideas through research and development (R&D) to create marketable devices. The activities are structured with students working together as a "virtual company," with targeted outcomes of commercialization (license agreements and new start-ups), competitive job placement, and/or career advancement.

NASA Launch Services Program Overview

NASA Technical Reports Server (NTRS)

Higginbotham, Scott

2016-01-01

The National Aeronautics and Space Administration (NASA) has need to procure a variety of launch vehicles and services for its unmanned spacecraft. The Launch Services Program (LSP) provides the Agency with a single focus for the acquisition and management of Expendable Launch Vehicle (ELV) launch services. This presentation will provide an overview of the LSP and its organization, approach, and activities.

Military Interprofessional Health Care Teams: How USU is Working to Harness the Power of Collaboration.

PubMed

D'Angelo, Matthew R; Saperstein, Adam K; Seibert, Diane C; Durning, Steven J; Varpio, Lara

2016-11-01

Despite efforts to increase patient safety, hundreds of thousands of lives are lost each year to preventable health care errors. The Institute of Medicine and other organizations have recommended that facilitating effective interprofessional health care team work can help address this problem. While the concept of interprofessional health care teams is known, understanding and organizing effective team performance have proven to be elusive goals. Although considerable research has been conducted in the civilian sector, scholars have yet to extend research to the military context. Indeed, delivering the highest caliber of health care to our service men and women is vitally important. This commentary describes a new initiative as the Uniformed Services University of the Health Sciences aimed at researching the characteristics of successful military interprofessional teams and why those characteristics are important. It also describes the interprofessional education initiative that Uniformed Services University is launching to help optimize U.S. military health care. Reprint & Copyright © 2016 Association of Military Surgeons of the U.S.

Capabilities of the Materials Contamination Team at Marshall Space Flight Center

NASA Technical Reports Server (NTRS)

Burns, Howard; Albyn, Keith; Edwards, David; Boothe, Richard; Finchum, Charles; Finckenor, Miria

2003-01-01

The Materials Contamination Team at the Marshall Space Flight Center (MSFC) has been recognized for its contributions supporting the National Aeronautics and Space Administration (NASA) spacecraft development programs. These programs include the Reusable Solid Rocket Motor (RSRM), Chandra X-Ray Observatory, and the International Space Station (ISS). The Environmental Effects Group, with the Materials Contamination Team and the Space Environmental Effects Team has been an integral part of NASA's success by the testing, evaluation, and qualification of materials, hardware, and processes. This paper focuses on the capabilities of the Materials Contamination Team. The Materials Contamination Team's realm of responsibility includes establishing contamination control during all phases of hardware development, including design, manufacturing, assembly, test, transportation, launch site processing, on-orbit exposure, return, and refurbishment. The team continues its mission of reducing the risk of equipment failure due to molecular or particulate contamination. Contamination is a concern in the Space Shuttle with sensitive bond-lines and reactive fluid (liquid oxygen) compatibility as well as for spacecraft with sensitive optics, such as Hubble Space Telescope and Chandra X-ray Observatory. The Materials Contamination Team has a variety of facilities and instrumentation capable of contaminant detection, identification, and monitoring. The team addresses material applications dealing with environments, including production facilities, clean rooms, and on-orbit exposure. The optically stimulated electron emission (OSEE) system, the Ultraviolet (UV) fluorescence (UVF) surface contamination detection, and the Surface Optics Corporation 400 (SOC 400) portable hand-held Fourier Transform Infrared (FTIR) spectrometer are state-of-the-art tools for in-process molecular contamination detection. The team of engineers and technicians also develop contamination calibration standards

Launch Condition Deviations of Reusable Launch Vehicle Simulations in Exo-Atmospheric Zoom Climbs

NASA Technical Reports Server (NTRS)

Urschel, Peter H.; Cox, Timothy H.

2003-01-01

The Defense Advanced Research Projects Agency has proposed a two-stage system to deliver a small payload to orbit. The proposal calls for an airplane to perform an exo-atmospheric zoom climb maneuver, from which a second-stage rocket is launched carrying the payload into orbit. The NASA Dryden Flight Research Center has conducted an in-house generic simulation study to determine how accurately a human-piloted airplane can deliver a second-stage rocket to a desired exo-atmospheric launch condition. A high-performance, fighter-type, fixed-base, real-time, pilot-in-the-loop airplane simulation has been modified to perform exo-atmospheric zoom climb maneuvers. Four research pilots tracked a reference trajectory in the presence of winds, initial offsets, and degraded engine thrust to a second-stage launch condition. These launch conditions have been compared to the reference launch condition to characterize the expected deviation. At each launch condition, a speed change was applied to the second-stage rocket to insert the payload onto a transfer orbit to the desired operational orbit. The most sensitive of the test cases was the degraded thrust case, yielding second-stage launch energies that were too low to achieve the radius of the desired operational orbit. The handling qualities of the airplane, as a first-stage vehicle, have also been investigated.

Launch - STS-6 - KSC

NASA Image and Video Library

1983-04-12

S83-30222 (4 April 1983) --- The second reusable spacecraft in history successfully launches from Launch Pad 39A at 1:30:00:88 p.m. (EST) on April 4, 1983, and heads for its history making five-day mission in Earth orbit. The space shuttle Challenger, its two solid rocket boosters (SRB), and a new lightweight?external fuel tank were captured on film by an automatically-tripped camera in a protected station nearer to the launch pad than human beings are able to be at launch time. Onboard the spacecraft are astronauts Paul J. Wietz, Karol J. Bobko, Dr. Story Musgrave and Donald H. Peterson. Photo credit: NASA

Lockheed Martin Skunk Works Single Stage to Orbit/Reusable Launch Vehicle

NASA Technical Reports Server (NTRS)

1999-01-01

Lockheed Martin Skunk Works has compiled an Annual Performance Report of the X-33/RLV Program. This report consists of individual reports from all industry team members, as well as NASA team centers. This portion of the report is comprised of a status report of Lockheed Martin's contribution to the program. The following is a summary of the Lockheed Martin Centers involved and work reviewed under their portion of the agreement: (1) Lockheed Martin Skunk Works - Vehicle Development, Operations Development, X-33 and RLV Systems Engineering, Manufacturing, Ground Operations, Reliability, Maintainability/Testability, Supportability, & Special Analysis Team, and X-33 Flight Assurance; (2) Lockheed Martin Technical Operations - Launch Support Systems, Ground Support Equipment, Flight Test Operations, and RLV Operations Development Support; (3) Lockheed Martin Space Operations - TAEM and A/L Guidance and Flight Control Design, Evaluation of Vehicle Configuration, TAEM and A/L Dispersion Analysis, Modeling and Simulations, Frequency Domain Analysis, Verification and Validation Activities, and Ancillary Support; (4) Lockheed Martin Astronautics-Denver - Systems Engineering, X-33 Development; (5) Sanders - A Lockheed Martin Company - Vehicle Health Management Subsystem Progress, GSS Progress; and (6) Lockheed Martin Michoud Space Systems - X-33 Liquid Oxygen (LOX) Tank, Key Challenges, Lessons Learned, X-33/RLV Composite Technology, Reusable Cyrogenic Insulation (RCI) and Vehicle Health Monitoring, Main Propulsion Systems (MPS), Structural Testing, X-33 System Integration and Analysis, and Cyrogenic Systems Operations.

14 CFR 417.25 - Post launch report.

Code of Federal Regulations, 2012 CFR

2012-01-01

... 14 Aeronautics and Space 4 2012-01-01 2012-01-01 false Post launch report. 417.25 Section 417.25... TRANSPORTATION LICENSING LAUNCH SAFETY General and License Terms and Conditions § 417.25 Post launch report. (a) For a launch operator launching from a Federal launch range, a launch operator must file a post launch...

14 CFR 417.25 - Post launch report.

Code of Federal Regulations, 2014 CFR

2014-01-01

... 14 Aeronautics and Space 4 2014-01-01 2014-01-01 false Post launch report. 417.25 Section 417.25... TRANSPORTATION LICENSING LAUNCH SAFETY General and License Terms and Conditions § 417.25 Post launch report. (a) For a launch operator launching from a Federal launch range, a launch operator must file a post launch...

14 CFR 417.25 - Post launch report.

Code of Federal Regulations, 2010 CFR

2010-01-01

... 14 Aeronautics and Space 4 2010-01-01 2010-01-01 false Post launch report. 417.25 Section 417.25... TRANSPORTATION LICENSING LAUNCH SAFETY General and License Terms and Conditions § 417.25 Post launch report. (a) For a launch operator launching from a Federal launch range, a launch operator must file a post launch...

14 CFR 417.25 - Post launch report.

Code of Federal Regulations, 2011 CFR

2011-01-01

... 14 Aeronautics and Space 4 2011-01-01 2011-01-01 false Post launch report. 417.25 Section 417.25... TRANSPORTATION LICENSING LAUNCH SAFETY General and License Terms and Conditions § 417.25 Post launch report. (a) For a launch operator launching from a Federal launch range, a launch operator must file a post launch...

14 CFR 417.25 - Post launch report.

Code of Federal Regulations, 2013 CFR

2013-01-01

... 14 Aeronautics and Space 4 2013-01-01 2013-01-01 false Post launch report. 417.25 Section 417.25... TRANSPORTATION LICENSING LAUNCH SAFETY General and License Terms and Conditions § 417.25 Post launch report. (a) For a launch operator launching from a Federal launch range, a launch operator must file a post launch...

NASA's Space Launch Transitions: From Design to Production

NASA Technical Reports Server (NTRS)

Askins, Bruce; Robinson, Kimberly

2016-01-01

NASA's Space Launch System (SLS) successfully completed its Critical Design Review (CDR) in 2015, a major milestone on the journey to an unprecedented era of exploration for humanity. CDR formally marked the program's transition from design to production phase just four years after the program's inception and the first such milestone for a human launch vehicle in 40 years. While challenges typical of a complex development program lie ahead, CDR evaluators concluded that the design is technically and programmatically sound and ready to press forward to Design Certification Review (DCR) and readiness for launch of Exploration Mission 1 (EM-1) in the 2018 timeframe. SLS is prudently based on existing propulsion systems, infrastructure and knowledge with a clear, evolutionary path as required by mission needs. In its initial configuration, designated Block I, SLS will a minimum of 70 metric tons (t) of payload to low Earth orbit (LEO). It can evolve to a 130 t payload capacity by upgrading its engines, boosters, and upper stage, dramatically increasing the mass and volume of human and robotic exploration while decreasing mission risk, increasing safety, and simplifying ground and mission operations. CDR was the central programmatic accomplishment among many technical accomplishments that will be described in this paper. The government/industry SLS team successfully test fired a flight-like five-segment solid rocket motor, as well as seven hotfire development tests of the RS-25 core stage engine. The majority of the major test article and flight barrels, rings, and domes for the core stage liquid oxygen, liquid hydrogen, engine section, intertank, and forward skirt were manufactured at NASA's Michoud Assembly Facility. Renovations to the B-2 test stand for stage green run testing were completed at NASA Stennis Space Center. Core stage test stands are rising at NASA Marshall Space Flight Center. The modified Pegasus barge for core stage transportation from manufacturing

Evolved Expendable Launch Vehicle (EELV)

DTIC Science & Technology

2015-12-15

FY13+ Phase I Buy Contractor: United Launch Services, LLC Contractor Location: 9501 East Panorama Circle Centennial , CO 80112 Contract Number...Contract Name: FY13+ Phase I Buy Contractor: United Launch Services, LLC Contractor Location: 9501 East Panorama Circle Centennial , CO 80112 Contract...FY12 EELV Launch Services (ELS5) Contractor: United Launch Services, LLC. Contractor Location: 9501 East Panorama Circle Centennial , CO 80112

ARES I-X Launch Prep

NASA Image and Video Library

2009-10-26

NASA Ares I-X Assistant Launch Director Pete Nickolenko, left, and NASA Ares I-X Launch Director Ed Mango monitor the launch countdown from Firing Room One of the Launch Control Center (LCC) at the Kennedy Space Center during the planned launch of the Ares I-X rocket from pad 39b at the Kennedy Space Center in Cape Canaveral, Fla., Tuesday, Oct. 27, 2009. The flight test of Ares I-X will provide NASA with an early opportunity to test and prove flight characteristics, hardware, facilities and ground operations associated with the Ares I. Photo Credit: (NASA/Bill Ingalls)

Throttleable GOX/ABS launch assist hybrid rocket motor for small scale air launch platform

NASA Astrophysics Data System (ADS)

Spurrier, Zachary S.

Aircraft-based space-launch platforms allow operational flexibility and offer the potential for significant propellant savings for small-to-medium orbital payloads. The NASA Armstrong Flight Research Center's Towed Glider Air-Launch System (TGALS) is a small-scale flight research project investigating the feasibility for a remotely-piloted, towed, glider system to act as a versatile air launch platform for nano-scale satellites. Removing the crew from the launch vehicle means that the system does not have to be human rated, and offers a potential for considerable cost savings. Utah State University is developing a small throttled launch-assist system for the TGALS platform. This "stage zero" design allows the TGALS platform to achieve the required flight path angle for the launch point, a condition that the TGALS cannot achieve without external propulsion. Throttling is required in order to achieve and sustain the proper launch attitude without structurally overloading the airframe. The hybrid rocket system employs gaseous-oxygen and acrylonitrile butadiene styrene (ABS) as propellants. This thesis summarizes the development and testing campaign, and presents results from the clean-sheet design through ground-based static fire testing. Development of the closed-loop throttle control system is presented.

76 FR 52694 - National Environmental Policy Act: Launch of NASA Routine Payloads on Expendable Launch Vehicles

Federal Register 2010, 2011, 2012, 2013, 2014

2011-08-23

...: Launch of NASA Routine Payloads on Expendable Launch Vehicles AGENCY: National Aeronautics and Space Administration (NASA). ACTION: Notice of availability and request for comments on the draft environmental assessment (``Draft EA'') for launch of NASA routine payloads on expendable launch vehicles. SUMMARY...

Launch, Jupiter-C, Explorer 1

NASA Technical Reports Server (NTRS)

1958-01-01

Launch of Jupiter-C/Explorer 1 at Cape Canaveral, Florida on January 31, 1958. After the Russian Sputnik 1 was launched in October 1957, the launching of an American satellite assumed much greater importance. After the Vanguard rocket exploded on the pad in December 1957, the ability to orbit a satellite became a matter of national prestige. On January 31, 1958, slightly more than four weeks after the launch of Sputnik.The ABMA (Army Ballistic Missile Agency) in Redstone Arsenal, Huntsville, Alabama, in cooperation with the Jet Propulsion Laboratory, launched a Jupiter from Cape Canaveral, Florida. The rocket consisted of a modified version of the Redstone rocket's first stage and two upper stages of clustered Baby Sergeant rockets developed by the Jet Propulsion Laboratory and later designated as Juno boosters for space launches

Advanced small launch vehicle study

NASA Technical Reports Server (NTRS)

Reins, G. E.; Alvis, J. F.

1972-01-01

A conceptual design study was conducted to determine the most economical (lowest cost/launch) approach for the development of an advanced small launch vehicle (ASLV) for use over the next decade. The ASLV design objective was to place a 340 kg (750 lb) payload into a 556 km (300 n.mi.) circular orbit when launched due east from Wallops Island, Virginia. The investigation encompassed improvements to the current Scout launch vehicle; use of existing military and NASA launch vehicle stages; and new, optionally staged vehicles. Staging analyses included use of liquid, solid, and hybrid propellants. Improvements in guidance, controls, interstages, telemetry, and payload shroud were also considered. It was concluded that the most economical approach is to progressively improve the Scout launch vehicle in three phased steps which are discussed.

Apollo 4 launch

NASA Image and Video Library

1967-09-11

S67-50903 (9 Nov. 1967) --- The Apollo 4 (Spacecraft 017/Saturn 501) space mission was launched from Pad A, Launch Complex 39, Kennedy Space Center, Florida. The liftoff of the huge 363-feet tall Apollo/Saturn V space vehicle was at 7:00:01 a.m. (EST), Nov. 9, 1967. The successful objectives of the Apollo 4 Earth-orbital unmanned space mission obtained included (1) flight information on launch vehicle and spacecraft structural integrity and compatibility, flight loads, stage separation, subsystem operation, emergency detection subsystem, and (2) evaluation of the Apollo Command Module heat shield under conditions encountered on return from a moon mission.

Diffusion algorithms and data reduction routine for onsite real-time launch predictions for the transport of Delta-Thor exhaust effluents

NASA Technical Reports Server (NTRS)

Stephens, J. B.

1976-01-01

The National Aeronautics and Space Administration/Marshall Space Flight Center multilayer diffusion algorithms have been specialized for the prediction of the surface impact for the dispersive transport of the exhaust effluents from the launch of a Delta-Thor vehicle. This specialization permits these transport predictions to be made at the launch range in real time so that the effluent monitoring teams can optimize their monitoring grids. Basically, the data reduction routine requires only the meteorology profiles for the thermodynamics and kinematics of the atmosphere as an input. These profiles are graphed along with the resulting exhaust cloud rise history, the centerline concentrations and dosages, and the hydrogen chloride isopleths.

Report of the Space Shuttle Management Independent Review Team

NASA Technical Reports Server (NTRS)

1995-01-01

At the request of the NASA Administrator a team was formed to review the Space Shuttle Program and propose a new management system that could significantly reduce operating costs. Composed of a group of people with broad and extensive experience in spaceflight and related areas, the team received briefings from the NASA organizations and most of the supporting contractors involved in the Shuttle Program. In addition, a number of chief executives from the supporting contractors provided advice and suggestions. The team found that the present management system has functioned reasonably well despite its diffuse structure. The team also determined that the shuttle has become a mature and reliable system, and--in terms of a manned rocket-propelled space launch system--is about as safe as today's technology will provide. In addition, NASA has reduced shuttle operating costs by about 25 percent over the past 3 years. The program, however, remains in a quasi-development mode and yearly costs remain higher than required. Given the current NASA-contractor structure and incentives, it is difficult to establish cost reduction as a primary goal and implement changes to achieve efficiencies. As a result, the team sought to create a management structure and associated environment that enables and motivates the Program to further reduce operational costs. Accordingly, the review team concluded that the NASA Space Shuttle Program should (1) establish a clear set of program goals, placing a greater emphasis on cost-efficient operations and user-friendly payload integration; (2) redefine the management structure, separating development and operations and disengaging NASA from the daily operation of the space shuttle; and (3) provide the necessary environment and conditions within the program to pursue these goals.

Report of the Space Shuttle Management Independent Review Team

NASA Astrophysics Data System (ADS)

1995-02-01

At the request of the NASA Administrator a team was formed to review the Space Shuttle Program and propose a new management system that could significantly reduce operating costs. Composed of a group of people with broad and extensive experience in spaceflight and related areas, the team received briefings from the NASA organizations and most of the supporting contractors involved in the Shuttle Program. In addition, a number of chief executives from the supporting contractors provided advice and suggestions. The team found that the present management system has functioned reasonably well despite its diffuse structure. The team also determined that the shuttle has become a mature and reliable system, and--in terms of a manned rocket-propelled space launch system--is about as safe as today's technology will provide. In addition, NASA has reduced shuttle operating costs by about 25 percent over the past 3 years. The program, however, remains in a quasi-development mode and yearly costs remain higher than required. Given the current NASA-contractor structure and incentives, it is difficult to establish cost reduction as a primary goal and implement changes to achieve efficiencies. As a result, the team sought to create a management structure and associated environment that enables and motivates the Program to further reduce operational costs. Accordingly, the review team concluded that the NASA Space Shuttle Program should (1) establish a clear set of program goals, placing a greater emphasis on cost-efficient operations and user-friendly payload integration; (2) redefine the management structure, separating development and operations and disengaging NASA from the daily operation of the space shuttle; and (3) provide the necessary environment and conditions within the program to pursue these goals.

MAVEN Atlas V Launch

NASA Image and Video Library

2013-11-18

The United Launch Alliance Atlas V rocket with NASA’s Mars Atmosphere and Volatile EvolutioN (MAVEN) spacecraft launches from the Cape Canaveral Air Force Station Space Launch Complex 41, Monday, Nov. 18, 2013, Cape Canaveral, Florida. NASA’s Mars-bound spacecraft, the Mars Atmosphere and Volatile EvolutioN, or MAVEN, is the first spacecraft devoted to exploring and understanding the Martian upper atmosphere. Photo Credit: (NASA/Bill Ingalls)

14 CFR 417.125 - Launch of an unguided suborbital launch vehicle.

Code of Federal Regulations, 2010 CFR

2010-01-01

... elevation angle setting that ensures the rocket will not fly uprange. A launch operator must set the... throughout each stage of powered flight. A caliber, for a rocket configuration, is defined as the distance... rocket configuration. (f) Tracking. A launch operator must track the flight of an unguided suborbital...

14 CFR 417.125 - Launch of an unguided suborbital launch vehicle.

Code of Federal Regulations, 2013 CFR

2013-01-01

... elevation angle setting that ensures the rocket will not fly uprange. A launch operator must set the... throughout each stage of powered flight. A caliber, for a rocket configuration, is defined as the distance... rocket configuration. (f) Tracking. A launch operator must track the flight of an unguided suborbital...

14 CFR 417.125 - Launch of an unguided suborbital launch vehicle.

Code of Federal Regulations, 2012 CFR

2012-01-01

... elevation angle setting that ensures the rocket will not fly uprange. A launch operator must set the... throughout each stage of powered flight. A caliber, for a rocket configuration, is defined as the distance... rocket configuration. (f) Tracking. A launch operator must track the flight of an unguided suborbital...

14 CFR 417.125 - Launch of an unguided suborbital launch vehicle.

Code of Federal Regulations, 2011 CFR

2011-01-01

... elevation angle setting that ensures the rocket will not fly uprange. A launch operator must set the... throughout each stage of powered flight. A caliber, for a rocket configuration, is defined as the distance... rocket configuration. (f) Tracking. A launch operator must track the flight of an unguided suborbital...

14 CFR 417.125 - Launch of an unguided suborbital launch vehicle.

Code of Federal Regulations, 2014 CFR

2014-01-01

... elevation angle setting that ensures the rocket will not fly uprange. A launch operator must set the... throughout each stage of powered flight. A caliber, for a rocket configuration, is defined as the distance... rocket configuration. (f) Tracking. A launch operator must track the flight of an unguided suborbital...

Making Teamwork Work: Team Knowledge for Team Effectiveness.

PubMed

Guchait, Priyanko; Lei, Puiwa; Tews, Michael J

2016-01-01

This study examined the impact of two types of team knowledge on team effectiveness. The study assessed the impact of taskwork knowledge and teamwork knowledge on team satisfaction and performance. A longitudinal study was conducted with 27 service-management teams involving 178 students in a real-life restaurant setting. Teamwork knowledge was found to impact both team outcomes. Furthermore, team learning behavior was found to mediate the relationships between teamwork knowledge and team outcomes. Educators and managers should therefore ensure these types of knowledge are developed in teams along with learning behavior for maximum effectiveness.

Liftoff and Transition Aerodynamics of the Ares I (A106) Launch Vehicle

NASA Technical Reports Server (NTRS)

Capone, Francis J.; Paulson, John W., Jr.; Erickson, Gary E.

2011-01-01

An investigation has been conducted in the NASA Langley Research Center 14- by 22- Foot Subsonic Wind Tunnel to obtain the liftoff and transition aerodynamics of the Ares I (A106) Crew Launch Vehicle. Data were obtained in free-air at angles of attack from 10 to 90 at various roll angles and at roll angles of 0 to 360 at various angles of attack. In addition, tower effects were assessed by testing with and without a mobile launcher/tower at all wind azimuth angles and at various model heights to simulate the rise of the vehicle as it clears the tower on launch. The free-air data will be used for low speed high angle of attack flight simulation and as a bridge to the low angle of attack ascent database (0.5 < Mach < 5.0) being developed with data from the Langley Unitary Plan Wind Tunnel and Boeing Polysonic Wind Tunnel. The Ares I Database Development Team will add incremental tower effects data to the free-air data to develop the database for tower clearance.

Team Cognition in Experienced Command-and-Control Teams

ERIC Educational Resources Information Center

Cooke, Nancy J.; Gorman, Jamie C.; Duran, Jasmine L.; Taylor, Amanda R.

2007-01-01

Team cognition in experienced command-and-control teams is examined in an UAV (Uninhabited Aerial Vehicle) simulation. Five 3-person teams with experience working together in a command-and-control setting were compared to 10 inexperienced teams. Each team participated in five 40-min missions of a simulation in which interdependent team members…

NASA Team Collaboration Pilot: Enabling NASA's Virtual Teams

NASA Technical Reports Server (NTRS)

Prahst, Steve

2003-01-01

Most NASA projects and work activities are accomplished by teams of people. These teams are often geographically distributed - across NASA centers and NASA external partners, both domestic and international. NASA "virtual" teams are stressed by the challenge of getting team work done - across geographic boundaries and time zones. To get distributed work done, teams rely on established methods - travel, telephones, Video Teleconferencing (NASA VITS), and email. Time is our most critical resource - and team members are hindered by the overhead of travel and the difficulties of coordinating work across their virtual teams. Modern, Internet based team collaboration tools offer the potential to dramatically improve the ability of virtual teams to get distributed work done.

Ivins examines Destiny with the processing team in the SSPF

NASA Technical Reports Server (NTRS)

1999-01-01

In the Space Station Processing Facility, Marsha Ivins, a mission specialist on the STS-98 crew, inspects the U.S. Laboratory with members of the laboratory's processing team. The laboratory module, considered the centerpiece of the International Space Station (ISS), has been named 'Destiny' in honor of its prominent role in the world's largest science and technology effort. It is planned for launch aboard Space Shuttle Endeavour on the sixth ISS construction flight currently targeted for March 2000. From left to right are Ivins, Jerry Hopkins, Danny Whittington, Melissa Orozco, Vicki Reese and Suzanne Fase.

Ivins examines Destiny with the processing team in the SSPF

NASA Technical Reports Server (NTRS)

1999-01-01

In the Space Station Processing Facility, Marsha Ivins, a mission specialist on the STS-98 crew, inspects the U.S. Laboratory with members of the laboratory's processing team. The laboratory module, considered the centerpiece of the International Space Station (ISS), has been named 'Destiny' in honor of its prominent role in the world's largest science and technology effort. It is planned for launch aboard Space Shuttle Endeavour on the sixth ISS construction flight currently targeted for March 2000. From left to right are Ivins, Jerry Hopkins, Danny Whittington, Melissa Orozco, and Suzanne Fase.

Ivins examines Destiny with the processing team in the SSPF

NASA Technical Reports Server (NTRS)

1999-01-01

In the Space Station Processing Facility, Marsha Ivins (left), a mission specialist on the STS-98 crew, discusses the U.S. Laboratory with members of the laboratory's processing team, (left to right) James Thews, Suzanne Fase, and Danny Whittington. The laboratory module, considered the centerpiece of the International Space Station (ISS), has been named 'Destiny' in honor of its prominent role in the world's largest science and technology effort. It is planned for launch aboard Space Shuttle Endeavour on the sixth ISS construction flight currently targeted for March 2000.

Investigating Team Coordination in Baseball Using a Novel Joint Decision Making Paradigm

PubMed Central

Gray, Rob; Cooke, Nancy J.; McNeese, Nathan J.; McNabb, Jaimie

2017-01-01

A novel joint decision making paradigm for assessing team coordination was developed and tested using baseball infielders. Balls launched onto an infield at different trajectories were filmed using four video cameras that were each placed at one of the typical positions of the four infielders. Each participant viewed temporally occluded videos for one of the four positions and were asked to say either “ball” if they would attempt to field it or the name of the bag that they would cover. The evaluation of two experienced coaches was used to assign a group coordination score for each trajectory and group decision times were calculated. Thirty groups of 4 current college baseball players were: (i) teammates (players from same team/view from own position), (ii) non-teammates (players from different teams/view from own position), or (iii) scrambled teammates (players from same team/view not from own position). Teammates performed significantly better (i.e., faster and more coordinated decisions) than the other two groups, whereas scrambled teammates performed significantly better than non-teammates. These findings suggest that team coordination is achieved through both experience with one’s teammates’ responses to particular events (e.g., a ball hit up the middle) and one’s own general action capabilities (e.g., running speed). The sensitivity of our joint decision making paradigm to group makeup provides support for its use as a method for studying team coordination. PMID:28638354

Dawn Orbit Determination Team: Trajectory and Gravity Prediction Performance During Vesta Science Phases

NASA Technical Reports Server (NTRS)

Kennedy, Brian; Abrahamson, Matt; Ardito, Alessandro; Han, Dongsuk; Haw, Robert; Mastrodemos, Nicholas; Nandi, Sumita; Park, Ryan; Rush, Brian; Vaughan, Andrew

2013-01-01

The Dawn spacecraft was launched on September 27th, 2007. Its mission is to consecutively rendezvous with and observe the two largest bodies in the asteroid belt, Vesta and Ceres. It has already completed over a year's worth of direct observations of Vesta (spanning from early 2011 through late 2012) and is currently on a cruise trajectory to Ceres, where it will begin scientific observations in mid-2015. Achieving this data collection required careful planning and execution from all spacecraft teams. Dawn's Orbit Determination (OD) team was tasked with accurately predicting the trajectory of the Dawn spacecraft during the Vesta science phases, and also determining the parameters of Vesta to support future science orbit design. The future orbits included the upcoming science phase orbits as well as the transfer orbits between science phases. In all, five science phases were executed at Vesta, and this paper will describe some of the OD team contributions to the planning and execution of those phases.

U.S. advanced launch vehicle technology programs : Quarterly Launch Report : special report

DOT National Transportation Integrated Search

1996-01-01

U.S. firms and U.S. government agencies are jointly investing in advanced launch vehicle technology. This Special Report summarizes U.S. launch vehicle technology programs and highlights the changing : roles of government and industry players in pick...

New Horizons Launch Contingency Effort

NASA Astrophysics Data System (ADS)

Chang, Yale; Lear, Matthew H.; McGrath, Brian E.; Heyler, Gene A.; Takashima, Naruhisa; Owings, W. Donald

2007-01-01

On 19 January 2006 at 2:00 PM EST, the NASA New Horizons spacecraft (SC) was launched from the Cape Canaveral Air Force Station (CCAFS), FL, onboard an Atlas V 551/Centaur/STAR™ 48B launch vehicle (LV) on a mission to explore the Pluto Charon planetary system and possibly other Kuiper Belt Objects. It carried a single Radioisotope Thermoelectric Generator (RTG). As part of the joint NASA/US Department of Energy (DOE) safety effort, contingency plans were prepared to address the unlikely events of launch accidents leading to a near-pad impact, a suborbital reentry, an orbital reentry, or a heliocentric orbit. As the implementing organization. The Johns Hopkins University Applied Physics Laboratory (JHU/APL) had expanded roles in the New Horizons launch contingency effort over those for the Cassini mission and Mars Exploration Rovers missions. The expanded tasks included participation in the Radiological Control Center (RADCC) at the Kennedy Space Center (KSC), preparation of contingency plans, coordination of space tracking assets, improved aerodynamics characterization of the RTG's 18 General Purpose Heat Source (GPHS) modules, and development of spacecraft and RTG reentry breakup analysis tools. Other JHU/APL tasks were prediction of the Earth impact footprints (ElFs) for the GPHS modules released during the atmospheric reentry (for purposes of notification and recovery), prediction of the time of SC reentry from a potential orbital decay, pre-launch dissemination of ballistic coefficients of various possible reentry configurations, and launch support of an Emergency Operations Center (EOC) on the JHU/APL campus. For the New Horizons launch, JHU/APL personnel at the RADCC and at the EOC were ready to implement any real-time launch contingency activities. A successful New Horizons launch and interplanetary injection precluded any further contingency actions. The New Horizons launch contingency was an interagency effort by several organizations. This paper

Magnetic Launch Assist Demonstration Test

NASA Technical Reports Server (NTRS)

2001-01-01

This image shows a 1/9 subscale model vehicle clearing the Magnetic Launch Assist System, formerly referred to as the Magnetic Levitation (MagLev), test track during a demonstration test conducted at the Marshall Space Flight Center (MSFC). Engineers at MSFC have developed and tested Magnetic Launch Assist technologies. To launch spacecraft into orbit, a Magnetic Launch Assist System would use magnetic fields to levitate and accelerate a vehicle along a track at very high speeds. Similar to high-speed trains and roller coasters that use high-strength magnets to lift and propel a vehicle a couple of inches above a guideway, a launch-assist system would electromagnetically drive a space vehicle along the track. A full-scale, operational track would be about 1.5-miles long and capable of accelerating a vehicle to 600 mph in 9.5 seconds. This track is an advanced linear induction motor. Induction motors are common in fans, power drills, and sewing machines. Instead of spinning in a circular motion to turn a shaft or gears, a linear induction motor produces thrust in a straight line. Mounted on concrete pedestals, the track is 100-feet long, about 2-feet wide and about 1.5-feet high. The major advantages of launch assist for NASA launch vehicles is that it reduces the weight of the take-off, the landing gear, the wing size, and less propellant resulting in significant cost savings. The US Navy and the British MOD (Ministry of Defense) are planning to use magnetic launch assist for their next generation aircraft carriers as the aircraft launch system. The US Army is considering using this technology for launching target drones for anti-aircraft training.

Launch Vehicles

NASA Image and Video Library

1961-01-01

This is a comparison illustration of the Redstone, Jupiter-C, and Mercury Redstone launch vehicles. The Redstone ballistic missile was a high-accuracy, liquid-propelled, surface-to-surface missile. Originally developed as a nose cone re-entry test vehicle for the Jupiter intermediate range ballistic missile, the Jupiter-C was a modification of the Redstone missile and successfully launched the first American Satellite, Explorer-1, in orbit on January 31, 1958. The Mercury Redstone lifted off carrying the first American, astronaut Alan Shepard, in his Mercury spacecraft Freedom 7, on May 5, 1961.

Bulk-buy practices by satellite operators foster further commercialization of launch services industry : Quarterly Launch Report : special report

DOT National Transportation Integrated Search

1997-01-01

The satellite launch industry has steadily grown and matured to take on the features of a truly commercial industry. This year, commercial launches outnumber government launches for the first time. New launch systems, such as the Delta 3, Sea Launch,...

STS-135 Atlantis Launch

NASA Image and Video Library

2011-07-07

NASA Administrator Charles Bolden speaks to visitors at the NASA Kennedy Space Center Banana Creek viewing site prior to going to the Launch Control Center (LCC) for the planned launch of the space shuttle Atlantis from pad 39A on Friday, July 8, 2011, in Cape Canaveral, Fla. The launch of Atlantis, STS-135, is the final flight of the shuttle program, a 12-day mission to the International Space Station. Photo Credit: (NASA/Bill Ingalls)

Antares Rocket Test Launch

NASA Image and Video Library

2013-04-21

The Orbital Sciences Corporation Antares rocket is seen as it launches from Pad-0A of the Mid-Atlantic Regional Spaceport (MARS) at the NASA Wallops Flight Facility in Virginia, Sunday, April 21, 2013. The test launch marked the first flight of Antares and the first rocket launch from Pad-0A. The Antares rocket delivered the equivalent mass of a spacecraft, a so-called mass simulated payload, into Earth's orbit. Photo Credit: (NASA/Bill Ingalls)

Launching Garbage-Bag Balloons.

ERIC Educational Resources Information Center

Kim, Hy

1997-01-01

Presents a modification of a procedure for making and launching hot air balloons made out of garbage bags. Student instructions for balloon construction, launching instructions, and scale diagrams are included. (DDR)

Team behaviors: working effectively in teams.

PubMed

Wilson, C K

1998-12-01

The work of building and sustaining teams is often underestimated by middle managers. A manager must have the ability to develop and evolve staff toward a new level of competence, required because of radically upgraded expectations. Managers must be clear about what it means to empower teams, to avoid the trappings of giving "lip service" to authority boundaries, which may exist only on paper. Achieving this clarity means understanding the characteristics of effective teams: a high degree of interdependence, strong sense of organizational empowerment, self-determination, competence, commitment, and genuine concern about the quality of work being performed. An important tool for the manager interested in team development is the creation of a performance model, grounded in the foundational relationship competencies necessary for team success. Performance modeling assists not only in identifying of competency gaps that can be addressed by training but also in determining the workplace barriers to team success.

Russian Soyuz Moves to Launch Pad

NASA Technical Reports Server (NTRS)

2000-01-01

The Soyuz TM-31 launch vehicle, which carried the first resident crew to the International Space Station, moves toward the launch pad at the Baikonur complex in Kazakhstan. The Russian Soyuz launch vehicle is an expendable spacecraft that evolved out of the original Class A (Sputnik). From the early 1960' until today, the Soyuz launch vehicle has been the backbone of Russia's marned and unmanned space launch fleet. Today, the Soyuz launch vehicle is marketed internationally by a joint Russian/French consortium called STARSEM. As of August 2001, there have been ten Soyuz missions under the STARSEM banner.

Magnetic Launch Assist System-Artist's Concept

NASA Technical Reports Server (NTRS)

1999-01-01

This illustration is an artist's concept of a Magnetic Launch Assist System, formerly referred as the Magnetic Levitation (Maglev) system, for space launch. Overcoming the grip of Earth's gravity is a supreme challenge for engineers who design rockets that leave the planet. Engineers at the Marshall Space Flight Center have developed and tested Magnetic Launch Assist System technologies that could levitate and accelerate a launch vehicle along a track at high speeds before it leaves the ground. Using electricity and magnetic fields, a Magnetic Launch Assist system would drive a spacecraft along a horizontal track until it reaches desired speeds. A full-scale, operational track would be about 1.5-miles long and capable of accelerating a vehicle to 600 mph in 9.5 seconds. The major advantages of launch assist for NASA launch vehicles is that it reduces the weight of the take-off, landing gear and the wing size, as well as the elimination of propellant weight resulting in significant cost savings. The US Navy and the British MOD (Ministry of Defense) are planning to use magnetic launch assist for their next generation aircraft carriers as the aircraft launch system. The US Army is considering using this technology for launching target drones for anti-aircraft training.

Antares Rocket Test Launch

NASA Image and Video Library

2013-04-21

NASA Deputy Administrator Lori Garver and other guests react after having watched the successful launch of the Orbital Sciences Corporation Antares rocket from the Mid-Atlantic Regional Spaceport (MARS) at the NASA Wallops Flight Facility in Virginia, Sunday, April 21, 2013. The test launch marked the first flight of Antares and the first rocket launch from Pad-0A. The Antares rocket delivered the equivalent mass of a spacecraft, a so-called mass simulated payload, into Earth's orbit. Photo Credit: (NASA/Bill Ingalls)

Aquarius SAC-D Launch

NASA Image and Video Library

2011-06-10

A Delta II rocket launches with the Aquarius/SAC-D spacecraft payload from Space Launch Complex 2 at Vandenberg Air Force Base, Calif. on Friday, June 10, 2011. The joint U.S./Argentinian Aquarius/Satélite de Aplicaciones Científicas (SAC)-D mission, set to launch June 10, will map the salinity at the ocean surface, information critical to improving our understanding of two major components of Earth's climate system: the water cycle and ocean circulation. Photo Credit: (NASA/Bill Ingalls)

InSight Launch

NASA Image and Video Library

2018-05-05

The NASA InSight spacecraft launches onboard a United Launch Alliance Atlas-V rocket, Saturday, May 5, 2018, from Vandenberg Air Force Base in California. InSight, short for Interior Exploration using Seismic Investigations, Geodesy and Heat Transport, is a Mars lander designed to study the "inner space" of Mars: its crust, mantle, and core. Photo Credit: (NASA/Bill Ingalls)

Magnetic Launch Assist Vehicle-Artist's Concept

NASA Technical Reports Server (NTRS)

1999-01-01

This artist's concept depicts a Magnetic Launch Assist vehicle clearing the track and shifting to rocket engines for launch into orbit. The system, formerly referred as the Magnetic Levitation (MagLev) system, is a launch system developed and tested by Engineers at the Marshall Space Flight Center (MSFC) that could levitate and accelerate a launch vehicle along a track at high speeds before it leaves the ground. Using an off-board electric energy source and magnetic fields, a Magnetic Launch Assist system would drive a spacecraft along a horizontal track until it reaches desired speeds. The system is similar to high-speed trains and roller coasters that use high-strength magnets to lift and propel a vehicle a couple of inches above a guideway. A full-scale, operational track would be about 1.5-miles long, capable of accelerating a vehicle to 600 mph in 9.5 seconds, and the vehicle would then shift to rocket engines for launch into orbit. The major advantages of launch assist for NASA launch vehicles is that it reduces the weight of the take-off, the landing gear, the wing size, and less propellant resulting in significant cost savings. The US Navy and the British MOD (Ministry of Defense) are planning to use magnetic launch assist for their next generation aircraft carriers as the aircraft launch system. The US Army is considering using this technology for launching target drones for anti-aircraft training.

Explosion/Blast Dynamics for Constellation Launch Vehicles Assessment

NASA Technical Reports Server (NTRS)

Baer, Mel; Crawford, Dave; Hickox, Charles; Kipp, Marlin; Hertel, Gene; Morgan, Hal; Ratzel, Arthur; Cragg, Clinton H.

2009-01-01

An assessment methodology is developed to guide quantitative predictions of adverse physical environments and the subsequent effects on the Ares-1 crew launch vehicle associated with the loss of containment of cryogenic liquid propellants from the upper stage during ascent. Development of the methodology is led by a team at Sandia National Laboratories (SNL) with guidance and support from a number of National Aeronautics and Space Administration (NASA) personnel. The methodology is based on the current Ares-1 design and feasible accident scenarios. These scenarios address containment failure from debris impact or structural response to pressure or blast loading from an external source. Once containment is breached, the envisioned assessment methodology includes predictions for the sequence of physical processes stemming from cryogenic tank failure. The investigative techniques, analysis paths, and numerical simulations that comprise the proposed methodology are summarized and appropriate simulation software is identified in this report.

Ares I Crew Launch Vehicle Upper Stage/Upper Stage Engine Element Overview

NASA Technical Reports Server (NTRS)

McArthur, J. Craig

2008-01-01

The Ares I upper stage is an integral part of the Constellation Program transportation system. The upper stage provides guidance, navigation and control (GN and C) for the second stage of ascent flight for the Ares I vehicle. The Saturn-derived J-2X upper stage engine will provide thrust and propulsive impulse for the second stage of ascent flight for the Ares I launch vehicle. Additionally, the upper stage is responsible for the avionics system of the the entire Ares I. This brief presentation highlights the requirements, design, progress and production of the upper stage. Additionally, test facilities to support J-2X development are discussed and an overview of the operational and manufacturing flows are provided. Building on the heritage of the Apollo and Space Shuttle Programs, the Ares I Us and USE teams are utilizing extensive lessons learned to place NASA and the US into another era of space exploration. The NASA, Boeing and PWR teams are integrated and working together to make progress designing and building the Ares I upper stage to minimize cost, technical and schedule risks.

Groups Meet . . . Teams Improve: Building Teams That Learn

ERIC Educational Resources Information Center

Hillier, Janet; Dunn-Jensen, Linda M.

2013-01-01

Although most business students participate in team-based projects during undergraduate or graduate course work, the team experience does not always teach team skills or capture the team members' potential: Students complete the task at hand but the explicit process of becoming a team is often not learned. Drawing from organizational learning…

Teams make it work: how team work engagement mediates between social resources and performance in teams.

PubMed

Torrente, Pedro; Salanova, Marisa; Llorens, Susana; Schaufeli, Wilmar B

2012-02-01

In this study we analyze the mediating role of team work engagement between team social resources (i.e., supportive team climate, coordination, teamwork), and team performance (i.e., in-role and extra-role performance) as predicted by the Job Demands-Resources Model. Aggregated data of 533 employees nested within 62 teams and 13 organizations were used, whereas team performance was assessed by supervisor ratings. Structural equation modeling revealed that, as expected, team work engagement plays a mediating role between social resources perceived at the team level and team performance as assessed by the supervisor.

Constellation Ground Systems Launch Availability Analysis: Enhancing Highly Reliable Launch Systems Design

NASA Technical Reports Server (NTRS)

Gernand, Jeffrey L.; Gillespie, Amanda M.; Monaghan, Mark W.; Cummings, Nicholas H.

2010-01-01

Success of the Constellation Program's lunar architecture requires successfully launching two vehicles, Ares I/Orion and Ares V/Altair, in a very limited time period. The reliability and maintainability of flight vehicles and ground systems must deliver a high probability of successfully launching the second vehicle in order to avoid wasting the on-orbit asset launched by the first vehicle. The Ground Operations Project determined which ground subsystems had the potential to affect the probability of the second launch and allocated quantitative availability requirements to these subsystems. The Ground Operations Project also developed a methodology to estimate subsystem reliability, availability and maintainability to ensure that ground subsystems complied with allocated launch availability and maintainability requirements. The verification analysis developed quantitative estimates of subsystem availability based on design documentation; testing results, and other information. Where appropriate, actual performance history was used for legacy subsystems or comparative components that will support Constellation. The results of the verification analysis will be used to verify compliance with requirements and to highlight design or performance shortcomings for further decision-making. This case study will discuss the subsystem requirements allocation process, describe the ground systems methodology for completing quantitative reliability, availability and maintainability analysis, and present findings and observation based on analysis leading to the Ground Systems Preliminary Design Review milestone.

Team Trust in Online Education: Assessing and Comparing Team-Member Trust in Online Teams versus Face-to-Face Teams

ERIC Educational Resources Information Center

Beranek, Peggy M.; French, Monique L.

2011-01-01

Trust is a key factor in enabling effective team performance and, in online teams, needs to be built quickly and early. As universities expand their online offerings students are increasingly working in online teams. Understanding how trust development may differ in online teams versus face-to-face can have implications for online education…

Team Learning Beliefs and Behaviours in Response Teams

ERIC Educational Resources Information Center

Boon, Anne; Raes, Elisabeth; Kyndt, Eva; Dochy, Filip

2013-01-01

Purpose: Teams, teamwork and team learning have been the subject of many research studies over the last decades. This article aims at investigating and confirming the Team Learning Beliefs and Behaviours (TLB&B) model within a very specific population, i.e. police and firemen teams. Within this context, the paper asks whether the team's…

Personality and community prevention teams: Dimensions of team leader and member personality predicting team functioning.

PubMed

Feinberg, Mark E; Kim, Ji-Yeon; Greenberg, Mark T

2008-11-01

The predictors and correlates of positive functioning among community prevention teams have been examined in a number of research studies; however, the role of personality has been neglected. In this study, we examined whether team member and leader personality dimensions assessed at the time of team formation predicted local prevention team functioning 2.5-3.5 years later. Participants were 159 prevention team members in 14 communities participating in the PROSPER study of prevention program dissemination. Three aspects of personality, aggregated at the team level, were examined as predictors: Openness to Experience, Conscientiousness, and Agreeableness. A series of multivariate regression analyses were performed that accounted for the interdependency of five categories of team functioning. Results showed that average team member Openness was negatively, and Conscientiousness was positively linked to team functioning. The findings have implications for decisions about the level and nature of technical assistance support provided to community prevention teams.

ARES I-X Launch

NASA Image and Video Library

2009-10-27

NASA Ares I-X Launch Director Ed Mango, 3rd from left, along with other mission managers watches the launch of the Ares I-X rocket from Firing Room One of the Launch Control Center (LCC) at the Kennedy Space Center in Cape Canaveral, Fla., Wednesday, Oct. 28, 2009. The flight test of Ares I-X will provide NASA with an early opportunity to test and prove flight characteristics, hardware, facilities and ground operations associated with the Ares I. Photo Credit: (NASA/Bill Ingalls)

ARES I-X Launch Prep

NASA Image and Video Library

2009-10-26

NASA Ares I-X Launch Director Ed Mango monitors the launch countdown from Firing Room One of the Launch Control Center (LCC) at the Kennedy Space Center during the planned launch of the Ares I-X rocket from pad 39b at the Kennedy Space Center in Cape Canaveral, Fla., Tuesday, Oct. 27, 2009. The flight test of Ares I-X will provide NASA with an early opportunity to test and prove flight characteristics, hardware, facilities and ground operations associated with the Ares I. Photo Credit: (NASA/Bill Ingalls)

Evolved Expendable Launch Vehicle: DOD Is Assessing Data on Worldwide Launch Market to Inform New Acquisition Strategy

DTIC Science & Technology

2016-07-22

Launch Services (ILS) of a Proton M launch vehicle and one provided by Space Exploration Technologies ( SpaceX ) of a Falcon 9 launch vehicle — and...U.S. based providers are United Launch Alliance (ULA), Space Exploration Technologies Corporation ( SpaceX ), and Orbital ATK. Countries we reviewed

STS Derived Exploration Launch Operations

NASA Technical Reports Server (NTRS)

Best, Joel; Sorge, L.; Siders, J.; Sias, Dave

2004-01-01

A key aspect of the new space exploration programs will be the approach to optimize launch operations. A STS Derived Launch Vehicle (SDLV) Program can provide a cost effective, low risk, and logical step to launch all of the elements of the exploration program. Many benefits can be gained by utilizing the synergy of a common launch site as an exploration spaceport as well as evolving the resources of the current Space Shuttle Program (SSP) to meet the challenges of the Vision for Space Exploration. In particular, the launch operation resources of the SSP can be transitioned to the exploration program and combined with the operations efficiencies of unmanned EELVs to obtain the best of both worlds, resulting in lean launch operations for crew and cargo missions of the exploration program. The SDLV Program would then not only capture the extensive human space flight launch operations knowledge, but also provide for the safe fly-out of the SSP through continuity of system critical skills, manufacturing infrastructure, and ability to maintain and attract critical skill personnel. Thus, a SDLV Program can smoothly transition resources from the SSP and meet the transportation needs to continue the voyage of discovery of the space exploration program.

Antares Rocket Test Launch

NASA Image and Video Library

2013-04-21

NASA Administrator Charles Bolden and NASA Deputy Administrator Lori Garver and other guests react after having watched the successful launch of the Orbital Sciences Corporation Antares rocket from the Mid-Atlantic Regional Spaceport (MARS) at the NASA Wallops Flight Facility in Virginia, Sunday, April 21, 2013. The test launch marked the first flight of Antares and the first rocket launch from Pad-0A. The Antares rocket delivered the equivalent mass of a spacecraft, a so-called mass simulated payload, into Earth's orbit. Photo Credit: (NASA/Bill Ingalls)

M-V launch vehicle

NASA Astrophysics Data System (ADS)

Matsuo, Hiroki; Kawaguchi, Jun'ichiro

1995-01-01

M-V is the next generation satellite launcher of the Institute of Space and Astronautical Science (IS AS) expected to be a work horse for Japanese scientific missions beyond late 1990s. It is a three staged, solid propellant rocket with 2ton class launch capability into LEO. Its development is underway toward the revised first launch date in 1996. This paper describes the back ground and the design philosophy of M-V along with vehicle characteristics featuring new technology to be introduced. Also given are the development status and the launch schedule.

Dawn Orbit Determination Team: Modeling and Fitting of Optical Data at Vesta

NASA Technical Reports Server (NTRS)

Kennedy, Brian; Abrahamson, Matt; Ardito, Alessandro; Haw, Robert; Mastrodemos, Nicholas; Nandi, Sumita; Park, Ryan; Rush, Brian; Vaughan, Andrew

2013-01-01

The Dawn spacecraft was launched on September 27th, 2007. Its mission is to consecutively rendezvous with and observe the two largest bodies in the main asteroid belt, Vesta and Ceres. It has already completed over a year's worth of direct observations of Vesta (spanning from early 2011 through late 2012) and is currently on a cruise trajectory to Ceres, where it will begin scientific observations in mid-2015. Achieving this data collection required careful planning and execution from all Dawn operations teams. Dawn's Orbit Determination (OD) team was tasked with reconstruction of the as-flown trajectory as well as determination of the Vesta rotational rate, pole orientation and ephemeris, among other Vesta parameters. Improved knowledge of the Vesta pole orientation, specifically, was needed to target the final maneuvers that inserted Dawn into the first science orbit at Vesta. To solve for these parameters, the OD team used radiometric data from the Deep Space Network (DSN) along with optical data reduced from Dawn's Framing Camera (FC) images. This paper will de-scribe the initial determination of the Vesta ephemeris and pole using a combination of radiometric and optical data, and also the progress the OD team has made since then to further refine the knowledge of Vesta's body frame orientation and rate with these data.

Consequences of team charter quality: Teamwork mental model similarity and team viability in engineering design student teams

NASA Astrophysics Data System (ADS)

Conway Hughston, Veronica

Since 1996 ABET has mandated that undergraduate engineering degree granting institutions focus on learning outcomes such as professional skills (i.e. solving unstructured problems and working in teams). As a result, engineering curricula were restructured to include team based learning---including team charters. Team charters were diffused into engineering education as one of many instructional activities to meet the ABET accreditation mandates. However, the implementation and execution of team charters into engineering team based classes has been inconsistent and accepted without empirical evidence of the consequences. The purpose of the current study was to investigate team effectiveness, operationalized as team viability, as an outcome of team charter implementation in an undergraduate engineering team based design course. Two research questions were the focus of the study: a) What is the relationship between team charter quality and viability in engineering student teams, and b) What is the relationship among team charter quality, teamwork mental model similarity, and viability in engineering student teams? Thirty-eight intact teams, 23 treatment and 15 comparison, participated in the investigation. Treatment teams attended a team charter lecture, and completed a team charter homework assignment. Each team charter was assessed and assigned a quality score. Comparison teams did not join the lecture, and were not asked to create a team charter. All teams completed each data collection phase: a) similarity rating pretest; b) similarity posttest; and c) team viability survey. Findings indicate that team viability was higher in teams that attended the lecture and completed the charter assignment. Teams with higher quality team charter scores reported higher levels of team viability than teams with lower quality charter scores. Lastly, no evidence was found to support teamwork mental model similarity as a partial mediator of the team charter quality on team viability

ELaNa - Educational Launch of Nanosatellite Enhance Education Through Space Flight

NASA Technical Reports Server (NTRS)

Skrobot, Garrett Lee

2011-01-01

-Picosatellite Orbital Deployer (P-POD), was developed and built by students at California Polytechnic State University (Cal Poly). Integrating a P-POD on a NASA ELV was not an easy task. The creation of new processes and requirements as well as numerous reviews and approvals were necessary within NASA before the first ELaNa mission could be attached to a NASA launch vehicle (LV). One of the key objectives placed on an ELaNa mission is that the CubeSat and PPOD does not increase the baseline risk to the primary mission and launch vehicle. The ELaNa missions achieve this objective by placing a rigorous management and engineering process on both the LV and CubeSat teams. So, what is the future of ELaNa? Currently there are 16 P-POD missions manifested across four launch vehicles to support educational CubeSats selected under the NASA CubeSat Initiative. From this initiative, a rigorous selection process produced 22-student CubeSat missions that are scheduled to fly before the end of 2012. For the initiative to continue, organizations need to submit proposals to the annual CubeSat initiative call so they have the opportunity to be manifested and launched.

Integrating TeamSTEPPS® into ambulatory reproductive health care: Early successes and lessons learned.

PubMed

Paul, Maureen E; Dodge, Laura E; Intondi, Evelyn; Ozcelik, Guzey; Plitt, Ken; Hacker, Michele R

2017-04-01

Most medical teamwork improvement interventions have occurred in hospitals, and more efforts are needed to integrate them into ambulatory care settings. In 2014, Affiliates Risk Management Services, Inc. (ARMS), the risk management services organization for a large network of reproductive health care organizations in the United States, launched a voluntary 5-year initiative to implement a medical teamwork system in this network using the TeamSTEPPS model. This article describes the ARMS initiative and progress made during the first 2 years, including lessons learned. The ARMS TeamSTEPPS program consists of the following components: preparation of participating organizations, TeamSTEPPS master training, implementation of teamwork improvement programs, and evaluation. We used self-administered questionnaires to assess satisfaction with the ARMS program and with the master training course. In the first 2 years, 20 organizations enrolled. Participants found the preparation phase valuable and were highly satisfied with the master training course. Although most attendees felt that the course imparted the knowledge and tools critical for TeamSTEPPS implementation, they identified time restraints and competing initiatives as potential barriers. The project team has learned valuable lessons about obtaining buy-in, consolidating the change teams, making the curriculum relevant, and evaluation. Ambulatory care settings require innovative approaches to integration of teamwork improvement systems. Evaluating and sharing lessons learned will help to hone best practices as we navigate this new frontier in the field of patient safety. © 2017 American Society for Healthcare Risk Management of the American Hospital Association.

Enabling Science and Deep Space Exploration through Space Launch System (LSL) Secondary Payload Opportunities

NASA Technical Reports Server (NTRS)

Singer, Jody; Pelfrey, Joseph; Norris, George

2016-01-01

For the first time in almost 40 years, a NASA human-rated launch vehicle has completed its Critical Design Review (CDR). By reaching this milestone, NASA's Space Launch System (SLS) and Orion spacecraft are on the path to launch a new era of deep space exploration. NASA is making investments to expand science and exploration capability of the SLS by developing the capability to deploy small satellites during the trans-lunar phase of the mission trajectory. Exploration Mission 1 (EM-1), currently planned for launch no earlier than July 2018, will be the first mission to carry such payloads on the SLS. The EM-1 launch will include thirteen 6U Cubesat small satellites that will be deployed beyond low earth orbit. By providing an earth-escape trajectory, opportunities are created for advancement of small satellite subsystems, including deep space communications and in-space propulsion. This SLS capability also creates low-cost options for addressing existing Agency strategic knowledge gaps and affordable science missions. A new approach to payload integration and mission assurance is needed to ensure safety of the vehicle, while also maintaining reasonable costs for the small payload developer teams. SLS EM-1 will provide the framework and serve as a test flight, not only for vehicle systems, but also payload accommodations, ground processing, and on-orbit operations. Through developing the requirements and integration processes for EM-1, NASA is outlining the framework for the evolved configuration of secondary payloads on SLS Block upgrades. The lessons learned from the EM-1 mission will be applied to processes and products developed for future block upgrades. In the heavy-lift configuration of SLS, payload accommodations will increase for secondary opportunities including small satellites larger than the traditional Cubesat class payload. The payload mission concept of operations, proposed payload capacity of SLS, and the payload requirements for launch and

Constellation Ground Systems Launch Availability Analysis: Enhancing Highly Reliable Launch Systems Design

NASA Technical Reports Server (NTRS)

Gernand, Jeffrey L.; Gillespie, Amanda M.; Monaghan, Mark W.; Cummings, Nicholas H.

2010-01-01

Success of the Constellation Program's lunar architecture requires successfully launching two vehicles, Ares I/Orion and Ares V/Altair, within a very limited time period. The reliability and maintainability of flight vehicles and ground systems must deliver a high probability of successfully launching the second vehicle in order to avoid wasting the on-orbit asset launched by the first vehicle. The Ground Operations Project determined which ground subsystems had the potential to affect the probability of the second launch and allocated quantitative availability requirements to these subsystems. The Ground Operations Project also developed a methodology to estimate subsystem reliability, availability, and maintainability to ensure that ground subsystems complied with allocated launch availability and maintainability requirements. The verification analysis developed quantitative estimates of subsystem availability based on design documentation, testing results, and other information. Where appropriate, actual performance history was used to calculate failure rates for legacy subsystems or comparative components that will support Constellation. The results of the verification analysis will be used to assess compliance with requirements and to highlight design or performance shortcomings for further decision making. This case study will discuss the subsystem requirements allocation process, describe the ground systems methodology for completing quantitative reliability, availability, and maintainability analysis, and present findings and observation based on analysis leading to the Ground Operations Project Preliminary Design Review milestone.

Team members' emotional displays as indicators of team functioning.

PubMed

Homan, Astrid C; Van Kleef, Gerben A; Sanchez-Burks, Jeffrey

2016-01-01

Emotions are inherent to team life, yet it is unclear how observers use team members' emotional expressions to make sense of team processes. Drawing on Emotions as Social Information theory, we propose that observers use team members' emotional displays as a source of information to predict the team's trajectory. We argue and show that displays of sadness elicit more pessimistic inferences regarding team dynamics (e.g., trust, satisfaction, team effectiveness, conflict) compared to displays of happiness. Moreover, we find that this effect is strengthened when the future interaction between the team members is more ambiguous (i.e., under ethnic dissimilarity; Study 1) and when emotional displays can be clearly linked to the team members' collective experience (Study 2). These studies shed light on when and how people use others' emotional expressions to form impressions of teams.

Thermographic testing used on the X-33 space launch vehicle program by BFGoodrich Aerospace

NASA Astrophysics Data System (ADS)

Burleigh, Douglas D.

1999-03-01

The X-33 program is a team effort sponsored by NASA under Cooperative Agreement NCC8-115, and led by the Lockheed Martin Corporation. Team member BFGoodrich Aerospace Aerostructures Group (formerly Rohr) is responsible for design, manufacture, and integration of the Thermal Protection System (TPS) of the X-33 launch vehicle. The X-33 is a half-scale, experimental prototype of a vehicle called RLV (Reusable Launch Vehicle) or VentureStarTM, an SSTO (single stage to orbit) vehicle, which is a proposed successor to the aging Space Shuttle. Thermographic testing has been employed by BFGoodrich Aerospace Aerostructures Group for a wide variety of uses in the testing of components of the X-33. Thermographic NDT (TNDT) has been used for inspecting large graphite- epoxy/aluminum honeycomb sandwich panels used on the Leeward Aeroshell structure of the X-33. And TNDT is being evaluated for use in inspecting carbon-carbon composite parts such as the nosecap and wing leading edge components. Pulsed Infrared Testing (PIRT), a special form of TNDT, is used for the routine inspection of sandwich panels made of brazed inconel honeycomb and facesheets. In the developmental and qualification testing of sub-elements of the X-33, thermography has been used to monitor (1) Arc Jet tests at NASA Ames Research Center in Mountain view, CA and NASA Johnson Space Center in Houston, TX, (2) High Temperature (wind) Tunnel Tests (HTT) at Nasa Langley Research Center in Langley, VA, and (3) Hot Gas Tests at NASA Marshall Space Flight Center in Huntsville, AL.

Near-term Horizontal Launch for Flexible Operations: Results of the DARPA/NASA Horizontal Launch Study

NASA Technical Reports Server (NTRS)

Bartolotta, Paul A.; Wilhite, Alan W.; Schaffer, Mark G.; Huebner, Lawrence D.; Voland, Randall T.; Voracek, David F.

2012-01-01

Horizontal launch has been investigated for 60 years by over 130 different studies. During this time only one concept, Pegasus, has ever been in operation. The attractiveness of horizontal launch is the capability to provide a "mobile launch pad" that can use existing aircraft runways, cruise above weather, loiter for mission instructions, and provide precise placement for orbital intercept, rendezvous, or reconnaissance. A jointly sponsored study by DARPA and NASA, completed in 2011, explored the trade space of horizontal launch system concepts which included an exhaustive literature review of the past 70 years. The Horizontal Launch Study identified potential near- and mid-term concepts capable of delivering 15,000 lb payloads to a 28.5 due East inclination, 100 nautical-mile low-Earth orbit. Results are presented for a range of near-term system concepts selected for their availability and relatively low design, development, test, and evaluation (DDT&E) costs. This study identified a viable low-cost development path forward to make a robust and resilient horizontal launch capability a reality.

Commercial space and launch insurance : current market and future outlook : fourth quarter 2002 Quarterly Launch Report

DOT National Transportation Integrated Search

2002-01-01

Since the last review of the space and launch insurance industry (see "Update of the Space and Launch Insurance Industry," 4th quarter, : 1998 Quarterly Launch Report), many changes have occurred in the market. This report endeavors to examine the cu...

Intelsat communications satellite scheduled for launch

NASA Technical Reports Server (NTRS)

1983-01-01

To be placed into a highly elliptical transfer orbit by the Atlas Centaur (AC-61) launch vehicle, the INTELSAT V-F satellite has 12,000 voice circuits and 2 color television channels and incorporates a maritime communication system for ship to shore communications. The stages of the launch vehicle and the launch operations are described. A table shows the launch sequence.

The experience of Patient Aligned Care Team (PACT) members.

PubMed

Ladebue, Amy C; Helfrich, Christian D; Gerdes, Zachary T; Fihn, Stephan D; Nelson, Karin M; Sayre, George G

2016-01-01

In April 2010, the Veterans Health Administration (VHA) launched the Patient Aligned Care Team (PACT) initiative to implement a patient-centered medical home (PCMH) model. Few evaluations have addressed the effects of PCMH on health care professionals' experiences. The aim of this study was to contribute to evaluation of the PACT initiative and the broader literature on PCMH by assessing respondents' experiences of implementing a PCMH model and becoming a teamlet. A retrospective qualitative analysis of open-text responses in a survey fielded to all VHA Primary Care personnel (VHA Primary Care physicians, nurse practitioners, physician assistants, nurse care managers, clinical associates, and administrative clerks) in May and June 2012 (approximately 2 years into the 5-year planned implementation of PACT) using deductive and inductive content analysis. The main measures were two open-response fields: "Is there anything else you would like us to relay to the VA leadership in Central Office?" and "Do you have any other comments or feedback on PACT?" The data consisted of free text responses of 3,868 survey participants who provided text for one or both of the open-response fields. Although respondents viewed PACT positively as a model and reported it improved relationships with patients and increased patient satisfaction, they described multiple barriers to achieving functioning teamlets and unintended consequences, including reduced time with patients, increased participant burnout, and decreased team efficacy because of low-performing team members. A central theme related to staffing being insufficient for the new model. Insufficient staffing of PCMH teams is a critical barrier to realizing the benefits of the new model. Frontline staff have concrete recommendations for other problems, such as using back-up teams to cover during absences, but that will require providing more opportunities for feedback from staff to be heard.

Ivins examines Destiny with the processing team in the SSPF

NASA Technical Reports Server (NTRS)

1999-01-01

In the Space Station Processing Facility, Marsha Ivins, a mission specialist on the STS-98 crew, inspects the U.S. Laboratory with members of the laboratory's processing team. The laboratory module, considered the centerpiece of the International Space Station (ISS), has been named 'Destiny' in honor of its prominent role in the world's largest science and technology effort. It is planned for launch aboard Space Shuttle Endeavour on the sixth ISS construction flight currently targeted for March 2000. From left to right are Ivins, Danny Whittington (face not visible), Melissa Orozco, Jerry Hopkins, and Suzanne Fase.

Assemby, test, and launch operations for the Mars Exploration Rovers

NASA Technical Reports Server (NTRS)

Wallace, Matthew T.; Hardy, Paul V.; Romero, Raul A.; Salvo, Christopher G.; Shain, Thomas W.; Thompson, Arthur D.; Wirth, John W.

2005-01-01

In January of 2004, NASA's twin Mars rovers, Spirit and Opportunity, successfully landed on opposite sides of the Red Planet after a seven month Earth to Mars cruise period. Both vehicles have operated well beyond their 90 day primary mission design life requirements. The Assembly, Test, and Launch Operations (ATLO) program for these missions presented unique technical and schedule challenges to the team at the Jet Propulsion Laboratory (JPL). Among these challenges were a highly compressed schedule and late deliveries leading to extended double shift staffing, dual spacecraft operations requiring test program diversification and resource arbitration, multiple atypical test configurations for airbag/rocket landings and surface mobility testing, and verification of an exceptionally large number of separations, deployments, and mechanisms. This paper discusses the flight system test philosophies and approach, and presents lessons learned.

Athena: Advanced air launched space booster

NASA Astrophysics Data System (ADS)

Booker, Corey G.; Ziemer, John; Plonka, John; Henderson, Scott; Copioli, Paul; Reese, Charles; Ullman, Christopher; Frank, Jeremy; Breslauer, Alan; Patonis, Hristos

1994-06-01

The infrastructure for routine, reliable, and inexpensive access of space is a goal that has been actively pursued over the past 50 years, but has yet not been realized. Current launch systems utilize ground launching facilities which require the booster vehicle to plow up through the dense lower atmosphere before reaching space. An air launched system on the other hand has the advantage of being launched from a carrier aircraft above this dense portion of the atmosphere and hence can be smaller and lighter compared to its ground based counterpart. The goal of last year's Aerospace Engineering Course 483 (AE 483) was to design a 227,272 kg (500,000 lb.) air launched space booster which would beat the customer's launch cost on existing launch vehicles by at least 50 percent. While the cost analysis conducted by the class showed that this goal could be met, the cost and size of the carrier aircraft make it appear dubious that any private company would be willing to invest in such a project. To avoid this potential pitfall, this year's AE 483 class was to design as large an air launched space booster as possible which can be launched from an existing or modification to an existing aircraft. An initial estimate of the weight of the booster is 136,363 kg (300,000 lb.) to 159,091 kg (350,000 lb.).

Athena: Advanced air launched space booster

NASA Technical Reports Server (NTRS)

Booker, Corey G.; Ziemer, John; Plonka, John; Henderson, Scott; Copioli, Paul; Reese, Charles; Ullman, Christopher; Frank, Jeremy; Breslauer, Alan; Patonis, Hristos

1994-01-01

The infrastructure for routine, reliable, and inexpensive access of space is a goal that has been actively pursued over the past 50 years, but has yet not been realized. Current launch systems utilize ground launching facilities which require the booster vehicle to plow up through the dense lower atmosphere before reaching space. An air launched system on the other hand has the advantage of being launched from a carrier aircraft above this dense portion of the atmosphere and hence can be smaller and lighter compared to its ground based counterpart. The goal of last year's Aerospace Engineering Course 483 (AE 483) was to design a 227,272 kg (500,000 lb.) air launched space booster which would beat the customer's launch cost on existing launch vehicles by at least 50 percent. While the cost analysis conducted by the class showed that this goal could be met, the cost and size of the carrier aircraft make it appear dubious that any private company would be willing to invest in such a project. To avoid this potential pitfall, this year's AE 483 class was to design as large an air launched space booster as possible which can be launched from an existing or modification to an existing aircraft. An initial estimate of the weight of the booster is 136,363 kg (300,000 lb.) to 159,091 kg (350,000 lb.).

Launch Vehicle Communications

NASA Technical Reports Server (NTRS)

Welch, Bryan; Greenfeld, Israel

2005-01-01

As the National Aeronautics and Space Administration's (NASA) planning for updated launch vehicle operations progresses, there is a need to consider improved methods. This study considers the use of phased array antennas mounted on launch vehicles and transmitting data to either NASA's Tracking and Data Relay Satellite System (TDRSS) satellites or to the commercial Iridium, Intelsat, or Inmarsat communications satellites. Different data rate requirements are analyzed to determine size and weight of resulting antennas.

Magnetic Launch Assist Experimental Track

NASA Technical Reports Server (NTRS)

1999-01-01

In this photograph, a futuristic spacecraft model sits atop a carrier on the Magnetic Launch Assist System, formerly known as the Magnetic Levitation (MagLev) System, experimental track at the Marshall Space Flight Center (MSFC). Engineers at MSFC have developed and tested Magnetic Launch Assist technologies that would use magnetic fields to levitate and accelerate a vehicle along a track at very high speeds. Similar to high-speed trains and roller coasters that use high-strength magnets to lift and propel a vehicle a couple of inches above a guideway, a Magnetic Launch Assist system would electromagnetically drive a space vehicle along the track. A full-scale, operational track would be about 1.5-miles long and capable of accelerating a vehicle to 600 mph in 9.5 seconds. This track is an advanced linear induction motor. Induction motors are common in fans, power drills, and sewing machines. Instead of spinning in a circular motion to turn a shaft or gears, a linear induction motor produces thrust in a straight line. Mounted on concrete pedestals, the track is 100-feet long, about 2-feet wide, and about 1.5-feet high. The major advantages of launch assist for NASA launch vehicles is that it reduces the weight of the take-off, the landing gear, the wing size, and less propellant resulting in significant cost savings. The US Navy and the British MOD (Ministry of Defense) are planning to use magnetic launch assist for their next generation aircraft carriers as the aircraft launch system. The US Army is considering using this technology for launching target drones for anti-aircraft training.

Effects of Team Emotional Authenticity on Virtual Team Performance.

PubMed

Connelly, Catherine E; Turel, Ofir

2016-01-01

Members of virtual teams lack many of the visual or auditory cues that are usually used as the basis for impressions about fellow team members. We focus on the effects of the impressions formed in this context, and use social exchange theory to understand how these impressions affect team performance. Our pilot study, using content analysis (n = 191 students), suggested that most individuals believe that they can assess others' emotional authenticity in online settings by focusing on the content and tone of the messages. Our quantitative study examined the effects of these assessments. Structural equation modeling (SEM) analysis (n = 81 student teams) suggested that team-level trust and teamwork behaviors mediate the relationship between team emotional authenticity and team performance, and illuminate the importance of team emotional authenticity for team processes and outcomes.

Effects of Team Emotional Authenticity on Virtual Team Performance

PubMed Central

Connelly, Catherine E.; Turel, Ofir

2016-01-01

Members of virtual teams lack many of the visual or auditory cues that are usually used as the basis for impressions about fellow team members. We focus on the effects of the impressions formed in this context, and use social exchange theory to understand how these impressions affect team performance. Our pilot study, using content analysis (n = 191 students), suggested that most individuals believe that they can assess others' emotional authenticity in online settings by focusing on the content and tone of the messages. Our quantitative study examined the effects of these assessments. Structural equation modeling (SEM) analysis (n = 81 student teams) suggested that team-level trust and teamwork behaviors mediate the relationship between team emotional authenticity and team performance, and illuminate the importance of team emotional authenticity for team processes and outcomes. PMID:27630605

Team dynamics within quality improvement teams: a scoping review.

PubMed

Rowland, Paula; Lising, Dean; Sinclair, Lynne; Baker, G Ross

2018-03-31

This scoping review examines what is known about the processes of quality improvement (QI) teams, particularly related to how teams impact outcomes. The aim is to provide research-informed guidance for QI leaders and to inform future research questions. Databases searched included: MedLINE, EMBASE, CINAHL, Web of Science and SCOPUS. Eligible publications were written in English, published between 1999 and 2016. Articles were included in the review if they examined processes of the QI team, were related to healthcare QI and were primary research studies. Studies were excluded if they had insufficient detail regarding QI team processes. Descriptive detail extracted included: authors, geographical region and health sector. The Integrated (Health Care) Team Effectiveness Model was used to synthesize findings of studies along domains of team effectiveness: task design, team process, psychosocial traits and organizational context. Over two stages of searching, 4813 citations were reviewed. Of those, 48 full-text articles are included in the synthesis. This review demonstrates that QI teams are not immune from dysfunction. Further, a dysfunctional QI team is not likely to influence practice. However, a functional QI team alone is unlikely to create change. A positive QI team dynamic may be a necessary but insufficient condition for implementing QI strategies. Areas for further research include: interactions between QI teams and clinical microsystems, understanding the role of interprofessional representation on QI teams and exploring interactions between QI team task, composition and process.

Taking the Next Steps: The Ares I Crew Launch Vehicle and Ares V Cargo Launch Vehicle

NASA Technical Reports Server (NTRS)

Cook, Stephen A.; Vanhooser, Teresa

2008-01-01

The National Aeronautics and Space Administration (NASA)'s Constellation Program is depending on the Ares Projects Office (APO) to deliver the crew and cargo launch capabilities needed to send human explorers to the Moon, Mars, and beyond. The APO continues to make progress toward design, component testing, and early flight testing of the Ares I crew launch vehicle, as well as early design work for the Ares V cargo launch vehicle. Ares I and Ares V will form the core space launch capabilities that the United States needs to continue its pioneering tradition as a spacefaring nation (Figure 1). This paper will discuss design, fabrication, and testing progress toward building these new launch vehicles.

No Launch Before Its Time

NASA Technical Reports Server (NTRS)

Townsend, Bill

2004-01-01

Aura is an Earth-observing satellite developed to help us study the quality of the air we breathe. It will look at the state of the ozone and the atmospheric composition in regards to the Earth's changing climate. I headed to California on July 5, 2004. The plan was that the satellite would launch on the tenth, but we had a few problems getting it off. This was the fifty-ninth launch of my career, and it was also a little different than most of my previous launches. Most of the time it's weather that postpones a launch; there aren't usually that many technical issues this late in the game. This time. however, we had several problems, equally split between the launch vehicle and the spacecraft. I remember a member of the crew asking me, 'Is this normal?' And in my experience, it wasn't.

High Altitude Launch for a Practical SSTO

NASA Technical Reports Server (NTRS)

Landis, Geoffrey A.; Denis, Vincent

2003-01-01

Existing engineering materials allow the construction of towers to heights of many kilometers. Orbital launch from a high altitude has significant advantages over sea-level launch due to the reduced atmospheric pressure, resulting in lower atmospheric drag on the vehicle and allowing higher rocket engine performance. High-altitude launch sites are particularly advantageous for single-stage to orbit (SSTO) vehicles, where the payload is typically 2 percent of the initial launch mass. An earlier paper enumerated some of the advantages of high altitude launch of SSTO vehicles. In this paper, we calculate launch trajectories for a candidate SSTO vehicle, and calculate the advantage of launch at launch altitudes 5 to 25 kilometer altitudes above sea level. The performance increase can be directly translated into increased payload capability to orbit, ranging from 5 to 20 percent increase in the mass to orbit. For a candidate vehicle with an initial payload fraction of 2 percent of gross lift-off weight, this corresponds to 31 percent increase in payload (for 5-kilometer launch altitude) to 122 percent additional payload (for 25-kilometer launch altitude).

High Altitude Launch for a Practical SSTO

NASA Technical Reports Server (NTRS)

Landis, Geoffrey A.; Denis, Vincent

2003-01-01

Existing engineering materials allow the construction of towers to heights of many kilometers. Orbital launch from a high altitude has significant advantages over sea-level launch due to the reduced atmospheric pressure, resulting in lower atmospheric drag on the vehicle and allowing higher rocket engine performance. high-altitude launch sites are particularly advantageous for single-stage to orbit (SSTO) vehicles, where the payload is typically 2% of the initial launch mass. An earlier paper enumerated some of the advantages of high altitude launch of SSTO vehicles. In this paper, we calculate launch trajectories for a candidate SSTO vehicle, and calculate the advantage of launch at launch altitudes 5 to 25 kilometer altitudes above sea level. The performance increase can be directly translated in to increased payload capability to orbit, ranging from 5 to 20% increase in the mass to orbit. For a candidate vehicle with an initial payload fraction of 2% of gross lift-off weight, this corresponds to 31 % increase in payload (for 5-km launch altitude) to 122% additional payload (for 25-km launch altitude).

High Altitude Launch for a Practical SSTO

NASA Technical Reports Server (NTRS)

Landis, Geoffrey A.; Denis, Vincent; Lyons, Valerie (Technical Monitor)

2003-01-01

Existing engineering materials allow the construction of towers to heights of many kilometers. Orbital launch from a high altitude has significant advantages over sea-level launch due to the reduced atmospheric pressure, resulting in lower atmospheric drag on the vehicle and allowing higher rocket engine performance. High-altitude launch sites are particularly advantageous for single-stage to orbit (SSTO) vehicles, where the payload is typically 2% of the initial launch mass. An earlier paper enumerated some of the advantages of high altitude launch of SSTO vehicles. In this paper, we calculate launch trajectories for a candidate SSTO vehicle, and calculate the advantage of launch at launch altitudes 5 to 25 kilometer altitudes above sea level. The performance increase can be directly translated into increased payload capability to orbit, ranging from 5 to 20% increase in the mass to orbit. For a candidate vehicle with an initial payload fraction of 2% of gross lift-off weight, this corresponds to 31% increase in payload (for 5-km launch altitude) to 122% additional payload (for 25-km launch altitude).

High Altitude Launch for a Practical SSTO

NASA Astrophysics Data System (ADS)

Landis, Geoffrey A.; Denis, Vincent

2003-01-01

Existing engineering materials allow the constuction of towers to heights of many kilometers. Orbital launch from a high altitude has significant advantages over sea-level launch due to the reduced atmospheric pressure, resulting in lower atmospheric drag on the vehicle and allowing higher rocket engine performance. High-altitude launch sites are particularly advantageous for single-stage to orbit (SSTO) vehicles, where the payload is typically 2% of the initial launch mass. An earlier paper enumerated some of the advantages of high altitude launch of SSTO vehicles. In this paper, we calculate launch trajectories for a candidate SSTO vehicle, and calculate the advantage of launch at launch altitudes 5 to 25 kilometer altitudes above sea level. The performance increase can be directly translated into increased payload capability to orbit, ranging from 5 to 20% increase in the mass to orbit. For a candidate vehicle with an initial payload fraction of 2% of gross lift-off weight, this corresponds to 31% increase in payload (for 5-km launch altitude) to 122% additional payload (for 25-km launch altitude).

Rocket Launch Trajectory Simulations Mechanism

NASA Technical Reports Server (NTRS)

Margasahayam, Ravi; Caimi, Raoul E.; Hauss, Sharon; Voska, N. (Technical Monitor)

2002-01-01

The design and development of a Trajectory Simulation Mechanism (TSM) for the Launch Systems Testbed (LST) is outlined. In addition to being one-of-a-kind facility in the world, TSM serves as a platform to study the interaction of rocket launch-induced environments and subsequent dynamic effects on the equipment and structures in the close vicinity of the launch pad. For the first time, researchers and academicians alike will be able to perform tests in a laboratory environment and assess the impact of vibroacoustic behavior of structures in a moving rocket scenario on ground equipment, launch vehicle, and its valuable payload or spacecraft.

ARES I-X Launch Prep

NASA Image and Video Library

2009-10-26

Mission managers, from left, NASA Ares I-X Assistant Launch Director Pete Nickolenko, Ground Operations Manager Philip "Pepper" Phillips, Ares I-X Launch Director Ed Mango, and Constellation Program manager Jeff Hanley review the latest weather radar from Firing Room One of the Launch Control Center (LCC) at the Kennedy Space Center during the launch countdown of the Ares I-X rocket in Cape Canaveral, Fla., Tuesday, Oct. 27, 2009. The flight test of Ares I-X will provide NASA with an early opportunity to test and prove flight characteristics, hardware, facilities and ground operations associated with the Ares I. Photo Credit: (NASA/Bill Ingalls)

Launch of Jupiter-C/Explorer 1

NASA Technical Reports Server (NTRS)

1958-01-01

Launch of Jupiter-C/Explorer 1 at Cape Canaveral, Florida on January 31, 1958. After the Russian Sputnik 1 was launched in October 1957, the launching of an American satellite assumed much greater importance. After the Vanguard rocket exploded on the pad in December 1957, the ability to orbit a satellite became a matter of national prestige. On January 31, 1958, slightly more than four weeks after the launch of Sputnik.The ABMA (Army Ballistic Missile Agency) in Redstone Arsenal, Huntsville, Alabama, in cooperation with the Jet Propulsion Laboratory, launched a Jupiter from Cape Canaveral, Florida. The rocket consisted of a modified version of the Redstone rocket's first stage and two upper stages of clustered Baby Sergeant rockets developed by the Jet Propulsion Laboratory and later designated as Juno boosters for space launches

Nonlinear effects of team tenure on team psychological safety climate and climate strength: Implications for average team member performance.

PubMed

Koopmann, Jaclyn; Lanaj, Klodiana; Wang, Mo; Zhou, Le; Shi, Junqi

2016-07-01

The teams literature suggests that team tenure improves team psychological safety climate and climate strength in a linear fashion, but the empirical findings to date have been mixed. Alternatively, theories of group formation suggest that new and longer tenured teams experience greater team psychological safety climate than moderately tenured teams. Adopting this second perspective, we used a sample of 115 research and development teams and found that team tenure had a curvilinear relationship with team psychological safety climate and climate strength. Supporting group formation theories, team psychological safety climate and climate strength were higher in new and longer tenured teams compared with moderately tenured teams. Moreover, we found a curvilinear relationship between team tenure and average team member creative performance as partially mediated by team psychological safety climate. Team psychological safety climate improved average team member task performance only when team psychological safety climate was strong. Likewise, team tenure influenced average team member task performance in a curvilinear manner via team psychological safety climate only when team psychological safety climate was strong. We discuss theoretical and practical implications and offer several directions for future research. (PsycINFO Database Record (c) 2016 APA, all rights reserved).

The Challenges of Integrating NASA's Human, Budget, and Data Capital within the Constellation Program's Exploration Launch Projects Office

NASA Technical Reports Server (NTRS)

Kidd, Luanne; Morris, Kenneth B.; Self, Timothy A.

2007-01-01

The U.S. Vision for Space Exploration directs NASA to retire the Space Shuttle in 2010 and replace it with safe, reliable, and cost-effective space transportation systems for crew and cargo travel to the Moon, Mars, and beyond. Such emerging space transportation initiatives face massive organizational challenges, including building and nurturing an experienced, dedicated team with the right skills for the required tasks; allocating and tracking the fiscal capital invested in achieving technical progress against an integrated master schedule; and turning generated data into useful knowledge that equips the team to design and develop superior products for customers and stakeholders. It has been more than 30 years since the Space Shuttle was designed; therefore, the current aerospace workforce has limited experience with developing new designs for human-rated spaceflight hardware. To accomplish these activities, NASA is using a wide range of state-of-the-art information technology tools that connect its diverse, decentralized teams and provide timely, accurate information for decision makers. In addition, business professionals are assisting technical managers with planning, tracking, and forecasting resource use against an integrated master schedule that horizontally and vertically interlinks hardware elements and milestone events. Furthermore, NASA is employing a wide variety of strategies to ensure that it has the motivated and qualified staff it needs for the tasks ahead. This paper discusses how NASA's Exploration Launch Projects Office, which is responsible for delivering these new launch vehicles, integrates its resources to create an engineering business environment that promotes mission success, which is defined by replacing the Space Shuttle by 2014 and returning to the Moon by 2020.

NASA's Space Launch System Program Update

NASA Technical Reports Server (NTRS)

May, Todd; Lyles, Garry

2015-01-01

Hardware and software for the world's most powerful launch vehicle for exploration is being welded, assembled, and tested today in high bays, clean rooms and test stands across the United States. NASA's Space Launch System (SLS) continued to make significant progress in 2014 with more planned for 2015, including firing tests of both main propulsion elements and the program Critical Design Review (CDR). Developed with the goals of safety, affordability, and sustainability, SLS will still deliver unmatched capability for human and robotic exploration. The initial Block 1 configuration will deliver more than 70 metric tons of payload to low Earth orbit (LEO). The evolved Block 2 design will deliver some 130 metric tons to LEO. Both designs offer enormous opportunity and flexibility for larger payloads, simplifying payload design as well as ground and on-orbit operations, shortening interplanetary transit times, and decreasing overall mission risk. Over the past year, every vehicle element has manufactured or tested hardware. An RS-25 liquid propellant engine was hotfire-tested at NASA's Stennis Space Center, Miss. for the first time since 2009 exercising and validating the new engine controller, the renovated A-1 test stand, and the test teams. Four RS-25s will power the SLS core stage. A qualification five-segment solid rocket motor incorporating several design, material, and process changes was scheduled to be test-fired in March at the prime contractor's facility in Utah. The booster also successfully completed its Critical Design Review (CDR) validating the planned design. All six major manufacturing tools for the core stage are in place at the Michoud Assembly Facility in Louisiana, and have been used to build numerous pieces of confidence, qualification, and even flight hardware, including barrel sections, domes and rings used to assemble the world's largest rocket stage. SLS Systems Engineering accomplished several key tasks including vehicle avionics software

Environmentally-Preferable Launch Coatings

NASA Technical Reports Server (NTRS)

Kessel, Kurt R.

2015-01-01

The Ground Systems Development and Operations (GSDO) Program at NASA Kennedy Space Center (KSC), Florida, has the primary objective of modernizing and transforming the launch and range complex at KSC to benefit current and future NASA programs along with other emerging users. Described as the launch support and infrastructure modernization program in the NASA Authorization Act of 2010, the GSDO Program will develop and implement shared infrastructure and process improvements to provide more flexible, affordable, and responsive capabilities to a multi-user community. In support of NASA and the GSDO Program, the objective of this project is to determine the feasibility of environmentally friendly corrosion protecting coatings for launch facilities and ground support equipment (GSE). The focus of the project is corrosion resistance and survivability with the goal to reduce the amount of maintenance required to preserve the performance of launch facilities while reducing mission risk. The project compares coating performance of the selected alternatives to existing coating systems or standards.

Increasing Student-Learning Team Effectiveness with Team Charters

ERIC Educational Resources Information Center

Hunsaker, Phillip; Pavett, Cynthia; Hunsaker, Johanna

2011-01-01

Because teams are a ubiquitous part of most organizations today, it is common for business educators to use team assignments to help students experientially learn about course concepts and team process. Unfortunately, students frequently experience a number of problems during team assignments. The authors describe the results of their research and…

Measuring Team Learning Behaviours through Observing Verbal Team Interaction

ERIC Educational Resources Information Center

Raes, Elisabeth; Boon, Anne; Kyndt, Eva; Dochy, Filip

2015-01-01

Purpose: This study aims to explore, as an answer to the observed lack of knowledge about actual team learning behaviours, the characteristics of the actual observed basic team learning behaviours and facilitating team learning behaviours more in-depth of three project teams. Over time, team learning in an organisational context has been…

Mobile, high-wind, balloon-launching apparatus

NASA Technical Reports Server (NTRS)

Rust, W. David; Marshall, Thomas C.

1989-01-01

In order to place instruments for measuring meteorological and electrical parameters into thunderstorms, an inexpensive apparatus has been developed which makes it possible to inflate, transport, and launch balloons in high winds. The launching apparatus is a cylinder of bubble plastic that is made by joining the sides of the cylinder together with a velcro rip strip. A balloon is launched by pulling the rip strip rapidly. This allows the balloon to pop upward into the ambient low-level wind and carry its instrumentation aloft. Different-sized launch tubes are constructed to accommodate particular sizes of balloons. Balloons have been launched in winds of about 20 m/s.

TEAMS. Team Exercise for Action Management Skills: A Semester-Long Team-Management Simulation.