SHEFEX - the vehicle and sub-systems for a hypersonic re-entry flight experiment

NASA Astrophysics Data System (ADS)

Turner, John; Hörschgen, Marcus; Turner, Peter; Ettl, Josef; Jung, Wolfgang; Stamminger, Andreas

2005-08-01

The purpose of the Sharp Edge Flight Experiment (SHEFEX) is to investigate the aerodynamic behaviour and thermal problems of an unconventional shape for re-entry vehicles, comprising multi-facetted surfaces with sharp edges. The main object of this experiment is the correlation of numerical analysis with real flight data in terms of the aerodynamic effects and structural concept for the thermal protection system (TPS). The Mobile Rocket Base of the German Aerospace Center (DLR) is responsible for the test flight of SHEFEX on a two stage unguided solid propellant sounding rocket which is required to provide a velocity of the order of March 7 for more than 30 seconds during atmospheric re-entry. This paper discusses the problems associated with the mission requirements and the solutions developed for the vehicle and sub-systems.

Automated Re-Entry System using FNPEG

NASA Technical Reports Server (NTRS)

Johnson, Wyatt R.; Lu, Ping; Stachowiak, Susan J.

2017-01-01

This paper discusses the implementation and simulated performance of the FNPEG (Fully Numerical Predictor-corrector Entry Guidance) algorithm into GNC FSW (Guidance, Navigation, and Control Flight Software) for use in an autonomous re-entry vehicle. A few modifications to FNPEG are discussed that result in computational savings -- a change to the state propagator, and a modification to cross-range lateral logic. Finally, some Monte Carlo results are presented using a representative vehicle in both a high-fidelity 6-DOF (degree-of-freedom) sim as well as in a 3-DOF sim for independent validation.

X-38 V201 Avionics Architecture

NASA Technical Reports Server (NTRS)

Bedos, Thierry; Anderson, Brian L.

1999-01-01

The X-38 is an experimental NASA project developing a core human capable spacecraft at a fraction of the cost of any previous human rated vehicle. The first operational derivative developed from the X-38 program will be the International Space Station (ISS) Crew Return Vehicle (CRV). Although the current X-38 vehicles are designed as re-entry vehicles only, the option exists to modify the vehicle for uses as an upward vehicle launched from an expendable launch vehicle or from the X-33 operational derivative. The Operational CRV, that will be derived from the X-38 spaceflight vehicle, will provide an emergency return capability from the International Space Station (ISS). The spacecraft can hold a crew of up to seven inside a pressurized cabin. The CRV is passively delivered to ISS, stays up to three year on-orbit attached to ISS in a passive mode with periodic functional checkout, before separation from ISS, de-orbit, entry and landing. The X-38 Vehicle 201 (V201) is being developed at NASA/JSC to demonstrate key technologies associated with the development of the CRV design. The X-38 flight test will validate the low cost development concept by demonstrating the entire station departure, re-entry, guidance and landing portions of the CRV mission. All new technologies and subsystems proposed for CRV will be validated during either the on orbit checkout or flight phases of the X-38 space flight test. The X-38 subsystems are required to be similar to those subsystems required for the CRV to the greatest extent possible. In many cases, the subsystems are identical to those that will be utilized on the Operational CRV.

The use of inflatable structures for re-entry of orbiting vehicles

NASA Astrophysics Data System (ADS)

Kendall, Robert T.; Maddox, Arthur R.

1990-10-01

Inflatable recovery systems offer the unique advantage that a large high-drag shape can be stored initially in a relatively small package. The resulting shapes decelerate rapidly with lower heating inputs than other types of re-entry vehicles. Recent developments have led to some light-weight materials, with little thermal protection, can withstand the heating inputs to such vehicles. As a result, inflatable recovery vehicles offer a simple, reliable and economical way to return various vehicles from orbit. This paper examines the application of this concept to a large and a small vehicle with the accompanying dynamics that might be expected. More complex systems could extend the concept to emergency personnel escape systems, payload abort and satellite recovery systems.

FLPP IXV Re-Entry Vehicle, Supersonic Charectisation Based on DNW SST Wind Tunnel Tests and CFD

NASA Astrophysics Data System (ADS)

Kapteijn, C.; Maseland, H.; Chiarelli, C.; Mareschi, V.; Tribot, J.-P.; Binetti, P.; Walloscheck, T.

2009-01-01

The European Space Agency ESA, has engaged in 2004, the IXV project (Intermediate eXperimental Vehicle) which is part of the FLPP (Future Launcher Preparatory Programme) aiming at answering to critical technological issues for controlled re-entry, while supporting the future generation launchers and to improve in general European capabilities in the strategic field of atmospheric re-entry for future space transportation, exploration and scientific applications. The IXV key mission and system objectives are the design, development, manufacturing, assembling and on- ground to in-flight verification of an autonomous European lifting and aerodynamically controlled re- entry system, integrating the critical re- entry technologies at the system level. In particular, the IXV shall demonstrate system integrated key technologies such as lifting flight control by means of aerodynamic surfaces that are one of the main primary objectives of the experimental investigation. Lifting and aerodynamic controlled re-entry represents a significant capability advancement with respect to the ballistic re-entry of capsules like the ARD. Since hypersonic aerodynamics is essentially different from supersonic aerodynamics, the current mission is to perform an atmospheric re-entry in combination with a safe recovery the in supersonic flight regime. However, mission extension to trimmed transonic flight is under consideration based on a preliminary analysis of the aerodynamic characteristics of the IXV configuration. Since the beginning of the IXV project, an aerodynamic data base (AEDB) has been built up and continuously updated integrating the additional information mainly provided by means of CFD (ie: Euler and Navier-Stokes) and lately also by means of WTTs. This AEDB serves for flying qualities analysis and for re-entry simulations. During the development phase B2/C1, the effectiveness of the control surfaces and their impact on te vehicle's aerodynamic forces in the supersonic regime is measured for a number of discrete deflection settings in the Super-Sonic wind Tunnel (SST) of DNW. Enabling an improved understanding of the measured aerodynamic characteristics, complementary computations were performed by Thales Alenia Space. The complete set of data was analyzed and compared enabling a consolidation of the nominal aerodynamic and aerodynamic uncertainties as well. The paper presents the main objectives of the supersonic characterisation of IXV including WTTs, and the main outcomes of the current data comparisons.

Development Of Metallic Thermal Protection System For The Expert Re-Entry Vehicle: Design Verification

NASA Astrophysics Data System (ADS)

Fatemi, Javad

2011-05-01

The thermal protection system of the EXPERT re-entry vehicle is subjected to accelerations, vibrations, acoustic and shock loads during launch and aero-heating loads and aerodynamic forces during re-entry. To fully understand the structural and thermomechanical performances of the TPS, heat transfer analysis, thermal stress analysis, and thermal buckling analysis must be performed. This requires complex three-dimensional thermal and structural models of the entire TPS including the insulation and sensors. Finite element (FE) methods are employed to assess the thermal and structural response of the TPS to the mechanical and aerothermal loads. The FE analyses results are used for the design verification and design improvement of the EXPERT thermal protection system.

EXPERT: An atmospheric re-entry test-bed

NASA Astrophysics Data System (ADS)

Massobrio, F.; Viotto, R.; Serpico, M.; Sansone, A.; Caporicci, M.; Muylaert, J.-M.

2007-06-01

In recognition of the importance of an independent European access to the International Space Station (ISS) and in preparation for the future needs of exploration missions, ESA is conducting parallel activities to generate flight data using atmospheric re-entry test-beds and to identify vehicle design solutions for human and cargo transportation vehicles serving the ISS and beyond. The EXPERT (European eXPErimental Re-entry Test-bed) vehicle represents the major on-going development in the first class of activities. Its results may also benefit in due time scientific missions to planets with an atmosphere and future reusable launcher programmes. The objective of EXPERT is to provide a test-bed for the validation of aerothermodynamics models, codes and ground test facilities in a representative flight environment, to improve the understanding of issues related to analysis, testing and extrapolation to flight. The vehicle will be launched on a sub-orbital trajectory using a Volna missile. The EXPERT concept is based on a symmetrical re-entry capsule whose shape is composed of simple geometrical elements. The suborbital trajectory will reach 120 km altitude and a re-entry velocity of 5 6km/s. The dimensions of the capsule are 1.6 m high and 1.3 m diameter; the overall mass is in the range of 250 350kg, depending upon the mission parameters and the payload/instrumentation complement. A consistent number of scientific experiments are foreseen on-board, from innovative air data system to shock wave/boundary layer interaction, from sharp hot structures characterisation to natural and induced regime transition. Currently the project is approaching completion of the phase B, with Alenia Spazio leading the industrial team and CIRA coordinating the scientific payload development under ESA contract.

KSC-2011-5112

NASA Image and Video Library

2011-07-07

CAPE CANAVERAL, Fla. -- A media event was held on the grounds near the Press Site at NASA's Kennedy Space Center in Florida where a Multi-Purpose Crew Vehicle (MPCV) is on display. The MPCV is based on the Orion design requirements for traveling beyond low Earth orbit and will serve as the exploration vehicle that will carry the crew to space, provide emergency abort capability, sustain the crew during the space travel, and provide safe re-entry from deep space return velocities. Seen here is Mark Geyer, Multi-Purpose Crew Vehicle program manager speaking to media during a question-and-answer session. Photo credit: NASA/Frankie Martin

Coronas-F Orbit Monitoring and Re-Entry Prediction

NASA Technical Reports Server (NTRS)

Ivanov, N. M.; Kolyuka, Yu. F.; Afanasieva, T. I.; Gridchina, T. A.

2007-01-01

Russian scientific satellite CORONAS-F was launched on July, 31, 2001. The object was inserted in near-circular orbit with the inclination 82.5deg and a mean altitude approx. 520 km. Due to the upper atmosphere drag CORONAS-F was permanently descended and as a result on December, 6, 2005 it has finished the earth-orbital flight, having lifetime in space approx. 4.5 years. The satellite structural features and its flight attitude control led to the significant variations of its ballistic coefficient during the flight. It was a cause of some specific difficulties in the fulfillment of the ballistic and navigation support of this space vehicle flight. Besides the main mission objective CORONAS-F also has been selected by the Inter-Agency Space Debris Coordination Committee (IADC) as a target object for the next regular international re-entry test campaign on a program of surveillance and re-entry prediction for the hazard space objects within their de-orbiting phases. Spacecraft (S/C) CORONAS-F kept its working state right up to the end of the flight - down to the atmosphere entry. This fact enabled to realization of the additional research experiments, concerning with an estimation of the atmospheric density within the low earth orbits (LEO) of the artificial satellites, and made possible to continue track the S/C during final phase of its flight by means of Russian regular command & tracking system, used for it control. Thus there appeared a unique possibility of using for tracking S/C at its de-orbiting phase not only passive radar facilities, belonging to the space surveillance systems and traditionally used for support of the IADC re-entry test campaigns, but also more precise active trajectory radio-tracking facilities from the ground control complex (GCC) applied for this object. Under the corresponding decision of the Russian side such capability of additional high-precise tracking control of the CORONAS-F flight in this period of time has been implemented. The organizing of the CORONAS-F ballistic and navigational support (BNS) and solving its main tasks (such as S/C orbit determination (OD) and its motion prediction and connected with them) both for regular mission stage and for additional flight program were realized by the group of specialists from the Mission Control Center (MCC). MCC was also assigned as a principal organization from the Russian side for participation in the 7th IADC re-entry test campaign on CORONAS-F. The CORONAS-F flight features and space environments circumstances during its flight as well as a methodology and technology of spacecraft ballistic and navigational support are given below. The BNS results for different phases of S/C flight, including the results of its re-entry predictions, obtained during the realization of the 7th IADC test campaign are submitted. The accuracy of space vehicle re-entry prediction and its dependence on various factors are analyzed in more details.

Radar cross section measurements of a scale model of the space shuttle orbiter vehicle

NASA Technical Reports Server (NTRS)

Yates, W. T.

1978-01-01

A series of microwave measurements was conducted to determine the radar cross section of the Space Shuttle Orbiter vehicle at a frequency and at aspect angles applicable to re-entry radar acquisition and tracking. The measurements were performed in a microwave anechoic chamber using a 1/15th scale model and a frequency applicable to C-band tracking radars. The data were digitally recorded and processed to yield statistical descriptions useful for prediction of orbiter re-entry detection and tracking ranges.

Impact of Vehicle Flexibility on IRVE-II Flight Dynamics

NASA Technical Reports Server (NTRS)

Bose, David M.; Toniolo, Matthew D.; Cheatwood, F. M.; Hughes, Stephen J.; Dillman, Robert A.

2011-01-01

The Inflatable Re-entry Vehicle Experiment II (IRVE-II) successfully launched from Wallops Flight Facility (WFF) on August 17, 2009. The primary objectives of this flight test were to demonstrate inflation and re-entry survivability, assess the thermal and drag performance of the reentry vehicle, and to collect flight data for refining pre-flight design and analysis tools. Post-flight analysis including trajectory reconstruction outlined in O Keefe3 demonstrated that the IRVE-II Research Vehicle (RV) met mission objectives but also identified a few anomalies of interest to flight dynamics engineers. Most notable of these anomalies was high normal acceleration during the re-entry pressure pulse. Deflection of the inflatable aeroshell during the pressure pulse was evident in flight video and identified as the likely cause of the anomaly. This paper provides a summary of further post-flight analysis with particular attention to the impact of aeroshell flexibility on flight dynamics and the reconciliation of flight performance with pre-flight models. Independent methods for estimating the magnitude of the deflection of the aeroshell experienced on IRVE-II are discussed. The use of the results to refine models for pre-flight prediction of vehicle performance is then described.

Effects of Angle of Attack on the Behaviour of Imperfections in Thermal Protection Systems of Re-entry Vehicles

NASA Astrophysics Data System (ADS)

Palharini, R. C.; Scanlon, T. J.; Reese, J. M.

The study of atmospheric re-entry under rarefied nonequilibrium flows is a challenging problem directly related to the development of new aerospace technologies, where the prediction of thermal loads acting over the spacecraft is critical during descent phase.

School re-entry of the pediatric heart transplant recipient.

PubMed

Weil, Constance M; Rodgers, S; Rubovits, S

2006-12-01

Pediatric cardiac transplant has become increasingly frequent in the last decade and survival rates have improved remarkably. Outcome research on this population suggests that the majority of children have the capacity for healthy adaptation although 25-40% have been shown to have some type of psychiatric difficulties. As school plays a major role in these children's lives, early intervention and close liaison with schools is indicated to reduce psychological morbidity, enhance adaptation within the school environment and enhance overall adjustment. This paper proposes a model for a school re-entry program for this population. The school re-entry program is aimed at children who are undergoing cardiac transplant and will be entering or re-entering the school system. They may range in academic age from preschool to college level and have been attending private or public schools with placements in regular education programs, regular education programs with resource support, special education programs, and alternative school programs. Others may not have been attending school because of the severity of their medical condition and have been receiving in-home tutoring. Each child is offered school re-entry assistance by a multi-disciplinary team composed of members from the Cardiology Transplant Service. The re-entry program includes cognitive and psychosocial assessment, liaison with the child's school pre- and post-transplant, academic planning and provision of academic, emotional, and behavioral support before, during, and immediately after transplant, a school re-entry visit, and an ongoing school consultation. The goal is to address issues necessary for a successful school re-entry including appropriate academic placement and support, psychosocial adjustment, education of school personnel and ongoing health needs of the student. The next step is to formally evaluate the efficacy of this program in successful school re-entry.

Near-Optimal Re-Entry Trajectories for Reusable Launch Vehicles

NASA Technical Reports Server (NTRS)

Chou, H.-C.; Ardema, M. D.; Bowles, J. V.

1997-01-01

A near-optimal guidance law for the descent trajectory for earth orbit re-entry of a fully reusable single-stage-to-orbit pure rocket launch vehicle is derived. A methodology is developed to investigate using both bank angle and altitude as control variables and selecting parameters that maximize various performance functions. The method is based on the energy-state model of the aircraft equations of motion. The major task of this paper is to obtain optimal re-entry trajectories under a variety of performance goals: minimum time, minimum surface temperature, minimum heating, and maximum heading change; four classes of trajectories were investigated: no banking, optimal left turn banking, optimal right turn banking, and optimal bank chattering. The cost function is in general a weighted sum of all performance goals. In particular, the trade-off between minimizing heat load into the vehicle and maximizing cross range distance is investigated. The results show that the optimization methodology can be used to derive a wide variety of near-optimal trajectories.

Concepts and system design of a space emergency re-entry vehicle.

NASA Technical Reports Server (NTRS)

Huang, C. J.; Dickerson, S. L.

1971-01-01

Discussion of the spectrum of remedial concepts and realistic mission constraints. A vehicle design is presented which is offered as the 'best' solution among a number of alternative designs in terms of its cost effectiveness. The probability of the safe reentry and recovery of one to three stranded astronauts is 0.80. The vehicle is symmetrical and lenticular in shape, and exhibits a modest lift-to-drag ratio of 0.5, allowing it to reenter a two-skip trajectory with minimal gravity forces on the astronauts. Attitude control, voice and beacon communication, and impact attenuation are also provided. The vehicle could be delivered in a docked position on the Apollo Applications Program multiple docking adapter.

Advanced Concept

NASA Image and Video Library

2008-02-15

THIS IS A TEST OF THE 1ST STAGE RE-ENTRY VEHICLE. HEAT TESTING OF A 3% MODEL TO SUPPORT THE ARES/ CLV FIRST STAGE RE-ENTRY. THIS TEST OCCURRED AT ARNOLD AIR FORCE BASE, TENNESSEE. THIS TESTING SUPPORTS THE DEVELOPMENT OF THE CONSTELLATION/ARES PROJECT. THIS IMAGE IS EXTRACTED FROM A HIGH DEFINITION VIDEO FILE AND IS THE HIGHEST RESOLUTION AVAILABLE.

Role Management, Educational Satisfaction, and Role Dynamics in Post-Secondary, Re-entry Women.

ERIC Educational Resources Information Center

Edmondon, Mary Ellen; And Others

1986-01-01

A sample of 42 post-secondary, educational re-entry women completed questionnaires focusing on background status, role dynamics, and satisfaction with their re-entry experience. Results showed no differences between students in a vocational program and those in a traditional, academic program. Role-dynamic variables--but not background-status…

Intermediate Experimental Vehicle, ESA Program IXV ATDB Tool and Aerothermodynamic Characterization

NASA Astrophysics Data System (ADS)

Mareschi, Vincenzo; Ferrarella, Daniela; Zaccagnino, Elio; Tribot, Jean-Pierre; Vallee, Jean-Jacques; Haya-Ramos, Rodrigo; Rufolo, Giuseppe; Mancuso, Salvatore

2011-05-01

In the complex domain of the space technologies and among the different applications available in Europe, a great interest has been placed since several years in the development of re-entry technologies. Among the different achievements obtained in that field it is to be recalled the experience of the Atmospheric Re-entry Vehicle flight in 1998 and a certain number of important investments per-formed at Agency and national levels like Hermes, MSTP, Festip, X-38, FLPP, TRP, GSTP, HSTS, AREV, Pre-X. IXV (Intermediate eXperimental V ehicle) builds on these past experiences and studies and it is conceived to be the next technological step forward with respect to ARD With respect to previous European ballistic or quasi- ballistic demonstrators, IXV will have an increased in- flight manoeuvrability and the planned mission will allow verifying the performances of the required technologies against a wider re-entry corridor. This will imply from the pure technological aspect to increase the level of engagement on critical technologies and disciplines like aerodynamics/aerothermodynamics, guidance, navigation, control, thermal protection materials and in flight measurements. In order to support the TPS design and the other sub- systems, an AeroThermodynamicDataBase Tool has been developed by Dassault Aviation and integrated by Thales Alenia Space with the Functional Engineering Simulator (used for GNC performances evaluation) in order to characterize the aerothermodynamic behaviour of the vehicle. This paper will describe: - The methodology used to develop the ATDB tool, based on the processing of CFD computations and WTT campaigns results. - The utilization of the ATDB tool, by means of its integration into the System process. - The methodology used for the aerothermal characterization of IXV.

Overview of the Mars Sample Return Earth Entry Vehicle

NASA Technical Reports Server (NTRS)

Dillman, Robert; Corliss, James

2008-01-01

NASA's Mars Sample Return (MSR) project will bring Mars surface and atmosphere samples back to Earth for detailed examination. Langley Research Center's MSR Earth Entry Vehicle (EEV) is a core part of the mission, protecting the sample container during atmospheric entry, descent, and landing. Planetary protection requirements demand a higher reliability from the EEV than for any previous planetary entry vehicle. An overview of the EEV design and preliminary analysis is presented, with a follow-on discussion of recommended future design trade studies to be performed over the next several years in support of an MSR launch in 2018 or 2020. Planned topics include vehicle size for impact protection of a range of sample container sizes, outer mold line changes to achieve surface sterilization during re-entry, micrometeoroid protection, aerodynamic stability, thermal protection, and structural materials selection.

The IXV Ground Segment design, implementation and operations

NASA Astrophysics Data System (ADS)

Martucci di Scarfizzi, Giovanni; Bellomo, Alessandro; Musso, Ivano; Bussi, Diego; Rabaioli, Massimo; Santoro, Gianfranco; Billig, Gerhard; Gallego Sanz, José María

2016-07-01

The Intermediate eXperimental Vehicle (IXV) is an ESA re-entry demonstrator that performed, on the 11th February of 2015, a successful re-entry demonstration mission. The project objectives were the design, development, manufacturing and on ground and in flight verification of an autonomous European lifting and aerodynamically controlled re-entry system. For the IXV mission a dedicated Ground Segment was provided. The main subsystems of the IXV Ground Segment were: IXV Mission Control Center (MCC), from where monitoring of the vehicle was performed, as well as support during pre-launch and recovery phases; IXV Ground Stations, used to cover IXV mission by receiving spacecraft telemetry and forwarding it toward the MCC; the IXV Communication Network, deployed to support the operations of the IXV mission by interconnecting all remote sites with MCC, supporting data, voice and video exchange. This paper describes the concept, architecture, development, implementation and operations of the ESA Intermediate Experimental Vehicle (IXV) Ground Segment and outlines the main operations and lessons learned during the preparation and successful execution of the IXV Mission.

Teaching Composition to Re-Entry Students

ERIC Educational Resources Information Center

Foulkes, Natalie; Taines, Beatrice

1978-01-01

Describes the Women's Re-Entry Program at Diablo Valley College which uses structured teaching methods to alleviate the two principal weaknesses found in English compositions written by re-entry women, vagueness and lack of organization. (TP)

Development and flight qualification of the C-SiC thermal protection systems for the IXV

NASA Astrophysics Data System (ADS)

Buffenoir, François; Zeppa, Céline; Pichon, Thierry; Girard, Florent

2016-07-01

The Intermediate experimental Vehicle (IXV) atmospheric re-entry demonstrator, developed within the FLPP (Future Launcher Preparatory Programme) and funded by ESA, aimed at developing a demonstration vehicle that gave Europe a unique opportunity to increase its knowledge in the field of advanced atmospheric re-entry technologies. A key technology that has been demonstrated in real conditions through the flight of this ambitious vehicle is the thermal protection system (TPS) of the Vehicle. Within this programme, HERAKLES, Safran Group, has been in charge of the TPS of the windward and nose assemblies of the vehicle, and has developed and manufactured SepcarbInox® ceramic matrix composite (CMC) protection systems that provided a high temperature resistant non ablative outer mould line (OML) for enhanced aerodynamic control. The design and flight justification of these TPS has been achieved through extensive analysis and testing:

Artist's Concept of X-37 Re-entry

NASA Technical Reports Server (NTRS)

1999-01-01

Pictured is an artist's concept of the experimental X-37 Reusable Launch Vehicle re-entering Earth`s atmosphere. NASA and the Boeing Company entered a cooperative agreement to develop and fly a new experimental space plane called the X-37 that would be ferried into orbit to test new technologies. The reusable space plane incorporated technologies aimed at significantly cutting the cost of space flight. The X-37 would be carried into orbit by the Space Shuttle or be launched by an expendable rocket. After the X-37 was deployed, it would remain in orbit up to 21 days, performing a variety of experiments before re-entering the Earth's atmosphere and landing. The X-37 program was discontinued in 2003.

Guttiferone K impedes cell cycle re-entry of quiescent prostate cancer cells via stabilization of FBXW7 and subsequent c-MYC degradation.

PubMed

Xi, Z; Yao, M; Li, Y; Xie, C; Holst, J; Liu, T; Cai, S; Lao, Y; Tan, H; Xu, H-X; Dong, Q

2016-06-02

Cell cycle re-entry by quiescent cancer cells is an important mechanism for cancer progression. While high levels of c-MYC expression are sufficient for cell cycle re-entry, the modality to block c-MYC expression, and subsequent cell cycle re-entry, is limited. Using reversible quiescence rendered by serum withdrawal or contact inhibition in PTEN(null)/p53(WT) (LNCaP) or PTEN(null)/p53(mut) (PC-3) prostate cancer cells, we have identified a compound that is able to impede cell cycle re-entry through c-MYC. Guttiferone K (GUTK) blocked resumption of DNA synthesis and preserved the cell cycle phase characteristics of quiescent cells after release from the quiescence. In vehicle-treated cells, there was a rapid increase in c-MYC protein levels upon release from the quiescence. However, this increase was inhibited in the presence of GUTK with an associated acceleration in c-MYC protein degradation. The inhibitory effect of GUTK on cell cycle re-entry was significantly reduced in cells overexpressing c-MYC. The protein level of FBXW7, a subunit of E3 ubiquitin ligase responsible for degradation of c-MYC, was reduced upon the release from the quiescence. In contrast, GUTK stabilized FBXW7 protein levels during release from the quiescence. The critical role of FBXW7 was confirmed using siRNA knockdown, which impaired the inhibitory effect of GUTK on c-MYC protein levels and cell cycle re-entry. Administration of GUTK, either in vitro prior to transplantation or in vivo, suppressed the growth of quiescent prostate cancer cell xenografts. Furthermore, elevation of FBXW7 protein levels and reduction of c-MYC protein levels were found in the xenografts of GUTK-treated compared with vehicle-treated mice. Hence, we have identified a compound that is capable of impeding cell cycle re-entry by quiescent PTEN(null)/p53(WT) and PTEN(null)/p53(mut) prostate cancer cells likely by promoting c-MYC protein degradation through stabilization of FBXW7. Its usage as a clinical modality to prevent prostate cancer progression should be further evaluated.

Behavior of HfB2-SiC Materials in Simulated Re-Entry Environments

NASA Technical Reports Server (NTRS)

Ellerby, Don; Beckman, Sarah; Irby, Edward; Johnson, Sylvia M.; Gunsman, Michael; Gasch, Matthew; Ridge, Jerry; Martinez, Ed; Squire, Tom; Olejniczak, Joe

2003-01-01

The objectives of this research are to: 1) Investigate the oxidation/ablation behavior of HfB2/SiC materials in simulated re-entry environments; 2) Use the arc jet test results to define appropriate use environments for these materials for use in vehicle design. The parameters to be investigated include: surface temperature, stagnation pressure, duration, number of cycles, and thermal stresses.

Dynamic and Static High Temperature Resistant Ceramic Seals for X- 38 re-Entry Vehicle

NASA Astrophysics Data System (ADS)

Handrick, Karin E.; Curry, Donald M.

2002-01-01

In a highly successful partnership, NAS A, ESA, DLR (German Space Agency) and European industry are building the X-38, V201 re-entry spacecraft, the prototype of the International Space Station's Crew Return Vehicle (CRV). This vehicle would serve both as an ambulance for medical emergencies and as an evacuation vehicle for the Space Station. The development of essential systems and technologies for a reusable re-entry vehicle is a first for Europe, and sharing the development of an advanced re-entry spacecraft with foreign partners is a first for NASA. NASA, in addition to its subsystem responsibilities, is performing overall X-38 vehicle system engineering and integration, will launch V201 on the Space Shuttle, deliver flight data for post-flight analysis and assessment and is responsible for development and manufacture of structural vehicle components and thermal protection (TPS) tiles. The major European objective for cooperation with NASA on X-38 was to establish a clear path through which key technologies needed for future space transportation systems could be developed and validated at affordable cost and with controlled risk. Europe has taken the responsibility to design and manufacture hot control surfaces like metallic rudders and ceramic matrix composites (CMC) body flaps, thermal protection systems such as CMC leading edges, the CMC nose cap and -skirt, insulation, landing gears and elements of the V201 primary structure. Especially hot control surfaces require extremely high temperature resistant seals to limit hot gas ingestion and transfer of heat to underlying low-temperature structures to prevent overheating of these structures and possible loss of the vehicle. Complex seal interfaces, which have to fulfill various, tight mission- and vehicle-related requirements exist between the moveable ceramic body flaps and the bottom surface of the vehicle, between the rudder and fin structure and the ceramic leading edge panel and TPS tiles. While NASA concentrated on the development, qualification and manufacture of dynamic seals in the rudder area, the responsibility of MAN Technologie focused on the development, lay-out, qualification and flight hardware manufacture of static and dynamic seals in ceramic hot structures' associated gaps and interfaces, dealing with re-entry temperatures up to 1600°C. This paper presents results for temperature and mechanical stability, flow, scrub (up to 1000 cycles) and of arc jet tests under representative low boundary conditions and plasma step/gap tests, conducted during the development and qualification phases of these different kind of ceramic seals. Room temperature seal compression tests were performed at low compression levels to determine load versus linear compression, preload, contact area, stiffness and resiliency characteristics under low load conditions. Flow tests with thermally aged seals were conducted at ambient temperature to examine leakage at low compression levels and in as-manufactured conditions. Seal scrub tests were performed to examine durability and wear resistance and to recommend surface treatments required to maximize seal wear life. Results of arc jet/plasma tests under simulated re-entry conditions (pressure, temperature) verified seal temperature stability and function under representative assembly and interface conditions. Each of these specifically developed seals fulfilled the requirements and is qualified for flight on X-38, V201.

Casualty Risk Assessment Controlled Re-Entry of EPS - Ariane 5ES - ATV Mission

NASA Astrophysics Data System (ADS)

Arnal, M.-H.; Laine, N.; Aussilhou, C.

2012-01-01

To fulfil its mission of compliance check to the French Space Operations Act, CNES has developed ELECTRA© tool in order to estimate casualty risk induced by a space activity (like rocket launch, controlled or un-controlled re-entry on Earth of a space object). This article describes the application of such a tool for the EPS controlled re-entry during the second Ariane 5E/S flight (Johannes Kepler mission has been launched in February 2011). EPS is the Ariane 5E/S upper composite which is de-orbited from a 260 km circular orbit after its main mission (release of the Automated Transfer Vehicle - ATV). After a brief description of the launcher, the ATV-mission and a description of all the failure cases taken into account in the mission design (which leads to "back-up scenarios" into the flight software program), the article will describe the steps which lead to the casualty risk assessment (in case of failure) with ELECTRA©. In particular, the presence on board of two propulsive means of de-orbiting (main engine of EPS, and 4 ACS longitudinal nozzles in case of main engine failure or exhaustion) leads to a low remaining casualty risk.

ASTRONAUTICS INFORMATION. OPEN LITERATURE SURVEY, VOLUME III, NO. 2 (ENTRIES 30,202-30,404)

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

None

1961-02-01

<>15:014925. An annotated list of references on temperature control of satellite and space vehicles is presented. Methods and systems for maintaining vehicles within tolerable temperature bounds while operating outside planetary atmospheres are outlined. Discussions of the temperature environment in space and how it might affect vehicle operation are given. Re-entry heating problems are not included. Among the sources used were: Engineering Index, Applied Science and Technology Index, Astronautics Abstracts, PAL uniterm index, ASTIA, and LMSD card catalog. (auth)

Guidance/Navigation Requirements Study Final Report. Volume III. Appendices

DTIC Science & Technology

1978-04-30

shown Figure G-2. The free-flight simulation program FFSIM uses quaternions to calculate the body attitude as a function of time. To calculate the...the lack of open-loop damping, the existence of a feedback controller which will stabilize the closed-loon system depends upon the satisfaction of a...re-entry vehicle has dynamic pecularitles which tend to discourage the use of "linear-quadratic" feedback regulators in guidance. The disadvantageous

Planetary Mission Entry Vehicles Quick Reference Guide. Version 3.0

NASA Technical Reports Server (NTRS)

Davies, Carol; Arcadi, Marla

2006-01-01

This is Version 3.0 of the planetary mission entry vehicle document. Three new missions, Re-entry F, Hayabusa, and ARD have been added to t he previously published edition (Version 2.1). In addition, the Huyge ns mission has been significantly updated and some Apollo data correc ted. Due to the changing nature of planetary vehicles during the desi gn, manufacture and mission phases, and to the variables involved in measurement and computation, please be aware that the data provided h erein cannot be guaranteed. Contact Carol Davies at cdavies@mail.arc. nasa.gov to correct or update the current data, or to suggest other missions.

Design Criteria for Low Risk Re-Entry Vehicles

NASA Astrophysics Data System (ADS)

Monti, R.; Pezzella, G.

2005-02-01

The paper shows how a sharp vehicle with low wing loading, is able to follow re-entry trajectories with low thermal risks by using Ultra High Temperature Ceramics (UHTC) to thermally protect the vehicle front edges. These reusable materials can withstand the global radiative equilibrium temperatures that are experienced during reentry characterized by a longer and a more gradual conversion of the kinetic and potential energy of the vehicle into thermal energy. A number of aerothermodynamic problems are addressed to assess the feasibility of the vehicle design and of the thermal protection of the payload. In particular, the boundary layer thermal protection concept is illustrated to show how a UHTC massive tip edges (fuselage and wings) are able to protect also the remaining vehicle structure made of conventional material, promoting a revolutionary approach to the Thermal Protection System (TPS) configuration for hypersonic vehicle flying at small angle of attack. CFD results and engineering formulations are adopted for the computation of the aerodynamic coefficients and heat fluxes. The analysis identifies the design criteria for a conventional looking vehicle for a crew return from LEO (e.g. from the International Space Station).

Returning nurses to the workforce: developing a fast track back program.

PubMed

Burns, Helen K; Sakraida, Teresa J; Englert, Nadine C; Hoffmann, Rosemary L; Tuite, Patricia; Foley, Susan M

2006-01-01

Fast Track Back: Re-entry into Nursing Practice program. Describes the development, implementation, and evaluation of a state-of-the-art re-entry program facilitating the return of licensed nonpracticing RNs to the workforce through a quality education program that retools them for the workforce in the areas of pharmacology, skill development using the latest technology, practice standards, and nursing issues. The program consists of didactic content taught via classroom, Internet, skills laboratory, and high fidelity human simulated technology and a clinical component. The program is a mechanism that enables re-entry nurses to improve skills and competencies necessary to practice in today's healthcare environment.

Space Shuttle Projects

NASA Image and Video Library

1986-01-01

Columbia, which opened the era of the Space Transportation System with four orbital flight tests, is featured in re-entry in the emblem designed by the STS-61C crew representing the seven team members who manned the vehicle for its seventh STS mission. Gold lettering against black background honors the astronaut crewmembers on the delta pattern surrounding colorful re-entry shock waves, and the payload specialists are honored similarly below the sphere

Simulation of launch and re-entry acceleration profiles for testing of shuttle and unmanned microgravity research payloads

NASA Astrophysics Data System (ADS)

Cassanto, J. M.; Ziserman, H. I.; Chapman, D. K.; Korszun, Z. R.; Todd, P.

Microgravity experiments designed for execution in Get-Away Special canisters, Hitchhiker modules, and Reusable Re-entry Satellites will be subjected to launch and re-entry accelerations. Crew-dependent provisions for preventing acceleration damage to equipment or products will not be available for these payloads during flight; therefore, the effects of launch and re-entry accelerations on all aspects of such payloads must be evaluated prior to flight. A procedure was developed for conveniently simulating the launch and re-entry acceleration profiles of the Space Shuttle (3.3 and 1.7 × g maximum, respectively) and of two versions of NASA's proposed materials research Re-usable Re-entry Satellite (8 × g maximum in one case and 4 × g in the other). By using the 7 m centrifuge of the Gravitational Plant Physiology Laboratory in Philadelphia it was found possible to simulate the time dependence of these 5 different acceleration episodes for payload masses up to 59 kg. A commercial low-cost payload device, the “Materials Dispersion Apparatus” of Instrumentation Technology Associates was tested for (1) integrity of mechanical function, (2) retention of fluid in its compartments, and (3) integrity of products under simulated re-entry g-loads. In particular, the sharp rise from 1 g to maximum g-loading that occurs during re-entry in various unmanned vehicles was successfully simulated, conditions were established for reliable functioning of the MDA, and crystals of 5 proteins suspended in compartments filled with mother liquor were subjected to this acceleration load.

Re-Thinking Re-Entry: New Approaches to Supporting Students after Study Abroad

ERIC Educational Resources Information Center

Brubaker, Cate

2017-01-01

While participation in study abroad continues to increase, and both pre-departure and in-country support and interventions have become more robust, the re-entry experience after a program ends still typically takes a back seat to other priorities. Consequently, most students are left to navigate the re-entry transition on their own. This article…

Overview of Orion Crew Module and Launch Abort Vehicle Dynamic Stability

NASA Technical Reports Server (NTRS)

Owens, Donald B.; Aibicjpm. Vamessa V.

2011-01-01

With the retirement of the Space Shuttle, NASA is designing a new spacecraft, called Orion, to fly astronauts to low earth orbit and beyond. Characterization of the dynamic stability of the Orion spacecraft is important for the design of the spacecraft and trajectory construction. Dynamic stability affects the stability and control of the Orion Crew Module during re-entry, especially below Mach = 2.0 and including flight under the drogues. The Launch Abort Vehicle is affected by dynamic stability as well, especially during the re-orientation and heatshield forward segments of the flight. The dynamic stability was assessed using the forced oscillation technique, free-to-oscillate, ballistic range, and sub-scale free-flight tests. All of the test techniques demonstrated that in heatshield-forward flight the Crew Module and Launch Abort Vehicle are dynamically unstable in a significant portion of their flight trajectory. This paper will provide a brief overview of the Orion dynamic aero program and a high-level summary of the dynamic stability characteristics of the Orion spacecraft.

Orion Entry Display Feeder and Interactions with the Entry Monitor System

NASA Technical Reports Server (NTRS)

Baird, Darren; Bernatovich, Mike; Gillespie, Ellen; Kadwa, Binaifer; Matthews, Dave; Penny, Wes; Zak, Tim; Grant, Mike; Bihari, Brian

2010-01-01

The Orion spacecraft is designed to return astronauts to a landing within 10 km of the intended landing target from low Earth orbit, lunar direct-entry, and lunar skip-entry trajectories. Al pile the landing is nominally controlled autonomously, the crew can fly precision entries manually in the event of an anomaly. The onboard entry displays will be used by the crew to monitor and manually fly the entry, descent, and landing, while the Entry Monitor System (EMS) will be used to monitor the health and status of the onboard guidance and the trajectory. The entry displays are driven by the entry display feeder, part of the Entry Monitor System (EMS). The entry re-targeting module, also part of the EMS, provides all the data required to generate the capability footprint of the vehicle at any point in the trajectory, which is shown on the Primary Flight Display (PFD). It also provides caution and warning data and recommends the safest possible re-designated landing site when the nominal landing site is no longer within the capability of the vehicle. The PFD and the EMS allow the crew to manually fly an entry trajectory profile from entry interface until parachute deploy having the flexibility to manually steer the vehicle to a selected landing site that best satisfies the priorities of the crew. The entry display feeder provides data from the ENIS and other components of the GNC flight software to the displays at the proper rate and in the proper units. It also performs calculations that are specific to the entry displays and which are not made in any other component of the flight software. In some instances, it performs calculations identical to those performed by the onboard primary guidance algorithm to protect against a guidance system failure. These functions and the interactions between the entry display feeder and the other components of the EMS are described.

Entry Atmospheric Flight Control Authority Impacts on GN and C and Trajectory Performance for Orion Exploration Flight Test 1

NASA Technical Reports Server (NTRS)

McNamara, Luke W.

2012-01-01

One of the key design objectives of NASA's Orion Exploration Flight Test 1 (EFT-1) is to execute a guided entry trajectory demonstrating GN&C capability. The focus of this paper is the ight control authority of the vehicle throughout the atmospheric entry ight to the target landing site and its impacts on GN&C, parachute deployment, and integrated performance. The vehicle's attitude control authority is obtained from thrusting 12 Re- action Control System (RCS) engines, with four engines to control yaw, four engines to control pitch, and four engines to control roll. The static and dynamic stability derivatives of the vehicle are determined to assess the inherent aerodynamic stability. The aerodynamic moments at various locations in the entry trajectory are calculated and compared to the available torque provided by the RCS system. Interaction between the vehicle's RCS engine plumes and the aerodynamic conditions are considered to assess thruster effectiveness. This document presents an assessment of Orion's ight control authority and its effectiveness in controlling the vehicle during critical events in the atmospheric entry trajectory.

Instrumentation Development for Large Scale Hypersonic Inflatable Aerodynamic Decelerator Characterization

NASA Technical Reports Server (NTRS)

Swanson, Gregory T.; Cassell, Alan M.

2011-01-01

Hypersonic Inflatable Aerodynamic Decelerator (HIAD) technology is currently being considered for multiple atmospheric entry applications as the limitations of traditional entry vehicles have been reached. The Inflatable Re-entry Vehicle Experiment (IRVE) has successfully demonstrated this technology as a viable candidate with a 3.0 m diameter vehicle sub-orbital flight. To further this technology, large scale HIADs (6.0 8.5 m) must be developed and tested. To characterize the performance of large scale HIAD technology new instrumentation concepts must be developed to accommodate the flexible nature inflatable aeroshell. Many of the concepts that are under consideration for the HIAD FY12 subsonic wind tunnel test series are discussed below.

Potential applications of skip SMV with thrust engine

NASA Astrophysics Data System (ADS)

Wang, Weilin; Savvaris, Al

2016-11-01

This paper investigates the potential applications of Space Maneuver Vehicles (SMV) with skip trajectory. Due to soaring space operations over the past decades, the risk of space debris has considerably increased such as collision risks with space asset, human property on ground and even aviation. Many active debris removal methods have been investigated and in this paper, a debris remediation method is first proposed based on skip SMV. The key point is to perform controlled re-entry. These vehicles are expected to achieve a trans-atmospheric maneuver with thrust engine. If debris is released at altitude below 80 km, debris could be captured by the atmosphere drag force and re-entry interface prediction accuracy is improved. Moreover if the debris is released in a cargo at a much lower altitude, this technique protects high value space asset from break up by the atmosphere and improves landing accuracy. To demonstrate the feasibility of this concept, the present paper presents the simulation results for two specific mission profiles: (1) descent to predetermined altitude; (2) descent to predetermined point (altitude, longitude and latitude). The evolutionary collocation method is adopted for skip trajectory optimization due to its global optimality and high-accuracy. This method is actually a two-step optimization approach based on the heuristic algorithm and the collocation method. The optimal-control problem is transformed into a nonlinear programming problem (NLP) which can be efficiently and accurately solved by the sequential quadratic programming (SQP) procedure. However, such a method is sensitive to initial values. To reduce the sensitivity problem, genetic algorithm (GA) is adopted to refine the grids and provide near optimum initial values. By comparing the simulation data from different scenarios, it is found that skip SMV is feasible in active debris removal and the evolutionary collocation method gives a truthful re-entry trajectory that satisfies the path and boundary constraints.

IRVE-3 Post-Flight Reconstruction

NASA Technical Reports Server (NTRS)

Olds, Aaron D.; Beck, Roger; Bose, David; White, Joseph; Edquist, Karl; Hollis, Brian; Lindell, Michael; Cheatwood, F. N.; Gsell, Valerie; Bowden, Ernest

2013-01-01

The Inflatable Re-entry Vehicle Experiment 3 (IRVE-3) was conducted from the NASA Wallops Flight Facility on July 23, 2012. Launched on a Black Brant XI sounding rocket, the IRVE-3 research vehicle achieved an apogee of 469 km, deployed and inflated a Hypersonic Inflatable Aerodynamic Decelerator (HIAD), re-entered the Earth's atmosphere at Mach 10 and achieved a peak deceleration of 20 g's before descending to splashdown roughly 20 minutes after launch. This paper presents the filtering methodology and results associated with the development of the Best Estimated Trajectory of the IRVE-3 flight test. The reconstructed trajectory is compared against project requirements and pre-flight predictions of entry state, aerodynamics, HIAD flexibility, and attitude control system performance.

Inflatable re-entry shield ready for test in space

NASA Astrophysics Data System (ADS)

2000-02-01

The Russian spacecraft Mars'96 for instance, which was launched in November 1996 but failed to reach its nominal orbit, carried two modules designed to land on that planet's surface. For the last part of the mission, an Inflatable Re-Entry and Descent Technology (IRDT) had been deployed. The main components of this system were an aerobraking and thermally protective shell, a densely packed inflating material and a pressurisation system. This technology is now considered applicable to other re-entry scenarios such as payload recovery from the International Space Station, planetary landers for science missions and atmospheric research. A demonstration mission on 9/10 February 2000 will evaluate the performance of this new technology before it is offered to potential users. A Russian Soyuz/Fregat launcher, lifting off from the Kazakh steppe near Baikonur, will provide a low-cost flight opportunity for the test vehicle, which is equipped with the inflatable heat shield and a sensor package developed by DaimlerChrysler Aerospace (DASA). After four orbits around the Earth, the test vehicle will be powered by the launcher's upper stage to re-enter the atmosphere for a landing the next day about 1800 km north-west of the launch site. During the mission, a number of technical parameters such as pressure, temperature and deceleration will be monitored and the inflation of the re-entry/descent structure observed. "From this novel technology, we are expecting a major breakthrough, to make re-entry of small payloads more and more reliable, simpler and less costly than traditional systems", explains Dieter Kassing, ESA's IRDT project manager. One of the main instruments on board the test vehicle is a sensor device developed by the University of Stuttgart for the determination of oxygen partial pressure in low Earth orbit and during re-entry. The scientific/technical investigations will be led by Dr. Ulrich Schoettle (Stuttgart University). Lionel Marraffa (ESA) will lead the evaluation of the IRDT's aerothermodynamic behaviour. DASA was responsible for integration of the sensor package and is ESA's co-investigator for evaluation of the application aspects of this new technology. In addition to the sensor package, the mission will accommodate a collection of special stones to study the physical and chemical modifications in sedimentary rocks, i.e. simulated meteorites, during atmospheric infall. Co-investors of this experiment are Dr. André Brack (CNRS, Orleans) and Dr. Gero Kurat (Vienna University). This experiment is being co-sponsored by ESA. The Russian/European Starsem launch company and NPO Lavochkin, the Russian company that developed the original IRDT technology, will be responsible for launch, orbit control, re-entry and recovery of the sensor package under contract with the International Science & Technology Centre (Moscow). ESA, the European Commission and DASA are co-funding this contract, contributing $600K each.

Orion Exploration Flight Test-1 (EFT-1) Absolute Navigation Performance

NASA Technical Reports Server (NTRS)

Zanetti, Renato

2015-01-01

The Orion vehicle, being design to take men back to the Moon and beyond, successfully completed its first flight test, EFT-1 (Exploration Flight Test-1), on December 5th, 2014. The main objective of the test was to demonstrate the capability of re-enter into the Earth's atmosphere and safely splash-down into the pacific ocean. This un-crewed mission completes two orbits around Earth, the second of which is highly elliptical with an apogee of approximately 5908 km, higher than any vehicle designed for humans has been since the Apollo program. The trajectory was designed in order to test a high-energy re-entry similar to those crews will undergo during lunar missions. The mission overview is shown in Figure 1. The objective of this paper is to document the performance of the absolute navigation system during EFT-1 and to present its design.

Thermal Management Design for the X-33 Lifting Body

NASA Technical Reports Server (NTRS)

Bouslog, S.; Mammano, J.; Strauss, B.

1998-01-01

The X-33 Advantage Technology Demonstrator offers a rare and exciting opportunity in Thermal Protection System development. The experimental program incorporates the latest design innovation in re-useable, low life cycle cost, and highly dependable Thermal Protection materials and constructions into both ground based and flight test vehicle validations. The unique attributes of the X-33 demonstrator for design application validation for the full scale Reusable Launch Vehicle, (RLV), are represented by both the configuration of the stand-off aeroshell, and the extreme exposures of sub-orbital hypersonic re-entry simulation. There are several challenges of producing a sub-orbital prototype demonstrator of Single Stage to Orbit/Reusable Launch Vehicle (SSTO/RLV) operations. An aggressive schedule with budgetary constraints precludes the opportunity for an extensive verification and qualification program of vehicle flight hardware. However, taking advantage of off the shelf components with proven technologies reduces some of the requirements for additional testing. The effects of scale on thermal heating rates must also be taken into account during trajectory design and analysis. Described in this document are the unique Thermal Protection System (TPS) design opportunities that are available with the lifting body configuration of the X-33. The two principal objectives for the TPS are to shield the primary airframe structure from excessive thermal loads and to provide an aerodynamic mold line surface. With the relatively benign aeroheating capability of the lifting body, an integrated stand-off aeroshell design with minimal weight and reduced procurement and operational costs is allowed. This paper summarizes the design objectives of the X-33 TPS, the flight test requirements driven configuration, and design benefits. Comparisons are made of the X-33 flight profiles and Space Shuttle Orbiter, and lifting body Reusable Launch Vehicle aerothermal environments. The X-33 TPS is based on a design to cost configuration concept. Only RLV critical technologies are verified to conform to cost and schedule restrictions. The one-off prototype vehicle configuration has evolved to minimize the tooling costs by reducing the number of unique components. Low cost approaches such as a composite/blanket leeward aeroshell and the use of Shuttle technology are implemented where applicable. The success of the X-33 will overcome the ballistic re-entry TPS mindset. The X-33 TPS is tailored to an aircraft type mission while maintaining sufficient operational margins. The flight test program for the X-33 will demonstrate that TPS for the RLV is not simply a surface insulation but rather an integrated aeroshell system.

ATV-3 undock from ISS

NASA Image and Video Library

2012-09-28

ISS033-E-007940 (28 Sept. 2012) --- European Space Agency's "Edoardo Amaldi" Automated Transfer Vehicle-3 (ATV-3) begins its relative separation from the International Space Station during the Expedition 33 mission. The ATV-3 undocked from the aft port of the Zvezda Service Module at 5:44 p.m. (EDT) on Sept. 28, 2012. The ATV-3 is scheduled to deorbit on Oct. 2 for a fiery re-entry over the Pacific Ocean that will destroy the trash-filled spacecraft. Inside the ATV-3 is the Re-Entry Breakup Recorder that will record various data such as temperature, pressure and speed as the resupply craft burns up during its return to Earth. Experts will use that data to design safer and more predictable destructive re-entry techniques.

ATV-3 undock from ISS

NASA Image and Video Library

2012-09-28

ISS033-E-008016 (28 Sept. 2012) --- European Space Agency's "Edoardo Amaldi" Automated Transfer Vehicle-3 (ATV-3) begins its relative separation from the International Space Station during the Expedition 33 mission. The ATV-3 undocked from the aft port of the Zvezda Service Module at 5:44 p.m. (EDT) on Sept. 28, 2012. The ATV-3 is scheduled to deorbit on Oct. 2 for a fiery re-entry over the Pacific Ocean that will destroy the trash-filled spacecraft. Inside the ATV-3 is the Re-Entry Breakup Recorder that will record various data such as temperature, pressure and speed as the resupply craft burns up during its return to Earth. Experts will use that data to design safer and more predictable destructive re-entry techniques.

ATV-3 undock from ISS

NASA Image and Video Library

2012-09-28

ISS033-E-007980 (28 Sept. 2012) --- European Space Agency's "Edoardo Amaldi" Automated Transfer Vehicle-3 (ATV-3) begins its relative separation from the International Space Station during the Expedition 33 mission. The ATV-3 undocked from the aft port of the Zvezda Service Module at 5:44 p.m. (EDT) on Sept. 28, 2012. The ATV-3 is scheduled to deorbit on Oct. 2 for a fiery re-entry over the Pacific Ocean that will destroy the trash-filled spacecraft. Inside the ATV-3 is the Re-Entry Breakup Recorder that will record various data such as temperature, pressure and speed as the resupply craft burns up during its return to Earth. Experts will use that data to design safer and more predictable destructive re-entry techniques.

ATV-3 undock from ISS

NASA Image and Video Library

2012-09-28

ISS033-E-007915 (28 Sept. 2012) --- European Space Agency's "Edoardo Amaldi" Automated Transfer Vehicle-3 (ATV-3) begins its relative separation from the International Space Station during the Expedition 33 mission. The ATV-3 undocked from the aft port of the Zvezda Service Module at 5:44 p.m. (EDT) on Sept. 28, 2012. The ATV-3 is scheduled to deorbit on Oct. 2 for a fiery re-entry over the Pacific Ocean that will destroy the trash-filled spacecraft. Inside the ATV-3 is the Re-Entry Breakup Recorder that will record various data such as temperature, pressure and speed as the resupply craft burns up during its return to Earth. Experts will use that data to design safer and more predictable destructive re-entry techniques.

ATV-3 undock from ISS

NASA Image and Video Library

2012-09-28

ISS033-E-007920 (28 Sept. 2012) --- European Space Agency's "Edoardo Amaldi" Automated Transfer Vehicle-3 (ATV-3) begins its relative separation from the International Space Station during the Expedition 33 mission. The ATV-3 undocked from the aft port of the Zvezda Service Module at 5:44 p.m. (EDT) on Sept. 28, 2012. The ATV-3 is scheduled to deorbit on Oct. 2 for a fiery re-entry over the Pacific Ocean that will destroy the trash-filled spacecraft. Inside the ATV-3 is the Re-Entry Breakup Recorder that will record various data such as temperature, pressure and speed as the resupply craft burns up during its return to Earth. Experts will use that data to design safer and more predictable destructive re-entry techniques.

Instrumentation Of C-Sic Tiles To Quantify Their Mechanical Behavior During Atmospheric Re-Entry

NASA Astrophysics Data System (ADS)

Pereira, C.; Romano, R.; Walz, S.; Schwarz, R.; Fremont, E.; Girard, F.

2011-05-01

The windward surfaces of re-entry vehicles are exposed to large thermal gradients and pressure loadings which result in changes to the surface topology and high transient loading of fixation elements. In particular positive steps result in local aero-thermodynamic effects with increased thermal loading of the adjacent tiles. An objective of the in-flight instrumentation of IXV is to document the aerodynamic and thermal loads on the tiles including deflection and the evolution of steps along the vehicle. To this end a combination of high temperature strain gauges and thermocouples will be placed at the metallic stand-offs behind the highest loaded tiles and on one half of the nose cap attachments. The deflection at the edges of the tiles and the steps will be measured using linear variable differential sensors (L VDT). This paper presents background information, the rationale for the chosen measurement points, the design evolution and the validation of the instrumentation both in terms of functionality and ability to withstand the launch and re-entry environment of the IXV

Education for Perspective Transformation. Women's Re-entry Programs in Community Colleges.

ERIC Educational Resources Information Center

Mezirow, Jack; Marsick, Victoria

The national field study of women's re-entry programs in community colleges reported here was done to identify factors that impeded or facilitated the progress of these programs. After an introduction, the content is presented in three sections. The first section deals with perspective transformation, the adult development process occurring in the…

Conceptual design of an Orbital Debris Defense System

NASA Technical Reports Server (NTRS)

Bedillion, Erik; Blevins, Gary; Bohs, Brian; Bragg, David; Brown, Christopher; Casanova, Jose; Cribbs, David; Demko, Richard; Henry, Brian; James, Kelly

1994-01-01

Man made orbital debris has become a serious problem. Currently NORAD tracks over 7000 objects in orbit and less than 10 percent of these are active payloads. Common estimates are that the amount of debris will increase at a rate of 10 percent per year. Impacts of space debris with operational payloads or vehicles is a serious risk to human safety and mission success. For example, the impact of a 0.2 mm diameter paint fleck with the Space Shuttle Challenger window created a 2 mm wide by 0.6 mm deep pit. The cost to replace the window was over $50,000. A conceptual design for a Orbital Debris Defense System (ODDS) is presented which considers a wide range of debris sizes, orbits and velocities. Two vehicles were designed to collect and remove space debris. The first would attach a re-entry package to de-orbit very large debris, e.g. inactive satellites and spent upper stages that tend to break up and form small debris. This vehicle was designed to contain several re-entry packages, and be refueled and resupplied with more re-entry packages as needed. The second vehicle was designed to rendezvous with and capture debris ranging from 10 cm to 2 m. Due to tracking limitations, no technically feasible method for collecting debris below 10 cm in size could be devised; it must be accomplished through international regulations which reduce the accumulation of space debris.

Optimization of entry-vehicle shapes during conceptual design

NASA Astrophysics Data System (ADS)

Dirkx, D.; Mooij, E.

2014-01-01

During the conceptual design of a re-entry vehicle, the vehicle shape and geometry can be varied and its impact on performance can be evaluated. In this study, the shape optimization of two classes of vehicles has been studied: a capsule and a winged vehicle. Their aerodynamic characteristics were analyzed using local-inclination methods, automatically selected per vehicle segment. Entry trajectories down to Mach 3 were calculated assuming trimmed conditions. For the winged vehicle, which has both a body flap and elevons, a guidance algorithm to track a reference heat-rate was used. Multi-objective particle swarm optimization was used to optimize the shape using objectives related to mass, volume and range. The optimizations show a large variation in vehicle performance over the explored parameter space. Areas of very strong non-linearity are observed in the direct neighborhood of the two-dimensional Pareto fronts. This indicates the need for robust exploration of the influence of vehicle shapes on system performance during engineering trade-offs, which are performed during conceptual design. A number of important aspects of the influence of vehicle behavior on the Pareto fronts are observed and discussed. There is a nearly complete convergence to narrow-wing solutions for the winged vehicle. Also, it is found that imposing pitch-stability for the winged vehicle at all angles of attack results in vehicle shapes which require upward control surface deflections during the majority of the entry.

Thermal Vacuum Facility for Testing Thermal Protection Systems

NASA Technical Reports Server (NTRS)

Daryabeigi, Kamran; Knutson, Jeffrey R.; Sikora, Joseph G.

2002-01-01

A thermal vacuum facility for testing launch vehicle thermal protection systems by subjecting them to transient thermal conditions simulating re-entry aerodynamic heating is described. Re-entry heating is simulated by controlling the test specimen surface temperature and the environmental pressure in the chamber. Design requirements for simulating re-entry conditions are briefly described. A description of the thermal vacuum facility, the quartz lamp array and the control system is provided. The facility was evaluated by subjecting an 18 by 36 in. Inconel honeycomb panel to a typical re-entry pressure and surface temperature profile. For most of the test duration, the average difference between the measured and desired pressures was 1.6% of reading with a standard deviation of +/- 7.4%, while the average difference between measured and desired temperatures was 7.6% of reading with a standard deviation of +/- 6.5%. The temperature non-uniformity across the panel was 12% during the initial heating phase (t less than 500 sec.), and less than 2% during the remainder of the test.

Parametric Study of Cantilever Plates Exposed to Supersonic and Hypersonic Flows

NASA Astrophysics Data System (ADS)

Sri Harsha, A.; Rizwan, M.; Kuldeep, S.; Giridhara Prasad, A.; Akhil, J.; Nagaraja, S. R.

2017-08-01

Analysis of hypersonic flows associated with re-entry vehicles has gained a lot of significance due to the advancements in Aerospace Engineering. An area that is studied extensively by researchers is the simultaneous reduction aerodynamic drag and aero heating in re-entry vehicles. Out of the many strategies being studied, the use of aerospikes at the stagnation point of the vehicle is found to give favourable results. The structural stability of the aerospike becomes important as it is exposed to very high pressures and temperatures. Keeping this in view, the deflection and vibration of an inclined cantilever plate in hypersonic flow is carried out using ANSYS. Steady state pressure distribution obtained from Fluent is applied as load to the transient structural module for analysis. After due validation of the methods, the effects of parameters like flow Mach number, plate inclination and plate thickness on the deflection and vibration are studied.

Constellation crew exploration vehicle, or CEV, is being prepare

NASA Image and Video Library

2007-11-27

In Hangar N at NASA's Kennedy Space Center, a heat shield for the Constellation crew exploration vehicle, or CEV, is being prepared for a demonstration. A developmental heat shield for the Orion spacecraft is being tested and evaluated at Kennedy. The shield was designed and assembled by the Boeing Company in Huntington Beach, Calif., for NASA's Constellation Program. The thermal protection system manufacturing demonstration unit is designed to protect astronauts from extreme heat during re-entry to Earth's atmosphere from low Earth orbit and lunar missions. The CEV will be used to dock and gain access to the International Space Station, travel to the moon in the 2018 timeframe and play a crucial role in exploring Mars.

Ongoing Capabilities and Developments of Re-Entry Plasma Ground Tests at EADS-ASTRIUM

NASA Technical Reports Server (NTRS)

Jullien, Pierre

2008-01-01

During re-entry, spacecrafts are subjected to extreme thermal loads. On mars, they may go through dust storms. These external heat loads are leading the design of re-entry vehicles or are affecting it for spacecraft facing solid propellant jet stream. Sizing the Thermal Protection System require a good knowledge of such solicitations and means to model and reproduce them on earth. Through its work on European projects, ASTRIUM has developed the full range of competences to deal with such issues. For instance, we have designed and tested the heat-shield of the Huygens probe which landed on Titan. In particular, our plasma generators aim to reproduce a wide variety of re-entry conditions. Heat loads are generated by the huge speed of the probes. Such conditions cannot be fully reproduced. Ground tests focus on reproducing local aerothermal loads by using slower but hotter flows. Our inductive plasma torch enables to test little samples at low TRL. Amongst the arc-jets, one was design to test architecture design of ISS crew return system and others fit more severe re-entry such as sample returns or Venus re-entry. The last developments aimed in testing samples in seeded flows. First step was to design and test the seeding device. Special diagnostics characterizing the resulting flow enabled us to fit it to the requirements.

Access from Space: A New Perspective on NASA's Space Transportation Technology Requirements and Opportunities

NASA Technical Reports Server (NTRS)

Rasky, Daniel J.

2004-01-01

The need for robust and reliable access from space is clearly demonstrated by the recent loss of the Space Shuttle Columbia; as well as the NASA s goals to get the Shuttle re-flying and extend its life, build new vehicles for space access, produce successful robotic landers and s a q k retrr? llisrions, and maximize the science content of ambitious outer planets missions that contain nuclear reactors which must be safe for re-entry after possible launch aborts. The technology lynch pin of access from space is hypersonic entry systems such the thermal protection system, along with navigation, guidance and control (NG&C). But it also extends to descent and landing systems such as parachutes, airbags and their control systems. Current space access technology maturation programs such as NASA s Next Generation Launch Technology (NGLT) program or the In-Space Propulsion (ISP) program focus on maturing laboratory demonstrated technologies for potential adoption by specific mission applications. A key requirement for these programs success is a suitable queue of innovative technologies and advanced concepts to mature, including mission concepts enabled by innovative, cross cutting technology advancements. When considering space access, propulsion often dominates the capability requirements, as well as the attention and resources. From the perspective of access from space some new cross cutting technology drivers come into view, along with some new capability opportunities. These include new miniature vehicles (micro, nano, and picosats), advanced automated systems (providing autonomous on-orbit inspection or landing site selection), and transformable aeroshells (to maximize capabilities and minimize weight). This paper provides an assessment of the technology drivers needed to meet future access from space mission requirements, along with the mission capabilities that can be envisioned from innovative, cross cutting access from space technology developments.

An Automated Method to Compute Orbital Re-entry Trajectories with Heating Constraints

NASA Technical Reports Server (NTRS)

Zimmerman, Curtis; Dukeman, Greg; Hanson, John; Fogle, Frank R. (Technical Monitor)

2002-01-01

Determining how to properly manipulate the controls of a re-entering re-usable launch vehicle (RLV) so that it is able to safely return to Earth and land involves the solution of a two-point boundary value problem (TPBVP). This problem, which can be quite difficult, is traditionally solved on the ground prior to flight. If necessary, a nearly unlimited amount of time is available to find the 'best' solution using a variety of trajectory design and optimization tools. The role of entry guidance during flight is to follow the pre- determined reference solution while correcting for any errors encountered along the way. This guidance method is both highly reliable and very efficient in terms of onboard computer resources. There is a growing interest in a style of entry guidance that places the responsibility of solving the TPBVP in the actual entry guidance flight software. Here there is very limited computer time. The powerful, but finicky, mathematical tools used by trajectory designers on the ground cannot in general be converted to do the job. Non-convergence or slow convergence can result in disaster. The challenges of designing such an algorithm are numerous and difficult. Yet the payoff (in the form of decreased operational costs and increased safety) can be substantiaL This paper presents an algorithm that incorporates features of both types of guidance strategies. It takes an initial RLV orbital re-entry state and finds a trajectory that will safely transport the vehicle to Earth. During actual flight, the computed trajectory is used as the reference to be flown by a more traditional guidance method.

7 CFR 1530.109 - Reporting.

Code of Federal Regulations, 2012 CFR

2012-01-01

... AGRICULTURE THE REFINED SUGAR RE-EXPORT PROGRAM, THE SUGAR CONTAINING PRODUCTS RE-EXPORT PROGRAM, AND THE... transaction; (2) The date of the entry, transfer (only a refiner shall report transfers to the Licensing... license number; (5) The country of origin (entry of raw sugar) or final destination (refined exports...

7 CFR 1530.109 - Reporting.

Code of Federal Regulations, 2013 CFR

2013-01-01

... AGRICULTURE THE REFINED SUGAR RE-EXPORT PROGRAM, THE SUGAR CONTAINING PRODUCTS RE-EXPORT PROGRAM, AND THE... transaction; (2) The date of the entry, transfer (only a refiner shall report transfers to the Licensing... license number; (5) The country of origin (entry of raw sugar) or final destination (refined exports...

7 CFR 1530.109 - Reporting.

Code of Federal Regulations, 2014 CFR

2014-01-01

... AGRICULTURE THE REFINED SUGAR RE-EXPORT PROGRAM, THE SUGAR CONTAINING PRODUCTS RE-EXPORT PROGRAM, AND THE... transaction; (2) The date of the entry, transfer (only a refiner shall report transfers to the Licensing... license number; (5) The country of origin (entry of raw sugar) or final destination (refined exports...

7 CFR 1530.109 - Reporting.

Code of Federal Regulations, 2011 CFR

2011-01-01

... AGRICULTURE THE REFINED SUGAR RE-EXPORT PROGRAM, THE SUGAR CONTAINING PRODUCTS RE-EXPORT PROGRAM, AND THE... transaction; (2) The date of the entry, transfer (only a refiner shall report transfers to the Licensing... license number; (5) The country of origin (entry of raw sugar) or final destination (refined exports...

7 CFR 1530.109 - Reporting.

Code of Federal Regulations, 2010 CFR

2010-01-01

... AGRICULTURE THE REFINED SUGAR RE-EXPORT PROGRAM, THE SUGAR CONTAINING PRODUCTS RE-EXPORT PROGRAM, AND THE... transaction; (2) The date of the entry, transfer (only a refiner shall report transfers to the Licensing... license number; (5) The country of origin (entry of raw sugar) or final destination (refined exports...

The US - European Cooperation in the X-38 and CRV Programs

NASA Astrophysics Data System (ADS)

Sygulla, D.; Sabath, D.; Püttmann, N.; Schmid, V.; Caporicci, M.; Anderson, B.

2002-01-01

The European participation in the US X-38 program was initiated in 1997 and is realized by contributions from two European programs, by ESA's "Applied Reentry Technology Program", (ARTP) and the German/DLR "Technologies for Future Space Transportation Systems" (TETRA) program. The space agencies of USA, Europe and Germany have established two Memoranda of Understanding - NASA-ESA and NASA-DLR - for the European participation in the X-38 Program to deliver flight hard- and software in exchange to a re-entry flight opportunity with Vehicle 201 (V201). By October 2002 all European contributions to V201 of the X-38 program will be delivered to NASA JSC. Vehicle 201 represents the orbital test vehicle of the experimental vehicle family, developed and built from 1996 onwards by NASA at Johnson Space Center, JSC in Houston. The X-38 Program was initiated by NASA to prepare and develop the Crew Return Vehicle (CRV) with Vehicle 201 as prototype. NASA conducts the overall X-38 vehicle system engineering and integration, intended to provide the launch of the vehicle 201 with the Space Shuttle and will deliver flight data for post-flight analysis and assessment to DLR and ESA. The German national project TETRA (Technologies for future Space Transportation Systems) and the European ARTP (Applied Re-entry Technology Programme) are providing engineering support for design, analysis, system engineering and layout as well as delivering essential flight hard- and software: CMC Body flaps and CMC nose assembly from TETRA; rudders, CMC leading edges, landing gears and major elements of the V201 primary structure from ARTP. Since both programmes contribute in cooperation the major part of the aerodynamic database is generated, the flexible external insulation is developed and manufactured, and advanced sensors and data acquisition systems are built. The parts for V201 have been developed, fulfill the requirements, are qualified for flight and they are in the process of being integrated on the vehicle X- 38 V201. There will be no exchange of funds since the delivery of contributions and the flight opportunity are parts of a barter agreement. Presently NASA is assembling the vehicle's structure in preparation of the structural vehicle test in 2002. In the following period all major subsystems will be included and checked out before the envisaged orbital test flight of V201. The Shuttle Columbia will set it free in orbit and after an autonomous reentry flight it is proposed to glide towards Australia, hanging on the largest parafoil ever been built (7.500 square feet). Parallel to the final installation of all flight systems in V201, it was foreseen to develop the CRV using most of the systems of V201, provided the critical cost situation on the International Space Station can be solved. In this case the CRV would be used from about 2008/2009 as `ambulance - lifeboat' and/or as `return vehicle' for the crew of the International Space Station. Manifold contributions from European companies could be provided for the CRV: All in all this paper will give an overview about the programs X-38, CRV, TETRA and ARTP, as well as an overview about the status of the development of flight hard- and software for the reusable vehicle X-38 V201. *)CMC Ceramic Matrix Composites

Sacramento City College Re-Entry Services Comprehensive Plan.

ERIC Educational Resources Information Center

White, Maureen E.; Smith, William A.

Sacramento City College (SCC) established its Re-Entry Services program to provide information, referral and support services to students returning to the academic environment after an absence. Since the inception of the program in 1977, the college community has changed considerably. Among these changes are an aging student population, increased…

78 FR 40531 - Self-Regulatory Organizations; BATS Exchange, Inc.; Notice of Filing of a Proposed Rule Change...

Federal Register 2010, 2011, 2012, 2013, 2014

2013-07-05

... Exchange from allowing re-entry into the Program where the Exchange deems such re-entry as proper. CLP... its status as a CLP, such Member may re- apply for CLP status. Such application process shall occur at...

Improved Re-Configurable Sliding Mode Controller for Reusable Launch Vehicle of Second Generation Addressing Aerodynamic Surface Failures and Thrust Deficiencies

NASA Technical Reports Server (NTRS)

Shtessel, Yuri B.

2002-01-01

In this report we present a time-varying sliding mode control (TV-SMC) technique for reusable launch vehicle (RLV) attitude control in ascent and entry flight phases. In ascent flight the guidance commands Euler roll, pitch and yaw angles, and in entry flight it commands the aerodynamic angles of bank, attack and sideslip. The controller employs a body rate inner loop and the attitude outer loop, which are separated in time-scale by the singular perturbation principle. The novelty of the TVSMC is that both the sliding surface and the boundary layer dynamics can be varied in real time using the PD-eigenvalue assignment technique. This salient feature is used to cope with control command saturation and integrator windup in the presence of severe disturbance or control effector failure, which enhances the robustness and fault tolerance of the controller. The TV-SMC is developed and tuned up for the X-33 sub-orbital technology demonstration vehicle in launch and re-entry modes. A variety of nominal, dispersion and failure scenarios have tested via high fidelity 6DOF simulations using MAVERIC/SLIM simulation software.

An Automated Method to Compute Orbital Re-Entry Trajectories with Heating Constraints

NASA Technical Reports Server (NTRS)

Zimmerman, Curtis; Dukeman, Greg; Hanson, John; Fogle, Frank R. (Technical Monitor)

2002-01-01

Determining how to properly manipulate the controls of a re-entering re-usable launch vehicle (RLV) so that it is able to safely return to Earth and land involves the solution of a two-point boundary value problem (TPBVP). This problem, which can be quite difficult, is traditionally solved on the ground prior to flight. If necessary, a nearly unlimited amount of time is available to find the "best" solution using a variety of trajectory design and optimization tools. The role of entry guidance during flight is to follow the pre-determined reference solution while correcting for any errors encountered along the way. This guidance method is both highly reliable and very efficient in terms of onboard computer resources. There is a growing interest in a style of entry guidance that places the responsibility of solving the TPBVP in the actual entry guidance flight software. Here there is very limited computer time. The powerful, but finicky, mathematical tools used by trajectory designers on the ground cannot in general be made to do the job. Nonconvergence or slow convergence can result in disaster. The challenges of designing such an algorithm are numerous and difficult. Yet the payoff (in the form of decreased operational costs and increased safety) can be substantial. This paper presents an algorithm that incorporates features of both types of guidance strategies. It takes an initial RLV orbital re-entry state and finds a trajectory that will safely transport the vehicle to a Terminal Area Energy Management (TAEM) region. During actual flight, the computed trajectory is used as the reference to be flown by a more traditional guidance method.

Building Bridges to the Economic Mainstream for African American Male Ex-Offenders: A Preliminary Assessment of an Inmate Education Re-Entry Program.

ERIC Educational Resources Information Center

Johnson, James H., Jr.; Farrell, Walter C., Jr.; Braithwaite, Lawrence P.

This paper describes a state-funded inmate education and re-entry program that provides soft skills training for soon-to-be released offenders. The paper presents preliminary evidence regarding the impact of this training on 14 young male participants. Data came from information prepared by inmates throughout the training program and ethnographic…

The IXV experience, from the mission conception to the flight results

NASA Astrophysics Data System (ADS)

Tumino, G.; Mancuso, S.; Gallego, J.-M.; Dussy, S.; Preaud, J.-P.; Di Vita, G.; Brunner, P.

2016-07-01

The atmospheric re-entry domain is a cornerstone of a wide range of space applications, ranging from reusable launcher stages developments, robotic planetary exploration, human space flight, to innovative applications such as reusable research platforms for in orbit validation of multiple space applications technologies. The Intermediate experimental Vehicle (IXV) is an advanced demonstrator which has performed in-flight experimentation of atmospheric re-entry enabling systems and technologies aspects, with significant advancements on Europe's previous flight experiences, consolidating Europe's autonomous position in the strategic field of atmospheric re-entry. The IXV mission objectives were the design, development, manufacturing, assembling and on-ground to in-flight verification of an autonomous European lifting and aerodynamically controlled reentry system, integrating critical re-entry technologies at system level. Among such critical technologies of interest, special attention was paid to aerodynamic and aerothermodynamics experimentation, including advanced instrumentation for aerothermodynamics phenomena investigations, thermal protections and hot-structures, guidance, navigation and flight control through combined jets and aerodynamic surfaces (i.e. flaps), in particular focusing on the technologies integration at system level for flight, successfully performed on February 11th, 2015.

Ceramic Foams for TPS Applications

NASA Technical Reports Server (NTRS)

Stockpoole, Mairead

2003-01-01

Ceramic foams have potential in many areas of Thermal Protection Systems (TPS) including acreage and tile leading edges as well as being suitable as a repair approach for re-entry vehicles. NASA Ames is conducting ongoing research in developing lower-density foams from pre-ceramic polymer routes. One of the key factors to investigate, when developing new materials for re-entry applications, is their oxidation behavior in the appropriate re-entry environment which can be simulated using ground based arc jet (plasma jet) testing. Arc jet testing is required to provide the appropriate conditions (stagnation pressures, heat fluxes, enthalpies, heat loads and atmospheres) encountered during flight. This work looks at the response of ceramic foams (Si systems) exposed to simulated reentry environments and investigates the influence of microstructure and composition on the material? response. Other foam properties (mechanical and thermal) will also be presented.

8 CFR 212.1 - Documentary requirements for nonimmigrants.

Code of Federal Regulations, 2011 CFR

2011-01-01

... Cards and a valid Taiwan passport with a valid re-entry permit issued by the Taiwan Ministry of Foreign... valid re-entry permit issued by the Taiwan Ministry of Foreign Affairs. (2) Program Countries and... the United States from contiguous territory or adjacent islands at a land or sea port-of-entry. A...

Career Assessment, Remediation, Education, Employment, and Re-entry Program (CAREER). El Paso Community College Career Grant. Final Report.

ERIC Educational Resources Information Center

LaFleur, Carol A.

Objectives of the Career Assessment, Remediation, Education, Employment, and Re-entry (CAREER) project were to establish a series of intensive, short-term job training programs using competency-based instruction to serve Hispanic persons who were economically disadvantaged, displaced, unemployed, or underemployed, as well as Hispanic females who…

German Contribution to the X-38 CRV Demonstrator in the Field of Guidance, Navigation and Control (GNC)

NASA Astrophysics Data System (ADS)

Soppa, Uwe; Görlach, Thomas; Roenneke, Axel Justus

2002-01-01

As a solution to meet a safety requirement to the future full scale space station infrastructure, the Crew Return/Rescue Vehicle (CRV) was supposed to supply the return capability for the complete ISS crew of 7 astronauts back to earth in case of an emergency. A prototype of such a vehicle named X-38 has been developed and built by NASA with European partnership (ESA, DLR). An series of aerial demonstrators (V13x) for tests of the subsonic TAEM phase and the parafoil descent and landing system has been flown by NASA from 1998 to 2001. A full scale unmanned space flight demonstrator (V201) has been built at JSC Houston and although the project has been stopped for budgetary reasons in 2002, it will hopefully still be flown in near future. The X-38 is a lifting body with hypersonic lift to drag ratio about 0.9. In comparison to the Space Shuttle Orbiter, this design provides less aerodynamic maneuvrability and a different actuator layout (divided body flap and winglet rudders instead as combined aileron and elevon in addition to thrust- ers for the early re-entry phase). Hence, the guidance and control concepts used onboard the shuttle orbiter had to be adapted and further developed for the application on the new vehicle. In the frame of the European share of the X-38 project and also of the German TETRA (TEchnol- ogy for future space TRAnsportation) project different GNC related contributions have been made: First, the primary flight control software for the autonomous guidance and control of the X-38 para- foil descent and landing phase has been developed, integrated and successfully flown on multiple vehicles and missions during the aerial drop test campaign conducted by NASA. Second, a real time X-38 vehicle simulator was provided to NASA which has also been used for the validation of a European re-entry guidance and control software (see below). According to the NASA verification and validation plan this simulator is supposed to be used as an independent vali- dation tool for the X-38 re-entry simulation and onboard software. Third, alternate guidance and control algorithms for the re-entry flight phase of X-38, using onboard flight path optimization for the guidance task and dynamic inversion control methods for attitude control have been developed. The resulting alternate guidance and control software shall be flown as a flight experiment onboard the V201 spaceflight test vehicle. Fourth, a fault tolerant computer similar to the one used onboard the ISS is planned to be integrated into the V201 spaceflight test vehicle as a host of the re-entry GNC software mentioned above. This paper will summarize the development and test phases of European guidance and control soft- ware and avionics elements for the different phases of the X-38 mission. Flight test results from the X38 aerial drop test campaigns will be presented and discussed. In addition, the flight experiment of the fault tolerant computer will be described.

A Modified Triples Algorithm for Flush Air Data Systems that Allows a Variety of Pressure Port Configurations

NASA Technical Reports Server (NTRS)

Millman, Daniel R.

2017-01-01

Air Data Systems (FADS) are becoming more prevalent on re-entry vehicles, as evi- denced by the Mars Science Laboratory and the Orion Multipurpose Crew Vehicle. A FADS consists of flush-mounted pressure transducers located at various locations on the fore-body of a flight vehicle or the heat shield of a re-entry capsule. A pressure model converts the pressure readings into useful air data quantities. Two algorithms for converting pressure readings to air data have become predominant- the iterative Least Squares State Estimator (LSSE) and the Triples Algorithm. What follows herein is a new algorithm that takes advantage of the best features of both the Triples Algorithm and the LSSE. This approach employs the potential flow model and strategic differencing of the Triples Algorithm to obtain the defective flight angles; however, the requirements on port placement are far less restrictive, allowing for configurations that are considered optimal for a FADS.

The Advanced Re-Entry Vehicle (ARV) A Development Step From ATV Toward Manned Transportation Systems

NASA Astrophysics Data System (ADS)

Bottacini, Massimiliano; Berthe, Philippe; Vo, Xavier; Pietsch, Klaus

2011-05-01

The Advanced Re-entry Vehicle (ARV) programme has been undertaken by Europe with the objective to contribute to the preparation of a future European crew transportation system, while providing a valuable logistic support to the ISS through an operational cargo return system. This development would allow: - the early acquisition of critical technologies; - the design, development and testing of elements suitable for the follow up human rated transportation system. These vehicles should also serve future LEO infrastructures and exploration missions. With the aim to satisfy the above objectives a team composed by major European industries and led by EADS Astrium Space Transportation is currently conducting the phase A of the programme under contract with the European Space Agency (ESA). Two vehicle versions are being investigated: a Cargo version, transporting cargo only to/from the ISS, and a Crew version, which will allow the transfer of both crew and cargo to/from the ISS. The ARV Cargo version, in its present configuration, is composed of three modules. The Versatile Service Module (VSM) provides to the system the propulsion/GNC for orbital manoeuvres and attitude control and the orbital power generation. Its propulsion system and GNC shall be robust enough to allow its use for different launch stacks and different LEO missions in the future. The Un-pressurised Cargo Module (UCM) provides the accommodation for about 3000 kg of unpressurised cargo and is to be sufficiently flexible to ensure the transportation of: - orbital infrastructure components (ORU’s); - scientific / technological experiments; - propellant for re-fuelling, re-boost (and de-orbiting) of the ISS. The Re-entry Module (RM) provides a pressurized volume to accommodate active/passive cargo (2000 kg upload/1500 kg download). It is conceived as an expendable conical capsule with spherical heat-shield, interfacing with the new docking standard of the ISS, i.e. it carries the IBDM docking system, on a dedicated adapter. Its thermo-mechanical design, GNC, descent & landing systems take into account its future evolution for crew transportation. The ARV Crew version is also composed of three main modules: - an Integrated Resource Module (IRM) providing the main propulsion and power functions during the on-orbit phases of the mission; - a Re-entry Module (RM) providing the re-entry function and a pressurized environment for four crew members and about 250 kg of passive / active cargo; - a Crew Escape System (CES) providing the function of emergency separation of the RM from the launcher (in case of failure of this latter). The paper presents an overview of the ARV Cargo and Crew versions requirements derived from the above objectives, their mission scenarios, system architectures and performances. The commonality aspects between the ARV Cargo version and future transportation systems (including also the ARV Crew version and logistic carriers) are also highlighted.

The Advanced Re-Entry Vehicle (ARV) a Development Step from ATV Toward Manned Transportation Systems

NASA Astrophysics Data System (ADS)

Bottacini, M.; Berthe, P.; Vo, X.; Pietsch, K.

2011-08-01

The Advanced Re-entry Vehicle (ARV) programme has been undertaken by Europe with the objective to contribute to the preparation of a future European crew transportation system, while providing a valuable logistic support to the ISS through an operational cargo return system. This development would allow: - the early acquisition of critical technologies; - the design, development and testing of elements suitable for the follow up human rated transportation system. These vehicles should also serve future LEO infrastructures and exploration missions. With the aim to satisfy the above objectives a team composed by major European industries and led by EADS Astrium Space Transportation is currently conducting the phase A of the programme under contract with the European Space Agency (ESA). Two vehicle versions are being investigated: a Cargo version, transporting cargo only to/from the ISS, and a Crew version, which will allow the transfer of both crew and cargo to/from the ISS. The ARV Cargo version, in its present configuration, is composed of three modules. The Versatile Service Module (VSM) provides to the system the propulsion/GNC for orbital manoeuvres and attitude control and the orbital power generation. Its propulsion system and GNC shall be robust enough to allow its use for different launch stacks and different LEO missions in the future. The Un-pressurised Cargo Module (UCM) provides the accommodation for about 3000 kg of un-pressurised cargo and is to be sufficiently flexible to ensure the transportation of: - orbital infrastructure components (ORU's); - scientific / technological experiments; - propellant for re-fuelling, re-boost (and deorbiting) of the ISS. The Re-entry Module (RM) provides a pressurized volume to accommodate active/passive cargo (2000 kg upload/1500 kg download). It is conceived as an expendable conical capsule with spherical heat- hield, interfacing with the new docking standard of the ISS, i.e. it carries the IBDM docking system, on a dedicated adapter. Its thermo-mechanical design, GNC, descent & landing systems take into account its future evolution for crew transportation. The ARV Crew version is also composed of three main modules: - an Integrated Resource Module (IRM) providing the main propulsion and power functions during the on-orbit phases of the mission; - a Re-entry Module (RM) providing the re-entry function and a pressurized environment for four crew members and about 250 kg of passive / active cargo; - a Crew Escape System (CES) providing the function of emergency separation of the RM from the launcher (in case of failure of this latter). The paper presents an overview of the ARV Cargo and Crew versions requirements derived from the above objectives, their mission scenarios, system architectures and performances. The commonality aspects between the ARV Cargo version and future transportation systems (including also the ARV Crew version and logistic carriers) are also highlighted.

7 CFR 1530.101 - Definitions.

Code of Federal Regulations, 2014 CFR

2014-01-01

... AGRICULTURE THE REFINED SUGAR RE-EXPORT PROGRAM, THE SUGAR CONTAINING PRODUCTS RE-EXPORT PROGRAM, AND THE...-packers. Bond or letter of credit means an insurance agreement pledging surety for the entry of foreign sugar without the required re-export within the program guidelines. Certain polyhydric alcohols means...

Experimental Study Of SHEFEX II Hypersonic Aerodynamics And Canard Efficiency In H2K

NASA Astrophysics Data System (ADS)

Neeb, D.; Gulhan, A.

2011-05-01

One main objective of the DLR SHEFEX programme is to prove that sharp edged vehicles are capable of performing a re-entry into earth atmosphere by using a simple thermal protection system consisting of flat ceramic tiles. In comparison to blunt nose configurations like the Space shuttle, which are normally used for re-entry configurations, the SHEFEX TPS design is able to significantly reduce the costs and complexity of TPS structures and simultaneously increase the aerodynamic performance of the flight vehicle [1], [2]. To study its characteristics and perform several defined in-flight experiments during re-entry, the vehicle’s attitude will be controlled actively by canards [3]. In the framework of the SHEFEX II project an experimental investigation has been conducted in the hypersonic wind tunnel H2K to characterize the aerodynamic performance of the vehicle in hypersonic flow regime. The model has a modular design to enable the study of a variety of different influencing parameters. Its 4 circumferential canards have been made independently adjustable to account for the simulation of different manoeuvre conditions. To study the control behaviour of the vehicle and validate CFD data, a variation of canard deflections, angle of attack and angle of sideslip have been applied. Tests have been carried out at Mach 7 and 8.7 with a Reynolds number sensitivity study at the lower Mach number. The model was equipped with a six component internal balance to realize accurate coefficient measurements. The flow topology has been analyzed using Schlieren images. Beside general aerodynamic performance and canard efficiencies, flow phenomena like shock impingement on the canards could be determined by Schlieren images as well as by the derived coefficients.

KSC-2013-3938

NASA Image and Video Library

2013-11-07

CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, all four ogive panels have been installed on the Orion ground test vehicle in Vehicle Assembly Building high bay 4. The ogive panels enclose and protect the Orion spacecraft and attach to the Launch Abort System. The test vehicle is being used by the Ground Systems Development and Operations Program for path finding operations, including simulated manufacturing, assembly and stacking procedures. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Kim Shiflett

KSC-2013-3926

NASA Image and Video Library

2013-10-30

CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, the Orion ground test vehicle is being prepared for installation of the ogive panels in Vehicle Assembly Building high bay 4. The ogive panels enclose and protect the Orion spacecraft and attach to the Launch Abort System. The test vehicle is being used by the Ground Systems Development and Operations Program for path finding operations, including simulated manufacturing, assembly and stacking procedures. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Kim Shiflett

KSC-2013-3937

NASA Image and Video Library

2013-11-07

CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, technicians attach the fourth ogive panel on the Orion ground test vehicle in Vehicle Assembly Building high bay 4. The ogive panels enclose and protect the Orion spacecraft and attach to the Launch Abort System. The test vehicle is being used by the Ground Systems Development and Operations Program for path finding operations, including simulated manufacturing, assembly and stacking procedures. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Kim Shiflett

THE LARGE HIGH PRESSURE ARC PLASMA GENERATOR: A FACILITY FOR SIMULATING MISSLE AND SATELLITE RE-ENTRY. Research Report 56

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

Rose, P.; Powers, W.; Hritzay, D.

1959-06-01

The development of an arc wind tunnel capable of stagnation pressures in the excess of twenty atmospheres and using as much as fifteen megawatts of electrical power is described. The calibration of this facility shows that it is capable of reproducing the aerodynamic environment encountered by vehicles flying at velocities as great as satellite velocity. Its use as a missile re-entry material test facility is described. The large power capacity of this facility allows one to make material tests on specimens of size sufficient to be useful for material development yet at realistic energy and Reynolds number values. By themore » addition of a high-capacity vacuum system, this facility can be used to produce the low density, high Mach number environment needed for simulating satellite re-entry, as well as hypersonic flight at extreme altitudes. (auth)« less

KSC-2011-5114

NASA Image and Video Library

2011-07-07

CAPE CANAVERAL, Fla. -- A media event was held on the grounds near the Press Site at NASA's Kennedy Space Center in Florida where a Multi-Purpose Crew Vehicle (MPCV) is on display. The MPCV is based on the Orion design requirements for traveling beyond low Earth orbit and will serve as the exploration vehicle that will carry the crew to space, provide emergency abort capability, sustain the crew during the space travel, and provide safe re-entry from deep space return velocities. Seen here is a sample of the Orion launch-and-entry suit on display. Photo credit: NASA/Frankie Martin

Development of FIAT-Based Parametric Thermal Protection System Mass Estimating Relationships for NASA's Multi-Mission Earth Entry Concept

NASA Technical Reports Server (NTRS)

Sepka, Steven A.; Zarchi, Kerry; Maddock, Robert W.; Samareh, Jamshid A.

2013-01-01

Part of NASAs In-Space Propulsion Technology (ISPT) program is the development of the tradespace to support the design of a family of multi-mission Earth Entry Vehicles (MMEEV) to meet a wide range of mission requirements. An integrated tool called the Multi Mission System Analysis for Planetary Entry Descent and Landing or M-SAPE tool is being developed as part of Entry Vehicle Technology project under In-Space Technology program. The analysis and design of an Earth Entry Vehicle (EEV) is multidisciplinary in nature, requiring the application many disciplines. Part of M-SAPE's application required the development of parametric mass estimating relationships (MERs) to determine the vehicle's required Thermal Protection System (TPS) for safe Earth entry. For this analysis, the heat shield was assumed to be made of a constant thickness TPS. This resulting MERs will then e used to determine the pre-flight mass of the TPS. Two Mers have been developed for the vehicle forebaody. One MER was developed for PICA and the other consisting of Carbon Phenolic atop an Advanced Carbon-Carbon composition. For the the backshell, MERs have been developed for SIRCA, Acusil II, and LI-900. How these MERs were developed, the resulting equations, model limitations, and model accuracy are discussed in this poster.

Range of Density Variability from Surface To 120 km Altitude

NASA Technical Reports Server (NTRS)

Smith, Orvel E.; Chenoweth, Halsey B.

1961-01-01

A re-entry space vehicle development program, such as Project Apollo, requires a knowledge of the variability of atmospheric density from the surface of the earth to re-entry altitude (120 km). This report summarizes the data on density given in the most recent literature on the subject. The range of atmospheric density with respect to the ARDC 1959 Model Atmosphere is determined and shown graphically. From the surface to 30 km altitude abundant information on density is available. From 30 to 90 km altitude the summarized reports of observations made at a limited number of stations have been used. Between 90 and 120 km altitude the density is somewhat speculative, there being but few measurements available. Therefore, the qualitative values for the variability of density above 30 km must be considered tentative. Variations of atmospheric density by latitude and seasons made it necessary to develop a family of curves rather than a single profile. Three curves are presented to show the range of density deviation versus altitudes with respect to the ARDC 1959 Model Atmosphere. Each curve is used for a specific latitude range and season.

Diversion at re-entry using criminogenic CBT: Review and prototypical program development.

PubMed

Heilbrun, Kirk; Pietruszka, Victoria; Thornewill, Alice; Phillips, Sarah; Schiedel, Rebecca

2017-09-01

Society and the criminal justice system prioritize the reduction of reoffending risk as part of any criminal justice intervention. The Sequential Intercept Model identifies five points of interception at which justice-involved individuals can be diverted into a more rehabilitative alternative: (1) law enforcement/emergency services; (2) booking/initial court hearings; (3) jails/courts; (4) re-entry; and (5) community corrections/community support. The present article focuses on diversion as part of Intercept 5 - re-entry planning and specialized services in the community. We describe the challenges associated with diversion at this stage, and review the relevant research. Next, we describe a "criminogenic cognitive behavioral therapy" project that has been developed and implemented as part of a federal re-entry court. Finally, we discuss the implications of the challenges of intervention at this stage, and the recently developed "Re-entry Project," for research, policy, and practice. Copyright © 2017 John Wiley & Sons, Ltd.

KSC-2013-3934

NASA Image and Video Library

2013-11-07

CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, technicians monitor the progress as the fourth ogive panel is lifted by crane so that they can be installed on the Orion ground test vehicle in Vehicle Assembly Building high bay 4. Three of the panels have already been installed on the test vehicle. The ogive panels enclose and protect the Orion spacecraft and attach to the Launch Abort System. The test vehicle is being used by the Ground Systems Development and Operations Program for path finding operations, including simulated manufacturing, assembly and stacking procedures. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Kim Shiflett

KSC-2013-3936

NASA Image and Video Library

2013-11-07

CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, technicians monitor the progress as the fourth ogive panel is lifted by crane so that they can be installed on the Orion ground test vehicle in Vehicle Assembly Building high bay 4. Three of the panels have already been installed on the test vehicle. The ogive panels enclose and protect the Orion spacecraft and attach to the Launch Abort System. The test vehicle is being used by the Ground Systems Development and Operations Program for path finding operations, including simulated manufacturing, assembly and stacking procedures. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Kim Shiflett

KSC-2013-3935

NASA Image and Video Library

2013-11-07

CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, technicians monitor the progress as the fourth ogive panel is lifted by crane so that they can be installed on the Orion ground test vehicle in Vehicle Assembly Building high bay 4. Three of the panels have already been installed on the test vehicle. The ogive panels enclose and protect the Orion spacecraft and attach to the Launch Abort System. The test vehicle is being used by the Ground Systems Development and Operations Program for path finding operations, including simulated manufacturing, assembly and stacking procedures. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Kim Shiflett

2004 NASA Seal/Secondary Air System Workshop, Volume 1

NASA Technical Reports Server (NTRS)

2005-01-01

The 2004 NASA Seal/Secondary Air System workshop covered the following topics: (1) Overview of NASA s new Exploration Initiative program aimed at exploring the Moon, Mars, and beyond; (2) Overview of the NASA-sponsored Ultra-Efficient Engine Technology (UEET) program; (3) Overview of NASA Glenn s seal program aimed at developing advanced seals for NASA s turbomachinery, space, and reentry vehicle needs; (4) Reviews of NASA prime contractor and university advanced sealing concepts including tip clearance control, test results, experimental facilities, and numerical predictions; and (5) Reviews of material development programs relevant to advanced seals development. The NASA UEET overview illustrated for the reader the importance of advanced technologies, including seals, in meeting future turbine engine system efficiency and emission goals. For example, the NASA UEET program goals include an 8- to 15-percent reduction in fuel burn, a 15-percent reduction in CO2, a 70-percent reduction in NOx, CO, and unburned hydrocarbons, and a 30-dB noise reduction relative to program baselines. The workshop also covered several programs NASA is funding to develop technologies for the Exploration Initiative and advanced reusable space vehicle technologies. NASA plans on developing an advanced docking and berthing system that would permit any vehicle to dock to any on-orbit station or vehicle, as part of NASA s new Exploration Initiative. Plans to develop the necessary mechanism and androgynous seal technologies were reviewed. Seal challenges posed by reusable re-entry space vehicles include high-temperature operation, resiliency at temperature to accommodate gap changes during operation, and durability to meet mission requirements.

The ESA/NASA Multi-Aircraft ATV-1 Re-Entry Campaign: Analysis of Airborne Intensified Video Observations from the NASA/JSC Experiment

NASA Technical Reports Server (NTRS)

Barker, Ed; Maley, Paul; Mulrooney, Mark; Beaulieu, Kevin

2009-01-01

In September 2008, a joint ESA/NASA multi-instrument airborne observing campaign was conducted over the Southern Pacific ocean. The objective was the acquisition of data to support detailed atmospheric re-entry analysis for the first flight of the European Automated Transfer Vehicle (ATV)-1. Skilled observers were deployed aboard two aircraft which were flown at 12.8 km altitude within visible range of the ATV-1 re-entry zone. The observers operated a suite of instruments with low-light-level detection sensitivity including still cameras, high speed and 30 fps video cameras, and spectrographs. The collected data has provided valuable information regarding the dynamic time evolution of the ATV-1 re-entry fragmentation. Specifically, the data has satisfied the primary mission objective of recording the explosion of ATV-1's primary fuel tank and thereby validating predictions regarding the tanks demise and the altitude of its occurrence. Furthermore, the data contains the brightness and trajectories of several hundred ATV-1 fragments. It is the analysis of these properties, as recorded by the particular instrument set sponsored by NASA/Johnson Space Center, which we present here.

CARS Measurement of Vibrational/Rotational Temperatures with Total Radiation Visualization behind Strong Shock Waves of 5-7 km/s

NASA Astrophysics Data System (ADS)

Sakurai, K.; Bindu, V. Hima; Niinomi, S.; Ota, M.; Maeno, K.

2011-05-01

In the development of aerospace technology the design of space vehicles is important in phase of reentry flight. The space vehicles reenter into the atmosphere with range of 6-8 km/s. The non-equilibrium flow with radiative heating from strongly shocked air ahead of the vehicles plays an important role on the heat flux to the wall surface structure as well as convective heating. The experimental data for re-entry analyses, however, have remained in classical level. Recent development of optical instruments enables us to have novel approach of diagnostics to the re-entry problems. We employ the CARS (Coherent Anti-Stokes Raman Spectroscopy) method for measurement of real gas temperatures of N2 with radiation of the strong shock wave. The CARS signal can be acquired even in the strong radiation area behind the strong shock waves. In addition, we try to use the CCD camera to obtain 2D images of total radiation simultaneously. The strong shock wave in front of the reentering space vehicles is experimentally realigned by free-piston, double-diaphragm shock tube with low density test gas.

7 CFR 1530.110 - Records, certification, and documentation.

Code of Federal Regulations, 2010 CFR

2010-01-01

... SERVICE, DEPARTMENT OF AGRICULTURE THE REFINED SUGAR RE-EXPORT PROGRAM, THE SUGAR CONTAINING PRODUCTS RE... documents to substantiate entries, transfers, exports, or use as appropriate. The Licensing Authority shall...; (3) Include all U.S. Customs forms submitted in the entry or export process; (4) Provide the correct...

7 CFR 1530.110 - Records, certification, and documentation.

Code of Federal Regulations, 2011 CFR

2011-01-01

... SERVICE, DEPARTMENT OF AGRICULTURE THE REFINED SUGAR RE-EXPORT PROGRAM, THE SUGAR CONTAINING PRODUCTS RE... documents to substantiate entries, transfers, exports, or use as appropriate. The Licensing Authority shall...; (3) Include all U.S. Customs forms submitted in the entry or export process; (4) Provide the correct...

7 CFR 1530.110 - Records, certification, and documentation.

Code of Federal Regulations, 2013 CFR

2013-01-01

... SERVICE, DEPARTMENT OF AGRICULTURE THE REFINED SUGAR RE-EXPORT PROGRAM, THE SUGAR CONTAINING PRODUCTS RE... documents to substantiate entries, transfers, exports, or use as appropriate. The Licensing Authority shall...; (3) Include all U.S. Customs forms submitted in the entry or export process; (4) Provide the correct...

7 CFR 1530.110 - Records, certification, and documentation.

Code of Federal Regulations, 2014 CFR

2014-01-01

... SERVICE, DEPARTMENT OF AGRICULTURE THE REFINED SUGAR RE-EXPORT PROGRAM, THE SUGAR CONTAINING PRODUCTS RE... documents to substantiate entries, transfers, exports, or use as appropriate. The Licensing Authority shall...; (3) Include all U.S. Customs forms submitted in the entry or export process; (4) Provide the correct...

7 CFR 1530.110 - Records, certification, and documentation.

Code of Federal Regulations, 2012 CFR

2012-01-01

... SERVICE, DEPARTMENT OF AGRICULTURE THE REFINED SUGAR RE-EXPORT PROGRAM, THE SUGAR CONTAINING PRODUCTS RE... documents to substantiate entries, transfers, exports, or use as appropriate. The Licensing Authority shall...; (3) Include all U.S. Customs forms submitted in the entry or export process; (4) Provide the correct...

Structural Analysis and Testing of the Inflatable Re-entry Vehicle Experiment (IRVE)

NASA Technical Reports Server (NTRS)

Lindell, Michael C.; Hughes, Stephen J.; Dixon, Megan; Wiley, Cliff E.

2006-01-01

The Inflatable Re-entry Vehicle Experiment (IRVE) is a 3.0 meter, 60 degree half-angle sphere cone, inflatable aeroshell experiment designed to demonstrate various aspects of inflatable technology during Earth re-entry. IRVE will be launched on a Terrier-Improved Orion sounding rocket from NASA s Wallops Flight Facility in the fall of 2006 to an altitude of approximately 164 kilometers and re-enter the Earth s atmosphere. The experiment will demonstrate exo-atmospheric inflation, inflatable structure leak performance throughout the flight regime, structural integrity under aerodynamic pressure and associated deceleration loads, thermal protection system performance, and aerodynamic stability. Structural integrity and dynamic response of the inflatable will be monitored with photogrammetric measurements of the leeward side of the aeroshell during flight. Aerodynamic stability and drag performance will be verified with on-board inertial measurements and radar tracking from multiple ground radar stations. In addition to demonstrating inflatable technology, IRVE will help validate structural, aerothermal, and trajectory modeling and analysis techniques for the inflatable aeroshell system. This paper discusses the structural analysis and testing of the IRVE inflatable structure. Equations are presented for calculating fabric loads in sphere cone aeroshells, and finite element results are presented which validate the equations. Fabric material properties and testing are discussed along with aeroshell fabrication techniques. Stiffness and dynamics tests conducted on a small-scale development unit and a full-scale prototype unit are presented along with correlated finite element models to predict the in-flight fundamental mod

Post-Flight Analysis of the Guidance, Navigation, and Control Performance During Orion Exploration Flight Test 1

NASA Technical Reports Server (NTRS)

Barth, Andrew; Mamich, Harvey; Hoelscher, Brian

2015-01-01

The first test flight of the Orion Multi-Purpose Crew Vehicle presented additional challenges for guidance, navigation and control as compared to a typical re-entry from the International Space Station or other Low Earth Orbit. An elevated re-entry velocity and steeper flight path angle were chosen to achieve aero-thermal flight test objectives. New IMU's, a GPS receiver, and baro altimeters were flight qualified to provide the redundant navigation needed for human space flight. The guidance and control systems must manage the vehicle lift vector in order to deliver the vehicle to a precision, coastal, water landing, while operating within aerodynamic load, reaction control system, and propellant constraints. Extensive pre-flight six degree-of-freedom analysis was performed that showed mission success for the nominal mission as well as in the presence of sensor and effector failures. Post-flight reconstruction analysis of the test flight is presented in this paper to show whether that all performance metrics were met and establish how well the pre-flight analysis predicted the in-flight performance.

PIRATES: A Program for Offenders Transitioning into the World of Work

ERIC Educational Resources Information Center

Musgrove, Kate Racoff; Derzis, Nicholas C.; Shippen, Margaret E.; Brigman, Holly E.

2012-01-01

The study assessed the effectiveness of the Preparing Inmates for Re-Entry through Assistance, Training, and Employment Skills (PIRATES) group, which focused on improving dysfunctional career thoughts. Participants were male offenders (n = 14) enrolled in a re-entry training class. Results showed a statistically significant decrease in…

"Our commonality is our past:" a qualitative analysis of re-entry community health workers' meaningful experiences.

PubMed

Bedell, Precious; Wilson, John L; White, Ann Marie; Morse, Diane S

Re-entry community health workers (CHWs) are individuals who connect diverse community residents at risk for chronic health issues such as Hepatitis C virus and cardiovascular disease with post-prison healthcare and re-entry services. While the utilization of CHWs has been documented in other marginalized populations, there is little knowledge surrounding the work of re-entry CHWs with individuals released from incarceration. Specifically, CHWs' experiences and perceptions of the uniqueness of their efforts to link individuals to healthcare have not been documented systematically. This study explored what is meaningful to formerly incarcerated CHWs as they work with released individuals. The authors conducted a qualitative thematic analysis of twelve meaningful experiences written by re-entry CHWs employed by the Transitions Clinic Network who attended a CHW training program during a conference in San Francisco, CA. Study participants were encouraged to recount meaningful CHW experiences and motivations for working with re-entry populations in a manner consistent with journal-based qualitative analysis techniques. Narratives were coded using an iterative process and subsequently organized according to themes in ATLAS.ti. Study personnel came to consensus with coding and major themes. The narratives highlighted thought processes and meaning related to re-entry CHWs' work helping patients navigate complex social services for successful re-integration. Six major themes emerged from the analysis: advocacy and support, empathy relating to a personal history of incarceration, giving back, professional satisfaction and responsibilities, resiliency and educational advancement, and experiences of social inequities related to race. Re-entry CHWs described former incarceration, employment, and social justice as sources of meaning for assisting justice-involved individuals receive effective, efficient, and high-quality healthcare. Health clinics for individuals released from incarceration provide a unique setting that links high risk patients to needed care and professionalizes career opportunities for formerly incarcerated re-entry CHWs. The commonality of past correctional involvement is a strong indicator of the meaning and perceived effectiveness re-entry CHWs find in working with individuals leaving prison. Expansion of reimbursable visits with re-entry CHWs in transitions clinics designed for re-entering individuals is worthy of further consideration.

ARC-2008-ACD08-0218-003

NASA Image and Video Library

2008-09-30

European Space Agency's 'Jules Verne' Automated Transfer Vehicle ATV-1 re-entry in Earth's atmosphere over Pacific Ocean. The breakup ad fragmentation of the ESA's ATV-1 was captured in dramatic fashion by scientists aboard NASA's DC-8 airborne laboratory and a Gulfstream V aircraft as it re-entered the atmosphere early Monday morning over the South Pacific. Photo Credit: NASA Ames Research Center/ESA/Jesse Carpenter/Bill Moede

ARC-2008-ACD08-0218-008

NASA Image and Video Library

2008-09-30

European Space Agency's 'Jules Verne' Automated Transfer Vehicle ATV-1 re-entry in Earth's atmosphere over Pacific Ocean. The breakup ad fragmentation of the ESA's ATV-1 was captured in dramatic fashion by scientists aboard NASA's DC-8 airborne laboratory and a Gulfstream V aircraft as it re-entered the atmosphere early Monday morning over the South Pacific. Photo Credit: NASA Ames Research Center/ESA/Jesse Carpenter/Bill Moede

ARC-2008-ACD08-0218-009

NASA Image and Video Library

2008-09-30

European Space Agency's 'Jules Verne' Automated Transfer Vehicle ATV-1 re-entry in Earth's atmosphere over Pacific Ocean. The breakup ad fragmentation of the ESA's ATV-1 was captured in dramatic fashion by scientists aboard NASA's DC-8 airborne laboratory and a Gulfstream V aircraft as it re-entered the atmosphere early Monday morning over the South Pacific. Photo Credit: NASA Ames Research Center/ESA/Jesse Carpenter/Bill Moede

ARC-2008-ACD08-0218-001

NASA Image and Video Library

2008-09-30

European Space Agency's 'Jules Verne' Automated Transfer Vehicle ATV-1 re-entry in Earth's atmosphere over Pacific Ocean. The breakup ad fragmentation of the ESA's ATV-1 was captured in dramatic fashion by scientists aboard NASA's DC-8 airborne laboratory and a Gulfstream V aircraft as it re-entered the atmosphere early Monday morning over the South Pacific. Photo Credit: NASA Ames Research Center/ESA/Jesse Carpenter/Bill Moede

ARC-2008-ACD08-0218-010

NASA Image and Video Library

2008-09-30

European Space Agency's 'Jules Verne' Automated Transfer Vehicle ATV-1 re-entry in Earth's atmosphere over Pacific Ocean. The breakup ad fragmentation of the ESA's ATV-1 was captured in dramatic fashion by scientists aboard NASA's DC-8 airborne laboratory and a Gulfstream V aircraft as it re-entered the atmosphere early Monday morning over the South Pacific. Photo Credit: NASA Ames Research Center/ESA/Jesse Carpenter/Bill Moede

ARC-2008-ACD08-0218-005

NASA Image and Video Library

2008-09-30

European Space Agency's 'Jules Verne' Automated Transfer Vehicle ATV-1 re-entry in Earth's atmosphere over Pacific Ocean. The breakup ad fragmentation of the ESA's ATV-1 was captured in dramatic fashion by scientists aboard NASA's DC-8 airborne laboratory and a Gulfstream V aircraft as it re-entered the atmosphere early Monday morning over the South Pacific. Photo Credit: NASA Ames Research Center/ESA/Jesse Carpenter/Bill Moede

ARC-2008-ACD08-0218-012

NASA Image and Video Library

2008-09-30

European Space Agency's 'Jules Verne' Automated Transfer Vehicle ATV-1 re-entry in Earth's atmosphere over Pacific Ocean. The breakup ad fragmentation of the ESA's ATV-1 was captured in dramatic fashion by scientists aboard NASA's DC-8 airborne laboratory and a Gulfstream V aircraft as it re-entered the atmosphere early Monday morning over the South Pacific. Photo Credit: NASA Ames Research Center/ESA/Jesse Carpenter/Bill Moede

ARC-2008-ACD08-0218-006

NASA Image and Video Library

2008-09-30

European Space Agency's 'Jules Verne' Automated Transfer Vehicle ATV-1 re-entry in Earth's atmosphere over Pacific Ocean. The breakup ad fragmentation of the ESA's ATV-1 was captured in dramatic fashion by scientists aboard NASA's DC-8 airborne laboratory and a Gulfstream V aircraft as it re-entered the atmosphere early Monday morning over the South Pacific. Photo Credit: NASA Ames Research Center/ESA/Jesse Carpenter/Bill Moede

ARC-2008-ACD08-0218-007

NASA Image and Video Library

2008-09-30

European Space Agency's 'Jules Verne' Automated Transfer Vehicle ATV-1 re-entry in Earth's atmosphere over Pacific Ocean. The breakup ad fragmentation of the ESA's ATV-1 was captured in dramatic fashion by scientists aboard NASA's DC-8 airborne laboratory and a Gulfstream V aircraft as it re-entered the atmosphere early Monday morning over the South Pacific. Photo Credit: NASA Ames Research Center/ESA/Jesse Carpenter/Bill Moede

ARC-2008-ACD08-0218-004

NASA Image and Video Library

2008-09-30

European Space Agency's 'Jules Verne' Automated Transfer Vehicle ATV-1 re-entry in Earth's atmosphere over Pacific Ocean. The breakup ad fragmentation of the ESA's ATV-1 was captured in dramatic fashion by scientists aboard NASA's DC-8 airborne laboratory and a Gulfstream V aircraft as it re-entered the atmosphere early Monday morning over the South Pacific. Photo Credit: NASA Ames Research Center/ESA/Jesse Carpenter/Bill Moede

ARC-2008-ACD08-0218-011

NASA Image and Video Library

2008-09-30

European Space Agency's 'Jules Verne' Automated Transfer Vehicle ATV-1 re-entry in Earth's atmosphere over Pacific Ocean. The breakup ad fragmentation of the ESA's ATV-1 was captured in dramatic fashion by scientists aboard NASA's DC-8 airborne laboratory and a Gulfstream V aircraft as it re-entered the atmosphere early Monday morning over the South Pacific. Photo Credit: NASA Ames Research Center/ESA/Jesse Carpenter/Bill Moede

ARC-2008-ACD08-0218-002

NASA Image and Video Library

2008-09-30

European Space Agency's 'Jules Verne' Automated Transfer Vehicle ATV-1 re-entry in Earth's atmosphere over Pacific Ocean. The breakup ad fragmentation of the ESA's ATV-1 was captured in dramatic fashion by scientists aboard NASA's DC-8 airborne laboratory and a Gulfstream V aircraft as it re-entered the atmosphere early Monday morning over the South Pacific. Photo Credit: NASA Ames Research Center/ESA/Jesse Carpenter/Bill Moede

Recording animal vocalizations from a UAV: bat echolocation during roost re-entry.

PubMed

Kloepper, Laura N; Kinniry, Morgan

2018-05-17

Unmanned aerial vehicles (UAVs) are rising in popularity for wildlife monitoring, but direct recordings of animal vocalizations have not yet been accomplished, likely due to the noise generated by the UAV. Echolocating bats, especially Tadarida brasiliensis, are good candidates for UAV recording due to their high-speed, high-altitude flight. Here, we use a UAV to record the signals of bats during morning roost re-entry. We designed a UAV to block the noise of the propellers from the receiving microphone, and report on the characteristics of bioacoustic recordings from a UAV. We report the first published characteristics of echolocation signals from bats during group flight and cave re-entry. We found changes in inter-individual time-frequency shape, suggesting that bats may use differences in call design when sensing in complex groups. Furthermore, our first documented successful recordings of animals in their natural habitat demonstrate that UAVs can be important tools for bioacoustic monitoring, and we discuss the ethical considerations for such monitoring.

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.

SHEFEX II - Aerodynamic Re-Entry Controlled Sharp Edge Flight Experiment

NASA Astrophysics Data System (ADS)

Longo, J. M. A.; Turner, J.; Weihs, H.

2009-01-01

In this paper the basic goals and architecture of the SHEFEX II mission is presented. Also launched by a two staged sounding rocket system SHEFEX II is a consequent next step in technology test and demonstration. Considering all experience and collected flight data obtained during the SHEFEX I Mission, the test vehicle has been re-designed and extended by an active control system, which allows active aerodynamic control during the re-entry phase. Thus, ceramic based aerodynamic control elements like rudders, ailerons and flaps, mechanical actuators and an automatic electronic control unit has been implemented. Special focus is taken on improved GNC Elements. In addition, some other experiments including an actively cooled thermal protection element, advanced sensor equipment, high temperature antenna inserts etc. are part of the SHEFEX II experimental payload. A final 2 stage configuration has been selected considering Brazilian solid rocket boosters derived from the S 40 family. During the experiment phase a maximum entry velocity of Mach around 10 is expected for 50 seconds. Considering these flight conditions, the heat loads are not representative for a RLV re-entry, however, it allows to investigate the principal behaviour of such a facetted ceramic TPS, a sharp leading edge at the canards and fins and all associated gas flow effects and their structural response.

Inflatable Re-Entry Vehicle Experiment (IRVE) Design Overview

NASA Technical Reports Server (NTRS)

Hughes, Stephen J.; Dillman, Robert A.; Starr, Brett R.; Stephan, Ryan A.; Lindell, Michael C.; Player, Charles J.; Cheatwood, F. McNeil

2005-01-01

Inflatable aeroshells offer several advantages over traditional rigid aeroshells for atmospheric entry. Inflatables offer increased payload volume fraction of the launch vehicle shroud and the possibility to deliver more payload mass to the surface for equivalent trajectory constraints. An inflatable s diameter is not constrained by the launch vehicle shroud. The resultant larger drag area can provide deceleration equivalent to a rigid system at higher atmospheric altitudes, thus offering access to higher landing sites. When stowed for launch and cruise, inflatable aeroshells allow access to the payload after the vehicle is integrated for launch and offer direct access to vehicle structure for structural attachment with the launch vehicle. They also offer an opportunity to eliminate system duplication between the cruise stage and entry vehicle. There are however several potential technical challenges for inflatable aeroshells. First and foremost is the fact that they are flexible structures. That flexibility could lead to unpredictable drag performance or an aerostructural dynamic instability. In addition, durability of large inflatable structures may limit their application. They are susceptible to puncture, a potentially catastrophic insult, from many possible sources. Finally, aerothermal heating during planetary entry poses a significant challenge to a thin membrane. NASA Langley Research Center and NASA's Wallops Flight Facility are jointly developing inflatable aeroshell technology for use on future NASA missions. The technology will be demonstrated in the Inflatable Re-entry Vehicle Experiment (IRVE). This paper will detail the development of the initial IRVE inflatable system to be launched on a Terrier/Orion sounding rocket in the fourth quarter of CY2005. The experiment will demonstrate achievable packaging efficiency of the inflatable aeroshell for launch, inflation, leak performance of the inflatable system throughout the flight regime, structural integrity when exposed to a relevant dynamic pressure and aerodynamic stability of the inflatable system. Structural integrity and structural response of the inflatable will be verified with photogrammetric measurements of the back side of the aeroshell in flight. Aerodynamic stability as well as drag performance will be verified with on board inertial measurements and radar tracking from multiple ground radar stations. The experiment will yield valuable information about zero-g vacuum deployment dynamics of the flexible inflatable structure with both inertial and photographic measurements. In addition to demonstrating inflatable technology, IRVE will validate structural, aerothermal, and trajectory modeling techniques for the inflatable. Structural response determined from photogrammetrics will validate structural models, skin temperature measurements and additional in-depth temperature measurements will validate material thermal performance models, and on board inertial measurements along with radar tracking from multiple ground radar stations will validate trajectory simulation models.

Public Risk Assessment Program

NASA Technical Reports Server (NTRS)

Mendeck, Gavin

2010-01-01

The Public Entry Risk Assessment (PERA) program addresses risk to the public from shuttle or other spacecraft re-entry trajectories. Managing public risk to acceptable levels is a major component of safe spacecraft operation. PERA is given scenario inputs of vehicle trajectory, probability of failure along that trajectory, the resulting debris characteristics, and field size and distribution, and returns risk metrics that quantify the individual and collective risk posed by that scenario. Due to the large volume of data required to perform such a risk analysis, PERA was designed to streamline the analysis process by using innovative mathematical analysis of the risk assessment equations. Real-time analysis in the event of a shuttle contingency operation, such as damage to the Orbiter, is possible because PERA allows for a change to the probability of failure models, therefore providing a much quicker estimation of public risk. PERA also provides the ability to generate movie files showing how the entry risk changes as the entry develops. PERA was designed to streamline the computation of the enormous amounts of data needed for this type of risk assessment by using an average distribution of debris on the ground, rather than pinpointing the impact point of every piece of debris. This has reduced the amount of computational time significantly without reducing the accuracy of the results. PERA was written in MATLAB; a compiled version can run from a DOS or UNIX prompt.

Space Debris Alert System for Aviation

NASA Astrophysics Data System (ADS)

Sgobba, Tommaso

2013-09-01

Despite increasing efforts to accurately predict space debris re-entry, the exact time and location of re-entry is still very uncertain. Partially, this is due to a skipping effect uncontrolled spacecraft may experience as they enter the atmosphere at a shallow angle. Such effect difficult to model depends on atmospheric variations of density. When the bouncing off ends and atmospheric re-entry starts, the trajectory and the overall location of surviving fragments can be precisely predicted but the time to impact with ground, or to reach the airspace, becomes very short.Different is the case of a functional space system performing controlled re-entry. Suitable forecasts methods are available to clear air and maritime traffic from hazard areas (so-called traffic segregation).In US, following the Space Shuttle Columbia accident in 2003, a re-entry hazard areas location forecast system was putted in place for the specific case of major malfunction of a Reusable Launch Vehicles (RLV) at re-entry. The Shuttle Hazard Area to Aircraft Calculator (SHAAC) is a system based on ground equipment and software analyses and prediction tools, which require trained personnel and close coordination between the organization responsible for RLV operation (NASA for Shuttle) and the Federal Aviation Administration. The system very much relies on the operator's capability to determine that a major malfunction has occurred.This paper presents a US pending patent by the European Space Agency, which consists of a "smart fragment" using a GPS localizer together with pre- computed debris footprint area and direct broadcasting of such hazard areas.The risk for aviation from falling debris is very remote but catastrophic. Suspending flight over vast swath of airspace for every re-entering spacecraft or rocket upper stage, which is a weekly occurrence, would be extremely costly and disruptive.The Re-entry Direct Broadcasting Alert System (R- DBAS) is an original merging and evolution of the Re- entry Breakup Recorder (REBR) concept developed by The Aerospace Corporation, often called the black box of spacecraft, and of the Shuttle Hazard Area to Aircraft Calculator (SHAAC). Unlike the REBR, whichdownloads data via satellite link for later analysis, the R-DBAS is intended as a direct communication tool with the end user. As a spacecraft carrying R-DBAS re- enters into the atmosphere, it relays a message with the coordinates of the falling debris footprint area to anyone with a receiver and a display like laptop or iPad, warning them of the hazard.Much like the REBR, the R-DBAS is designed to release from its host vehicle when it experiences significant heat which melts the attachment point and closes the power circuit. Once activated, the R-DBAS determines its own location and computes the final coordinates of the preloaded debris footprint which is then broadcasted to anyone holding a receiver in the proximity of the hazard area.The R-DBAS is intended to provide precise information directly to the cockpit. An airplane would have about 5- 7 minutes to get out of the way. Being the hazard area 1,000-2000 km long but very narrow, 30 -70 km, an escape manoeuvre from the risky area can be readily performed or go on holding before crossing the hazard area.By equipping aircraft and other vulnerable systems with a simple receivers that can be attached to a common laptop, escape manoeuvres can be performed as in front of bad weather or shelter can be taken by people on ground.

Re-entry and reintegration: returning home after combat.

PubMed

Doyle, Michael E; Peterson, Kris A

2005-01-01

Soldier life exists on a continuum of readiness for deployment. Re-entry and reintegration-the return home and reunion with family and community-key the success of the deployment cycle. In current and projected future operations, the Army and society will both bear the burden of this re-entry and re-integration. Programs and procedures in place work towards improving communication, mitigating distress and resolving crises during reentry and reintegration. Key elements include: inclusion of families and communities early into the planning for reentry and reintegration; normalization (non-medicalization of distress); easy access to behavioral health professionals; and education of families on resources and benefits. Through broad collaboration, maximal benefit to the Soldier, family members and society be realized.

A Second Chance to Dream: Initiating ODeL in Secondary School Re-Entry Programs for Young Adult Secondary School Dropouts the Case of Mumias District, Western Kenya

ERIC Educational Resources Information Center

Musita, Richard; Ogange, Betty O.; Lugendo, Dorine

2018-01-01

The Kenyan education system has very limited re-entry options for learners who drop out before attaining secondary school certificate. It is very difficult to access training and or secure a job that requires at least secondary school education. This study examined the prospects of initiating Open and Distance e-Learning(ODeL) in re-entry…

KSC-2013-3933

NASA Image and Video Library

2013-11-07

CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, three ogive panels have been installed on the Orion ground test vehicle in Vehicle Assembly Building high bay 4. The fourth ogive panel is being lifted by crane for installation. The ogive panels enclose and protect the Orion spacecraft and attach to the Launch Abort System. The test vehicle is being used by the Ground Systems Development and Operations Program for path finding operations, including simulated manufacturing, assembly and stacking procedures. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Kim Shiflett

KSC-2013-3930

NASA Image and Video Library

2013-10-30

CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, technicians assist as a crane is used to move one of four ogive panels closer for installation on the Orion ground test vehicle in Vehicle Assembly Building high bay 4. The ogive panels enclose and protect the Orion spacecraft and attach to the Launch Abort System. The test vehicle is being used by the Ground Systems Development and Operations Program for path finding operations, including simulated manufacturing, assembly and stacking procedures. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Kim Shiflett

KSC-2013-3929

NASA Image and Video Library

2013-10-30

CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, technicians monitor the progress as a crane is used to move one of four ogive panels closer for installation on the Orion ground test vehicle in Vehicle Assembly Building high bay 4. The ogive panels enclose and protect the Orion spacecraft and attach to the Launch Abort System. The test vehicle is being used by the Ground Systems Development and Operations Program for path finding operations, including simulated manufacturing, assembly and stacking procedures. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Kim Shiflett

KSC-2013-3927

NASA Image and Video Library

2013-10-30

CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, technicians prepare the four ogive panels for lifting by crane so that they can be installed on the Orion ground test vehicle in Vehicle Assembly Building high bay 4. The ogive panels enclose and protect the Orion spacecraft and attach to the Launch Abort System. The test vehicle is being used by the Ground Systems Development and Operations Program for path finding operations, including simulated manufacturing, assembly and stacking procedures. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Kim Shiflett

KSC-2013-3932

NASA Image and Video Library

2013-10-30

CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, technicians assist as a crane is used to move one of four ogive panels closer for installation on the Orion ground test vehicle in Vehicle Assembly Building high bay 4. The ogive panels enclose and protect the Orion spacecraft and attach to the Launch Abort System. The test vehicle is being used by the Ground Systems Development and Operations Program for path finding operations, including simulated manufacturing, assembly and stacking procedures. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Kim Shiflett

KSC-2013-3931

NASA Image and Video Library

2013-10-30

CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, technicians assist as a crane is used to move one of four ogive panels closer for installation on the Orion ground test vehicle in Vehicle Assembly Building high bay 4. The ogive panels enclose and protect the Orion spacecraft and attach to the Launch Abort System. The test vehicle is being used by the Ground Systems Development and Operations Program for path finding operations, including simulated manufacturing, assembly and stacking procedures. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Kim Shiflett

KSC-2013-3928

NASA Image and Video Library

2013-10-30

CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, technicians monitor the progress as a crane is used to move one of four ogive panels closer for installation on the Orion ground test vehicle in Vehicle Assembly Building high bay 4. The ogive panels enclose and protect the Orion spacecraft and attach to the Launch Abort System. The test vehicle is being used by the Ground Systems Development and Operations Program for path finding operations, including simulated manufacturing, assembly and stacking procedures. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Kim Shiflett

7 CFR 1530.107 - Bond or letter of credit requirements.

Code of Federal Regulations, 2013 CFR

2013-01-01

... SERVICE, DEPARTMENT OF AGRICULTURE THE REFINED SUGAR RE-EXPORT PROGRAM, THE SUGAR CONTAINING PRODUCTS RE..., which meets the criteria set forth in this section. (b) The bond or letter of credit may cover entries made either during the period of time specified in the bond (a term bond) or for a specified entry (a...

7 CFR 1530.107 - Bond or letter of credit requirements.

Code of Federal Regulations, 2012 CFR

2012-01-01

... SERVICE, DEPARTMENT OF AGRICULTURE THE REFINED SUGAR RE-EXPORT PROGRAM, THE SUGAR CONTAINING PRODUCTS RE..., which meets the criteria set forth in this section. (b) The bond or letter of credit may cover entries made either during the period of time specified in the bond (a term bond) or for a specified entry (a...

7 CFR 1530.107 - Bond or letter of credit requirements.

Code of Federal Regulations, 2014 CFR

2014-01-01

... SERVICE, DEPARTMENT OF AGRICULTURE THE REFINED SUGAR RE-EXPORT PROGRAM, THE SUGAR CONTAINING PRODUCTS RE..., which meets the criteria set forth in this section. (b) The bond or letter of credit may cover entries made either during the period of time specified in the bond (a term bond) or for a specified entry (a...

7 CFR 1530.107 - Bond or letter of credit requirements

Code of Federal Regulations, 2011 CFR

2011-01-01

... SERVICE, DEPARTMENT OF AGRICULTURE THE REFINED SUGAR RE-EXPORT PROGRAM, THE SUGAR CONTAINING PRODUCTS RE..., which meets the criteria set forth in this section. (b) The bond or letter of credit may cover entries made either during the period of time specified in the bond (a term bond) or for a specified entry (a...

Orion Entry Performance-Based Center-of-Gravity Box

NASA Technical Reports Server (NTRS)

Rea, Jeremy R.

2010-01-01

The Orion capsule is designed both for Low Earth Orbit missions to the ISS and for missions to the moon. For ISS class missions, the capsule will use an Apollo-style direct entry. For lunar return missions, depending on the timing of the mission, the capsule could perform a direct entry or a skip entry of up to 4800 n.mi. in order to land in the coastal waters of California. The physics of atmospheric re-entry determine the capability of the Orion vehicle. For a given vehicle mass and shape, physics tells us that the driving parameters for an entry vehicle are the hypersonic lift-to-drag ratio (L/D) and the flight path angle at entry interface (gamma(sub EI)). The design of the Orion atmospheric re-entry must meet constraints during both nominal and dispersed flight conditions on landing accuracy, heating rate, total heat load, sensed acceleration, and proper disposal of the Service Module. These constraints define an entry corridor in the space of L/D-gamma(sub EI); if the vehicle falls within this corridor, then all constraints are met. The gamma(sub EI) dimension of the corridor can be further constrained by the gloads experienced during emergency entries. Thus, the entry performance for the Orion vehicle can be described completely by the L/D. Bounds on the hypersonic L/D necessary to achieve all the mission requirements can be defined for the given entry corridor. Landing accuracy performance drives the lower limit on L/D. In order to achieve the desired landing accuracy, a minimum L/D must be ensured. The design of the Thermal Protection System (TPS) drives the upper limit on L/D. A higher L/D can drive mass into the design of the TPS. Conversely, once the TPS is designed, the L/D must be ensured to stay below a certain limit in order for the TPS to stay within its design envelop. The L/D must stay within its upper and lower bounds during dispersed flight conditions. L/D is a function of both the aerodynamics and the center-of-gravity (CG) of the vehicle. The aerodynamics of the vehicle are determined by Computational Fluid Mechanics (CFD) and wind tunnel tests. However, the aerodynamics are not known precisely. Instead, an aerodynamic database has been developed where the aerodynamic coefficients are known to fall within a probabilistic band defined by upper and lower bounds. It is expected that the probabilistic band will shrink after the first missions are flown and real-world data is collected. Until that time, the Orion must be designed to the current aerodynamic database. Thus, for a given aerodynamic database with given uncertainties, the allowable range in L/D can be mapped to an allowable box for the CG location. The CG box is used to set requirements on the dispersions allowed for vehicle packaging and cargo storage. As the aerodynamic uncertainties decrease, the size of the CG box can increase. This paper discusses the technique used to map the minimum and maximum L/D bounds set by the entry performance requirements to the allowable dispersions in CG while accounting for aerodynamic uncertainties. The L/D is defined as the ratio of the lift force to the drag force. It is equivalent to the ratio of lift coefficient (C(sub L)) over drag coefficient (C(sub D)). C(sub L) and C(sub D) are functions of Mach number (M) and angle of attack (alpha). A Mach number of 25 is used as a measuring point of the hypersonic L/D. Variations in C(sub L), C(sub D) and alpha cause variations in L/D. Equation (1) shows the three contributions to the variation in L/D.

Impact fuze testing at 3000 m/sec employing explosively accelerating plates

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

Gill, W.

1981-01-01

The Explosives Testing Division at Sandia has developed a method of simulating a re-entry vehicle impacting the ground. The purpose of the simulation is to evaluate different fusing concepts. The design and operation of this impact testing facility are described.

CPAS Parachute Testing, Model Development, & Verification

NASA Technical Reports Server (NTRS)

Romero, Leah M.

2013-01-01

Capsule Parachute Assembly System (CPAS) is the human rated parachute system for the Orion vehicle used during re-entry. Similar to Apollo parachute design. Human rating requires additional system redundancy. A Government Furnished Equipment (GFE) project responsible for: Design; Development testing; Performance modeling; Fabrication; Qualification; Delivery

Orion Flight Test-1 Thermal Protection System Instrumentation

NASA Technical Reports Server (NTRS)

Kowal, T. John

2011-01-01

The Orion Crew Exploration Vehicle (CEV) was originally under development to provide crew transport to the International Space Station after the retirement of the Space Shuttle, and to provide a means for the eventual return of astronauts to the Moon. With the current changes in the future direction of the United States human exploration programs, the focus of the Orion project has shifted to the project s first orbital flight test, designated Orion Flight Test 1 (OFT-1). The OFT-1 is currently planned for launch in July 2013 and will demonstrate the Orion vehicle s capability for performing missions in low Earth orbit (LEO), as well as extensibility beyond LEO for select, critical areas. Among the key flight test objectives are those related to validation of the re-entry aerodynamic and aerothermal environments, and the performance of the thermal protection system (TPS) when exposed to these environments. A specific flight test trajectory has been selected to provide a high energy entry beyond that which would be experienced during a typical low Earth orbit return, given the constraints imposed by the possible launch vehicles. This trajectory resulted from a trade study that considered the relative benefit of conflicting objectives from multiple subsystems, and sought to provide the maximum integrated benefit to the re-entry state-of-the-art. In particular, the trajectory was designed to provide: a significant, measureable radiative heat flux to the windward surface; data on boundary transition from laminar to turbulent flow; and data on catalytic heating overshoot on non-ablating TPS. In order to obtain the necessary flight test data during OFT-1, the vehicle will need to have an adequate quantity of instrumentation. A collection of instrumentation is being developed for integration in the OFT-1 TPS. In part, this instrumentation builds upon the work performed for the Mars Science Laboratory Entry, Descent and Landing Instrument (MEDLI) suite to instrument the OFT-1 ablative heat shield. The MEDLI integrated sensor plugs and pressure sensors will be adapted for compatibility with the Orion TPS design. The sensor plugs will provide in-depth temperature data to support aerothermal and TPS model correlation, and the pressure sensors will provide a flush air data system for validation of the entry and descent aerodynamic environments. In addition, a radiometer design will be matured to measure the radiative component of the reentry heating at two locations on the heat shield. For the back shell, surface thermocouple and pressure port designs will be developed and applied which build upon the heritage of the Space Shuttle Program for instrumentation of reusable surface insulation (RSI) tiles. The quantity and location of the sensors has been determined to balance the needs of the reentry disciplines with the demands of the hardware development, manufacturing and integration. Measurements which provided low relative value and presented significant engineering development effort were, unfortunately, eliminated. The final TPS instrumentation has been optimized to target priority test objectives. The data obtained will serve to provide a better understanding of reentry environments for the Orion capsule design, reduce margins, and potentially reduce TPS mass or provide TPS extensibility for alternative missions.

The Status of Spacecraft Bus and Platform Technology Development under the NASA ISPT Program

NASA Technical Reports Server (NTRS)

Anderson, David J.; Munk, Michelle M.; Pencil, Eric; Dankanich, John; Glaab, Louis; Peterson, Todd

2013-01-01

The In-Space Propulsion Technology (ISPT) program is developing spacecraft bus and platform technologies that will enable or enhance NASA robotic science missions. The ISPT program is currently developing technology in four areas that include Propulsion System Technologies (electric and chemical), Entry Vehicle Technologies (aerocapture and Earth entry vehicles), Spacecraft Bus and Sample Return Propulsion Technologies (components and ascent vehicles), and Systems/Mission Analysis. Three technologies are ready for near-term flight infusion: 1) the high-temperature Advanced Material Bipropellant Rocket (AMBR) engine providing higher performance; 2) NASA s Evolutionary Xenon Thruster (NEXT) ion propulsion system, a 0.6-7 kW throttle-able gridded ion system; and 3) Aerocapture technology development with investments in a family of thermal protection system (TPS) materials and structures; guidance, navigation, and control (GN&C) models of blunt-body rigid aeroshells; and aerothermal effect models. Two component technologies being developed with flight infusion in mind are the Advanced Xenon Flow Control System and ultralightweight propellant tank technologies. Future directions for ISPT are technologies that relate to sample return missions and other spacecraft bus technology needs like: 1) Mars Ascent Vehicles (MAV); 2) multi-mission technologies for Earth Entry Vehicles (MMEEV); and 3) electric propulsion. These technologies are more vehicles and mission-focused, and present a different set of technology development and infusion steps beyond those previously implemented. The Systems/Mission Analysis area is focused on developing tools and assessing the application of propulsion and spacecraft bus technologies to a wide variety of mission concepts. These inspace propulsion technologies are applicable, and potentially enabling for future NASA Discovery, New Frontiers, and sample return missions currently under consideration, as well as having broad applicability to potential Flagship missions. This paper provides a brief overview of the ISPT program, describing the development status and technology infusion readiness of in-space propulsion technologies in the areas of electric propulsion, Aerocapture, Earth entry vehicles, propulsion components, Mars ascent vehicle, and mission/systems analysis.

The status of spacecraft bus and platform technology development under the NASA ISPT program

NASA Astrophysics Data System (ADS)

Anderson, D. J.; Munk, M. M.; Pencil, E.; Dankanich, J.; Glaab, L.; Peterson, T.

The In-Space Propulsion Technology (ISPT) program is developing spacecraft bus and platform technologies that will enable or enhance NASA robotic science missions. The ISPT program is currently developing technology in four areas that include Propulsion System Technologies (electric and chemical), Entry Vehicle Technologies (aerocapture and Earth entry vehicles), Spacecraft Bus and Sample Return Propulsion Technologies (components and ascent vehicles), and Systems/Mission Analysis. Three technologies are ready for near-term flight infusion: 1) the high-temperature Advanced Material Bipropellant Rocket (AMBR) engine providing higher performance; 2) NASA's Evolutionary Xenon Thruster (NEXT) ion propulsion system, a 0.6-7 kW throttle-able gridded ion system; and 3) Aerocapture technology development with investments in a family of thermal protection system (TPS) materials and structures; guidance, navigation, and control (GN& C) models of blunt-body rigid aeroshells; and aerothermal effect models. Two component technologies being developed with flight infusion in mind are the Advanced Xenon Flow Control System and ultra-lightweight propellant tank technologies. Future directions for ISPT are technologies that relate to sample return missions and other spacecraft bus technology needs like: 1) Mars Ascent Vehicles (MAV); 2) multi-mission technologies for Earth Entry Vehicles (MMEEV); and 3) electric propulsion. These technologies are more vehicles and mission-focused, and present a different set of technology development and infusion steps beyond those previously implemented. The Systems/Mission Analysis area is focused on developing tools and assessing the application of propulsion and spacecraft bus technologies to a wide variety of mission concepts. These in-space propulsion technologies are applicable, and potentially enabling for future NASA Discovery, New Frontiers, and sample return missions currently under consideration, as well as having broad applicabilit- to potential Flagship missions. This paper provides a brief overview of the ISPT program, describing the development status and technology infusion readiness of in-space propulsion technologies in the areas of electric propulsion, Aerocapture, Earth entry vehicles, propulsion components, Mars ascent vehicle, and mission/systems analysis.

The Status of Spacecraft Bus and Platform Technology Development Under the NASA ISPT Program

NASA Technical Reports Server (NTRS)

Anderson, David J.; Munk, Michelle M.; Pencil, Eric J.; Dankanich, John; Glaab, Louis J.

2013-01-01

The In-Space Propulsion Technology (ISPT) program is developing spacecraft bus and platform technologies that will enable or enhance NASA robotic science missions. The ISPT program is currently developing technology in four areas that include Propulsion System Technologies (electric and chemical), Entry Vehicle Technologies (aerocapture and Earth entry vehicles), Spacecraft Bus and Sample Return Propulsion Technologies (components and ascent vehicles), and Systems/Mission Analysis. Three technologies are ready for near-term flight infusion: 1) the high-temperature Advanced Material Bipropellant Rocket (AMBR) engine providing higher performance 2) NASAs Evolutionary Xenon Thruster (NEXT) ion propulsion system, a 0.6-7 kW throttle-able gridded ion system and 3) Aerocapture technology development with investments in a family of thermal protection system (TPS) materials and structures guidance, navigation, and control (GN&C) models of blunt-body rigid aeroshells and aerothermal effect models. Two component technologies being developed with flight infusion in mind are the Advanced Xenon Flow Control System, and ultra-lightweight propellant tank technologies. Future direction for ISPT are technologies that relate to sample return missions and other spacecraft bus technology needs like: 1) Mars Ascent Vehicles (MAV) 2) multi-mission technologies for Earth Entry Vehicles (MMEEV) and 3) electric propulsion. These technologies are more vehicle and mission-focused, and present a different set of technology development and infusion steps beyond those previously implemented. The Systems/Mission Analysis area is focused on developing tools and assessing the application of propulsion and spacecraft bus technologies to a wide variety of mission concepts. These in-space propulsion technologies are applicable, and potentially enabling for future NASA Discovery, New Frontiers, and sample return missions currently under consideration, as well as having broad applicability to potential Flagship missions. This paper provides a brief overview of the ISPT program, describing the development status and technology infusion readiness of in-space propulsion technologies in the areas of electric propulsion, Aerocapture, Earth entry vehicles, propulsion components, Mars ascent vehicle, and mission/systems analysis.

Design, integration and preliminary results of the IXV Catalysis experiment

NASA Astrophysics Data System (ADS)

Viladegut, Alan; Panerai, F.; Chazot, O.; Pichon, T.; Bertrand, P.; Verdy, C.; Coddet, C.

2017-06-01

The CATalytic Experiment (CATE) is an in-flight demonstration of catalysis effects at the surface of thermal protection materials. A high-catalytic coating was applied over the baseline ceramic material on the windward side of the intermediate experimental vehicle (IXV). The temperature jump due to different catalytic activities was detected during re-entry through measurements made with near-surface thermocouples on the windward side of the vehicle. The experiment aimed at contributing to the development and validation of gas/surface interaction models for re-entry applications. The present paper summarizes the design of CATE and its integration on the windward side of the IXV. Results of a qualification campaign at the Plasmatron facility of the von Karman Institute for Fluid Dynamics are presented. They provided an experimental evidence of the temperature jump at the low-to-high catalytic interface of the heat shield under aerothermal conditions relevant to the actual IXV flight. These tests also gave confidence so that the high-catalytic patch would not endanger the integrity of the vehicle and the safety of the mission. A preliminary assessment of flight data from the thermocouple measurements shows consistency with results of the qualification tests.

Pre-X Experimental Re-Entry Lifting Body: Design of Flight Test Experiments for Critical Aerothermal Phenomena

DTIC Science & Technology

2007-06-01

the CNES proposal to perform in-flight experimentation mainly on reusable thermal protections, aero-thermo-dynamics and guidance to secure the second...the vehicle. A preliminary in-flight experimentation and measurement plan has been assessed defining the main objectives in terms of reusable Thermal ...Energy Management THEFA Thermographie Face Arrière TPS Thermal Protection System VKI Von Karman Institute WRT With Respect To WTT Wind

Hot-Air Jets/Ceramic Heat Exchangers/ Materials for Nose Cones and Reentry Vehicles

NASA Image and Video Library

1957-09-07

L57-5383 Hot-air jets employing ceramic heat exchangers played an important role at Langley in the study of materials for ballistic missile nose cones and re-entry vehicles. Here a model is being tested in one of theses jets at 4000 degrees Fahrenheit in 1957. Photograph published in Engineer in Charge: A History of the Langley Aeronautical Laboratory, 1917-1958 by James R. Hansen. Page 477.

Pegasus5 is Co-Winner of NASA's 2016 Software of the Year Award

NASA Image and Video Library

2016-11-04

Shareable video highlighting the Pegasus5 software, which was the co-winner of the NASA's 2016 Software of the Year award. Developed at NASA Ames, it helps in the simulation of air flow around space vehicles during launch and re-entry.

75 FR 5579 - Privacy Act of 1974; System of Records

Federal Register 2010, 2011, 2012, 2013, 2014

2010-02-03

... with re-entry controlled by passwords. The DLA Enterprise Hotline Program Database is also password...: * * * * * System location: Delete entry and replace with ``Director, DLA Accountability Office (DA), Headquarters....'' * * * * * Retention and disposal: Delete entry and replace with ``Records are destroyed/deleted 10 years after...

Solar power satellite system definition study. Part 2, volume 8: SPS launch vehicle ascent and entry sonic overpressure and noise effects

NASA Technical Reports Server (NTRS)

1977-01-01

Recoverable launch vehicle concepts for the Solar Power Satellite program were identified. These large launch vehicles are powered by proposed engines in the F-1 thrust level class. A description of the candidate launch vehicles and their operating mode was provided. Predictions of the sonic over pressures during ascent and entry for both types of vehicles, and prediction of launch noise levels in the vicinity of the launch site were included. An overall assessment and criteria for sonic overpressure and noise levels was examined.

Aerodynamic Challenges for the Mars Science Laboratory Entry, Descent and Landing

NASA Technical Reports Server (NTRS)

Schoenenberger, Mark; Dyakonov, Artem; Buning, Pieter; Scallion, William; Norman, John Van

2009-01-01

An overview of several important aerodynamics challenges new to the Mars Science Laboratory (MSL) entry vehicle are presented. The MSL entry capsule is a 70 degree sphere cone-based on the original Mars Viking entry capsule. Due to payload and landing accuracy requirements, MSL will be flying at the highest lift-to-drag ratio of any capsule sent to Mars (L/D = 0.24). The capsule will also be flying a guided entry, performing bank maneuvers, a first for Mars entry. The system's mechanical design and increased performance requirements require an expansion of the MSL flight envelope beyond those of historical missions. In certain areas, the experience gained by Viking and other recent Mars missions can no longer be claimed as heritage information. New analysis and testing is re1quired to ensure the safe flight of the MSL entry vehicle. The challenge topics include: hypersonic gas chemistry and laminar-versus-turbulent flow effects on trim angle, a general risk assessment of flying at greater angles-of-attack than Viking, quantifying the aerodynamic interactions induced by a new reaction control system and a risk assessment of recontact of a series of masses jettisoned prior to parachute deploy. An overview of the analysis and tests being conducted to understand and reduce risk in each of these areas is presented. The need for proper modeling and implementation of uncertainties for use in trajectory simulation has resulted in a revision of prior models and additional analysis for the MSL entry vehicle. The six degree-of-freedom uncertainty model and new analysis to quantify roll torque dispersions are presented.

Grid resolution and solution convergence for Mars Pathfinder forebody

NASA Technical Reports Server (NTRS)

Nettelhorst, Heather L.; Mitcheltree, Robert A.

1994-01-01

As part of the Discovery Program, NASA Plans to launch a series of probes to Mars. The Mars Pathfinder project is the first of this series with a scheduled Mars arrival in July 1997. The entry vehicle will perform a direct entry into the atmosphere and deliver a lander to the surface. Predicting the entry vehicle's flight performance and designing the forebody heatshield requires knowledge of the expected aerothermodynamic environment. Much of this knowledge can be obtained through computational fluid dynamic (CFD) analysis.

Incarcerated Veterans Outreach Program.

PubMed

Schaffer, Bradley J

2016-01-01

The objective of this study is to identify and facilitate re-entry services for military veterans in the Criminal Justice System through the Incarcerated Veteran Outreach Program. Veterans are explored as a subgroup of the general inmate jail populations in southern Ohio based upon veteran's status, military discharges, service-related injuries, treatment needs, pre-release planning, and re-entry services. Veterans reported having psycho-social problems, diverse levels of criminality, criminogenic needs, and significant episodes of homelessness. A sample of 399 incarcerated veterans in state prison, county jails, and community corrections setting were identified and completed the psycho-social pre-release assessment. Their average age was 44.6; they were more likely to be White males, divorced, most honorably discharged, and were represented in the following eras: 34% Vietnam, 35% post-Vietnam, 26% Persian Gulf War, and 5% Operation Iraqi Freedom/Operation Enduring Freedom. The findings encourage the development of a re-entry outreach model and strategies to prevent episodes of criminal recidivism.

Atomic and molecular data for spacecraft re-entry plasmas

NASA Astrophysics Data System (ADS)

Celiberto, R.; Armenise, I.; Cacciatore, M.; Capitelli, M.; Esposito, F.; Gamallo, P.; Janev, R. K.; Laganà, A.; Laporta, V.; Laricchiuta, A.; Lombardi, A.; Rutigliano, M.; Sayós, R.; Tennyson, J.; Wadehra, J. M.

2016-06-01

The modeling of atmospheric gas, interacting with the space vehicles in re-entry conditions in planetary exploration missions, requires a large set of scattering data for all those elementary processes occurring in the system. A fundamental aspect of re-entry problems is represented by the strong non-equilibrium conditions met in the atmospheric plasma close to the surface of the thermal shield, where numerous interconnected relaxation processes determine the evolution of the gaseous system towards equilibrium conditions. A central role is played by the vibrational exchanges of energy, so that collisional processes involving vibrationally excited molecules assume a particular importance. In the present paper, theoretical calculations of complete sets of vibrationally state-resolved cross sections and rate coefficients are reviewed, focusing on the relevant classes of collisional processes: resonant and non-resonant electron-impact excitation of molecules, atom-diatom and molecule-molecule collisions as well as gas-surface interaction. In particular, collisional processes involving atomic and molecular species, relevant to Earth (N2, O2, NO), Mars (CO2, CO, N2) and Jupiter (H2, He) atmospheres are considered.

Analysis of bluetooth and wi-fi technology to measure wait times of personal vehicles at Arizona-Mexico ports of entry : [executive summary].

DOT National Transportation Integrated Search

2015-11-01

The Arizona Department of Transportation (ADOT), Office of P3 Initiatives and International : Affairs selected Lee Engineering to analyze the penetration rate of Anonymous Re-Identification : (ARID) technology to measure wait time of U.S. and Mexico ...

Orion Heat Shield Manufacturing Producibility Improvements for the EM-1 Flight Test Program

NASA Technical Reports Server (NTRS)

Koenig, William J.; Stewart, Michael; Harris, Richard F.

2018-01-01

This paper describes how the ORION program is incorporating improvements in the heat shield design and manufacturing processes reducing programmatic risk and ensuring crew safety in support of NASA's Exploration missions. The approach for the EFT-1 heat shield utilized a low risk Apollo heritage design and manufacturing process using an Avcoat TPS ablator with a honeycomb substrate to provide a one piece heat shield to meet the mission re-entry heating environments. The EM-1 mission will have additional flight systems installed to fly to the moon and return to Earth. Heat shield design and producibility improvements have been incorporated in the EM-1 vehicle to meet deep space mission requirements. The design continues to use the Avcoat material, but in a block configuration to enable improvements in consistant and repeatable application processes using tile bonding experience developed on the Space Shuttle Transportation System Program.

Aerobraking characteristics for several potential manned Mars entry vehicles

NASA Technical Reports Server (NTRS)

Tartabini, Paul V.; Suit, William T.

1989-01-01

While a reduction in weight is always desirable for any space vehicle, it is crucial for vehicles to be used in the proposed Manned Mars Mission (MMM). One such way to reduce a spacecraft's weight is through aeroassist braking which is an alternative to retro-rockets, the traditional method of slowing a craft approaching from a high energy orbit. In this paper aeroassist braking was examined for two blunt vehicle configurations and one streamlined configuration. For each vehicle type, a range of lift-to-drag ratios was examined and the entry angle windows, bank profiles, and trajectory parameters were recorded here. In addition, the sensitivities of velocity and acceleration with respect to the entry angle and bank angles were included. Also, the effect of using different atmosphere models was tested by incorporating several models into the simulation program.

Connected Vehicle Pilot Deployment Program, Comprehensive Installation Plan - WYDOT CV Pilot

DOT National Transportation Integrated Search

2018-02-16

The Wyoming Department of Transportation's (WYDOT) Connected Vehicle (CV) Pilot Deployment Program is intended to develop a suite of applications that utilize vehicle-to-infrastructure (V2I) and vehicle-to-vehicle (V2V) communication technology to re...

Connected vehicle pilot deployment program phase 2 : data management plan - Tampa (THEA).

DOT National Transportation Integrated Search

2017-10-01

The Tampa Hillsborough Expressway Authority (THEA) Connected Vehicle (CV) Pilot Deployment Program is intended to develop a suite of applications that utilize vehicle-to-infrastructure (V2I) and vehicle-to-vehicle (V2V) communication technology to re...

Orion Entry Performance-Based Center-of-Gravity Box

NASA Technical Reports Server (NTRS)

Rea, Jeremy R.

2010-01-01

The Orion capsule has many performance requirements for its atmospheric entry trajectory. Requirements on landing accuracy, maximum heating rate, total heat load, propellant usage, and sensed acceleration must all be satised. It is desired to define a methodology to translate the many performance requirements for an atmospheric entry trajectory into language easily understood by vehicle designers in terms of an allowable center-of-gravity box. This is possible by noting that most entry performance parameters for a capsule vehicle are mainly determined by the lift-to-drag ratio of the vehicle. However, the lift-to- drag ratio should be considered a probabilistic quantity rather than deterministic, where variations in the lift-to-drag are caused by both aerodynamic and center-of-gravity un- certainties. This paper discusses the technique used by the Orion program to define the allowable dispersions in center-of-gravity to achieve the desired entry performance while accounting for aerodynamic uncertainty.

7 CFR 1260.302 - Organic exemption.

Code of Federal Regulations, 2014 CFR

2014-01-01

... National Organic Program (NOP) (7 CFR part 205) system plan; only produces products that re eligible to be... classification should be entered by the importer on the Customs entry documentation. Any line item entry of 100...

7 CFR 1260.302 - Organic exemption.

Code of Federal Regulations, 2011 CFR

2011-01-01

... National Organic Program (NOP) (7 CFR part 205) system plan; only produces products that re eligible to be... classification should be entered by the importer on the Customs entry documentation. Any line item entry of 100...

7 CFR 1260.302 - Organic exemption.

Code of Federal Regulations, 2012 CFR

2012-01-01

... National Organic Program (NOP) (7 CFR part 205) system plan; only produces products that re eligible to be... classification should be entered by the importer on the Customs entry documentation. Any line item entry of 100...

7 CFR 1260.302 - Organic exemption.

Code of Federal Regulations, 2013 CFR

2013-01-01

... National Organic Program (NOP) (7 CFR part 205) system plan; only produces products that re eligible to be... classification should be entered by the importer on the Customs entry documentation. Any line item entry of 100...

A cost engineered launch vehicle for space tourism

NASA Astrophysics Data System (ADS)

Koelle, -Ing. Dietrich E., , Dr.

1999-09-01

The paper starts with a set of major requirements for a space tourism vehicle and discusses major vehicle options proposed for this purpose. It seems that the requirements can be met best with a Ballistic SSTO Vehicle which has the additional advantage of lowest development cost compared to other launch vehicle options — important for a commercial development venture. The BETA Ballistic Reusable Vehicle Concept is characterized by the plug nozzle cluster engine configuration where the plug nozzle serves also as base plate and re-entry heat shield. In this case no athmospheric turn maneuver is required (as in case-of the front-entry Delta-Clipper DC-Y concept). In our specific case for space tourism this mode has the avantage that the forces at launch and reentry are in exactly the same direction, easing passenger seating arrangements. The second basic advantage is the large available volume on top of the vehicle providing ample space for passenger accomodation, visibility and volume for zero-g experience (free floating), one of the major passenger mission requirements. An adequate passenger cabin design for 100 passengers is presented, as well as the modern BETA-STV Concept with its mass allocations.

Connected Vehicle Pilot Deployment Program phase 1 : application deployment : Tampa (THEA) : final report.

DOT National Transportation Integrated Search

2016-09-01

The Tampa Hillsborough Expressway Authority (THEA) Connected Vehicle (CV) Pilot Deployment Program is intended to develop a suite of applications that utilize vehicle-to-infrastructure (V2I) and vehicle-to-vehicle (V2V) communication technology to re...

Connected vehicle pilot deployment program phase II data privacy plan – Tampa (THEA).

DOT National Transportation Integrated Search

2017-02-01

The Tampa Hillsborough Expressway Authority (THEA) Connected Vehicle (CV) Pilot Deployment Program is intended to develop a suite of applications that utilize vehicle to infrastructure (V2I) and vehicle to vehicle (V2V) communication technology to re...

Student retention practices in associate degree, entry-level dental hygiene programs.

PubMed

Holt, Marianne P

2005-01-01

The main purpose of this study was to investigate student retention strategies and practices implemented in associate degree, entry-level dental hygiene programs. Included are student attrition issues, academic standards, re-entry policies, and clinical remediation strategies. A survey consisting of forced choice and open-ended questions was mailed to 31 randomly selected associate degree, entry-level dental hygiene programs. Surveys were analyzed using descriptive statistics and frequency distributions. Open-ended questions were analyzed using the constant comparative qualitative method to identify recurring themes. There was an 80% (n=25) return response to the survey. The findings of this study determined that dental hygiene programs are graduating, on average, a higher percentage (83%) of students when compared to two-year, associate degree programs in general (46%). The primary reasons reported by respondents for student attrition included: academic difficulties (88%), dissatisfaction with career choice (76%), family/personal responsibilities (72%), and clinical skill difficulties (56%). A wide variety of retention strategies were reported. Those most often cited were academic remediation (92%), clinical skill development/remediation (84%), academic advising (84%), financial aid assistance (84%), and tutoring (80%). Participating programs also reported setting high academic and ethical standards. Specific criteria for student re-entry were discussed. The findings of this study suggest that associate degree, entry-level dental hygiene programs are committed to student retention and make considerable efforts to help students succeed. Student retention efforts could be enhanced for those student groups identified as possibly being at high risk for attrition. The findings and recommendations in this investigation may assist associate degree, entry-level dental hygiene programs in their efforts to retain a higher percentage of students.

Physician Assistant profession (PA)

MedlinePlus

... administer a certification program. This program includes an entry-level examination, continuing medical education, and periodic re-examination for recertification. Only physician assistants who are ...

Predictors of homeless services re-entry within a sample of adults receiving Homelessness Prevention and Rapid Re-Housing Program (HPRP) assistance.

PubMed

Brown, Molly; Vaclavik, Danielle; Watson, Dennis P; Wilka, Eric

2017-05-01

Local and national evaluations of the federal Homelessness Prevention and Rapid Re-Housing Program (HPRP) have demonstrated a high rate of placement of program participants in permanent housing. However, there is a paucity of research on the long-term outcomes of HPRP, and research on rehousing and prevention interventions for single adults experiencing homelessness is particularly limited. Using Homeless Management Information System data from 2009 to 2015, this study examined risk of return to homeless services among 370 permanently housed and 71 nonpermanently housed single adult HPRP participants in Indianapolis, Indiana. Kaplan-Meier survival curves were conducted to analyze time-to-service re-entry for the full sample, and the homelessness prevention and rapid rehousing participants separately. With an average follow-up of 4.5 years after HPRP exit, 9.5% of the permanently housed HPRP participants and 16.9% of those nonpermanently housed returned to homeless services. By assistance type, 5.4% of permanently housed and 15.8% of nonpermanently housed homelessness prevention recipients re-entered services, and 12.8% of permanently housed and 18.2% of nonpermanently housed rapid rehousing recipients re-entered during the follow-up period. Overall, veterans, individuals receiving rapid rehousing services, and those whose income did not increase during HPRP had significantly greater risk of returning to homeless services. Veterans were at significantly greater risk of re-entry when prevention and rehousing were examined separately. Findings suggest a need for future controlled studies of prevention and rehousing interventions for single adults, aiming to identify unique service needs among veterans and those currently experiencing homelessness in need of rehousing to inform program refinement. (PsycINFO Database Record (c) 2017 APA, all rights reserved).

HIFiRE-5 Flight Vehicle Design

NASA Technical Reports Server (NTRS)

Kimmel, Roger L.; Adamczak, David; Berger, Karen; Choudhari, Meelan

2010-01-01

The Hypersonic International Flight Research Experimentation (HIFiRE) program is a hypersonic flight test program executed by the Air Force Research Laboratories (AFRL) and Australian Defence Science and Technology Organization (DSTO). HIFiRE flight 5 is devoted to measuring transition on a three-dimensional body. This paper summarizes payload configuration, trajectory, vehicle stability limits and roughness tolerances. Results show that the proposed configuration is suitable for testing transition on a three-dimensional body. Transition is predicted to occur within the test window, and a design has been developed that will allow the vehicle to be manufactured within prescribed roughness tolerances

NASA In-Space Propulsion Technologies and Their Infusion Potential

NASA Technical Reports Server (NTRS)

Anderson, David J.; Pencil,Eric J.; Peterson, Todd; Vento, Daniel; Munk, Michelle M.; Glaab, Louis J.; Dankanich, John W.

2012-01-01

The In-Space Propulsion Technology (ISPT) program has been developing in-space propulsion technologies that will enable or enhance NASA robotic science missions. The ISPT program is currently developing technology in four areas that include Propulsion System Technologies (Electric and Chemical), Entry Vehicle Technologies (Aerocapture and Earth entry vehicles), Spacecraft Bus and Sample Return Propulsion Technologies (components and ascent vehicles), and Systems/Mission Analysis. Three technologies are ready for flight infusion: 1) the high-temperature Advanced Material Bipropellant Rocket (AMBR) engine providing higher performance; 2) NASA s Evolutionary Xenon Thruster (NEXT) ion propulsion system, a 0.6-7 kW throttle-able gridded ion system; and 3) Aerocapture technology development with investments in a family of thermal protection system (TPS) materials and structures; guidance, navigation, and control (GN&C) models of blunt-body rigid aeroshells; and aerothermal effect models. Two component technologies that will be ready for flight infusion in the near future will be Advanced Xenon Flow Control System, and ultra-lightweight propellant tank technologies. Future focuses for ISPT are sample return missions and other spacecraft bus technologies like: 1) Mars Ascent Vehicles (MAV); 2) multi-mission technologies for Earth Entry Vehicles (MMEEV) for sample return missions; and 3) electric propulsion for sample return and low cost missions. These technologies are more vehicle-focused, and present a different set of technology infusion challenges. While the Systems/Mission Analysis area is focused on developing tools and assessing the application of propulsion technologies to a wide variety of mission concepts. These in-space propulsion technologies are applicable, and potentially enabling for future NASA Discovery, New Frontiers, and sample return missions currently under consideration, as well as having broad applicability to potential Flagship missions. This paper provides a brief overview of the ISPT program, describing the development status and technology infusion readiness of in-space propulsion technologies in the areas of electric propulsion, aerocapture, Earth entry vehicles, propulsion components, Mars ascent vehicle, and mission/systems analysis.

Connected vehicle pilot deployment program phase I : security management operational concept, Tampa Hillsborough Expressway Authority (THEA).

DOT National Transportation Integrated Search

2016-05-01

The Tampa Hillsborough Expressway Authority (THEA) Connected Vehicle (CV) Pilot Deployment Program is intended to develop a suite of applications that utilize vehicle to infrastructure (V2I) and vehicle to vehicle (V2V) communication technology to re...

75 FR 23631 - Sugar Re-Export Program, the Sugar-Containing Products Re-Export Program, and the Polyhydric...

Federal Register 2010, 2011, 2012, 2013, 2014

2010-05-04

...), Additional U.S. Note 6, which authorizes entry of raw cane sugar under subheading 1701.11.20 of the HTS for..., or to be substituted for domestically produced raw cane sugar that has been or will be exported. The...

Hypersonic vehicle control law development using H(infinity) and micron-synthesis

NASA Technical Reports Server (NTRS)

Gregory, Irene M.; Mcminn, John D.; Shaughnessy, John D.; Chowdhry, Rajiv S.

1993-01-01

Hypersonic vehicle control law development using H(infinity) and mu-synthesis is discussed. Airbreathing SSTO vehicles has a mutli-faceted mission that includes orbital operations, as well as re-entry and descent culminating in horizontal landing. However, the most challenging part of the operations is the ascent to orbit. The airbreathing propulsion requires lengthy atmospheric flight that may last as long as 30 minutes and take the vehicle half way around the globe. The vehicles's ascent is characterized by tight payload to orbit margins which translate into minimum fuel orbit as the performance criteria. Issues discussed include: SSTO airbreathing vehicle issues; control system performance requirements; robust control law framework; H(infinity) controller frequency analysis; and mu controller frequency analysis.

Evaluation of the Positive Re-Entry in Corrections Program: A Positive Psychology Intervention With Prison Inmates.

PubMed

Huynh, Kim H; Hall, Brittany; Hurst, Mark A; Bikos, Lynette H

2015-08-01

Two groups of male inmates (n = 31, n = 31) participated in the Positive Re-Entry in Corrections Program (PRCP). This positive psychology intervention focused on teaching offenders skills that facilitate re-entry into the community. Offenders participated in weekly lectures, discussions, and homework assignments focused on positive psychology principles. The two groups differed in duration of treatment (8 weeks and 12 weeks). Participants completed pre- and post-intervention measures of gratitude, hope, and life satisfaction. Using a 2 × 2 mixed design ANOVA, we hypothesized that the intervention (with two between-subjects levels of 8 and 12 weeks) and duration (with two repeated measures levels of pre and post) of treatment would moderate pre- to post-intervention change. Results indicated significant differences on pre- and post-intervention scores for both groups of offenders on all measures. The analysis did not yield statistically significant differences between groups, demonstrating no additive benefits from the inclusion of four additional sessions, thus saving time and money for correctional programming and funding. This research supports the use of positive psychology in prison interventions. © The Author(s) 2014.

Re-entry and related predictors among HIV-infected clients receiving methadone maintenance treatment in Guangdong province, China.

PubMed

Luo, Xiaofeng; Gong, Xiao; Zhao, Peizhen; Zou, Xia; Chen, Wen; Ling, Li

2017-07-24

This study examined the re-entry characteristics and related predictors among HIV-infected methadone maintenance treatment (MMT) clients in Guangdong, China. Data on HIV-infected MMT clients was obtained from the clinic MMT registration system in Guangdong. Of the 653 participants, only 9.0% remained in the MMT program until the end of the study. For the drop-outs, 70.0% returned to MMT at least once by the end of the study. Re-entry was independently associated with marital status (OR never married = 2.24, 95% CI: 1.02-4.93; OR married currently = 2.34, 95% CI: 1.05-5.22), being unemployed (OR = 1.92, 95% CI: 1.12-3.27), lower positive percentages of urine tests (OR <40% = 4.08, 95% CI: 2.21-7.54; OR 40%-80% = 2.52, 95% CI: 1.39-4.56), higher maintenance doses (OR = 3.78, 95% CI: 2.21-7.54)and poorer MMT attendance percentages (OR <20% = 282.02, 95% CI: 62.75-1268.11; OR20-49% = 20.75, 95% CI: 10.52-40.93; OR50-79% = 6.07, 95% CI: 3.44-10.73). A higher re-entry frequency was independently associated with lower education level (ORjunior high school = 0.49, 95% CI: 0.26-0.93), average drug use times less than twice (OR = 0.64, 95% CI: 0.41-1.00), lower positive percentages of urine tests (OR = 0.39, 95% CI: 0.22-0.70) and poorer percentages of MMT attendance (OR<20% = 7.24, 95% CI: 2.99-17.55; OR20-49% = 14.30, 95% CI: 5.94-34.42; OR50-79% = 6.15, 95% CI: 2.55-14.85). Re-entry and repeated re-entry were prevalent among HIV-infected MMT clients in Guangdong, underscoring the urgent needs of tailored interventions and health education programs for this population.

KSC-2012-4386

NASA Image and Video Library

2012-07-24

LAS VEGAS -- The Boeing Company tests the forward heat shield FHS jettison system of its CST-100 spacecraft at the Bigelow Aerospace facility in Las Vegas as part of an agreement with NASA's Commercial Crew Program CCP during Commercial Crew Development Round 2 CCDev2) activities. The FHS will protect the spacecraft's parachutes, rendezvous-and-docking sensor packages, and docking mechanism during ascent and re-entry. During a mission to low Earth orbit, the shield will be jettisoned after re-entry heating, allowing the spacecraft's air bags to deploy for a safe landing. In 2011, NASA selected Boeing for CCDev2 to mature the design and development of a crew transportation system with the overall goal of accelerating a United States-led capability to the International Space Station. The goal of CCP is to drive down the cost of space travel as well as open up space to more people than ever before by balancing industry’s own innovative capabilities with NASA's 50 years of human spaceflight experience. Six other aerospace companies also were selected to mature launch vehicle and spacecraft designs under CCDev2, including Alliant Techsystems Inc. ATK, Excalibur Almaz Inc., Blue Origin, Sierra Nevada Corp. SNC, Space Exploration Technologies SpaceX, and United Launch Alliance ULA. For more information, visit www.nasa.gov/commercialcrew. Image credit: Boeing The Ground Systems Development and Operations Program is developing the necessary ground systems, infrastructure and operational approaches required to safely process, assemble, transport and launch the next generation of rockets and spacecraft in support of NASA’s exploration objectives. Future work also will replace the antiquated communications, power and vehicle access resources with modern efficient systems. Some of the utilities and systems slated for replacement have been used since the VAB opened in 1965. For more information, visit http://www.nasa.gov/exploration/systems/ground/index.html Photo credit: Boeing

Mercury Project

NASA Image and Video Library

1959-09-01

An Atlas launch vehicle carrying the Big Joe capsule leaves its launching pad on a 2,000-mile ballistic flight to the altitude of 100 miles. The Big Joe capsule is a boilerplate model of the marned orbital capsule under NASA's Project Mercury. The capsule was recovered and studied for the effect of re-entry heat and other flight stresses.

Spacecraft Bus and Platform Technology Development under the NASA ISPT Program

NASA Technical Reports Server (NTRS)

Anderson, David J.; Munk, Michelle M.; Pencil, Eric; Dankanich, John; Glaab, Louis; Peterson, Todd

2013-01-01

The In-Space Propulsion Technology (ISPT) program is developing spacecraft bus and platform technologies that will enable or enhance NASA robotic science missions. The ISPT program is currently developing technology in four areas that include Propulsion System Technologies (electric and chemical), Entry Vehicle Technologies (aerocapture and Earth entry vehicles), Spacecraft Bus and Sample Return Propulsion Technologies (components and ascent vehicles), and Systems/Mission Analysis. Three technologies are ready for near-term flight infusion: 1) the high-temperature Advanced Material Bipropellant Rocket (AMBR) engine providing higher performance; 2) NASA s Evolutionary Xenon Thruster (NEXT) ion propulsion system, a 0.6-7 kW throttle-able gridded ion system; and 3) Aerocapture technology development with investments in a family of thermal protection system (TPS) materials and structures; guidance, navigation, and control (GN&C) models of blunt-body rigid aeroshells; and aerothermal effect models. Two component technologies being developed with flight infusion in mind are the Advanced Xenon Flow Control System, and ultra-lightweight propellant tank technologies. Future direction for ISPT are technologies that relate to sample return missions and other spacecraft bus technology needs like: 1) Mars Ascent Vehicles (MAV); 2) multi-mission technologies for Earth Entry Vehicles (MMEEV) for sample return missions; and 3) electric propulsion for sample return and low cost missions. These technologies are more vehicle and mission-focused, and present a different set of technology development and infusion steps beyond those previously implemented. The Systems/Mission Analysis area is focused on developing tools and assessing the application of propulsion and spacecraft bus technologies to a wide variety of mission concepts. These in-space propulsion technologies are applicable, and potentially enabling for future NASA Discovery, New Frontiers, and sample return missions currently under consideration, as well as having broad applicability to potential Flagship missions. This paper provides a brief overview of the ISPT program, describing the development status and technology infusion readiness of in-space propulsion technologies in the areas of electric propulsion, Aerocapture, Earth entry vehicles, propulsion components, Mars ascent vehicle, and mission/systems analysis.

Spacecraft Bus and Platform Technology Development under the NASA ISPT Program

NASA Technical Reports Server (NTRS)

Anderson, David J.; Munk, Michelle M.; Pencil, Eric J.; Dankanich, John W.; Glaab, Louis J.; Peterson, Todd T.

2013-01-01

The In-Space Propulsion Technology (ISPT) program is developing spacecraft bus and platform technologies that will enable or enhance NASA robotic science missions. The ISPT program is currently developing technology in four areas that include Propulsion System Technologies (electric and chemical), Entry Vehicle Technologies (aerocapture and Earth entry vehicles), Spacecraft Bus and Sample Return Propulsion Technologies (components and ascent vehicles), and Systems/Mission Analysis. Three technologies are ready for near-term flight infusion: 1) the high-temperature Advanced Material Bipropellant Rocket (AMBR) engine providing higher performance 2) NASAs Evolutionary Xenon Thruster (NEXT) ion propulsion system, a 0.6-7 kW throttle-able gridded ion system and 3) Aerocapture technology development with investments in a family of thermal protection system (TPS) materials and structures guidance, navigation, and control (GN&C) models of blunt-body rigid aeroshells and aerothermal effect models. Two component technologies being developed with flight infusion in mind are the Advanced Xenon Flow Control System, and ultra-lightweight propellant tank technologies. Future direction for ISPT are technologies that relate to sample return missions and other spacecraft bus technology needs like: 1) Mars Ascent Vehicles (MAV) 2) multi-mission technologies for Earth Entry Vehicles (MMEEV) for sample return missions and 3) electric propulsion for sample return and low cost missions. These technologies are more vehicle and mission-focused, and present a different set of technology development and infusion steps beyond those previously implemented. The Systems/Mission Analysis area is focused on developing tools and assessing the application of propulsion and spacecraft bus technologies to a wide variety of mission concepts. These in-space propulsion technologies are applicable, and potentially enabling for future NASA Discovery, New Frontiers, and sample return missions currently under consideration, as well as having broad applicability to potential Flagship missions. This paper provides a brief overview of the ISPT program, describing the development status and technology infusion readiness of in-space propulsion technologies in the areas of electric propulsion, Aerocapture, Earth entry vehicles, propulsion components, Mars ascent vehicle, and mission/systems analysis.

An Analysis of Soviet Military Writing on United States Reentry Vehicle Technology, 1965-1983

DTIC Science & Technology

1986-05-01

accomplish its maneuvering "with the help of Jet fins [struynyy rul’].൞ In fact, the B(MV, as tested in 1967, contained a propulsion system for...ICBMs.6" An active coating was, however, flight tested on a U.S. RV in * late 1974-approximately six months after this author’s book was signed to...U.S. MIRV deployments had begun the previous year (1970); maneuvering re-entry vehicles--while undergoing flight testing during this period--were still

The Status of Spacecraft Bus and Platform Technology Development Under the NASA ISPT Program

NASA Technical Reports Server (NTRS)

Anderson, David; Munk, Michelle M.; Pencil, Eric; Dankanich, John; Glaab, Louis; Peterson, Todd

2014-01-01

The In-Space Propulsion Technology (ISPT) program is developing spacecraft bus and platform technologies that will enable or enhance NASA robotic science missions. The ISPT program is currently developing technology in three areas that include Propulsion System Technologies, Entry Vehicle Technologies, and Systems Mission Analysis. ISPTs propulsion technologies include: 1) NASAs Evolutionary Xenon Thruster (NEXT) ion propulsion system, a 0.6-7 kW throttle-able gridded ion system; 2) a Hall-effect electric propulsion (HEP) system for sample return and low cost missions; 3) the Advanced Xenon Flow Control System (AXFS); ultra-lightweight propellant tank technologies (ULTT); and propulsion technologies for a Mars Ascent Vehicle (MAV). The AXFS and ULTT are two component technologies being developed with nearer-term flight infusion in mind, whereas NEXT and the HEP are being developed as EP systems. ISPTs entry vehicle technologies are: 1) Aerocapture technology development with investments in a family of thermal protection system (TPS) materials and structures; guidance, navigation, and control (GNC) models of blunt-body rigid aeroshells; and aerothermal effect models; and 2) Multi-mission technologies for Earth Entry Vehicles (MMEEV) for sample return missions. The Systems Mission Analysis area is focused on developing tools and assessing the application of propulsion, entry vehicle, and spacecraft bus technologies to a wide variety of mission concepts. Several of the ISPT technologies are related to sample return missions and other spacecraft bus technology needs like: MAV propulsion, MMEEV, and electric propulsion. These technologies, as well as Aerocapture, are more vehicle and mission-focused, and present a different set of technology development challenges. These in-space propulsion technologies are applicable, and potentially enabling for future NASA Discovery, New Frontiers, Flagship and sample return missions currently under consideration. This paper provides a brief overview of the ISPT program, describing the development status and technology infusion readiness.

Psychophysiological assessment and correction of spatial disorientation during simulated Orion spacecraft re-entry.

PubMed

Cowings, Patricia S; Toscano, William B; Reschke, Millard F; Tsehay, Addis

2018-03-02

The National Aeronautics and Space Administration (NASA) has identified a potential risk of spatial disorientation, motion sickness, and degraded performance to astronauts during re-entry and landing of the proposed Orion crew vehicle. The purpose of this study was to determine if a physiological training procedure, Autogenic-Feedback Training Exercise (AFTE), can mitigate these adverse effects. Fourteen men and six women were assigned to two groups (AFTE, no-treatment Control) matched for motion sickness susceptibility and gender. All subjects received a standard rotating chair test to determine motion sickness susceptibility; three training sessions on a manual performance task; and four exposures in the rotating chair (Orion tests) simulating angular accelerations of the crew vehicle during re-entry. AFTE subjects received 2 h of training before Orion tests 2, 3, and 4. Motion sickness symptoms, task performance, and physiological measures were recorded on all subjects. Results showed that the AFTE group had significantly lower symptom scores when compared to Controls on test 2 (p = .05), test 3 (p = .03), and test 4 (p = .02). Although there were no significant group differences on task performance, trends showed that AFTE subjects were less impaired than Controls. Heart rate change scores (20 rpm minus baseline) of AFTE subjects indicated significantly less reactivity on Test 4 compared to Test 1 (10.09 versus 16.59, p = .02), while Controls did not change significantly across tests. Results of this study indicate that AFTE may be an effective countermeasure for mitigating spatial disorientation and motion sickness in astronauts. Copyright © 2018. Published by Elsevier B.V.

FINAL SAFETY ANALYSIS REPORT--SNAP 1A RADIOISOTOPE FUELED THERMOELECTRIC GENERATOR

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

Dix, G.P.

1960-06-30

The safety aspects involved in utilizing the Task 2 radioisotope-powered thermoelectric generator in a terrestrial satellite are described. It is based upon a generalized satellite mission having a 600-day orbital lifetime. A description of the basic design of the generator is presented in order to establish the analytical model. This includes the generator design, radiocerium fuel properties, and the fuel core. The transport of the generator to the launch site is examined, including the shipping cask, shipping procedures, and shipping hazards. A description of ground handling and vehicle integration is presented including preparation for fuel transfer, transfer, mating of generatorsmore » to final stage, mating final stage to booster, and auxiliary support equipment. The flight vehicle is presented to complete the analytical model. Contained in this chapter are descriptions of the booster-sustainer, final stage, propellants, and built-in safety systems. The typical missile range is examined with respect to the launch complex and range safety characteristics. The shielding of the fuel is discussed and includes both dose rates and shield thicknesses required. The bare core, shielded generator, fuel transfer operation and dose rates for accidental conditions are treated. mechanism of re-entry from the successful mission is covered. Radiocerium inventories with respect to time and the chronology of re-entry are specifically treated. The multiplicity of conditions for aborted missions is set forth. The definition of aborted missions is treated first in order to present the initial conditions. Following this, a definition of the forces imposed upon the generator is presented. The aborted missions is presented. A large number of initial vehicle failure cases is narrowed down into categories of consequences. Since stratospheric injection of fuel results in cases where the fuel is not contained after re-entry, an extensive discussion of the fall-out mechanism is presented. (auth)« less

40 CFR 86.096-7 - Maintenance of records; submittal of information; right of entry.

Code of Federal Regulations, 2013 CFR

2013-07-01

... records for each such vehicle: (i) EPA engine family; (ii) Vehicle identification number; (iii) Model year... AGENCY (CONTINUED) AIR PROGRAMS (CONTINUED) CONTROL OF EMISSIONS FROM NEW AND IN-USE HIGHWAY VEHICLES AND ENGINES General Provisions for Emission Regulations for 1977 and Later Model Year New Light-Duty Vehicles...

40 CFR 86.096-7 - Maintenance of records; submittal of information; right of entry.

Code of Federal Regulations, 2011 CFR

2011-07-01

... records for each such vehicle: (i) EPA engine family; (ii) Vehicle identification number; (iii) Model year... AGENCY (CONTINUED) AIR PROGRAMS (CONTINUED) CONTROL OF EMISSIONS FROM NEW AND IN-USE HIGHWAY VEHICLES AND ENGINES General Provisions for Emission Regulations for 1977 and Later Model Year New Light-Duty Vehicles...

40 CFR 86.096-7 - Maintenance of records; submittal of information; right of entry.

Code of Federal Regulations, 2012 CFR

2012-07-01

... records for each such vehicle: (i) EPA engine family; (ii) Vehicle identification number; (iii) Model year... AGENCY (CONTINUED) AIR PROGRAMS (CONTINUED) CONTROL OF EMISSIONS FROM NEW AND IN-USE HIGHWAY VEHICLES AND ENGINES General Provisions for Emission Regulations for 1977 and Later Model Year New Light-Duty Vehicles...

Further Investigations of Control Surface Seals for the X-38 Re-Entry Vehicle

NASA Technical Reports Server (NTRS)

Dunlap, Patrick H., Jr.; Steinetz, Bruce M.; Curry, Donald M.; Newquist, Charles W.; Verzemnieks, Juris

2001-01-01

NASA is currently developing the X-38 vehicle that will be used to demonstrate the technologies required for a potential crew return vehicle (CRV) for the International Space Station. This vehicle would serve both as an ambulance for medical emergencies and as an evacuation vehicle for the Space Station. Control surfaces on the X-38 (body flaps and rudder/fin assemblies) require high temperature seals to limit hot gas ingestion and transfer of heat to underlying low-temperature structures to prevent over-temperature of these structures and possible loss of the vehicle. NASAs Johnson Space Center (JSC) and Glenn Research Center (GRC) are working together to develop and evaluate seals for these control surfaces. This paper presents results for compression. flow, scrub, and arc jet tests conducted on the baseline X-38 rudder/fin seal design. Room temperature seal compression tests were performed at low compression levels to determine load versus linear compression, preload. contact area, stiffness. and resiliency characteristics under low load conditions. For all compression levels that were tested, unit loads and contact pressures for the seals were below the 5 lb/in. and 10 psi limits required to limit the loads on the adjoining Shuttle thermal tiles that the seals will contact. Flow rates through an unloaded (i.e. 0% compression) double arrangement were twice those of a double seal compressed to the 20% design compression level. The seals survived an ambient temperature 1000 cycle scrub test over relatively rough Shuttle tile surfaces. The seals were able to disengage and re-engage the edges of the rub surface tiles while being scrubbed over them. Arc jet tests were performed to experimentally determine anticipated seal temperatures for representative flow boundary conditions (pressures and temperatures) under simulated vehicle re-entry conditions. Installation of a single seat in the gap of the test fixture caused a large temperature drop (1710 F) across the seal location as compared to an open gap condition (140 F) confirming the need for seals in the rudder/fin gap location. The seal acted as an effective thermal barrier limiting heat convection through the seal gap and minimizing temperature increases downstream of the seal during maximum heating conditions.

7 CFR 1530.105 - Terms and conditions.

Code of Federal Regulations, 2011 CFR

2011-01-01

... OF AGRICULTURE THE REFINED SUGAR RE-EXPORT PROGRAM, THE SUGAR CONTAINING PRODUCTS RE-EXPORT PROGRAM...) shall, not later than 90 days after entering a quantity of raw cane sugar under subheading 1701.11.20 of the HTS, export or transfer an equivalent quantity of refined sugar if the entry results in a positive...

KSC-07pd3481

NASA Image and Video Library

2007-11-27

KENNEDY SPACE CENTER, FLA. -- In Hangar N at NASA's Kennedy Space Center, a heat shield for the Constellation crew exploration vehicle, or CEV, is being prepared for a demonstration. A developmental heat shield for the Orion spacecraft is being tested and evaluated at Kennedy. The shield was designed and assembled by the Boeing Company in Huntington Beach, Calif., for NASA's Constellation Program. The thermal protection system manufacturing demonstration unit is designed to protect astronauts from extreme heat during re-entry to Earth's atmosphere from low Earth orbit and lunar missions. The CEV will be used to dock and gain access to the International Space Station, travel to the moon in the 2018 timeframe and play a crucial role in exploring Mars. Photo credit: NASA/Kim Shiflett

KSC-07pd3479

NASA Image and Video Library

2007-11-27

KENNEDY SPACE CENTER, FLA. -- In Hangar N at NASA's Kennedy Space Center, a heat shield for the Constellation crew exploration vehicle, or CEV, is being prepared for a demonstration. A developmental heat shield for the Orion spacecraft is being tested and evaluated at Kennedy. The shield was designed and assembled by the Boeing Company in Huntington Beach, Calif., for NASA's Constellation Program. The thermal protection system manufacturing demonstration unit is designed to protect astronauts from extreme heat during re-entry to Earth's atmosphere from low Earth orbit and lunar missions. The CEV will be used to dock and gain access to the International Space Station, travel to the moon in the 2018 timeframe and play a crucial role in exploring Mars. Photo credit: NASA/Kim Shiflett

KSC-07pd3482

NASA Image and Video Library

2007-11-27

KENNEDY SPACE CENTER, FLA. -- In Hangar N at NASA's Kennedy Space Center, a heat shield for the Constellation crew exploration vehicle, or CEV, is being prepared for a demonstration. A developmental heat shield for the Orion spacecraft is being tested and evaluated at Kennedy. The shield was designed and assembled by the Boeing Company in Huntington Beach, Calif., for NASA's Constellation Program. The thermal protection system manufacturing demonstration unit is designed to protect astronauts from extreme heat during re-entry to Earth's atmosphere from low Earth orbit and lunar missions. The CEV will be used to dock and gain access to the International Space Station, travel to the moon in the 2018 timeframe and play a crucial role in exploring Mars. Photo credit: NASA/Kim Shiflett

KSC-07pd3478

NASA Image and Video Library

2007-11-27

KENNEDY SPACE CENTER, FLA. -- In Hangar N at NASA's Kennedy Space Center, a heat shield for the Constellation crew exploration vehicle, or CEV, is being prepared for a demonstration. A developmental heat shield for the Orion spacecraft is being tested and evaluated at Kennedy. The shield was designed and assembled by the Boeing Company in Huntington Beach, Calif., for NASA's Constellation Program. The thermal protection system manufacturing demonstration unit is designed to protect astronauts from extreme heat during re-entry to Earth's atmosphere from low Earth orbit and lunar missions. The CEV will be used to dock and gain access to the International Space Station, travel to the moon in the 2018 timeframe and play a crucial role in exploring Mars. Photo credit: NASA/Kim Shiflett

KSC-07pd3477

NASA Image and Video Library

2007-11-27

KENNEDY SPACE CENTER, FLA. -- In Hangar N at NASA's Kennedy Space Center, a heat shield for the Constellation crew exploration vehicle, or CEV, is being prepared for a demonstration. A developmental heat shield for the Orion spacecraft is being tested and evaluated at Kennedy. The shield was designed and assembled by the Boeing Company in Huntington Beach, Calif., for NASA's Constellation Program. The thermal protection system manufacturing demonstration unit is designed to protect astronauts from extreme heat during re-entry to Earth's atmosphere from low Earth orbit and lunar missions. The CEV will be used to dock and gain access to the International Space Station, travel to the moon in the 2018 timeframe and play a crucial role in exploring Mars. Photo credit: NASA/Kim Shiflett

KSC-07pd3480

NASA Image and Video Library

2007-11-27

KENNEDY SPACE CENTER, FLA. -- In Hangar N at NASA's Kennedy Space Center, a heat shield for the Constellation crew exploration vehicle, or CEV, is being prepared for a demonstration. A developmental heat shield for the Orion spacecraft is being tested and evaluated at Kennedy. The shield was designed and assembled by the Boeing Company in Huntington Beach, Calif., for NASA's Constellation Program. The thermal protection system manufacturing demonstration unit is designed to protect astronauts from extreme heat during re-entry to Earth's atmosphere from low Earth orbit and lunar missions. The CEV will be used to dock and gain access to the International Space Station, travel to the moon in the 2018 timeframe and play a crucial role in exploring Mars. Photo credit: NASA/Kim Shiflett

Early Rockets

NASA Image and Video Library

1958-01-31

Jupiter-C Missile No. 27 assembly at the Army Ballistic Missile Agency (ABMA), Redstone Arsenal, in Huntsville, Aalabama. The Jupiter-C was a modification of the Redstone Missile, and originally developed as a nose cone re-entry test vehicle for the Jupiter Intermediate Range Ballistic Missile (IRBM). Jupiter-C successfully launched the first American Satellite, Explorer 1, in orbit on January 31, 1958.

Retiring Old Cars : Programs To Save Gasoline and Reduce Emissions

DOT National Transportation Integrated Search

1992-07-01

Older vehicles produce a disproportionate share of total U.S. vehicle air emissions. Congress asked Office of Technology Assessment to examine the ability of vehicle scrappage programs to reduce gasoline use and emissions. This report presents the re...

Propulsion Technology Development for Sample Return Missions Under NASA's ISPT Program

NASA Technical Reports Server (NTRS)

Anderson, David J.; Pencil, Eric J.; Vento, Daniel; Dankanich, John W.; Munk, Michelle M.; Hahne, David

2011-01-01

The In-Space Propulsion Technology (ISPT) Program was tasked in 2009 to start development of propulsion technologies that would enable future sample return missions. Sample return missions could be quite varied, from collecting and bringing back samples of comets or asteroids, to soil, rocks, or atmosphere from planets or moons. The paper will describe the ISPT Program s propulsion technology development activities relevant to future sample return missions. The sample return propulsion technology development areas for ISPT are: 1) Sample Return Propulsion (SRP), 2) Planetary Ascent Vehicles (PAV), 3) Entry Vehicle Technologies (EVT), and 4) Systems/mission analysis and tools that focuses on sample return propulsion. The Sample Return Propulsion area is subdivided into: a) Electric propulsion for sample return and low cost Discovery-class missions, b) Propulsion systems for Earth Return Vehicles (ERV) including transfer stages to the destination, and c) Low TRL advanced propulsion technologies. The SRP effort will continue work on HIVHAC thruster development in FY2011 and then transitions into developing a HIVHAC system under future Electric Propulsion for sample return (ERV and transfer stages) and low-cost missions. Previous work on the lightweight propellant-tanks will continue under advanced propulsion technologies for sample return with direct applicability to a Mars Sample Return (MSR) mission and with general applicability to all future planetary spacecraft. A major effort under the EVT area is multi-mission technologies for Earth Entry Vehicles (MMEEV), which will leverage and build upon previous work related to Earth Entry Vehicles (EEV). The major effort under the PAV area is the Mars Ascent Vehicle (MAV). The MAV is a new development area to ISPT, and builds upon and leverages the past MAV analysis and technology developments from the Mars Technology Program (MTP) and previous MSR studies.

A Study on Re-entry Predictions of Uncontrolled Space Objects for Space Situational Awareness

NASA Astrophysics Data System (ADS)

Choi, Eun-Jung; Cho, Sungki; Lee, Deok-Jin; Kim, Siwoo; Jo, Jung Hyun

2017-12-01

The key risk analysis technologies for the re-entry of space objects into Earth’s atmosphere are divided into four categories: cataloguing and databases of the re-entry of space objects, lifetime and re-entry trajectory predictions, break-up models after re-entry and multiple debris distribution predictions, and ground impact probability models. In this study, we focused on re- entry prediction, including orbital lifetime assessments, for space situational awareness systems. Re-entry predictions are very difficult and are affected by various sources of uncertainty. In particular, during uncontrolled re-entry, large spacecraft may break into several pieces of debris, and the surviving fragments can be a significant hazard for persons and properties on the ground. In recent years, specific methods and procedures have been developed to provide clear information for predicting and analyzing the re-entry of space objects and for ground-risk assessments. Representative tools include object reentry survival analysis tool (ORSAT) and debris assessment software (DAS) developed by National Aeronautics and Space Administration (NASA), spacecraft atmospheric re-entry and aerothermal break-up (SCARAB) and debris risk assessment and mitigation analysis (DRAMA) developed by European Space Agency (ESA), and semi-analytic tool for end of life analysis (STELA) developed by Centre National d’Etudes Spatiales (CNES). In this study, various surveys of existing re-entry space objects are reviewed, and an efficient re-entry prediction technique is suggested based on STELA, the life-cycle analysis tool for satellites, and DRAMA, a re-entry analysis tool. To verify the proposed method, the re-entry of the Tiangong-1 Space Lab, which is expected to re-enter Earth’s atmosphere shortly, was simulated. Eventually, these results will provide a basis for space situational awareness risk analyses of the re-entry of space objects.

The Mission Accessibility of Near-Earth Asteroids

NASA Technical Reports Server (NTRS)

Barbee, Brent W.; Abell, Paul A.; Adamo, Daniel R.; Mazanek, Daniel D.; Johnson, Lindley N.; Yeomans, Donald K.; Chodas, Paul W.; Chamberlin, Alan B.; Benner, Lance A. M.; Taylor, Patrick;

Aerothermodynamics of expert ballistic vehicle at hypersonic speeds

NASA Astrophysics Data System (ADS)

Kharitonov, A. M.; Adamov, N. P.; Chirkashenko, V. F.; Mazhul, I. I.; Shpak, S. I.; Shiplyuk, A. N.; Vasenyov, L. G.; Zvegintsev, V. I.; Muylaert, J. M.

2012-01-01

The European EXPErimental Re-entry Test bed (EXPERT) vehicle is intended for studying various basic phenomena, such as the boundary-layer transition on blunted bodies, real gas effects during shock wave/boundary layer interaction, and effect of surface catalycity. Another task is to develop methods for recalculating the results of windtunnel experiments to flight conditions. The EXPERT program implies large-scale preflight research, in particular, various calculations with the use of advanced numerical methods, experimental studies of the models in various wind tunnels, and comparative analysis of data obtained for possible extrapolation of data to in-flight conditions. The experimental studies are performed in various aerodynamic centers of Europe and Russia under contracts with ESA-ESTEC. In particular, extensive experiments are performed at the Von Karman Institute for Fluid Dynamics (VKI, Belgium) and also at the DLR aerospace center in Germany. At ITAM SB RAS, the experimental studies of the EXPERT model characteristic were performed under ISTC Projects 2109, 3151, and 3550, in the T-313 supersonic wind tunnel and AT-303 hypersonic wind tunnel.

KSC-2014-2496

NASA Image and Video Library

2014-05-10

CAPE CANAVERAL, Fla. – The San Diego Padres' mascot checks out NASA's Orion boilerplate test vehicle inside Petco Park in San Diego, California. The boilerplate test vehicle is being prepared for an Exploration Flight Test-1, or EFT-1, pre-transportation test. The Ground Systems Development and Operations Program will run the test at the U.S. Naval Base San Diego to simulate retrieval and transportation procedures for Orion after it splashes down in the ocean and is retrieved for return to land and ground transportation back to Kennedy Space Center in Florida. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of the Orion is scheduled to launch later this year atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Kim Shiflett

A Software Upgrade of the NASA Aeroheating Code "MINIVER"

NASA Technical Reports Server (NTRS)

Louderback, Pierce Mathew

2013-01-01

Computational Fluid Dynamics (CFD) is a powerful and versatile tool simulating fluid and thermal environments of launch and re-entry vehicles alike. Where it excels in power and accuracy, however, it lacks in speed. An alternative tool for this purpose is known as MINIVER, an aeroheating code widely used by NASA and within the aerospace industry. Capable of providing swift, reasonably accurate approximations of the fluid and thermal environment of launch vehicles, MINIVER is used where time is of the essence and accuracy need not be exact. However, MINIVER is an old, aging tool: running on a user-unfriendly, legacy command-line interface, it is difficult for it to keep pace with more modem software tools. Florida Institute of Technology was tasked with the construction of a new Graphical User Interface (GUI) that implemented the legacy version's capabilities and enhanced them with new tools and utilities. This thesis provides background to the legacy version of the program, the progression and final version of a modem user interface, and benchmarks to demonstrate its usefulness.

Magnetohydrodynamic Power Generation in the Laboratory Simulated Martian Entry Plasma

NASA Technical Reports Server (NTRS)

Vuskovic, L.; Popovic, S.; Drake, J.; Moses, R. W.

2005-01-01

This paper addresses the magnetohydrodynamic (MHD) conversion of the energy released during the planetary entry phase of an interplanetary vehicle trajectory. The effect of MHD conversion is multi-fold. It reduces and redirects heat transferred to the vehicle, and regenerates the dissipated energy in reusable and transportable form. A vehicle on an interplanetary mission carries about 10,000 kWh of kinetic energy per ton of its mass. This energy is dissipated into heat during the planetary atmospheric entry phase. For instance, the kinetic energy of Mars Pathfinder was about 4220 kWh. Based on the loss in velocity, Mars Pathfinder lost about 92.5% of that energy during the plasma-sustaining entry phase that is approximately 3900 kWh. An ideal MHD generator, distributed over the probe surface of Mars Pathfinder could convert more than 2000 kWh of this energy loss into electrical energy, which correspond to more than 50% of the kinetic energy loss. That means that the heat transferred to the probe surface can be reduced by at least 50% if the converted energy is adequately stored, or re-radiated, or directly used. Therefore, MHD conversion could act not only as the power generating, but also as the cooling process. In this paper we describe results of preliminary experiments with light and microwave emitters powered by model magnetohydrodynamic generators and discuss method for direct use of converted energy.

42 CFR 488.61 - Special procedures for approval and re-approval of organ transplant centers.

Code of Federal Regulations, 2012 CFR

2012-10-01

... Approval. Centers that have lost their Medicare approval may seek re-entry into the Medicare program at any... 42 Public Health 5 2012-10-01 2012-10-01 false Special procedures for approval and re-approval of... ENFORCEMENT PROCEDURES Special Requirements § 488.61 Special procedures for approval and re-approval of organ...

42 CFR 488.61 - Special procedures for approval and re-approval of organ transplant centers.

Code of Federal Regulations, 2011 CFR

2011-10-01

... Approval. Centers that have lost their Medicare approval may seek re-entry into the Medicare program at any... 42 Public Health 5 2011-10-01 2011-10-01 false Special procedures for approval and re-approval of... ENFORCEMENT PROCEDURES Special Requirements § 488.61 Special procedures for approval and re-approval of organ...

42 CFR 488.61 - Special procedures for approval and re-approval of organ transplant centers.

Code of Federal Regulations, 2013 CFR

2013-10-01

... Approval. Centers that have lost their Medicare approval may seek re-entry into the Medicare program at any... 42 Public Health 5 2013-10-01 2013-10-01 false Special procedures for approval and re-approval of... ENFORCEMENT PROCEDURES Special Requirements § 488.61 Special procedures for approval and re-approval of organ...

42 CFR 488.61 - Special procedures for approval and re-approval of organ transplant centers.

Code of Federal Regulations, 2010 CFR

2010-10-01

... Approval. Centers that have lost their Medicare approval may seek re-entry into the Medicare program at any... 42 Public Health 5 2010-10-01 2010-10-01 false Special procedures for approval and re-approval of... ENFORCEMENT PROCEDURES Special Requirements § 488.61 Special procedures for approval and re-approval of organ...

Resin-Impregnated Carbon Ablator: A New Ablative Material for Hyperbolic Entry Speeds

NASA Technical Reports Server (NTRS)

Esper, Jaime; Lengowski, Michael

2012-01-01

Ablative materials are required to protect a space vehicle from the extreme temperatures encountered during the most demanding (hyperbolic) atmospheric entry velocities, either for probes launched toward other celestial bodies, or coming back to Earth from deep space missions. To that effect, the resin-impregnated carbon ablator (RICA) is a high-temperature carbon/phenolic ablative thermal protection system (TPS) material designed to use modern and commercially viable components in its manufacture. Heritage carbon/phenolic ablators intended for this use rely on materials that are no longer in production (i.e., Galileo, Pioneer Venus); hence the development of alternatives such as RICA is necessary for future NASA planetary entry and Earth re-entry missions. RICA s capabilities were initially measured in air for Earth re-entry applications, where it was exposed to a heat flux of 14 MW/sq m for 22 seconds. Methane tests were also carried out for potential application in Saturn s moon Titan, with a nominal heat flux of 1.4 MW/sq m for up to 478 seconds. Three slightly different material formulations were manufactured and subsequently tested at the Plasma Wind Tunnel of the University of Stuttgart in Germany (PWK1) in the summer and fall of 2010. The TPS integrity was well preserved in most cases, and results show great promise.

Analysis Of The ATV1 Re-Entry Using Near-UV Spectroscopic Data From The ESA/NASA Multi-Instrument Aircraft Observation Campaign

NASA Astrophysics Data System (ADS)

Lohle, Stefan; Marynowski, Thomas; Knapp, Andreas; Wernitz, Ricarda; Lips, Tobias

2011-05-01

The first Automated Transfer Vehicle (ATV1) named Jules Verne was launched in March 2009 to carry over seven tons of experiments, fuel, water, food and other supplies to the International Space Station (ISS) orbiting at about 350 km. Attached to the ISS, it served as an extension to the space station, giving extra space for the six astronauts and cosmonauts who will ultimately form the permanent ISS Crew. On September 29, 2009, a controlled de-orbit maneuver lead the spacecraft to enter the Earth's atmosphere over the south pacific ocean. The following destructive re-entry was observed by two aircraft equipped with a wide variety of imaging and spectroscopic instruments. In this paper, we present quantitative results from the near-UV spectroscopic measurements acquired aboard an experimental DC-8 aircraft operated by NASA. The wavelength range of observation allows a determination of temperatures from radiation and the investigation of atomic radiation with respect to the identification of the destructive process. Furthermore, the excitation temperatures of chromium give an insight into the explosive events occurring during re-entry. Analysing the continuum of the measured spectra, the Planck radiation temperature is fitted to the data. These temperatures indicate that most of the radiating parts are titanium alloys, i.e. the outer structure of ATV1. All results within this paper are compared to a simulated break-up scenario and related to basic results from other experimenters which allows drawing an overall scenario for this destructive re-entry.

Spacecraft Re-Entry Impact Point Targeting Using Aerodynamic Drag

NASA Technical Reports Server (NTRS)

Omar, Sanny R.; Bevilacqua, Riccardo

2017-01-01

The ability to re-enter the atmosphere at a desired location is important for spacecraft containing components that may survive re-entry. While impact point targeting has traditionally been initiated through impulsive burns with chemical thrusters on large vehicles such as the Space Shuttle, and the Soyuz and Apollo capsules, many small spacecraft do not host thrusters and require an alternative means of impact point targeting to ensure that falling debris do not cause harm to persons or property. This paper discusses the use of solely aerodynamic drag force to perform this targeting. It is shown that by deploying and retracting a drag device to vary the ballistic coefficient of the spacecraft, any desired longitude and latitude on the ground can be targeted provided that the maneuvering begins early enough and the latitude is less than the inclination of the orbit. An analytical solution based on perturbations from a numerically propagated trajectory is developed to map the initial state and ballistic coefficient profile of a spacecraft to its impact point. This allows the ballistic coefficient profile necessary to reach a given target point to be rapidly calculated, making it feasible to generate the guidance for the decay trajectory onboard the spacecraft. The ability to target an impact point using aerodynamic drag will enhance the capabilities of small spacecraft and will enable larger space vehicles containing thrusters to save fuel by more effectively leveraging the available aerodynamic drag.

A Fast Proceduere for Optimizing Thermal Protection Systems of Re-Entry Vehicles

NASA Astrophysics Data System (ADS)

Ferraiuolo, M.; Riccio, A.; Tescione, D.; Gigliotti, M.

The aim of the present work is to introduce a fast procedure to optimize thermal protection systems for re-entry vehicles subjected to high thermal loads. A simplified one-dimensional optimization process, performed in order to find the optimum design variables (lengths, sections etc.), is the first step of the proposed design procedure. Simultaneously, the most suitable materials able to sustain high temperatures and meeting the weight requirements are selected and positioned within the design layout. In this stage of the design procedure, simplified (generalized plane strain) FEM models are used when boundary and geometrical conditions allow the reduction of the degrees of freedom. Those simplified local FEM models can be useful because they are time-saving and very simple to build; they are essentially one dimensional and can be used for optimization processes in order to determine the optimum configuration with regard to weight, temperature and stresses. A triple-layer and a double-layer body, subjected to the same aero-thermal loads, have been optimized to minimize the overall weight. Full two and three-dimensional analyses are performed in order to validate those simplified models. Thermal-structural analyses and optimizations are executed by adopting the Ansys FEM code.

The application of quaternions and other spatial representations to the reconstruction of re-entry vehicle motion.

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

De Sapio, Vincent

2010-09-01

The analysis of spacecraft kinematics and dynamics requires an efficient scheme for spatial representation. While the representation of displacement in three dimensional Euclidean space is straightforward, orientation in three dimensions poses particular challenges. The unit quaternion provides an approach that mitigates many of the problems intrinsic in other representation approaches, including the ill-conditioning that arises from computing many successive rotations. This report focuses on the computational utility of unit quaternions and their application to the reconstruction of re-entry vehicle (RV) motion history from sensor data. To this end they will be used in conjunction with other kinematic and data processingmore » techniques. We will present a numerical implementation for the reconstruction of RV motion solely from gyroscope and accelerometer data. This will make use of unit quaternions due to their numerical efficacy in dealing with the composition of many incremental rotations over a time series. In addition to signal processing and data conditioning procedures, algorithms for numerical quaternion-based integration of gyroscope data will be addressed, as well as accelerometer triangulation and integration to yield RV trajectory. Actual processed flight data will be presented to demonstrate the implementation of these methods.« less

40 CFR 86.000-7 - Maintenance of records; submittal of information; right of entry.

Code of Federal Regulations, 2013 CFR

2013-07-01

...: (i) EPA engine family; (ii) Vehicle identification number; (iii) Model year and production date; (iv... AGENCY (CONTINUED) AIR PROGRAMS (CONTINUED) CONTROL OF EMISSIONS FROM NEW AND IN-USE HIGHWAY VEHICLES AND ENGINES General Provisions for Emission Regulations for 1977 and Later Model Year New Light-Duty Vehicles...

40 CFR 86.000-7 - Maintenance of records; submittal of information; right of entry.

Code of Federal Regulations, 2010 CFR

2010-07-01

...: (i) EPA engine family; (ii) Vehicle identification number; (iii) Model year and production date; (iv... AGENCY (CONTINUED) AIR PROGRAMS (CONTINUED) CONTROL OF EMISSIONS FROM NEW AND IN-USE HIGHWAY VEHICLES AND ENGINES General Provisions for Emission Regulations for 1977 and Later Model Year New Light-Duty Vehicles...

40 CFR 86.000-7 - Maintenance of records; submittal of information; right of entry.

Code of Federal Regulations, 2011 CFR

2011-07-01

...: (i) EPA engine family; (ii) Vehicle identification number; (iii) Model year and production date; (iv... AGENCY (CONTINUED) AIR PROGRAMS (CONTINUED) CONTROL OF EMISSIONS FROM NEW AND IN-USE HIGHWAY VEHICLES AND ENGINES General Provisions for Emission Regulations for 1977 and Later Model Year New Light-Duty Vehicles...

40 CFR 86.000-7 - Maintenance of records; submittal of information; right of entry.

Code of Federal Regulations, 2012 CFR

2012-07-01

...: (i) EPA engine family; (ii) Vehicle identification number; (iii) Model year and production date; (iv... AGENCY (CONTINUED) AIR PROGRAMS (CONTINUED) CONTROL OF EMISSIONS FROM NEW AND IN-USE HIGHWAY VEHICLES AND ENGINES General Provisions for Emission Regulations for 1977 and Later Model Year New Light-Duty Vehicles...

STS-114: Discovery Day 13 Mission Status Briefing

NASA Technical Reports Server (NTRS)

2005-01-01

LeRoy Cain, STS-114 Ascent/Entry Flight Director, takes a solo stand with the Press in this briefing. He reports that the vehicle is in good shape, consumable status is excellent, and the shuttle crew is in high spirits and preparing for de-orbit and landing. LeRoy and his team have completed the entry system check up, flight control check up, reactor control system check up, and noted that all are at nominal performance; weather forecast is very good, the Entry team is ready and looking forward to de-orbit and landing at the Kennedy Space Center on Monday, August 8th. Re-entry, personal feelings, Columbia accident, data gathering, consumable situation, back up sites, weather, communication block out, night and day landing, and Commander Collin's piloting skills during night flight are some of the topics covered with the News media.

Dissection and re-entry techniques and longer-term outcomes following successful percutaneous coronary intervention of chronic total occlusion.

PubMed

Rinfret, Stéphane; Ribeiro, Henrique Barbosa; Nguyen, Can Manh; Nombela-Franco, Luis; Ureña, Marina; Rodés-Cabau, Josep

2014-11-01

New techniques involving dissection of the subintimal space and re-entry into the true lumen increase success rates in chronic total occlusion (CTO) percutaneous coronary intervention (PCI). However, their long-term safety and efficacy were unknown. This study included a series of consecutive patients who underwent CTO PCI. All patients who did not present events were contacted 12 to 18 months after their PCI. The combined incidence of cardiac death, myocardial infarction, ischemia-driven target-vessel revascularization (TVR), or reocclusion was assessed as our primary outcome. From January 2010 to January 2013, of 212 CTOs treated in our CTO program, 192 (91%) were successfully opened (in 179 patients). Follow-up data were available for 187 CTOs (97.4%), with 82 (44%) that were opened with dissection re-entry and 105 (56%) with conventional wire escalation techniques. At a median follow-up of 398 days, the primary outcome occurred in 18 of 179 CTOs treated (10.7%), driven by TVR. No patient died from cardiac causes. Eleven CTOs (15.2%) treated with dissection re-entry versus 7 CTOs (7.3%) treated with wire escalation presented with the primary outcome (p = 0.17). With multivariate adjustment, dissection re-entry techniques had no significant impact on outcomes. However, treatment of an in-stent occlusion was independently associated with TVR (hazards ratio >6.0, p <0.001). In conclusion, dissection re-entry techniques have minimal impact on long-term outcomes after CTO PCI, which are favorable in most patients. However, treatment of an in-stent occlusion and use of sirolimus-eluting stent were predictors of subsequent adverse outcomes. Copyright © 2014 Elsevier Inc. All rights reserved.

Parametric Thermal Soak Model for Earth Entry Vehicles

NASA Technical Reports Server (NTRS)

Agrawal, Parul; Samareh, Jamshid; Doan, Quy D.

2013-01-01

The analysis and design of an Earth Entry Vehicle (EEV) is multidisciplinary in nature, requiring the application many disciplines. An integrated tool called Multi Mission System Analysis for Planetary Entry Descent and Landing or M-SAPE is being developed as part of Entry Vehicle Technology project under In-Space Technology program. Integration of a multidisciplinary problem is a challenging task. Automation of the execution process and data transfer among disciplines can be accomplished to provide significant benefits. Thermal soak analysis and temperature predictions of various interior components of entry vehicle, including the impact foam and payload container are part of the solution that M-SAPE will offer to spacecraft designers. The present paper focuses on the thermal soak analysis of an entry vehicle design based on the Mars Sample Return entry vehicle geometry and discusses a technical approach to develop parametric models for thermal soak analysis that will be integrated into M-SAPE. One of the main objectives is to be able to identify the important parameters and to develop correlation coefficients so that, for a given trajectory, can estimate the peak payload temperature based on relevant trajectory parameters and vehicle geometry. The models are being developed for two primary thermal protection (TPS) materials: 1) carbon phenolic that was used for Galileo and Pioneer Venus probes and, 2) Phenolic Impregnated Carbon Ablator (PICA), TPS material for Mars Science Lab mission. Several representative trajectories were selected from a very large trade space to include in the thermal analysis in order to develop an effective parametric thermal soak model. The selected trajectories covered a wide range of heatload and heatflux combinations. Non-linear, fully transient, thermal finite element simulations were performed for the selected trajectories to generate the temperature histories at the interior of the vehicle. Figure 1 shows the finite element model that was used for the simulations. The results indicate that it takes several hours for the thermal energy to soak into the interior of the vehicle and achieve maximum payload temperatures. In addition, a strong correlation between the heatload and peak payload container temperature is observed that will help establishing the parametric thermal soak model.

Status of Sample Return Propulsion Technology Development Under NASA's ISPT Program

NASA Technical Reports Server (NTRS)

Anderson, David J.; Glaab, Louis J.; Munk, Michelle M.; Pencil, Eric; Dankanich, John; Peterson, Todd T.

2012-01-01

The In-Space Propulsion Technology (ISPT) program was tasked in 2009 to start development of propulsion technologies that would enable future sample return missions. ISPT s sample return technology development areas are diverse. Sample Return Propulsion (SRP) addresses electric propulsion for sample return and low cost Discovery-class missions, propulsion systems for Earth Return Vehicles (ERV) including transfer stages to the destination, and low technology readiness level (TRL) advanced propulsion technologies. The SRP effort continues work on HIVHAC thruster development to transition into developing a Hall-effect propulsion system for sample return (ERV and transfer stages) and low-cost missions. Previous work on the lightweight propellant-tanks continues for sample return with direct applicability to a Mars Sample Return (MSR) mission with general applicability to all future planetary spacecraft. The Earth Entry Vehicle (EEV) work focuses on building a fundamental base of multi-mission technologies for Earth Entry Vehicles (MMEEV). The main focus of the Planetary Ascent Vehicles (PAV) area is technology development for the Mars Ascent Vehicle (MAV), which builds upon and leverages the past MAV analysis and technology developments from the Mars Technology Program (MTP) and previous MSR studies

KSC-2014-3994

NASA Image and Video Library

2014-09-17

SAN DIEGO, Calif. – The Orion boilerplate test vehicle floats in the Pacific Ocean, a distance away from the USS Anchorage, during the third day of Orion Underway Recovery Test 3. The orange stabilizers inflated on top help keep the test vehicle floating upright. U.S. Navy divers in a Zodiac boat, at left, and other team members in a rigid hull inflatable boat prepare the test vehicle for return to the ship. NASA, Lockheed Martin and U.S. Navy personnel are conducting the recovery test using the test vehicle to prepare for recovery of the Orion crew module on its return from a deep space mission. The test allows the teams to demonstrate and evaluate the recovery processes, procedures, hardware and personnel in open waters. The Ground Systems Development and Operations Program is conducting the underway recovery tests. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion is scheduled to launch in 2014 atop a United Launch Alliance Delta IV Heavy rocket and in 2018 on NASA’s Space Launch System rocket. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Kim Shiflett

Re-examining Responsibilities: Health Educators as Researchers.

ERIC Educational Resources Information Center

Drolet, Judy C.

1991-01-01

Discusses seven areas of responsibility for entry-level health educators which can be demonstrated through research: assessing individual and community needs for health education; planning effective health education programs; implementing programs; evaluating program effectiveness; coordinating service provision; acting as a resource; and…

M2-F1 in flight

NASA Technical Reports Server (NTRS)

1964-01-01

The M2-F1 Lifting Body is seen here under tow by an unseen C-47 at the NASA Flight Research Center (later redesignated the Dryden Flight Research Center), Edwards, California. The low-cost vehicle was the first piloted lifting body to be test flown. The lifting-body concept originated in the mid-1950s at the National Advisory Committee for Aeronautics' Ames Aeronautical Laboratory, Mountain View California. By February 1962, a series of possible shapes had been developed, and R. Dale Reed was working to gain support for a research vehicle. The wingless, lifting body aircraft design was initially concieved as a means of landing an aircraft horizontally after atmospheric reentry. The absence of wings would make the extreme heat of re-entry less damaging to the vehicle. In 1962, Dryden management approved a program to build a lightweight, unpowered lifting body as a prototype to flight test the wingless concept. It would look like a 'flying bathtub,' and was designated the M2-F1, the 'M' referring to 'manned' and 'F' referring to 'flight' version. It featured a plywood shell placed over a tubular steel frame crafted at Dryden. Construction was completed in 1963. The first flight tests of the M2-F1 were over Rogers Dry Lake at the end of a tow rope attached to a hopped-up Pontiac convertible driven at speeds up to about 120 mph. These initial tests produced enough flight data about the M2-F1 to proceed with flights behind a NASA C-47 tow plane at greater altitudes. The C-47 took the craft to an altitude of 12,000 where free flights back to Rogers Dry Lake began. Pilot for the first series of flights of the M2-F1 was NASA research pilot Milt Thompson. Typical glide flights with the M2-F1 lasted about two minutes and reached speeds of 110 to l20 mph. More than 400 ground tows and 77 aircraft tow flights were carried out with the M2-F1. The success of Dryden's M2-F1 program led to NASA's development and construction of two heavyweight lifting bodies based on studies at NASA's Ames and Langley research centers--the M2-F2 and the HL-10, both built by the Northrop Corporation, and the U.S. Air Force's X-24 program. The Lifting Body program also heavily influenced the Space Shuttle program. The M2-F1 program demonstrated the feasibility of the lifting-body concept for horizontal landings of atmospheric entry vehicles. It also demonstrated a procurement and management concept for prototype flight research vehicles that produced rapid results at very low cost (approximately $50,000, excluding salaries of government employees assigned to the project).

The Adaptable, Deployable Entry and Placement Technology (ADEPT)

NASA Technical Reports Server (NTRS)

Wercinski, Paul

2017-01-01

The initial system-level development of the nano-ADEPT architecture will culminate in the launch of a 0.7 meter deployed diameter ADEPT sounding rocket flight experiment named, SR-1. Launch is planned for August 2017. The test will utilize the NASA Flight Opportunities Program sounding rocket platform provided by UP Aerospace to launch SR-1 to an apogee over 100 km and achieve re-entry conditions with a peak velocity near Mach 3. The SR-1 flight experiment will demonstrate most of the primary end-to-end mission stages including: launch in a stowed configuration, separation and deployment in exo-atmospheric conditions, and passive ballistic re-entry of a 70-degree half-angle faceted cone geometry.

Numerical Skip-Entry Guidance

NASA Technical Reports Server (NTRS)

Tigges, Michael; Crull, Timothy; Rea, Jeremy; Johnson, Wyatt

2006-01-01

This paper assesses a preliminary guidance and targeting strategy for accomplishing Skip-Entry (SE) flight during a lunar return-capsule entry flight. One of the primary benefits of flying a SE trajectory is to provide the crew with continuous Continental United States (CONUS) landing site access throughout the lunar month. Without a SE capability, the capsule must land either in water or at one of several distributed land sites in the Southern Hemisphere for a significant portion of a lunar month using a landing and recovery scenario similar to that employed during the Apollo program. With a SE trajectory, the capsule can land either in water at a site in proximity to CONUS or at one of several distributed landing sites within CONUS, thereby simplifying the operational requirements for crew retrieval and vehicle recovery, and possibly enabling a high degree of vehicle reusability. Note that a SE capability does not require that the vehicle land on land. A SE capability enables a longer-range flight than a direct-entry flight, which permits the vehicle to land at a much greater distance from the Entry Interface (EI) point. This does not exclude using this approach to push the landing point to a water location in proximity of CONUS and utilizing water or airborne recovery forces.

Post-Flight Analysis of GPSR Performance During Orion Exploration Flight Test 1

NASA Technical Reports Server (NTRS)

Barker, Lee; Mamich, Harvey; McGregor, John

2016-01-01

On 5 December 2014, the first test flight of the Orion Multi-Purpose Crew Vehicle executed a unique and challenging flight profile including an elevated re-entry velocity and steeper flight path angle to envelope lunar re-entry conditions. A new navigation system including a single frequency (L1) GPS receiver was evaluated for use as part of the redundant navigation system required for human space flight. The single frequency receiver was challenged by a highly dynamic flight environment including flight above low Earth orbit, as well as single frequency operation with ionospheric delay present. This paper presents a brief description of the GPS navigation system, an independent analysis of flight telemetry data, and evaluation of the GPSR performance, including evaluation of the ionospheric model employed to supplement the single frequency receiver. Lessons learned and potential improvements will be discussed.

Ceramic Adhesive and Methods for On-Orbit Repair of Re-Entry Vehicles

NASA Technical Reports Server (NTRS)

Riedell, James A.; Easler, Timothy E.

2013-01-01

This adhesive is capable of repairing damaged leading edge components of reentry vehicles while in space, and is novel with regard to its ability to be applied in the vacuum of space, and in a microgravity environment. Once applied, the adhesive provides thermal and oxidation protection to the substrate (in this case, reinforced carbon/carbon composites, RCCs) during re-entry of a space vehicle. Although there may be many formulations for repair adhesives, at the time of this reporting, this is the first known adhesive capable of an on-orbit repair. The adhesive is an engineered ceramic material composed of a pre-ceramic polymer and refractory powders in the form of a paste or putty that can be applied to a scratched, cracked, or fractured composite surface, covering and protecting the damaged area. The adhesive is then "cured" with a heat cycle, thereby cross-linking the polymer into a hardened material and bonding it to the substrate. During the heat of reentry, the material is converted to a ceramic coating that provides thermal and oxidative stability to the repaired area, thus allowing the vehicle to pass safely from space into the upper atmosphere. Ceramic powders such as SiC, ZrB2 and Y2O3 are combined with allylhydridopolycarbosilane (AHPCS) resin, and are mixed to form a paste adhesive. The material is then applied to the damaged area by brush, spatula, trowel, or other means to fill cracks, gaps, and holes, or used to bond patches onto the damaged area. The material is then cured, in a vacuum, preferably at 250F (approximately equal to 121C) for two hours. The re-entry heating of the vehicle at temperatures in excess of 3,000F (approximately equal to 1,650C) then converts this material into a ceramic coating. This invention has demonstrated advantages in resistance to high temperatures, as was demonstrated in more than 100 arc-jet tests in representative environments at NASA. Extensive testing verified oxidation protection for the repaired substrate (RCC), and confirmed that the microstructure of the resulting repair leads to durability and resistance to melting or flow. Its processability and working life in a vacuum was demonstrated by NASA astronauts in glovebox processing studies, as well as on-orbit in the open space shuttle bay. All of these advantages increase the working life of NASA vehicles, as well as improve safety for any crew on a manned vehicle. The adhesive, trademarked NOAX(TM). or Non-Oxide Adhesive Experimental, flew on all space shuttle missions from Return To Flight (STS-114) until the final flight (STS- 135) as a crack repair material for the leading edges and nose cap of the vehicle. NOAX(TM) was patented under U.S. Patents 7,628,878 and 7,888,277.

Exploration Flight Test 1 Afterbody Aerothermal Environment Reconstruction

NASA Technical Reports Server (NTRS)

Hyatt, Andrew J.; Oliver, Brandon; Amar, Adam; Lessard, Victor

2016-01-01

The Exploration Flight Test 1 vehicle included roughly 100 near surface thermocouples on the after body of the vehicle. The temperature traces at each of these instruments have been used to perform inverse environment reconstruction to determine the aerothermal environment experienced during re-entry of the vehicle. This paper provides an overview of the reconstructed environments and identifies critical aspects of the environment. These critical aspects include transition and reaction control system jet influence. A blind test of the process and reconstruction tool was also performed to build confidence in the reconstructed environments. Finally, an uncertainty quantification analysis was also performed to identify the impact of each of the uncertainties on the reconstructed environments.

Characterisation of re-entrant circuit (or rotational activity) in vitro using the HL1-6 myocyte cell line.

PubMed

Houston, Charles; Tzortzis, Konstantinos N; Roney, Caroline; Saglietto, Andrea; Pitcher, David S; Cantwell, Chris D; Chowdhury, Rasheda A; Ng, Fu Siong; Peters, Nicholas S; Dupont, Emmanuel

2018-06-01

Fibrillation is the most common arrhythmia observed in clinical practice. Understanding of the mechanisms underlying its initiation and maintenance remains incomplete. Functional re-entries are potential drivers of the arrhythmia. Two main concepts are still debated, the "leading circle" and the "spiral wave or rotor" theories. The homogeneous subclone of the HL1 atrial-derived cardiomyocyte cell line, HL1-6, spontaneously exhibits re-entry on a microscopic scale due to its slow conduction velocity and the presence of triggers, making it possible to examine re-entry at the cellular level. We therefore investigated the re-entry cores in cell monolayers through the use of fluorescence optical mapping at high spatiotemporal resolution in order to obtain insights into the mechanisms of re-entry. Re-entries in HL1-6 myocytes required at least two triggers and a minimum colony area to initiate (3.5 to 6.4 mm 2 ). After electrical activity was completely stopped and re-started by varying the extracellular K + concentration, re-entries never returned to the same location while 35% of triggers re-appeared at the same position. A conduction delay algorithm also allows visualisation of the core of the re-entries. This work has revealed that the core of re-entries is conduction blocks constituted by lines and/or groups of cells rather than the round area assumed by the other concepts of functional re-entry. This highlights the importance of experimentation at the microscopic level in the study of re-entry mechanisms. Copyright © 2018 The Authors. Published by Elsevier Ltd.. All rights reserved.

PredGuid+A: Orion Entry Guidance Modified for Aerocapture

NASA Technical Reports Server (NTRS)

Lafleur, Jarret

2013-01-01

PredGuid+A software was developed to enable a unique numerical predictor-corrector aerocapture guidance capability that builds on heritage Orion entry guidance algorithms. The software can be used for both planetary entry and aerocapture applications. Furthermore, PredGuid+A implements a new Delta-V minimization guidance option that can take the place of traditional targeting guidance and can result in substantial propellant savings. PredGuid+A allows the user to set a mode flag and input a target orbit's apoapsis and periapsis. Using bank angle control, the guidance will then guide the vehicle to the appropriate post-aerocapture orbit using one of two algorithms: Apoapsis Targeting or Delta-V Minimization (as chosen by the user). Recently, the PredGuid guidance algorithm was adapted for use in skip-entry scenarios for NASA's Orion multi-purpose crew vehicle (MPCV). To leverage flight heritage, most of Orion's entry guidance routines are adapted from the Apollo program.

The design and realisation of the IXV Mission Analysis and Flight Mechanics

NASA Astrophysics Data System (ADS)

Haya-Ramos, Rodrigo; Blanco, Gonzalo; Pontijas, Irene; Bonetti, Davide; Freixa, Jordi; Parigini, Cristina; Bassano, Edmondo; Carducci, Riccardo; Sudars, Martins; Denaro, Angelo; Angelini, Roberto; Mancuso, Salvatore

2016-07-01

The Intermediate eXperimental Vehicle (IXV) is a suborbital re-entry demonstrator successfully launched in February 2015 focusing on the in-flight demonstration of a lifting body system with active aerodynamic control surfaces. This paper presents an overview of the Mission Analysis and Flight Mechanics of the IXV vehicle, which comprises computation of the End-to-End (launch to splashdown) design trajectories, characterisation of the Entry Corridor, assessment of the Mission Performances through Monte Carlo campaigns, contribution to the aerodynamic database, analysis of the Visibility and link budget from Ground Stations and GPS, support to safety analyses (off nominal footprints), specification of the Centre of Gravity box, selection of the Angle of Attack trim line to be flown and characterisation of the Flying Qualities performances. An initial analysis and comparison with the raw flight data obtained during the flight will be discussed and first lessons learned derived.

Planetary/DOD entry technology flight experiments. Volume 1: Executive summary

NASA Technical Reports Server (NTRS)

Christensen, H. E.; Krieger, R. J.; Mcneilly, W. R.; Vetter, H. C.

1976-01-01

The feasibility of using the space shuttle to launch planetary and DoD entry flight experiments was examined. The results of the program are presented in two parts: (1) simulating outer planet environments during an earth entry test, the prediction of Jovian and earth radiative heating dominated environments, mission strategy, booster performance and entry vehicle design, and (2) the DoD entry test needs for the 1980's, the use of the space shuttle to meet these DoD test needs, modifications of test procedures as pertaining to the space shuttle, modifications to the space shuttle to accommodate DoD test missions and the unique capabilities of the space shuttle. The major findings of this program are summarized.

Aerodynamics of the EXPERT Re-Entry Ballistic Vehicle

NASA Astrophysics Data System (ADS)

Kharitonov, A. M.; Adamov, N. P.; Mazhul, I. I.; Vasenyov, L. G.; Zvegintsev, V. I.; Muylaert, J. M.

2009-01-01

Since 2002 till now, experimental studies of the EXPERT reentry capsule have been performed in ITAM SB RAS wind tunnels. These studies have been performed in consecutive ISTC project No. 2109, 3151, and currently ongoing project No. 3550. The results of earlier studies in ITAM wind tunnels can be found in [1-4]. The present paper describes new data obtained for the EXPERT model.

Military Power of the People’s Republic of China, 2009

DTIC Science & Technology

2009-01-01

executed for taking bribes to approve fake drugs. Environment . China’s economic development has come at a significant environmental cost...Satellite ASEAN : Association of Southeast Asian Nations ASEM: Asia-Europe Meeting ASBM: Anti-Ship Ballistic Missile ASCM: Anti-Ship Cruise Missile ASM...Operational Capability IRBM: Intermediate-Range Ballistic Missile LACM: Land Attack Cruise Missile LEO: Low Earth Orbit MaRV: Maneuvering Re- entry Vehicle

Symmetric Missile Dynamic Instabilities - A Review

DTIC Science & Technology

1980-03-01

and a Magnus side moment must be added to the total aerodynamic moment. Since statically stable missiles are usually spun to reduce the effect of...Identify by block~ numbef) Symmetric Missile Roil Moment Resonance Spin Dynamic Stability Side Moment Damxping Moment Trim Moment Magnus Moment Moving...dlamping moments for nonspin- ning re-entry vehicles, nonlinear Magnus moments for spinning missiles, and internal resonances with moving payload

Evaluation of a school re-entry nursing intervention for children with cancer.

PubMed

McCarthy, A M; Williams, J; Plumer, C

1998-07-01

A retrospective qualitative design was used to identify and compare the concerns, parents, teachers, and children have regarding school re-entry after a cancer diagnosis and to describe the impact of a school re-entry program on parents', teachers', and children's concerns. Audiotaped, semistructured interviews were obtained from a convenience sample of 10 children with cancer (ages 5 to 13 years), 10 mothers, and nine teachers. All participants were positive about the school re-entry nursing intervention, which is described. Results of content analyses indicate that before the intervention, mothers were concerned about their child's safety and peer teasing; teachers were concerned about their own knowledge and peers' adjustment, and children were concerned with keeping up with school activities. After the intervention, mothers were less concerned about peer teasing but continued to be worried about their child's safety in the school setting and began to have concerns about academic progress and physical stamina; teachers reported increased concerns for the child's safety and academic progress, and a desire to return to normal routines in the classroom: and the children continued to have concerns with maintaining academic and/physical progress. Clinical and research implications are discussed.

Procedural and Early Outcomes of Two Re-entry Devices for Subintimal Recanalization of Aortoiliac and Femoropopliteal Chronic Total Occlusions.

PubMed

Vuruskan, Ertan; Saracoglu, Erhan

2017-01-01

Subintimal angioplasty is a common treatment choice for chronic total occlusions (CTO) in the iliac and femoropopliteal arteries. This article describes the technical aspects and early outcomes of two different re-entry devices and comparison with manual re-entry technique. A retrospective review of 61 patients (re-entry group) treated with Outback or Pioneer Plus catheters was carried out. A matched cohort of patients (n=62) who underwent lower extremity interventions without the use of re-entry devices (manual re-entry group) were also analyzed (overall 123 patients were analyzed). Procedural success, procedural durations, patency estimates, ankle-brachial indices, and complications were analyzed. Sixty-one patients underwent Outback or Pioneer Plus guided subintimal recanalization. After the procedure, ankle-brachial indices significantly increased in all patients during follow-up. Primary patency for the entire cohort was 83% in the first month. When the re-entry device group was compared with manual re-entry group, no difference was found with respect to success, complication, and patencies between the two groups during follow-up. However, procedure duration and the amount of contrast agent used was significantly decreased in re-entry groups (p<0.001). Also, re-entry time was significantly decreased in Pioneer plus group according to Outback group (p<0.001). Recanalization of CTO using re-entry devices for aortoiliac or femoropopliteal arteries is safe and effective. These devices shorten the procedure time, the re-entry time, reduce radiation risk, and reduce the amount of contrast agent employed.

Orbiter Return-To-Flight Entry Aeroheating

NASA Technical Reports Server (NTRS)

Campbell, Charles H.; Anderson, Brian; Bourland, Gary; Bouslog, Stan; Cassady, Amy; Horvath, Tom; Berry, Scott A.; Gnoffo, Peter; Wood, Bill; Reuther, James;

Effective Thermal Conductivity of High Temperature Insulations for Reusable Launch Vehicles

NASA Technical Reports Server (NTRS)

Daryabeigi, Kamran

1999-01-01

An experimental apparatus was designed to measure the effective thermal conductivity of various high temperature insulations subject to large temperature gradients representative of typical launch vehicle re-entry aerodynamic heating conditions. The insulation sample cold side was maintained around room temperature, while the hot side was heated to temperatures as high as 1800 degrees Fahrenheit. The environmental pressure was varied from 0.0001 to 760 torr. All the measurements were performed in a dry gaseous nitrogen environment. The effective thermal conductivity of Saffil, Q-Fiber felt, Cerachrome, and three multi-layer insulation configurations were measured.

A theoretical study of the initiation, maintenance and termination of gastric slow wave re-entry.

PubMed

Du, Peng; Paskaranandavadivel, Niranchan; O'Grady, Greg; Tang, Shou-Jiang; Cheng, Leo K

2015-12-01

Gastric slow wave dysrhythmias are associated with motility disorders. Periods of tachygastria associated with slow wave re-entry were recently recognized as one important dysrhythmia mechanism, but factors promoting and sustaining gastric re-entry are currently unknown. This study reports two experimental forms of gastric re-entry and presents a series of multi-scale models that define criteria for slow wave re-entry initiation, maintenance and termination. High-resolution electrical mapping was conducted in porcine and canine models and two spatiotemporal patterns of re-entrant activities were captured: single-loop rotor and double-loop figure-of-eight. Two separate multi-scale mathematical models were developed to reproduce the velocity and entrainment frequency of these experimental recordings. A single-pulse stimulus was used to invoke a rotor re-entry in the porcine model and a figure-of-eight re-entry in the canine model. In both cases, the simulated re-entrant activities were found to be perpetuated by tachygastria that was accompanied by a reduction in the propagation velocity in the re-entrant pathways. The simulated re-entrant activities were terminated by a single-pulse stimulus targeted at the tip of re-entrant wave, after which normal antegrade propagation was restored by the underlying intrinsic frequency gradient. (i) the stability of re-entry is regulated by stimulus timing, intrinsic frequency gradient and conductivity; (ii) tachygastria due to re-entry increases the frequency gradient while showing decreased propagation velocity; (iii) re-entry may be effectively terminated by a targeted stimulus at the core, allowing the intrinsic slow wave conduction system to re-establish itself. © The authors 2014. Published by Oxford University Press on behalf of the Institute of Mathematics and its Applications. All rights reserved.

A theoretical study of the initiation, maintenance and termination of gastric slow wave re-entry

PubMed Central

Du, Peng; Paskaranandavadivel, Niranchan; O’Grady, Greg; Tang, Shou-Jiang; Cheng, Leo K.

2015-01-01

Gastric slow wave dysrhythmias are associated with motility disorders. Periods of tachygastria associated with slow wave re-entry were recently recognized as one important dysrhythmia mechanism, but factors promoting and sustaining gastric re-entry are currently unknown. This study reports two experimental forms of gastric re-entry and presents a series of multi-scale models that define criteria for slow wave re-entry initiation, maintenance and termination. High-resolution electrical mapping was conducted in porcine and canine models and two spatiotemporal patterns of re-entrant activities were captured: single-loop rotor and double-loop figure-of-eight. Two separate multi-scale mathematical models were developed to reproduce the velocity and entrainment frequency of these experimental recordings. A single-pulse stimulus was used to invoke a rotor re-entry in the porcine model and a figure-of-eight re-entry in the canine model. In both cases, the simulated re-entrant activities were found to be perpetuated by tachygastria that was accompanied by a reduction in the propagation velocity in the re-entrant pathways. The simulated re-entrant activities were terminated by a single-pulse stimulus targeted at the tip of re-entrant wave, after which normal antegrade propagation was restored by the underlying intrinsic frequency gradient. Main findings: (i) the stability of re-entry is regulated by stimulus timing, intrinsic frequency gradient and conductivity; (ii) tachygastria due to re-entry increases the frequency gradient while showing decreased propagation velocity; (iii) re-entry may be effectively terminated by a targeted stimulus at the core, allowing the intrinsic slow wave conduction system to re-establish itself. PMID:25552487

Integrated Thermal Response Tool for Earth Entry Vehicles

NASA Technical Reports Server (NTRS)

Chen, Y.-K.; Milos, F. S.; Partridge, Harry (Technical Monitor)

2001-01-01

A system is presented for multi-dimensional, fully-coupled thermal response modeling of hypersonic entry vehicles. The system consists of a two-dimensional implicit thermal response, pyrolysis and ablation program (TITAN), a commercial finite-element thermal and mechanical analysis code (MARC), and a high fidelity Navier-Stokes equation solver (GIANTS). The simulations performed by this integrated system include hypersonic flow-field, fluid and solid interaction, ablation, shape change, pyrolysis gas generation and flow, and thermal response of heatshield and structure. The thermal response of the ablating and charring heatshield material is simulated using TITAN, and that of the underlying structural is simulated using MARC. The ablating heatshield is treated as an outer boundary condition of the structure, and continuity conditions of temperature and heat flux are imposed at the interface between TITAN and MARC. Aerothermal environments with fluid and solid interaction are predicted by coupling TITAN and GIANTS through surface energy balance equations. With this integrated system, the aerothermal environments for an entry vehicle and the thermal response of both the heatshield and the structure can be obtained simultaneously. Representative computations for a proposed blunt body earth entry vehicle are presented and discussed in detail.

Assessment on EXPERT Descent and Landing System Aerodynamics

NASA Astrophysics Data System (ADS)

Wong, H.; Muylaert, J.; Northey, D.; Riley, D.

2009-01-01

EXPERT is a re-entry vehicle designed for validation of aero-thermodynamic models, numerical schemes in Computational Fluid Dynamics codes and test facilities for measuring flight data under an Earth re-entry environment. This paper addresses the design for the descent and landing sequence for EXPERT. It includes the descent sequence, the choice of drogue and main parachutes, and the parachute deployment condition, which can be supersonic or subsonic. The analysis is based mainly on an engineering tool, PASDA, together with some hand calculations for parachute sizing and design. The tool consists of a detailed 6-DoF simulation performed with the aerodynamics database of the vehicle, an empirical wakes model and the International Standard Atmosphere database. The aerodynamics database for the vehicle is generated by DNW experimental data and CFD codes within the framework of an ESA contract to CIRA. The analysis will be presented in terms of altitude, velocity, accelerations, angle-of- attack, pitch angle and angle of rigging line. Discussion on the advantages and disadvantages of each parachute deployment condition is included in addition to some comparison with the available data based on a Monte-Carlo method from a Russian company, FSUE NIIPS. Sensitivity on wind speed to the performance of EXPERT is shown to be strong. Supersonic deployment of drogue shows a better performance in stability at the expense of a larger G-load than those from the subsonic deployment of drogue. Further optimization on the parachute design is necessary in order to fulfill all the EXPERT specifications.

Re-Entry Women: Special Programs for Special Populations. Field Evaluation Draft.

ERIC Educational Resources Information Center

Hall, Roberta M.; Gleaves, Francelia D.

This pamphlet provides information on what higher education institutions can do to accomodate women over 25 who have interrupted their education for several years and are now entering or re-entering postsecondary institutions. Topics discussed include institutional attitudes, double discrimination, institutional invisibility, and barriers to…

Anatomy of an entry vehicle experiment

NASA Technical Reports Server (NTRS)

Eide, D. G.; Wurster, K. E.; Helms, V. T.; Ashby, G. C.

1981-01-01

The anatomy and evolution of a simple small-scale unmanned entry vehicle is described that is delivered to orbit by the shuttle and entered into the atmosphere from orbit to acquire flight data to improve our knowledge of boundary-layer behavior and evaluate advanced thermal protection systems. The anatomy of the experiment includes the justification for the experiments, instrumentation, configuration, material, and operational needs, and the translation of these needs into a configuration, weight statement, aerodynamics, program cost, and trajectory. Candidates for new instrumentation development are also identified for nonintrusive measurements of the boundary-layer properties.

Balloon launched decelerator test program: Post-test test report

NASA Technical Reports Server (NTRS)

Dickinson, D.; Schlemmer, J.; Hicks, F.; Michel, F.; Moog, R. D.

1972-01-01

Balloon Launched Decelerator Test (BLDT) flights were conducted during the summer of 1972 over the White Sands Missile Range. The purpose of these tests was to qualify the Viking disk-gap band parachute system behind a full-scale simulator of the Viking Entry Vehicle over the maximum range of entry conditions anticipated in the Viking '75 soft landing on Mars. Test concerns centered on the ability of a minimum weight parachute system to operate without structural damage in the turbulent wake of the blunt-body entry vehicle (140 deg, 11.5 diameter cone). This is the first known instance of parachute operation at supersonic speeds in the wake of such a large blunt body. The flight tests utilized the largest successful balloon-payload weight combination known to get to high altitude (120kft) where rocket engines were employed to boost the test vehicle to supersonic speeds and dynamic pressures simulating the range of conditions on Mars.

Maraia Capsule Flight Testing and Results for Entry, Descent, and Landing

NASA Technical Reports Server (NTRS)

Sostaric, Ronald R.; Strahan, Alan L.

2016-01-01

The Maraia concept is a modest size (150 lb., 30" diameter) capsule that has been proposed as an ISS based, mostly autonomous earth return capability to function either as an Entry, Descent, and Landing (EDL) technology test platform or as a small on-demand sample return vehicle. A flight test program has been completed including high altitude balloon testing of the proposed capsule shape, with the purpose of investigating aerodynamics and stability during the latter portion of the entry flight regime, along with demonstrating a potential recovery system. This paper includes description, objectives, and results from the test program.

Pathological implications of cell cycle re-entry in Alzheimer disease.

PubMed

Bonda, David J; Lee, Hyun-pil; Kudo, Wataru; Zhu, Xiongwei; Smith, Mark A; Lee, Hyoung-gon

2010-06-29

The complex neurodegeneration underlying Alzheimer disease (AD), although incompletely understood, is characterised by an aberrant re-entry into the cell cycle in neurons. Pathological evidence, in the form of cell cycle markers and regulatory proteins, suggests that cell cycle re-entry is an early event in AD, which precedes the formation of amyloid-beta plaques and neurofibrillary tangles (NFTs). Although the exact mechanisms that induce and mediate these cell cycle events in AD are not clear, significant advances have been made in further understanding the pathological role of cell cycle re-entry in AD. Importantly, recent studies indicate that cell cycle re-entry is not a consequence, but rather a cause, of neurodegeneration, suggesting that targeting of cell cycle re-entry may provide an opportunity for therapeutic intervention. Moreover, multiple inducers of cell cycle re-entry and their interactions in AD have been proposed. Here, we review the most recent advances in understanding the pathological implications of cell cycle re-entry in AD.

Re-entry simulation chamber for thermo-mechanical characterisation of space materials

NASA Astrophysics Data System (ADS)

Liedtke, Volker

2003-09-01

During re-entry, materials and components are subject to very high thermal and mechanical loads. Any failure may cause loss of mission. Therefore, materials and components have to be tested under most rigid conditions to verify the suitability of the material and to verify the design of the components. The Re-Entry Simulation Chamber (RESiC) at ARC Seibersdorf research (ARCS) allows simulating the high thermal loads as well as complex mechanical load profiles that may occur during a re-entry; additionally, the influence of chemical reactions of materials with gaseous components of the atmosphere can be studied. The high vacuum chamber (better than 1×10-6 mbar) has a diameter of 650 mm and allows a sample height of 500 mm, or 1000 mm with extension flange. The gas dosing system is designed to emulate the increasing atmospheric pressure during the re-entry trajectory of a vehicle. Heating is performed by a 30 kW induction generator that allows a sufficiently rapid heating of larger components; electrically conductive materials such as metals or carbon fibre reinforced ceramics are directly heated, while for electrical insulators, susceptor plates or tubes will be employed. The uniaxial servo-hydraulic testing machine has a maximum load of 70 kN, either static or with a frequency of up to 70 Hz, with any given load profile (sinus, rectangular, triangular, ...). Strain measurements will be done by non-contacting laser speckle system for maximum flexibility and minimum instrumentation time effort (currently under application testing), or by strain gauges. All relevant process parameters are controlled and recorded by microcomputer. The highly sophisticated control software allows a convenient and reliable multi-channel data acquisition, e.g. temperatures at various positions of the test piece, pressure, loads, strains, and any other test data according to customer specifications; the data format is suitable for any further data processing. During the set-up and operation testing, the device has successfully been employed for thermal shock testing, thermal cycling and gas cycling tests, thermomechanical tests and combinations thereof, e.g. sintering or hot-pressing. During the current final test series, the device will be completed, further optimised and shall be fully operational in summer 2003.

APOLLO/SATURN (A/S) 201 - LAUNCH - CAPE

NASA Image and Video Library

1966-02-26

A/S 201 was launched from the Kennedy Space Center Launch Complex 34 at 11:12 a.m., 02/26/1966. The instrumented Apollo Command and Service Module, and, a spacecraft Lunar Excursion Module Adapter, was successfully launched on the unmanned suborbital mission by the Saturn 1B to check spacecraft launch vehicle mechanical compatibility and to test the spacecraft heat shield in a high-velocity re-entry mode. CAPE KENNEDY, FL

Military Power of the People’s Republic of China

DTIC Science & Technology

2009-01-01

executed for taking bribes to approve fake drugs. Environment . China’s economic development has come at a significant environmental cost. Acceptable air... ASEAN : Association of Southeast Asian Nations ASEM: Asia-Europe Meeting ASBM: Anti-Ship Ballistic Missile ASCM: Anti-Ship Cruise Missile ASM: Air-to...Capability IRBM: Intermediate-Range Ballistic Missile LACM: Land Attack Cruise Missile LEO: Low Earth Orbit MaRV: Maneuvering Re- entry Vehicle MINUSTAH

KSC-2014-2502

NASA Image and Video Library

2014-05-11

CAPE CANAVERAL, Fla. – Fans sign the banner surrounding NASA's Orion boilerplate test vehicle on display at Petco Park in San Diego, California, before the start of a San Diego Padres' baseball game. The boilerplate test vehicle is being prepared for an Exploration Flight Test-1, or EFT-1, pre-transportation test. The Ground Systems Development and Operations Program will run the test at the U.S. Naval Base San Diego to simulate retrieval and transportation procedures for Orion after it splashes down in the ocean and is retrieved for return to land and ground transportation back to Kennedy Space Center in Florida. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of the Orion is scheduled to launch later this year atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Kim Shiflett

KSC-2014-2497

NASA Image and Video Library

2014-05-10

CAPE CANAVERAL, Fla. – Doug Lenhardt, Kennedy Space Center's Exploration Flight Test-1, or EFT-1, mission integration manager displays a baseball from the San Diego Padres inside Petco Park in San Diego, California. NASA's Orion boilerplate test vehicle is on display at the stadium. The boilerplate test vehicle is being prepared for an EFT-1 pre-transportation test. The Ground Systems Development and Operations Program will run the test to simulate retrieval and transportation procedures for Orion after it splashes down in the ocean and is retrieved for return to land and ground transportation back to Kennedy Space Center in Florida. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of the Orion is scheduled to launch later this year atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Kim Shiflett

KSC-2014-2495

NASA Image and Video Library

2014-05-10

CAPE CANAVERAL, Fla. – The Orion boilerplate test vehicle is on display at Petco Park in San Diego, California, before the San Diego Padres' baseball game. The boilerplate test vehicle is being prepared for an Exploration Flight Test-1, or EFT-1, pre-transportation test. The Ground Systems Development and Operations Program will run the test at the U.S. Naval Base San Diego to simulate retrieval and transportation procedures for Orion after it splashes down in the ocean and is retrieved for return to land and ground transportation back to Kennedy Space Center in Florida. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of the Orion is scheduled to launch later this year atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Kim Shiflett

KSC-2014-2498

NASA Image and Video Library

2014-05-11

CAPE CANAVERAL, Fla. – A San Diego Padres fan on stilts stands near NASA's Orion boilerplate test vehicle on display at Petco Park in San Diego, California. The boilerplate test vehicle will be prepared for an Exploration Flight Test-1, or EFT-1, pre-transportation test. The Ground Systems Development and Operations Program will run the test at the U.S. Naval Base San Diego to simulate retrieval and transportation procedures for Orion after it splashes down in the ocean and is retrieved for return to land and ground transportation back to Kennedy Space Center in Florida. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of the Orion is scheduled to launch later this year atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Kim Shiflett

KSC-2014-2499

NASA Image and Video Library

2014-05-11

CAPE CANAVERAL, Fla. – Fans sign the banner draped around NASA's Orion boilerplate test vehicle on display at the San Diego Padres Petco Field in San Diego, California, before the start of the baseball game. The test vehicle is being prepared for an Exploration Flight Test-1, or EFT-1, pre-transportation test. The Ground Systems Development and Operations Program will run the test at the U.S. Naval Base San Diego to simulate retrieval and transportation procedures for Orion after it splashes down in the ocean and is retrieved for return to land and ground transportation back to Kennedy Space Center in Florida. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of the Orion is scheduled to launch later this year atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Kim Shiflett

KSC-2014-2494

NASA Image and Video Library

2014-05-10

CAPE CANAVERAL, Fla. – The Orion boilerplate test vehicle is on display at Petco Park in San Diego, California, before the San Diego Padres' baseball game. The boilerplate test vehicle is being prepared for an Exploration Flight Test-1, or EFT-1, pre-transportation test. The Ground Systems Development and Operations Program will run the test at the U.S. Naval Base San Diego to simulate retrieval and transportation procedures for Orion after it splashes down in the ocean and is retrieved for return to land and ground transportation back to Kennedy Space Center in Florida. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of the Orion is scheduled to launch later this year atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Kim Shiflett

KSC-2014-2501

NASA Image and Video Library

2014-05-11

CAPE CANAVERAL, Fla. – Fans check out NASA's Orion boilerplate test vehicle on display at Petco Park in San Diego, California, before the start of a San Diego Padres' baseball game. The boilerplate test vehicle is being prepared for an Exploration Flight Test-1, or EFT-1, pre-transportation test. The Ground Systems Development and Operations Program will run the test at the U.S. Naval Base San Diego to simulate retrieval and transportation procedures for Orion after it splashes down in the ocean and is retrieved for return to land and ground transportation back to Kennedy Space Center in Florida. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of the Orion is scheduled to launch later this year atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Kim Shiflett

KSC-2014-2492

NASA Image and Video Library

2014-05-10

CAPE CANAVERAL, Fla. – The Orion boilerplate test vehicle is on display at Petco Park in San Diego, California, before the San Diego Padres' baseball game. The boilerplate test vehicle is being prepared for an Exploration Flight Test-1, or EFT-1, pre-transportation test. The Ground Systems Development and Operations Program will run the test at the U.S. Naval Base San Diego to simulate retrieval and transportation procedures for Orion after it splashes down in the ocean and is retrieved for return to land and ground transportation back to Kennedy Space Center in Florida. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of the Orion is scheduled to launch later this year atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Kim Shiflett

KSC-2014-2503

NASA Image and Video Library

2014-05-11

CAPE CANAVERAL, Fla. – Fans check out NASA's Orion boilerplate test vehicle on display at Petco Park in San Diego, California, before the start of a San Diego Padres' baseball game. The boilerplate test vehicle is being prepared for an Exploration Flight Test-1, or EFT-1, pre-transportation test. The Ground Systems Development and Operations Program will run the test at the U.S. Naval Base San Diego to simulate retrieval and transportation procedures for Orion after it splashes down in the ocean and is retrieved for return to land and ground transportation back to Kennedy Space Center in Florida. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of the Orion is scheduled to launch later this year atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Kim Shiflett

CMC thermal protection system for future reusable launch vehicles: Generic shingle technological maturation and tests

NASA Astrophysics Data System (ADS)

Pichon, T.; Barreteau, R.; Soyris, P.; Foucault, A.; Parenteau, J. M.; Prel, Y.; Guedron, S.

2009-07-01

Experimental re-entry demonstrators are currently being developed in Europe, with the objective of increasing the technology readiness level (TRL) of technologies applicable to future reusable launch vehicles. Among these are the Pre-X programme, currently funded by CNES, the French Space Agency, and which is about to enter into development phase B, and the IXV, within the future launcher preparatory programme (FLPP) funded by ESA. One of the major technologies necessary for such vehicles is the thermal protection system (TPS), and in particular the ceramic matrix composites (CMC) based windward TPS. In support of this goal, technology maturation activities named "generic shingle" were initiated beginning of 2003 by SPS, under a CNES contract, with the objective of performing a test campaign of a complete shingle of generic design, in preparation of the development of a re-entry experimental vehicle decided in Europe. The activities performed to date include: the design, manufacturing of two C/SiC panels, finite element model (FEM) calculation of the design, testing of technological samples extracted from a dedicated panel, mechanical pressure testing of a panel, and a complete study of the attachment system. Additional testing is currently under preparation on the panel equipped with its insulation, seal, attachment device, and representative portion of cold structure, to further assess its behaviour in environments relevant to its application The paper will present the activities that will have been performed in 2006 on the prediction and preparation of these modal characterization, dynamic, acoustic as well as thermal and thermo-mechanical tests. Results of these tests will be presented and the lessons learned will be discussed.

Electromagnetic shielding of thermal protection system for hypersonic vehicles

NASA Astrophysics Data System (ADS)

Albano, M.; Micheli, D.; Gradoni, G.; Morles, R. B.; Marchetti, M.; Moglie, F.; Mariani Primiani, V.

2013-06-01

The numerical simulation and the measurement of electromagnetic shielding at microwave frequencies of thermal protection system for hypersonic vehicles is presented using nested reverberation chamber. An example of a possible thermal protection system for a re-entry vehicle is presented. This system based on carbon material is electromagnetically characterized. The characterization takes into account not only the materials but also the final assembly configuration of the thermal protection system. The frequency range is 2-8 GHz. The results of measurements and simulations show that the microwave shielding effectiveness of carbon materials is above 60 dB for a single tile and that the tile inter-distance is able to downgrade the shielding effectiveness on the average to about 40 dB.

KSC-2013-3718

NASA Image and Video Library

2013-10-22

CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, the Orion test vehicle, or GTA, is lifted by crane in the transfer aisle of the Vehicle Assembly Building. The ground test vehicle is being used for path finding operations, including simulated manufacturing, assembly and stacking procedures. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Dimitri Gerondidakis

Re-entry vehicle shape for enhanced performance

NASA Technical Reports Server (NTRS)

Brown, James L. (Inventor); Garcia, Joseph A. (Inventor); Prabhu, Dinesh K. (Inventor)

2008-01-01

A convex shell structure for enhanced aerodynamic performance and/or reduced heat transfer requirements for a space vehicle that re-enters an atmosphere. The structure has a fore-body, an aft-body, a longitudinal axis and a transverse cross sectional shape, projected on a plane containing the longitudinal axis, that includes: first and second linear segments, smoothly joined at a first end of each the first and second linear segments to an end of a third linear segment by respective first and second curvilinear segments; and a fourth linear segment, joined to a second end of each of the first and second segments by curvilinear segments, including first and second ellipses having unequal ellipse parameters. The cross sectional shape is non-symmetric about the longitudinal axis. The fourth linear segment can be replaced by a sum of one or more polynomials, trigonometric functions or other functions satisfying certain constraints.

Re-Entry of Women to the Labour Market After an Interruption in Employment.

ERIC Educational Resources Information Center

Seear, B. N.

The problems involved in the re-entry of women into employment were studied, and the extent to which there exists a demand for employment for re-entry women was examined. A growing number of women are seeking re-entry in a wide range of income levels. The demand for part-time work appears to exceed supply. Official machinery for assisting re-entry…

Method of Determining the Aerodynamic Characteristics of a Flying Vehicle from the Surface Pressure

NASA Astrophysics Data System (ADS)

Volkov, V. F.; Dyad'kin, A. A.; Zapryagaev, V. I.; Kiselev, N. P.

2017-11-01

The paper presents a description of the procedure used for determining the aerodynamic characteristics (forces and moments acting on a model of a flying vehicle) obtained from the results of pressure measurements on the surface of a model of a re-entry vehicle with operating retrofire brake rockets in the regime of hovering over a landing surface is given. The algorithm for constructing the interpolation polynomial over interpolation nodes in the radial and azimuthal directions using the assumption on the symmetry of pressure distribution over the surface is presented. The aerodynamic forces and moments at different tilts of the vehicle are obtained. It is shown that the aerodynamic force components acting on the vehicle in the regime of landing and caused by the action of the vertical velocity deceleration nozzle jets are negligibly small in comparison with the engine thrust.

Analysis of flight test transition and turbulent heating data. Part 1: Boundary layer transition results

NASA Technical Reports Server (NTRS)

Martellucci, A.; Maguire, B. L.; Neff, R. S.

1972-01-01

The objective of the study was to provide a detailed post flight evaluation of ballistic vehicle flight test boundary layer transition data. A total of fifty-five vehicles were selected for analysis. These vehicles were chosen from a data sampling of roughly two hundred flights and the criteria for vehicle selection is delineated herein. The results of the analysis indicate that frustum transition of re-entry vehicles appears to be nose tip dominated. Frustum related parameters and materials apparently have a second order effect on transition. This implies that local viscous parameters on the frustum should not correlate flight test transition data, and in fact they do not. Specific parameters relative to the nose tip have been identified as the apparent dominant factors that characterize the transition phenomena and a correlation of flight test data is presented.

Preventing re-entry to foster care.

PubMed

Carnochan, Sarah; Rizik-Baer, Daniel; Austin, Michael J

2013-01-01

Re-entry to foster care generally refers to circumstances in which children who have been discharged from foster care to be reunified with their family of origin, adopted, or provided kinship guardianship are returned to foster care. In the context of the federal performance measurement system, re-entry refers specifically to a return to foster care following an unsuccessful reunification. The federal Children and Family Services Review measures re-entry to foster care with a single indicator, called the permanency of reunification indicator, one of four indicators comprising the reunification composite measure. This review focuses on research related to the re-entry indicator, including the characteristics of children, caregivers and families, as well as case and child welfare services that are associated with a higher or lower risk of re-entry to foster care. Promising post-reunification services designed to prevent re-entry to foster care are described.

Radiative and convective heating during Venus entry.

NASA Technical Reports Server (NTRS)

Page, W. A.; Woodward, H. T.

1972-01-01

Determination of the stagnation region heating of probes entering the Venusian atmosphere. Both convective and radiative heat-transfer rates are predicted, and account is taken of the important effects of radiative transport in the vehicle shock layer. A nongray radiative transport model is utilized which parallels a four-band treatment previously developed for air (Page et al., 1969), but includes two additional bands to account for the important CO(4+) molecular band system. Some comparisons are made between results for Venus entry and results for earth entry obtained using a viscous earth entry program.

KSC-2013-2342

NASA Image and Video Library

2013-05-13

CAPE CANAVERAL, Fla. -- At NASA’s Kennedy Space Center in Florida, workers move the Orion ground test vehicle, or GTA, into the Launch Equipment Test Facility, or LETF, from the Operations and Checkout Building. At the LETF, Lockheed Martin will put the GTA through a series of pyrotechnic bolt tests. The ground test vehicle is being used for path finding operations in the O&C, including simulated manufacturing and assembly procedures. Launching atop NASA's heavy-lift Space Launch System SLS, which also is under development, the Orion Multi-Purpose Crew Vehicle MPCV will serve as the exploration vehicle that will carry astronaut crews beyond low Earth orbit. It also will provide emergency abort capabilities, sustain the crew during space travel and provide safe re-entry from deep space return velocities. For more information, visit www.nasa.gov/orion. Photo credit: Jim Grossman

KSC-2013-2340

NASA Image and Video Library

2013-05-13

CAPE CANAVERAL, Fla. -- At NASA’s Kennedy Space Center in Florida, workers prepare to move the Orion ground test vehicle, or GTA, from the Operations and Checkout Building to the Launch Equipment Test Facility, or LETF. At the LETF, Lockheed Martin will put the GTA through a series of pyrotechnic bolt tests. The ground test vehicle is being used for path finding operations in the O&C, including simulated manufacturing and assembly procedures. Launching atop NASA's heavy-lift Space Launch System SLS, which also is under development, the Orion Multi-Purpose Crew Vehicle MPCV will serve as the exploration vehicle that will carry astronaut crews beyond low Earth orbit. It also will provide emergency abort capabilities, sustain the crew during space travel and provide safe re-entry from deep space return velocities. For more information, visit www.nasa.gov/orion. Photo credit: Jim Grossman

KSC-2013-2341

NASA Image and Video Library

2013-05-13

CAPE CANAVERAL, Fla. -- At NASA’s Kennedy Space Center in Florida, workers move the Orion ground test vehicle, or GTA, from the Operations and Checkout Building to the Launch Equipment Test Facility, or LETF. At the LETF, Lockheed Martin will put the GTA through a series of pyrotechnic bolt tests. The ground test vehicle is being used for path finding operations in the O&C, including simulated manufacturing and assembly procedures. Launching atop NASA's heavy-lift Space Launch System SLS, which also is under development, the Orion Multi-Purpose Crew Vehicle MPCV will serve as the exploration vehicle that will carry astronaut crews beyond low Earth orbit. It also will provide emergency abort capabilities, sustain the crew during space travel and provide safe re-entry from deep space return velocities. For more information, visit www.nasa.gov/orion. Photo credit: Jim Grossman

KSC-2013-2343

NASA Image and Video Library

2013-05-13

CAPE CANAVERAL, Fla. -- At NASA’s Kennedy Space Center in Florida, workers move the Orion ground test vehicle, or GTA, into the Launch Equipment Test Facility, or LETF, from the Operations and Checkout Building. At the LETF, Lockheed Martin will put the GTA through a series of pyrotechnic bolt tests. The ground test vehicle is being used for path finding operations in the O&C, including simulated manufacturing and assembly procedures. Launching atop NASA's heavy-lift Space Launch System SLS, which also is under development, the Orion Multi-Purpose Crew Vehicle MPCV will serve as the exploration vehicle that will carry astronaut crews beyond low Earth orbit. It also will provide emergency abort capabilities, sustain the crew during space travel and provide safe re-entry from deep space return velocities. For more information, visit www.nasa.gov/orion. Photo credit: Jim Grossman

Development of an innovative validation strategy of gas-surface interaction modelling for re-entry applications

NASA Astrophysics Data System (ADS)

Joiner, N.; Esser, B.; Fertig, M.; Gülhan, A.; Herdrich, G.; Massuti-Ballester, B.

2016-12-01

This paper summarises the final synthesis of an ESA technology research programme entitled "Development of an Innovative Validation Strategy of Gas Surface Interaction Modelling for Re-entry Applications". The focus of the project was to demonstrate the correct pressure dependency of catalytic surface recombination, with an emphasis on Low Earth Orbit (LEO) re-entry conditions and thermal protection system materials. A physics-based model describing the prevalent recombination mechanisms was proposed for implementation into two CFD codes, TINA and TAU. A dedicated experimental campaign was performed to calibrate and validate the CFD model on TPS materials pertinent to the EXPERT space vehicle at a wide range of temperatures and pressures relevant to LEO. A new set of catalytic recombination data was produced that was able to improve the chosen model calibration for CVD-SiC and provide the first model calibration for the Nickel-Chromium super-alloy PM1000. The experimentally observed pressure dependency of catalytic recombination can only be reproduced by the Langmuir-Hinshelwood recombination mechanism. Due to decreasing degrees of (enthalpy and hence) dissociation with facility stagnation pressure, it was not possible to obtain catalytic recombination coefficients from the measurements at high experimental stagnation pressures. Therefore, the CFD model calibration has been improved by this activity based on the low pressure results. The results of the model calibration were applied to the existing EXPERT mission profile to examine the impact of the experimentally calibrated model at flight relevant conditions. The heat flux overshoot at the CVD-SiC/PM1000 junction on EXPERT is confirmed to produce radiative equilibrium temperatures in close proximity to the PM1000 melt temperature.This was anticipated within the margins of the vehicle design; however, due to the measurements made here for the first time at relevant temperatures for the junction, an increased confidence in this finding is placed on the computations.

Optogenetic manipulation of anatomical re-entry by light-guided generation of a reversible local conduction block.

PubMed

Watanabe, Masaya; Feola, Iolanda; Majumder, Rupamanjari; Jangsangthong, Wanchana; Teplenin, Alexander S; Ypey, Dirk L; Schalij, Martin J; Zeppenfeld, Katja; de Vries, Antoine A F; Pijnappels, Daniël A

2017-03-01

Anatomical re-entry is an important mechanism of ventricular tachycardia, characterized by circular electrical propagation in a fixed pathway. It's current investigative and therapeutic approaches are non-biological, rather unspecific (drugs), traumatizing (electrical shocks), or irreversible (ablation). Optogenetics is a new biological technique that allows reversible modulation of electrical function with unmatched spatiotemporal precision using light-gated ion channels. We therefore investigated optogenetic manipulation of anatomical re-entry in ventricular cardiac tissue. Transverse, 150-μm-thick ventricular slices, obtained from neonatal rat hearts, were genetically modified with lentiviral vectors encoding Ca2+-translocating channelrhodopsin (CatCh), a light-gated depolarizing ion channel, or enhanced yellow fluorescent protein (eYFP) as control. Stable anatomical re-entry was induced in both experimental groups. Activation of CatCh was precisely controlled by 470-nm patterned illumination, while the effects on anatomical re-entry were studied by optical voltage mapping. Regional illumination in the pathway of anatomical re-entry resulted in termination of arrhythmic activity only in CatCh-expressing slices by establishing a local and reversible, depolarization-induced conduction block in the illuminated area. Systematic adjustment of the size of the light-exposed area in the re-entrant pathway revealed that re-entry could be terminated by either wave collision or extinction, depending on the depth (transmurality) of illumination. In silico studies implicated source-sink mismatches at the site of subtransmural conduction block as an important factor in re-entry termination. Anatomical re-entry in ventricular tissue can be manipulated by optogenetic induction of a local and reversible conduction block in the re-entrant pathway, allowing effective re-entry termination. These results provide distinctively new mechanistic insight into re-entry termination and a novel perspective for cardiac arrhythmia management. Published on behalf of the European Society of Cardiology. All rights reserved. © The Author 2017. For permissions, please email: journals.permissions@oup.com.

An Upgrade of the Imaging for Hypersonic Experimental Aeroheating Testing (IHEAT) Software

NASA Technical Reports Server (NTRS)

Mason, Michelle L.; Rufer, Shann J.

2015-01-01

The Imaging for Hypersonic Experimental Aeroheating Testing (IHEAT) code is used at NASA Langley Research Center to analyze global aeroheating data on wind tunnel models tested in the Langley Aerothermodynamics Laboratory. One-dimensional, semi-infinite heating data derived from IHEAT are used to design thermal protection systems to mitigate the risks due to the aeroheating loads on hypersonic vehicles, such as re-entry vehicles during descent and landing procedures. This code was originally written in the PV-WAVE programming language to analyze phosphor thermography data from the two-color, relativeintensity system developed at Langley. To increase the efficiency, functionality, and reliability of IHEAT, the code was migrated to MATLAB syntax and compiled as a stand-alone executable file labeled version 4.0. New features of IHEAT 4.0 include the options to batch process all of the data from a wind tunnel run, to map the two-dimensional heating distribution to a three-dimensional computer-aided design model of the vehicle to be viewed in Tecplot, and to extract data from a segmented line that follows an interesting feature in the data. Results from IHEAT 4.0 were compared on a pixel level to the output images from the legacy code to validate the program. The differences between the two codes were on the order of 10-5 to 10-7. IHEAT 4.0 replaces the PV-WAVE version as the production code for aeroheating experiments conducted in the hypersonic facilities at NASA Langley.

Mission Management Computer Software for RLV-TD

NASA Astrophysics Data System (ADS)

Manju, C. R.; Joy, Josna Susan; Vidya, L.; Sheenarani, I.; Sruthy, C. N.; Viswanathan, P. C.; Dinesh, Sudin; Jayalekshmy, L.; Karuturi, Kesavabrahmaji; Sheema, E.; Syamala, S.; Unnikrishnan, S. Manju; Ali, S. Akbar; Paramasivam, R.; Sheela, D. S.; Shukkoor, A. Abdul; Lalithambika, V. R.; Mookiah, T.

2017-12-01

The Mission Management Computer (MMC) software is responsible for the autonomous navigation, sequencing, guidance and control of the Re-usable Launch Vehicle (RLV), through lift-off, ascent, coasting, re-entry, controlled descent and splashdown. A hard real-time system has been designed for handling the mission requirements in an integrated manner and for meeting the stringent timing constraints. Redundancy management and fault-tolerance techniques are also built into the system, in order to achieve a successful mission even in presence of component failures. This paper describes the functions and features of the components of the MMC software which has accomplished the successful RLV-Technology Demonstrator mission.

The samara spacecraft: Design and development of a self-stabilizing, auto-rotating, distributed sensing system

NASA Astrophysics Data System (ADS)

Lalloobhai, Amit Desai

The objective of this research is the design and development of a self-stabilizing re-entry vehicle that closely resembles naturally occurring seeds in nature. It was hypothesized that a femto-satellite with a shape of a samara could self stabilize and passively generate lift, as well as transmit a signal during its descent through the atmosphere. The research included a conceptual design phase and a preliminary design phase that entailed analytic simulations, and an experimental demonstration. The goal was to investigate the feasibility of developing the above-mentioned femto-vehicle that could increase the range capability of its descent to maximize data capture.

KSC-04pd1428

NASA Image and Video Library

2004-07-07

KENNEDY SPACE CENTER, FLA. - - Workers in the Orbiter Processing Facility complete the installation of the Reinforced Carbon-Carbon panel on Discovery. The chin panel is the smile-shaped section of RCC directly below the nose cap that provides a thermal barrier during re-entry. The nose cap, with chin panel, was removed from the vehicle in the summer of 2003 and returned to the vendor, where it underwent numerous forms of Non-Destructive Evaluation. These tests included X-ray, ultrasound and eddy current to ensure its structural integrity prior to reinstallation. Discovery is designated as the Return to Flight vehicle for mission STS-114, no earlier than March 2005.

KSC-04pd1424

NASA Image and Video Library

2004-07-07

KENNEDY SPACE CENTER, FLA. - Workers in the Orbiter Processing Facility lift the Reinforced Carbon-Carbon (RCC) chin panel to install on Discovery. The chin panel is the smile-shaped section of RCC directly below the nose cap that provides a thermal barrier during re-entry. The nose cap, with chin panel, was removed from the vehicle in the summer of 2003 and returned to the vendor, where it underwent numerous forms of Non-Destructive Evaluation. These tests included X-ray, ultrasound and eddy current to ensure its structural integrity prior to reinstallation. Discovery is designated as the Return to Flight vehicle for mission STS-114, no earlier than March 2005.

KSC-04pd1425

NASA Image and Video Library

2004-07-07

KENNEDY SPACE CENTER, FLA. - Workers in the Orbiter Processing Facility lift the Reinforced Carbon-Carbon (RCC) chin panel into place on Discovery. The chin panel is the smile-shaped section of RCC directly below the nose cap that provides a thermal barrier during re-entry. The nose cap, with chin panel, was removed from the vehicle in the summer of 2003 and returned to the vendor, where it underwent numerous forms of Non-Destructive Evaluation. These tests included X-ray, ultrasound and eddy current to ensure its structural integrity prior to reinstallation. Discovery is designated as the Return to Flight vehicle for mission STS-114, no earlier than March 2005.

KSC-04pd1423

NASA Image and Video Library

2004-07-07

KENNEDY SPACE CENTER, FLA. - Workers in the Orbiter Processing Facility prepare the Reinforced Carbon-Carbon (RCC) chin panel to install on Discovery. The chin panel is the smile-shaped section of RCC directly below the nose cap that provides a thermal barrier during re-entry. The nose cap, with chin panel, was removed from the vehicle in the summer of 2003 and returned to the vendor, where it underwent numerous forms of Non-Destructive Evaluation. These tests included X-ray, ultrasound and eddy current to ensure its structural integrity prior to reinstallation. Discovery is designated as the Return to Flight vehicle for mission STS-114, no earlier than March 2005.

KSC-04pd1427

NASA Image and Video Library

2004-07-07

KENNEDY SPACE CENTER, FLA. - - Workers in the Orbiter Processing Facility check the placement of the Reinforced Carbon-Carbon chin panel on Discovery. The chin panel is the smile-shaped section of RCC directly below the nose cap that provides a thermal barrier during re-entry. The nose cap, with chin panel, was removed from the vehicle in the summer of 2003 and returned to the vendor, where it underwent numerous forms of Non-Destructive Evaluation. These tests included X-ray, ultrasound and eddy current to ensure its structural integrity prior to reinstallation. Discovery is designated as the Return to Flight vehicle for mission STS-114, no earlier than March 2005.

KSC-04pd1426

NASA Image and Video Library

2004-07-07

KENNEDY SPACE CENTER, FLA. - Workers in the Orbiter Processing Facility check the placement of the Reinforced Carbon-Carbon (RCC) chin panel on Discovery. . The chin panel is the smile-shaped section of RCC directly below the nose cap that provides a thermal barrier during re-entry. The nose cap, with chin panel, was removed from the vehicle in the summer of 2003 and returned to the vendor, where it underwent numerous forms of Non-Destructive Evaluation. These tests included X-ray, ultrasound and eddy current to ensure its structural integrity prior to reinstallation. Discovery is designated as the Return to Flight vehicle for mission STS-114, no earlier than March 2005.

Roles of Engineering Correlations in Hypersonic Entry Boundary Layer Transition Prediction

NASA Technical Reports Server (NTRS)

Campbell, Charles H.; King, Rudolph A.; Kergerise, Michael A.; Berry, Scott A.; Horvath, Thomas J.

2010-01-01

Efforts to design and operate hypersonic entry vehicles are constrained by many considerations that involve all aspects of an entry vehicle system. One of the more significant physical phenomenon that affect entry trajectory and thermal protection system design is the occurrence of boundary layer transition from a laminar to turbulent state. During the Space Shuttle Return To Flight activity following the loss of Columbia and her crew of seven, NASA's entry aerothermodynamics community implemented an engineering correlation based framework for the prediction of boundary layer transition on the Orbiter. The methodology for this implementation relies upon the framework of correlation techniques that have been in use for several decades. What makes the Orbiter boundary layer transition correlation implementation unique is that a statistically significant data set was acquired in multiple ground test facilities, flight data exists to assist in establishing a better correlation and the framework was founded upon state of the art chemical nonequilibrium Navier Stokes flow field simulations. The basic tenets that guided the formulation and implementation of the Orbiter Return To Flight boundary layer transition prediction capability will be reviewed as a recommended format for future empirical correlation efforts. The validity of this approach has since been demonstrated by very favorable comparison of recent entry flight testing performed with the Orbiter Discovery, which will be graphically summarized. These flight data can provide a means to validate discrete protuberance engineering correlation approaches as well as high fidelity prediction methods to higher confidence. The results of these Orbiter engineering and flight test activities only serve to reinforce the essential role that engineering correlations currently exercise in the design and operation of entry vehicles. The framework of information-related to the Orbiter empirical boundary layer transition prediction capability will be utilized to establish a fresh perspective on this role, to illustrate how quantitative statistical evaluations of empirical correlations can and should be used to assess accuracy and to discuss what the authors' perceive as a recent heightened interest in the application of high fidelity numerical modeling of boundary layer transition. Concrete results will also be developed related to empirical boundary layer transition onset correlations. This will include assessment of the discrete protuberance boundary layer transition onset data assembled for the Orbiter configuration during post-Columbia Return To Flight. Assessment of these data will conclude that momentum thickness Reynolds number based correlations have superior coefficients and uncertainty in comparison to roughness height based Reynolds numbers, aka Re(sub k) or Re(sub kk). In addition, linear regression results from roughness height Reynolds number based correlations will be evaluated, leading to a hypothesis that non-continuum effects play a role in the processes associated with incipient boundary layer transition on discrete protuberances.

KSC-2014-4094

NASA Image and Video Library

2014-09-17

SAN DIEGO, Calif. – A Zodiac boat containing U.S. Navy divers approaches the Orion boilerplate test vehicle floating in the Pacific Ocean, a distance away from the USS Anchorage, during the third day of Orion Underway Recovery Test 3. Orange stabilizers on the top of the test vehicle were inflated to simulate the system that will be used to upright Orion in the water after splashdown. NASA, Lockheed Martin and U.S. Navy personnel are conducting the recovery test using the test vehicle to prepare for recovery of the Orion crew module on its return from a deep space mission. The test allows the teams to demonstrate and evaluate the recovery processes, procedures, hardware and personnel in open waters. The Ground Systems Development and Operations Program is conducting the underway recovery tests. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion is scheduled to launch in 2014 atop a United Launch Alliance Delta IV Heavy rocket and in 2018 on NASA’s Space Launch System rocket. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Cory Huston

Design, Integration, Certification and Testing of the Orion Crew Module Propulsion System

NASA Technical Reports Server (NTRS)

McKay, Heather; Freeman, Rich; Cain, George; Albright, John D.; Schoenberg, Rich; Delventhal, Rex

2014-01-01

The Orion Multipurpose Crew Vehicle (MPCV) is NASA's next generation spacecraft for human exploration of deep space. Lockheed Martin is the prime contractor for the design, development, qualification and integration of the vehicle. A key component of the Orion Crew Module (CM) is the Propulsion Reaction Control System, a high-flow hydrazine system used during re-entry to orient the vehicle for landing. The system consists of a completely redundant helium (GHe) pressurization system and hydrazine fuel system with monopropellant thrusters. The propulsion system has been designed, integrated, and qualification tested in support of the Orion program's first orbital flight test, Exploration Flight Test One (EFT-1), scheduled for 2014. A subset of the development challenges and lessons learned from this first flight test campaign will be discussed in this paper for consideration when designing future spacecraft propulsion systems. The CONOPS and human rating requirements of the CM propulsion system are unique when compared with a typical satellite propulsion reaction control system. The system requires a high maximum fuel flow rate. It must operate at both vacuum and sea level atmospheric pressure conditions. In order to meet Orion's human rating requirements, multiple parts of the system must be redundant, and capable of functioning after spacecraft system fault events.

Development of the VS-50 as an Intermediate Step Towards LM-1

NASA Astrophysics Data System (ADS)

Ettl, J.; Kirchhartz, R.; Hrbud, I.; Basken, R.; Raith, G.; Hecht, M.; de Almeide, F. A.; Roda, E. D.

2015-09-01

The VS-50 launch vehicle is the designated intermediate development step of the VLM-1. The VLM-1 launch system is a joint venture between the research center for space DCTAIIAE in Brazil and the German Aerospace Center (DLR) in Germany. Development highlights are application of carbon fiber technologies for the S50 motor case and interstage adaptor, use of fiberglass for the fairing, newly developed thrust vector assembly (TVA) consisting of commercial components, unique navigation system encompassing two IMUs, a GPS receiver, and adaptive control algorithms guiding the vehicle. The VS-50 is a two-stage vehicle using S50 and S44 motors. The development of the VS-50 serves two major purposes: First, VS-SO represents a technological development stage in the VLM-1 development roadmap, and second, it serves as a carrier for scientific payloads. Potential payloads are aerodynamic probes for yielding scientific aero-dynamic and thermo-dynamic data sets at regimes up to 18 Mach. Further, the VS-50 could be used for re-entry research and investigation of re-usable flight objectives.

Comparison of cryoablation with 3D mapping versus conventional mapping for the treatment of atrioventricular re-entrant tachycardia and right-sided paraseptal accessory pathways.

PubMed

Russo, Mario S; Drago, Fabrizio; Silvetti, Massimo S; Righi, Daniela; Di Mambro, Corrado; Placidi, Silvia; Prosperi, Monica; Ciani, Michele; Naso Onofrio, Maria T; Cannatà, Vittorio

2016-06-01

Aim Transcatheter cryoablation is a well-established technique for the treatment of atrioventricular nodal re-entry tachycardia and atrioventricular re-entry tachycardia in children. Fluoroscopy or three-dimensional mapping systems can be used to perform the ablation procedure. The aim of this study was to compare the success rate of cryoablation procedures for the treatment of right septal accessory pathways and atrioventricular nodal re-entry circuits in children using conventional or three-dimensional mapping and to evaluate whether three-dimensional mapping was associated with reduced patient radiation dose compared with traditional mapping. In 2013, 81 children underwent transcatheter cryoablation at our institution, using conventional mapping in 41 children - 32 atrioventricular nodal re-entry tachycardia and nine atrioventricular re-entry tachycardia - and three-dimensional mapping in 40 children - 24 atrioventricular nodal re-entry tachycardia and 16 atrioventricular re-entry tachycardia. Using conventional mapping, the overall success rate was 78.1 and 66.7% in patients with atrioventricular nodal re-entry tachycardia or atrioventricular re-entry tachycardia, respectively. Using three-dimensional mapping, the overall success rate was 91.6 and 75%, respectively (p=ns). The use of three-dimensional mapping was associated with a reduction in cumulative air kerma and cumulative air kerma-area product of 76.4 and 67.3%, respectively (p<0.05). The use of three-dimensional mapping compared with the conventional fluoroscopy-guided method for cryoablation of right septal accessory pathways and atrioventricular nodal re-entry circuits in children was associated with a significant reduction in patient radiation dose without an increase in success rate.

Cross-cultural re-entry for missionaries: a new application for the Dual Process Model.

PubMed

Selby, Susan; Clark, Sheila; Braunack-Mayer, Annette; Jones, Alison; Moulding, Nicole; Beilby, Justin

Nearly half a million foreign aid workers currently work worldwide, including over 140,000 missionaries. During re-entry these workers may experience significant psychological distress. This article positions previous research about psychological distress during re-entry, emphasizing loss and grief. At present there is no identifiable theoretical framework to provide a basis for assessment, management, and prevention of re-entry distress in the clinical setting. The development of theoretical concepts and frameworks surrounding loss and grief including the Dual Process Model (DPM) are discussed. All the parameters of the DPM have been shown to be appropriate for the proposed re-entry model, the Dual Process Model applied to Re-entry (DPMR). It is proposed that the DPMR is an appropriate framework to address the processes and strategies of managing re-entry loss and grief. Possible future clinical applications and limitations of the proposed model are discussed. The DPMR is offered for further validation and use in clinical practice.

Convective Heating Predictions of Apollo IV Flight Data

NASA Technical Reports Server (NTRS)

White, Molly E.

2012-01-01

It has been more than 50 years since NASA engineers have attempted to design a manned space vehicle with the capability to return from beyond low Earth orbit. In this interval, our methodologies for designing the thermal protection system (TPS) to protect humans from the extremely high temperatures of re-entry have changed significantly. With these considerations in mind, we return to the Apollo IV (AS-501) flight data. This incredible data set allows us to assess the current tools and methodologies being used to design Orion MPCV. In particular, our ability to predict the aftbody separated region convective heating environments for MPCV is critical. The design uses reusable TPS in this area, whereas Apollo designers used ablative TPS which can withstand much more severe environments. This presentation will revisit the flight data, summarize the assumptions going into the analysis, present the results and draw conclusions regarding how accurately we can currently predict the heating in the aftbody separated region of a re-entry capsule.

HL-10 on lakebed showing subsonic control surface configuration

NASA Technical Reports Server (NTRS)

1966-01-01

This photo shows the HL-10 on lakebed with its subsonic control surface configuration. The unusual shapes of the lifting bodies, as well as the demands of flying a re-entry shape to comparative low-speed landings, required a complex set of control surfaces. The rudders also served as speed brakes, allowing the pilot to adjust his speed during descent. Moving the flaps at the rear of the fuselage in the same direction pitched the nose up, while moving them in opposite directions rolled the vehicle to the right or left. After the HL-10's fins were modified to improve its handling qualities, the vehicle proved to be the best handling of the original heavy-weight lifting bodies. The HL-10 was one of five heavyweight lifting-body designs flown at NASA's Flight Research Center (FRC--later Dryden Flight Research Center), Edwards, California, from July 1966 to November 1975 to study and validate the concept of safely maneuvering and landing a low lift-over-drag vehicle designed for reentry from space. Northrop Corporation built the HL-10 and M2-F2, the first two of the fleet of 'heavy' lifting bodies flown by the NASA Flight Research Center. The contract for construction of the HL-10 and the M2-F2 was $1.8 million. 'HL' stands for horizontal landing, and '10' refers to the tenth design studied by engineers at NASA's Langley Research Center, Hampton, Va. After delivery to NASA in January 1966, the HL-10 made its first flight on Dec. 22, 1966, with research pilot Bruce Peterson in the cockpit. Although an XLR-11 rocket engine was installed in the vehicle, the first 11 drop flights from the B-52 launch aircraft were powerless glide flights to assess handling qualities, stability, and control. In the end, the HL-10 was judged to be the best handling of the three original heavy-weight lifting bodies (M2-F2/F3, HL-10, X-24A). The HL-10 was flown 37 times during the lifting body research program and logged the highest altitude and fastest speed in the Lifting Body program. On Feb. 18, 1970, Air Force test pilot Peter Hoag piloted the HL-10 to Mach 1.86 (1,228 mph). Nine days later, NASA pilot Bill Dana flew the vehicle to 90,030 feet, which became the highest altitude reached in the program. Some new and different lessons were learned through the successful flight testing of the HL-10. These lessons, when combined with information from it's sister ship, the M2-F2/F3, provided an excellent starting point for designers of future entry vehicles, including the Space Shuttle.

A successful retrograde re-entry at aorta using the Outback LTD catheter for a bilateral common iliac artery occlusion.

PubMed

Kim, Tae-Hoon; Ahn, Ji-Hun; Kim, Do-Hoi

2013-05-01

The Outback LTD re-entry catheter system has become a valuable tool for peripheral intervention and it has been widely used for variable peripheral chronic total occlusion (CTO). However, its use in the setting of the aorta was restricted because of concerns of bleeding risks resulting from re-entry puncture or ballooning. This report presents a case of successful re-entry using the Outback LTD Re-Entry Catheter (Cordis, Bridgewater, New Jersy) at the aorta in a patient with bilateral common iliac artery occlusion. Copyright © 2012 Wiley Periodicals, Inc.

Adaptable, Deployable Entry and Placement Technology (ADEPT) Overview of FY15 Accomplishments

NASA Technical Reports Server (NTRS)

Wercinski, P.; Brivkalns, C.; Cassell, A.; Chen, Y.-K.; Boghozian, T.; Chinnapongse, R.; Gasch, M.; Kruger, C.; Makino, A.; Milos, F.;

Aerodynamic and Aerothermal TPS Instrumentation Reference Guide

NASA Technical Reports Server (NTRS)

Woollard, Bryce A.; Braun, Robert D.; Bose, Deepack

2016-01-01

The hypersonic regime of planetary entry combines the most severe environments that an entry vehicle will encounter with the greatest amount of uncertainty as to the events unfolding during that time period. This combination generally leads to conservatism in the design of an entry vehicle, specifically that of the thermal protection system (TPS). Each planetary entry provides a valuable aerodynamic and aerothermal testing opportunity; the utilization of this opportunity is paramount in better understanding how a specific entry vehicle responds to the demands of the hypersonic entry environment. Previous efforts have been made to instrument entry vehicles in order to collect data during the entry period and reconstruct the corresponding vehicle response. The purpose of this paper is to cumulatively document past TPS instrumentation designs for applicable planetary missions, as well as to list pertinent results and any explainable shortcomings.

KSC-2013-3722

NASA Image and Video Library

2013-10-22

CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, the Orion ground test vehicle, or GTA, has been lifted high in the air by crane in the transfer aisle of the Vehicle Assembly Building. The ground test vehicle is being used for path finding operations, including simulated manufacturing, assembly and stacking procedures. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Dimitri Gerondidakis

KSC-2013-3720

NASA Image and Video Library

2013-10-22

CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, a view from above shows the Orion ground test vehicle, or GTA, being lifted by crane in the transfer aisle of the Vehicle Assembly Building. The ground test vehicle is being used for path finding operations, including simulated manufacturing, assembly and stacking procedures. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Dimitri Gerondidakis

KSC-2013-3717

NASA Image and Video Library

2013-10-22

CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, technicians monitor the progress as the Orion ground test vehicle, or GTA, is lifted by crane in the transfer aisle of the Vehicle Assembly Building. The ground test vehicle is being used for path finding operations, including simulated manufacturing, assembly and stacking procedures. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Dimitri Gerondidakis

KSC-2013-2344

NASA Image and Video Library

2013-05-13

CAPE CANAVERAL, Fla. -- At NASA’s Kennedy Space Center in Florida, Lockheed Martin crews begin uncovering the Orion ground test vehicle in the Launch Equipment Test Facility, or LETF. The GTA was moved from the Operations and Checkout Facility to the LETF for a series of pyrotechnic bolt tests. The GTA is being used for path finding operations in the O&C, including simulated manufacturing and assembly procedures. Launching atop NASA's heavy-lift Space Launch System SLS, which also is under development, the Orion Multi-Purpose Crew Vehicle MPCV will serve as the exploration vehicle that will carry astronaut crews beyond low Earth orbit. It also will provide emergency abort capabilities, sustain the crew during space travel and provide safe re-entry from deep space return velocities. For more information, visit www.nasa.gov/orion. Photo credit: Jim Grossman

KSC-2013-3721

NASA Image and Video Library

2013-10-22

CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, a view from above shows the Orion ground test vehicle, or GTA, being lifted by crane in the transfer aisle of the Vehicle Assembly Building. The ground test vehicle is being used for path finding operations, including simulated manufacturing, assembly and stacking procedures. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Dimitri Gerondidakis

KSC-2013-3729

NASA Image and Video Library

2013-10-22

CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, technicians attach the Orion ground test vehicle, or GTA, to a mockup of the service module in high bay 4 of the Vehicle Assembly Building. The ground test vehicle is being used for path finding operations, including simulated manufacturing, assembly and stacking procedures. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Dimitri Gerondidakis

KSC-2013-2345

NASA Image and Video Library

2013-05-13

CAPE CANAVERAL, Fla. -- At NASA’s Kennedy Space Center in Florida, Lockheed Martin crews uncover the Orion ground test vehicle in the Launch Equipment Test Facility, or LETF. The GTA was moved from the Operations and Checkout Facility to the LETF for a series of pyrotechnic bolt tests. The GTA is being used for path finding operations in the O&C, including simulated manufacturing and assembly procedures. Launching atop NASA's heavy-lift Space Launch System SLS, which also is under development, the Orion Multi-Purpose Crew Vehicle MPCV will serve as the exploration vehicle that will carry astronaut crews beyond low Earth orbit. It also will provide emergency abort capabilities, sustain the crew during space travel and provide safe re-entry from deep space return velocities. For more information, visit www.nasa.gov/orion. Photo credit: Jim Grossman

KSC-2013-3719

NASA Image and Video Library

2013-10-22

CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, technicians monitor the progress as the Orion ground test vehicle, or GTA, is lifted by crane in the transfer aisle of the Vehicle Assembly Building. The ground test vehicle is being used for path finding operations, including simulated manufacturing, assembly and stacking procedures. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Dimitri Gerondidakis

Multiple Re-entry Closures After TEVAR for Ruptured Chronic Post-dissection Thoraco-abdominal Aortic Aneurysm.

PubMed

Kinoshita, R; Ganaha, F; Ito, J; Ohyama, N; Abe, N; Yamazato, T; Munakata, H; Mabuni, K; Kugai, T

2018-01-01

Although thoracic endovascular aortic repair (TEVAR) has become a promising treatment for complicated acute type B dissection, its role in treating chronic post-dissection thoraco-abdominal aortic aneurysm (TAA) is still limited owing to persistent retrograde flow into the false lumen (FL) through abdominal or iliac re-entry tears. A case of chronic post-dissection TAA treatment, in which a dilated descending FL ruptured into the left thorax, is described. The primary entry tear was closed by emergency TEVAR and multiple abdominal re-entries were closed by EVAR. In addition, major re-entries at the detached right renal artery and iliac bifurcation were closed using covered stents. To close re-entries as far as possible, EVAR was carried out using the chimney technique, and additional aortic extenders were placed above the coeliac artery. A few re-entries remained, but complete FL thrombosis of the rupture site was achieved. Follow-up computed tomography showed significant shrinkage of the FL. In treating post-dissection TAA, entry closure by TEVAR is sometimes insufficient, owing to persistent retrograde flow into the FL from abdominal or iliac re-entries. Adjunctive techniques are needed to close these distal re-entries to obtain complete FL exclusion, especially in rupture cases. Recently, encouraging results of complete coverage of the thoraco-abdominal aorta with fenestrated or branched endografts have been reported; however, the widespread employment of such techniques appears to be limited owing to technical difficulties. The present method with multiple re-entry closures using off the shelf and immediately available devices is an alternative for the endovascular treatment of post-dissection TAA, especially in the emergency setting.

Lander Trajectory Reconstruction computer program

NASA Technical Reports Server (NTRS)

Adams, G. L.; Bradt, A. J.; Ferguson, J. B.; Schnelker, H. J.

1971-01-01

The Lander Trajectory Reconstruction (LTR) computer program is a tool for analysis of the planetary entry trajectory and atmosphere reconstruction process for a lander or probe. The program can be divided into two parts: (1) the data generator and (2) the reconstructor. The data generator provides the real environment in which the lander or probe is presumed to find itself. The reconstructor reconstructs the entry trajectory and atmosphere using sensor data generated by the data generator and a Kalman-Schmidt consider filter. A wide variety of vehicle and environmental parameters may be either solved-for or considered in the filter process.

Foster care re-entry: Exploring the role of foster care characteristics, in-home child welfare services and cross-sector services.

PubMed

Lee, Sangmoo; Jonson-Reid, Melissa; Drake, Brett

2012-09-01

This study seeks to advance our understanding of how modifiable and non-modifiable factors may impact the likelihood of re-entry into foster care. Children who entered foster care for the first time following at least one report of maltreatment and were then reunified were followed from exit to re-entry, age 18 or the end of the study period using longitudinal administrative data. Risk of re-entry was explored according to a range of modifiable and non-modifiable case and service characteristics. Children removed from homes with parents who had multiple risk factors (e.g., no high school diploma, mental health diagnosis, criminal record, or teen parents) or were receiving AFDC prior to entry were more likely to re-enter. The receipt of in-home child welfare services during or after foster care was associated with reduced risk of re-entry. Having the longest placement with a relative was associated with decreased risk of re-entry. In conclusion, both modifiable and non-modifiable factors are associated with re-entry into foster care. Among modifiable factors, services appear to have a particularly strong relationship to re-entry. Our data also suggest that in-home child welfare services provided during and after foster care may be associated with improved long-term permanency after return home. Given the continued import of caregiver risk factors even among reunified families, services provided to support reunification should include attention to caregiver needs outside parenting.

Foster care re-entry: Exploring the role of foster care characteristics, in-home child welfare services and cross-sector services☆

PubMed Central

Lee, Sangmoo; Jonson-Reid, Melissa; Drake, Brett

2013-01-01

This study seeks to advance our understanding of how modifiable and non-modifiable factors may impact the likelihood of re-entry into foster care. Children who entered foster care for the first time following at least one report of maltreatment and were then reunified were followed from exit to re-entry, age 18 or the end of the study period using longitudinal administrative data. Risk of re-entry was explored according to a range of modifiable and non-modifiable case and service characteristics. Children removed from homes with parents who had multiple risk factors (e.g., no high school diploma, mental health diagnosis, criminal record, or teen parents) or were receiving AFDC prior to entry were more likely to re-enter. The receipt of in-home child welfare services during or after foster care was associated with reduced risk of re-entry. Having the longest placement with a relative was associated with decreased risk of re-entry. In conclusion, both modifiable and non-modifiable factors are associated with re-entry into foster care. Among modifiable factors, services appear to have a particularly strong relationship to re-entry. Our data also suggest that in-home child welfare services provided during and after foster care may be associated with improved long-term permanency after return home. Given the continued import of caregiver risk factors even among reunified families, services provided to support reunification should include attention to caregiver needs outside parenting. PMID:23729947

Internal velocity factors

NASA Technical Reports Server (NTRS)

Cathcart, J. R.; Frank, A. J.; Massaglia, J. L.

1968-01-01

Computer program analyzes the entries and planetary trajectories of space vehicles. It obtains the equivalence of altitude and flight path angle, respectively, to acceleration load factor with respect to velocity for a given inertial velocity.

Simulation and experimental research on trans-media vehicle water-entry motion characteristics at low speed.

PubMed

Yang, Jian; Li, Yongli; Feng, Jinfu; Hu, Junhua; Liu, An

2017-01-01

The motion characteristics of trans-media vehicles during the water-entry process were explored in this study in an effort to obtain the optimal water-entry condition of the vehicle for developing a novel, single control strategy integrating underwater non-control and in-air control. A water-entry dynamics model is established by combining the water-entry motion characteristics of the vehicle in uncontrolled conditions at low speed with time-varying parameters (e.g. buoyancy, added mass). A water-entry experiment is designed to confirm the effectiveness of the established model. After that, by comparing the experimental results with the simulated results, the model is further modified to more accurately reflect water-entry motion. The change laws of the vehicle's attitude and position during the water-entry process are also obtained by analyzing the simulation of the modified model under different velocity, angle, and angle of attack conditions. The results presented here have guiding significance for the future realization of reaching the stable underwater navigation state of the vehicle after water-entry process.

A theoretical analysis of anatomical and functional intestinal slow wave re-entry.

PubMed

Du, Peng; O'Grady, Gregory; Cheng, Leo K

2017-07-21

Intestinal bioelectrical slow waves are a key regulator of intestinal motility. Peripheral pacemakers, ectopic initiations and sustained periods of re-entrant activities have all been experimentally observed to be important factors in setting the frequency of intestinal slow waves, but the tissue-level mechanisms underpinning these activities are unclear. This theoretical analysis aimed to define the initiation, maintenance, and termination criteria of two classes of intestinal re-entrant activities: anatomical re-entry and functional re-entry. Anatomical re-entry was modeled in a three-dimensional (3D) cylindrical model, and functional rotor was modeled in a 2D rectangle model. A single-pulse stimulus was used to invoke an anatomical re-entry and a prolonged refractory block was used to invoke the rotor. In both cases, the simulated re-entrant activities operated at frequencies above the baseline entrainment frequency. The anatomical re-entry simulation results demonstrated that a temporary functional refractory block would be required to initiate the re-entrant activity in a single direction around the cylindrical model. The rotor could be terminated by a single-pulse stimulus delivered around the core of the rotor. In conclusion, the simulation results provide the following new insights into the mechanisms of intestinal re-entry: (i) anatomical re-entry is only maintained within a specific range of velocities, outside of which the re-entrant activities become either an ectopic activity or simultaneous activations of the intestinal wall; (ii) a maintained rotor entrained slow waves faster in the antegrade direction than in the retrograde direction. Simulations are shown to be a valuable tool for achieving novel insights into the mechanisms of intestinal slow wave dysrhythmia. Copyright © 2017 Elsevier Ltd. All rights reserved.

Advanced Technology and Mitigation (ATDM) SPARC Re-Entry Code Fiscal Year 2017 Progress and Accomplishments for ECP.

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

Crozier, Paul; Howard, Micah; Rider, William J.

The SPARC (Sandia Parallel Aerodynamics and Reentry Code) will provide nuclear weapon qualification evidence for the random vibration and thermal environments created by re-entry of a warhead into the earth’s atmosphere. SPARC incorporates the innovative approaches of ATDM projects on several fronts including: effective harnessing of heterogeneous compute nodes using Kokkos, exascale-ready parallel scalability through asynchronous multi-tasking, uncertainty quantification through Sacado integration, implementation of state-of-the-art reentry physics and multiscale models, use of advanced verification and validation methods, and enabling of improved workflows for users. SPARC is being developed primarily for the Department of Energy nuclear weapon program, with additional developmentmore » and use of the code is being supported by the Department of Defense for conventional weapons programs.« less

Progress in Guidance and Control Research for Space Access and Hypersonic Vehicles (Preprint)

DTIC Science & Technology

2006-09-01

affect range capabilities. In 2003 an integrated adaptive guidance control and trajectory re- shaping algorithm was flight demonstrated using in-flight...21] which tied for the best scores as well as a Linear Quadratic Regulator[22], Predictor - Corrector [23], and Shuttle-like entry[24] guidance method...Accurate knowledge of mass, center- of-gravity and moments of inertia improves the perfor- mance of not only IAG& C algorithms but also model based

A New Guidance Method for a Delta V and Re-entry Constrained Orbit Transfer Problem

DTIC Science & Technology

2005-06-01

a vehicle that undertakes a maneuver with the objective of precisely flying through a point in space at a particular time. The spacecraft must...for the Example Spacecraft . . . . 50 4-1 Graphical Results of Large Changes in Orbital Velocity . . . . . . . . . . . 62 4-2 Contours of Perigee...Orbit Relative to Rendezvous Point . . . . . . . . . . 98 6-2 Angular Rate and Angles for GEM-CR Maneuver with ∆θ = 90◦ . . . . . . 101 6-3 Position

NASA Ames Contributes to Orion / EFT-1 Test Flight (Reporter Pkg)

NASA Image and Video Library

2014-12-03

NASA's Orion spacecraft is built to take humans farther than they've ever gone before. Orion will serve as the exploration vehicle that will carry the crew to space, provide emergency abort capability, sustain the crew during the space travel, and provide safe re-entry from deep space return velocities. NASA's Ames Research Center played a critical role in the development and preparation for the flight test designated Exploration Flight Test 1, or EFT-1.

SHEFEX II Flight Instrumentation And Preparation Of Post Flight Analysis

NASA Astrophysics Data System (ADS)

Thiele, Thomas; Siebe, Frank; Gulhan, Ali

2011-05-01

A main disadvantage of modern TPS systems for re- entry vehicles is the expensive manufacturing and maintenance process due to the complex geometry of these blunt nose configurations. To reduce the costs and to improve the aerodynamic performance the German Aerospace Center (DLR) is following a different approach using TPS structures consisting of flat ceramic tiles. To test these new sharp edged TPS structures the SHEFEX I flight experiment was designed and successfully performed by DLR in 2005. To further improve the reliability of the sharp edged TPS design at even higher Mach numbers, a second flight experiment SHEFEX II will be performed in September 2011. In comparison to SHEFEX I the second flight experiment has a fully symmetrical shape and will reach a maximum Mach number of about 11. Furthermore the vehicle has an active steering system using four canards to control the flight attitude during re-entry, e.g. roll angle, angle of attack and sideslip. After a successful flight the evaluation of the flight data will be performed using a combination of numerical and experimental tools. The data will be used for the improvement of the present numerical analysis tools and to get a better understanding of the aerothermal behaviour of sharp TPS structures. This paper presents the flight instrumentation of the SHEFEX II TPS. In addition the concept of the post flight analysis is presented.

Planetary/DOD entry technology flight experiments. Volume 2: Planetary entry flight experiments

NASA Technical Reports Server (NTRS)

Christensen, H. E.; Krieger, R. J.; Mcneilly, W. R.; Vetter, H. C.

1976-01-01

The technical feasibility of launching a high speed, earth entry vehicle from the space shuttle to advance technology for the exploration of the outer planets' atmospheres was established. Disciplines of thermodynamics, orbital mechanics, aerodynamics propulsion, structures, design, electronics and system integration focused on the goal of producing outer planet environments on a probe shaped vehicle during an earth entry. Major aspects of analysis and vehicle design studied include: planetary environments, earth entry environment capability, mission maneuvers, capabilities of shuttle upper stages, a comparison of earth entry planetary environments, experiment design and vehicle design.

Nonequilibrium radiation and chemistry models for aerocapture vehicle flowfields, volume 2

NASA Technical Reports Server (NTRS)

Carlson, Leland A.

1991-01-01

A technique was developed for predicting the character and magnitude of the shock wave precursor ahead of an entry vehicle and the effect of this precursor on the vehicle flow field was ascertained. A computational method and program were developed to properly model this precursor. Expressions were developed for the mass production rates of each species due to photodissociation and photoionization reactions. Also, consideration was given to the absorption and emission of radiation and how it affects the energy in each of the energy modes of both the atomic and diatomic species. A series of parametric studies were conducted covering a range of entry conditions in order to predict the effects of the precursor on the shock layer and the radiative heat transfer to the body.

Use of a Re-entry Device in Left Subclavian Occlusion: Case Series.

PubMed

Thomas, Wiliam Rhodri; Chick, Christopher; Goyal, Nimit

2018-01-01

To describe the use of a re-entry catheter in the endovascular treatment of left subclavian stenosis. We present three patients where initial attempts at re-vascularisation using standard techniques were unsuccessful. An OUTBACK catheter was employed to facilitate re-entry in these patients. True lumen re-entry was achieved in all patients, leading to successful treatment of all stenoses. There was a lack of filling of the left vertebral artery post-angioplasty in one patient; this was not clinically significant. The case series presented is encouraging for the use of a re-entry catheter in the treatment of subclavian occlusion. In our limited experience this has proved to be a safe technique for use in patients who fail re-vascularisation by standard methods; a larger study is required to confirm this.

Development and Test Plans for the MSR EEV

NASA Technical Reports Server (NTRS)

Dillman, Robert; Laub, Bernard; Kellas, Sotiris; Schoenenberger, Mark

2005-01-01

The goal of the proposed Mars Sample Return mission is to bring samples from the surface of Mars back to Earth for thorough examination and analysis. The Earth Entry Vehicle is the passive entry body designed to protect the sample container from entry heating and deceleration loads during descent through the Earth s atmosphere to a recoverable location on the surface. This paper summarizes the entry vehicle design and outlines the subsystem development and testing currently planned in preparation for an entry vehicle flight test in 2010 and mission launch in 2013. Planned efforts are discussed for the areas of the thermal protection system, vehicle trajectory, aerodynamics and aerothermodynamics, impact energy absorption, structure and mechanisms, and the entry vehicle flight test.

Policy advocacy and leadership training for formerly incarcerated women: an empowerment evaluation of ReConnect, a program of the Women in Prison Project, Correctional Association of New York.

PubMed

Pinto, R M; Rahman, R; Williams, A

2014-12-01

There is limited knowledge on re-entry initiatives for formerly incarcerated women specifically on building women's advocacy and leadership skills. Our research highlights an empowerment evaluation on ReConnect, a 12-session; innovative advocacy and leadership development program rooted in an integrated framework of empowerment, and transformational leadership theories. Using thematic analysis, we coded three focus groups with 24 graduates, for themes that matched our framework's concepts. ReConnect graduates reported being empowered by the information they received on parental rights, housing, and employment. Participants agreed that ReConnect improved their communication skills, preparing them to advocate for themselves and community members. Copyright © 2014 Elsevier Ltd. All rights reserved.

Cardiac re-entry dynamics and self-termination in DT-MRI based model of Human Foetal Heart

NASA Astrophysics Data System (ADS)

Biktasheva, Irina V.; Anderson, Richard A.; Holden, Arun V.; Pervolaraki, Eleftheria; Wen, Fen Cai

2018-02-01

The effect of human foetal heart geometry and anisotropy on anatomy induced drift and self-termination of cardiac re-entry is studied here in MRI based 2D slice and 3D whole heart computer simulations. Isotropic and anisotropic models of 20 weeks of gestational age human foetal heart obtained from 100μm voxel diffusion tensor MRI data sets were used in the computer simulations. The fiber orientation angles of the heart were obtained from the orientation of the DT-MRI primary eigenvectors. In a spatially homogeneous electrophysiological monodomain model with the DT-MRI based heart geometries, cardiac re-entry was initiated at a prescribed location in a 2D slice, and in the 3D whole heart anatomy models. Excitation was described by simplified FitzHugh-Nagumo kinetics. In a slice of the heart, with propagation velocity twice as fast along the fibres than across the fibers, DT-MRI based fiber anisotropy changes the re-entry dynamics from pinned to an anatomical re-entry. In the 3D whole heart models, the fiber anisotropy changes cardiac re-entry dynamics from a persistent re-entry to the re-entry self-termination. The self-termination time depends on the re-entry’s initial position. In all the simulations with the DT-MRI based cardiac geometry, the anisotropy of the myocardial tissue shortens the time to re-entry self-termination several folds. The numerical simulations depend on the validity of the DT-MRI data set used. The ventricular wall showed the characteristic transmural rotation of the helix angle of the developed mammalian heart, while the fiber orientation in the atria was irregular.

Piloted Simulator Tests of a Guidance System which Can Continously Predict Landing Point of a Low L/D Vehicle During Atmosphere Re-Entry

NASA Technical Reports Server (NTRS)

Wingrove, Rodney C.; Coate, Robert E.

1961-01-01

The guidance system for maneuvering vehicles within a planetary atmosphere which was studied uses the concept of fast continuous prediction of the maximum maneuver capability from existing conditions rather than a stored-trajectory technique. used, desired touchdown points are compared with the maximum range capability and heating or acceleration limits, so that a proper decision and choice of control inputs can be made by the pilot. In the method of display and control a piloted fixed simulator was used t o demonstrate the feasibility od the concept and to study its application to control of lunar mission reentries and recoveries from aborts.

Evaluation and Influence of Brachiocephalic Branch Re-entry in Patients With Type A Acute Aortic Dissection.

PubMed

Yasuda, Shota; Imoto, Kiyotaka; Uchida, Keiji; Karube, Norihisa; Minami, Tomoyuki; Goda, Motohiko; Suzuki, Shinichi; Masuda, Munetaka

2016-12-22

Stanford type A acute aortic dissection (A-AAD) extends to the brachiocephalic branches in some patients. After ascending aortic replacement, a remaining re-entry tear in the distal brachiocephalic branches may act as an entry and result in a patent false lumen in the aortic arch. However, the effect of brachiocephalic branch re-entry concomitant with A-AAD remains unknown.Methods and Results:Eighty-five patients with A-AAD who underwent ascending aortic replacement in which both preoperative and postoperative multiple-detector computed tomography (MDCT) scans could be evaluated were retrospectively studied. The presence of a patent false lumen in at least one of the brachiocephalic branches on preoperative MDCT was defined as brachiocephalic branch re-entry, and 41 patients (48%) had this. Postoperatively, 47 of 85 (55%) patients had a patent false lumen in the aortic arch. False lumen remained patent after operation in 34 out of the 41 (83%) patients with brachiocephalic branch re-entry, as compared to that in 13 of the 44 (30%) patients without such re-entry (P<0.001). Brachiocephalic branch re-entry was a significant risk factor for a late increase in the aortic arch diameter greater than 10 mm (P=0.047). Brachiocephalic branch re-entry in patients with A-AAD is related to a patent false lumen in the aortic arch early after ascending aortic replacement and is a risk factor for late aortic arch enlargement.

Predictors of re-entry into the child protection system in Singapore: a cumulative ecological-transactional risk model.

PubMed

Li, Dongdong; Chu, Chi Meng; Ng, Wei Chern; Leong, Wai

2014-11-01

This study examines the risk factors of re-entry for 1,750 child protection cases in Singapore using a cumulative ecological-transactional risk model. Using administrative data, the present study found that the overall percentage of Child Protection Service (CPS) re-entry in Singapore is 10.5% based on 1,750 cases, with a range from 3.9% (within 1 year) to 16.5% (within 8 years after case closure). One quarter of the re-entry cases were observed to occur within 9 months from case closure. Seventeen risk factors, as identified from the extant literature, were tested for their utility to predict CPS re-entry in this study using a series of Cox regression analyses. A final list of seven risk factors (i.e., children's age at entry, case type, case closure result, duration of case, household income, family size, and mother's employment status) was used to create a cumulative risk score. The results supported the cumulative risk model in that higher risk score is related to higher risk of CPS re-entry. Understanding the prevalence of CPS re-entry and the risk factors associated with re-entry is the key to informing practice and policy in a culturally relevant way. The results from this study could then be used to facilitate critical case management decisions in order to enhance positive outcomes of families and children in Singapore's care system. Copyright © 2014 Elsevier Ltd. All rights reserved.

Mars Underground News.

NASA Astrophysics Data System (ADS)

Edgett, K.

Contents: Next entry to Mars (Mars Pathfinder and the microrover Sojourner). Hello, Mars, we're back! Mars Global Surveyor update. The Mars program - 2001 and beyond. Schedule of missions to Mars (as of June 11, 1997). Mars on the Web.

NASA Tech Briefs, May 2013

NASA Technical Reports Server (NTRS)

2013-01-01

Topics include: Test Waveform Applications for JPL STRS Operating Environment; Pneumatic Proboscis Heat-Flow Probe; Method to Measure Total Noise Temperature of a Wireless Receiver During Operation; Cursor Control Device Test Battery; Functional Near-Infrared Spectroscopy Signals Measure Neuronal Activity in the Cortex; ESD Test Apparatus for Soldering Irons; FPGA-Based X-Ray Detection and Measurement for an X-Ray Polarimeter; Sequential Probability Ratio Test for Spacecraft Collision Avoidance Maneuver Decisions; Silicon/Carbon Nanotube Photocathode for Splitting Water; Advanced Materials and Fabrication Techniques for the Orion Attitude Control Motor; Flight Hardware Packaging Design for Stringent EMC Radiated Emission Requirements; RF Reference Switch for Spaceflight Radiometer Calibration; An Offload NIC for NASA, NLR, and Grid Computing; Multi-Scale CNT-Based Reinforcing Polymer Matrix Composites for Lightweight Structures; Ceramic Adhesive and Methods for On-Orbit Repair of Re-Entry Vehicles; Self-Healing Nanocomposites for Reusable Composite Cryotanks; Pt-Ni and Pt-Co Catalyst Synthesis Route for Fuel Cell Applications; Aerogel-Based Multilayer Insulation with Micrometeoroid Protection; Manufacturing of Nanocomposite Carbon Fibers and Composite Cylinders; Optimized Radiator Geometries for Hot Lunar Thermal Environments; A Mission Concept: Re-Entry Hopper-Aero-Space-Craft System on-Mars (REARM-Mars); New Class of Flow Batteries for Terrestrial and Aerospace Energy Storage Applications; Reliability of CCGA 1152 and CCGA 1272 Interconnect Packages for Extreme Thermal Environments; Using a Blender to Assess the Microbial Density of Encapsulated Organisms; Mixed Integer Programming and Heuristic Scheduling for Space Communication; Video Altimeter and Obstruction Detector for an Aircraft; Control Software for Piezo Stepping Actuators; Galactic Cosmic Ray Event-Based Risk Model (GERM) Code; Sasquatch Footprint Tool; and Multi-User Space Link Extension (SLE) System.

A real-time digital computer program for the simulation of automatic spacecraft reentries

NASA Technical Reports Server (NTRS)

Kaylor, J. T.; Powell, L. F.; Powell, R. W.

1977-01-01

The automatic reentry flight dynamics simulator, a nonlinear, six-degree-of-freedom simulation, digital computer program, has been developed. The program includes a rotating, oblate earth model for accurate navigation calculations and contains adjustable gains on the aerodynamic stability and control parameters. This program uses a real-time simulation system and is designed to examine entries of vehicles which have constant mass properties whose attitudes are controlled by both aerodynamic surfaces and reaction control thrusters, and which have automatic guidance and control systems. The program has been used to study the space shuttle orbiter entry. This report includes descriptions of the equations of motion used, the control and guidance schemes that were implemented, the program flow and operation, and the hardware involved.

Satellite Re-entry Modeling and Uncertainty Quantification

NASA Astrophysics Data System (ADS)

Horsley, M.

2012-09-01

LEO trajectory modeling is a fundamental aerospace capability and has applications in many areas of aerospace, such as maneuver planning, sensor scheduling, re-entry prediction, collision avoidance, risk analysis, and formation flying. Somewhat surprisingly, modeling the trajectory of an object in low Earth orbit is still a challenging task. This is primarily due to the large uncertainty in the upper atmospheric density, about 15-20% (1-sigma) for most thermosphere models. Other contributions come from our inability to precisely model future solar and geomagnetic activities, the potentially unknown shape, material construction and attitude history of the satellite, and intermittent, noisy tracking data. Current methods to predict a satellite's re-entry trajectory typically involve making a single prediction, with the uncertainty dealt with in an ad-hoc manner, usually based on past experience. However, due to the extreme speed of a LEO satellite, even small uncertainties in the re-entry time translate into a very large uncertainty in the location of the re-entry event. Currently, most methods simply update the re-entry estimate on a regular basis. This results in a wide range of estimates that are literally spread over the entire globe. With no understanding of the underlying distribution of potential impact points, the sequence of impact points predicted by the current methodology are largely useless until just a few hours before re-entry. This paper will discuss the development of a set of the High Performance Computing (HPC)-based capabilities to support near real-time quantification of the uncertainty inherent in uncontrolled satellite re-entries. An appropriate management of the uncertainties is essential for a rigorous treatment of the re-entry/LEO trajectory problem. The development of HPC-based tools for re-entry analysis is important as it will allow a rigorous and robust approach to risk assessment by decision makers in an operational setting. Uncertainty quantification results from the recent uncontrolled re-entry of the Phobos-Grunt satellite will be presented and discussed. This work performed under the auspices of the U.S. Department of Energy by Lawrence Livermore National Laboratory under Contract DE-AC52-07NA27344.

Aerodynamics and Aerothermodynamics of undulated re-entry vehicles

NASA Astrophysics Data System (ADS)

Kaushikh, K.; Arunvinthan, S.; Pillai, S. Nadaraja

2018-01-01

Aerodynamic and aerothermodynamic analysis is a fundamental basis for the design of a hypersonic vehicle. In this work, aerodynamic and aerothermodynamic analyses of a blunt body vehicle with undulations on its after-body are studied with the help of numerical simulations. A crew exploration vehicle (CEV) is taken for initial analysis and undulations with varying amplitude and wavelength are introduced on CEV's after-body. Numerical simulations were carried out for CEV and for CEV with undulations at Mach 3.0 and 7.0 for angles of attack ranging from -20° to +20° with increments of +5°. The results show that introduction of undulations did not have a significant impact on mono stability and lift-drag characteristics of the vehicle. It was also observed that introduction of undulations improved the aerothermodynamic characteristics of CEV. A reduction of about 36% in maximum heat flux at Mach 3.0 and about 21% at Mach 7.0 compared to the maximum heat flux for CEV was observed.

Integrated Composite Stiffener Structure (ICoSS) Concept for Planetary Entry Vehicles

NASA Technical Reports Server (NTRS)

Kellas, Sotiris

2016-01-01

Results from the design, manufacturing, and testing of a lightweight Integrated Composite Stiffened Structure (ICoSS) concept, intended for multi-mission planetary entry vehicles are presented. Tests from both component and full-scale tests for a typical Earth Entry Vehicle forward shell manufactured using the ICoSS concept are presented and advantages of the concept for the particular application of passive Earth Entry Vehicles over other structural concepts are discussed.

KSC-2014-3321

NASA Image and Video Library

2014-08-02

SAN DIEGO, Calif. – U.S. Navy personnel in a rigid hull inflatable boat practice with tether lines attached to the Orion boilerplate test vehicle during an evolution of the Underway Recovery Test 2 near the USS Anchorage in the Pacific Ocean off the coast of San Diego. The vehicle is outside of the ship. NASA, Lockheed Martin and the U.S. Navy are conducting the test to prepare for recovery of the Orion crew module on its return from a deep space mission. The underway recovery test will allow the teams to demonstrate and evaluate the recovery processes, procedures, new hardware and personnel in open waters. The Ground Systems Development and Operations Program is conducting the underway recovery test. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of the Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Tony Gray

KSC-2014-3322

NASA Image and Video Library

2014-08-02

SAN DIEGO, Calif. – U.S. Navy personnel in rigid hull inflatable boats practice with tether lines attached to the Orion boilerplate test vehicle during an evolution of the Underway Recovery Test 2 near the USS Anchorage in the Pacific Ocean off the coast of San Diego. The vehicle is outside of the ship. NASA, Lockheed Martin and the U.S. Navy are conducting the test to prepare for recovery of the Orion crew module on its return from a deep space mission. The underway recovery test will allow the teams to demonstrate and evaluate the recovery processes, procedures, new hardware and personnel in open waters. The Ground Systems Development and Operations Program is conducting the underway recovery test. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of the Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit http://www.nasa.gov/orion. Photo credit: U.S. Navy/Specialist 1st Class Gary Keen

KSC-2014-3337

NASA Image and Video Library

2014-08-04

SAN DIEGO, Calif. – Inside the well deck of the USS Anchorage, NASA, Lockheed Martin and U.S. Navy personnel monitor the Orion boilerplate test vehicle as the well deck fills with water. Tending lines have been attached to the test vehicle in preparation for an evolution of Underway Recovery Test 2 in the Pacific Ocean off the coast of San Diego. The test is being conducted to prepare for recovery of the Orion crew module on its return from a deep space mission. The underway recovery test will allow the teams to demonstrate and evaluate the recovery processes, procedures, new hardware and personnel in open waters. The Ground Systems Development and Operations Program is conducting the underway recovery test. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of the Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Kim Shiflett

KSC-2014-3992

NASA Image and Video Library

2014-09-17

SAN DIEGO, Calif. – During the third day of Orion Underway Recovery Test 3 on the USS Anchorage in the Pacific Ocean, two Zodiac boats with U.S. Navy divers aboard, at left, and two rigid hull inflatable boats with Navy and other team personnel aboard, prepare for recovery of the Orion boilerplate test vehicle. NASA, Lockheed Martin and U.S. Navy personnel are conducting recovery tests using the Orion boilerplate test vehicle to prepare for recovery of the Orion crew module on its return from a deep space mission. The test allows the teams to demonstrate and evaluate the recovery processes, procedures, hardware and personnel in open waters. The Ground Systems Development and Operations Program is conducting the underway recovery tests. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion is scheduled to launch in 2014 atop a United Launch Alliance Delta IV Heavy rocket and in 2018 on NASA’s Space Launch System rocket. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Kim Shiflett

KSC-2014-3426

NASA Image and Video Library

2014-08-03

SAN DIEGO, Calif. – The Orion boilerplate test vehicle floats in the Pacific Ocean off the coast of San Diego during a portion of Underway Recovery Test 2. U.S. Navy divers in a Zodiac boat are practicing techniques to attach a lifting sling to the test vehicle. NASA, Lockheed Martin and the U.S. Navy are conducting the test from the USS Anchorage to prepare for recovery of the Orion crew module on its return from a deep space mission. The underway recovery test will allow the team to demonstrate and evaluate the recovery processes, procedures, new hardware and personnel in open waters. The Ground Systems Development and Operations Program is conducting the underway recovery test. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of the Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Kim Shiflett

KSC-2014-3427

NASA Image and Video Library

2014-08-03

SAN DIEGO, Calif. – The Orion boilerplate test vehicle floats in the Pacific Ocean off the coast of San Diego during a portion of Underway Recovery Test 2. U.S. Navy divers in a Zodiac boat are practicing techniques to attach a lifting sling to the test vehicle. NASA, Lockheed Martin and the U.S. Navy are conducting the test from the USS Anchorage to prepare for recovery of the Orion crew module on its return from a deep space mission. The underway recovery test will allow the team to demonstrate and evaluate the recovery processes, procedures, new hardware and personnel in open waters. The Ground Systems Development and Operations Program is conducting the underway recovery test. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of the Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Kim Shiflett

KSC-2014-2500

NASA Image and Video Library

2014-05-11

CAPE CANAVERAL, Fla. – San Diego Padres fans talk to Doug Lenhardt, Kennedy Space Center's Exploration Flight Test-1, or EFT-1, mission integration manager outside Petco Field in San Diego, California. NASA's Orion boilerplate test vehicle is on display. The boilerplate test vehicle is being prepared for an Exploration Flight Test-1, or EFT-1, pre-transportation test. The Ground Systems Development and Operations Program will run the test at the U.S. Naval Base San Diego to simulate retrieval and transportation procedures for Orion after it splashes down in the ocean and is retrieved for return to land and ground transportation back to Kennedy Space Center in Florida. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of the Orion is scheduled to launch later this year atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Kim Shiflett

KSC-2014-2493

NASA Image and Video Library

2014-05-10

CAPE CANAVERAL, Fla. – Doug Lenhardt, Kennedy Space Center's Exploration Flight Test-1, or EFT-1, mission integration manager, and the San Diego Padres mascot wave at the crowds at Petco Field in San Diego, California before the start of the baseball game. The Orion boilerplate test vehicle is on display in the stadium. The boilerplate test vehicle is being prepared for an EFT-1 pre-transportation test. The Ground Systems Development and Operations Program will run the test at the U.S. Naval Base San Diego to simulate retrieval and transportation procedures for Orion after it splashes down in the ocean and is retrieved for return to land and ground transportation back to Kennedy Space Center in Florida. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of the Orion is scheduled to launch later this year atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Kim Shiflett

KSC-2014-3423

NASA Image and Video Library

2014-08-03

SAN DIEGO, Calif. – The Orion boilerplate test vehicle floats in the Pacific Ocean off the coast of San Diego during a portion of Underway Recovery Test 2. Nearby, U.S. Navy personnel in a rigid hull inflatable boat practice with tether lines on the test vehicle. Positioned further out in the ocean are three other rigid hull inflatable boats. NASA, Lockheed Martin and the U.S. Navy are conducting the test to prepare for recovery of the Orion crew module on its return from a deep space mission. The underway recovery test will allow the team to demonstrate and evaluate the recovery processes, procedures, new hardware and personnel in open waters. The Ground Systems Development and Operations Program is conducting the underway recovery test. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of the Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Kim Shiflett

Targeted True Lumen Re-Entry With the Outback Catheter: Accuracy, Success, and Complications in 100 Peripheral Chronic Total Occlusions and Systematic Review of the Literature.

PubMed

Kitrou, Panagiotis; Parthipun, Aneeta; Diamantopoulos, Athanasios; Paraskevopoulos, Ioannis; Karunanithy, Narayan; Katsanos, Konstantinos

2015-08-01

To report a single-center experience with the Outback re-entry device for targeted distal true lumen re-entry during subintimal recanalization of chronic total occlusions (CTOs) and compare the results with a systematic review of the literature. Between February 2011 and July 2013, 104 Outback devices were employed in 91 patients (mean age 64±9 years; 57 men) for subintimal recanalization of 100 vessels with CTOs after initial failure of spontaneous reentry. Fifty-two cases involved a retrograde approach to aortoiliac occlusions and 48 were re-entry attempts in infrainguinal CTOs. Outcome measures included complications and technical success, defined as successful targeted re-entry at the preplanned site of the distal true lumen. To evaluate device accuracy, the re-entry distance (between the point of true vessel reconstitution and the eventual re-entry point) was measured. Outback success was 93% (93/100); only 7 cases failed owing to heavy calcification (5/52 aortoiliac vs 2/48 infrainguinal, p=0.44). Re-entry was highly accurate, with a re-entry distance of ~1 cm in both subgroups (1.2±0.1 cm in aortoiliac vs 1.3±0.1 cm in infrainguinal, p=0.40). There were no major and 17 minor complications (9/52 aortoiliac vs 8/48 infrainguinal, p=0.93). Results are in line with the systematic review that identified 11 studies (only 1 randomized trial) involving mostly the femoropopliteal segment (119 aortoiliac and 464 infrainguinal segments). The pooled Outback success rate was 90% (95% confidence interval 85% to 94%) and the pooled complication rate was 4.3% (95% confidence interval 1.6% to 8.3%). The Outback device is safe and has a very high rate of achieving targeted true lumen re-entry, which minimizes the sacrifice of healthy vessel in the aortoiliac and infrainguinal arteries. © The Author(s) 2015.

Targeting of cytosolic phospholipase A2α impedes cell cycle re-entry of quiescent prostate cancer cells.

PubMed

Yao, Mu; Xie, Chanlu; Kiang, Mei-Yee; Teng, Ying; Harman, David; Tiffen, Jessamy; Wang, Qian; Sved, Paul; Bao, Shisan; Witting, Paul; Holst, Jeff; Dong, Qihan

2015-10-27

Cell cycle re-entry of quiescent cancer cells has been proposed to be involved in cancer progression and recurrence. Cytosolic phospholipase A2α (cPLA2α) is an enzyme that hydrolyzes membrane glycerophospholipids to release arachidonic acid and lysophospholipids that are implicated in cancer cell proliferation. The aim of this study was to determine the role of cPLA2α in cell cycle re-entry of quiescent prostate cancer cells. When PC-3 and LNCaP cells were rendered to a quiescent state, the active form of cPLA2α with a phosphorylation at Ser505 was lower compared to their proliferating state. Conversely, the phospho-cPLA2α levels were resurgent during the induction of cell cycle re-entry. Pharmacological inhibition of cPLA2α with Efipladib upon induction of cell cycle re-entry inhibited the re-entry process, as manifested by refrained DNA synthesis, persistent high proportion of cells in G0/G1 and low percentage of cells in S and G2/M phases, together with a stagnant recovery of Ki-67 expression. Simultaneously, Efipladib prohibited the emergence of Skp2 while maintained p27 at a high level in the nuclear compartment during cell cycle re-entry. Inhibition of cPLA2α also prevented an accumulation of cyclin D1/CDK4, cyclin E/CDK2, phospho-pRb, pre-replicative complex proteins CDC6, MCM7, ORC6 and DNA synthesis-related protein PCNA during induction of cell cycle re-entry. Moreover, a pre-treatment of the prostate cancer cells with Efipladib during induction of cell cycle re-entry subsequently compromised their tumorigenic capacity in vivo. Hence, cPLA2α plays an important role in cell cycle re-entry by quiescent prostate cancer cells.

KSC-2014-4096

NASA Image and Video Library

2014-09-17

SAN DIEGO, Calif. – The Orion boilerplate test vehicle floats in the Pacific Ocean, a distance away from the USS Anchorage, during the third day of Orion Underway Recovery Test 3. Orange stabilizers on the top of the test vehicle were inflated to simulate the system that will be used to upright Orion in the water after splashdown. U.S. Navy divers in a Zodiac boat, at right, and other team members in a rigid hull inflatable boat prepare the test vehicle for return to the well deck of the ship. NASA, Lockheed Martin and U.S. Navy personnel are conducting the recovery test using the test vehicle to prepare for recovery of the Orion crew module on its return from a deep space mission. The test allows the teams to demonstrate and evaluate the recovery processes, procedures, hardware and personnel in open waters. The Ground Systems Development and Operations Program is conducting the underway recovery tests. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion is scheduled to launch in 2014 atop a United Launch Alliance Delta IV Heavy rocket and in 2018 on NASA’s Space Launch System rocket. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Cory Huston

Limitations of the Outback LTD re-entry device in femoropopliteal chronic total occlusions.

PubMed

Shin, Susanna H; Baril, Donald; Chaer, Rabih; Rhee, Robert; Makaroun, Michel; Marone, Luke

2011-05-01

Subintimal recanalization for the treatment of femoropopliteal chronic total occlusions (CTO) occasionally requires re-entry devices to access the true lumen distally, but limited information is available on factors predicting the success or failure of these devices. We evaluated the Outback LTD re-entry device (LuMend, Redwood City, Calif; acquired by Cordis Corp, Miami Lakes, Fla). A retrospective review of patients with femoropopliteal CTO from August 2006 to August 2009 was performed. Age, gender, occlusion length, site of re-entry, and the angle of the aortic bifurcation were recorded. Procedural angiograms were used to assign a calcification score (none, mild, moderate, severe) at the re-entry site. Univariate and multivariate logistic regression analyses were used to identify factors predicting failure of re-entry into the true lumen. Of 249 CTOs treated, the re-entry device was used 52 times (20.9%): 47 superficial femoral artery (SFA) occlusions and 5 combined SFA and popliteal artery occlusions (33 TransAtlantic InterSociety Consensus II type C and 18 type D lesions). Of 48 procedures with available angiograms for review, the target re-entry site was at the adductor canal in 30 (62.5%), the above-knee popliteal artery in 13 (27.1%), behind the knee joint in 4 (8.3%), and the mid-SFA in 2 (4.2%). Patients (54% men) were a mean age of 73.1 years. Re-entry was successful in 34 attempts (64.5%). Causes of failure included inability to re-enter the true lumen in 11 (61.1%), difficulty tracking the device over a wire in 3 (16.7%), acute angle of aortic bifurcation in 2 (11.1%), mechanical failure of the device in 1 (5.6%), and difficulty tracking the device through the lesion in 1 (5.6%). Moderate or severe calcification at the site of re-entry was the only significant predictor of failure (odds ratio, 6.3; 95% confidence interval, 1.45-24.48; P = .01). An aortic bifurcation angle ≥40° did trend toward predicting success (odds ratio, 0.23; 95% confidence interval, 0.05-1.02; P = .054). Although the Outback re-entry device can be successful in extending the applicability of endovascular management to difficult femoropopliteal occlusions, it is not uniformly successful in current clinical practice. Significant calcification at the proposed re-entry site is a strong predictor of failure. Copyright © 2011 Society for Vascular Surgery. Published by Mosby, Inc. All rights reserved.

Parametric Study of Biconic Re-Entry Vehicles

NASA Technical Reports Server (NTRS)

Steele, Bryan; Banks, Daniel W.; Whitmore, Stephen A.

2007-01-01

An optimization based on hypersonic aerodynamic performance and volumetric efficiency was accomplished for a range of biconic configurations. Both axisymmetric and quasi-axisymmetric geometries (bent and flattened) were analyzed. The aerodynamic optimization wag based on hypersonic simple Incidence angle analysis tools. The range of configurations included those suitable for r lunar return trajectory with a lifting aerocapture at Earth and an overall volume that could support a nominal crew. The results yielded five configurations that had acceptable aerodynamic performance and met overall geometry and size limitations

HTV3 Approach

NASA Image and Video Library

2012-07-27

ISS032-E-010428 (27 July 2012) --- The unpiloted Japan Aerospace Exploration Agency (JAXA) H-II Transfer Vehicle (HTV-3) approaches the International Space Station. The Japan Aerospace Exploration Agency launched HTV-3 aboard an H-IIB launch vehicle from the Tanegashima Space Center in southern Japan at 10:06 p.m. EDT July 20 (11:06 a.m. July 21, Japan time). The HTV is bringing 7,000 pounds of cargo including food and clothing for the crew members, an aquatic habitat experiment, a remote-controlled Earth-observation camera for environmental studies, a catalytic reactor for the station’s water regeneration system and a Japanese cooling water recirculation pump. The vehicle will remain at the space station until Sept. 6 when, like its predecessors, it will be detached from the Harmony node by Canadarm2 and released for a fiery re-entry over the Pacific Ocean.

HTV-3 Approach

NASA Image and Video Library

2012-07-27

ISS032-E-009997 (27 July 2012) --- The unpiloted Japan Aerospace Exploration Agency (JAXA) H-II Transfer Vehicle (HTV-3) approaches the International Space Station. The Japan Aerospace Exploration Agency launched HTV-3 aboard an H-IIB launch vehicle from the Tanegashima Space Center in southern Japan at 10:06 p.m. EDT July 20 (11:06 a.m. July 21, Japan time). The HTV is bringing 7,000 pounds of cargo including food and clothing for the crew members, an aquatic habitat experiment, a remote-controlled Earth-observation camera for environmental studies, a catalytic reactor for the station?s water regeneration system and a Japanese cooling water recirculation pump. The vehicle will remain at the space station until Sept. 6 when, like its predecessors, it will be detached from the Harmony node by Canadarm2 and released for a fiery re-entry over the Pacific Ocean.

HTV-3 Approach

NASA Image and Video Library

2012-07-27

ISS032-E-010006 (27 July 2012) --- The unpiloted Japan Aerospace Exploration Agency (JAXA) H-II Transfer Vehicle (HTV-3) approaches the International Space Station. The Japan Aerospace Exploration Agency launched HTV-3 aboard an H-IIB launch vehicle from the Tanegashima Space Center in southern Japan at 10:06 p.m. EDT July 20 (11:06 a.m. July 21, Japan time). The HTV is bringing 7,000 pounds of cargo including food and clothing for the crew members, an aquatic habitat experiment, a remote-controlled Earth-observation camera for environmental studies, a catalytic reactor for the station?s water regeneration system and a Japanese cooling water recirculation pump. The vehicle will remain at the space station until Sept. 6 when, like its predecessors, it will be detached from the Harmony node by Canadarm2 and released for a fiery re-entry over the Pacific Ocean.

HTV3 Approach

NASA Image and Video Library

2012-07-27

ISS032-E-010819 (27 July 2012) --- The unpiloted Japan Aerospace Exploration Agency (JAXA) H-II Transfer Vehicle (HTV-3) approaches the International Space Station. The Japan Aerospace Exploration Agency launched HTV-3 aboard an H-IIB launch vehicle from the Tanegashima Space Center in southern Japan at 10:06 p.m. EDT July 20 (11:06 a.m. July 21, Japan time). The HTV is bringing 7,000 pounds of cargo including food and clothing for the crew members, an aquatic habitat experiment, a remote-controlled Earth-observation camera for environmental studies, a catalytic reactor for the station’s water regeneration system and a Japanese cooling water recirculation pump. The vehicle will remain at the space station until Sept. 6 when, like its predecessors, it will be detached from the Harmony node by Canadarm2 and released for a fiery re-entry over the Pacific Ocean.

HTV3 Approach

NASA Image and Video Library

2012-07-27

ISS032-E-010399 (27 July 2012) --- The unpiloted Japan Aerospace Exploration Agency (JAXA) H-II Transfer Vehicle (HTV-3) approaches the International Space Station. The Japan Aerospace Exploration Agency launched HTV-3 aboard an H-IIB launch vehicle from the Tanegashima Space Center in southern Japan at 10:06 p.m. EDT July 20 (11:06 a.m. July 21, Japan time). The HTV is bringing 7,000 pounds of cargo including food and clothing for the crew members, an aquatic habitat experiment, a remote-controlled Earth-observation camera for environmental studies, a catalytic reactor for the station’s water regeneration system and a Japanese cooling water recirculation pump. The vehicle will remain at the space station until Sept. 6 when, like its predecessors, it will be detached from the Harmony node by Canadarm2 and released for a fiery re-entry over the Pacific Ocean.

HTV3 Approach

NASA Image and Video Library

2012-07-27

ISS032-E-010386 (27 July 2012) --- The unpiloted Japan Aerospace Exploration Agency (JAXA) H-II Transfer Vehicle (HTV-3) approaches the International Space Station. The Japan Aerospace Exploration Agency launched HTV-3 aboard an H-IIB launch vehicle from the Tanegashima Space Center in southern Japan at 10:06 p.m. EDT July 20 (11:06 a.m. July 21, Japan time). The HTV is bringing 7,000 pounds of cargo including food and clothing for the crew members, an aquatic habitat experiment, a remote-controlled Earth-observation camera for environmental studies, a catalytic reactor for the station’s water regeneration system and a Japanese cooling water recirculation pump. The vehicle will remain at the space station until Sept. 6 when, like its predecessors, it will be detached from the Harmony node by Canadarm2 and released for a fiery re-entry over the Pacific Ocean.

HTV-3 Approach

NASA Image and Video Library

2012-07-27

ISS032-E-010005 (27 July 2012) --- The unpiloted Japan Aerospace Exploration Agency (JAXA) H-II Transfer Vehicle (HTV-3) approaches the International Space Station. The Japan Aerospace Exploration Agency launched HTV-3 aboard an H-IIB launch vehicle from the Tanegashima Space Center in southern Japan at 10:06 p.m. EDT July 20 (11:06 a.m. July 21, Japan time). The HTV is bringing 7,000 pounds of cargo including food and clothing for the crew members, an aquatic habitat experiment, a remote-controlled Earth-observation camera for environmental studies, a catalytic reactor for the station?s water regeneration system and a Japanese cooling water recirculation pump. The vehicle will remain at the space station until Sept. 6 when, like its predecessors, it will be detached from the Harmony node by Canadarm2 and released for a fiery re-entry over the Pacific Ocean.

HTV3 Approach

NASA Image and Video Library

2012-07-27

ISS032-E-010392 (27 July 2012) --- The unpiloted Japan Aerospace Exploration Agency (JAXA) H-II Transfer Vehicle (HTV-3) approaches the International Space Station. The Japan Aerospace Exploration Agency launched HTV-3 aboard an H-IIB launch vehicle from the Tanegashima Space Center in southern Japan at 10:06 p.m. EDT July 20 (11:06 a.m. July 21, Japan time). The HTV is bringing 7,000 pounds of cargo including food and clothing for the crew members, an aquatic habitat experiment, a remote-controlled Earth-observation camera for environmental studies, a catalytic reactor for the station’s water regeneration system and a Japanese cooling water recirculation pump. The vehicle will remain at the space station until Sept. 6 when, like its predecessors, it will be detached from the Harmony node by Canadarm2 and released for a fiery re-entry over the Pacific Ocean.

HTV3 Approach

NASA Image and Video Library

2012-07-27

ISS032-E-010758 (27 July 2012) --- The unpiloted Japan Aerospace Exploration Agency (JAXA) H-II Transfer Vehicle (HTV-3) approaches the International Space Station. The Japan Aerospace Exploration Agency launched HTV-3 aboard an H-IIB launch vehicle from the Tanegashima Space Center in southern Japan at 10:06 p.m. EDT July 20 (11:06 a.m. July 21, Japan time). The HTV is bringing 7,000 pounds of cargo including food and clothing for the crew members, an aquatic habitat experiment, a remote-controlled Earth-observation camera for environmental studies, a catalytic reactor for the station’s water regeneration system and a Japanese cooling water recirculation pump. The vehicle will remain at the space station until Sept. 6 when, like its predecessors, it will be detached from the Harmony node by Canadarm2 and released for a fiery re-entry over the Pacific Ocean.

KSC-2013-3728

NASA Image and Video Library

2013-10-22

CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, technicians monitor the progress as the Orion ground test vehicle, or GTA, is lowered by crane toward a mockup of the service module in high bay 4 of the Vehicle Assembly Building. The ground test vehicle is being used for path finding operations, including simulated manufacturing, assembly and stacking procedures. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Dimitri Gerondidakis

KSC-2013-3727

NASA Image and Video Library

2013-10-22

CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, technicians monitor the progress as the Orion ground test vehicle, or GTA, is being lowered by crane toward a mockup of the service module in high bay 4 of the Vehicle Assembly Building. The ground test vehicle is being used for path finding operations, including simulated manufacturing, assembly and stacking procedures. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Dimitri Gerondidakis

KSC-2013-3723

NASA Image and Video Library

2013-10-22

CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, the Orion ground test vehicle, or GTA, has been lifted high in the air by crane in the transfer aisle of the Vehicle Assembly Building and is being lowered into high bay 4. The ground test vehicle is being used for path finding operations, including simulated manufacturing, assembly and stacking procedures. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Dimitri Gerondidakis

Thermochemical Modeling of Nonequilibrium Oxygen Flows

NASA Astrophysics Data System (ADS)

Neitzel, Kevin Joseph

The development of hypersonic vehicles leans heavily on computational simulation due to the high enthalpy flow conditions that are expensive and technically challenging to replicate experimentally. The accuracy of the nonequilibrium modeling in the computer simulations dictates the design margin that is required for the thermal protection system and flight dynamics. Previous hypersonic vehicles, such as Apollo and the Space Shuttle, were primarily concerned with re-entry TPS design. The strong flow conditions of re-entry, involving Mach numbers of 25, quickly dissociate the oxygen molecules in air. Sustained flight, hypersonic vehicles will be designed to operate in Mach number ranges of 5 to 10. The oxygen molecules will not quickly dissociate and will play an important role in the flow field behavior. The development of nonequilibrium models of oxygen is crucial for limiting modeling uncertainty. Thermochemical nonequilibrium modeling is investigated for oxygen flows. Specifically, the vibrational relaxation and dissociation behavior that dominate the nonequilibrium physics in this flight regime are studied in detail. The widely used two-temperature (2T) approach is compared to the higher fidelity and more computationally expensive state-to-state (STS) approach. This dissertation utilizes a wide range of rate sources, including newly available STS rates, to conduct a comprehensive study of modeling approaches for hypersonic nonequilibrium thermochemical modeling. Additionally, the physical accuracy of the computational methods are assessed by comparing the numerical results with available experimental data. The numerical results and experimental measurements present strong nonequilibrium, and even non-Boltzmann behavior in the vibrational energy mode for the sustained hypersonic flight regime. The STS approach is able to better capture the behavior observed in the experimental data, especially for stronger nonequilibrium conditions. Additionally, a reduced order model (ROM) modification to the 2T model is developed to improve the capability of the 2T approach framework.

Canal switch and re-entry phenomenon in benign paroxysmal positional vertigo: difference between immediate and delayed occurrence.

PubMed

Dispenza, F; DE Stefano, A; Costantino, C; Rando, D; Giglione, M; Stagno, R; Bennici, E

2015-04-01

This prospective study was designed to evaluate the differences between immediate and delayed canal re-entry of otoliths after therapeutic manoeuvres in patients with benign paroxysmal positional vertigo (BPPV). A total of 196 patients with BPPV were visited and 127 matched our inclusion criteria. The mean age was 54.74 years. The horizontal semicircular canal (HSC) was involved in 30 cases and the posterior semicircular canal (PSC) in 97 patients. Patients with hearing loss in the ear affected by BPPV have a more recurrent form, compared to those with normal hearing. An immediate canal re-entry was recorded in 3 patients with HSC BPPV, all with geotropic nystagmus. In 7 patients with PSC BPPV, the immediate canal re-entry was detected and the delayed form was noted in 5 patients. The patients with the delayed canal re-entry underwent more than 2 previous manoeuvres. The canal re-entry was not related to the manoeuvre performed. The timing of the Dix-Hallpike test to verify the resolution of the BPPV had a significant role in immediate canal re-entry. A recurrence in the follow-up at least one month after treatment was recorded in 20 patients and was more frequent in patients that had canal re-entry. The canal re-entry or canal switch is a clinical entity that should be kept in mind of the neurotologist when approaching BPPV patients. It is important to distinguish it from recurrence when delayed and from manoeuvre failure when immediate. The timing of manoeuvre performing, in particular the final verification test after therapeutic sessions, is important to prevent the immediate reflux of particles into canals.

Factors associated with a second deferral among donors eligible for re-entry after a false-positive screening test for syphilis, HCV, HBV and HIV.

PubMed

Grégoire, Y; Germain, M; Delage, G

2018-05-01

Since 25 May 2010, all donors at our blood centre who tested false-positive for HIV, HBV, HCV or syphilis are eligible for re-entry after further testing. Donors who have a second false-positive screening test, either during qualification for or after re-entry, are deferred for life. This study reports on factors associated with the occurrence of such deferrals. Rates of second false-positive results were compared by year of deferral, transmissible disease marker, gender, age, donor status (new or repeat) and testing platform (same or different) both at qualification for re-entry and afterwards. Chi-square tests were used to compare proportions. Cox regression was used for multivariate analyses. Participation rates in the re-entry programme were 42·1%: 25·6% failed to qualify for re-entry [different platform: 2·7%; same platform: 42·9% (P < 0·0001)]. After re-entry, rates of deferral for second false-positive results were 8·4% after 3 years [different platform: 1·8%; same platform: 21·4% (P < 0·0001)]. Deferral rates were higher for HIV and HCV than for HBV at qualification when tested on the same platform. The risk, when analysed by multivariate analyses, of a second deferral for a false-positive result, both at qualification and 3 years after re-entry, was lower for donors deferred on a different platform; this risk was higher for HIV, HCV and syphilis than for HBV and for new donors if tested on the same platform. Re-entry is more often successful when donors are tested on a testing platform different from the one on which they obtained their first false-positive result. © 2018 International Society of Blood Transfusion.

Numerical Flight Mechanics Analysis Of The SHEFEX I Ascent And Re-Entry Phases

NASA Astrophysics Data System (ADS)

Bartolome Calvo, Javier; Eggers, Thino

2011-08-01

The SHarp Edge Flight EXperiment (SHEFEX) I provides a huge amount of scientific data to validate numerical tools in hypersonic flows. These data allow the direct comparison of flight measurements with the current numerical tools available at DLR. Therefore, this paper is devoted to apply a recently developed direct coupling between aerodynamics and flight dynamics to the SHEFEX I flight. In a first step, mission analyses are carried out using the trajectory optimization program REENT 6D coupled to missile DATCOM. In a second step, the direct coupling between the trajectory program and the DLR TAU code, in which the unsteady Euler equations including rigid body motion are solved, is applied to analyze some interesting parts of ascent and re-entry phases of the flight experiment. The agreement of the numerical predictions with the obtained flight data is satisfactory assuming a variable fin deflection angle.

Ablative Heat Shield Studies for NASA Mars/Earth Return Entry Vehicles

DTIC Science & Technology

1990-09-01

RETURN ENTRY VEHICLES by Michael K. Hamm September, 1990 NASA Thesis Advisor: William D. Henline Thesis Co-Advisor: Max F. Platzer Approved for public...STUDIES FOR NASA MARS/EARTH RETURN ENTRY VEHICLES (UNCLASSIFIED) 12. PERSONAL AUTHOR(S) Harm, Michael, K. 13a TYPE OF REPORT 13b TIME COVERED 14 DATE OF...theoretical values. The tests were performed to ascertain if RSI type materials could be used for entry vehicles proposed in NASA Mars missions. 20

Project PRIME. Interim Report Year One 1971-1972 (Purpose and Procedures).

ERIC Educational Resources Information Center

Kaufman, Martin J.; And Others

Project PRIME (Programmed Re-Entry Into Mainstream Education) is concerned with evaluating the effectiveness of programs that aim at integration of handicapped children into regular classrooms. The main goals of the project are to determine which handicapped children can benefit from integration and under which conditions would it prove the most…

Coming Home: Continuing Intercultural Learning during the Re-Entry Semester Following a Study Abroad Experience

ERIC Educational Resources Information Center

Marx, Helen A.; Moss, David M.

2015-01-01

International experiences through structured study abroad programs are proposed as a powerful way to impact pre-service teachers' intercultural understandings and competence. In recent years attention has been placed on the nature of such study abroad programs, seeking to illuminate design elements that might enhance intercultural learning prior…

An Assessment of a Community College Reentry Program for Women.

ERIC Educational Resources Information Center

Forrest, Joy Davis

In 1980, a study was conducted to determine the characteristics, attitudes, and subsequent experiences of women who had completed the Women's Education Development Incentive (WENDI) re-entry program at Brevard Community College, Florida, in 1977. From the original mailing of 79 questionnaires, 33 usable responses were returned. Two-thirds of the…

KSC-2014-3449

NASA Image and Video Library

2014-08-10

LOS ANGELES, Calif. – Andy Quiett, Detachment 3 deputy operations lead for the Orion program and DoD liaison for NASA, answers questions about the Orion boilerplate test vehicle from visitors touring the well deck of the USS Anchorage during the Science, Technology, Engineering and Mathematics, or STEM, Expo for L.A. Navy Days at the Port of Los Angeles in California. A combined team from NASA’s Ground Systems Development and Operations Program and the U.S. Navy were in San Diego to practice recovering Orion from the ocean, as they will do in December following the spacecraft's first trip to space during Exploration Flight Test-1. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep-space return velocities. The first unpiloted test flight of the Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Kim Shiflett

KSC-2014-3448

NASA Image and Video Library

2014-08-10

LOS ANGELES, Calif. – Andy Quiett, Detachment 3 deputy operations lead for the Orion program and DoD liaison for NASA, answers questions about the Orion boilerplate test vehicle from visitors touring the well deck of the USS Anchorage during the Science, Technology, Engineering and Mathematics, or STEM, Expo for L.A. Navy Days at the Port of Los Angeles in California. A combined team from NASA’s Ground Systems Development and Operations Program and the U.S. Navy were in San Diego to practice recovering Orion from the ocean, as they will do in December following the spacecraft's first trip to space during Exploration Flight Test-1. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep-space return velocities. The first unpiloted test flight of the Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Kim Shiflett

KSC-2014-3447

NASA Image and Video Library

2014-08-10

LOS ANGELES, Calif. – Andy Quiett, Detachment 3 deputy operations lead for the Orion program and DoD liaison for NASA, answers questions about the Orion boilerplate test vehicle from visitors touring the well deck of the USS Anchorage during the Science, Technology, Engineering and Mathematics, or STEM, Expo for L.A. Navy Days at the Port of Los Angeles in California. A combined team from NASA’s Ground Systems Development and Operations Program and the U.S. Navy were in San Diego to practice recovering Orion from the ocean, as they will do in December following the spacecraft's first trip to space during Exploration Flight Test-1. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep-space return velocities. The first unpiloted test flight of the Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Kim Shiflett

Simulation and experimental research on trans-media vehicle water-entry motion characteristics at low speed

PubMed Central

Yang, Jian; Feng, Jinfu; Hu, Junhua; Liu, An

2017-01-01

The motion characteristics of trans-media vehicles during the water-entry process were explored in this study in an effort to obtain the optimal water-entry condition of the vehicle for developing a novel, single control strategy integrating underwater non-control and in-air control. A water-entry dynamics model is established by combining the water-entry motion characteristics of the vehicle in uncontrolled conditions at low speed with time-varying parameters (e.g. buoyancy, added mass). A water-entry experiment is designed to confirm the effectiveness of the established model. After that, by comparing the experimental results with the simulated results, the model is further modified to more accurately reflect water-entry motion. The change laws of the vehicle’s attitude and position during the water-entry process are also obtained by analyzing the simulation of the modified model under different velocity, angle, and angle of attack conditions. The results presented here have guiding significance for the future realization of reaching the stable underwater navigation state of the vehicle after water-entry process. PMID:28558012

Trajectory Design and Control for the Compton Gamma Ray Observatory Re-Entry

NASA Technical Reports Server (NTRS)

Hoge, Susan; Vaughn, Frank; Bauer, Frank H. (Technical Monitor)

2000-01-01

The Compton Gamma Ray Observatory (CGRO) controlled re-entry operation was successfully conducted in June of 2000. The surviving parts of the spacecraft landed in the Pacific Ocean within the predicted footprint. The design of the maneuvers to control the trajectory to accomplish this re-entry presented several challenges. These challenges included timing and duration of the maneuvers, fuel management, post maneuver position knowledge, collision avoidance with other spacecraft, accounting for the break-up of the spacecraft into several pieces with a wide range of ballistic coefficients, and ensuring that the impact footprint would remain within the desired landing area in the event of contingencies. This paper presents the initial re-entry trajectory design and the evolution of the design into the maneuver sequence used for the re-entry. The paper discusses the constraints on the trajectory design, the modifications made to the initial design and the reasons behind these modifications. Data from the re-entry operation are presented.

Factors associated with re-entry to out-of-home care among children in England.

PubMed

Mc Grath-Lone, Louise; Dearden, Lorraine; Harron, Katie; Nasim, Bilal; Gilbert, Ruth

2017-01-01

Exiting and re-entering out-of-home care (OHC) is considered a disruption to permanence which may have long-lasting, negative consequences for children due to a lack of stability and continuity. Each year approximately one-third of children in OHC in England exit, but information is lacking on rates of re-entries and associated factors. Using national administrative data, we calculated rates of re-entry among children exiting OHC from 2007 to 2012, identified key child and care factors associated with re-entry using Cox proportional hazards modelling, and developed a simple probability calculator to estimate which groups of children are most likely to re-enter OHC within three months. Between 2007 and 2012 re-entries to OHC in England decreased (from 23.3% to 14.4% within one year of exit, p<0.001), possibly due to concurrent changes in the way children exited OHC. Overall, more than one-third of children exiting OHC in 2008 re-entered within five years (35.3%, N=4076), but rates of re-entry varied by child and care characteristics including age, ethnicity, mode of exit, and placement stability. Based on these associated factors, we developed a calculator that can estimate the likelihood of rapid re-entry to OHC for a group of children and could be used by social care practitioners or service planners. Our findings provide insight into which groups of children are most likely to re-enter OHC, who may benefit from additional support or ongoing monitoring. Copyright © 2016 The Authors. Published by Elsevier Ltd.. All rights reserved.

Vulnerability to re-entry in simulated two-dimensional cardiac tissue: effects of electrical restitution and stimulation sequence.

PubMed

Tran, Diana X; Yang, Ming-Jim; Weiss, James N; Garfinkel, Alan; Qu, Zhilin

2007-12-01

Ventricular fibrillation is a lethal arrhythmia characterized by multiple wavelets usually starting from a single or figure-of-eight re-entrant circuit. Understanding the factors regulating vulnerability to the re-entry is essential for developing effective therapeutic strategies to prevent ventricular fibrillation. In this study, we investigated how pre-existing tissue heterogeneities and electrical restitution properties affect the initiation of re-entry by premature extrastimuli in two-dimensional cardiac tissue models. We studied two pacing protocols for inducing re-entry following the "sinus" rhythm (S1) beat: (1) a single premature (S2) extrastimulus in heterogeneous tissue; (2) two premature extrastimuli (S2 and S3) in homogeneous tissue. In the first case, the vulnerable window of re-entry is determined by the spatial dimension and extent of the heterogeneity, and is also affected by electrical restitution properties and the location of the premature stimulus. The vulnerable window first increases as the action potential duration (APD) difference between the inside and outside of the heterogeneous region increases, but then decreases as this difference increases further. Steeper APD restitution reduces the vulnerable window of re-entry. In the second case, electrical restitution plays an essential role. When APD restitution is flat, no re-entry can be induced. When APD restitution is steep, re-entry can be induced by an S3 over a range of S1S2 intervals, which is also affected by conduction velocity restitution. When APD restitution is even steeper, the vulnerable window is reduced due to collision of the spiral tips.

KSC-2014-3883

NASA Image and Video Library

2014-09-14

SAN DIEGO, Calif. – The Orion boilerplate test vehicle floats in the Pacific Ocean during Underway Recovery Test 4A. Orion was lowered into the water with a stationary crane from the USS Salvor, a safeguard-class rescue and salvage ship. Nearby, U.S. Navy personnel in a Zodiac boat, left, and a rigid hull inflatable boat practice procedures to tether and retrieve the test vehicle. U.S. Navy divers are standing on the flotation collar that has been placed around the test vehicle. NASA, Lockheed Martin and the U.S. Navy are conducting crane recovery tests to prepare for recovery of the Orion crew module on its return from a deep space mission. The underway recovery test will allow the teams to demonstrate and evaluate the recovery processes, procedures, new hardware and personnel in open waters. The Ground Systems Development and Operations Program is conducting the underway recovery test. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of the Orion is scheduled to launch in December 2014 atop a United Launch Alliance Delta IV Heavy rocket and in 2018 on NASA’s Space Launch System rocket. For more information, visit http://www.nasa.gov/orion. Photo credit: Kim Shiflett

76 FR 58197 - Pre-Release Community Confinement

Federal Register 2010, 2011, 2012, 2013, 2014

2011-09-20

... for pre-release RRC [Residential Re- entry Centers] placement pursuant to 28 CFR 570.20-22 until such.... For clarity, we also add a parenthetical that explains that the Bureau includes residential re-entry... (including residential re-entry centers); and participation in gainful employment, employment search efforts...

HSV-1 infection of human corneal epithelial cells: receptor-mediated entry and trends of re-infection.

PubMed

Shah, Arpeet; Farooq, Asim V; Tiwari, Vaibhav; Kim, Min-Jung; Shukla, Deepak

2010-11-20

The human cornea is a primary target for herpes simplex virus-1 (HSV-1) infection. The goals of the study were to determine the cellular modalities of HSV-1 entry into human corneal epithelial (HCE) cells. Specific features of the study included identifying major entry receptors, assessing pH dependency, and determining trends of re-infection. A recombinant HSV-1 virus expressing beta-galactosidase was used to ascertain HSV-1 entry into HCE cells. Viral replication within cells was confirmed using a time point plaque assay. Lysosomotropic agents were used to test for pH dependency of entry. Flow cytometry and immunocytochemistry were used to determine expression of three cellular receptors--nectin-1, herpesvirus entry mediator (HVEM), and paired immunoglobulin-like 2 receptor alpha (PILR-a). The necessity of these receptors for viral entry was tested using antibody-blocking. Finally, trends of re-infection were investigated using viral entry assay and flow cytometry post-primary infection. Cultured HCE cells showed high susceptibility to HSV-1 entry and replication. Entry was demonstrated to be pH dependent as blocking vesicular acidification decreased entry. Entry receptors expressed on the cell membrane include nectin-1, HVEM, and PILR-α. Receptor-specific antibodies blocked entry receptors, reduced viral entry and indicated nectin-1 as the primary receptor used for entry. Cells re-infected with HSV-1 showed a decrease in entry, which was correlated to decreased levels of nectin-1 as demonstrated by flow cytometry. HSV-1 is capable of developing an infection in HCE cells using a pH dependent entry process that involves primarily nectin-1 but also the HVEM and PILR-α receptors. Re-infected cells show decreased levels of entry, correlated with a decreased level of nectin-1 receptor expression.

Re-Entry: Managing Cross-Cultural Transitions.

ERIC Educational Resources Information Center

Adler, Nancy J.

1981-01-01

Studied the re-entry process of corporate and governmental employees (N=200) returning to Canada after working overseas. Research found re-entry into the original culture was a more difficult transition than moving to the foreign culture. Home-country managers tended to exhibit xenophobia in assessing the potential and actual effectiveness of…

Preparing International Students for the Re-Entry Transition.

ERIC Educational Resources Information Center

Arthur, Nancy

2003-01-01

Counselors play an integral role in assisting international students to manage cross-cultural transitions. Re-entry counseling can support international students to examine their transition experiences, provide education about re-entry, and help to develop anticipatory coping strategies. An example of a workshop is described as a method of…

Locking Nut with Stress-Distributing Insert

NASA Technical Reports Server (NTRS)

Daniels, Christopher C.

2010-01-01

Reusable holders have been devised for evaluating high-temperature, plasma-resistant re-entry materials, especially fabrics. Typical material samples tested support thermal-protection-system damage repair requiring evaluation prior to re-entry into terrestrial atmosphere. These tests allow evaluation of each material to withstand the most severe predicted re-entry conditions.

A Method for Semi-quantitative Assessment of Exposure to Pesticides of Applicators and Re-entry Workers: An Application in Three Farming Systems in Ethiopia.

PubMed

Negatu, Beyene; Vermeulen, Roel; Mekonnen, Yalemtshay; Kromhout, Hans

2016-07-01

To develop an inexpensive and easily adaptable semi-quantitative exposure assessment method to characterize exposure to pesticide in applicators and re-entry farmers and farm workers in Ethiopia. Two specific semi-quantitative exposure algorithms for pesticides applicators and re-entry workers were developed and applied to 601 farm workers employed in 3 distinctly different farming systems [small-scale irrigated, large-scale greenhouses (LSGH), and large-scale open (LSO)] in Ethiopia. The algorithm for applicators was based on exposure-modifying factors including application methods, farm layout (open or closed), pesticide mixing conditions, cleaning of spraying equipment, intensity of pesticide application per day, utilization of personal protective equipment (PPE), personal hygienic behavior, annual frequency of application, and duration of employment at the farm. The algorithm for re-entry work was based on an expert-based re-entry exposure intensity score, utilization of PPE, personal hygienic behavior, annual frequency of re-entry work, and duration of employment at the farm. The algorithms allowed estimation of daily, annual and cumulative lifetime exposure for applicators, and re-entry workers by farming system, by gender, and by age group. For all metrics, highest exposures occurred in LSGH for both applicators and female re-entry workers. For male re-entry workers, highest cumulative exposure occurred in LSO farms. Female re-entry workers appeared to be higher exposed on a daily or annual basis than male re-entry workers, but their cumulative exposures were similar due to the fact that on average males had longer tenure. Factors related to intensity of exposure (like application method and farm layout) were indicated as the main driving factors for estimated potential exposure. Use of personal protection, hygienic behavior, and duration of employment in surveyed farm workers contributed less to the contrast in exposure estimates. This study indicated that farmers' and farm workers' exposure to pesticides can be inexpensively characterized, ranked, and classified. Our method could be extended to assess exposure to specific active ingredients provided that detailed information on pesticides used is available. The resulting exposure estimates will consequently be used in occupational epidemiology studies in Ethiopia and other similar countries with few resources. © The Author 2016. Published by Oxford University Press on behalf of the British Occupational Hygiene Society.

Project EGRESS: The design of an assured crew return vehicle for the space station

NASA Technical Reports Server (NTRS)

1990-01-01

Keeping preliminary studies by NASA in mind, an Assured Crew Return Vehicle (ACRV) was developed. The system allows the escape of one or more crew members from Space Station Freedom in case of emergency. The design of the vehicle addresses propulsion, orbital operations, reentry, landing and recovery, power and communication, and life support. In light of recent modifications in Space Station design, Project EGRESS (Earthbound Guaranteed ReEntry from Space Station) pays particular attention to its impact on Space Station operations, interfaces and docking facilities, and maintenance needs. A water landing, medium lift vehicle was found to best satisfy project goals of simplicity and cost efficiency without sacrificing the safety and reliability requirements. With a single vehicle, one injured crew member could be returned to Earth with minimal pilot involvement. Since the craft is capable of returning up to five crew members, two such permanently docked vehicles would allow full evacuation of the Space Station. The craft could be constructed entirely with available 1990 technology and launched aboard a shuttle orbiter.

Alternative Fuels Data Center

Science.gov Websites

Advanced Technology Vehicle (ATV) and Alternative Fuel Infrastructure Manufacturing Incentives Through the Advanced Technology Vehicles Manufacturing Loan Program, manufacturers may be eligible for direct loans for up to 30% of the cost of re-equipping, expanding, or establishing manufacturing

Hyperspectral imager for components identification in the atmosphere

NASA Astrophysics Data System (ADS)

Dewandel, Jean-Luc; Beghuin, Didier; Dubois, Xavier; Antoine, Philippe

2017-11-01

Several applications require the identification of chemical elements during re-entry of material in the atmosphere. The materials can be from human origin or meteorites. The Automated Transfer Vehicle (ATV) re-entry has been filmed with conventional camera from airborne manual operation. In order to permit the identification of the separate elements from their glow, spectral analysis needs to be added to the video data. In a LET-SME contract with ESA, Lambda-X has built a Fourier Transform Imaging Spectrometer to permit, in a future work, to bring the technology to the readiness level required for the application. In this paper, the principles of the Fourier Transform Imaging spectroscopy are recalled, the different interferometers suitable for supporting the technique are reviewed and the selection process is explained. The final selection of the interferometer corresponds to a birefringent prism based common path shear interferometer. The design of the breadboard and its performances are presented in terms of spatial resolution, aperture, and spectral resolution. A discussion is open regarding perspective of the technique for other remote sensing applications compared to more usual push broom configurations.

Ceramic-ceramic shell tile thermal protection system and method thereof

NASA Technical Reports Server (NTRS)

Riccitiello, Salvatore R. (Inventor); Smith, Marnell (Inventor); Goldstein, Howard E. (Inventor); Zimmerman, Norman B. (Inventor)

1986-01-01

A ceramic reusable, externally applied composite thermal protection system (TPS) is proposed. The system functions by utilizing a ceramic/ceramic upper shell structure which effectively separates its primary functions as a thermal insulator and as a load carrier to transmit loads to the cold structure. The composite tile system also prevents impact damage to the atmospheric entry vehicle thermal protection system. The composite tile comprises a structurally strong upper ceramic/ceramic shell manufactured from ceramic fibers and ceramic matrix meeting the thermal and structural requirements of a tile used on a re-entry aerospace vehicle. In addition, a lightweight high temperature ceramic lower temperature base tile is used. The upper shell and lower tile are attached by means effective to withstand the extreme temperatures (3000 to 3200F) and stress conditions. The composite tile may include one or more layers of variable density rigid or flexible thermal insulation. The assembly of the overall tile is facilitated by two or more locking mechanisms on opposing sides of the overall tile assembly. The assembly may occur subsequent to the installation of the lower shell tile on the spacecraft structural skin.

CubeSat Material Limits for Design for Demise

NASA Technical Reports Server (NTRS)

Kelley, R. L.; Jarkey, D. R.

2014-01-01

The CubeSat form factor of nano-satellite (a satellite with a mass between one and ten kilograms) has grown in popularity due to their ease of construction and low development and launch costs. In particular, their use as student led payload design projects has increased due to the growing number of launch opportunities. CubeSats are often deployed as secondary or tertiary payloads on most US launch vehicles or they may be deployed from the ISS. The focus of this study will be on CubeSats launched from the ISS. From a space safety standpoint, the development and deployment processes for CubeSats differ significantly from that of most satellites. For large satellites, extensive design reviews and documentation are completed, including assessing requirements associated with re-entry survivability. Typical CubeSat missions selected for ISS deployment have a less rigorous review process that may not evaluate aspects beyond overall design feasibility. CubeSat design teams often do not have the resources to ensure their design is compliant with re-entry risk requirements. A study was conducted to examine methods to easily identify the maximum amount of a given material that can be used in the construction of a CubeSats without posing harm to persons on the ground. The results demonstrate that there is not a general equation or relationship that can be used for all materials; instead a limiting value must be defined for each unique material. In addition, the specific limits found for a number of generic materials that have been previously used as benchmarking materials for re-entry survivability analysis tool comparison will be discussed.

Advanced Propulsion and TPS for a Rapidly-Prototyped CEV

NASA Astrophysics Data System (ADS)

Hudson, Gary C.

2005-02-01

Transformational Space Corporation (t/Space) is developing for NASA the initial designs for the Crew Exploration Vehicle family, focusing on a Launch CEV for transporting NASA and civilian passengers from Earth to orbit. The t/Space methodology is rapid prototyping of major vehicle systems, and deriving detailed specifications from the resulting hardware, avoiding "written-in-advance" specs that can force the costly invention of new capabilities simply to meet such specs. A key technology shared by the CEV family is Vapor Pressurized propulsion (Vapak) for simplicity and reliability, which provides electrical power, life support gas and a heat sink in addition to propulsion. The CEV family also features active transpiration cooling of re-entry surfaces (for reusability) backed up by passive thermal protection.

Thermal protection system ablation sensor

NASA Technical Reports Server (NTRS)

Gorbunov, Sergey (Inventor); Martinez, Edward R. (Inventor); Scott, James B. (Inventor); Oishi, Tomomi (Inventor); Fu, Johnny (Inventor); Mach, Joseph G. (Inventor); Santos, Jose B. (Inventor)

2011-01-01

An isotherm sensor tracks space vehicle temperatures by a thermal protection system (TPS) material during vehicle re-entry as a function of time, and surface recession through calibration, calculation, analysis and exposed surface modeling. Sensor design includes: two resistive conductors, wound around a tube, with a first end of each conductor connected to a constant current source, and second ends electrically insulated from each other by a selected material that becomes an electrically conductive char at higher temperatures to thereby complete an electrical circuit. The sensor conductors become shorter as ablation proceeds and reduced resistance in the completed electrical circuit (proportional to conductor length) is continually monitored, using measured end-to-end voltage change or current in the circuit. Thermocouple and/or piezoelectric measurements provide consistency checks on local temperatures.

SpaceX Dragon Parachute Test

NASA Image and Video Library

2018-03-04

SpaceX performed its fourteenth overall parachute test supporting Crew Dragon development. This most recent exercise was the first of several planned parachute system qualification tests ahead of the spacecraft’s first crewed flight and resulted in the successful touchdown of Crew Dragon’s parachute system. During this test, a C-130 aircraft transported the parachute test vehicle, designed to achieve the maximum speeds that Crew Dragon could experience on re-entry, over the Mojave Desert in Southern California and dropped the vehicle from an altitude of 25,000 feet. The test demonstrated an off-nominal situation, deploying only one of the two drogue chutes and intentionally skipping a reefing stage on one of the four main parachutes, proving a safe landing in such a contingency scenario.

KSC-2013-3716

NASA Image and Video Library

2013-10-22

CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, the Orion ground test vehicle, or GTA, is being prepared for lifting in the transfer aisle of the Vehicle Assembly Building. The GTA is being used for path finding operations, including simulated manufacturing, assembly and stacking procedures. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Dimitri Gerondidakis

Non-intrusive flow measurements on a reentry vehicle

NASA Technical Reports Server (NTRS)

Miles, R. B.; Satavicca, D. A.; Zimmermann, G. M.

1983-01-01

This study evaluates the utility of various non-intrusive techniques for the measurement of the flow field on the windward side of the Space Shuttle or a similar re-entry vehicle. Included are linear (Rayleigh, Raman, Mie, Laser Doppler Velocimetry, Resonant Doppler Velocimetry) and nonlinear (Coherent Anti-Stokes Raman, Laser Induced Fluorescence) light scattering, electron beam fluorescence, thermal emission and mass spectroscopy. Flow field properties are taken from a nonequilibrium flow model by Shinn, Moss and Simmonds at NASA Langley. Conclusions are, when possible, based on quantitative scaling of known laboratory results to the conditions projected. Detailed discussion with researchers in the field contributed further to these conclusions and provided valuable insights regarding the experimental feasibility of each of the techniques.

Flexible Learning Options: The Experiences and Perceptions of Regional Youth

ERIC Educational Resources Information Center

Msapenda, Vanessa; Hudson, Cate

2013-01-01

Over the past few decades a variety of alternative or re-entry educational programs have been developed in Australia as an approach to address early school leaving and promote engagement with learning. In South Australia, one of the largest initiatives has been the implementation of Flexible Learning Programs (FLPs) as part of the State…

The Professional Experiences of International Counseling Graduates upon Returning to Their Home Country

ERIC Educational Resources Information Center

Duenyas, Deborah Lynn

2017-01-01

This study investigated the first-person accounts of eight international counseling graduates (ICGs) upon re-entry to their home country to work after earning a university counseling degree from a program accredited by the Counsel for Accreditation and Counseling Related Educational Programs (CACREP) in the United States. An assumption of the…

Adaptable Holders for Arc-Jet Screening Candidate Thermal Protection System Repair Materials

NASA Technical Reports Server (NTRS)

Riccio, Joe; Milhoan, Jim D.

2010-01-01

Reusable holders have been devised for evaluating high-temperature, plasma-resistant re-entry materials, especially fabrics. Typical material samples tested support thermal-protection-system damage repair requiring evaluation prior to re-entry into terrestrial atmosphere. These tests allow evaluation of each material to withstand the most severe predicted re-entry conditions.

Report of the Defense Science Board Task Force on Future Strategic Strike Skills

DTIC Science & Technology

2006-03-01

25 Figure 11: Re - entry Systems – Critical Skills...SKILLS___________________________________________________25 Figure 9: Guidance – Critical Skills Figure 10: Re - entry Systems – Critical Skills ICBMS/BASING...ability to survive intercontinental ballistic missile re - entry and then to operate effectively thereafter, is another area where current skills are

Re-Entry, Recruitment, and Retention: A Community Relations Model for Sacramento City College.

ERIC Educational Resources Information Center

White, Maureen E.

Enrollment statistics and projections confirm the importance of focusing community college student recruitment and retention efforts on re-entry students. Re-entry students are a distinct and growing population whose educational requirements often differ from those of younger, traditional students. The literature on adult learners indicates that:…

University of Wisconsin-Milwaukee

Science.gov Websites

Online Pre-College Continuing Education Grades & Transcripts Student Success Study Abroad Academic Freshman Graduate Study International Transfer Adult & Returning Re-entry Second Degree UWM Online Out Academic Programs Study Abroad Research Outreach Partnerships Learning Communities Center for International

NASA's Morphing Project Research Summaries in Fiscal Year 2002

NASA Technical Reports Server (NTRS)

McGowan, Anna-Maria R.; Waszak, Martin R.

2005-01-01

The Morphing Project at the National Aeronautics and Space Agency s (NASA) Langley Research Center (LaRC) is part of the Breakthrough Vehicle Technologies Project, Vehicle Systems Program that conducts fundamental research on advanced technologies for future flight vehicles. The objectives of the Morphing Project are to develop and assess the advanced technologies and integrated component concepts to enable efficient, multi-point adaptability of flight vehicles; primarily through the application of adaptive structures and adaptive flow control to substantially alter vehicle performance characteristics. This document is a compilation of research summaries and other information on the project for fiscal year 2002. The focus is to provide a brief overview of the project content, technical results and lessons learned. At the time of publication, the Vehicle Systems Program (which includes the Morphing Project) is undergoing a program re-planning and reorganization. Accordingly, the programmatic descriptions of this document pertain only to the program as of fiscal year 2002.

M2-F1 in flight

NASA Technical Reports Server (NTRS)

1965-01-01

The M2-F1 Lifting Body is seen here under tow, high above Rogers Dry Lake near the Flight Research Center (later redesignated the Dryden Flight Research Center), Edwards, California. R. Dale Reed effectively advocated the project with the support of NASA research pilot Milt Thompson. Together, they gained the support of Flight Research Center Director Paul Bikle. After a six-month feasibility study, Bikle gave approval in the fall of 1962 for the M2-F1 to be built. The wingless, lifting body aircraft design was initially concieved as a means of landing an aircraft horizontally after atmospheric reentry. The absence of wings would make the extreme heat of re-entry less damaging to the vehicle. In 1962, Flight Research Center management approved a program to build a lightweight, unpowered lifting body as a prototype to flight test the wingless concept. It would look like a 'flying bathtub,' and was designated the M2-F1, the 'M' referring to 'manned' and 'F' referring to 'flight' version. It featured a plywood shell placed over a tubular steel frame crafted at Dryden. Construction was completed in 1963. The first flight tests of the M2-F1 were over Rogers Dry Lake at the end of a tow rope attached to a hopped-up Pontiac convertible driven at speeds up to about 120 mph. These initial tests produced enough flight data about the M2-F1 to proceed with flights behind a NASA C-47 tow plane at greater altitudes. The C-47 took the craft to an altitude of 12,000 where free flights back to Rogers Dry Lake began. Pilot for the first series of flights of the M2-F1 was NASA research pilot Milt Thompson. Typical glide flights with the M2-F1 lasted about two minutes and reached speeds of 110 to l20 mph. More than 400 ground tows and 77 aircraft tow flights were carried out with the M2-F1. The success of Dryden's M2-F1 program led to NASA's development and construction of two heavyweight lifting bodies based on studies at NASA's Ames and Langley research centers--the M2-F2 and the HL-10, both built by the Northrop Corporation, and the U.S. Air Force's X-24 program. The Lifting Body program also heavily influenced the Space Shuttle program. The M2-F1 program demonstrated the feasibility of the lifting body concept for horizontal landings of atmospheric entry vehicles. It also demonstrated a procurement and management concept for prototype flight research vehicles that produced rapid results at very low cost (approximately $50,000, excluding salaries of government employees assigned to the project).

ENTRYSAT: A 3U Cubesat to Study the Re-Entry Atmospheric Environment

NASA Astrophysics Data System (ADS)

Garcia, R. F.; Chaix, J.; Mimoun, D.; EntrySat student Team

2014-04-01

The EntrySat is a 3U CubeSat designed to study the uncontrolled atmospheric re-entry. The project, developed by ISAE in collaboration with ONERA, is funded by CNES and is intended to be launched in January 2016, in the context of the QB50 network. The scientific goal is to relate the kinematics of the satellite with the aerothermodynamic environment during re-entry. In particular, data will be compared with the computations of MUSIC/FAST, a new 6-degree of freedom code developed by ONERA to predict the trajectory of space debris. According to these requirements, the satellite will measure the temperature, pressure, heat flux, and drag force during re-entry, as well as the trajectory and attitude of the satellite. One of the major technological challenges is the retrieval of data during the re-entry phase, which will be based on the Iridium satellite network. The system design is based on the use of commercial COTS components, and is mostly developed by students from ISAE. As such, the EntrySat has an important educational value in the formation of young engineers.

HTV3 Approach

NASA Image and Video Library

2012-07-27

ISS032-E-010425 (27 July 2012) --- The unpiloted Japan Aerospace Exploration Agency (JAXA) H-II Transfer Vehicle (HTV-3) is photographed from a window in the Cupola by an Expedition 32 crew member as it approaches the International Space Station. The Japan Aerospace Exploration Agency launched HTV-3 aboard an H-IIB launch vehicle from the Tanegashima Space Center in southern Japan at 10:06 p.m. EDT July 20 (11:06 a.m. July 21, Japan time). The HTV is bringing 7,000 pounds of cargo including food and clothing for the crew members, an aquatic habitat experiment, a remote-controlled Earth-observation camera for environmental studies, a catalytic reactor for the station’s water regeneration system and a Japanese cooling water recirculation pump. The vehicle will remain at the space station until Sept. 6 when, like its predecessors, it will be detached from the Harmony node by Canadarm2 and released for a fiery re-entry over the Pacific Ocean.

HTV3 Approach

NASA Image and Video Library

2012-07-27

ISS032-E-010430 (27 July 2012) --- The Canadarm2 moves toward the unpiloted Japan Aerospace Exploration Agency (JAXA) H-II Transfer Vehicle (HTV-3) as it approaches the International Space Station. The Japan Aerospace Exploration Agency launched HTV-3 aboard an H-IIB launch vehicle from the Tanegashima Space Center in southern Japan at 10:06 p.m. EDT July 20 (11:06 a.m. July 21, Japan time). The HTV is bringing 7,000 pounds of cargo including food and clothing for the crew members, an aquatic habitat experiment, a remote-controlled Earth-observation camera for environmental studies, a catalytic reactor for the station’s water regeneration system and a Japanese cooling water recirculation pump. The vehicle will remain at the space station until Sept. 6 when, like its predecessors, it will be detached from the Harmony node by Canadarm2 and released for a fiery re-entry over the Pacific Ocean.

Development and tests on OREX vehicle thermal structure system

NASA Astrophysics Data System (ADS)

Yoshinaka, Toshinari; Morino, Yoshiki

1992-08-01

An overview of the thermal system structure development and their tests for Orbital Re-entry Experiment (OREX) vehicle, being developed as a part of H-2 Orbiting Plane (HOPE) development, is presented. The results of study on the OREX vehicle thermal structure system and concept of the system study are shown. The results of HOPE thermal structure system research were reflected to OREX in employing polyacrylonitrile tissues with conversion coating for the nose cap, Carbon-Thermal Protection System (TPS), and ceramic tile TPS for the structure. Test plans were established for material characteristics and design verifications, and flight validation for C/C (Carbon/Carbon Composite) nose cap and TPS, and gap filler, arc wind tunnel, heat insulation, and adhesion quality verification tests. Environment resistance of the C/C nose cone, C/C TPS, and ceramic tile TPS were verified and prospects of their manufacturing were obtained.

KSC-2013-3724

NASA Image and Video Library

2013-10-22

CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, the Orion ground test vehicle, or GTA, was lifted high in the air by crane in the transfer aisle of the Vehicle Assembly Building and is being lowered toward a mockup of the service module in high bay 4. The ground test vehicle is being used for path finding operations, including simulated manufacturing, assembly and stacking procedures. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Dimitri Gerondidakis

KSC-2013-3726

NASA Image and Video Library

2013-10-22

CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, technicians monitor the progress as the Orion ground test vehicle, or GTA, was lifted high in the air by crane in the transfer aisle of the Vehicle Assembly Building and is being lowered toward a mockup of the service module in high bay 4. The ground test vehicle is being used for path finding operations, including simulated manufacturing, assembly and stacking procedures. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Dimitri Gerondidakis

KSC-2013-3725

NASA Image and Video Library

2013-10-22

CAPE CANAVERAL, Fla. – At NASA’s Kennedy Space Center in Florida, the Orion ground test vehicle, or GTA, was lifted high in the air by crane in the transfer aisle of the Vehicle Assembly Building and is being lowered toward a mockup of the service module in high bay 4. The ground test vehicle is being used for path finding operations, including simulated manufacturing, assembly and stacking procedures. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit www.nasa.gov/orion. Photo credit: Dimitri Gerondidakis

Evaluation of Mars Entry Reconstructured Trajectories Based on Hypothetical 'Quick-Look' Entry Navigation Data

NASA Technical Reports Server (NTRS)

Pastor, P. Rick; Bishop, Robert H.; Striepe, Scott A.

2000-01-01

A first order simulation analysis of the navigation accuracy expected from various Navigation Quick-Look data sets is performed. Here quick-look navigation data are observations obtained by hypothetical telemetried data transmitted on the fly during a Mars probe's atmospheric entry. In this simulation study, navigation data consists of 3-axis accelerometer sensor and attitude information data. Three entry vehicle guidance types are studied: I. a Maneuvering entry vehicle (as with Mars 01 guidance where angle of attack and bank angle are controlled); II. Zero angle-of-attack controlled entry vehicle (as with Mars 98); and III. Ballistic, or spin stabilized entry vehicle (as with Mars Pathfinder);. For each type, sensitivity to progressively under sampled navigation data and inclusion of sensor errors are characterized. Attempts to mitigate the reconstructed trajectory errors, including smoothing, interpolation and changing integrator characteristics are also studied.

Exploring Career Decision-Making Experiences of Mexican American Re-Entry Community College Women

ERIC Educational Resources Information Center

Dominguez, Cecilia Sophia

2010-01-01

The purpose of this phenomenological investigation was to increase understanding of the career perspectives of 12 Mexican American, re-entry women who were attending a community college. The questions guiding this investigation were: (a) How do Mexican American re-entry college women describe their career decision-making experiences, (b) What do…

Circumferential and functional re-entry of in vivo slow-wave activity in the porcine small intestine.

PubMed

Angeli, T R; O'Grady, G; Du, P; Paskaranandavadivel, N; Pullan, A J; Bissett, I P; Cheng, L K

2013-05-01

Slow-waves modulate the pattern of small intestine contractions. However, the large-scale spatial organization of intestinal slow-wave pacesetting remains uncertain because most previous studies have had limited resolution. This study applied high-resolution (HR) mapping to evaluate intestinal pacesetting mechanisms and propagation patterns in vivo. HR serosal mapping was performed in anesthetized pigs using flexible arrays (256 electrodes; 32 × 8; 4 mm spacing), applied along the jejunum. Slow-wave propagation patterns, frequencies, and velocities were calculated. Slow-wave initiation sources were identified and analyzed by animation and isochronal activation mapping. Analysis comprised 32 recordings from nine pigs (mean duration 5.1 ± 3.9 min). Slow-wave propagation was analyzed, and a total of 26 sources of slow-wave initiation were observed and classified as focal pacemakers (31%), sites of functional re-entry (23%) and circumferential re-entry (35%), or indeterminate sources (11%). The mean frequencies of circumferential and functional re-entry were similar (17.0 ± 0.3 vs 17.2 ± 0.4 cycle min(-1) ; P = 0.5), and greater than that of focal pacemakers (12.7 ± 0.8 cycle min(-1) ; P < 0.001). Velocity was anisotropic (12.9 ± 0.7 mm s(-1) circumferential vs 9.0 ± 0.7 mm s(-1) longitudinal; P < 0.05), contributing to the onset and maintenance of re-entry. This study has shown multiple patterns of slow-wave initiation in the jejunum of anesthetized pigs. These results constitute the first description and analysis of circumferential re-entry in the gastrointestinal tract and functional re-entry in the in vivo small intestine. Re-entry can control the direction, pattern, and frequency of slow-wave propagation, and its occurrence and functional significance merit further investigation. © 2013 Blackwell Publishing Ltd.

Re-entry Adjustment and Job Embeddedness: The Mediating Role of Professional Identity in Indonesian Returnees.

PubMed

Andrianto, Sonny; Jianhong, Ma; Hommey, Confidence; Damayanti, Devi; Wahyuni, Honey

2018-01-01

The present study examined the relationship between difficulty in re-entry adjustment and job embeddedness, considering the mediating role of sense of professional identity. The online data on demographic characteristics, difficulty on re-entry adjustment, sense of professional identity, and job embeddedness were collected from 178 Indonesian returnees from multiple organizations. The results showed that difficulty in re-entry adjustment was a significant predictor of a sense of professional identity; a sense of professional identity was a significant predictor of job embeddedness. Furthermore, sense of professional identity is an effective mediating variable, bridging the relationship between post-return conditions to the home country and work atmosphere. Finally, the key finding of this study was that sense of professional identity mediated the effect of difficulty in re-entry adjustment on job embeddedness. The theoretical and practical implications, study limitations, and future research needs of our findings are noted.

An Overview of the Role of Systems Analysis in NASA's Hypersonics Project

NASA Technical Reports Server (NTRS)

Robinson, Jeffrey S.; Martin John G.; Bowles, Jeffrey V> ; Mehta, Unmeel B.; Snyder, CHristopher A.

2006-01-01

NASA's Aeronautics Research Mission Directorate recently restructured its Vehicle Systems Program, refocusing it towards understanding the fundamental physics that govern flight in all speed regimes. Now called the Fundamental Aeronautics Program, it is comprised of four new projects, Subsonic Fixed Wing, Subsonic Rotary Wing, Supersonics, and Hypersonics. The Aeronautics Research Mission Directorate has charged the Hypersonics Project with having a basic understanding of all systems that travel at hypersonic speeds within the Earth's and other planets atmospheres. This includes both powered and unpowered systems, such as re-entry vehicles and vehicles powered by rocket or airbreathing propulsion that cruise in and accelerate through the atmosphere. The primary objective of the Hypersonics Project is to develop physics-based predictive tools that enable the design, analysis and optimization of such systems. The Hypersonics Project charges the systems analysis discipline team with providing it the decision-making information it needs to properly guide research and technology development. Credible, rapid, and robust multi-disciplinary system analysis processes and design tools are required in order to generate this information. To this end, the principal challenges for the systems analysis team are the introduction of high fidelity physics into the analysis process and integration into a design environment, quantification of design uncertainty through the use of probabilistic methods, reduction in design cycle time, and the development and implementation of robust processes and tools enabling a wide design space and associated technology assessment capability. This paper will discuss the roles and responsibilities of the systems analysis discipline team within the Hypersonics Project as well as the tools, methods, processes, and approach that the team will undertake in order to perform its project designated functions.

ATV-4 Undocking

NASA Image and Video Library

2013-10-28

ISS037-E-021218 (28 Oct. 2013) --- The European Space Agency’s fourth Automated Transfer Vehicle (ATV-4), also known as the “Albert Einstein,” begins its relative separation from the International Space Station during the Expedition 37 mission. The ATV-4 undocked from the aft port of the Zvezda Service Module at 4:55 a.m. (EDT) Oct. 28, 2013. The ATV, filled with trash and unneeded items, is scheduled to be sent into Earth’s atmosphere for a planned destructive re-entry over an uninhabited area of the south Pacific Ocean on Nov. 2.

ATV-4 Undocking

NASA Image and Video Library

2013-10-28

ISS037-E-021161 (28 Oct. 2013) --- The European Space Agency’s fourth Automated Transfer Vehicle (ATV-4), also known as the “Albert Einstein,” begins its relative separation from the International Space Station during the Expedition 37 mission. The ATV-4 undocked from the aft port of the Zvezda Service Module at 4:55 a.m. (EDT) Oct. 28, 2013. The ATV, filled with trash and unneeded items, is scheduled to be sent into Earth’s atmosphere for a planned destructive re-entry over an uninhabited area of the south Pacific Ocean on Nov. 2.

ATV-4 Undocking

NASA Image and Video Library

2013-10-28

ISS037-E-021216 (28 Oct. 2013) --- The European Space Agency’s fourth Automated Transfer Vehicle (ATV-4), also known as the “Albert Einstein,” begins its relative separation from the International Space Station during the Expedition 37 mission. The ATV-4 undocked from the aft port of the Zvezda Service Module at 4:55 a.m. (EDT) Oct. 28, 2013. The ATV, filled with trash and unneeded items, is scheduled to be sent into Earth’s atmosphere for a planned destructive re-entry over an uninhabited area of the south Pacific Ocean on Nov. 2.

ATV-4 Undocking

NASA Image and Video Library

2013-10-28

ISS037-E-021195 (28 Oct. 2013) --- The European Space Agency’s fourth Automated Transfer Vehicle (ATV-4), also known as the “Albert Einstein,” begins its relative separation from the International Space Station during the Expedition 37 mission. The ATV-4 undocked from the aft port of the Zvezda Service Module at 4:55 a.m. (EDT) Oct. 28, 2013. The ATV, filled with trash and unneeded items, is scheduled to be sent into Earth’s atmosphere for a planned destructive re-entry over an uninhabited area of the south Pacific Ocean on Nov. 2.

ATV-4 Undocking

NASA Image and Video Library

2013-10-28

ISS037-E-021215 (28 Oct. 2013) --- The European Space Agency’s fourth Automated Transfer Vehicle (ATV-4), also known as the “Albert Einstein,” begins its relative separation from the International Space Station during the Expedition 37 mission. The ATV-4 undocked from the aft port of the Zvezda Service Module at 4:55 a.m. (EDT) Oct. 28, 2013. The ATV, filled with trash and unneeded items, is scheduled to be sent into Earth’s atmosphere for a planned destructive re-entry over an uninhabited area of the south Pacific Ocean on Nov. 2.

Polyimide Boosts High-Temperature Performance

NASA Technical Reports Server (NTRS)

2008-01-01

Maverick Corporation, of Blue Ash, Ohio, licensed DMBZ-15 polyimide technology from Glenn Research Center. This ultrahigh-temperature material provides substantial weight savings and reduced machining costs compared to the same component made with more traditional metallic materials. DMBZ-15 has a wide range of applications from aerospace (aircraft engine and airframe components, space transportation systems, and missiles) to non-aerospace (oil drilling, rolling mill), and is particularly well-suited to use as face sheets with honey cones or thermal protection systems for reusable launch vehicles, which encounter elevated temperatures during launch and re-entry.

A Comparison of Two Skip Entry Guidance Algorithms

NASA Technical Reports Server (NTRS)

Rea, Jeremy R.; Putnam, Zachary R.

2007-01-01

The Orion capsule vehicle will have a Lift-to-Drag ratio (L/D) of 0.3-0.35. For an Apollo-like direct entry into the Earth's atmosphere from a lunar return trajectory, this L/D will give the vehicle a maximum range of about 2500 nm and a maximum crossrange of 216 nm. In order to y longer ranges, the vehicle lift must be used to loft the trajectory such that the aerodynamic forces are decreased. A Skip-Trajectory results if the vehicle leaves the sensible atmosphere and a second entry occurs downrange of the atmospheric exit point. The Orion capsule is required to have landing site access (either on land or in water) inside the Continental United States (CONUS) for lunar returns anytime during the lunar month. This requirement means the vehicle must be capable of flying ranges of at least 5500 nm. For the L/D of the vehicle, this is only possible with the use of a guided Skip-Trajectory. A skip entry guidance algorithm is necessary to achieve this requirement. Two skip entry guidance algorithms have been developed: the Numerical Skip Entry Guidance (NSEG) algorithm was developed at NASA/JSC and PredGuid was developed at Draper Laboratory. A comparison of these two algorithms will be presented in this paper. Each algorithm has been implemented in a high-fidelity, 6 degree-of-freedom simulation called the Advanced NASA Technology Architecture for Exploration Studies (ANTARES). NASA and Draper engineers have completed several monte carlo analyses in order to compare the performance of each algorithm in various stress states. Each algorithm has been tested for entry-to-target ranges to include direct entries and skip entries of varying length. Dispersions have been included on the initial entry interface state, vehicle mass properties, vehicle aerodynamics, atmosphere, and Reaction Control System (RCS). Performance criteria include miss distance to the target, RCS fuel usage, maximum g-loads and heat rates for the first and second entry, total heat load, and control system saturation. The comparison of the performance criteria has led to a down select and guidance merger that will take the best ideas from each algorithm to create one skip entry guidance algorithm for the Orion vehicle.

78 FR 66898 - Low Enriched Uranium From France: Final Results of Changed Circumstances Review

Federal Register 2010, 2011, 2012, 2013, 2014

2013-11-07

... in U.S. customs territory, and (ii) are re-exported within eighteen (18) months of entry of the low... extend the deadline for re-exportation of this sole entry of low-enriched uranium. The Department determines that the deadline for re-exportation of this sole entry is November 1, 2015, and that this will be...

State Policies Affecting the "Adult Re-Entry Pipeline" in Postsecondary Education: Results of a Fifty-State Inventory

ERIC Educational Resources Information Center

Boeke, Marianne; Zis, Stacey; Ewell, Peter

2011-01-01

With support from the Bill and Melinda Gates Foundation, the National Center for Higher Education Management Systems (NCHEMS) is engaged in a two year project centered on state policies that foster student progression and success in the "adult re-entry pipeline." The adult re-entry pipeline consists of the many alternative pathways to…

Entry, Descent, and Landing technological barriers and crewed MARS vehicle performance analysis

NASA Astrophysics Data System (ADS)

Subrahmanyam, Prabhakar; Rasky, Daniel

2017-05-01

Mars has been explored historically only by robotic crafts, but a crewed mission encompasses several new engineering challenges - high ballistic coefficient entry, hypersonic decelerators, guided entry for reaching intended destinations within acceptable margins for error in the landing ellipse, and payload mass are all critical factors for evaluation. A comprehensive EDL parametric analysis has been conducted in support of a high mass landing architecture by evaluating three types of vehicles -70° Sphere Cone, Ellipsled and SpaceX hybrid architecture called Red Dragon as potential candidate options for crewed entry vehicles. Aerocapture at the Martian orbit of about 400 km and subsequent Entry-from-orbit scenarios were investigated at velocities of 6.75 km/s and 4 km/s respectively. A study on aerocapture corridor over a range of entry velocities (6-9 km/s) suggests that a hypersonic L/D of 0.3 is sufficient for a Martian aerocapture. Parametric studies conducted by varying aeroshell diameters from 10 m to 15 m for several entry masses up to 150 mt are summarized and results reveal that vehicles with entry masses in the range of about 40-80 mt are capable of delivering cargo with a mass on the order of 5-20 mt. For vehicles with an entry mass of 20 mt to 80 mt, probabilistic Monte Carlo analysis of 5000 cases for each vehicle were run to determine the final landing ellipse and to quantify the statistical uncertainties associated with the trajectory and attitude conditions during atmospheric entry. Strategies and current technological challenges for a human rated Entry, Descent, and Landing to the Martian surface are presented in this study.

Analyzing the Impacts of Natural Environments on Launch and Landing Availability for NASA's Eploration Systems Development Programs

NASA Technical Reports Server (NTRS)

Altino, Karen M.; Burns, K. Lee; Barbre, Robert E.; Leahy, Frank B.

2014-01-01

NASA is developing new capabilities for human and scientific exploration beyond Earth orbit. Natural environments information is an important asset for NASA's development of the next generation space transportation system as part of the Exploration Systems Development Program, which includes the Space Launch System (SLS) and MultiPurpose Crew Vehicle (MPCV) Programs. Natural terrestrial environment conditions - such as wind, lightning and sea states - can affect vehicle safety and performance during multiple mission phases ranging from prelaunch ground processing to landing and recovery operations, including all potential abort scenarios. Space vehicles are particularly sensitive to these environments during the launch/ascent and the entry/landing phases of mission operations. The Marshall Space Flight Center (MSFC) Natural Environments Branch provides engineering design support for NASA space vehicle projects and programs by providing design engineers and mission planners with natural environments definitions as well as performing custom analyses to help characterize the impacts the natural environment may have on vehicle performance. One such analysis involves assessing the impact of natural environments to operational availability. Climatological time series of operational surface weather observations are used to calculate probabilities of meeting or exceeding various sets of hypothetical vehicle-specific parametric constraint thresholds.

KSC-2014-3445

NASA Image and Video Library

2014-08-10

LOS ANGELES, Calif. – Visitors tour the well deck of the USS Anchorage and view the Orion boilerplate test vehicle secured in its recovery cradle during the Science, Technology, Engineering and Mathematics, or STEM, Expo for L.A. Navy Days at the Port of Los Angeles in California. A combined team from NASA’s Ground Systems Development and Operations Program and the U.S. Navy were in San Diego to practice recovering Orion from the ocean, as they will do in December following the spacecraft's first trip to space during Exploration Flight Test-1. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep-space return velocities. The first unpiloted test flight of the Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Kim Shiflett

KSC-2014-3446

NASA Image and Video Library

2014-08-10

LOS ANGELES, Calif. – Visitors tour the well deck of the USS Anchorage and view the Orion boilerplate test vehicle secured in its recovery cradle during the Science, Technology, Engineering and Mathematics, or STEM, Expo for L.A. Navy Days at the Port of Los Angeles in California. A combined team from NASA’s Ground Systems Development and Operations Program and the U.S. Navy were in San Diego to practice recovering Orion from the ocean, as they will do in December following the spacecraft's first trip to space during Exploration Flight Test-1. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep-space return velocities. The first unpiloted test flight of the Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Kim Shiflett

URT-3 At Sea Recovery Operation with Bolden

NASA Image and Video Library

2014-09-15

The Orion boilerplate test vehicle is in the water-filled well deck of the USS Anchorage during the first day of Underway Recovery Test 3 in the Pacific Ocean. NASA, Lockheed Martin and U.S. Navy personnel are conducting the recovery test to prepare for recovery of the Orion crew module on its return from a deep space mission. The test allows the teams to demonstrate and evaluate the recovery processes, procedures, hardware and personnel in open waters. The Ground Systems Development and Operations Program is conducting the underway recovery tests. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion is scheduled to launch in 2014 atop a United Launch Alliance Delta IV Heavy rocket and in 2018 on NASA’s Space Launch System rocket.

URT-3 At Sea Recovery Operation with Bolden

NASA Image and Video Library

2014-09-15

Underway Recovery Test team members help secure the Orion boilerplate test vehicle in the well deck of the USS Anchorage during the first day of Underway Recovery Test 3 in the Pacific Ocean. NASA, Lockheed Martin and U.S. Navy personnel are conducting the recovery test to prepare for recovery of the Orion crew module on its return from a deep space mission. The test allows the teams to demonstrate and evaluate the recovery processes, procedures, hardware and personnel in open waters. The Ground Systems Development and Operations Program is conducting the underway recovery tests. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion is scheduled to launch in 2014 atop a United Launch Alliance Delta IV Heavy rocket and in 2018 on NASA’s Space Launch System rocket.

URT-3 At Sea Recovery Operation with Bolden

NASA Image and Video Library

2014-09-15

The Orion boilerplate test vehicle is secured in the well deck of the USS Anchorage during the first day of Underway Recovery Test 3 in the Pacific Ocean. NASA, Lockheed Martin and U.S. Navy personnel are conducting the recovery test to prepare for recovery of the Orion crew module on its return from a deep space mission. The test allows the teams to demonstrate and evaluate the recovery processes, procedures, hardware and personnel in open waters. The Ground Systems Development and Operations Program is conducting the underway recovery tests. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of Orion is scheduled to launch in 2014 atop a United Launch Alliance Delta IV Heavy rocket and in 2018 on NASA’s Space Launch System rocket.

Entry Vehicle Control System Design for the Mars Smart Lander

NASA Technical Reports Server (NTRS)

Calhoun, Philip C.; Queen, Eric M.

2002-01-01

The NASA Langley Research Center, in cooperation with the Jet Propulsion Laboratory, participated in a preliminary design study of the Entry, Descent and Landing phase for the Mars Smart Lander Project. This concept utilizes advances in Guidance, Navigation and Control technology to significantly reduce uncertainty in the vehicle landed location on the Mars surface. A candidate entry vehicle controller based on the Reaction Control System controller for the Apollo Lunar Excursion Module digital autopilot is proposed for use in the entry vehicle attitude control. A slight modification to the phase plane controller is used to reduce jet-firing chattering while maintaining good control response for the Martian entry probe application. The controller performance is demonstrated in a six-degree-of-freedom simulation with representative aerodynamics.

9 CFR 381.198 - Importer to make application for inspection of poultry products offered for entry.

Code of Federal Regulations, 2012 CFR

2012-01-01

... Import Field Office for an inspection assignment (see § 301.2(yyy)). (1) If the Automated Import... place samples in the vehicle for easy removal and reinspection by a Program import inspector. (3) In the...

9 CFR 381.198 - Importer to make application for inspection of poultry products offered for entry.

Code of Federal Regulations, 2014 CFR

2014-01-01

... Import Field Office for an inspection assignment (see § 301.2(yyy)). (1) If the Automated Import... place samples in the vehicle for easy removal and reinspection by a Program import inspector. (3) In the...

9 CFR 381.198 - Importer to make application for inspection of poultry products offered for entry.

Code of Federal Regulations, 2013 CFR

2013-01-01

... Import Field Office for an inspection assignment (see § 301.2(yyy)). (1) If the Automated Import... place samples in the vehicle for easy removal and reinspection by a Program import inspector. (3) In the...

9 CFR 381.198 - Importer to make application for inspection of poultry products offered for entry.

Code of Federal Regulations, 2011 CFR

2011-01-01

... Import Field Office for an inspection assignment (see § 301.2(yyy)). (1) If the Automated Import... place samples in the vehicle for easy removal and reinspection by a Program import inspector. (3) In the...

Development of the reentry flight dynamics simulator for evaluation of space shuttle orbiter entry systems

NASA Technical Reports Server (NTRS)

Rowell, L. F.; Powell, R. W.; Stone, H. W., Jr.

1980-01-01

A nonlinear, six degree of freedom, digital computer simulation of a vehicle which has constant mass properties and whose attitudes are controlled by both aerodynamic surfaces and reaction control system thrusters was developed. A rotating, oblate Earth model was used to describe the gravitational forces which affect long duration Earth entry trajectories. The program is executed in a nonreal time mode or connected to a simulation cockpit to conduct piloted and autopilot studies. The program guidance and control software used by the space shuttle orbiter for its descent from approximately 121.9 km to touchdown on the runway.

In Situ Magnetohydrodynamic Energy Generation for Planetary Entry Vehicles

NASA Astrophysics Data System (ADS)

Ali, H. K.; Braun, R. D.

2014-06-01

This work aims to study the suitability of multi-pass entry trajectories for harnessing of vehicle kinetic energy through magnetohydrodynamic power generation from the high temperature entry plasma. Potential mission configurations are analyzed.

Health status of people with work-related musculoskeletal disorders in return to work programs: a Malaysian study.

PubMed

Murad, Mohd Suleiman; O'Brien, Lisa; Farnworth, Louise; Chien, Chi-Wen

2013-07-01

This study examined the health status of injured workers with musculoskeletal disorders enrolled in the Malaysian Return to Work (RTW) program. The 102 participants were categorized into three RTW groups: Off-work (n = 30, 29.4%), Re-entry (n = 44, 43.1%), and Maintenance (n = 28, 27.5%). Overall health status, as measured by the SF-36 version 2, of the workers exhibited below average compared to the internationally established normative population, with their physical health component summary rated lower than mental health. Across the different groups, significant differences were found in role-physical, vitality, bodily pain, general health, and mental health. However, the mean values of these variables were higher in the Maintenance group and were found significant. The current health status of injured workers at Off-work and Re-entry phases was significantly low and warranted to be improved by involving other health professionals such as occupational therapists, ergonomists, and psychologists.

Re-Entry Point Targeting for LEO Spacecraft using Aerodynamic Drag

NASA Technical Reports Server (NTRS)

Omar, Sanny; Bevilacqua, Riccardo; Fineberg, Laurence; Treptow, Justin; Johnson, Yusef; Clark, Scott

2016-01-01

Most Low Earth Orbit (LEO) spacecraft do not have thrusters and re-enter atmosphere in random locations at uncertain times. Objects pose a risk to persons, property, or other satellites. Has become a larger concern with the recent increase in small satellites. Working on a NASA funded project to design a retractable drag device to expedite de-orbit and target a re-entry location through modulation of the drag area. Will be discussing the re-entry point targeting algorithm here.

Shuttle Risk Progression by Flight

NASA Technical Reports Server (NTRS)

Hamlin, Teri; Kahn, Joe; Thigpen, Eric; Zhu, Tony; Lo, Yohon

2011-01-01

Understanding the early mission risk and progression of risk as a vehicle gains insights through flight is important: . a) To the Shuttle Program to understand the impact of re-designs and operational changes on risk. . b) To new programs to understand reliability growth and first flight risk. . Estimation of Shuttle Risk Progression by flight: . a) Uses Shuttle Probabilistic Risk Assessment (SPRA) and current knowledge to calculate early vehicle risk. . b) Shows impact of major Shuttle upgrades. . c) Can be used to understand first flight risk for new programs.

SHARP Demonstration Flight: Video Broadcast System for Research in Intelligent Flight Characterization and Control

NASA Technical Reports Server (NTRS)

Kitts, Christopher

2001-01-01

The NASA Ames Research Center (Thermal Protection Materials and Systems Branch) is investigating new ceramic materials for the thermal protection of atmospheric entry vehicles. An incremental approach to proving the capabilities of these materials calls for a lifting entry flight test of a sharp leading edge component on the proposed SHARP (Slender Hypervelocity Aerothermodynamic Research Probe) vehicle. This flight test will establish the aerothermal performance constraint under real lifting entry conditions. NASA Ames has been developing the SHARP test flight with SSDL (responsible for the SHARP S I vehicle avionics), Montana State University (responsible for the SHARP S I vehicle airframe), the Wickman Spacecraft and Propulsion Company (responsible for the sounding rocket and launch operations), and with the SCU Intelligent Robotics Program, The SCU team was added well after the rest of the development team had formed. The SCU role was to assist with the development of a real-time video broadcast system which would relay onboard flight video to a communication groundstation. The SCU team would also assist with general vehicle preparation as well as flight operations. At the time of the submission of the original SCU proposal, a test flight in Wyoming was originally targeted for September 2000. This date was moved several times into the Fall of 2000. It was then postponed until the Spring of 2001, and later pushed into late Summer 2001. To date, the flight has still not taken place. These project delays resulted in SCU requesting several no-cost extensions to the project. Based on the most recent conversations with the project technical lead, Paul Kolodjiez, the current plan is for the overall SHARP team to assemble what exists of the vehicle, to document the system, and to 'mothball' the vehicle in anticipation of future flight and funding opportunities.

KSC-2014-3391

NASA Image and Video Library

2014-08-06

LOS ANGELES, Calif. – Visitors tour the well deck of the USS Anchorage and view the Orion boilerplate test vehicle secured in its recovery cradle during the Science, Technology, Engineering and Mathematics, or STEM, Expo for L.A. Navy Days at the Port of Los Angeles, California. NASA, Lockheed Martin and the U.S. Navy completed Underway Recovery Test 2 on the Orion test vehicle in the Pacific Ocean off the coast of San Diego to prepare for recovery of the Orion crew module on its return from a deep space mission. The underway recovery test allowed the teams to demonstrate and evaluate the recovery processes, procedures, new hardware and personnel in open waters. The Ground Systems Development and Operations Program conducted the underway recovery test. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of the Orion is scheduled to launch in 2014 on Exploration Flight Test-1, or EFT-1, atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit http://www.nasa.gov/orion. Photo credit: Kim Shiflett

KSC-2014-3881

NASA Image and Video Library

2014-09-14

SAN DIEGO, Calif. – The Orion boilerplate test vehicle has been lowered into the water with a stationary crane from the USS Salvor, a safeguard-class rescue and salvage ship, during Underway Recovery Test 4A in the Pacific Ocean. Nearby, U.S. Navy personnel in a Zodiac boat prepare to practice procedures to tether and retrieve the test vehicle. NASA, Lockheed Martin and the U.S. Navy are testing crane recovery operations to prepare for recovery of the Orion crew module on its return from a deep space mission. The underway recovery test will allow the teams to demonstrate and evaluate the recovery processes, procedures, new hardware and personnel in open waters. The Ground Systems Development and Operations Program is conducting the underway recovery test. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of the Orion is scheduled to launch in December 2014 atop a United Launch Alliance Delta IV Heavy rocket and in 2018 on NASA’s Space Launch System rocket. For more information, visit http://www.nasa.gov/orion. Photo credit: Kim Shiflett

KSC-2014-3884

NASA Image and Video Library

2014-09-14

SAN DIEGO, Calif. – The Orion boilerplate test vehicle floats in the Pacific Ocean during Underway Recovery Test 4A. Orion was lowered into the water with a stationary crane from the USS Salvor, a safeguard-class rescue and salvage ship. Nearby, U.S. Navy personnel in a Zodiac boat and rigid hull inflatable boat prepare to practice procedures to tether and retrieve the test vehicle. NASA, Lockheed Martin and the U.S. Navy are conducting crane recovery tests to prepare for recovery of the Orion crew module on its return from a deep space mission. The underway recovery test will allow the teams to demonstrate and evaluate the recovery processes, procedures, new hardware and personnel in open waters. The Ground Systems Development and Operations Program is conducting the underway recovery test. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of the Orion is scheduled to launch in December 2014 atop a United Launch Alliance Delta IV Heavy rocket and in 2018 on NASA’s Space Launch System rocket. For more information, visit http://www.nasa.gov/orion. Photo credit: Kim Shiflett

KSC-2014-3882

NASA Image and Video Library

2014-09-14

SAN DIEGO, Calif. – The Orion boilerplate test vehicle floats in the Pacific Ocean during Underway Recovery Test 4A. Orion was lowered into the water with a stationary crane from the USS Salvor, a safeguard-class rescue and salvage ship. Nearby, U.S. Navy personnel in a Zodiac boat prepare to practice procedures to tether and retrieve the test vehicle. NASA, Lockheed Martin and the U.S. Navy are conducting crane recovery tests to prepare for recovery of the Orion crew module on its return from a deep space mission. The underway recovery test will allow the teams to demonstrate and evaluate the recovery processes, procedures, new hardware and personnel in open waters. The Ground Systems Development and Operations Program is conducting the underway recovery test. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of the Orion is scheduled to launch in December 2014 atop a United Launch Alliance Delta IV Heavy rocket and in 2018 on NASA’s Space Launch System rocket. For more information, visit http://www.nasa.gov/orion. Photo credit: Kim Shiflett

KSC-2014-3885

NASA Image and Video Library

2014-09-14

SAN DIEGO, Calif. – The Orion boilerplate test vehicle floats in the Pacific Ocean during Underway Recovery Test 4A. Orion was lowered into the water with a stationary crane from the USS Salvor, a safeguard-class rescue and salvage ship. Nearby, U.S. Navy personnel in a Zodiac boat have attached a flotation collar and tether lines to Orion to bring the test vehicle closer to the ship. NASA, Lockheed Martin and the U.S. Navy are conducting crane recovery tests to prepare for recovery of the Orion crew module on its return from a deep space mission. The underway recovery test will allow the teams to demonstrate and evaluate the recovery processes, procedures, new hardware and personnel in open waters. The Ground Systems Development and Operations Program is conducting the underway recovery test. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of the Orion is scheduled to launch in December 2014 atop a United Launch Alliance Delta IV Heavy rocket and in 2018 on NASA’s Space Launch System rocket. For more information, visit http://www.nasa.gov/orion. Photo credit: Kim Shiflett

KSC-2014-3915

NASA Image and Video Library

2014-09-14

SAN DIEGO, Calif. – The Orion boilerplate test vehicle floats in the Pacific Ocean during the third day of Underway Recovery Test 4A. Orion was lowered into the water from the USS Salvor, a safeguard-class rescue and salvage ship, using a stationary crane. Tether lines were attached to the test vehicle from the ship for a towing test. Navy divers in a Zodiac boat practice recovery procedures and monitor Orion. NASA, Lockheed Martin and the U.S. Navy are conducting the test to prepare for recovery of the Orion crew module on its return from a deep space mission. The underway recovery test allows the teams to demonstrate and evaluate the recovery processes, procedures, new hardware and personnel in open waters. The Ground Systems Development and Operations Program is conducting the underway recovery test. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of the Orion is scheduled to launch in December 2014 atop a United Launch Alliance Delta IV Heavy rocket and in 2018 on NASA’s Space Launch System rocket. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Kim Shiflett

KSC-2014-3428

NASA Image and Video Library

2014-08-03

SAN DIEGO, Calif. – U.S. Navy personnel in a rigid hull inflatable boat use tether lines to bring the Orion boilerplate test vehicle back to the USS Anchorage during a portion of Underway Recovery Test 2 in the Pacific Ocean off the coast of San Diego. Behind the test vehicle is another rigid hull inflatable boat. To the far left are U.S. Navy divers in a Zodiac boat. NASA, Lockheed Martin and the U.S. Navy are conducting the test to prepare for recovery of the Orion crew module on its return from a deep space mission. The underway recovery test will allow the team to demonstrate and evaluate the recovery processes, procedures, new hardware and personnel in open waters. The Ground Systems Development and Operations Program is conducting the underway recovery test. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of the Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Kim Shiflett

KSC-2014-3425

NASA Image and Video Library

2014-08-03

SAN DIEGO, Calif. – The Orion boilerplate test vehicle floats in the Pacific Ocean off the coast of San Diego during a portion of Underway Recovery Test 2. To the right are U.S. Navy personnel in two rigid hull inflatable boats. To the left are U.S. Navy divers in two Zodiac boats. They are preparing to practice techniques to attach a lifting sling to the test vehicle. NASA, Lockheed Martin and the U.S. Navy are conducting the test from the USS Anchorage to prepare for recovery of the Orion crew module on its return from a deep space mission. The underway recovery test will allow the team to demonstrate and evaluate the recovery processes, procedures, new hardware and personnel in open waters. The Ground Systems Development and Operations Program is conducting the underway recovery test. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of the Orion is scheduled to launch in 2014 atop a Delta IV rocket and in 2017 on NASA’s Space Launch System rocket. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Kim Shiflett

KSC-2014-2580

NASA Image and Video Library

2014-05-13

SAN DIEGO, Calif. – The Orion boilerplate test vehicle is being moved into a protective structure at the Mole Pier at the Naval Base San Diego in California for a simulated fit check of the hatch cover. The test vehicle is attached to the crew module recovery cradle. The Ground Systems Development and Operations Program, Lockheed Martin and the U.S. Navy are evaluating the hardware and processes for preparing the Orion crew module for Exploration Flight Test-1, or EFT-1, for overland transport from the naval base to NASA's Kennedy Space Center in Florida. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of the Orion is scheduled to launch later this year atop a Delta IV rocket from Cape Canaveral Air Force Station in Florida to an altitude of 3,600 miles above the Earth's surface. The two-orbit, four-hour flight test will help engineers evaluate the systems critical to crew safety including the heat shield, parachute system and launch abort system. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Kim Shiflett

KSC-2014-2586

NASA Image and Video Library

2014-05-13

SAN DIEGO, Calif. – Inside a protective structure at the Mole Pier at the Naval Base San Diego in California, workers prepare for a simulated fit check of the hatch cover on the Orion boilerplate test vehicle. The test vehicle is secured on the crew module recovery cradle. The Ground Systems Development and Operations Program, Lockheed Martin and the U.S. Navy are evaluating the hardware and processes for preparing the Orion crew module for Exploration Flight Test-1, or EFT-1, for overland transport from the naval base to NASA's Kennedy Space Center in Florida. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of the Orion is scheduled to launch later this year atop a Delta IV rocket from Cape Canaveral Air Force Station in Florida to an altitude of 3,600 miles above the Earth's surface. The two-orbit, four-hour flight test will help engineers evaluate the systems critical to crew safety including the heat shield, parachute system and launch abort system. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Kim Shiflett

KSC-2014-2582

NASA Image and Video Library

2014-05-13

SAN DIEGO, Calif. – The Orion boilerplate test vehicle is being moved into a protective structure at the Mole Pier at the Naval Base San Diego in California for a simulated fit check of the hatch cover. The test vehicle is attached to the crew module recovery cradle. The Ground Systems Development and Operations Program, Lockheed Martin and the U.S. Navy are evaluating the hardware and processes for preparing the Orion crew module for Exploration Flight Test-1, or EFT-1, for overland transport from the naval base to NASA's Kennedy Space Center in Florida. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of the Orion is scheduled to launch later this year atop a Delta IV rocket from Cape Canaveral Air Force Station in Florida to an altitude of 3,600 miles above the Earth's surface. The two-orbit, four-hour flight test will help engineers evaluate the systems critical to crew safety including the heat shield, parachute system and launch abort system. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Kim Shiflett

KSC-2014-2581

NASA Image and Video Library

2014-05-13

SAN DIEGO, Calif. – The Orion boilerplate test vehicle is being moved into a protective structure at the Mole Pier at the Naval Base San Diego in California for a simulated fit check of the hatch cover. The test vehicle is attached to the crew module recovery cradle. The Ground Systems Development and Operations Program, Lockheed Martin and the U.S. Navy are evaluating the hardware and processes for preparing the Orion crew module for Exploration Flight Test-1, or EFT-1, for overland transport from the naval base to NASA's Kennedy Space Center in Florida. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of the Orion is scheduled to launch later this year atop a Delta IV rocket from Cape Canaveral Air Force Station in Florida to an altitude of 3,600 miles above the Earth's surface. The two-orbit, four-hour flight test will help engineers evaluate the systems critical to crew safety including the heat shield, parachute system and launch abort system. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Kim Shiflett

KSC-2014-2587

NASA Image and Video Library

2014-05-13

SAN DIEGO, Calif. – Inside a protective structure at the Mole Pier at the Naval Base San Diego in California, workers prepare for a simulated fit check of the hatch cover on the Orion boilerplate test vehicle. The test vehicle is secured on the crew module recovery cradle. The Ground Systems Development and Operations Program, Lockheed Martin and the U.S. Navy are evaluating the hardware and processes for preparing the Orion crew module for Exploration Flight Test-1, or EFT-1, for overland transport from the naval base to NASA's Kennedy Space Center in Florida. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of the Orion is scheduled to launch later this year atop a Delta IV rocket from Cape Canaveral Air Force Station in Florida to an altitude of 3,600 miles above the Earth's surface. The two-orbit, four-hour flight test will help engineers evaluate the systems critical to crew safety including the heat shield, parachute system and launch abort system. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Kim Shiflett

KSC-2014-2583

NASA Image and Video Library

2014-05-13

SAN DIEGO, Calif. – The Orion boilerplate test vehicle has been moved into a protective structure at the Mole Pier at the Naval Base San Diego in California for a simulated fit check of the hatch cover. The test vehicle is attached to the crew module recovery cradle. The Ground Systems Development and Operations Program, Lockheed Martin and the U.S. Navy are evaluating the hardware and processes for preparing the Orion crew module for Exploration Flight Test-1, or EFT-1, for overland transport from the naval base to NASA's Kennedy Space Center in Florida. Orion is the exploration spacecraft designed to carry astronauts to destinations not yet explored by humans, including an asteroid and Mars. It will have emergency abort capability, sustain the crew during space travel and provide safe re-entry from deep space return velocities. The first unpiloted test flight of the Orion is scheduled to launch later this year atop a Delta IV rocket from Cape Canaveral Air Force Station in Florida to an altitude of 3,600 miles above the Earth's surface. The two-orbit, four-hour flight test will help engineers evaluate the systems critical to crew safety including the heat shield, parachute system and launch abort system. For more information, visit http://www.nasa.gov/orion. Photo credit: NASA/Kim Shiflett

Finite-Rate Ablation Boundary Conditions for Carbon-Phenolic Heat-Shield

NASA Technical Reports Server (NTRS)

Chen, Y.-K.; Milos, Frank S.

2003-01-01

A formulation of finite-rate ablation surface boundary conditions, including oxidation, nitridation, and sublimation of carbonaceous material with pyrolysis gas injection, has been developed based on surface species mass conservation. These surface boundary conditions are discretized and integrated with a Navier-Stokes solver. This numerical procedure can predict aerothermal heating, chemical species concentration, and carbonaceous material ablation rate over the heatshield surface of re-entry space vehicles. In this study, the gas-gas and gas-surface interactions are established for air flow over a carbon-phenolic heatshield. Two finite-rate gas-surface interaction models are considered in the present study. The first model is based on the work of Park, and the second model includes the kinetics suggested by Zhluktov and Abe. Nineteen gas phase chemical reactions and four gas-surface interactions are considered in the present model. There is a total of fourteen gas phase chemical species, including five species for air and nine species for ablation products. Three test cases are studied in this paper. The first case is a graphite test model in the arc-jet stream; the second is a light weight Phenolic Impregnated Carbon Ablator at the Stardust re-entry peak heating conditions, and the third is a fully dense carbon-phenolic heatshield at the peak heating point of a proposed Mars Sample Return Earth Entry Vehicle. Predictions based on both finite-rate gas- surface interaction models are compared with those obtained using B' tables, which were created based on the chemical equilibrium assumption. Stagnation point convective heat fluxes predicted using Park's finite-rate model are far below those obtained from chemical equilibrium B' tables and Zhluktov's model. Recession predictions from Zhluktov's model are generally lower than those obtained from Park's model and chemical equilibrium B' tables. The effect of species mass diffusion on predicted ablation rate is also examined.

Development of FIAT-based Thermal Protection System Mass Estimating Relationships for NASA's Multi-Mission Earth Entry Concep

NASA Technical Reports Server (NTRS)

Sepka, Steven Andrew; Zarchi, Kerry Agnes; Maddock, Robert W.; Samareh, Jamshid A.

2011-01-01

Mass Estimating Relationships (MERs) have been developed for use in the Program to Optimize Simulated Trajectories II (POST2) as part of NASA's multi-mission Earth Entry Vehicle (MMEEV) concept. MERs have been developed for the thermal protection systems of PICA and of Carbon Phenolic atop Advanced Carbon-Carbon on the forebody and for SIRCA and Acusil II on the backshell. How these MERs were developed, the resulting equations, model limitations, and model accuracy are discussed herein.

Development Of FIAT-Based Thermal Protection System Mass Estimating Relationships For NASA's Multi-Mission Earth Entry Concept

NASA Technical Reports Server (NTRS)

Sepka, Steven; Trumble, Kerry A.; Maddock, Robert W.; Samareh, Jamshid

2012-01-01

Mass Estimating Relationships (MERs) have been developed for use in the Program to Optimize Simulated Trajectories II (POST2) as part of NASA's multi-mission Earth Entry Vehicle (MMEEV) concept. MERs have been developed for the thermal protection systems of PICA and of Carbon Phenolic atop Advanced Carbon-Carbon on the forebody and for SIRCA and Acusil II on the backshell. How these MERs were developed, the resulting equations, model limitations, and model accuracy are discussed herein.

77 FR 19642 - Low Enriched Uranium From France: Final Results of Antidumping Duty Changed Circumstances Review

Federal Register 2010, 2011, 2012, 2013, 2014

2012-04-02

... in U.S. customs territory, and (ii) are re-exported within eighteen (18) months of entry of the LEU... amend the scope of the order and to extend the deadline for the re-exportation of this sole LEU entry... transporter(s) while in U.S. customs territory, and (ii) are re-exported within eighteen (18) months of entry...

The Rewarding Challenge: Welcoming Re-Entry Women Students to the Small College.

ERIC Educational Resources Information Center

Midland Lutheran Coll., Fremont, NE.

This handbook was designed to offer a low-cost, local, and practical approach to working with re-entry women college students. It is intended for use by staff in small colleges (under 1,000 students) where women's centers and on-campus child care are rare and where the needs of re-entry students have not been adequately addressed. The information…

Investigation of the Landing Characteristics of a Re-entry Vehicle Having a Canted Multiple Air Bag Load Alleviation System

NASA Technical Reports Server (NTRS)

McGehee, John R.; Stubbs, Sandy M.

1963-01-01

An investigation was made to determine the landing-impact characteristics of a reentry vehicle having a multiple-air-bag load-alleviation system. A 1/16-scale dynamic model having four canted air bags was tested at flight-path angles of 90 degrees (vertical), 45 degrees, and 27 degrees for a parachute or paraglider vertical letdown velocity of 30 feet per second (full scale). Landings were made on concrete at attitudes ranging from -l5 degrees to 20 degrees. The friction coefficient between the model heat shield and the concrete was approximately 0.4. An aluminum diaphragm, designed to rupture at 10.8 pounds per square inch gage, was used to maintain initial pressure in the air bags for a short time period.

Journal of Chinese Society of Astronautics (Selected Articles),

DTIC Science & Technology

1983-03-10

Graphics Disclaimer...................... ..... .. . .. .. . . ... Calculation of Minimum Entry Heat Transfer Shape of a Space * Vehicle , by, Zhou Qi...the best quality copy available. ..- ii CALCULATION OF MINIMUM ENTRY HEAT TRANSFER SHAPE OF A SPACE VEHICLE Zhou Qi cheng ABSTRACT This paper dealt...entry heat transfer shape under specified fineness ratio and total vehicle weight conditions could be obtained using a variational method. Finally, the

Research on the water-entry attitude of a submersible aircraft.

PubMed

Xu, BaoWei; Li, YongLi; Feng, JinFu; Hu, JunHua; Qi, Duo; Yang, Jian

2016-01-01

The water entry of a submersible aircraft, which is transient, highly coupled, and nonlinear, is complicated. After analyzing the mechanics of this process, the change rate of every variable is considered. A dynamic model is build and employed to study vehicle attitude and overturn phenomenon during water entry. Experiments are carried out and a method to organize experiment data is proposed. The accuracy of the method is confirmed by comparing the results of simulation of dynamic model and experiment under the same condition. Based on the analysis of the experiment and simulation, the initial attack angle and angular velocity largely influence the water entry of vehicle. Simulations of water entry with different initial and angular velocities are completed, followed by an analysis, and the motion law of vehicle is obtained. To solve the problem of vehicle stability and control during water entry, an approach is proposed by which the vehicle sails with a zero attack angle after entering water by controlling the initial angular velocity. With the dynamic model and optimization research algorithm, calculation is performed, and the optimal initial angular velocity of water-entry is obtained. The outcome of simulations confirms that the effectiveness of the propose approach by which the initial water-entry angular velocity is controlled.

Remote Imaging of Exploration Flight Test-1 (EFT-1) Entry Heating Risk Reduction

NASA Technical Reports Server (NTRS)

Schuster, David M.; Horvath, Thomas J.; Schwartz, Richard J.

2016-01-01

A Measure of Performance (MOP) identified with an Exploration Flight Test-1 (EFT-1) Multi- Purpose Crew Vehicle (MPCV) Program Flight Test Objective (FTO) (OFT1.091) specified an observation during reentry though external ground-based or airborne assets with thermal detection capabilities. The objective of this FTO was to be met with onboard Developmental Flight Instrumentation (DFI), but the MOP for external observation was intended to provide complementary quantitative data and serve as a risk reduction in the event of anomalous DFI behavior (or failure). Mr. Gavin Mendeck, the Entry, Descent, and Landing (EDL) Phase Engineer for the MPCV Program (Vehicle Integration Office/Systems & Mission Integration) requested a risk-reduction assessment from the NASA Engineering and Safety Center (NESC) to determine whether quantitative imagery could be obtained from remote aerial assets to support the external observation MOP. If so, then a viable path forward was to be determined, risks identified, and an observation pursued. If not, then the MOP for external observation was to be eliminated.

Sample Return Propulsion Technology Development Under NASA's ISPT Project

NASA Technical Reports Server (NTRS)

Anderson, David J.; Dankanich, John; Hahne, David; Pencil, Eric; Peterson, Todd; Munk, Michelle M.

2011-01-01

Abstract In 2009, the In-Space Propulsion Technology (ISPT) program was tasked to start development of propulsion technologies that would enable future sample return missions. Sample return missions can be quite varied, from collecting and bringing back samples of comets or asteroids, to soil, rocks, or atmosphere from planets or moons. As a result, ISPT s propulsion technology development needs are also broad, and include: 1) Sample Return Propulsion (SRP), 2) Planetary Ascent Vehicles (PAV), 3) Multi-mission technologies for Earth Entry Vehicles (MMEEV), and 4) Systems/mission analysis and tools that focuses on sample return propulsion. The SRP area includes electric propulsion for sample return and low cost Discovery-class missions, and propulsion systems for Earth Return Vehicles (ERV) including transfer stages to the destination. Initially the SRP effort will transition ongoing work on a High-Voltage Hall Accelerator (HIVHAC) thruster into developing a full HIVHAC system. SRP will also leverage recent lightweight propellant-tanks advancements and develop flight-qualified propellant tanks with direct applicability to the Mars Sample Return (MSR) mission and with general applicability to all future planetary spacecraft. ISPT s previous aerocapture efforts will merge with earlier Earth Entry Vehicles developments to form the starting point for the MMEEV effort. The first task under the Planetary Ascent Vehicles (PAV) effort is the development of a Mars Ascent Vehicle (MAV). The new MAV effort will leverage past MAV analysis and technology developments from the Mars Technology Program (MTP) and previous MSR studies. This paper will describe the state of ISPT project s propulsion technology development for future sample return missions.12

Thermochemical Ablation Analysis of the Orion Heatshield

NASA Technical Reports Server (NTRS)

Sixel, William

2015-01-01

The Orion Multi-Purpose Crew Vehicle will one day carry astronauts to the Moon and beyond, and Orion's heatshield is a critical component in ensuring their safe return to Earth. The Orion heatshield is the structural component responsible for absorbing the intense heating environment caused by re-entry to Earth's atmosphere. The heatshield is primarily composed of Avcoat, an ablative material that is consumed during the re-entry process. Ablation is primarily characterized by two processes: pyrolysis and recession. The decomposition of in-depth virgin material is known as pyrolysis. Recession occurs when the exposed surface of the heatshield reacts with the surrounding flow. The Orion heatshield design was changed from an individually filled Avcoat honeycomb to a molded block Avcoat design. The molded block Avcoat heatshield relies on an adhesive bond to keep it attached to the capsule. In some locations on the heatshield, the integrity of the adhesive bond cannot be verified. For these locations, a mechanical retention device was proposed. Avcoat ablation was modelled in CHAR and the in-depth virgin material temperatures were used in a Thermal Desktop model of the mechanical retention device. The retention device was analyzed and shown to cause a large increase in the maximum bondline temperature. In order to study the impact of individual ablation modelling parameters on the heatshield sizing process, a Monte Carlo simulation of the sizing process was proposed. The simulation will give the sensitivity of the ablation model to each of its input parameters. As part of the Monte Carlo simulation, statistical uncertainties on material properties were required for Avcoat. Several properties were difficult to acquire uncertainties for: the pyrolysis gas enthalpy, non-dimensional mass loss rate (B´c), and Arrhenius equation parameters. Variability in the elemental composition of Avcoat was used as the basis for determining the statistical uncertainty in pyrolysis gas enthalpy and B´c. A MATLAB program was developed to allow for faster, more accurate and automated computation of Arrhenius reaction parameters. These parameters are required for a material model to be used in the CHAR ablation analysis program. This MATLAB program, along with thermogravimetric analysis (TGA) data, was used to generate uncertainties on the Arrhenius parameters for Avcoat. In addition, the TGA fitting program was developed to provide Arrhenius parameters for the ablation model of the gap filler material, RTV silicone.

Mission Sizing and Trade Studies for Low Ballistic Coefficient Entry Systems to Venus

NASA Technical Reports Server (NTRS)

Dutta, Soumyo; Smith, Brandon; Prabhu, Dinesh; Venkatapathy, Ethiraj

2012-01-01

The U.S and the U.S.S.R. have sent seventeen successful atmospheric entry missions to Venus. Past missions to Venus have utilized rigid aeroshell systems for entry. This rigid aeroshell paradigm sets performance limitations since the size of the entry vehicle is constrained by the fairing diameter of the launch vehicle. This has limited ballistic coefficients (beta) to well above 100 kg/m2 for the entry vehicles. In order to maximize the science payload and minimize the Thermal Protection System (TPS) mass, these missions have entered at very steep entry flight path angles (gamma). Due to Venus thick atmosphere and the steep-gamma, high- conditions, these entry vehicles have been exposed to very high heat flux, very high pressures and extreme decelerations (upwards of 100 g's). Deployable aeroshells avoid the launch vehicle fairing diameter constraint by expanding to a larger diameter after the launch. Due to the potentially larger wetted area, deployable aeroshells achieve lower ballistic coefficients (well below 100 kg/m2), and if they are flown at shallower flight path angles, the entry vehicle can access trajectories with far lower decelerations (50-60 g's), peak heat fluxes (400 W/cm2) and peak pressures. The structural and TPS mass of the shallow-gamma, low-beta deployables are lower than their steep-gamma, high-beta rigid aeroshell counterparts at larger diameters, contributing to lower areal densities and potentially higher payload mass fractions. For example, at large diameters, deployables may attain aeroshell areal densities of 10 kg/m2 as opposed to 50 kg/m2 for rigid aeroshells. However, the low-beta, shallow-gamma paradigm also raises issues, such as the possibility of skip-out during entry. The shallow-gamma could also increase the landing footprint of the vehicle. Furthermore, the deployable entry systems may be flexible, so there could be fluid-structure interaction, especially in the high altitude, low-density regimes. The need for precision in guidance, navigation and control during entry also has to be better understood. This paper investigates some of the challenges facing the design of a shallow-gamma, low-beta entry system.

Orbital transfer vehicle concept definition and systems analysis study. Volume 11: Study extension 2 results

NASA Technical Reports Server (NTRS)

Willcockson, W. H.

1988-01-01

Work conducted in the second extension of the Phase A Orbit Transfer Vehicle Concept Definition and Systems Analysis Study is summarized. Four major tasks were identified: (1) define an initial OTV program consistent with near term Civil Space Leadership Initiative missions; (2) develop program evolution to long term advanced missions; (3) investigate the implications of current STS safety policy on an Aft Cargo Carrier based OTV; and (4) expand the analysis of high entry velocity aeroassist. An increased emphasis on the breath of OTV applications was undertaken to show the need for the program on the basis of the expansion of the nation's capabilities in space.

Combined Structural and Trajectory Control of Variable-Geometry Planetary Entry Systems

NASA Technical Reports Server (NTRS)

Quadrelli, Marco B.; Pellegrino, Sergio; Kwok, Kawai

2011-01-01

Some of the key challenges of planetary entry are to dissipate the large kinetic energy of the entry vehicle and to land with precision. Past missions to Mars were based on unguided entry, where entry vehicles carried payloads of less than 0.6 T and landed within 100 km of the designated target. The Mars Science Laboratory (MSL) is expected to carry a mass of almost 1 T to within 20 km of the target site. Guided lifting entry is needed to meet these higher deceleration and targeting demands. If the aerodynamic characteristics of the decelerator are variable during flight, more trajectory options are possible, and can be tailored to specific mission requirements. In addition to the entry trajectory modulation, having variable aerodynamic properties will also favor maneuvering of the vehicle prior to descent. For proper supersonic parachute deployment, the vehicle needs to turn to a lower angle of attack. One approach to entry trajectory improvement and angle of attack control is to embed a variable geometry decelerator in the design of the vehicle. Variation in geometry enables the vehicle to adjust its aerodynamic performance continuously without additional fuel cost because only electric power is needed for actuating the mechanisms that control the shape change. Novel structural and control concepts have been developed that enable the decelerator to undergo variation in geometry. Changing the aerodynamic characteristics of a flight vehicle by active means can potentially provide a mechanically simple, affordable, and enabling solution for entry, descent, and landing across a wide range of mission types, sample capture and return, and reentry to Earth, Titan, Venus, or Mars. Unguided ballistic entry is not sufficient to meet this more stringent deceleration, heating, and targeting demands. Two structural concepts for implementing the cone angle variation, a segmented shell, and a corrugated shell, have been presented.

Trajectory Design and Control for the Compton Gamma Ray Observatory Re-Entry

NASA Technical Reports Server (NTRS)

Hoge, Susan; Vaughn, Frank J., Jr.

2001-01-01

The Compton Gamma Ray Observatory (CGRO) controlled re-entry operation was successfully conducted in June of 2000. The surviving parts of the spacecraft landed in the Pacific Ocean within the nominal impact target zone. The design of the maneuvers to control the trajectory to accomplish this re-entry presented several challenges. These challenges included the timing and duration of the maneuvers, propellant management, post-maneuver state determination, collision avoidance with other spacecraft, accounting for the break-up of the spacecraft into several pieces with a wide range of ballistic coefficients, and ensuring that the impact footprint would remain within the desired impact target zone in the event of contingencies. This paper presents the initial re-entry trajectory design and traces the evolution of that design into the maneuver sequence used for the re-entry. The paper also discusses the spacecraft systems and operational constraints imposed on the trajectory design and the required modifications to the initial design based on those constraints. Data from the reentry operation are also presented.

An adaptive guidance algorithm for an aerodynamically assisted orbital plane change maneuver. M.S. Thesis

NASA Technical Reports Server (NTRS)

Blissit, J. A.

1986-01-01

Using analysis results from the post trajectory optimization program, an adaptive guidance algorithm is developed to compensate for density, aerodynamic and thrust perturbations during an atmospheric orbital plane change maneuver. The maneuver offers increased mission flexibility along with potential fuel savings for future reentry vehicles. Although designed to guide a proposed NASA Entry Research Vehicle, the algorithm is sufficiently generic for a range of future entry vehicles. The plane change analysis provides insight suggesting a straight-forward algorithm based on an optimized nominal command profile. Bank angle, angle of attack, and engine thrust level, ignition and cutoff times are modulated to adjust the vehicle's trajectory to achieve the desired end-conditions. A performance evaluation of the scheme demonstrates a capability to guide to within 0.05 degrees of the desired plane change and five nautical miles of the desired apogee altitude while maintaining heating constraints. The algorithm is tested under off-nominal conditions of + or -30% density biases, two density profile models, + or -15% aerodynamic uncertainty, and a 33% thrust loss and for various combinations of these conditions.

A Computer Based Data Management System for Automating the Air Force Vehicle Master Plan

DTIC Science & Technology

1989-09-01

and columns -- but a much more sophisticated approach defining the relations among the data. Dr. Edgar F . Codd , who first proposed the relational...39 f . Vehicle Types Screen ... .......... 41 7. NSN Selection Screen ... .......... 41 8. NSN Retry Screen ..... ............ 9. F:ve-Year Outlook...had a single source o: inormation on the vehicle fleet, to be used in deve- uctn..: f .. ng and prioratizing the vehicle program- re~suireo to meet the

M2-F1 in flight on tow line

NASA Technical Reports Server (NTRS)

1964-01-01

The M2-F1 Lifting Body is seen here under tow at the Flight Research Center (later redesignated the Dryden Flight Research Center), Edwards, California. The wingless, lifting-body aircraft design was initially concieved as a means of landing an aircraft horizontally after atmospheric reentry. The absence of wings would make the extreme heat of re-entry less damaging to the vehicle. In 1962, Flight Research Center management approved a program to build a lightweight, unpowered lifting body as a prototype to flight test the wingless concept. It would look like a 'flying bathtub,' and was designated the M2-F1, the 'M' referring to 'manned' and 'F' referring to 'flight' version. It featured a plywood shell placed over a tubular steel frame crafted at Dryden. Construction was completed in 1963. The M2-F1 project had limited goals. They were to show that a piloted lifting body could be built, that it could not only fly but be controlled in flight, and that it could make a successful landing. While the M2-F1 did prove the concept, with a wooden fuselage and fixed landing gear, it was far from an operational spacecraft. The next step in the lifting-body development was to build a heavyweight, rocket-powered vehicle that was more like an operational lifting body, albeit one without the thermal protection system that would be needed for reentry into the atmosphere from space at near-orbital speeds. The first flight tests of the M2-F1 were over Rogers Dry Lake at the end of a tow rope attached to a hopped-up Pontiac convertible driven at speeds up to about 120 mph. These initial tests produced enough flight data about the M2-F1 to proceed with flights behind a NASA C-47 tow plane at greater altitudes. The C-47 took the craft to an altitude of 12,000 where free flights back to Rogers Dry Lake began. Pilot for the first series of flights of the M2-F1 was NASA research pilot Milt Thompson. Typical glide flights with the M2-F1 lasted about two minutes and reached speeds of 110 to l20 mph. More than 400 ground tows and 77 aircraft tow flights were carried out with the M2-F1. The success of Dryden's M2-F1 program led to NASA's development and construction of two heavyweight lifting bodies based on studies at NASA's Ames and Langley research centers--the M2-F2 and the HL-10, both built by the Northrop Corporation, and the U.S. Air Force's X-24 program. The Lifting Body program also heavily influenced the Space Shuttle program. The M2-F1 program demonstrated the feasibility of the lifting body concept for horizontal landings of atmospheric entry vehicles. It also demonstrated a procurement and management concept for prototype flight test vehicles that produced rapid results at very low cost (approximately $50,000, excluding salaries of government employees assigned to the project).

A Novel 'Cheese Wire' Technique for Stent Positioning Following Difficult Iliac Artery Subintimal Dissection and Aortic Re-Entry

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

Watkinson, A. F., E-mail: anthony.watkinson@rdeft.nhs.u

2009-07-15

Subintimal wire dissection is a well-established method for traversing difficult vascular occlusions. This technique relies on re-entry of the true lumen distal to the occlusion, which may be difficult in diseased vessels with significant calcification. This case report describes a novel 'cheese wire' technique to allow stent positioning without the use of proprietary re-entry devices.

A Mission Concept: Re-Entry Hopper-Aero-Space-Craft System on-Mars (REARM-Mars)

NASA Technical Reports Server (NTRS)

Davoodi, Faranak

2013-01-01

Future missions to Mars that would need a sophisticated lander, hopper, or rover could benefit from the REARM Architecture. The mission concept REARM Architecture is designed to provide unprecedented capabilities for future Mars exploration missions, including human exploration and possible sample-return missions, as a reusable lander, ascend/descend vehicle, refuelable hopper, multiple-location sample-return collector, laboratory, and a cargo system for assets and humans. These could all be possible by adding just a single customized Re-Entry-Hopper-Aero-Space-Craft System, called REARM-spacecraft, and a docking station at the Martian orbit, called REARM-dock. REARM could dramatically decrease the time and the expense required to launch new exploratory missions on Mars by making them less dependent on Earth and by reusing the assets already designed, built, and sent to Mars. REARM would introduce a new class of Mars exploration missions, which could explore much larger expanses of Mars in a much faster fashion and with much more sophisticated lab instruments. The proposed REARM architecture consists of the following subsystems: REARM-dock, REARM-spacecraft, sky-crane, secure-attached-compartment, sample-return container, agile rover, scalable orbital lab, and on-the-road robotic handymen.

STS 61C - CREW INSIGNIA

NASA Image and Video Library

1985-10-10

S85-41917 (October 1985) --- Columbia, which opened the era of the Space Transportation System with four orbital flight tests, is featured in re-entry in the emblem designed by the STS61-C crew to represent the seven team members who will man the vehicle for its seventh STS mission later this year. Gold lettering against black background honors the astronaut crew members on the delta pattern surrounding colorful re-entry shock waves, and the payload specialists are honored similarly below the sphere. Robert L. Gibson is mission commander; Charles F. Bolden, pilot; and mission specialists are George D. Nelson, Steven A. Hawley and Franklin R. Chang-Diaz. Payload specialists are Robert J. Cenker of RCA and Bill Nelson, U.S. Representative (D., Florida). Representations of the U.S. flag and the constellation Draco flank the emblem's core. The NASA insignia design for space shuttle flights is reserved for use by the astronauts and for other official use as the NASA Administrator may authorize. Public availability has been approved only in the forms of illustrations by the various news media. When and if there is any change in this policy, which is not anticipated, the change will be publicly announced. Photo credit: NASA

Structural Integrity Of Low-Velocity Impacted C/SIC Ceramic Matrix Composites

NASA Astrophysics Data System (ADS)

Knoche, R.; Drose, A.

2012-07-01

Carbon fibre reinforced silicon carbide (C/SiC) ceramic matrix composites (CMC) are most favourable for thermal protection systems & hot structures in re-entry vehicles since they offer superior heat resistance, high specific strength as well as a low coefficient of temperature expansion (CTE). To ensure the structural integrity of these C/SiC structures and thus mission safety all potential degradation effects during manufacturing and lifetime have to be considered. One of the most probable defects which may harm the structural integrity significantly can be caused by low-velocity impacts (LVI) which may occur during transportation and integration by e.g. dropping of tools. Thus the present study focuses on the residual mechanical and thermo-mechanical performance of C/SiC composites after being exposed to a low-velocity impact in terms of initial and residual mechanical performance, changes in microstructure, as well as thermo-mechanical performance through exposing specimens to multiple experimentally simulated re-entries. The results reveal the impact characteristics and damage mechanisms of C/SiC CMC exposed to a low-velocity impact and evidence the functional reliability as well as the damage tolerance of the C/SiC material investigated.

Initial experience with a dedicated coronary re-entry device for revascularization of chronic total occlusions.

PubMed

Whitlow, Patrick L; Lombardi, William L; Araya, Mario; Michael Wyman, R; Torres, Humberto; Dauvergne, Christian; Tsuchikane, Etsuo; Lansky, Alexandra; Thompson, Craig A

2012-11-01

The aim of this registry was to evaluate a new device designed to facilitate antegrade guidewire re-entry into the true lumen of a chronic total coronary occlusion (CTO) from the adjacent subintimal space. Successful recanalization of CTOs results in clinical improvement in appropriately selected patients. CTO intervention is time- and resource-consuming, and a simplified approach enabling antegrade guidewire re-entry into the distal true lumen might improve success. Patients with CTO and ischemia were entered into a prospective registry regardless of lesion characteristics. If wire manipulation resulted in subintimal wire entrapment, a new re-entry tool (a 2.5-mm flat subintimal balloon with two exit ports offset by 180°) was used as a platform to attempt guidewire penetration into the distal true lumen. The primary endpoint assessed was successful device-guided re-entry. Standard techniques were then utilized to open the CTO. In 40 consecutive CTO lesions attempted, 19 resulted in subintimal wire entrapment (mean occlusion length 44 mm). Sixteen of these 19 were successfully crossed with an antegrade guidewire into the distal true lumen using the new device (84%). One patient with unsuccessful re-entry was subsequently recanalized with a retrograde technique. All crossed lesions were stented (17/17), resulting in TIMI 3 flow without major complications. Two cases were unsuccessful. One patient had a grade I coronary perforation requiring no treatment. A new device to recanalize CTOs complicated by subintimal wire entrapment can be used successfully by experienced operators. Further study of this coronary re-entry device is ongoing. Copyright © 2011 Wiley Periodicals, Inc.

How do children with a chronic or long-term illness perceive their school re-entry after a period of homebound instruction?

PubMed

Boonen, H; Petry, K

2012-07-01

A considerable number of children are confronted with a chronic or long-term illness in their lives. For these children, absenteeism is problematic, because education plays a major role in stimulating their cognitive development and in promoting a sense of normalcy and psychosocial well-being. In the literature, a great deal of attention has been paid to school reintegration programmes, which try to counter the barriers that these children may face when they return to school. Another way of surmounting these barriers is through the use of homebound instruction, in which the educational process for the child is continued during the period of absence. Despite the growing awareness of the necessity of education for these children, there is still little empirical research available addressing programmes that facilitate school re-entry. The major goal of this study is to investigate how parents and their children with a chronic or long-term illness perceive school re-entry after a period of homebound instruction, by using a descriptive-explorative, multi-informant research design. Participants were 60 children and their parents who filled in a self-constructed questionnaire. Both parents and children perceived the period of homebound instruction, as well as their school re-entry, predominantly positively. Most of the children stated that they had been able to keep up with their subjects, and that they had good contact with their peers when they returned to school. According to parents, homebound instruction made a positive contribution to the school re-entry of their child. The current study is one of the first to explore the school re-entry of children with a chronic or long-term illness. According to both parents and children, the school re-entry process passed off positively. However, more research is needed with regard to the quality of education and the programmes aimed at facilitating school re-entry. © 2011 Blackwell Publishing Ltd.

Scratch2 prevents cell cycle re-entry by repressing miR-25 in postmitotic primary neurons.

PubMed

Rodríguez-Aznar, Eva; Barrallo-Gimeno, Alejandro; Nieto, M Angela

2013-03-20

During the development of the nervous system the regulation of cell cycle, differentiation, and survival is tightly interlinked. Newly generated neurons must keep cell cycle components under strict control, as cell cycle re-entry leads to neuronal degeneration and death. However, despite their relevance, the mechanisms controlling this process remain largely unexplored. Here we show that Scratch2 is involved in the control of the cell cycle in neurons in the developing spinal cord of the zebrafish embryo. scratch2 knockdown induces postmitotic neurons to re-enter mitosis. Scratch2 prevents cell cycle re-entry by maintaining high levels of the cycle inhibitor p57 through the downregulation of miR-25. Thus, Scratch2 appears to safeguard the homeostasis of postmitotic primary neurons by preventing cell cycle re-entry.

MS Garneau in his LES during re-entry preparations for STS-97

NASA Image and Video Library

2000-12-11

STS097-310-026 (11 December 2000) --- Astronaut Marc Garneau, mission specialist representing the Canadian Space Agency (CSA), is photographed in the launch and entry suit on the middeck of the Earth-orbiting Space Shuttle Endeavour prior to re-entry.

Trajectory and Aeroheating Environment Development and Sensitivity Analysis for Capsule-shaped Vehicles

NASA Technical Reports Server (NTRS)

Robinson, Jeffrey S.; Wurster, Kathryn E.

2006-01-01

Recently, NASA's Exploration Systems Research and Technology Project funded several tasks that endeavored to develop and evaluate various thermal protection systems and high temperature material concepts for potential use on the crew exploration vehicle. In support of these tasks, NASA Langley's Vehicle Analysis Branch generated trajectory information and associated aeroheating environments for more than 60 unique entry cases. Using the Apollo Command Module as the baseline entry system because of its relevance to the favored crew exploration vehicle design, trajectories for a range of lunar and Mars return, direct and aerocapture Earth-entry scenarios were developed. For direct entry, a matrix of cases was created that reflects reasonably expected minimum and maximum values of vehicle ballistic coefficient, inertial velocity at entry interface, and inertial flight path angle at entry interface. For aerocapture, trajectories were generated for a range of values of initial velocity and ballistic coefficient that, when combined with proper initial flight path angles, resulted in achieving a low Earth orbit either by employing a full lift vector up or full lift vector down attitude. For each trajectory generated, aeroheating environments were generated which were intended to bound the thermal protection system requirements for likely crew exploration vehicle concepts. The trades examined clearly pointed to a range of missions / concepts that will require ablative systems as well as a range for which reusable systems may be feasible. In addition, the results clearly indicated those entry conditions and modes suitable for manned flight, considering vehicle deceleration levels experienced during entry. This paper presents an overview of the analysis performed, including the assumptions, methods, and general approach used, as well as a summary of the trajectory and aerothermal environment information that was generated.

The RN-BSN Bridge Course: Transitioning the Re-Entry Learner.

ERIC Educational Resources Information Center

Huston, Carol; Shovein, Julia; Damazo, Becky; Fox, Sherry

2001-01-01

A 6-week bridge course designed to ease the transition of registered nurses into baccalaureate degree programs focused on critical thinking, learning styles, professional roles, values clarification, time management, and career planning. It also oriented students to Web Course Tools, used for distance learning. Outcomes included role and campus…

NASA aerodynamics program

NASA Technical Reports Server (NTRS)

Williams, Louis J.; Hessenius, Kristin A.; Corsiglia, Victor R.; Hicks, Gary; Richardson, Pamela F.; Unger, George; Neumann, Benjamin; Moss, Jim

1992-01-01

The annual accomplishments is reviewed for the Aerodynamics Division during FY 1991. The program includes both fundamental and applied research directed at the full spectrum of aerospace vehicles, from rotorcraft to planetary entry probes. A comprehensive review is presented of the following aerodynamics elements: computational methods and applications; CFD validation; transition and turbulence physics; numerical aerodynamic simulation; test techniques and instrumentation; configuration aerodynamics; aeroacoustics; aerothermodynamics; hypersonics; subsonics; fighter/attack aircraft and rotorcraft.

Intermediate eXperimental Vehicle Jettison Mechanism Engineering and Test

NASA Astrophysics Data System (ADS)

Caldirola, L.; Schmid, B.

2015-09-01

The IXV (Intermediate eXperimental Vehicle) is a project of the European Space Agency that aims to develop an autonomous atmospheric re-entry system. A flight model has been launched on a Vega rocket on the 11th of February 2015 and after descending from an altitude of 420km splashed down in the Pacific Ocean. In the frame of this project RUAG space has developed the entire cold structure and the mechanisms able to eject the panels closing the parachute and floatation balloons bays. Panels ejection allows respectively parachutes deployment, reducing the IXV re-entry speed from Mach 1.5 to few meters per second just before the splash down, and buoyancy balloons inflation which let the vehicle float on the sea surface until arrival of the recovery ship.Such panels and the relevant mechanisms had to be designed not only to guarantee the correct external aerodynamic shape needed for the flight performance, but also to provide enough stiffness and strength to the IXV structure, being capable of transfer high shear loads.Moreover the floatation doors design enclosed both the hold down and release mechanism, based on a non- explosive separation nut, and the jettison springs, therefore particular attention had to be put to prevent any damage to the panel during the release which could have potentially led to jamming of the panel itself which jeopardise the floatation balloon deployment. The chosen design was therefore based on a spherical joint, so that shear load can be withstand and bending moment on the jettison-able panels limited at the same time.Test activities have been performed at mechanism level for environmental and preliminary functional qualification, subsystem level, including dummy panel jettison and full scale IXV drop test, to complete the functional qualification and system level test to close qualification campaign.The purpose of this paper is to present the mechanism design and the activities performed to qualify at component and sub-system level the jettison mechanism of the floatation balloons doors.

Simulation-Based Analysis of Reentry Dynamics for the Sharp Atmospheric Entry Vehicle

NASA Technical Reports Server (NTRS)

Tillier, Clemens Emmanuel

1998-01-01

This thesis describes the analysis of the reentry dynamics of a high-performance lifting atmospheric entry vehicle through numerical simulation tools. The vehicle, named SHARP, is currently being developed by the Thermal Protection Materials and Systems branch of NASA Ames Research Center, Moffett Field, California. The goal of this project is to provide insight into trajectory tradeoffs and vehicle dynamics using simulation tools that are powerful, flexible, user-friendly and inexpensive. Implemented Using MATLAB and SIMULINK, these tools are developed with an eye towards further use in the conceptual design of the SHARP vehicle's trajectory and flight control systems. A trajectory simulator is used to quantify the entry capabilities of the vehicle subject to various operational constraints. Using an aerodynamic database computed by NASA and a model of the earth, the simulator generates the vehicle trajectory in three-dimensional space based on aerodynamic angle inputs. Requirements for entry along the SHARP aerothermal performance constraint are evaluated for different control strategies. Effect of vehicle mass on entry parameters is investigated, and the cross range capability of the vehicle is evaluated. Trajectory results are presented and interpreted. A six degree of freedom simulator builds on the trajectory simulator and provides attitude simulation for future entry controls development. A Newtonian aerodynamic model including control surfaces and a mass model are developed. A visualization tool for interpreting simulation results is described. Control surfaces are roughly sized. A simple controller is developed to fly the vehicle along its aerothermal performance constraint using aerodynamic flaps for control. This end-to-end demonstration proves the suitability of the 6-DOF simulator for future flight control system development. Finally, issues surrounding real-time simulation with hardware in the loop are discussed.

A hypersonic vehicle approach to planetary exploration

NASA Technical Reports Server (NTRS)

Murbach, Marcus S.

1993-01-01

An enhanced Mars network class mission using a lifting hypersonic entry vehicle is proposed. The basic vehicle, derived from a mature hypersonic flight system called SWERVE, offers several advantages over more conventional low L/D or ballistic entry systems. The proposed vehicle has greatly improved lateral and cross range capability (e.g., it is capable of reaching the polar regions during less than optimal mission opportunities), is not limited to surface target areas of low elevation, and is less susceptible to problems caused by Martian dust storms. Further, the integrated vehicle has attractive deployment features and allows for a much improved evolutionary path to larger vehicles with greater science capability. Analysis of the vehicle is aided by the development of a Mars Hypersonic Flight Simulator from which flight trajectories are obtained. Atmospheric entry performance of the baseline vehicle is improved by a deceleration skirt and transpiration cooling system which significantly reduce TPS (Thermal Protection System) and flight battery mass. The use of the vehicle is also attractive in that the maturity of the flight systems make it cost-competitive with the development of a conventional low L/D entry system. Finally, the potential application of similar vehicles to other planetary missions is discussed.