SCIENTIFIC AND TECHNICAL AEROSPACE REPORTS
A Biweekly Publication of the National Aeronautics and Space Administration
VOLUME 44, ISSUE 14 - JULY 18, 2006
15 LAUNCH VEHICLES AND LAUNCH OPERATIONS
Includes all classes of launch vehicles, launch/space vehicle systems, and boosters; and launch operations.
For related information see also 18 Spacecraft Design, Testing and Performance; and 20 Spacecraft Propulsion and Power.
20060019376 European Aeronautic Defence and Space Co. Airbus S.A., Toulouse, France
The CMOS Breakthrough for Space Optical Detection: Recent Advances and Short Term Perspectives
Saint-Pe, Olivier; Breart de Boisanger, Michel; Larnaudie, Franck; Tulet, Michel; Davancens, Robert; Magnan, Pierre; Martin Gonthier, Philippe; Jul 13, 2005; 11 pp.; In English; Original contains color illustrations Report No.(s): AD-A446234; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA446234; Avail.: CASI: A03, Hardcopy
Today, both CCD and CMOS sensors can be envisaged for nearly all visible sensors and instruments designed for space needs. Indeed, detectors built with both technologies allow excellent electro-optics performances to be reached, the selection of the most adequate device being driven by their functional and technological features and limits. The first part of the paper presents electro-optics characterisation results of CMOS image sensors (CIS) built with an optimised CMOS process, demonstrating the large improvements of CIS electro-optics performances. The second part reviews the advantages of CMOS technology for space applications, illustrated by examples of CIS developments performed by EADS Astrium and Supa ro/CIMI for current and short term coming space programs. DTIC
Aerospace Environments; CMOS; Detection; Optical Measurement
20060019377 Rutherford Appleton Lab., Chilton, UK
Development of a Large-Format Science-Grade CMOSActive Pixel Sensor, for Extreme Ultra Violet Spectroscopy and Imaging in Space Science
Waltham, N R; Prydderch, M; Mapson-Menard, H; Morrissey, Q; Turchetta, R; Pool, P; Harris, A; Jul 13, 2005; 13 pp.; In English; Original contains color illustrations Report No.(s): AD-A446235; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA446235; Avail.: CASI: A03, Hardcopy
We describe our programme to develop a large-format science-grade CMOS active pixel sensor for future space science missions, and in particular an extreme ultra-violet spectrograph for solar physics studies on ESA's Solar Orbiter. Our route to EUV sensitivity relies on adapting the back-thinning and rear-illumination techniques first developed for CCD sensors. So far we have designed and tested a 4k x 3k 5-micrometer pixel sensor fabricated on a 0.25-micrometer CMOS imager process. Wafer samples of these sensors have been thinned by e2v technologies with the aim of obtaining good sensitivity at EUV wavelengths. We present our results to date, and plans for a new sensor of 2k x 2k 10-micrometer pixels to be fabricated on a 0.35-micrometer CMOS process. DTIC
CMOS; Images; Imaging Techniques; Pixels; Spectroscopy; Ultraviolet Spectroscopy
20060019478 European Aeronautic Defence and Space Co. Airbus S.A., Toulouse, France
Validation of a Wireless Optical Layer for On-Board Data Communications
Pelissou, Patrice; Santammaria, Asuncion; Hernandez, Francisco J; Plancke, Patrck; Jul 13, 2005; 17 pp.; In English; Original contains color illustrations Report No.(s): AD-A446386; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA446386; Avail.: CASI: A03, Hardcopy
This study was conducted in 2003/2004. The objective was to assess the feasibility of an intra-satellite communication using a wireless optical network. The study includes: The review of existing technologies; the space and spacecraft environment, and the design, manufacturing and test of demonstrators. DTIC
Communication Networks; Data Transmission; Optical Communication; Wireless Communication
20060019526 Air Force Research Lab., Edwards AFB, CA USA
U.S. Air Force Basic Research in Weakly Ionized Gasdynamics
Tishkoff, Julian; Jun 25, 2004; 24 pp.; In English; Original contains color illustrations Report No.(s): AD-A446458; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA446458; Avail.: CASI: A03, Hardcopy
RESEARCH OBJECTIVE: Understand, predict, and control weakly ionized flows to revolutionize the performance of aerospace vehicles. DTIC
Gas Dynamics; Gas Flow; Ionized Gases; Military Technology; Research and Development
20060019626 Air Force Inst. of Tech., Wright-Patterson AFB, OH USA
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Discrete Event Simulation Model of the Ground Maintenance Operations Cycle of a Reusable Launch Vehicle
Pope III, John T; Mar 2006; 249 pp.; In English; Original contains color illustrations Report No.(s): AD-A446392; AFIT/GLM/ENS/06-14; No Copyright; Avail.: Defense Technical Information Center (DTIC)
The Air Force uses a family of expendable launch vehicles to meet its spacelift needs. Unfortunately, this method is not responsive: months of preparation are typically required and launch costs are high. Consequently, the Air Force seeks a reusable military launch vehicle that can be launched inexpensively and quickly regenerated between flights. Air Force Research Laboratory personnel desire a tool to help evaluate candidate designs and perform tradeoff studies necessary to acquire a launch vehicle that will achieve Air Force goals. The objective of this research was first to develop a conceptual model of maintenance operations needed to regenerate a launch vehicle between flights, and then to translate this conceptual model into a discrete event simulation tool. This research was accomplished concurrently with Stiegelmeier, who focused on vehicle prelaunch operations. DTIC
Computerized Simulation; Ground Operational Support System; Launch Vehicles; Maintenance; Mathematical Models;Reusable Launch Vehicles; Simulation
20060019641 Princeton Univ., NJ USA
Weakly Ionized Plasmas and MHD for Enhanced Performance of Hypersonic Vehicles
Macheret, Sergey; Shneider, Mikhail; Miles, Richard; Jun 22, 2004; 37 pp.; In English; Original contains color illustrations Report No.(s): AD-A446523; No Copyright; Avail.: CASI: A03, Hardcopy
Aerospace Applications of Weakly Ionized Plasmas: * Power generation using MHD * Use of power to control aerodynamics and propulsion: (1) Surface plasmas for separation and turbulent transition control (virtual shapes) (2) Virtual shapes created by off-body energy addition for drag reduction, steering, shock control, flow turning (3) Plasma-assisted combustion. * Power extraction from one region and its use in another region (MHD bypass) * Dual-use MHD devices (both power generation and flow control): (1) Forces created by magnetic and electric fields acting on charged particles (transferred to neutral gas by collisions) (2) Ionization level per se is not critical if plasmas are used as a means of delivering energy to the flow (3) Ionization is critical in MHD power generation and flow control, and in cold-plasma generation of radicals 4) At high T (reentry, scramjet combustor) -- thermal ionization with alkali seed (5) At low T, artificial ionization is eeded, and the ionization cost determines design and performance (6) Similar to ionization, cold plasma generation of chemically active species for combustion can have considerable energy cost (7) Both energy addition and extraction result in flow heating and losses of total pressure and (if in propulsion flowpath) thrust DTIC
Hypersonic Vehicles; Ionized Gases; Magnetohydrodynamics; Plasmas (Physics)
20060019697 Centre National de la Recherche Scientifique, Orsay, France
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Fusion Reactions and Matter-Antimatter Annihilation for Space Propulsion
Deutsch, Claude; Jul 13, 2005; 42 pp.; In English Report No.(s): AD-A446638; No Copyright; Avail.: CASI: A03, Hardcopy
Magnetic confinement fusion (MCF) and inertial confinement fusion (ICF are critically contrasted in the context of far-distant travels throughout solar system. Both are shown to potentially display superior capabilities for vessel maneuvring at high speed, which are unmatched by standard cryogenic propulsion (SCP). Costs constraints seem less demanding than for ground-based power plants. Main issue is the highly problematic takeoff from earth, in view of safety hazards concomitant to ratioactive spills in case of emergency. So, it is recommended to assemble the given powered vessel at high earth altitude ~ 700 km, above upper atmosphere. Fusion propulsion is also compared to fission powered one, which secures a factor of two improvement over SCP. As far a specific impulse (sec) is considered, one expects 500-3000 from fission and as much as 104 - 105 from fusion through deuterium-tritium. Next, we turn attention to the most performing fusion reaction, i.e. protonantiproton annihilation with specific impulse ~ 103 - 106 and thrust-to-weight ratio ~ 10-3 - 1. Production and costs are timely reviewed. The latter could drop by 4 orders of magnitude, which is possible with successful MCF or ICF. Appropriate vessel designs will be presented for fusion as well as for antimatter propulsion. In particuclar, ICAN-II project to Mars in 30 days with fusion catalyzed by 140 ng of antiprotons will be detailed (specific impulse ~ 13500 sec). DTIC
Annihilation Reactions; Antimatter; Matter (Physics); Nuclear Propulsion; Propulsion; Spacecraft Propulsion
20060019758 European Aeronautic Defence and Space Co., Les Mureaux, France
Potential Applications of Micro and Nano Technologies on Space Transportation Systems
Coumar, Oudea; Jul 13, 2005; 13 pp.; In English; Original contains color illustrations Report No.(s): AD-A446756; No Copyright; Avail.: CASI: A03, Hardcopy
This paper highlights the current state of art of Micro and Nano technologies and also describes the Research and Developments activities going on at EADS-Space transportation with CNES and ESA. A diverse range of MEMS COTS/MOTS (MEMS Commercial off The shelf) are available in the markets that are primarily applicable to Space Transportation vehicles particularly on the Telemetry Sub systems with some specific upgrading activities. For the 'End-User' reliability assurance is an integral part of the space qualification process. The testing methods/protocols are also very device dependent EADS-ET has participated with CNES ESA and research labs tor the development of PoF (Physics of Failure) modelling on reliability prediction. In order to apply MNT's (Micro and Nano Technologies) in the space domain launchers, satellites, probes,) validation of these devices under space launchers environment is essential. Flight opportunities are a key issue since technologies not qualified in-orbit are usually seen as risky and are discarded by the Space Industry. There are some flight opportunities tor MNT in-orbit demonstration with Ariane 5 launchers. For that we propose to develop a recurrent Technology Test Bed (TTB) which could offer standard interfaces with technology experiments. The target in short term (5 years) is the development of Low cost telemetry sub-systems' by using smart MEMS sensors. For that, we started the following works for coming three years (2005-2007): Phase 1: Spatialization (up grading), qualification and adaptation of MEMS COTS tor a flight demonstrator on Ariane 5 launchers environments Phase 2: Realization of test bed to make flight demonstration of MNTs for space transportation use Phase 3: Study of 'Low cost telemetry sub-systems' by using smart MEMS sensors. DTIC
Aerospace Engineering; Microelectromechanical Systems; Nanotechnology; Space Transportation System
20060019801 Air Force Research Lab., Kirkland AFB, NM USA
Modeling and Analysis of a Robust Thermal Control System Based on Forced Convection Thermal Switches
Williams, Andrew D; Palo, Scott E; Jan 2005; 12 pp.; In English; Original contains color illustrations Report No.(s): AD-A446849; AFRL-VS-PS-TP-2006-1010; No Copyright; Avail.: CASI: A03, Hardcopy
There is a critical need, not just in the Department of Defense (DOD) but the entire space industry, to reduce the development time and overall cost of satellite missions. To that end, the DOD is actively pursuing the capability to reduce the deployment time of a new system from years to weeks or even days. The goal is to provide the advantages space affords not just to the strategic planner but also to the battlefield commanders. One of the most challenging aspects of this problem is the satellite's thermal control system (TCS). Traditionally the TCS must be vigorously designed, analyzed, tested, and optimized from the ground up for every satellite mission. This reinvention of the wheel is costly and time intensive. The next generation satellite TCS must be modular and scalable in order to cover a wide range of applications, orbits, and mission requirements. To meet these requirements a robust thermal control system utilizing forced convection thermal switches was investigated. The problem was investigated in two separate stages. The first focused on the overall design of the bus. The second stage focused on the overarching bus architecture and the design impacts of employing a thermal switch based TCS design. For the hot case, the fan provided additional cooling to increase the heat transfer rate of the subsystem. During the cold case, the result was a significant reduction in survival heater power. DTIC
Forced Convection; Military Spacecraft; Switches; Temperature Control
20060020103 Government Accountability Office, Washington, DC, USA
Space Acquisitions: DOD Needs Additional Knowledge as it Embarks on a New Approach for Transformational Satellite Communications System
May 2006; 38 pp.; In English Report No.(s): PB2006-112263; GAO-06-537; No Copyright; Avail.: CASI: A03, Hardcopy
The Department of Defense (DOD) wants to create a networked force where soldiers and systems are able to operate together seamlessly. To help facilitate this transformation, DOD began the Transformational Satellite Communications System (TSAT) program in January 2004. We reported in 2003 that TSAT was about to begin without sufficiently mature technology. In this report, at your request, we followed up with an assessment of (1) how the TSAT program is progressing, and (2) whether the program is using an acquisition approach that will provide the knowledge needed to enter product development. NTIS
Communication Satellites; Military Spacecraft; Satellite Communication
20060020107
High Power Electric Propulsion System for NEP (systemes propulsifs electriques de forte puissance pour propulsion nucleo-electrique)
Koppel, Christophe R; Duchemin, Olivier; Valentian, Dominique; Jul 13, 2005; 15 pp.; In English; Original contains color illustrations Report No.(s): AD-A446639; No Copyright; Avail.: CASI: A03, Hardcopy
Recent US initiatives in Nuclear Propulsion lend themselves naturally to raising the question of the assessment of various options and particularly to propose the High Power Electric Propulsion Subsystem (HPEPS) for the Nuclear Electric Propulsion (NEP). The purpose of this paper is to present the guidelines for the HPEPS with respect to the mission to Mars, for automatic probes as well as for manned missions. Among the various options, the technological options and the trajectory options are pointed out. The consequences of the increase of the electrical power of a thruster are first an increase of the thrust itself, but also, as a general rule, an increase of the thruster performance due to its higher efficiency. The drawback is the increase of the thruster's size. Due to the large mass of gas needed to perform the foreseen missions, the right selection of the propellant feeding the thruster is of prime importance. The paper presents a discussion on the thruster specific impulse increase that is sometime considered an increase of the main system performances parameter, but that induces for all electric propulsion systems drawbacks in the system power and mass design that are proportional to the thruster specific power increase (kW/N). The compatibility with NEP systems that implies orbiting a sizeable nuclear reactor and a power generation system capable of converting thermal into electric power, with minimum mass and volumes fitting in with Ariane 5 or the Space Shuttle bay, is assessed. DTIC
Electric Propulsion; Propellants; Propulsion
20060020188 NASA Marshall Space Flight Center, Huntsville, AL, USA
The Vehicle Integrated Performance Analysis Experience: Reconnecting With Technical Integration
McGhee, D. S.; January 2006; 28 pp.; In English; Original contains color illustrations Report No.(s): NASA/TM-2006-214271; M-1156; No Copyright; Avail.: CASI: A03, Hardcopy
Very early in the Space Launch Initiative program, a small team of engineers at MSFC proposed a process for performing system-level assessments of a launch vehicle. Aimed primarily at providing insight and making NASA a smart buyer, the Vehicle Integrated Performance Analysis (VIPA) team was created. The difference between the VIPA effort and previous integration attempts is that VIPA a process using experienced people from various disciplines, which focuses them on a technically integrated assessment. The foundations of VIPA s process are described. The VIPA team also recognized the need to target early detailed analysis toward identifying significant systems issues. This process is driven by the T-model for technical integration. VIPA s approach to performing system-level technical integration is discussed in detail. The VIPA process significantly enhances the development and monitoring of realizable project requirements. VIPA s assessment validates the concept s stated performance, identifies significant issues either with the concept or the requirements, and then reintegrates these issues to determine impacts. This process is discussed along with a description of how it may be integrated into a program s insight and review process. The VIPA process has gained favor with both engineering and project organizations for being responsive and insightful Author
Reliability Analysis; Systems Integration; Spacecraft Launching; Launch Vehicles; Identifying
20060021063 Naval Research Lab., Monterey, CA USA
Aerosol Optical Depth Analysis with NOAA GOES and POES in the Western Atlantic
Kuciauskas, Arunas P; Durkee, Philip A; Westphal, Douglas L; Feb 17, 2006; 41 pp.; In English; Original contains color illustrations Contract(s)/Grant(s): N00039-05-WXF-R151 Report No.(s): AD-A447536; NRL/MR/7540-06-8870; No Copyright; Avail.: CASI: A03, Hardcopy
An aerosol optical depth retrieval algorithm in the visible wavelengths for the NOAA POES AVHRR and GOES-8 visible imager is presented for the cloud free, marine atmosphere. The algorithm combines linearized single-scatter theory with an estimate of surface reflectance. Phase functions are parameterized using an aerosol size distribution model and the ratio of radiance values measured in channels 1 and 2 of the AVHRR. Retrieved satellite aerosol optical depth (AOD) is compared to three land-based sun photometer stations located on islands in the western Atlantic during July and September, 2001. GOES-8 channel 1 (visible wavelength) radiance values were initially calibrated using techniques developed by Rao and Zhang (1999). Additional corrections to the channel 1 GOES-8 radiances were made by applying a linear offset factor obtained during the experimental time period through comparison with AVHRR radiances. The results for the GOES-derived AOD compare favorably to the Aerosol Robotic NETwork (AERONET) AOD values. For both NOAA and GOES data, the comparison dataset has a correlation coefficient of 0.67 with a standard error of 0.7. During dusty conditions with corresponding higher AOD levels greater than or equal to 0.25, the general trend was for the satellite-derived AOD values to underestimate AERONET AOD values. Within these conditions, the scattering phase function pattern deviated from the expected pattern, especially between the scattering angles of 140 degrees to 180 degrees. Overall, the more accurate calculations of AOD occurred over scatter angles between 140 degrees to 150 degrees and 170 degrees to 180 degrees. DTIC
Aerosols; Atlantic Ocean; Depth; Optical Thickness
20060021067 Surrey Univ., Guildford, UK
Sizing/Optimization of a Small Satellite Energy Storage and Attitude Control System
Richie, David J; Lappas, Vaios J; Palmer, Phil L; Apr 14, 2006; 16 pp.; In English; Original contains color illustrations Report No.(s): AD-A447543; CI04-1763; No Copyright; Avail.: CASI: A03, Hardcopy
The recent advent of miniature single gimbal control moment gyroscopes has spawned interest in variable speed versions for combined energy storage and attitude control systems on small satellites. Although much has been studied on the theory behind such a system, little has been done In optimally sizing these actuators for small satellite applications. Therefore this paper investigates the fundamental design concepts, optimal sizing, and mission benefits for these actuators. Given a set of small satellite agility and energy storage requirements, an optimal, nonlinear programming method is applied to this problem. DTIC
Artificial Satellites; Attitude Control; Energy Storage; Satellite Attitude Control
Source: NASA
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