SCIENTIFIC AND TECHNICAL AEROSPACE REPORTS
A Biweekly Publication of the National Aeronautics and Space Administration
VOLUME 44, ISSUE 13 - JULY 5, 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.
20060016593 Collier Research and Development Corp., Hampton, VA USA
Consistent Structural Integrity and Efficient Certification with Analysis. Volume 2: Detailed Report on Innovative Research Developed, Applied, and Commercially Available
Collier, Craig; May 2005; 252 pp.; In English Contract(s)/Grant(s): F33615-02-C-3216; Proj-A01V Report No.(s): AD-A444113; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA444113; Avail.: CASI: A12, Hardcopy
This SBIR report maintains that reliable pretest predictions and efficient certification are suffering from inconsistent structural integrity that is prevalent throughout a project's design maturity. Eight primary inconsistencies practiced in aerospace structural analysis are identified. This SBIR proposes solutions for these inconsistencies and documents software implementation and real world examples. Volume 2 looks at four example failure analysis correlations to test and describes new analysis methods developed for composite bonded joint stress analysis and failure and composite material stress analysis and failure. DTIC
Aerospace Systems; Certification; Stress Analysis; Structural Failure
20060016595 Air Force Research Lab., Edwards AFB, CA USA
Performance Testing of a Microfabricated Propulsion System for Nanosatellite Applications (POSTPRINT)
Ketsdever, Andrew D; Lee, Riki H; Lilly, Taylor C; Apr 22, 2005; 11 pp.; In English Contract(s)/Grant(s): Proj-5026 Report No.(s): AD-A444117; AFRL-PR-ED-JA-2005-132; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA444117; Avail.: CASI: A03, Hardcopy
There is a growing interest in the use of micro and nanosatellites within the aerospace community. Constellations of small satellites may eventually replace much larger, single function spacecraft as a cheaper, more flexible alternative. Microtechnologies will be required to enable small satellite missions including efficient, low-cost propulsion systems for maneuvering. A MEMS fabricated propulsion system has been developed for maneuvers on an upcoming University nanosatellite mission. The Free Molecule Micro-Resistojet (FMMR) is an electrothermal propulsion system designed for on-orbit maneuvers of nanosatellites, which are defined as spacecraft with an initial mass less than 10 kg. The FMMR has been tested using a torsion force balance to assess its performance using a variety of propellants including helium, argon, nitrogen and carbon dioxide. The experimental performance results compare favorably with results obtained from gas kinetic theory, which were used in the design phase to estimate the thruster's performance. The measured performance of the FMMR in this study has proven to be adequate to perform attitude control maneuvers for the University nanosatellite mission. DTIC
Artificial Satellites; Kinetic Theory; Microelectromechanical Systems; Nanosatellites; Nanotechnology; Performance Tests; Propulsion
20060016656 Maryland Univ., College Park, MD USA
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Feedback Stabilization via Center Manifold Reduction with Application to Tethered Satellites
Liaw, Der-Cherng; Jan 1990; 225 pp.; In English Report No.(s): AD-A444245; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA444245; Avail.: CASI: A10, Hardcopy
Center manifold reduction has recently been introduced as a tool for design of stabilizing control laws for nonlinear systems in critical cases. In this dissertation, the center manifold approach is elaborated for general such nonlinear systems in several critical cases of interest, and the results are applied to the control of tethered satellite systems (TSS). In addition, to address stability questions for satellite deployment via TSS, we obtain new results in finite-time stability theory. The critical cases considered in the general feedback stabilization studies include the cases in which the system linearization possesses a simple zero eigenvalue (of multiplicity one or two), a pair of simple pure imaginary eigenvalues, one zero eigenvalues along with a pair of simple pure imaginary eigenvalues, and two pairs of simple pure imaginary eigenvalues. The calculations involve center manifold reduction, normal form transformations, and Liapunov function construction for critical systems. These calculations are explicit.
The tethered satellite systems considered here consist of a satellite and subsatellite connected by a tether, in orbit around the Earth. The Lagrangian formulation of dynamics is used to obtain a nonlinear system of ordinary differential equations for TSS dynamics. For simplicity, a rigid, massless tether is assumed. Linear analysis reveals the presence of critical eigenvalues in the station-keeping mode of operation. This renders useful results on stabilization in critical cases to this application. The control variable assumed is tether tension feedback. Besides the design of stabilizing station-keeping controllers, stability of deployment and instability of retrieval are also shown for a constant angle deployment/retrieval scheme. DTIC
Artificial Satellites; Feedback; Nonlinear Systems; Tethered Satellites
20060016941 South Carolina Univ., Columbia, SC USA
High-Voltage Power Switching for a Conducting Tether
Harkare, Sriram; Dougal, Roger; Carroll, Joseph A; Liu, Shengyi; Jan 2006; 11 pp.; In English; Original contains color illustrations Report No.(s): AD-A444519; No Copyright; Avail.: CASI: A03, Hardcopy
The ElectroDynamic Delivery Express (EDDE) is an autonomous space vehicle that can maneuver throughout low earth orbit without using fuel. EDDE uses solar power to drive multi-ampere currents through a kilometers-long aluminum conductor, creating a force normal to both the conductor and the local magnetic field that drives the space vehicle. The tether spins at about 8 times/orbit. This stabilizes its dynamics and also allows a wider range of electrodynamic thrust directions as it spins. The current circuit is closed through the ambient plasma around the conductor. To provide complete control of the orbit, the high-voltage current must be switched repeatedly as a function of the orbital position, to modulate the force on the conductor. This paper describes our solution to this power switching and control problem. Arcing from the conductor to the ambient plasma is a potentially serious problem. To reduce the possibility of arcing, the solar arrays are distributed along the conductor length to reduce the peak potential between the conductor and the local plasma. If arcing does start, it can be quenched by electrically isolating the tether segments upstream of the arcing section, using high-voltage control switches in each power module. This makes it feasible to pull the arcing segment positive to quench the arc. Each power module includes an H-bridge so the solar array can drive current through the tether in either direction. Turning the bridge off isolates the conductor segments and array from each other, to help quench arcs from both the array and the conductor. The bridge also includes a shunt switch so tether current can bypass the solar array. This lets EDDE continue operating despite failed power switches or mis-aimed solar arrays. Effective control of current and arcing requires communication between the modules. This can be done optically, or with RF signals transmitted along the conductor, superimposed on the drive current. DTIC
Electrical Resistivity; High Voltages; Switching; Tethering
20060017031 NASA Ames Research Center, Moffett Field, CA, USA
Simulations of SSLV Ascent and Debris Transport
Rogers, Stuart; Aftosmis, Michael; Murman, Scott; Chan, William; Gomez, Ray; Gomez, Ray; Vicker, Darby; Stuart, Phil; [2006]; 5 pp.; In English; Simulations of SSLVAscent and Debris Transport, 11 Oct. 2006, CA, USA; Original contains black and white illustrations; No Copyright; Avail.: CASI: A01, Hardcopy
A viewgraph presentation on Computational Fluid Dynamic (CFD) Simulation of Space Shuttle Launch Vehicle (SSLV) ascent and debris transport analysis is shown. The topics include: 1) CFD simulations of the Space Shuttle Launch Vehicle ascent; 2) Debris transport analysis; 3) Debris aerodynamic modeling; and 4) Other applications.
CASI Ascent; Computational Fluid Dynamics; Debris; Launch Vehicles; Space Shuttles; Simulation
20060017051 CSA Engineering, Inc., Albuquerque, NM USA
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Design and Evaluation of a Reinforced Advanced-Grid Stiffened Composite Structure
Biskner, Adam; Higgins, John; Jan 2005; 10 pp.; In English; Original contains color illustrations Report No.(s): AD-A443361; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA443361; Avail.: CASI: A02, Hardcopy
A composite grid-stiffened structure concept was selected for the payload fairing of the Minotaur launch vehicle. Compared to previous designs, this concept is lighter weight and requires reduced manufacturing costs. Various failure mechanisms were examined for the composite grid-stiffened structure. The controlling criterion for this design was determined to be joint peel-off failure. The identification of this failure mechanism and the assessment of bounding strains to control it, required extensive test and analysis effort. The final fairing design incorporated an undesirably thick skin to reduce the strain between the skin and ribs. This project investigated a means of controlling joint failure of the un-reinforced grid-stiffened structure in an effort to reduce the skin thickness. Implementing lightweight foam inserts between the stiffeners on the interior of the fairing delayed failure to higher loads. A foam reinforced test panel, designed with equal mass to the current structure, withstood a substantially greater compressive force. The alternative concept also demonstrated an improved response, failing in global buckling instead of experiencing early failure due to joint strain. DTIC
Composite Structures; Reinforcing Materials; Ribs (Supports); Loads (Forces)
20060017644 Air Force Research Lab., Wright-Patterson AFB, OH USA
Ground Moving Target Engagement by Cooperative UAVs
Schumacher, Corey; Jun 2005; 5 pp.; In English; Original contains color illustrations Report No.(s): AD-A445128; FRB16.4; No Copyright; Avail.: CASI: A01, Hardcopy
The purpose of this tutorial paper is to present an application example for the MultiUAV cooperative control simulation.MultiUAV has been used to simulate a Cooperative Moving Target Engagement (CMTE) scenario, with a team of UAVs acting as a sensor and communication network to cooperatively track and attack moving ground targets. This scenario illustrates the utility of MultiUAV for cooperative control applications requiring heterogeneous vehicles with varied sensor, communication, dynamic, and weapon capabilities. A human supervisor designates one or more moving ground targets for the vehicles to attack. The vehicle agents must then autonomously and cooperatively determine which vehicles will perform the required tasks, when the tasks will be performed, and what flight paths will be used. This requires assigning time-dependent cooperativeand joint tasks, where multiple sub-elements of the primary task must be accomplished by different vehicles, for any of the tasks to have value. This tutorial focuses on the unique requirements of the CMTE scenario and how they are addressed in the MultiUAV simulation. DTIC
Communication Networks; Targets
20060017654 Air Force Academy, CO USA
The Undergraduate Satellite and Rocket Design, Fabrication, Launch and Operations Program at the USA Air Force Academy
Busch, Brian; Lawrence, Timothy L; Meerman, Maarten J; Aug 20, 2004; 8 pp.; In English Report No.(s): AD-A445147; No Copyright; Avail.: CASI: A02, Hardcopy
The Space Systems Research Center at the USAAir Force Academy is building a cadre of space professionals 'one cadet at a time'. Cadets majoring in astronautical engineering and space operations participate in a two-semester capstone program in the design, fabrication, testing and launching of a sounding rocket (the FalconLAUNCH program), or in the design, fabrication, testing, launching and operation of a satellite in space (the FalconSAT and FalconOPS programs) . This paper details the development, challenges, and advantages or conducting an undergraduate space program performing world class research. DTIC
Aerospace Systems; Armed Forces (United States); Fabrication; Launch Vehicles; Military Spacecraft; Satellite Design; Sounding Rockets; Spacecraft Launching; United States; Universities
20060017678 European Aeronautic Defence and Space Co., Munich, Germany
Reconfigurable Computing Technology for Image Compression in the BayernSAT Mission
Cotrino, Javier; Helfers, Tim; Schueler, Eberhard; Walter, Ulrich; Jul 13, 2005; 12 pp.; In English; Original contains color illustrations Report No.(s): AD-A445190; No Copyright; Avail.: CASI: A03, Hardcopy
The next generation earth-observation satellites will have significantly increased performance requirements. New advanced compression techniques like Bit- Plane Encoding and transformation steps based on wavelets are gaining importance. However, due to the small size of the space electronics market, the availability of devices capable to implement such algorithms is decreasing. This has motivated EADS-Astrium GmbH to search new processing technologies that can be transferred in the short term to reliable commercial space technologies. The emphasis is put on reconfigurable processing, since this is the only way to reduce risks and costs and assure the proper functionality of the satellite during its whole life. The eXtreme Processing Platform is a new runtime reconfigurable processor technology, An ESA study, with the name 'XPP Applicability Study' was already carried out to prove the feasibility of this new technology and its superiority over different architectures being offered in the market. An important part of this study was also the transfer of the architecture to a radiation-tolerant semiconductor technology. The small satellite mission BayernSAT of the Technische Universitat Munchen will serve as a demonstration of the image processing capabilities of a new reconfigurable processing technology, the XPP, integrated in a configurable processor system based on the LEON Sparc processor. DTIC
Artificial Satellites; Computation; Computers; Data Compression; Image Processing; Microprocessors
20060017685 Centre National de la Recherche Scientifique, Toulouse, France
Low Phase Noise Fiber Optics Links for Space Applications
Onillon, Bertrand; Constant, Stephanie; Quardi, Gianandrea; Benazet, Benoit; Llopis, Olivier; Jul 13, 2005; 9 pp.; In English; Original contains color illustrations Report No.(s): AD-A445206; No Copyright; Avail.: CASI: A02, Hardcopy
This paper summarises the results obtained on different systems dedicated to the optical distribution of high spectral purity RF and microwave signals in a satellite payload or towards the elements of an active antenna. First, the interest of the photo-oscillator receiver for these applications in the RF frequency range is pointed out. Then, different emitter configurations are investigated in the microwave range . Finally, an application of these low phase noise microwave links in the field of time-frequency metrology i.e. an ultra high sensitivity microwave frequency discriminator, is addressed. DTIC
Aerospace Engineering; Fiber Optics; Low Noise; Technology Utilization
20060017803 Air Force Inst. of Tech., Wright-Patterson AFB, OH USA
Optimizing Mean Mission Duration for Multiple-Payload Satellites
Flory, John A; Mar 2006; 131 pp.; In English Report No.(s): AD-A445180; AFIT/GOR/ENS/06-08; No Copyright; Avail.: CASI: A07, Hardcopy
This thesis addresses the problem of optimally selecting and specifying satellite payloads for inclusion on a satellite bus to be launched into a constellation. The objective is to select and specify payloads so that the total lifetime utility of the constellation is maximized. The satellite bus is limited by finite power, weight, volume, and cost constraints. This problem is modeled as a classical knapsack problem in one and multiple dimensions, and dynamic programming and binary integer programming formulations are provided to solve the problem. Due to the computational complexity of the problem, the solution techniques include exact methods as well as four heuristic procedures including a greedy heuristic, two norm-base heuristics, and a simulated anneling heuristic. The performance of the exact and heuristic approaches is evaluated on the basis of solution quality and computation time by solving a series of notional and randomly-generated problem instances. The numerical results indicate that, when an exact solution is required for a moderately-sized constellation, the integer programming formulation is most reliable in solving the problem to optimality. However, if the problem size is very large, and near-optimal solutions are acceptable, then the simulated annealing algorithm performs best among the heuristic procedures. DTIC
Artificial Satellites; Dynamic Programming; Payloads
20060017821 NASA Ames Research Center, Moffett Field, CA, USA
Decision Facilitator for Launch Operations using Intelligent Agents
Thirumalainambi, Rajkumar; Bardina, Jorge; [2005]; 5 pp.; In English; SAE World Aviation Congress 2005, 3-6 Oct. 2005, Dallas, TX, USA; Original contains black and white illustrations Report No.(s): SAE-2005-01-3367; Copyright; Avail.: Other Sources
Launch operations require millions of micro-decisions which contribute to the macro decision of 'Go/No-Go' for a launch. Knowledge workers"(such as managers and technical professionals) need information in a timely precise manner as it can greatly affect mission success. The intelligent agent (web search agent) uses the words of a hypertext markup language document which is connected through the internet. The intelligent agent's actions are to determine if its goal of seeking a website containing a specified target (e.g., keyword or phrase), has been met. There are few parameters that should be defined for the keyword search like 'Go' and 'No-Go'. Instead of visiting launch and range decision making servers individually, the decision facilitator constantly connects to all servers, accumulating decisions so the final decision can be decided in a timely manner. The facilitator agent uses the singleton design pattern, which ensures that only a single instance of the facilitator agent exists at one time. Negotiations could proceed between many agents resulting in a final decision. This paper describes details of intelligent agents and their interaction to derive an unified decision support system. Author
Decision Support Systems; Spacecraft Launching; Artificial Intelligence; Computer Programs
20060018305 Air Force Research Lab., Wright-Patterson AFB, OH USA
UAV Team Decision and Control Using Efficient Collaborative Estimation
Shima, Tal; Rasmussen, Steven J; Chandler, Phillip; Jun 2005; 7 pp.; In English Report No.(s): AD-A444825; FRB04.5; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA444825; Avail.: CASI: A02, Hardcopy
A novel decision-estimation architecture for a team of agents cooperating under communication imperfections is presented. The scenario of interest is that of a group of uninhabited aerial vehicles performing cooperative task assignment under communication delays. In the proposed architecture, each UAV in the group runs multiple filters in parallel on: its own states, teammates' states, and its states as viewed by teammates. The estimation of team members' states allows each UAV to synchronize the transmitted cost of performing known tasks, obtained from the different group members, to a common time base. It also enables estimating the expected cost for teammates to prosecute new tasks. Thus, the group performance, under communication imperfections, can be improved. For the estimation, two different algorithms are proposed. The first is communication efficient in which asynchronous information updates are sent to the network by individual members based on the value of the information to the rest of the group. Taking into account that the plan and plant of each UAV are known to the rest of the group, improves the overall estimation process. Moreover, it allows proposing another, computationally efficient, estimation algorithm utilizing synchronous information updates. DTIC
Drone Vehicles; Pilotless Aircraft; Decision Making
20060018454 Office of the Secretary of Defense, Washington, DC USA
Unmanned Aircraft Systems Roadmap, 2005-2030
Jan 2005; 213 pp.; In English; Original contains color illustrations Report No.(s): AD-A445081; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA445081; Avail.: CASI: A10, Hardcopy
As the Global War on Terrorism (GWOT) enters its fourth year, the contributions of unmanned aircraft (UA) in sorties, hours, and expanded roles continue to increase. As of September 2004, some twenty types of coalition UA, large and small, have flown over 100,000 total flight hours in support of Operation ENDURING FREEDOM (OEF) and Operation IRAQI FREEDOM (OIF). Their once reconnaissance- only role is now shared with strike, force protection and signals collection, and, in doing so have helped reduce the complexity and time lag in the sensor-to-shooter chain for acting on 'actionable intelligence.' UA systems (UAS) continue to expand, encompassing a broad range of mission capabilities. These diverse systems range in cost from a few thousand dollars to tens of millions of dollars, and range in capability from Micro Air Vehicles (MAV) weighing less than one pound to aircraft weighing over 40,000 pounds. UA, and unmanned systems in general, are changing the conduct of military operations in the GWOT by providing unrelenting pursuit without offering the terrorist a high value target or a potential captive. DTIC
Military Operations; Pilotless Aircraft; Terrorism; Unmanned Spacecraft; Warfare
20060018456 Centre National d'Etudes Spatiales, Toulouse, France
Will Schedulers be Available on Board in the Next Generation of Robots?
Fayard, Thierry; Jul 13, 2005; 11 pp.; In English; Original contains color illustrations Report No.(s): AD-A445130; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA445130; Avail.: CASI: A03, Hardcopy
This paper presents a simulated annealing solution procedure for a Resource Constraint Project Scheduling Problem (RCPSP) as it may be found in future space robotic applications. Such RCPSPs also are found in some game problems in which it is easy to compare computerized solutions with human play. The player, or the computer, has to find the best sequence of activities in which an objective function is maximized within a given time. The scheduling problem found both in robotics applications and in such games, is more difficult than usual because it is subject to temporal constraints, and to constraints for renewable, nonrenewable, and cumulative resources. The cumulative resources are depleted or replenished over time, depending on the player's choice. In this study, a simulated annealing algorithm is successfully tested. The results show that its performance can satisfy a good player and that it may be of some help in robotic applications. The results also show that the algorithm is robust because the heuristic is always able to find a rather good solution, and that it is realistic since the computing power needed for it will be available on board in the medium-term future. DTIC
Optimization; Resources Management; Robots; Scheduling; Space Missions
20060018458 Centre National d'Etudes Spatiales, Toulouse, France
Off-The-Shelf and Free Software Technologies for Spacecraft Control & Command: An Example, Balloon-Borne Stabilised Gondolas
Laurens, Andre; Jul 13, 2005; 17 pp.; In English; Original contains color illustrations Report No.(s): AD-A445196; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA445196; Avail.: CASI: A03, Hardcopy
Balloons are low-cost, short development time space vehicles for science missions and technology in-flight experiments that need out-of-atmosphere or in-situ measurements, thus being complementary to the satellite. CNES stabilised gondolas are versatile space platforms used to fly science instruments mainly for aeronomy and astrophysics that need stabilisation and pointing capabilities, analogous to satellite attitude control subsystems. In order to increase gondola flexibility to new missions, promoted control & command technologies are those of industrial computers, ground networks, free software and, over all, Ada language, for they are open, standard, powerful, low-cost and longlasting solutions. After a brief description of domain-oriented characteristics of stabilised gondola control & command, this paper introduces the various technologies and main design principles proposed to meet system-level goals. Then focus is put on on-board architectures (Ada95 real-time distributed applications), and describes the prototyping work and preliminary development done to ensure feasibility. The paper then discusses the applicability of such solutions to global, ground-toboard, distributed control & command applications, through an IP-based telemetry & telecommand link, such as the one under development in CNES for balloon systems. As a conclusion, this paper shows how adoption of the above technologies for other space programs such as satellite platforms and payloads may change design, development costs, duration and organisation, as well as it may open new ways in ground-to-board communication and spacecraft operation. DTIC
Ada (Programming Language); Artificial Satellites; Attitude Control; Balloons; Command and Control; Commercial Off-the-Shelf Products; Gondolas; Software Engineering; Spacecraft Control
20060018468 Centre National d'Etudes Spatiales, Toulouse, France
Very High-Performance Embedded Computing Will Allow Ambitious Space Science Investigation
Pignol, Michel; Jul 13, 2005; 15 pp.; In English; Original contains color illustrations Report No.(s): AD-A445276; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA445276; Avail.: CASI: A03, Hardcopy
Up to now, the definition of space science missions was bounded by electronic components authorised by Space Agencies, i.e. developed on radiation tolerant technologies. Unfortunately, the microprocessors today available on such technologieshave the computing throughput which was available about 10 years ago on the commercial market. Today, one of the main weakness of commercial components for space usage is their sensitivity to upsets, which generate transient faults during execution of flight software. Thus, to the condition to have 'light' fault-tolerant architectures, the space community could define a new class of space science missions having very ambitious scientific goals and disrupting with classical missions thanks to high-performance embedded computers based on commercial electronic components. DTIC
Embedding; Fault Tolerance; Microprocessors
20060018469 Centre National d'Etudes Spatiales, Toulouse, France
Development of a CMOS Snapshot Active Pixel Sensor for Spaceborne Earth Observation Applications
Materne, Alex; Buil, Christian; Jul 13, 2005; 12 pp.; In English; Original contains color illustrations Report No.(s): AD-A445277; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA445277; Avail.: CASI: A03, Hardcopy
For metric resolutions earth observation missions - in the visible spectrum - CMOS Active Pixel Sensors (APS) may be a competitive alternative to 2D array CCD thanks to the high readout frequencies and to the shutter capability offered by the snapshot mode. In order to evaluate the interest of CMOS APS for those missions, CNES has launched the development of a CMOS snapshot APS demonstrator. Although a multi-mission capability is targeted, the requirement specification has been mainly built on the basis of a typical low Earth orbit microsatellite mission scenario aiming at capturing images at 1 meter spatial resolution for a 8 km x 8 km minimum FOV, in the visible spectral band. Main driving requirements are presented together with the expected trade-off to be solved during architecture and design phases. DTIC
CMOS; Earth Observations (From Space); Pixels; Satellite Imagery; Satellite Observation
20060018470 Air Force Inst. of Tech., Wright-Patterson AFB, OH USA
A Discrete Event Simulation Model for Evaluating Air Force Reusable Military Launch Vehicle Prelaunch Operations
Stiegelmeier, Adam T; Mar 2006; 147 pp.; In English; Original contains color illustrations Report No.(s): AD-A445279; AFIT/GLM/ENS/06-16; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA445279; Avail.: CASI: A07, Hardcopy
As the control and exploitation of space becomes more important to the USA military, a responsive spacelift capability will become essential. Responsive spacelift could be defined as the ability to launch a vehicle within hours or days from the time a launch order is given, instead of the weeks or months it takes currently. As the Air Force contemplates moving toward a reusable military launch vehicle (RMLV) capability, it faces key design and ground processing decisions that will affect the vehicle regeneration timeline. This thesis develops a computer simulation model that mimics RMLV prelaunch operationsthose activities that take place during vehicle integration and launch pad operations. This simulation model can help the Air Force make RMLV acquisition decisions by analyzing how different RMLV designs and ground processing scenarios will affect RMLV regeneration time. The model was developed by comparing and contrasting existing launch vehicle processing flows to create the RMLV prelaunch operations model. To foster confidence in model credibility, the model was analyzed and validated by a panel of launch vehicle experts. Model verification was accomplished via an Assertion Checking method that compared model developer intent to actual model operation. The model was used to conduct three experiments that analyzed how different ground processing scenarios affected RMLV regeneration time. DTIC
Launch Vehicles; Mathematical Models; Reusable Launch Vehicles; Simulation
20060018570 EADS Astrium Ltd., Stevenage, UK
A Novel, Flexible Approach to Packaging Integrated Microsystems for Space Applications
Eckersley, Steven; Coumar, Oudea; Schalk, Josef; Kluge, Martin; Jul 13, 2005; 3 pp.; In English; Original contains color illustrations Report No.(s): AD-A445456; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA445456; Avail.: CASI: A01, Hardcopy
The European Aeronautic Defence and Space Company (EADS) recognizes the potential for Microsystems Technology (MST) to disrupt and revolutionize the space industry, where it can dramatically reduce mass, size, and power requirements, and, therefore, mission cost. EADS is developing a novel modular approach to packaging integrated microsystems for space applications, called 'micropacks.' The micropack include suites of commercial off-the-shelf (COTS) MST sensors, packaged and integrated into a 3D modular multi-layer ceramic package. This impressively light and compact micropack technology can be adapted to form the basis of a solution for a range of exciting future mission concepts, such as the following: (1) highly integrated multi-functional nanosatellites (e.g. for solar terrestrial physics or space weather monitoring); (2) planetary aerobots on Mars, Venus, the Giant Planets, and Titan (e.g. as a payload/system package); (3) sub-100g planetary microprobes for measuring atmospheric profiles; (4) solar sails (e.g. as the central hub of the spacecraft); (5) penetrators (e.g. as a payload/system package); and (6) robotic planetary explorers (e.g. landers, rovers, walkers, hoppers). The micropack consists of five ceramic layers, including an atmospheric sensor unit (e.g. pressure sensor), an acceleration sensor unit, a power supply unit, a data handling unit (a Texas Instruments MSP430 micro-controller), and a chip-size radiofrequency transceiver unit laminated into the ceramic. Each module has a standardized interface, which ultimately combines with other modules to form a system platform. The size of the micropack will be a mere 20x25x25mm(exp 3), with power consumption of less than 100mW and a mass of just 25g. DTIC
Aerospace Engineering; Commercial Off-the-Shelf Products; Microelectromechanical Systems; Microinstrumentation; Packaging; Sensors; Technology Utilization
20060018571 EADS Space Transportation, Lampoldshausen, Germany
New European Apogee Motor -- Advanced Propulsion Technology
Ehmann, Dieter; Gotzig, Ulrich; Schulte, Georg; Beyer, Steffen; Schmidt, Stefan; Jul 13, 2005; 3 pp.; In English; Original contains color illustrations Report No.(s): AD-A445457; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA445457; Avail.: CASI: A01, Hardcopy
Apogee motors will transfer large geostationary satellites into their final orbit within the next decade. Approximately 60% of a geostationary satellite's mass is propellant, 90% of which is consumed by the apogee motor. An increase in motor performance and motor efficiency would offer significant mass savings for the satellites. Therefore, an optimum performing apogee motor is still an element of strategic importance for the competitiveness of large geostationary satellites. The need for developing a new High Performance Bi-propellant Apogee Motor is driven by customers' demands for higher performance, higher reliability, and lower prices. The benefit for customers will be strategic (independence for Europe) and commercial (greater payloads and more competitive pricing in the world market). There are two essential elements for a high performance apogee motor: injector technology and combustion chamber technology. This paper describes the development objectives for the motor's injector system and combustion chamber. DTIC
Apogees; Combustion Chambers; Fuel Injection; Geosynchronous Orbits; Propulsion; Rocket Engines; Synchronous Platforms; Synchronous Satellites
20060018572 Alcatel Space Industries, Toulouse, France
SuperComputers for Space Applications
Estaves, G; Leconte, P; Vissio, G; Leyre, X; Jul 13, 2005; 10 pp.; In English; Original contains color illustrations Report No.(s): AD-A445458; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA445458; Avail.: CASI: A02, Hardcopy
Upcoming new science and Earth observation projects, like GAIA, make the need for high-power computing systems more and more evident in the space community. Commercial technologies, like PowerPC processors, have very promising properties apart from their computing performance. Tests performed by various space agencies (ESA & CNES) to verify the SEU tolerance of new microelectronic technologies show that a possible convergence between space and ground technologies will be necessary for supercomputers to be used in space. Fault-tolerant supercomputers could be used to complement the European radiation-hardened LEON processor line. These systems would allow for high-power processing to occur onboardthe spacecraft as a first step. Then, once the validity of the technology has been demonstrated, it is likely to generate a revolution in space systems. This paper presents the ALCATEL SPACE (ASP) vision of commercial off-the-shelf (COTS) computers in space systems. The paper discusses the experience ASP has acquired with COTS processors that incorporate fault tolerant techniques beginning with the Skybridge Project, and how that experience has been reworked for the GAIA project. The paper also provides an overview of next-generation space systems and how they will be affected by COTS products. DTIC
Aerospace Systems; Commercial Off-the-Shelf Products; Computer Systems Design; Fault Tolerance; Microprocessors;
Radiation Hardening; Supercomputers; Technology Utilization
20060018591 EADS-ST, En Jalles, France
Helium High Pressure Tanks at EADS Space Transportation New Technology with Thermoplastic Liner
Benedic, Fabien; Leard, Jean-Philippe; Lefloch, Christian; Jul 13, 2005; 10 pp.; In English; Original contains color illustrations Report No.(s): AD-A445482; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA445482; Avail.: CASI: A02, Hardcopy
Although EADS ST has been involved in high pressure tanks for 25 years. EADS ST is still developing new technologies and products to provide the best solution in response to the evolution of the market in terms of performances and costs. In order to achieve the new target prices, a new disruptive technology has been performing for several years in using a thermoplastic liner instead the usual expensive concept of metallic forged liner. This new thermoplastic technology o offers a significant cost reduction by 30% at tank level and a tank cycle production half size both directly impacting the management of Space Programs. This paper presents the state of the art in the domain of the thermoplastic liner applied on a new version of the 300 litres ARIANE 5 helium tank currently produced for the A5 launcher with a titanium liner. The objective of this new development is to replace the titanium liner with a thermoplastic one in order to reduce both the cost of the liner and the tank cycle. This paper also details the logic of the development chosen for this application and the results obtained for the last 3 years, which have all ended in a full success of the thermoplastic concept. All the works made in the frame of the feasibility of a 300 L thermoplastic lined tank fully demonstrate the compliance to the major requirements of AS launcher. These works finalize the feasibility phase of this new disruptive technology which is now rather mature with the aim of a complete qualification for the production of such tanks. DTIC
Gas Pressure; Helium; High Pressure; Linings; Space Transportation; Thermoplastic Resins; Thermoplasticity
20060018592 Commissariat a l'Energie Atomique, Grenoble, France
Development of Fast NbN RSFQ Logic Gates in Sigma-Delta Converters for Space Telecommunications
Baggaetta, Emanuele; Maignan, Michel; Villegier, Jean-Claude; Jul 13, 2005; 14 pp.; In English; Original contains color illustrations Report No.(s): AD-A445484; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA445484; Avail.: CASI: A03, Hardcopy
In the future generations of telecommunication satellites, it will be necessary to reduce the analog part in reception systems and achieve RF front-end at higher carrier frequencies with higher sensitivity and higher bandwidth. RSFQ (Rapid Single Flux Quantum) superconducting logic is suitable to process very high speed digital data processing with very low power dissipation and with performances well beyond what should be possible with CMOS technology in the next decades. The RSFQ circuit technology based on superconducting niobium nitride (NbN) presently developed at CEA-G involves NbN/Ta(sub X)N/NbN internally shunted Josephson junctions with high critical current density and high maximum switching frequency close to 1THz, as required by ultra-fast RSFQ electronics. Very low power dissipation and very low noise level of fast NbN RSFQ gates designed and fabricated at CEA-G are presented. The RSFQ circuit for a sampling comparator has been studied operating in a sigma-delta modulator with a 30 GHz sinusoidal input carrier signal and high sampling clock frequency of about 200 GHz. We will present the thermal noise and how it influences the phase fluctuations. Such a nitride technology has been recently demonstrated to be fully compatible with large scale integration on 200 mm diameter silicon wafer at reasonable fabrication cost in a micro-nano-electronic platform at CEA-Leti. The applicability of NbN RSFQ digital functions in the next decade Space Telecoms will finally be possible thanks to the development of reliable, low power consuming, space qualified cryocoolers operating at about 10K. Moreover semiconductor system design and integration techniques can be simply adapted to superconductivity, to fit the rules of any RSFQ library-foundry network, such as 'CONNECT' for Japan and 'FLUXONICS' for Europe. DTIC
Gates (Circuits); Niobium Compounds; Nitrides; Space Communication; Telecommunication
20060018607 Alcatel Space, Toulouse, France
Potentialities of HTS Superconductor Technology in Telecommunication Satellites
Maignan, M; Brevart, B; Trollier, T; Madrangeas, V; Zanchi, C; Jul 13, 2005; 12 pp.; In English; Original contains color illustrations Report No.(s): AD-A445515; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA445515; Avail.: CASI: A03, Hardcopy
High temperature super-conductive (HTS) technology is presented as a disruptive technology able to improve the performances of microwave equipment: mass and volume savings, electrical properties, etc. To verify the well-founded of these qualities for telecom satellite payloads, the research department of Alcatel Space has studied two proof-of-concept ofmicrowave space equipment including super-conductive and chill electronics. The objectives of these projects are to estimate the potential of HTS technology, evaluate the impact of the cryo-system on the satellite platform, determine the threshold of interest and estimate the development duration between the state of art and future credible equipment for commercial applications. In this paper, HTS is based on super-conductive thin film material. The material is YBaCuO or lBaCuO deposited on LaAlO3 or MgO substrates. The reduced microwave resistivity of HTS thin films compared to copper allows realizing micro-strip or coplanar resonators and lines which are more compact than classical cavity resonators. Superconductive micro-strip has a quality factor equivalent to the one of a bulk resonator in C-band. Thin films are etched to obtain elementary resonators and mutual coupling between resonators. The steady progress of electromagnetic simulation softwareassociated with the reproducibility of etching process is a way to make up filters without the tedious resonator tuning inherent to bulk filters and reduced the manufacturing cost. In association with HTS device, cooling permits the introduction of chill electronics in the equipment. It is known that operating at low physical temperature decreases the noise factor of radiofrequency amplifier (LNA). DTIC
Artificial Satellites; High Temperature Superconductors; Microwave Equipment; Superconductors (Materials); Telecommunication; Thin Films
20060018611 Alcatel Space, Toulouse, France
High-Throughput Optical Interconnect Technology for Future On-Board Digital Processors
Sotom, Michel; Venet, Norbert; Aubry, Pierre; Berthon, Jacques; Jul 13, 2005; 9 pp.; In English; Original contains color illustrations Report No.(s): AD-A445521; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA445521; Avail.: CASI: A02, Hardcopy
Digital processing is expected to take place in many satellite payload sub-systems, including advanced telecom repeaters and antenna beam-formers, next-generation radars and data handling units of remote sensors. The capabilities of integrated circuits and processors have been growing so rapidly over the last decades that the pressure is being now shifted to the interconnect function. Whereas the speed and pin count of IC's increases rapidly, the bandwidth and density of backplanes and connectors for space applications do not improve at the same pace. A breakthrough is needed in order to go on improving the overall system, and interconnects with commensurate performance have to be made available. Alcatel Space is investigating optical interconnects as an enabling technology that may offer the high-throughput data communication capabilities required for the future on-board processors and digital equipment. Optical interconnects may constitute a generic solution for supporting both intra- and inter-equipment communications, with almost unlimited bandwidth, distance-independent performance, unprecedented connector density and low-mass cabling. Suppression of EM crosstalk issues and impedance mismatches, full isolation between transmitting and receiver ends, simplification of routing might, in the end, shorten the design and integration phases. DTIC
Aerospace Environments; Optical Interconnects; Pulse Communication
20060018612 Japan Aerospace Exploration Agency, Chofu, Japan
A New Space Robot End-Effector for On-Orbit Reflector Assembly
Nishida, Shin-ichiro; Hirabayashi, Hisashi; Yoshikawa, Tsuneo; Jul 13, 2005; 8 pp.; In English; Original contains color illustrations Report No.(s): AD-A445522; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA445522; Avail.: CASI: A02, Hardcopy
In Earth orbit, astronomical observations are possible, free from absorption or disturbances by the Earth's atmosphere. Therefore, some large space telescopes and large space radio telescopes are planned for the future. Launch vehicle payload bay diameters impose severe restrictions on the sizes of these telescopes, and so, structures larger than the payload bay have to be deployed or assembled in orbit. Structures assembled in orbit may have a finer surface accuracy and can be made more rigid than deployable structures. When assembling such large structures, space robots have to move around on the structure. It is necessary to supply power and electronic signals to a robot arm from the structure under construction. Therefore, the power supply line and the communication network have to be incorporated in the structural elements, and the composition which has the connector attaching mechanism of a line was studied. We discuss the design of a telescope reflector which can be assembled in orbit, with its networks and connecting mechanisms suitable for robot tasks. The characteristics of the new end-effector mechanisms and their suitability for onboard assembly tasks were confirmed by test using a two dimensional ground test arm. The test results are also described in this paper. DTIC
Aerospace Environments; End Effectors; Radio Telescopes; Reflectors; Robots
20060018622 Space Engineering S.p.a., Rome, Italy
Fuzzy Logic Controller for Small Satellites Navigation
Della Pietra, G; Falzini, S; Colzi, E; Crisconio, M; Jul 13, 2005; 13 pp.; In English; Original contains color illustrations Report No.(s): AD-A445552; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA445552;Avail.: CASI: A03, Hardcopy
The development of a navigator for small satellites (SSN) is in progress with a joint effort of Space Engineering and ASI in the fram of a technological development program dedicated to SME. The navigator aims at operating satellites in orbit with a minimum ground support and very good performances, by the adoption of innovative technologies, such as attitude observation GPS, attitude state estimation by Kalman Filter and fuzzy logic for attitude control. The SSN is very attractive in space applications where analytical non-linear models prevent an easy synthesis of classical controllers, and where the volume of parameters affecting the plant behavior is very high. The navigator was verified through HW-in-the-loop simulations and the following feature emerged: - three axes control with control performances compatible with Earth observation missions with optical payloads - autonomous on-board management, and non-nominal pointing capacity without ground planning, permitting to acquire images without scheduling in advance - independence from ground commands in selecting operational modes - autonomous wheels desaturation - autonomous system reconfiguration in response to unexpectedevents, such as sensors or actuators failures -capability to perform both large re-pointing in low times and accurately maintainattitude - robustness against external and internal disturbances and large variations of platform parameters. DTIC
Artificial Satellites; Autonomous Navigation; Controllers; Fuzzy Systems; Navigation
20060018625 European Space Agency. Ulysses Office, Pasadena, CA USA
Lessons Learned with the Innovation Triangle Initiative
Freire, Marco; Guglielmi, Marco; Lascar, Stephane; Jul 13, 2005; 9 pp.; In English; Original contains color illustrations Report No.(s): AD-A445555; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA445555; Avail.: CASI: A02, Hardcopy
One of the roles of the European Space Agency (ESA) is to support the introduction of technology innovation in the space environment. This is the aim of the Innovation Triangle Initiative (ITI), whose specific goal is to explore technologies or services for space applications that are not currently being used or exploited in the context of space, but that have the potential for being the seed for significant innovation. ITI is based on the concept that a close collaboration between three different entities -- the inventor, the developer, and the customer -- is an important factor for the rapid and successful introduction of technology innovations in industry. Following a successful pilot phase, the operational phase of ITI was officially launched on 16th March 2004 with funding of 1.5 MEURO for 2004. The objective of this presentation is to present the ITI concept, the results achieved during ITI's first year of operation, lessons learned, and plans for 2005. The paper includes discussions of the concepts of disruptive innovation, stage-gate process, and Technology Readiness Level; a description of ITI's web-based proposal process; and figures showing the distribution of proposals submitted by member states in 2004, and the 26 Technical Domains in which ITI funds research. DTIC
Aerospace Engineering; Europe; Research Management; Triangles
20060018626 Alcatel Space, Toulouse, France
Technology Disruptions in Future Communication Payloads (Technologies de rupture pour futures charges utiles de telecommunications)
Gayrard, Jean-Didier; Jul 13, 2005; 8 pp.; In English; Original contains color illustrations Report No.(s): AD-A445566; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA445566; Avail.: CASI: A02, Hardcopy
The future market of satellite telecommunications will be shaped by four main trends: democratization, regionalization, digitalization, and the use of higher frequency bands. To cope with the economic and technical demands of the market and to compete with terrestrial networks, operators and manufacturers will need to upgrade their satellites. The evolution of satellite communications could go one of three ways: gigantism, adaptation, or modularity. Any of these ways will require satellite payloads to evolve from present levels of complexity that are mainly suited for TV broadcasting and telephone trunking in the Ku and C bands, to a new and higher level of complexity. In any scenario, innovative and disruptive technologies will be welcome. A first wave of disruptive technologies could come from optical and optoelectronic technologies. The rapid expansion of these techniques in terabit terrestrial networks could benefit satellite wideband payloads. Large bandwidth, mass savings, flexibility, and advanced processing are expected. A second wave of disruptive technologies could come from the cold, specifically, chill electronics, superconductivity, and cryogenics. High-temperature superconductors (HTS) allow for very low noise front ends and compact and lossless filters. Low-temperature superconductors (LTS) used in rapid single-flux-quantum (RSFQ) logic integrated circuits give the required computing power for wideband signal processing and analog-to-digital flash conversion of microwave signals. Digital signal processing also will bring disruptions to communication satellites. Digital techniques will enhance every aspect of payload processing, including beam forming, filtering, routing, linearization, and demodulation. Digitized onboard processors will enhance flexibility, performance, and reconfigurability. Microelectromechanical systems (MEMS) also will play a leading role in the design of next-generation payloads. DTIC
Broadband; Digital Systems; Disrupting; Payloads; Satellite Communication; Telecommunication
20060018628 Alcatel Space Industries, Toulouse, France
Internet Switching by Satellite: An Ultra Fast Processor with Radio Burst Switching
Haardt, Celine; Couville, Nicolas; Jul 13, 2005; 19 pp.; In English; Original contains color illustrations Report No.(s): AD-A445571; No Copyright; ONLINE: http://hdl.handle.net/100.2/ADA445571; Avail.: CASI: A03, Hardcopy
This paper introduces a new switching approach for satellites involved in routing statistical traffic, such as Internet Protocol (IP) data. Inherited from the optical domain, Radio Burst Switching (RBS) can combine a coarse switching granularity (such as circuit switching) with statistical multiplexing (such as packet switching) to better cope with the increasing bandwidth demands of Internet traffic and the need for high connectivity. RBS allows for packet switching missions in which the main burden of data does not require processing. RBS splits header-like information (control plane) from useful data (data plane), each one travelling on separate but linked paths. RBS then demodulates and decodes the header part of the packet and the main burden of data flow is not processed, but simply switched. Savings on embedded mass and power can be achieved because the processing stage is sized to header traffic only. This is the reason why RBS could be the solution to next-generation broadband satellite system requirements. Thanks to relevant data and control channel organization and selective onboard regeneration of signaling, it could be possible to integrate RBS into a Digital Video Broadcasting Return Channel Satellite (DVB-RCS) environment. Under this scenario, processor implementation would be very challenging, mainly due to the interconnect power costs and memory intensive processing. Because of integrated multi-gigabit transceivers (MGT) and multi-stage switch architecture, an ultra-fast packet switch will be feasible using year 2010 technologies. This paper describes the Ultra-Fast Internet Satellite Switching (ULISS) project upstream activities. The main ULISS goal is to develop and demonstrate the feasibility of the RBS concept and the ultra-fast packet switch processor. DTIC
Broadband; Bursts; Data Transmission; Internets; Packet Switching; Radio Bursts; Satellite Communication; Switching; Time Division Multiplexing
20060018897 Academy of Sciences (USSR), Novosibirsk, Russian Federation
DSMC and Navier-Stokes Study of Backflow for Nozzle Plumes Expanding into Vacuum
Vashchenkov, P V; Kudryavtsev, A N; Khotyanovsky, D V; Ivanov, M S; Jul 13, 2005; 7 pp.; In English; Original contains color illustrations Report No.(s): AD-A445940; No Copyright; Avail.: CASI: A02, Hardcopy
An important problem for space vehicles is contamination of the spacecraft surface by combustion products and unburned fuel exhausting from control thruster nozzles. The objective of the present work is a detailed simulation of the backflow in the case of gas exhaustion from the nozzle into vacuum. A specific feature of this problem is the drastic expansion of the initially dense flow at the nozzle exit, which makes necessary simulations of the near-continuum flow inside the nozzle, the transitional flow near the nozzle exit, and the free-molecular flow outside the nozzle. The simulations are performed by acombined Navier-Stokes/DSMC approach. DTIC
Computerized Simulation; Monte Carlo Method; Navier-Stokes Equation; Nozzles; Plumes; Thrust Control; Vacuum
Source: NASA
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