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Spacecraft engineering - spacecraft design, testing and performance

A Comparison between Models of Flexible Spacecraft

This paper was given at the 6th Dynamics and Control of Systems and Structures in Space (DCSSS) conference by Dario Izzo, Lorenzo Pettazzi and Chiara Valente. The conference took place in July 2004 at Riomaggiore, Italy. Flexibility plays an important role in the design of space missions. Algorithms able to derive the dynamical equations for a generic chain of flexible and rigid bodies have been developed in the past decades so that accurate dynamic simulations of large multi-body chains are possible. On the other hand control devices are getting more and more sophisticated so that the guidance of satellite platforms equipped with last generation fly-wheels is a quite complex task. In order to develop control laws, restrictive hypotheses are commonly introduced to make the equation of motion as simple as possible: rigid body dynamic, small angular velocities, small deformations, symmetric appendages bending, reduced degrees of freedom and many other hypotheses lead to as many different mathematical models. Simple modeling leads to fast simulations and allows an easier design of attitude steering laws or vibration suppression controls. In this work a mathematical model describing the full non-linear dynamic of a flexible satellite platform equipped with a system of rigid fly-wheels is developed in an explicit form. The equations are than compared to those obtained by applying standard multi-body analysis. The advantages of having an explicit form of the equations in term of the sole state of the central platform (the state of the wheels is considered as a control) are particularly attractive for control design. The set of ordinary differential equations written returns widely used model when restrictive hypotheses are introduced and has to be used in connection to a preliminary Finite Element Method analysis in order to evaluate the structural invariants. [Taken from abstract]. This is a PDF file, so Adobe Acrobat software will be required in order to read it.

A Guide for the Design of Highly Reusable Space Transportation

This web site provides access to the final report of Nasa's Space Propulsion Synergy Team, dated August 29 1997. The report was produced as part of the Highly Reusable Space Transportation (HRST) programme. It identifies key factors and relationships between factors, in order to ensure a highly reusable, safe, dependable, operable and affordable solution. Abstract and contents pages are presented in HTML format, and the full text of the report is available online in PDF (335 Kb) and MS Word (499 Kb) formats. The report is made available through the Kennedy Space Center's Next Generation Web site.

A Linear Coupling Controller For Plate Vibration

This paper was given at the 5th Dynamics and Control of Systems and Structures in Space (DCSSS) conference by B. Liu, F. Golnaraghi and G. R. Heppler. The conference took place in July 2002 at King's College, Cambridge. A method for optimally placing the actuators for use with a linear coupling controller (LCC) applied to a thin plate with arbitrary boundary conditions is presented. The LCC is is shown to provide good control properties over a wide frequency range. [Taken from abstract]. This is a PDF file, so Adobe Acrobat software will be required in order to read it.

ABLE Engineering : Deployable Space Systems

This is the web site of ABLE Engineering, a company that designs and produces deployable space systems, structures, and solar arrays. The site devotes pages to solar arrays, payload structures and booms and describes the products, including data sheets for some. The 'News' section contains several full text technical publications authored by members of staff.

Advanced Polymeric & Metallic Composite Materials for Space and Aerospace Vehicle Structures and Strength Optimization of Composite Structures and their Certification

This is Research and Technology Organization (RTO) AGARD Lecture Series report, AGARD-LS-204, dated December 1995. This lecture series presents and discusses the sci entific problem of advanced polymer and metallic c omposite materials for aerospace structures, stren gth optimization of composite structures, and thei r certification. Some challenges of using composit e structures, including airframe concept definitio n, are studied. Fiber orientation optimization pri nciples for composite panels and shells are outlin ed. Procedures for certification of assemblies mad e out of composites are dealt with. Certification requirements, including requirements to estimate s tatic and fatigue strengths, are formulated. Desig n conditions for composite structures are analyzed , including development. For individual titles, see N96-23937 through N96-23946. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (33 kB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

AdvanceSpace

This site acts as an educational guide to quality scientific space content on the web and is maintained by a space systems engineer, space systems operator, space systems user and an electrical engineer. The site links to several different categories of information including innovative concepts (e.g. Mars Direct and SpaceHub), space organisations, NASA sites, interactive solar system resources, US DoD/military sites and technology transfer resources. There are also links to free space tools software, news sources, and space jobs as well as spacecraft design resources by space system. There is also a virtual spacecraft design lab, with a suggested chronological approach to the process.

Affordable Spacecraft : Design and Launch Alternatives

This web site provides access to a U.S. Congress, Office of Technology Assessment Background Paper, OTA-BP-ISC-60, January 1990. The paper examines several proposals for reducing the costs of spacecraft and other payloads, and describes launch systems for implementing them. The full text of the report is available online in PDF format (928K). Alternatively the front matter, table of contents and individual chapters can be accessed as a separate PDF files.

An Application of Anti-Optimization in the Process of Validating Aerodynamic Codes

This is a Virginia Polytechnic Institute and State University Department of Aerospace and Ocean Engineering PhD dissertation, by Juan R. Cruz, dated April 4, 2003. The primary objectives of the work performed for this dissertation were to develop an approach using anti-optimization in the process of validating aerodynamic analyses through experiments, and to evaluate the effectiveness of this approach. Since this is an applied study, a suitable aerodynamic analysis needing validation and an appropriate corresponding experiment were selected to serve as a testbed for the approach being developed. A combination of two aerodynamic codes integrated into an analysis to predict the maximum lift coefficient of a wing and a related wind tunnel experiment were chosen to exercise and evaluate the proposed approach. An interesting flight domain for the validation of this analysis is the combination of Mach and Reynolds numbers encountered by airplanes operating within the atmosphere of Mars. Thus, secondary objectives of the dissertation were assist in the validation of an analysis in the flight regime used by airplanes designed to fly in the Martian atmosphere, and to generate an aerodynamics database in this flight regime. Bibliographic and abstract details are available in HTML format. The full text of the document is accessible online in PDF format [4.86 Mb]. This title is part of Virginia Tech’s Electronic Thesis and Dissertation Collection (VT ETD)

An Operational Assessment of Concepts and Technologies for Highly Reusable Space Transportation (HRST)

This web site provides access to a report prepared by NASA's Highly Reusable Space Transportation Study, Integration Task Force, Operations, dated November 1998. The HRST study was one of a number of NASA invesigations into the possibility of major reductions in the cost of space transportation. This report focuses on identifying launch system architectures and technologies that will enable significantly lower payload delivery costs. The full text of the report is available online in PDF format (1 Mb), and can be downloaded from the Kennedy Space Center's Next Generation web site.

Ansari XPrize

The ANSARI X PRIZE is a $10,000,000 prize designed to jumpstart the space tourism industry. The prize will be awarded, by the the non-profit X Prize Foundation, to the first team that privately finances, builds & launches a spaceship able to carry three people to 100 kilometers (62.5 miles)and return to Earth safely and repeats the launch with the same ship within 2 weeks. Since its inception in May 1996, the X PRIZE Foundation has registered more than 20 teams from seven countries to compete for the prize. The site covers the latest news, images and FAQs, the rules, a message board and a newsletter that can be subscribed to via email.

Arianespace

Arianespace is a major competitor in commercial space transportation, and information is provided on its current and past launch vehicles. Launch logs, mission updates and press releases are contained on the site, and thus it is useful for news of latest and forthcoming developments in the Ariane programme. The company annual report and the technical information booklet for the Ariane 5 are accessible, Europe's Spaceport is described and access is provided to the full-text of the Arianespace newsletter, E-Space.

Attitude Control of a Spacecraft with Two Reaction Wheels

This paper was given at the 5th Dynamics and Control of Systems and Structures in Space (DCSSS) conference by Takateru Urakubo, Kazuo Tsuchiya and Katsuyoshi Tsujita. The conference took place in July 2002 at King's College, Cambridge. This paper deals with the attitude control of a rigid spacecraft with two reaction wheels. First, we derive a discontinuous state feedback law based on Lyapunov control. When the angular momentum of the system is zero, the derived controller makes the desired point the only stable equilibrium point of the system. Next, we investigate the behavior of the controlled system when the angular momentum is not zero but small. [Taken from abstract]. This is a PDF file, so Adobe Acrobat software will be required in order to read it.

Attitude Dynamics and Control of a Dual-Body Spacecraft using Variable-Speed Control Moment Gyros

This paper was given at the 6th Dynamics and Control of Systems and Structures in Space (DCSSS) conference by Marcello Romano and Brij N. Agrawal. The conference took place in July 2004 at Riomaggiore, Italy. The dynamics equations of a spacecraft consisting of two bodies mutually rotating around an axis are derived. One body contains a cluster of single-gimbal variable-speed Control Moment Gyros. The equations include all the inertia terms and are written in a general form, valid for any cluster configurations and any numbers of actuators in the cluster. A non-linear control law is designed for the spacecraft attitude and joint rotation. An acceleration-based steering law is used for the variable-speed Control Moment Gyros. The analytical results are tested by numerical simulations. A three-axis test-bed was designed and is in the final set-up phase. [Taken from abstract]. This is a PDF file, so Adobe Acrobat software will be required in order to read it.

ATV GNC during Rendezvous with ISS

This paper was given at the 5th Dynamics and Control of Systems and Structures in Space (DCSSS) conference by Martine Ganet, Isabelle Quinquis, Jerome Bourdon and Patrick Delpy. The conference took place in July 2002 at King's College, Cambridge. The Automated Transfer Vehicle (ATV) is a European cargo transfer vehicle designed to contribute to the logistic servicing of the International Space Station. This paper presents the ATV GNC design for the last meters of the rendezvous with the ISS. After a brief survey on ATV mission and ATV architecture, the architecture of the ATV GNC chain is described. According to the external and internal ATV constraints and to the rendezvous objectives, the GNC strategies are fully detailed and justified. Then we present the synthesis process of the control function based on flexible modes filtering and HĹ  method. This method is retained because of its adaptability to the frequential compromise needed between the various objectives and constraints. Finally, the achieved accuracy performances, stability and robustness margins of the ATV GNC show that the retained strategy and design are fully compliant with the requirements. [Taken from abstract]. This is a PDF file, so Adobe Acrobat software will be required in order to read it.

Automating the Process of Optimization in Spacecraft Design

This paper, prepared by Alex Fukunaga, Steve Chien, Darren Mutz, Robert L. Sherwood and Andre D. Stechert at the NASA Jet Propulsion Laboratory, was published on February 1, 1997. The paper describes the development of a set of metaheuristic optimisation algorithms, which has been configured for a particular optimisation problem by an adaptive problem solver based on artifical intelligence and machine learning. The full text of the report is accessible in PDF format so Adobe Acrobat software will be required in order to read it. The report is part of the BEACON eSpace collection at NASA Jet Propulsion Laboratory

Consultative Committee for Space Data Systems (CCSDS)

The Consultative Committee for Space Data Systems (CCSDS) is an international voluntary consensus organization of space agencies and industrial associates interested in mutually developing standard data handling techniques to support space research, including space science and applications. The web site provides access to a variety of information resources. These include information about CCSDS, its charter, history, functional model, organisational structure and current projects. The site also provides access to the CCSDS Library of Recommendations and other technical documents. These include the following: CCSDS Recommendations (Blue Books); CCSDS Draft Recommendations (Red Books); CCSDS Reports (Green Books); CCSDS Draft Reports (Draft Green Books); CCSDS Administrative Reports (Yellow Books); and, CCSDS Documents Under Review.

Critical Technologies for Hypersonic Vehicle Development

This is a NATO Research and Technology Organization (RTO) Educational Note, RTO-EN-AVT-116, Paris, December 2005. The material in this publication was assembled to support a Lecture Series under the sponsorship of the Applied Vehicle Technology Panel (AVT) held at the von Kármán Institute, Rhode-St-Genèse, Belgium, 14-18 May 2004. This RTO/VKI Lecture Series was focused on critical technologies in hypersonic vehicle development, including ground test, numerical simulation and flight test. The introduction comprised a historical overview on hypersonic vehicle development as well as a thorough review of ongoing vehicle development and flight-testing programs. To provide sufficient background information, lectures were presented on compressible flows of perfect and imperfect gases, with special attention given to shock-wave boundary-layer interactions, laminar to turbulent transition, and high temperature gas properties. Advancements in computational modeling capabilities for hypersonic vehicle design were addressed, and the ongoing need for validation data, as well as a consistent validation methodology, where highlighted. Specific critical technology areas, including trajectory aerothermal environment definition, system trade studies, propulsion systems, aerodynamic control laws, flight instrumentation, thermal protection systems and flight experiments were all addressed in separate lectures given by international experts. In all of the presentations the needs of future hypersonic flight vehicle development programs were addressed. Bibliographic and abstract details are available in HTML format. A table of contents, individual papers and the full text of the document (41.5 Mb) can be accessed online in PDF format

Design and Characterization of a Radiation Tolerant Triple Mode Redundant Sense Amplifier Flip-Flop for Space Applications

This is the full text of a Master's thesis by Second Lieutenant Mark E. Martin, USAF, AFIT/GE/ENG/06-39, which was presented to the Faculty Department of Electrical and Computer Engineering of Air University's Air Force Institute of Technology (AFIT), in March 2006. One of the more recently proposed flip-flop designs has been the sense amplifier flip-flop. It has gained acceptance in the commercial realm because of its power consumption, speed, setup time, clock line loading, and data line loading characteristics. In this thesis, a recently designed RADHARD version of D sense amplifier flip-flop was taken and a triple mode redundant version for space and radiation environment use was created. The design was created with valuable options to increase radiation hardness and to give end users greater flexibility in realizing their own radiation hardened version of flip-flop. In addition, a methodology for using a traditional circuit simulation tool, SPICE, was developed to test the operation of the flip-flop design for both normal conditions and under the influence of radiation. The prescribed level of radiation resilience was chosen to reflect the upper bound of radiation tolerant design which is equivalent to a 100MeV Fe ion interaction with Si. This work provides the results of the design effort and the characteristics of the final triple mode redundant sense amplifier flip-flop design both as a device which did not utilize any of the options created for use with the design and with various combinations of options employed. This work also provides information on a revolutionary technology coined by the author (S&IC Technology, Sensor and Integrated Circuit Technology) which when used in conjunction with the triple mode design of this work would realize a self-sensing, self-correcting, and self-repairing triple mode design which would be of immeasurable benefit to space applications, avionics, and terrestrial applications the world over. [Taken from abstract]. The full text is available in PDF format on the Scientific and Technical Information Network (STINET) which is provided by the Defense Technical Information Center (DTIC).

Development, Fabrication, and Ground Test of an Inflatable Structure Space-Flight Experiment

This is the full text of a thesis by Thomas Lee Philley, Jr. which was presented to the Air Force Institute of Technology (AFIT) in 2003. Since the first satellite launches of the 1950's, the requirements placed on space systems have evolved from the earliest beacons of Sputnik to the current state of the art technology. As requirements increase, space systems tend to grow in size and complexity, which in turn significantly increases the weight and cost of the system. In the current age of increasing requirements and limited budgets, the use of inflatable rigidizable structures provides a solution to reduce the costs associated with design, fabrication and launch of a space system while simultaneously increasing the deployment reliability and mission success of the system. However, due to insufficient data correlating ground tests to space flight results, the use of inflatable rigidizable structures in both the Air Force and industry has been very limited. Therefore, the goal of this research effort is to validate the ground testing methodology by correlating ground tests to space flight results of inflatable tubes. The Rigidizable Inflatable Get-Away-Special Experiment is a self-contained Space Shuttle experiment that will test the deployment and structural characteristics of three inflatable rigidizable tubes. Once inflated and rigidized, each tube will be excited using piezoelectric transducers in order to collect vibration data for structural characterization. This thesis will present the follow on to the preliminary design of the experiment along with the initial fabrication processes and ground testing results. [Taken from abstract]. The full text of the thesis is available in PDF format and is provided by the Air University ResearchWeb site.

Environmental Disturbance Modeling for Large Inflatable Space Structures

This is the full text of a MSc thesis by Donald J. Davis which was presented to the Graduate School of Engineering and Management of Air University's Air Force Institute of Technology (AFIT), in March 2001. It is available in PDF format. Abstract: Tightening space budgets and stagnating spacelift capabilities are driving the Air Force and other space agencies to focus on inflatable technology as a reliable, inexpensive means of deploying large structures in orbit. Recent improvements in rigidization techniques make the use of these inflatable structures feasible for a growing number of missions. For many of these missions, the primary design requirement is dimensional accuracy of the structure. Finite element analysis offers a means of predicting structural behavior in orbit. The analysis requires knowledge of external loads. This thesis examines the environmental disturbances which act upon large, orbiting structures. Calculations are made on a base model to relate the torques generated by these disturbances to the orbital altitude. This facilitates identification of the critical loads for large, inatable structures. An environmental disturbance model is then developed in MATLAB. The model calculates the critical loads on each element of a faceted structure as it propagates through its orbit. A basic structure is defined and entered into the model. Results and analysis for various orbits are presented to verify accuracy of the code and validate the derived torque-altitude relationships.

European Space Agency (ESA) Science and Technology Home Page

The European Space Agency's ESA Science web site brings together a large range of information resoruces. There are descriptions of past, present and planned missions including: Cluster II, Mars Express, SMART-1, Ulysses, Huygens, Rosetta, and SOHO. Other sections of the site bring together information on the solar system, astrophysics, fundamental physics, and payload and advanced concepts. The eduacational support area provides access to a variety of media resources including images, video clips, spacecraft 3D models, spacecraft orbits and publications.

Evaluation of the SPH Method for the Modelling of Spall in Anisotropic Alloys

This paper was given at the 5th Dynamics and Control of Systems and Structures in Space (DCSSS) conference by Tom De Vuyst, Rade Vignjevic, Neil K. Bourne and James Campbell. The conference took place in July 2002 at King's College, Cambridge. Spall caused by hypervelocity impacts at the lower range of velocities could result in significant damage to spacecraft. A number of polycrystalline alloys, used in spacecraft manufacturing, exhibit a pronounced anisotropy in their mechanical properties. The aluminium alloy AA 7010, whose orthotropy is a consequence of the meso-scale phase distribution or grain morphology, has been chosen for this investigation. The material failure observed in plate impact was simulated using an explicit finite element code and a smoothed particle hydrodynamics (SPH) code. A number of spall models where used, and the Hugoniot Elastic Limit (HEL) and spall strength have been studied as a function of orientation, and compared to experimental results. [Taken from abstract]. This is a PDF file, so Adobe Acrobat software is required in order to read it.

Force-limited Acceleration Spectra Derivation by Random Vibration Analysis: Methodological Cases and Industrial Application

This paper was given at the 6th Dynamics and Control of Systems and Structures in Space (DCSSS) conference by L. Trittoni and M. Martini. The conference took place in July 2004 at Riomaggiore, Italy. The standard methods used for the computation of Random Load Factors are based on Miles' formula. Nevertheless, standard methods have the following limitations: Do not allow taking into account the flexibility of the supporting structure; Assume that the acoustic load and the mechanical vibration at interface are statistically independent; Do not allow taking into account spatial variations of the acoustic field. These limitations can be overcome by performing a system Random Vibration Analysis, and deriving the interface force resultant. This methodology has been verified with simple test cases and applied in the frame of SOLAR CPD project. [Taken from abstract]. This is a PDF file, so Adobe Acrobat software will be required in order to read it.

Formation Flight of Autonomous Aerial Vehicles

This is a senior design project report subimtted by Ryan Becker, Chris Borowski and Ognjen Petrovic in June, 2004 to the Santa Clara University. This Santa Clara University’s Aerial Robotics Team developed an autonomous fleet of Uninhabited Aerial Vehicles (UAVs) capable of performing aerial reconnaissance and demonstrating basic formation flying capabilities. In a single plane configuration, the team exploited the capabilities of a commercial autopilot in order to automatically fly through a pre-determined set of navigational waypoints and using real-time video feed in order to image and provide open-loop tracking of specific targets. This capability was be showcased in the international Association for Unmanned Vehicle Systems International (AUVSI) UAV competition in June 2004. In a two-plane follow-the-leader configuration, a human pilot flys a lead plane, and a chase plane automatically follows the lead plane’s trajectory. This is accomplished through the use of Ground ControlStation software, written by the team, that collects trajectory information from both planes and controls the follow-the-leader formation. In performing this project, the team has accomplished three significant objectives. First, it has successfully developed a flight system that will prove to be competitive in the AUVSI competition. Second, it has demonstrated an impressive multi-UAV flight capability that demonstrates the power of multi-UAV formations for enhancing the ability of UAVs to perform scientific, civil, humanitarian, and national defense missions. Finally, it has established a viable and impressive multi-UAV test bed for future SCU robotics education and research projects. The full text of the report can be accessed as PDF document.

Generic Robust Attitude Determination (GRADe)

This paper was given at the 5th Dynamics and Control of Systems and Structures in Space (DCSSS) conference by D. Dungate, M. Allery and M. Shelley. The conference took place in July 2002 at King's College, Cambridge. The GRADe study has investigated attitude determination areas offering potentialimprovements in ADCS cost, robustness and performance, with applicability acrossa range of mission types. The primary areas of investigation were: Use of low mass/cost sensors based on Micro Systems Technology (MST, Improved attitude determination algorithms to combine available data from a number of disparate attitude sensors. Candidate MST gyro sensors and an enhanced quaternion estimation algorithm were investigated in detail, having potential applicability as a viable alternative to the use of conventional sensors and algorithms, while also demonstrating graceful degradation and improved robustness. [Taken from abstract]. This is a PDF file, so Adobe Acrobat software will be required in order to read it.

Guidelines for Mass Properties Control on International Space and Missile Systems - Society of Allied Weight Engineers (SAWE) Recommended Practice 2

The objective of the Society of Allied Weight Engineers Recommended practice 2, is to provide a reference book of guidelines for the establishment of an effective mass properties control program. The document has been compiled by a panel of mass properties engineers, and draws specifically on the experience of the Space Shuttle/Space Lab programme. It was prepared by the Society of Allied Weight Engineers Government-Industry Workshop. The document was issued in March 1985, and revised in December 1995. Please note that this document has been superseded by recommended practices 9 and 11. This is a PDF format document. MS Word 95 and HTML versions are also available from the SAWE Recommended Practices web site.

Incorporating Uncertainty into Conceptual Design of Space Systems Architectures

This working paper (ESD-WP-2003-01.01) was published by the Massachusetts Insitute of Technology, Engineering Systems Division in 2003 and was written by Daniel E. Hastings, Annalisa L. Weigel and Miles A. Walton. The environment in which space systemsare developed and operated can be classified as nothing less than dynamic. However, it is clear that the methods and tools relied on in conceptual design are based on static assumtpions and leave little room for anything more than snapshots of the product and its environment. This paper introduces an approach to challenge that model and instead quantify and compare space system architectures around the central theme of uncertainty, with emphasis on policy uncertainty, as well as, technical and market uncertainty. Two cases of implementation are presented and three generalised principles are proposed that flow from the analysis: 1) engineering systems must be designed with uncertainty as one of the centralorganising principles, 2) since engineering systems have management and social dimensions and thus involve human interactions, there is an irreducible uncertainty associated with these dimensions that will affect the design of the system and 3) uncertainty in use may allow the engineering system to satisfy quite different missions from the original one intended. [Taken from abstract]. This is in PDF format so Adobe Acrobat software will be required in order to read it.

Input Shaping for Reducing Vibrations Following Orbit Adjustment and Slewing of Spacecraft

This paper was given at the 5th Dynamics and Control of Systems and Structures in Space (DCSSS) conference by Arun K. Banerjee. The conference took place in July 2002 at King's College, Cambridge. This paper considers two problems requiring vibration suppression, one following thruster firing for orbit adjustment, and the other following minimum time rest-torest slewing by control moment gyros. Solution to the first problem is basically a new application of the well-known three-impulse sequence for robust vibration suppression. For the second problem, a torque-time profile is assumed with limits on maximum torque and jerk and unknown switching times at the corners. These unknowns are determined by solving a minimization problem subject to the constraints of zero residual vibration, zero sensitivity to modeling error, and the terminal slewing conditions. Open loop results show significant reduction of vibrations. [Taken from abstract]. This is a PDF file, so Adobe Acrobat software will be required in order to read it.

Managing Space Radiation Risk in the New Era of Space Exploration

This is a full text book made available by National Academies Press written by Committee on the Evaluation of Radiation Shielding for Space Exploration, National Research Council and dated 2008. As part of the Vision for Space Exploration (VSE), NASA is planning for humans to revisit the Moon and someday go to Mars. An important consideration in this effort is protection against the exposure to space radiation. That radiation might result in severe long-term health consequences for astronauts on such missions if they are not adequately shielded. To help with these concerns, NASA asked the NRC to further the understanding of the risks of space radiation, to evaluate radiation shielding requirements, and recommend a strategic plan for developing appropriate mitigation capabilities. This book presents an assessment of current knowledge of the radiation environment; an examination of the effects of radiation on biological systems and mission equipment; an analysis of current plans for radiation protection; and a strategy for mitigating the risks to VSE astronauts. [Taken from abstract]. The full text is available to read online in open book format.

Marshall Technical Reports Server (MTRS)

This service can be searched on its own from this site, or as part of the NASA Technical Reports Server (NTRS). The service is made up of selected full text and abstracts and citations of NASA reports from the Technical Publications Office. Most of the recent reports are available in full as PDF files, older reports have only citations and abstracts. The service can be searched by keyword, or browsed by date.

Mass properties control for space vehicles : Society of Allied Weight Engineers (SAWE) Recommended Practice 11

The purpose of the Society of Allied Weight Engineers (SAWE) Recommended Practice 11, Revision Letter B, is to provide guidelines for monitoring, controlling, and reporting mass properties of spacecraft, launch vehicles, and exo-atmospheric missiles. The document was prepared by the SAWE Government - Industry Workshop. It was issued on 3 June 2000. This is a text document in PDF format.

Microcosm Inc.

Established in 1984, Microcosm is a small business, specializing in reducing space mission cost. It is currently developing via contracts with U.S. Air Force Research Laboratory, the Scorpius family of ultra-low-cost launch vehicles. The company also provides services and products to space mission engineers, educational programmes, aerospace software tools, and a selection of astronautics books that can be ordered online. The site includes a company profile, press releases, and information on products, sevices and expertise. This includes access to a number of publications relating specifically to Scorpius. The company's list of other publications includes Space Mission Analysis and Design, Reducing Space Mission Cost, and the Journal of Reducing Space Mission Cost.

Miniature Loop Heat Pipe with a Flat Evaporator - Thermal Modelling - Experimental Results

This technical report (NLR-TP-2002-273) was published by NLR (the National Aerospace Laboratory of the Netherlands) in 2002 and was written by A. A. M. Delil and V. Baturkin. This report contains two papers, being: - "Modelling of a Miniature Loop Heat Pipe with a Flat Evaporator", presented at the 32th International Conference on Environmental Systems (San Antonio, Texas, 14-18 July 2002). - "Experiments on Heat transfer Phenomena in a Miniature Loop Heat Pipe with a Flat Evaporator", presented at the 12th International Heat Pipe Conference (Moscow, Kostrama, Moscow, 19-24 May 2002). The reported activities were carried out within the INTAS-UKRAINE project 95-0196 "Research of Heat & Mass Transfer Processes in Passive Two-Phase Systems for Heat Transportation and Temperature Control for Usage in Energy Saving Equipment", by a team led by the project co-ordinator and scientific responsible, A.A.M. Delil (NLR). The Ukrainian team, leader was V. Baturkin (National Technical University of Ukraine "Kyiv Polytechnic Institute KPI"). Other Ukrainian contributors to the project were employed at KPI (O. Habatuk, Yu. Friedrichson, Yu. Khmelev, V. Kravec, D. Oliferenko, V. Savina, A. Savchenko, K. Shcoda, S. Zhuk and T. Zinchenko), at the National Space University "Kharkiv Aviation Institute" (G.A. Gorbenko, P.G. Gakal, K.A. Malukhin, V.I. Ruzaykin, N.I. Ivanenko, E.I. Ganja, N.A. Nrus, A.P. Sazonov and K.S. Epifanov), and at the "Institute for Low-Temperature Physics and Engineering of the National Academy of Sciences of Ukraine (V.V. Abraimov and L. Kolibaev). [Taken from abstract]. The full text is available as a PDF file.

Mission Design and System Requirements for a Multiple-Function Orbital Transfer Vehicle

Written by Hans F. Meissinger, John T. Collins, this paper was presented at the AIAA Space Technology Conference and Exposition at Albuquerque, New Mexico in September 1999. It presents functional and design concepts, as well as a number of scenarios, for use of a low-cost simple Orbital Transfer Vehicle. Preliminary cost estimates, a development schedule, and a list of maneuver performance requirements are also included. This is a PDF file [194k] so Adobe Acrobat software will be required in order to read it.

Modeling, Analysis and Optimization of Cylindrical Stiffened Panels for Reusable Launch Vehicle Structures

This web site provides access to a University of Florida, PhD dissertation, by Satchithanandam Venkataraman, dated 1999. Bibliographic and abstract details are available in HTML format. The title page, contents and the full text of the document are accessible online in PDF format. This title is part of the University of Florida's Electronic Theses and Dissertations Project

Modelling of Active Space Structures for Vibration Control

This paper was given at the 6th Dynamics and Control of Systems and Structures in Space (DCSSS) conference by A. Tralli, L. Rutigliano, M. Olivier , D. Sciacovelli and P. Gaudenzi. The conference took place in July 2004 at Riomaggiore, Italy. Active materials offer many opportunities to improve the performance of space systems, among which the possibility to control the vibration of lightweight structures. In this paper, a FEM simulation of laminated shell structures with piezoelectric elements is used to study an active payload support developed as a technology demonstrator in the frame of an ESA program. The code is then used in conjunction with the MATLAB code to provide a preliminary evaluation of the response of the system, subject to closed loop control. [Taken from abstract]. This is a PDF file, so Adobe Acrobat software is required in order to read it.

Modelling of Impact on a Fuel Tank Using Smoothed Particle Hydrodynamics

This paper was given at the 5th Dynamics and Control of Systems and Structures in Space (DCSSS) conference by R. Vignjevic, T. De Vuyst, J. Campbell and N. Bourne. The conference took place in July 2002 at King's College, Cambridge. This paper describes a modelling approach for the simulation of hypervelocity impact on fuel tanks using the Smoothed Particle Hydrodynamics (SPH) method. To determine a suitable particle density, three two-dimensional axi-symmetric models were analysed. Then three-dimensional simulations with cylindrical and cubic penetrators were performed. For each analysis the transient pressure values at locations corresponding to experimental transducer locations were recorded. The pressure time histories are shown for the axi-symmetric and 3D models. The simulation results are compared with the experimental results. The purpose of the research was to demonstrate the capability and potential of SPH for simulating this type of problem. [Taken from abstract]. This is a PDF file, so Adobe Acrobat software will be required in order to read it.

Multifunction Structures in Satellite Design : Thermoelectric Elements Embedded into Structural Honeycomb Panels

This a research project report submitted by Benjamin Thomas Blaine in 2004 to the Santa Clara University, California. The objective of this research is to assess the feasibility of a particular multifunction structure concept: thermoelectric devices embedded into aluminum honeycomb panels of a satellite. The satellite design process is complex and difficult due to the physical and operating constraints, uncertain environments, and extreme operating conditions. To reduce launch costs, mass and volume of the satellite must be minimized. Therefore, satellites must be efficiently configured to conserve mass and volume, and to exploit the resources from the environment. A novel approach to this problem is the concept of a multifunction structure. A multifunction structure is a system that combines structural elements and various components of an entire system into one space, therefore conserving mass and volume. In this research work, Finite Element Analysis (FEA) is used to perform 252 Thermal Analysis Experiments with varying thermal and material parameters, and 4 Structural Analysis Experiments with or without multiple thermoelectric elements embedded into the structure. The results of the Thermal and Structural Experiments have shown that the concept is viable with a structure made of honeycomb with a thermal conductivity less than 1.0 W/m•K. The Aluminum Honeycomb structure has a thermal conductivity of 180.0 W/m•K. Honeycomb materials composed of materials such as polyimide foams seem to be a possible future solution to the problem. Studies have shown Polyimide foam to have a thermal conductivity of 0.10 W/m•K. Further research is recommended in order to investigate the development of low thermal conducting honeycomb structures and high efficiency thermoelectric elements. With the application of these low thermal conductivity structural materials, this particular multifunction structure has merit. The full text of the report can be accessed as PDF document

NASA : Hypersonic X-43A Takes Flight

The X-43A is a hypersonic, scramjet-powered research aircraft designed to fly at speeds up to Mach 10. This is a NASA mission web site which brings together the latest news, features and supporting resources. There are a number of high resolution images, as well as video clips, including that of the historic flight of November 16 2004 during which the X-43A's scramjet air breathing engine pushed the aircraft to nearly Mach 9.8, or 7,000 mph, as it flew at about 110,000 feet. The site also provides access to a PDF format X-43A Fact Sheet.

NASA Aeronautics Research Mission Directorate (ARMD)

The ARMD at NASA Headquarters is responsible for guiding and managing NASA's aeronautics research, and defining the investments that NASA makes on behalf of the nation. NASA's 2003 Strategic Plan categorises the funding for is major research areas in topics designated as "Themes." The ARMD is responsible for the "Aeronautics Technology Theme" which consists of three integrated programmes: the Aviation Safety and Security Program; the Airspace Systems Program; and the Vehicle Systems Program. The programs are responsible for the research, development, and transfer of advanced concepts and technologies that are critical to the future of aeronautics in areas that are beyond the risk level or capability of other organisations. The enterprise team is represented by 5 NASA field centers, Ames Research Center, Dryden Flight Research Center, John H. Glenn Research Center, Langley Research Center, and Marshall Space Flight Center. The web site provides descriptions of the ARMD's three programmes areas, and make available a range of strategy, planning and report documents. Other sections of the site provide access to information on current events; exhibits and traveling programmes; educational activities including publications and software, web-based learning, distance learning, and student competitions, and multimedia collections. Links are provided to the ARMD Library which contains current documents and archives document and images, and links to the NASA centres which support the ARMD's programmes.

NASA Image eXchange (NIX)

The NASA Image eXchange (NIX) provides a single point of entry to various photographic databases of six NASA centers (Langley, Lewis, Ames, Dryden, Goddard and Johnson). Search capabilities of NIX include simple searches, complex searches, and browsing. NIX returns thumbnail sized images, textual descriptions, image numbers, links to higher resolution images, links to more information, and links to the NASA Center that stores each image. NIX also provides tips to users on searching, copyright information, and a comments section. NIX is currently being expanded to include additional photos from the remaining centers.

NASA Online Cost Models and Calculators

These Online NASA Cost Models allow the user to produce estimates of various cost categories for specified technical performance criteria and the estimate learning curve performance. Models include the following: Advanced Missions Cost Model (AMCM) for spacecraft, space transportation systems, aircraft, missiles, ships and land vehicles; Aircraft Turbine Engine Cost Model for aircraft turbine engines; Airframe Cost Model for aircraft airframes; Cost Estimating Cost Model for cost estimating Deep Space Network (DSN) projects; Expendable Launch Vehicles; Mission Operations Cost Model (MOCM) for mission operations of manned, unmanned and planetary spacecraft; Spacecraft/Vehicle Level Cost Model (SVLCM) for spacecraft, launch vehicle stages, engines and scientific instruments; inflation index calculator; and labor and materials worksheet. These models are written in JavaScript and require Netscape Navigator 2.01, Internet Explorer 3, or another browser with JavaScript capability. There is also a link to the NASA 2005 Cost Analysis Symposium Paper Presentations.

NASA Technical Standards Program

This site acts as a common access point for technical standards either developed by NASA, or adopted for use on NASA programmes. Standards developed by NASA, or pending development are available in full text in PDF format. The site offers a facility which allows for searching of preferred standards by document number, category, title or full text (NASA standards only). There is also access to a lessons learned/best practice database, information about standards under development, proposal submittals and links to technical standards organisations.

OBSIDIAN : Design of a Microsatellite

This is a senior design project report submitted by Vanessa Cuenca, Christina Jimenez, Jennifer Lundquist and Sara Nazemian in 2004 to the Santa Clara University, California. The use of microspacecraft such as small satellites is growing due to miniaturization and cost constraints. The university community is a leader in developing these very small, low-mass spacecraft often as part of hands-on education programs. OBSIDIAN (On Board Solar Intensity Directed Instrumentation for the Akoya Nanosatellite), a student satellite team, is investigating the use of these spacecraft. The mission of the OBSIDIAN spacecraft is to explore the use of such small autonomous devices as wireless differential solar pressure actuators for future solar sail missions. In exploring this technology, the OBSIDIAN project team has developed a sub-kilogram spacecraft to analyze and communicate data. Highlights of this work include collecting solar intensity data and on-board communications with Akoya. This microsatellite is slated for launch on a sounding rocket in July 2004 in order to verify critical design features; In addition, OBSIDIAN will be launched on-board Washington University in St. Louis’ twenty-kilogram AKOYA Nanosatellite in December 2005. This work has successfully demonstrated the utility of microspacecraft for specific classes of missions and presents, in detail, the current mechanical and electrical design of the OBSIDIAN microsatellite. The fukk text of the report can be accessed as PDF document.

Open Channel Foundation : Spacecraft Design and Space Missions

The aim of this US based organisation is to publish innovative open source software for a wide range of scientific and engineering applications. This section provides access to software applications for spacecraft design and space missions. The programmes include the SD_SURF collection of computer codes developed to assist in the design and analysis of space debris protection systems. CASE/A is an interactive trade study and analysis tool designed to increase productivity during all phases of systems engineering. Component Based Configurable Display Station Software (CBCDS) is architecture and prototype software for the development and certification of displays for system monitoring. The DET/MPS programmes model and simulate the Direct Energy Transfer and Multimission Spacecraft Modular Power System in order to aid both in design and in analysis of orbital energy balance. The Front End Processor (FEP) Real-Time Embedded Software performs command and data-processing functions for an aeronautical MIL-STD-1553B telemetry link and ground support equipment (GSE) in a spacecraft-equipment-testing environment. The Generalized Impact Stress Software (GISS) is designed to assist engineers in predicting impact stress caused by a variety of impact scenarios. IMP is a simulation language that is used to model missions around the Earth, Moon, Mars, or other planets. The Long-Term Orbit Predictor (LOP) trajectory propagation program is a useful tool in lifetime analysis of orbiting spacecraft. MLITEMP is a design tool that utilizes empirical equations to predict the hypervelocity impact damage to spacecraft and thermal effects of impact, including the amount of condensate formed. Other programmes include Galileo Interim Radiation Electron Model (GIRE), MOLecular FLUX Program (MOLFLUX), and Manual Procedures Viewer for Solaris x86 (MPV).

Open Channel Foundation

The aim of this US based organisation is to publish innovative open source software for a wide range of scientific and engineering applications. Much of the software available from the site has been produced from within the academic and research community. Over 200 software programmes are available. The site offers search and browse access to the software. The list of disciplines covered includes aerodynamics, antenna design and satellite communications; CAD CAM CAE, crack growth and fatigue analysis; digital signal processing, failure analysis, finite element analysis, life support systems, navigation and radar, optics and lasers, spacecraft design, and trajectories and orbital mechanics.

Propagating and Mitigating Uncertainty in the Design of Complex Multidisciplinary Systems

This is a California Institute of Technology, Department of Engineering and Applied Science PhD dissertation, by Daniel P. Thunnissen, defended 9 December, 2004. This thesis proposes a formal method to propagate and mitigate uncertainty in the design of complex multidisciplinary systems. Specifically, applying the proposed method produces a rigorous foundation for determining design margins. The method comprises five distinct steps: identifying tradable parameters; generating analysis models; classifying and addressing uncertainties; quantifying interaction uncertainty; and determining margins, analyzing the design, and trading parameters. As an example, the proposed method is applied to the preliminary design of a spacecraft attitude determination and control system. In particular, the design of the attitude control system on the Mars Exploration Rover spacecraft cruise stage is used. Use of the proposed method for the example presented yields significant differences between the calculated design margins and the values assumed by the Mars Exploration Rover project. Bibliographic and abstract details are available in HTML format. The full text of the document is accessible online in PDF format [3.08 Mb]. This title is part of California Institute of Technology's Electronic Thesis and Dissertation (ETD) Collection

Reducing Planetary Mission Cost by a Modified Launch Mode

Written by Hans Meissinger and Simon Dawson, this paper was presented at the 3rd IAA International Conference on Low-Cost Planetary Missions on April 27 - May 1 1998 at Pasadena, CA. It describes a modified launch mode and examines the various cost saving categories it offers. It compares the different mission and system requirements associated with the conventional and the modified launch mode, and describes cost differences and implementation factors. This is a PDF file [61k] so Adobe Acrobat software will be required in order to read it.

Review of NASA’s Aerospace Technology Enterprise: An Assessment of NASA’s Pioneering Revolutionary Technology Program

This is a report prepared by the National Research Council's Committee for the Review of NASA's Pioneering Revolutionary Technology (PRT), Washington, DC, National Academy Press, 2003. Please note this is a prepublication copy which might be subject to further editorial correction. The report provides a technical assessment of the quality of the PRT program and its components and provides recommendations for improving the program. Bibliographic and abstract information is available in HTML format, access to the full text is provided online in Open Book format with printable PDF files, and an abridged reports version is also available in PDF format

RSSD Electronic Preprint Delivery Service

Provided by ESA's Research and Scientific Support Department, this service provides access to over 1000 full text electronic preprints. The papers can be accessed by author, date and document reference.

Saab Group

The Saab Group is an international company specialising in aviation, space and defence. The site describes the companies business units, and provides investor information, key financial statistics, details of job opportunities. A searchable database of all products produced by the Saab Group is available. This includes the Gripen fighter, Unmanned Aerial Vehicles (UAVs), and the Saab 340 and 2000 family of commercial aircraft. There is also a publications database which provides access to the annual report, brochures and the in-house magazine. Documents are available in PDF format. In addition, there is a history of the Saab company, contact details, information on the press releases, as well as an image and a movie bank.

Society of Allied Weight Engineers (SAWE) - Recommended Practices

This web site provides access to the full-text of a number of recommended practice documents produced by the Society of Allied Weight Engineers (SAWE). The documents include the following: Requirements for Aircraft On-Board Weight and Balance System; Guidelines for Mass Properties Control on International Space and Missile Systems; Mass Properties Control System for Wheeled and Tracked Vehicles; Standard Coordinate Systems for Reporting the Mass Properties of Flight Vehicles; Mass Properties Management and Control For Military Aircraft; Weight and Balance Data Reporting Forms for Aircraft (including Rotorcraft); Weight and Balance Control System for Guided Missiles and Space Launch Vehicles; Weight and Balance Data Reporting Forms for Guided Missiles and Space Launch Vehicles; Mass Properties Control for Space Vehicles; Weight Control Technical Requirements For Naval Surface Ships; and Standard Coordinate System for Reporting Mass Properties of Surface Ships and Submarines. The documents are presented in a variety of formats including: PDF, MS Word 95 and MS Excel.

Solar Terrestrial Relations Observatory (STEREO)

This NASA's website provides information regarding the Solar Terrestrial Relations Observatory (STEREO) mission and objecives, multimedia, spacecrafts and instrumentation. Solar Terrestrial Relations Observatory (STEREO) provides a unique and revolutionary view of the Sun-Earth system. The satellites will trace the flow of energy and matter from the Sun to Earth as well as reveal the 3-D structure of coronal mass ejections and help us understand why they happen. STEREO will also provide alerts for Earth-directed solar ejections, from its unique side-viewing perspective adding it to the fleet of Space Weather detection satellites. STEREO has various capabilities such as the first stereo viewing of the Sun from out-of-Earth-orbit vantage points, the first imaging and tracking of space weather disturbances from the Sun to the Earth, the first continuous determination of interplanetary shock positions by radio triangulation, and the first simultaneous imaging of solar activity with in-situ measurement of energetic particles at 1 AU.

Space Environment Testbeds (SET)

The Space Environment Testbeds (SET) Project performs flight and ground investigations to address the Living With a Star (LWS) Program goal of understanding how the Sun/Earth interactions affect humanity. The SET Project is the element of the LWS Program that characterizes the space environment and its impact on hardware performance in space. the project goal is to improve the engineering approach to accommodation and/or mitigation of the effects of solar variability on spacecraft design and operations. Objectives: * Define the mechanisms for induced space environment and effects * Reduce uncertainties in the definitions of the induced environment and effects on spacecraft and their payloads * Improve design and operations guidelines and test protocols so that spacecraft anomalies and failures due to environmental effects during operations are reduced.

Spacecraft Design Concept to Explore Asteroids

This paper was given at the 6th Dynamics and Control of Systems and Structures in Space (DCSSS) conference by V. A. Volkov, V. A. Danilkin, V. G. Degtyar and G. G. Sytyi. The conference took place in July 2004 at Riomaggiore, Italy. Herein a research spacecraft design is theoretically and experimentally estimated. The suggested spacecraft ensures guidance of a massive penetrating probe impacted on an asteroid and carrying out telemetry analysis in synchronism with the spectroscope examination of the procedures accompanying the impact to determine physic-chemical and mechanical properties of the asteroid in-depth substance. Both the spacecraft and the penetrating probe being its component have propulsion and control systems providing direct probe penetration into the asteroid and the specified distance between position of the spacecraft equipped with telemetry instrumentation and the asteroid during the impact. The spacecraft is launched into the asteroid impact trajectory by the launch vehicles MOLNIYA, PROTON, TITAN-4, ARIANE-5, N-2, ANGARA. The spacecraft configuration will permit it to conduct effective investigations of asteroids approaching the Earth at a distance of up to one million kilometres. [Taken from abstract]. This is a PDF file, so Adobe Acrobat software will be required in order to read it.

Spacecraft Maximum Allowable Concentrations for Selected Airborne Contaminants : Volume 1

This web site provides access to a report prepared by the National Research Council's Subcommittee on Spacecraft Maximum Allowable Concentrations, National Academy Press, 1994. This report is part of a series which seeks to establish safe exposure limits to spacecraft contaminants for up to 180 days (for normal space station operations) and for short-term (1-24 hr) emergency exposures to a high level of contaminants. Volume 1 includes 11 compounds, while Volume 3 covers 12 compounds, Volume 2, 12 compounds, and Volume 4, 15 compounds. A brief abstract is available in HTML format, and the full text can be accessed online in Open Book format.

Spacecraft Maximum Allowable Concentrations for Selected Airborne Contaminants : Volume 2

This web site provides access to a report prepared by the National Research Council's Subcommittee on Spacecraft Maximum Allowable Concentrations, National Academy Press, 1996. This report is part of a series which seeks to establish safe exposure limits to spacecraft contaminants for up to 180 days (for normal space station operations) and for short-term (1-24 hr) emergency exposures to a high level of contaminants.Volume 2 includes 12 compounds, while Volume 1 covers 11 compounds, Volume 3, 12 compounds, and Volume 4, 15 compounds. A brief abstract is available in HTML format, and the full text can be accessed online in Open Book format

Spacecraft Maximum Allowable Concentrations for Selected Airborne Contaminants : Volume 3

This web site provides access to a report prepared by the National Research Council's Subcommittee on Spacecraft Maximum Allowable Concentrations, National Academy Press, 1997. This report is part of a series which seeks to establish safe exposure limits to spacecraft contaminants for up to 180 days (for normal space station operations) and for short-term (1-24 hr) emergency exposures to a high level of contaminants. Volume 3 includes 12 compounds, while Volume 1 covers 11 compounds, Volume 2, 12 compounds, and Volume 4, 15 compounds. A brief abstract is available in HTML format, and the full text can be accessed online in Open Book format.

Spacecraft Water Exposure Guidelines for Selected Contaminants : Volume 1

This is a full text book made vailable by National Academies Press written by Subcommittee on Spacecraft Exposure Guidelines, Committee on Toxicology, National Research Council dated 2004. To protect space crews from contaminants in potable and hygiene water, NASA requested that the National Research Council (NRC) provide guidance on how to develop water exposure guidelines and subsequently review NASA s development of exposure guidelines for specific chemicals. [Taken from abstract]. The full text is available to read online in open book format.

Spacecraft Water Exposure Guidelines for Selected Contaminants : Volume 2

This is a full text book made available by National Academies Press written by Committee on Spacecraft Exposure Guidelines, Committee on Toxicology, National Research Council and dated 2007. Construction of the International Space Station (ISS)—a multinational effort—began in 1999. In its present configuration, the ISS is expected to carry a crew of three to six astronauts for up to 180 days (d). Because the space station will be a closed and complex environment, some contamination of its internal atmosphere and water system is unavoidable. Several hundred chemical contaminants are likely to be found in the closed-loop atmosphere and recycled water of the space station. [Taken from abstract]. The full text is available to read online in open book format.

Spacecraft Water Exposure Guidelines for Selected Contaminants : Volume 3

This is a full text book made available by National Academies Press written by Committee on Spacecraft Exposure Guidelines, Committee on Toxicology, National Research Council and dated 2008. NASA maintains an active interest in the environmental conditions associated with living and working in spacecraft and identifying hazards that might adversely affect the health and well-being of crew members. Despite major engineering advances in controlling the spacecraft environment, some water and air contamination is inevitable. Several hundred chemical species are likely to be found in the closed environment of the spacecraft, and as the frequency, complexity, and duration of human space flight increase, identifying and understanding significant health hazards will become more complicated and more critical for the success of the missions. To protect space crews from contaminants in potable and hygiene water, NASA requested that the National Research Council NRC provide guidance on how to develop water exposure guidelines and subsequently review NASA's development of the exposure guidelines for specific chemicals. This book presents spacecraft water exposure guidelines (SWEGs) for antimony, benzene, ethylene glycol, methanol, methyl ethyl ketone, and propylene glycol. [Taken from abstract]. The full text is available to read online in open book format.

SpaceShipOne : Tier One Private Manned Space Program

Tier One project, by Scaled Composites, is the world's first privately funded manned space program and this site provides information on SpaceShipOne and its carrier aircraft White Knight. Information on the site covers the latest news, test logs (with details from every flight, press releases, photographs and FAQs.

SPRInT Inflatable Re-entry Study

This report has been prepared by students at Delft University as part of the final review of their Design Synthesis Exercise 2000. The object of this design exercise was to design a low-cost vehicle capable returning experiment results to Earth rapidly from the International Space Station (ISS). The report describes the design of a vehicle called SPRInT (Small Payload Re-entry Inflatable Transporter), which can carry a payload of up to 2 kilograms from the ISS back to Earth within 48 hours. The text of the report is available in PDF format.

Structural design applications of mathematical programming techniques

This is Research and Technology Organization (RTO) AGARD-AG-149, dated February 1971. The Structures and Materials Panel of the Advisory Group for Aerospace Research and Development (AGARD) comprises scientists , engineers and technical administrators from government, universities and industry, who are concerned with the advancement of aerospace research and development and with the provision of data necessary for the design and fabrication of the vehicles and equipment which NATO requires. The panel provides a mechanism for discussion, the exchange of information and for conducting co-operative theoretical and experimental studies in selected areas. This volume describes the present state of development of the use of mathematical programming techniques in the optimum design of aerospace and similar structures. Although optimization with respect to cost is considered when possible, the main emphasis is on the minimization of weight, due to the overwhelming importance of this parameter in aerospace applications, and also due to the fact that it is one of the few merit functions that can be defined with reasonable precision. The use of mathematical modelling techniques in the selection of materials is also discussed to the limited extent meaningful at the present time. This report is divided into four main sections. Bibliographic and abstract details are available in HTML format. A table of contents and the full text (16.19MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

Swedish Space Corporation : Space Systems Division

The Space Systems Division is a business unit of the Swedish Space Corporation (SSC). It is actively involved in the following: Small satellites and microsatellites; Microgravity experiments; Sounding Rockets (payload systems, sub-systems, and entire vehicles), Subsystems and equipment for space vehicles, Specification and procurement support for commercial telecom satellites, and Frequency co-ordination for commercial telecom satellites. The Division's web site provides access to a range of information sources including: products and services; news releases; and publications. The SSC's site also provides access to a number of full text technical papers covering microsatellites, microgravity experiments, and spacecraft propulsion systems. These papers are available in PDF format.

TacSats for Surveillance Verification and C3I

This is Research and Technology Organization (RTO) AGARD-CP-522, dated February 1993. The symposium dealt with small satellites used for tactical applications that might be of value to NATO. The 11 sessions covered TacSat concepts and needs, aspects of TacSat applications, TacSat system applications, communication concepts, launch systems, spacecraft bus, advanced technology, radar concepts, electro-optics concepts, and two panel discussions. The information generated by the symposium will be used by Working Group 16 to report on the utility of such satellites and applications to meet future NATO needs. For individual titles, see N93-29893 through N93-29913. Bibliographic and abstract details are available in HTML format. A table of contents, and the full text (59.03MB) of the document can be accessed online in PDF format. The document is contained in the RTO's Full Text Publication Library.

The Journal of Advanced Propulsion Methods

This is an online peer reviewed journal dealing with advanced theoretical propulsion methods, space craft design and space exploration. The purpose of the journal is to examine in a scientific context, modern theories and methodologies that may be applied to the area of space exploration and space craft propulsion. The full-text of articles is available in html and there is a readers forum and an opportunity to send letters to the editor as well as author guidelines and links. It is published in conjunction with Transtator Industries and the online Physics Group ESAA (Ex Somnium Ad Astra).

The National Space Transportation Policy : Issues for Congress

This web site provides access to a report produced by the U.S. Congress, Office of Technology Assessment, OTA-ISS-620, May 1995. This was the first of two reports produced as part of a broad OTA assessment of the U.S. space transportation technology and industrial base. It presents an examination of the U.S. Government's National Space Transportation Policy, in light of implementation plans prepared by NASA, DOD and the Transportation and Commerce Departments. The report is made available as part of the OTA Online Archive, hosted by Princeton University. The full text is accessible online in PDF format (2007K). Alternatively, the front matter, table of contents and individual chapters are available as separate PDF files

Universal Space Vehicle Design Concept to Defend the Earth against Asteroidal - Cometary Danger

This paper was given at the 6th Dynamics and Control of Systems and Structures in Space (DCSSS) conference by V. A. Volkov, V. A. Danilkin, V. G. Degtyar and G. G. Sytyi. The conference took place in July 2004 at Riomaggiore, Italy. Theoretical and experimental estimations are given on the structure of a universal space interceptor designed on the modular principle. The interceptor comprising one command-impact module and a variable number of separable impact modules, each with propulsion and guidance systems, can be injected into a trajectory towards an Earth approaching space object by launch vehicles MOLNIYA, PROTON, TITAN-4, ARIANE-5, N-2, and ANGARA. The universal space interceptor is capable to attack Earth approaching asteroids and comets of up to 300 m in diameter and destroy them into a number of safe fragments. In this case objects with a diameter of up to 100-150m are destroyed by non-nuclear kinetic module and to attack larger objects it is requiredto use a nuclear explosive device. [Taken from abstract]. This is a PDF file, so Adobe Acrobat software will be required in order to read it.

Weight and Balance Control System for Guided Missiles and Space Launch Vehicles : Society of Allied Weight Engineers (SAWE) Recommended Practice 9

This Society of Allied Weight Engineers (SAWE) Recommended Practice (RP-9) provides guidelines for monitoring, controlling and reporting mass properties of spacecraft, launch vehicles, and missiles. It was prepared by the Society of Allied Weight Engineers Government-Industry Workshop, and issued on 3rd June 2000. This is a PDF format document. An MS Word 95 version is also available for downloading from the SAWE Recommended Practices web site.

What's the Price of Low Cost?

This paper was presented at the 10th Annual AIAA/USU Conference on Small Satellites in September 1998 at Logan, UT by staff at Microcosm Inc. It examines ten case studies of space missions from the perspective of possible cost reduction strategies. Consideration is given to all mission segments including spacecraft, payload, ground systems. and mission operations. This is a PDF file [63k] so Adobe Acrobat software will be required in order to read it.

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