DOCSLIB.ORG

1 Spacecraft Systems Design

Total Page：16

File Type：pdf, Size：1020Kb

Download full-text PDF Read full-text
1 Spacecraft Systems Design Spacecraft Systems Design Short Course Prof. Craig Underwood Surrey Space Centre University of Surrey 1 Jun. 2012 © University of Surrey Key References Fortescue, P., Stark, J. and Swinerd, G. (Eds) Spacecraft Systems Engineering, John Wiley & Sons, Chichester, 2003. ISBN: 0-41-61951-5 Cruise, A.M., Bowles, J.A., Patrick, T.J. and Goodall, C.V. Principles of Space Instrument Design, Cambridge University Press, Cambridge, 1998. ISBN: 0-521- 45164-7 Griffin, M.D. and French, J.R. Space Vehicle Design, AIAA Education Series, Washington D.C., 1991. ISBN: 0-930403-90-8 Sellers, J.J. Understanding Space (3rd Ed.), Space Technology Series, McGraw- Hill, New York, 2005. ISBN:0-07-340775-5 Houston, A. and Rycroft, M. (Eds) Keys to Space, McGraw-Hill, Boston, 1999. ISBN: 0-07-029438-0 Larson, W.J. and Wertz, J.R. (Eds) Space Mission Analysis and Design (2nd Ed), Space Technology Series, Kluwer Academic Publishers, 1992. ISBN: 0-7923- 1998-2 Jun. 2011 2 © University of Surrey Introduction Spacecraft Systems Design involves techniques from a variety of scientific and engineering disciplines. The aim of this course is to introduce the key space system design principles and techniques. In particular, the course focuses on mechanical and thermal design of space vehicles, as well as the electrical and system design of their key sub-systems. The course ends by setting a spacecraft design exercise. Delegates should leave the course with a knowledge of: · Launching, Orbits and Manoeuvres; · The Space Environment & its Effects; · Spacecraft Platform Systems & Design; · Space Mission Analysis & Design; . Applications of Small, Low-Cost Satellites Jun. 2011 3 © University of Surrey Introduction What is a Spacecraft? Magellan – NASA’s Venus Space Probe, Launched 1989 4 Aug. 2011 Sellers, J.J. Understanding Space, pp. 367, McGraw-Hill Inc., 1994 © University of Surrey Introduction Sellers, J.J. Understanding Space, pp. 369, McGraw-Hill Inc., 1994 Aug. 2011 5 © University of Surrey Introduction 6 Aug. 2011 Sellers, J.J. Understanding Space, pp. 369, McGraw-Hill Inc., 1994 © University of Surrey Elements of a Space Mission 7 Aug. 2011 7 Jun. 2012 © University of Surrey Key References Fortescue, P., Stark, J. and Swinerd, G. (Eds) Spacecraft Systems Engineering, John Wiley & Sons, Chichester, 2003. ISBN: 0-41-61951-5 Sellers, J.J. Understanding Space (3rd Ed.), Space Technology Series, McGraw-Hill, New York, 2005. ISBN:0-07-340775-5 Houston, A. and Rycroft, M. (Eds) Keys to Space, McGraw-Hill, Boston, 1999. ISBN: 0-07-029438-0 Larson, W.J. and Wertz, J.R. (Eds) Space Mission Analysis and Design (2nd Ed), Space Technology Series, Kluwer Academic Publishers, 1992. ISBN: 0-7923-1998-2 Wertz, J.R. Spacecraft Attitude Determination and Control, Reidel, Dordrecht, 1978. Aug. 2011 8 © University of Surrey Space Mission Design All space missions are born of a set of requirements – objectives to be fulfilled within certain constraints such as budget and time (the latter sometimes defined by launch windows for exploration missions. The requirements of the mission must be well-defined and concise. Systems engineering plans and integrates technical solutions within the schedule and within budget. Much of the methodology resembles that from software engineering. The mission analysis should describe the mission, its operations, system configuration, subsystem specifications, quality assurance and reliability. The specification should flow-down from systems to subsystems to components to parts at increasing levels of detail to ensure consistency. Aug. 2011 9 © University of Surrey Space Mission Design Space Segment, Ground Segment, Launcher Segment Aug. 2011 Houston, A. and Rycroft, M. (Eds) Keys to Space, 10 McGraw-Hill, Boston, 1999. pp. 5-4 © University of Surrey Space Mission Design Space Segment, Ground Segment, Launcher Segment Aug. 2011 Houston, A. and Rycroft, M. (Eds) Keys to Space, 11 McGraw-Hill, Boston, 1999. pp. 5-5 © University of Surrey Space Mission Design In designing a space mission: - mission objectives must be clearly defined (requirements definition) - mission users must be defined (e.g. scientific community) - resource availability (typically budget, political considerations, and technological maturity) - design constraints (schedule, mass and power typically) Mission architecture must be defined on the basis of system level trade-off studies to achieve a given performance Aug. 2011 12 © University of Surrey Space Mission Design From the mission requirements and constraints, an iterative design based on a trade-off analysis is developed – often altering the mission requirements if necessary. All space missions comprise several major systems defining its architecture: - spacecraft payload which performs the function of the mission - spacecraft bus which supports the payload (housekeeping) - launcher to place the spacecraft into its required orbit - orbital trajectory which defines the ground coverage - ground system which controls the mission operations through a communications infrastructure Aug. 2011 13 © University of Surrey Space Mission Design The systems architecture is the end product of the mission design process consisting of an overall system design, and covering all elements of the system with the necessary specifications to meet the stated mission objectives in an optimum way. The systems architecture does not enter into the design of the individual elements any further than is required to establish its functional, cost and schedule feasibility in accordance with the corresponding assumptions included in the systems plan The systems architecture establishes clearly the mutual dependence of the various systems elements, thus providing a complete and structured framework of interdependency formulas for the requirements and characteristics of the various elements Aug. 2011 14 © University of Surrey Space Mission Design Houston, A. and Rycroft, M. (Eds) Keys to Space, McGraw-Hill, Boston, 1999. pp. 5-9 Aug. 2011 15 © University of Surrey Space Mission Design Phases of a Space Mission Aug. 2011 Houston, A. and Rycroft, M. (Eds) Keys to Space, 16 McGraw-Hill, Boston, 1999. pp. 5-7 © University of Surrey Space Mission Design Space mission design is an iterative process. All space missions have a well-defined programme of development with regular reviews with the client, e.g. ESA. Reviews provide independent, critical assessment and provide a forum for communication. It also ensures that documentation is clear and concise. ESA standards are described in ECSS (European Cooperation for Space Standardisation) standards documents. rd Aug. 2011 Sellers, J.J. Understanding Space (3 Ed.), Space 17 Technology Series, McGraw-Hill, New York, 2005. © University of Surrey pp.362 Mission and Operations Tasks Mission Design & Manufacturing Team Operations Team Aug. 2011 18 Sellers, J.J. Understanding Space (3rd Ed.), Space Technology © University of Surrey Series, McGraw-Hill, New York, 2005. pp.634 Mission and Operations Tasks Mission Definition and Design Sub Systems Design and Manufacturing AIT Testing EVT Launch Mission Commission & Operations Aug. 2011 Space Missions at Surrey 19 © University of Surrey Getting into Space Thought Experiment I Suppose we took a cannon to the top of a high mountain and experimented with firing projectiles: How fast would the projectile have to go to follow path 3? Motion in a circle implies a centripetal force must be acting • here supplied by gravity. Thus, mv2/r = GMm/r2 i.e. V2 = GM / r © University of Surrey Getting into Space Thought Experiment II Suppose our mountain was 300 km high (as high as a typical Space Shuttle orbit), then: Given the mass of the Earth, M = 5.977 x 1024 kg the radius of the orbit, r = 6.671 x 106 m and the Gravitational Constant G = 6.672 x 10-11 m3 s-2 kg-1 => V2 = 6.672 x 10-11 x 5.977 x 1024 / 6.671 x 106 i.e. V = 7.732 km s-1 ('Mach 24') Thus, in order to achieve a low-Earth orbit, we have to be able to attain speeds of the order of 7-8 km s-1 - this presents a challenge! © University of Surrey Getting into Space Thought Experiment III Do all orbits have to be circular? No, they can be any conic section: • Circle • Ellipse • Parabola • Hyperbola The last two trajectories are not ‘closed’, and so a spacecraft in these orbits will escape from the Earth altogether. © University of Surrey Rockets Principle: ROCKET EXHAUST GAS ROCKET MOVING WITH: EXHAUST GASSES MOVING WITH: MASS = MR MASS = MP VELOCITY = VR VELOCITY = VP MOMENTUM CONSERVATION MR . VR = MP . VP © University of Surrey Rockets The Rocket Equation: Suppose we have a rocket of mass 'M', which increases its velocity by an amount 'dV' after burning an amount of fuel 'dM', and ejecting the exhaust at a relative velocity 've', then by conservation: M dV = ve dM. Integrating this expression over time, the total velocity change, ‘DV' after burning a mass of fuel 'm', is : DV = ve loge [(M+m)/M]. This is more usually expressed in terms of specific impulse, Isp: DV = go Isp loge [ Minitial / Mfinal] -2 where go = 9.807 ms -the Earth's surface gravitational acceleration. Isp is a measure of the effectiveness of the rocket and depends upon the fuel/ oxidizer combination used, and upon the design of the rocket engine -particularly its exhaust nozzle. A 'good' rocket has a high Isp. © University of Surrey Rockets Rockets and Chemistry : A good rocket has a high exhaust velocity, thus, the molecules that comprise the exhaust products should be small and light so that they can move quickly: Water (H2O) and nitrogen (N2)
Load more

Recommended publications
  • A Quantitative Human Spacecraft Design Evaluation Model For
    A QUANTITATIVE HUMAN SPACECRAFT DESIGN EVALUATION MODEL FOR ASSESSING CREW ACCOMMODATION AND UTILIZATION by CHRISTINE FANCHIANG B.S., Massachusetts Institute of Technology, 2007 M.S., University of Colorado Boulder, 2010 A thesis submitted to the Faculty of the Graduate School of the University of Colorado in partial fulfillment of the requirement for the degree of Doctor of Philosophy Department of Aerospace Engineering Sciences 2017 i This thesis entitled: A Quantitative Human Spacecraft Design Evaluation Model for Assessing Crew Accommodation and Utilization written by Christine Fanchiang has been approved for the Department of Aerospace Engineering Sciences Dr. David M. Klaus Dr. Jessica J. Marquez Dr. Nisar R. Ahmed Dr. Daniel J. Szafir Dr. Jennifer A. Mindock Dr. James A. Nabity Date: 13 March 2017 The final copy of this thesis has been examined by the signatories, and we find that both the content and the form meet acceptable presentation standards of scholarly work in the above mentioned discipline. ii Fanchiang, Christine (Ph.D., Aerospace Engineering Sciences) A Quantitative Human Spacecraft Design Evaluation Model for Assessing Crew Accommodation and Utilization Thesis directed by Professor David M. Klaus Crew performance, including both accommodation and utilization factors, is an integral part of every human spaceflight mission from commercial space tourism, to the demanding journey to Mars and beyond. Spacecraft were historically built by engineers and technologists trying to adapt the vehicle into cutting edge rocketry with the assumption that the astronauts could be trained and will adapt to the design. By and large, that is still the current state of the art. It is recognized, however, that poor human-machine design integration can lead to catastrophic and deadly mishaps.
    [Show full text]
  • An Integrated Reliability and Physics-Based Risk Modeling Approach for Assessing Human Spaceflight Systems
    An Integrated Reliability and Physics-based Risk Modeling Approach for Assessing Human Spaceflight Systems Susie Go*a, Donovan Mathiasa, Chris Mattenbergerb, Scott Lawrencea, and Ken Geea a NASA Ames Research Center, Moffett Field, CA, USA b Science and Technology Corp., Moffett Field, CA, USA Abstract: This paper presents an integrated reliability and physics-based risk modeling approach for assessing human spaceflight systems. The approach is demonstrated using an example, end-to-end risk assessment of a generic crewed space transportation system during a reference mission to the International Space Station. The behavior of the system is modeled using analysis techniques from multiple disciplines in order to properly capture the dynamic time- and state- dependent consequences of failures encountered in different mission phases. We discuss how to combine traditional reliability analyses with Monte Carlo simulation methods and physics-based engineering models to produce loss- of-mission and loss-of-crew risk estimates supporting risk-based decision-making and requirement verification. This approach facilitates risk-informed design by providing more realistic representation of system failures and interactions; identifying key risk-driving sensitivities, dependencies, and assumptions; and tracking multiple figures of merit within a single, responsive assessment framework that can readily incorporate evolving design information throughout system development. Keywords: PRA, simulation, physical modeling, reliability modeling, risk-informed design. 1. INTRODUCTION Over the years, NASA has developed a working knowledge and body of standards to guide both the design and the evaluation of safe human space flight systems. These include specific requirements on procedures and best practices in addition to quantitative mission risk requirements.
    [Show full text]
  • Spacecraft Research and Design
    Spacecraft Research & Design Center Naval Postgraduate School NAVAL POSTGRADUATESCHOOL Thesis/Research Opportunities The Spacecraft Research and Design Center at the Naval The mission of the Naval Analytical and experimental investigation are performed to develop Postgraduate School consists of six state-of-the art laboratories: technologies for acquisition, tracking and pointing of flexible Postgraduate School is to Fltsatcom Laboratory, Spacecraft Attitude Dynamics and Control spacecraft with optical payloads; active vibration control, Isolation, enhance the security of the Laboratory, Smart Structures laboratory, Spacecraft Design and suppression using smart structures; space robotics, satellite United States of America Center, NPS-AFRL Optical Relay Mirror Spacecraft Laboratory, servicing, space system design, and computer aided design tools. through graduate and and Satellite Servicing Laboratory. These laboratories are used for professional education programs Three-Axis Simulator 1 Three-Axis Simulator 2 instruction and research in space system engineering and space • Slew maneuver torque profile to minimize settling time. focusing on the unique needs of operations curricula. The emphasis has been on providing • Active vibration isolation/suppression using smart sensors students with hands-on experience in the design, analysis, and and actuators the military officers. These programs are sustained by testing of space systems and systems and to provide students research and advanced studies directed towards the needs • Fast steering mirror pointing/jitter control facilities for experimental research. The emphasis in the research • Improved multi-body flexible dynamics and control models of the Navy and DoD. Our goals are to increase the combat h areas is on acquisition, tracking and pointing of flexible • Adaptive Optics Control effectiveness of the armed forces of the U.S.
    [Show full text]
  • Design Standard Spacecraft Charging and Discharging
    JERG-2-211A DESIGN STANDARD SPACECRAFT CHARGING AND DISCHARGING May 10, 2012 Revision A Japan Aerospace Exploration Agency JERG-2-211A This is an English translation of JREG-2-211A. Whenever there is anything ambiguous in this document, the original document (the Japanese version) shall be used to clarify the intent of the requirement. Disclaimer The information contained herein is for general informational purposes only. JAXA makes no warranty, express or implied, including as to the accuracy, usefulness or timeliness of any information herein. JAXA will not be liable for any losses relating to the use of the information. Published by Japan Aerospace Exploration Agency Safety and Mission Assurance Department 2-1-1 Sengen Tsukuba-shi,Ibaraki 305-8505, Japan JERG-2-211A － Contents － 1. Purpose and Scope of Application .............................................................................................. 1 2. Related Documents ....................................................................................................................... 2 2.1 Applicable documents .................................................................................................................. 2 2.2 References ................................................................................................................................... 2 3. Terminology, Definition, and Abbreviation ..................................................................................... 3 3.1 Terminology and definition .............................................................................................................
    [Show full text]
  • Spacecraft Design Innovations in the Apl Space Department
    ERIC J. HOFFMAN SPACECRAFT DESIGN INNOVATIONS IN THE APL SPACE DEPARTMENT The Applied Physics Laboratory has made several important contributions to spacecraft design in the fields of Doppler tracking and navigation, attitude control, mechanisms, drag compensation, antennas, spacebome computing, and autonomous satellite positioning. Many of these innovations have since become standard spacecraft techniques. Others are being rediscovered in the light of renewed interest in small, mission-capable satellites. INTRODUCTION Since its beginning in 1959, the APL Space Department the satellite's orbit. Researchers at other laboratories had has designed, built, and launched fifty-four satellites thought about this problem, but had oversimplified the (Fig. 1). Fifty-one were completely assembled at APL; analysis, concluding (incorrectly) that the orbit could not three (the Delta series) were built jointly with McDonnell be found at all or that it could be found only with low Douglas. An additional twenty-three satellites were fab­ accuracy. Only Guier and Weiffenbach solved the theo­ ricated by government and industry to APL'S designs as retical problem correctly, concluding that a highly accu­ part of the Navy Navigation Satellite System (Transit) rate orbit could be determined using Doppler data gath­ production runs. The Space Department has also provid­ ered from a single pass. ed about seventy scientific instruments and numerous en­ In March 1958, Guier and Weiffenbach were discuss­ gineering subsystems for launch on non-APL spacecraft. ing their Doppler tracking results with Frank T. McClure. Despite its relatively small size, the Space Department It occurred to McClure to invert the problem: if the has been remarkably productive in introducing and im­ position of the satellite were accurately known, Doppler plementing simple and effective technical solutions to data could tell an observer on the ground his unknown spacecraft engineering problems.
    [Show full text]
  • Design and Utilization of the Stanford Vision-Based Navigation Testbed for Spacecraft Rendezvous
    IWSCFF 17-26 DESIGN AND UTILIZATION OF THE STANFORD VISION-BASED NAVIGATION TESTBED FOR SPACECRAFT RENDEZVOUS Connor Beierle,∗ Joshua Sullivan,y and Simone D’Amicoz Vision-based navigation is an enabling technology for the new generation of on-orbit ser- vicing and debris-removal missions. In contrast to legacy metrology systems such as radar, lidar, and the global positioning system, vision sensors are passive, simple, and do not place stringent requirements on the spacecraft design in terms of power, weight, or inter-satellite communication. Most importantly, vision-based navigation has the potential to support ac- curate autonomous relative operations from hundreds of kilometers down to virtually zero separation in many orbit regimes. The demonstration of this capability calls for a new testbed capable of stimulating cameras in a representative sensing environment to assess functional- ity, performance, and robustness of the navigation tasks before deployment in space. Based on typical requirements posed by future autonomous rendezvous missions, the goal of this re- search is to design a virtual-reality sensor-in-the-loop optical stimulator with ten-arcseconds angular resolution and over eight orders of magnitude in radiometric dynamic range. This paper addresses the key challenges in the design, development, calibration, verification, and utilization of such an optical stimulator. A rendezvous hardware-in-the-loop simulation is then conducted to verify the functionality and performance of a new optical angles-only nav- igation article. This test demonstrates a successful estimation and recovery of the relative translational state of a non-stellar object using optical angles-only measurements to within 1% of the ground-truth.
    [Show full text]
  • Arxiv:1906.05079V1 [Astro-Ph.IM] 12 Jun 2019
    Draft version June 13, 2019 Typeset using LATEX twocolumn style in AASTeX61 A THOUSAND EARTHS: A VERY LARGE APERTURE, ULTRALIGHT SPACE TELESCOPE ARRAY FOR ATMOSPHERIC BIOSIGNATURE SURVEYS Daniel´ Apai,1 Tom D. Milster, Dae Wook Kim,2 Alex Bixel,3 Glenn Schneider,3 Ronguang Liang,4 and Jonathan Arenberg5 1Steward Observatory and the Lunar and Planetary Laboratory, The University of Arizona, Tucson, AZ 85721 2James C. Wyant College of Optical Sciences, The University of Arizona, Tucson, AZ 85721 3Steward Observatory, The University of Arizona, Tucson, AZ 85721 4College of Optical Sciences, The University of Arizona, Tucson, AZ 85721 5Northrop Grumman Aerospace Systems, Redondo Beach, CA 90278 (Received July 1, 2016; Revised September 27, 2016; Accepted June 13, 2019) Submitted to AJ ABSTRACT An outstanding, multi-disciplinary goal of modern science is the study of the diversity of potentially Earth-like planets and the search for life in them. This goal requires a bold new generation of space telescopes, but even the most ambitious designs yet hope to characterize several dozen potentially habitable planets. Such a sample may be too small to truly understand the complexity of exo-earths. We describe here a notional concept for a novel space observatory designed to characterize 1,000 transiting exo-earth candidates. The Nautilus concept is based on an array of inflatable spacecraft carrying very large diameter (8.5m), very low-weight, multi-order diffractive optical elements (MODE lenses) as light-collecting elements. The mirrors typical to current space telescopes are replaced by MODE lenses with a 10 times lighter areal density that are 100 times less sensitive to misalignments, enabling light-weight structure.
    [Show full text]
  • Integrating Spacecraft Systems
    NASA TECHNICAL NOTE __NASA TN- D-3049.- < o* d 0 Cr) d z c 4 VI 4 z NASA TN D-3049 INTEGRATING SPACECRAFT SYSTEMS By Allen L. Franta Goddard Space Flight Center Greenbelt, Md. NATIONAL AERONAUTICS AND SPACE ADMINISTRATION For sale by the Clearinghouse for Federal Scientific and Technical Information Springfield, Virginia 22151 - Price $0.30 ABSTRACT The integration of a satellite or spacecraft system consists of combining the mechanical and electrical subsystem elements into a single entity through the application of logical processes, and takes into account the physical and functional aspects of the subsystem interre- lationships. It is characterized by three levels of effort: (a) project management integration, (b) integration of physical systems, and (c) in- tegration by subsystem Combination through advanced design. The over-all coordination of a spacecraft project is a responsibility of a project management group assigned the task of translating functional concepts into an operating spacecraft. The actual physical integration of a spacecraft system is accomplished through the combined work of a mechanical integration group and an electronic integration group work- ing together in a concerted effort. Subsystem combination through advanced electronic design is a more sophisticated form of partial spacecraft integration. It is accomplished through improved circuit design utilizing the most advanced electronic packaging techniques. ii CONTENTS Abstract ................................ .. ii INTRODUCTION .......................... .. 1
    [Show full text]
  • System Engineering of Photonic Systems for Space Application
    System Engineering of Photonic Systems for Space Application Michael D. Watson and Jonathan E. Pryor NASA Marshall Space Flight Center, Huntsville, AL 35812 Abstract The application of photonics in space systems requires tight integration with the spacecraft systems to ensure accurate operation. This requires some detailed and specific system engineering to properly incorporate the photonics into the spacecraft architecture and to guide the spacecraft architecture in supporting the photonics devices. Recent research in product focused, elegant system engineering has led to a system approach which provides a robust approach to this integration. Focusing on the mission application and the integration of the spacecraft system physics incorporation of the photonics can be efficiently and effectively accomplished. This requires a clear understanding of the driving physics properties of the photonics device to ensure proper integration with no unintended consequences. The driving physics considerations in terms of optical performance will be identified for their use in system integration. Keywords: System Engineering, Optical Transfer Function, Optical Physics, Photonics, Image Jitter, Launch Vehicle, System Integration, Organizational Interaction 1. INTRODUCTION TO SYSTEM ENGINEERING PRINCIPLES Engineering of photonics systems has many effects that must be accounted for in order to support the optical functions. The photonic system’s interaction with the spacecraft and the environment has many different and complex effects.1,2 There are 4 system engineering aspects that must be understood in order to properly define and develop any system: Mission Context, Driving Physics, Organizational Dynamics, and Policy & Law constraints. The Mission Context sets many of the environments and system parameters. Astronomy missions (x-ray, ultra violet, visible, infrared), solar physics, planetary observation, planetary landers, planetary rovers, or launch vehicle monitoring are all missions with very different environments and spacecraft busses.
    [Show full text]
  • JERG-2-000 Spacecraft Design Standard
    JERG-2-000A SPACECRAFT DESIGN STANDARD March 29, 2013 Revision A Japan Aerospace Exploration Agency JERG-2-000A This is an English translation of JERG-2-000. Whenever there is anything ambiguous in this document, the original document (the Japanese version) shall be used to clarify the intent of the requirement. Disclaimer The information contained herein is for general informational purposes only. JAXA makes no warranty, express or implied, including as to the accuracy, usefulness or timeliness of any information herein. JAXA will not be liable for any losses relating to the use of the information. Published by Japan Aerospace Exploration Agency Safety and Mission Assurance Department 2-1-1 Sengen Tsukuba-shi, Ibaraki 305-8505, Japan i JERG-2-000A Contents 1. SCOPE ............................................................................................................................ 1 2. RELATED DOCUMENTS ................................................................................................ 1 2.1 Applicable Documents .............................................................................................. 1 3. DEFINITION OF TERMS ................................................................................................. 1 4. RELATIONSHIP BETWEEN LIFECYCLE AND DESIGN STANDARD OF SPACECRAFTS .............................................................................................................. 3 5. MEANING AND STRUCTURE OF DESIGN STANDARD ................................................ 4 6. APPLICATION
    [Show full text]
  • The Spacecraft Design/Flight Experience at the Undergraduate Level
    Session 1302 The Spacecraft Design/Flight Experience at the Undergraduate Level Lieutenant Colonel Billy R. Smith, Jr., PhD United States Air Force Department of Aerospace Engineering United States Naval Academy Professor Daryl Boden Department of Aerospace Engineering United States Naval Academy Mr Robert Bruninga Department of Aerospace Engineering United States Naval Academy Professor (Emeritus) William Bagaria Department of Aerospace Engineering United States Naval Academy On 30 September 2001, at 0240Z, the United States Naval Academy launched its own space program with the first successful flight of the USNA Small Satellite Program. USNA-1, Prototype Communications Satellite (PCSat) lifted off from Alaska Aerospace Development Corporation’s Kodiak Launch Complex on Kodiak Island, AK aboard the National Aeronautics and Space Administration (NASA) Kodiak Star Athena I rocket. PCSat successfully separated from the payload upper deck (PUD) (the shelf that supported the satellites during flight) on schedule. First contact with PCSat took place 97 minutes after launch via portable ground equipment carried to Alaska by the PCSat launch support team. With PCSat, USNA joins Weber State University and the United States Air Force Academy (USAFA) in the small group of purely undergraduate institutions that have enjoyed success with student-designed and built small satellites. The PCSat development effort was an ambitious attempt to inject reality into the First Class (senior) design experience for Astronautics students. The Department of Aerospace Engineering requires Astronautics students to complete a spacecraft design course (EA470) during the spring semester of their First Class year. This course challenges the students to consolidate and focus all of the mathematical, scientific, and engineering skills acquired in the major on conceptualization and design of a workable spacecraft.
    [Show full text]
  • Failures in Spacecraft Systems: an Analysis from The
    FAILURES IN SPACECRAFT SYSTEMS: AN ANALYSIS FROM THE PERSPECTIVE OF DECISION MAKING A Thesis Submitted to the Faculty of Purdue University by Vikranth R. Kattakuri In Partial Fulfillment of the Requirements for the Degree of Master of Science in Mechanical Engineering August 2019 Purdue University West Lafayette, Indiana ii THE PURDUE UNIVERSITY GRADUATE SCHOOL STATEMENT OF THESIS APPROVAL Dr. Jitesh H. Panchal, Chair School of Mechanical Engineering Dr. Ilias Bilionis School of Mechanical Engineering Dr. William Crossley School of Aeronautics and Astronautics Approved by: Dr. Jay P. Gore Associate Head of Graduate Studies iii ACKNOWLEDGMENTS I am extremely grateful to my advisor Prof. Jitesh Panchal for his patient guidance throughout the two years of my studies. I am indebted to him for considering me to be a part of his research group and for providing this opportunity to work in the fields of systems engineering and mechanical design for a period of 2 years. Being a research and teaching assistant under him had been a rewarding experience. Without his valuable insights, this work would not only have been possible, but also inconceivable. I would like to thank my co-advisor Prof. Ilias Bilionis for his valuable inputs, timely guidance and extremely engaging research meetings. I thank my committee member, Prof. William Crossley for his interest in my work. I had a great opportunity to attend all three courses taught by my committee members and they are the best among all the courses I had at Purdue. I would like to thank my mentors Dr. Jagannath Raju of Systemantics India Pri- vate Limited and Prof.
    [Show full text]