Hazard Analysis of Complex Spacecraft Using Systems- Theoretic Process Analysis *
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Tupod Press Release
G.A.U.S.S. SRL Via Lariana 5, Rome – Italy Phone: +39 06 97881440 GROUP OF ASTRODYNAMICS VAT No.: IT11900481000 FOR THE USE OF [email protected] SPACE SYSTEMS www.gaussteam.com TuPOD is ready for launch – Press Release – 5 December 2016 The TuPOD, a 3U CubeSat satellite and at the same time a deployer of TubeSat (a type of small satellite), originates from an innovative project of the Company G.A.U.S.S. Srl (Group of Astrodynamics for the Use of Space Systems), specialized in the development of satellites that are launcher platforms as well (like the previous satellites UniSat-5 and UniSat-6). The TuPOD is a CubeSat-type of satellite, with dimensions of 10x10x30cm, which will work itself as launch system for smaller satellites, the TubeSats. The TubeSats are a new type of Nanosatellites, cylindrically-shaped, not much bigger than an ordinary beverage can. To date, there wasn’t any launch possibility for this class of small satellites: with the TuPOD project, GAUSS Srl creates a new and affordable launch opportunity for the users of this new type of satellite. The TuPOD hosts two TubeSats onboard: TANCREDO I (Brazil) and OSNSAT (USA). Thanks to this specific kind of deployer – designed and built by GAUSS Srl – a couple of TubeSats are about to be UniSat-6 Platform released into Space for the first time ever. An important milestone for GAUSS Srl and for the whole Italian Aerospace Community. The TuPOD, in the middle, satellite/deployer for TubeSats from GAUSS Srl. On the right and on the left the TubeSats OSNSAT and TANCREDO I. -
A Zonal Safety Analysis Methodology for Preliminary Aircraft Systems and Structural Design
A Zonal Safety Analysis Methodology for Preliminary Aircraft Systems and Structural Design Chen, Z. and Fielding, J. P. School of Aerospace, Transport and Manufacturing, Cranfield University ABSTRACT Zonal Safety Analysis (ZSA) is a major part of the civil aircraft safety assessment process described in Aerospace Recommended Practice 4761 (ARP4761). It considers safety effects that systems/items installed in the same zone (i.e. a defined area within the aircraft body) may have on each other. Although the ZSA may be conducted at any design stage, it would be most cost-effective to do it during preliminary design, due to the greater opportunity for influence on system and structural designs and architecture. The existing ZSA methodology of ARP4761 was analysed but it was found to be more suitable for detail design rather than preliminary design. The authors therefore developed a methodology that would be more suitable for preliminary design and named it the Preliminary Zonal Safety Analysis (PZSA). This new methodology was verified by means of the use of a case-study, based on the NASA N3-X project. Several lessons were learnt from the case study, leading to refinement of the proposed method. These lessons included focusing on the positional layout of major components for the zonal safety inspection, and using the Functional Hazard Analysis (FHA)/Fault Tree Analysis (FTA) to identify system external failure modes. The resulting PZSA needs further refinement, but should prove to be a useful design tool for the preliminary design process. _____________________________________ INTRODUCTION This paper outlines the development of a methodology, hereafter referred to as the Preliminary Zonal Safety Historically, system safety analysis was primarily based Analysis (PZSA). -
Risk Assesment: Fault Tree Analysis
RISK ASSESMENT: FAULT TREE ANALYSIS Afzal Ahmed+, Saghir Mehdi Rizvi*Zeshan Anwer Rana* Faheem Abbas* +COMSAT Institute of Information and Technology, Sahiwal, Pakistan *Navy Engineering College National University of Sciences and Technology, Islamabad drafzal@ciitsahiwal>edu.pk, 03452325972 ABSTRACT The failure of engineering equipment causes loss of capital as well as human loss, injuries, and stoppage of production line. The hazards can be classified as safe, minor, major, critical and catastrophic Risk analysis or hazard analysis pin points the potential failures of engineering systems and or components when being used.. Failure mode and effects analysis is used to identify hazard and to make system safer. A system is broken down up to level of components and using reliability data the safety or probability of failure of assemblies and the system can be calculated. The failure mode and effects analysis is used with fault tree analysis to point the areas of a complex system where failure mode effect analysis is required. Fault tree analysis (FTA) is a technique which pinpoints any failure or severe accidents. It tells how things fail rather than emphasize on the design performance. It is a logic diagram connecting inputs an outputs using Boolean algebra. This paper shows how FTA can be applied to car carburetor failure and car brake failure. Key words : Risk Management, Reliability, Fault tree, Failure mode INTRODUCTION The world is full risk. We are at risk of accident minor. A failure of an aircraft may cause death when crossing a road or driving. We are at risk to passengers, while a machine may cause living in an apartment not properly designed. -
Launch / Tracking and Control Plan of Advanced Land Observing Satellite (ALOS) / H-IIA Launch Vehicle No
Launch / Tracking and Control Plan of Advanced Land Observing Satellite (ALOS) / H-IIA Launch Vehicle No. 8 (H-IIA F8) November 2005 Japan Aerospace Exploration Agency (JAXA) (Independent Administrative Agency) - 1 - Table of Contents Page 1. Overview of the Launch / Tracking and Control Plan 1 1.1 Organization in Charge of Launch / Tracking and Control 1 1.2 Person in Charge of Launch / Tracking and Control Operations 1 1.3 Objectives of Launch / Tracking and Control 1 1.4 Payload and Launch Vehicle 1 1.5 Launch Window (Day and Time) 2 1.6 Facilities for Launch / Tracking and Control 2 2. Launch Plan 3 2.1 Launch Site 3 2.2 Launch Organization 4 2.3 Launch Vehicle Flight Plan 5 2.4 Major Characteristics of the Launch Vehicle 5 2.5 Outline of the Advanced Land Observing Satellite (ALOS) 5 2.6 Securing Launch Safety 5 2.7 Correspondence Method of Launch information to Parties Concerned 6 3. Tracking and Control Plan 8 3.1 Tracking and Control Plan of the ALOS 8 3.1.1 Tracking and Control Sites 8 3.1.2 Tracking and Control Organization 8 3.1.3 Tracking and Control Period 8 3.1.4 Tracking and Control Operations 10 3.1.5 ALOS Flight Plan 10 3.1.6 Tracking and Control System 10 4. Launch Result Report 11 [List of Tables] Table-1: Launch Vehicle Flight Plan 13 Table-2: Major Characteristics of the Launch Vehicle 15 Table-3: Major Characteristics of the ALOS 17 Table-4: Tracking and Control Plan (Stations) of the ALOS 23 [List of Figures] Figure-1: Map of Launch / Tracking and Control Facilities 12 Figure-2: Launch Vehicle Flight Trajectory 14 Figure-3: Configuration of the Launch Vehicle 16 Figure-4: On-orbit Configuration of the ALOS 20 Figure-5: Access Control Areas for Launch 21 Figure-6: Impact Areas of the Launch Vehicle 22 Figure-7: ALOS Flight Plan 24 Figure-8: ALOS Footprint 25 Figure-9: ALOS Tracking and Control System 26 - 2 - 1. -
X103 H-IIB Launch Vehicle H-IIBロケット
Outdoor Exhibition Outdoor X103 H-IIB Launch Vehicle H-IIBロケット ■Purpose of Exhibition The domestically produced large rocket "H-IIB" is exhibited in the outdoor exhibition space. Most of this rocket has the same structure as the real rocket and served as a test. You can find the real parts in the chart including the first stage engine section, the first stage fuel tank, the center body section, the interstage adapter and the fairing, which are exhibited in the exhibition. The rest of the parts were made by referring to the actual rocket. When the rocket "H-IIB" is launched, two other main engines and four fixed rocket boosters are attached to the rocket. You can see the inside structure because the tank part is cut off. For making a light but strong rocket, it is manufactured like a honeycomb. For pouring low temperature liquid- hydrogen into the tank, the exterior of the rocket is coated by a thermal material. The rocket which is exhibited is also coated by using the same thermal material. Like this, the rockets were made by using the latest manufacturing technology and design techniques. We would like you to learn the structure of rocket and feel how big it is. ■Additional Knowledge Space Station had succeeded. The Japanese high- launching technology which put the rocket into the planned orbit accurately, and the connecting technology which controlled the HTV delicately and connected to the International Space Station in outer space, has been shown to the world. [The Other Rockets Exhibition in Japan] There are rocket exhibitions in regions where JAXA developed space technology (as of 2010).The Tanegashima Space Center is where the JAXA Research Institute is located in Tanegashima, Kagoshima Prefecture. -
Securing Japan an Assessment of Japan´S Strategy for Space
Full Report Securing Japan An assessment of Japan´s strategy for space Report: Title: “ESPI Report 74 - Securing Japan - Full Report” Published: July 2020 ISSN: 2218-0931 (print) • 2076-6688 (online) Editor and publisher: European Space Policy Institute (ESPI) Schwarzenbergplatz 6 • 1030 Vienna • Austria Phone: +43 1 718 11 18 -0 E-Mail: [email protected] Website: www.espi.or.at Rights reserved - No part of this report may be reproduced or transmitted in any form or for any purpose without permission from ESPI. Citations and extracts to be published by other means are subject to mentioning “ESPI Report 74 - Securing Japan - Full Report, July 2020. All rights reserved” and sample transmission to ESPI before publishing. ESPI is not responsible for any losses, injury or damage caused to any person or property (including under contract, by negligence, product liability or otherwise) whether they may be direct or indirect, special, incidental or consequential, resulting from the information contained in this publication. Design: copylot.at Cover page picture credit: European Space Agency (ESA) TABLE OF CONTENT 1 INTRODUCTION ............................................................................................................................. 1 1.1 Background and rationales ............................................................................................................. 1 1.2 Objectives of the Study ................................................................................................................... 2 1.3 Methodology -
Successful Mission of Tupod, an Innovative Cubesat, a Tubesats Deployer Manufactured Via Additive Manufacturing by CRP USA Using Windform® XT 2.0 Composite Material
Successful mission of TuPOD, an innovative CubeSat, a TubeSats deployer manufactured via Additive Manufacturing by CRP USA using Windform® XT 2.0 composite material ABSTRACT Small satellites provide a responsive alternative to larger, more expensive satellites. As demand grows, engineers must adapt these “nanosatellites” or CubeSats to provide new achievements and goals. One of these achievements is deploying TubeSats from International Space Station (ISS). TubeSats are cylindrical shape and are not compatible with normal CubeSats deployer platform (P-POD) on ISS, thus, an innovative nano-satellite, TuPOD (Tubesat-POD), was developed to address the challenge. TuPOD inaugurated a new era for scientists wanting to use small, highly reliable satellites. It is the first complete 3D printed satellite launched from the ISS, made by CRP USA from CRP Technology’s proprietary material Windform® XT 2.0, the ground breaking carbon fiber reinforced composite 3D printing material known for its mechanical properties, developed with CRP USA. (shown in Figure 1) Figure 1: TuPOD deployed © JAXA / NASA OVERVIEW The story of TuPOD began when a group of Brazilian Students needed to launch their TubeSat, TANCREDO-1, from ISS. They approached G.A.U.S.S. Srl (Group of Astrodynamics for the Use of Space Systems), an Italian company with close relationship to the University of Rome, to help them overcoming the challenge of launching their TubeSat from ISS. CRP USA LLC Headquarters Office 127 Goodwin Circle, Mooresville NC 28115 Phone 704-660-0258 GAUSS was faced with the challenge of designing an innovative system to deploy the first TubeSats into orbit that could act as both a satellite and release platform. -
Japan's Technical Prowess International Cooperation
Japan Aerospace Exploration Agency April 2016 No. 10 Special Features Japan’s Technical Prowess Technical excellence and team spirit are manifested in such activities as the space station capture of the HTV5 spacecraft, development of the H3 Launch Vehicle, and reduction of sonic boom in supersonic transport International Cooperation JAXA plays a central role in international society and contributes through diverse joint programs, including planetary exploration, and the utilization of Earth observation satellites in the environmental and disaster management fields Japan’s Technical Prowess Contents No. 10 Japan Aerospace Exploration Agency Special Feature 1: Japan’s Technical Prowess 1−3 Welcome to JAXA TODAY Activities of “Team Japan” Connecting the Earth and Space The Japan Aerospace Exploration Agency (JAXA) is positioned as We review some of the activities of “Team the pivotal organization supporting the Japanese government’s Japan,” including the successful capture of H-II Transfer Vehicle 5 (HTV5), which brought overall space development and utilization program with world- together JAXA, NASA and the International Space Station (ISS). leading technology. JAXA undertakes a full spectrum of activities, from basic research through development and utilization. 4–7 In 2013, to coincide with the 10th anniversary of its estab- 2020: The H3 Launch Vehicle Vision JAXA is currently pursuing the development lishment, JAXA defined its management philosophy as “utilizing of the H3 Launch Vehicle, which is expected space and the sky to achieve a safe and affluent society” and to become the backbone of Japan’s space development program and build strong adopted the new corporate slogan “Explore to Realize.” Under- international competitiveness. -
Cronología De Lanzamientos Espaciales
Cronología de lanzamientos espaciales Cronología de Lanzamientos Espaciales Año 2011 Copyright © 2009 by Eladio Miranda Batlle. All rights reserved. Los textos, imágenes y tablas que se encuentran en esta cronología cuentan con la autorización de sus propietarios para ser publicadas o se hace referencia a la fuente de donde se obtuvieron los mismos. Eladio Miranda Batlle [email protected] Cronología de lanzamientos espaciales Contenido 2011 Enero 20.05.2011 Telstar 14R (Estrela do Sul 2) 20.01.11 KH-12 USA224 20.05.2011 ST 2 / GSat 8 (Insat 4G) 20.01.11 Elektro-L 22.01.11 HTV 2 /Kounotori-2. Junio 28.01.11 Progress-M 09M/ARISSat 07.06.2011 Soyuz TMA-02M/27S Febrero 10.06.2011 Aquarius (SAC D, ESSP 6) 15.06.2011 Rasad 1 01.02.11 Cosmos 2470 Geo-lk-2 20.06.2011 ZX 10 (ChinaSat 10) 06.02.11 RPP (USA 225,NROL 66) 21.06.2011 Progress-M 11M 16.02.11 ATV 2 (Johannes Kepler) 27.06.2011 Kosmos 2472 (Yantar- 24.02.11 Discovery F39(STS133) 4K2M #7) /PMM(Leonardo)/ELC 4 30.06.2011 ORS 1 26.02.11 Kosmos 2471(Urangan-K1) Julio Marzo 06.07.2011 SJ 11-03 04.03.11 Glory/ E1P/ KySat 1/ 08.07.2011 Atlantis F33 (STS-135) Hermes MPLM 2-04 (Raffaello 05.03.11 X-37B OTV-2 (USA 226) F4) PSSC-Testbed 2 11.03.11 SDS-3 6(USA 227, NROL 11.07.2011 TL 1B (Tianlian) 27) 13.07.2011 Globalstar MO81/83/85/88/89/91 15.07.2011 GSat 12 Abril 15.07.2011 SES 3 / Kazsat 2 16.07.2011 GPS-2F 2 (Navstar 66, 04.04.11 Soyuz TMA 21 USA 231) 09.04.11 BD-2 13 18.07.2011 Spektr-R (Radio-Astron) 15.04.11 NOSS-35A (USA 229, 26.07.2011 BD-2 I4 NROL 34) 29.07.2011 SJ 11-02 20.04.11 -
NASA Fault Tree Handbook with Aerospace Applications
Fault Tree Handbook with Aerospace Applications Version 1.1 FFFaaauuulllttt TTTrrreeeeee HHHaaannndddbbbooooookkk wwwiiittthhh AAAeeerrrooossspppaaaccceee AAAppppppllliiicccaaatttiiiooonnnsss Prepared for NASA Office of Safety and Mission Assurance NASA Headquarters Washington, DC 20546 August, 2002 Fault Tree Handbook with Aerospace Applications Version 1.1 FFFaaauuulllttt TTTrrreeeeee HHHaaannndddbbbooooookkk wwwiiittthhh AAAeeerrrooossspppaaaccceee AAAppppppllliiicccaaatttiiiooonnnsss NASA Project Coordinators: Dr. Michael Stamatelatos, NASA Headquarters Office of Safety and Mission Assurance Mr. José Caraballo, NASA Langley Research Center Authors: NASA Dr. Michael Stamatelatos, NASA HQ, OSMA Lead Author: Dr. William Vesely, SAIC Contributing Authors (listed in alphabetic order): Dr. Joanne Dugan, University of Virginia Mr. Joseph Fragola, SAIC Mr. Joseph Minarick III, SAIC Mr. Jan Railsback, NASA JSC Fault Tree Handbook with Aerospace Applications Version 1.1 FFFaaauuulllttt TTTrrreeeeee HHHaaannndddbbbooooookkk wwwiiittthhh AAAeeerrrooossspppaaaccceee AAAppppppllliiicccaaatttiiiooonnnsss Acknowledgements The project coordinators and the authors express their gratitude to NASA Office of Safety and Mission Assurance (OSMA) management (Dr. Michael Greenfield, Deputy Associate Administrator and Dr. Peter Rutledge, Director of Enterprise Safety and Mission Assurance) and to Mr. Frederick Gregory, NASA Deputy Administrator, for their support and encouragement in developing this document. The authors also owe thanks to a number of reviewers -
China's Long-Range View
coverFEB2012FINAL_Layout 1 1/19/12 11:56 AM Page 1 2 AMERICA AEROSPACE February 2012 FEBRUARY 2012 FEBRUARY China’s long-range view Design for demise Orbiting twins tackle Moon’s mysteries A PUBLICATION OF THE AMERICAN INSTITUTE OF AERONAUTICS AND ASTRONAUTICS Support the AIAA Foundation CFC #53057 Impact, Inspire, Invest Our Vision A simple, compelling philosophy drives our commitment to education in science, technology, engineering, and math: Make it exciting, make it empowering, and make it fun. e AIAA Foundation: Advances STEM education through K–12 education programs, reaching more than 10,000 students each year. Prepares students for the workforce with merit-based scholarships and annual student conferences worldwide. Promotes professional achievement through our competitive honors and awards programs for industry professionals and educators. Fosters innovation as students and professionals participate in design competitions, paper competitions, and peer presentations. www.aiaafoundation.org 11-0638 aa ad.indd 1 9/9/11 2:15 PM TOC.FEB2012_AA Template 1/17/12 2:24 PM Page 1 February 2012 DEPARTMENTS EDITORIAL 3 Page 4 The power option. INTERNATIONAL BEAT 4 High-speed rail will impact airliner markets. ASIA UPDATE 8 China’s long-range view. WASHINGTON WATCH 12 ‘New’ defense strategy takes center stage. Page 20 CONVERSATIONS 16 With John Gedmark. ELECTRONICS UPDATE 20 Page 12 Man vs. machine: The future of electronic attack. ENGINEERING NOTEBOOK 24 Science spacecraft learn self-control. GREEN ENGINEERING 26 The greening of satellite propulsion. Page 24 OUT OF THE PAST 44 CAREER OPPORTUNITIES 46 FEATURES ORBITING TWINS TACKLE MOON’S MYSTERIES 32 By precisely measuring the Moon’s gravity, NASA’s twin GRAIL space- craft will also unlock secrets about Earth and other planets. -
A Differential Games Approach for Analysis of Spacecraft Post-Docking Operations
A DIFFERENTIAL GAMES APPROACH FOR ANALYSIS OF SPACECRAFT POST-DOCKING OPERATIONS By TAKASHI HIRAMATSU A DISSERTATION PRESENTED TO THE GRADUATE SCHOOL OF THE UNIVERSITY OF FLORIDA IN PARTIAL FULFILLMENT OF THE REQUIREMENTS FOR THE DEGREE OF DOCTOR OF PHILOSOPHY UNIVERSITY OF FLORIDA 2012 c 2012 Takashi Hiramatsu 2 I dedicate this to everyone that helped me write this manuscript. 3 ACKNOWLEDGMENTS My biggest appreciation goes to my advisor Dr. Norman G. Fitz-Coy for his great help and support. Every time I talked to him he motivated me with critical responses and encouraged me whenever I was stuck in the middle of my research. I also thank my committee Dr. Warren Dixon, Dr. Gloria Wiens, and Dr. William Hager for their supports. Finally, I thank my colleagues in Space Systems Group and all other friends, who directly or indirectly helped me throughout the years I spent at University of Florida. 4 TABLE OF CONTENTS page ACKNOWLEDGMENTS..................................4 LIST OF TABLES......................................8 LIST OF FIGURES.....................................9 ABSTRACT......................................... 11 CHAPTER 1 INTRODUCTION................................... 13 1.1 Spacecraft Rendezvous and Docking..................... 13 1.1.1 Cooperative Scenarios......................... 14 1.1.2 Noncooperative Scenarios....................... 14 1.2 Small Satellites................................. 15 1.3 Game Theoretic Approach........................... 15 2 MATHEMATICAL BACKGROUND FOR THE APPROACH............ 18 2.1 Differential Games and Control Theory.................... 18 2.1.1 Minimax Strategy............................ 20 2.1.2 Nash Strategy.............................. 20 2.1.3 Stackelberg Strategy.......................... 21 2.1.4 Open-Loop Strategies for Two-Person Linear Quadratic Differential Games.................................. 23 2.2 Numerical Methods to Optimal Control Problem............... 24 2.3 Bilevel Programming.............................