STK Start Training Manual

Total Page:16

File Type:pdf, Size:1020Kb

STK Start Training Manual STK Level 1 and Level 2 Training Manual STK VERSION 12.2, AUGUST, 2021 © 2021 ANALYTICAL GRAPHICS INC. ALL RIGHTS RESERVED Page 1 of 388 www.agi.com Table of Contents STK Level 1 and Level 2 Training Manual 1 Table of Contents 2 Level 1 - Beginner Training 24 Free License 24 Lesson One: Build Scenarios 26 Problem Statement 26 Solution 26 What You Will Learn 26 Video Guidance 27 Set Up a New STK Scenario 27 Changing Central Body 27 Creating a New Scenario 27 Saving the Scenario 29 The STK Workspace 29 Menus and Tools 30 Object Browser 30 Understand the STK Windows 30 Understand the 2D Graphics Window 31 2D Window Defaults Toolbar 31 2D Graphics Toolbar 31 Microsoft Bing™ Maps 32 3D Graphics Window 32 Using the Mouse 33 Page 2 of 388 www.agi.com 3D Graphics Defaults Toolbar 33 3D Graphics Toolbar 33 Globe Manager 34 Terrain Server 35 Animation Toolbar 36 Timeline View 37 Time Display 37 Summary 38 Lesson Two: Objects and Properties 39 Problem Statement 39 Solution 39 What You Will Learn 39 Video Guidance 40 Creating a New Scenario 40 Updating STK Databases 40 Create the New Scenario 41 Modifying Properties 41 Basic Time 41 Basic Units 42 Basic Database 42 Description 42 Global Attributes 42 Insert STK Objects Tool 44 New Object Preferences 45 Objects and Methods 45 Page 3 of 388 www.agi.com Satellite Object 46 View in 3D 51 Set the Nadir alignment back to ECI velocity constraint 53 Aircraft Object 56 Renaming Objects 57 Properties 57 View in the Graphics windows 61 Set the Animation Time 64 View in 3D 64 View in 3D 66 View in the Graphics windows 67 View in 3D 68 Animate the Scenario 69 Area Target Object 70 View in 2D 71 View in 3D 72 3D Graphics Window Properties - Label Declutter 73 Summary 79 Lesson Three: Access Report and Graphs 80 Problem Statement 80 Solution 80 What You Will Learn 80 Video Guidance 81 Create a New Scenario 81 Satellite Tracking Station 81 Page 4 of 388 www.agi.com Streaming Terrain from a Terrain Server 83 Castle Rock Teleport Properties 83 Castle Rock Teleport Field-of-View 84 Sensor Object Field-of-View 85 Set the Half Angle 85 Insert Satellites 86 The Access Tool 87 2D Graphics Window 88 Timeline View 89 Access Report 90 Access Graph 90 Azimuth Elevation Range Report (AER) 91 External Reports and Graphs 92 View Outside of STK 93 Extend the Sensor's Range 93 Refresh the Access Report 94 Report Units 94 Quick Reports 95 View the quick report 95 Setting the Scenario Time from a Report 96 Stored View Tool 96 The Report & Graph Manager 98 Styles 99 Groups, Data Providers and Elements 100 Data Providers by Object 101 Page 5 of 388 www.agi.com Units 102 Report Contents 102 Dynamic Display 104 3D Graphics Data Display 104 View the Data 105 Summary 106 Lesson Four: Movies and Visual Data Files 107 Problem Statement 107 Solution 107 What You Will Learn 107 Video Guidance 108 Create a New Scenario 108 Post Typhoon Aerial Photography Flight Route 109 Naha 109 Amami Oshima 109 Minamidaito 110 3D Graphics Window Properties - Label Declutter 110 Mission Aircraft 111 Create Waypoints 112 Adjust Altitude, Speed and Turn Radius 113 Adjust the Attitude 114 Change the Aircraft Object Model 114 Preparing the Scene 114 View in 3D 115 Edit PhotoMission's properties 116 Page 6 of 388 www.agi.com 3D Graphics Data Display 117 3D Graphics Window Size 118 Setting Animation Time 118 Movie Timeline Plugin 119 Movie Wizard 119 Filename & Format 119 Window 120 Resolution 120 Camera 121 Time & Length 121 Size & Quality 122 Record 122 Resetting the Scenario Animation Time 123 Creating Reports with Your Video 123 Save as Quick Reports 124 Visual Data File (VDF) 124 Windows File Explorer 125 Creating a VDF 125 STK Viewer 126 Open the VDF 126 Summary 127 On Your Own 127 Lesson Five: Introduction to Connect 128 Problem Statement 128 Solution 128 Page 7 of 388 www.agi.com What You Will Learn 128 Video Guidance 129 Create a New Scenario 129 Prepare STK 129 The HTML Viewer 129 API Demo Utility 130 New Command 130 Connect Command Library 132 Alphabetical Listing 132 SetPosition Command 133 Move the Facility () Object and Attach a Sensor () Object 133 Add a Satellite () Object 134 Propagate the Satellite (Satellite) Object 134 Insert an Aircraft () Object 135 Modify the Aircraft () Object 136 Compute an Access 136 Add Vectors 137 Summary 138 Become Level 1: STK Certified 139 What's in the Test? 139 STK Level 2 - Advanced 141 Evaluation License 141 Optional Third-Party Programs 141 Part 2: Introduction to STK Pro 144 Problem Statement 144 Page 8 of 388 www.agi.com Solution 144 Create a New Scenario 145 U.S. Geological Survey Data 146 Analytical Terrain 146 Terrain Regions Display 147 Color Elevation Imagery 148 2D Graphics Imagery 150 Imagery and Terrain Converter 151 Imagery 151 Terrain 152 Globe Manager 152 Insert the GPS Tracking Device 154 Define an Azimuth-Elevation Mask 154 Display the Azimuth-Elevation Mask 155 Constellation Objects 156 Chain Objects 157 Complete Chain Access 158 Individual Strand Access 159 Save Your Work 160 On Your Own 160 Part 3: Create an AzEl Mask from a 3D Model 161 AzEl Mask Tool 161 Part 4: Customize Analysis with Analysis Workbench 169 Problem Statement 169 Solution 169 Page 9 of 388 www.agi.com What You Will Learn 169 Create a New Scenario 170 Disable Terrain Server 171 Satellite Tracking Station 171 Recently Launched Satellite 172 Calculate Access 172 Vector Geometry Tool 173 Open Tracking Station's Properties 173 Display Sun Vector 173 Show Sun Vector 174 Show To Vector 174 Show Magnitude 175 View To Vector 175 Create a Custom Angle 176 Open Analysis Workbench Tools 176 Create a Between Vectors Angle 176 Select the From Vector 177 Select the To Vector 177 Display the Custom Angle 178 View Tracking Angle 178 Calculation Tool 179 Scalar 179 Create a Scalar 180 Define Scalar Calculation 180 Condition 181 Page 10 of 388 www.agi.com Create a Condition 181 Define Calculation Condition Type 181 Define the Scalar 181 Define the Calculation Conditions 182 Create a Report 182 View Accesses and Satisfaction Intervals in the Timeline View 183 Time Tool 183 Create an Interval List 184 Define the Interval List Type 184 Define the Operation 184 Remove Time Components 185 Define the Time Components 185 View Intervals in the Timeline View 186 Tracking Station Sensor 186 Insert a Sensor on Tracking Station 186 Model Limited Field-of-View 187 Target the Sensor 187 Calculate Access 188 Add Temporal Constraints 188 Create a New Access Report 189 Solar Exclusion Angle 190 Save Your Work 190 Summary 190 On Your Own 191 Part 5: Compute Coverage Over Regions 192 Page 11 of 388 www.agi.com STK Coverage 192 Coverage Quality 195 Part 6: Build a Volumetric Object 201 Volumetrics 201 Part 7: Perform Trade Studies with Analyzer 210 Problem 210 Solution 210 What You Will Learn 211 Create a New Scenario 211 View Both the 2D and 3D Graphics Windows 212 Turn Off Terrain Server 212 Design a Satellite Orbit 212 Sensor Object 213 Coverage Definition Object 214 Coverage Grid 214 Coverage Assets 214 Figures of Merit 215 Compute Accesses Tool 215 Percent Satisfied 216 STK Analyzer 217 Determine the Impact of Satellite Inclination on Percent Satisfied 217 Analyzer Layout 218 Input Inclination 218 Output Percent Satisfied 218 Parametric Study Tool 219 Page 12 of 388 www.agi.com Inclination Parametric Study 219 Data Explorer 220 Input Eccentricity 221 Eccentricity Parametric Study 222 Data Explorer 222 Carpet Plot Tool 224 Carpet Plot 224 The Best Combination 225 Save Your Work 226 Summary 226 On Your Own 227 Part 7: Introduction to STK Communications 228 Problem Statement 228 Solution 228 What You Will Learn 229 Create a New Scenario 229 Add Analytical and Visual Terrain 230 Declutter the Labels 231 Insert the Earth Observation Satellite 231 Insert the Scientists' Camp Site 232 Simple Transmitter Model 232 Transmitter Model Specs 233 Receiver Antenna Orientation 234 Half Power Sensor Patterns 234 Targeted Sensor 235 Page 13 of 388 www.agi.com Target Times 235 Complex Receiver Model 236 Receiver Model Specs 237 Receiver Antenna 237 Receiver Antenna Polarization 238 Simple Link Budget 238 Take Terrain Into Consideration 239 Detailed Link Budget 239 Rain Model 240 Atmospheric Absorption Model 241 System Noise Temperature 241 Summary 242 Save Your Work 243 On Your Own 243 Modulator 243 Additional Gains and Losses 244 Part 8: Introduction to STK Radar 245 Problem Statement 245 Solution 245 What You Will Learn 246 Create a New Scenario 246 Turn Off Terrain Server 247 Turn On Label Declutter 247 Insert the Target Aircraft 248 Create the Target Aircraft's Route 248 Page 14 of 388 www.agi.com Specify the Radar Cross Section 249 Display Radar Cross Section Graphics 249 Insert the Radar Site 250 Define the Radar Site's Location 251 Insert the Antenna Servo System 252 Define the Sensor Field of View 253 Target the Aircraft 253 Set Range and Elevation Angle Constraints 254 Determine Access 254 Generate an Azimuth Elevation Range Report 255 Look at the Sensor's Field of View 256 Insert an Airport Surveillance Radar 257 Model a Monostatic Radar 257 Define the Waveform 258 Define the Pulse Width 258 Define the Antenna Pattern 258 Define the Radar Transmitter 259 Set the Radar Receiver's Polarization 260 Add the Radar Receiver's System Noise Temperature 260 Probability of Detection 261 Compute Access 261 Generate a Radar SearchTrack Report 261 Understanding the Data 262 Observe Pdet 262 Observe SNR 263 Page 15 of 388 www.agi.com Observe S/T Ambig Tgt Range 263 Medium Sized Aircraft 263 Small Sized Aircraft 264 Birds and Stealth 265 Aspect Dependent RCS Files
Recommended publications
  • Orbit Determination
    Transiting Exoplanet Survey Satellite Transiting Exoplanet Survey Satellite (TESS) Flight Dynamics Commissioning Results and Experiences ( . - -~ . ' : .•. ' Joel J. K. Parker NASA Goddard Space Flight Center ', ~Qi Ryan L. Lebois L3 Applied Defense Solutions .•.-· e, • i Stephen Lutz L3 Applied Defense Solutions ,/,#· Craig Nickel L3 Applied Defense Solutions Kevin Ferrant Omitron, Inc. Adam Michaels Omitron, Inc. August 22, 2018 Contents Mission Overview Flight Dynamics Ground System TESS Commissioning . Launch . Phasing Loops & Maneuver Execution . PAM & Extended Mission Design . Commissioning Results Orbit Determination Conclusions 2 Mission Overview—Science Goals Primary Goal: Discover Transiting Earths and Super-Earths Orbiting Bright, Nearby Stars . Rocky planets & water worlds . Habitable planets Discover the “Best” ~1000 Small Exoplanets . “Best” means “readily characterizable” • Bright Host Stars • Measurable Mass & Atmospheric Properties Unique lunar-resonant mission orbit provides long view periods without station-keeping 27 days 54 days Large-Area Survey of Bright Stars . F, G, K dwarfs: +4 to +12 magnitude . M dwarfs known within ~60 parsecs . “All sky” observations in 2 years . All stars observed >20 days . Ecliptic poles observed ~1 year (JWST Continuous Viewing Zone) 3 s Mission Overview—Spacecraft LENS HOOD THERMAL . LENSES BLANKETS SUN SHADE REACTION WHEELS DETECTORS ELECTRONICS SOLAR ARRAYS MASTER ANTENNA COMPUTER PROPULSION TANK STRUCTURE Northrop Grumman LEOStar-2/750 bus Attitude Control: Propulsion:
    [Show full text]
  • Sg423finalreport.Pdf
    Notice: The cosmic study or position paper that is the subject of this report was approved by the Board of Trustees of the International Academy of Astronautics (IAA). Any opinions, findings, conclusions, or recommendations expressed in this report are those of the authors and do not necessarily reflect the views of the sponsoring or funding organizations. For more information about the International Academy of Astronautics, visit the IAA home page at www.iaaweb.org. Copyright 2019 by the International Academy of Astronautics. All rights reserved. The International Academy of Astronautics (IAA), an independent nongovernmental organization recognized by the United Nations, was founded in 1960. The purposes of the IAA are to foster the development of astronautics for peaceful purposes, to recognize individuals who have distinguished themselves in areas related to astronautics, and to provide a program through which the membership can contribute to international endeavours and cooperation in the advancement of aerospace activities. © International Academy of Astronautics (IAA) May 2019. This publication is protected by copyright. The information it contains cannot be reproduced without written authorization. Title: A Handbook for Post-Mission Disposal of Satellites Less Than 100 kg Editors: Darren McKnight and Rei Kawashima International Academy of Astronautics 6 rue Galilée, Po Box 1268-16, 75766 Paris Cedex 16, France www.iaaweb.org ISBN/EAN IAA : 978-2-917761-68-7 Cover Illustration: credit A Handbook for Post-Mission Disposal of Satellites
    [Show full text]
  • The Virginia Space Thinsat Program: Maiden Voyage and Future Progressions
    SSC18-WKVIII-01 The Virginia Space ThinSat Program: Maiden Voyage and Future Progressions Dale Nash, Sean Mulligan, Regan Smith, Susannah Miller Virginia Commercial Space Flight Authority 4111 Monarch Way #303, Norfolk, VA 23508; 757-440-4020 [email protected] Robert Twiggs, Matt Craft, Jose Garcia Twiggs Space Lab, LLC 2340 Old Hickory Lane, Suite 100, Lexington, KY 40515; 859-312-6686 [email protected] Brenda Dingwall NASA GSFC Wallops Flight Facility Wallops Island, VA; 757-824-2969 [email protected] ABSTRACT Science, technology, engineering, and mathematics (STEM) focus is rapidly being integrated into the modern-day classroom. This focus is essential for developing both the technical minds and creativity of the next generation. The education industry cannot push STEM activities to the next level without the help of outside partners who have industry insight and experience. This is why Virginia Commercial Space Flight Authority (Virginia Space), Twiggs Space Laboratory, LLC (TSL), Northrop Grumman (NG), NASA Wallops Flight Facility (WFF), and Near Space Launch Corp (NSL) have all partnered together to develop the Virginia Space ThinSat Program. With our primary focus being on STEM outreach, the program has developed a new way to bridge the gap between satellite development and the education industry. By utilizing this platform, we have already seen development of beneficial research potential from numerous institutions that shows the promise of a bright future for the Virginia Space ThinSat Program and Extreme Low Earth Orbit (ELEO) research. PROGRAM OVERVIEW National Aeronautics and Space Administration STEM advancement is on the forefront of (NASA). The ThinSat Program was developed with the most technical educator’s minds as the next generation vision to allow students to design and build their own of students are being molded to become the future payloads in order to be challenged with an engineering technical minds of the world.
    [Show full text]
  • Trajectory Optimization for Spacecraft Collision Avoidance
    Air Force Institute of Technology AFIT Scholar Theses and Dissertations Student Graduate Works 9-1-2013 Trajectory Optimization for Spacecraft olC lision Avoidance James W. Sales Follow this and additional works at: https://scholar.afit.edu/etd Part of the Aerospace Engineering Commons Recommended Citation Sales, James W., "Trajectory Optimization for Spacecraft oC llision Avoidance" (2013). Theses and Dissertations. 842. https://scholar.afit.edu/etd/842 This Thesis is brought to you for free and open access by the Student Graduate Works at AFIT Scholar. It has been accepted for inclusion in Theses and Dissertations by an authorized administrator of AFIT Scholar. For more information, please contact [email protected]. TRAJECTORY OPTIMIZATION FOR SPACECRAFT COLLISION AVOIDANCE THESIS James W Sales, Jr. Lieutenant, USN AFIT-ENY-13-S-01 DEPARTMENT OF THE AIR FORCE AIR UNIVERSITY AIR FORCE INSTITUTE OF TECHNOLOGY Wright-Patterson Air Force Base, Ohio DISTRIBUTION STATEMENT A: APPROVED FOR PUBLIC RELEASE; DISTRIBUTION UNLIMITED The views expressed in this thesis are those of the author and do not reflect the official policy or position of the United States Navy, United States Air Force, Department of Defense, or the United States Government. This material is declared a work of the U.S. Government and is not subject to copyright protection in the United States. AFIT-ENY-13-S-01 TRAJECTORY OPTIMIZATION FOR SPACECRAFT COLLISION AVOIDANCE THESIS Presented to the Faculty Department of Aeronautics and Astronautics Graduate School of Engineering and Management Air Force Institute of Technology Air University Air Education and Training Command In Partial Fulfillment of the Requirements for the Degree of Master of Science in Astronautical Engineering James W Sales, Jr., B.S.
    [Show full text]
  • Modeling & Simulation of Cubesat Mission
    Photo Credit: Derek Dalle Modeling & Simulation of CubeSat Mission Model-Based Systems Engineering (MBSE) Behavioral Modeling and Execution Integration of MagicDraw, Cameo Simulation Toolkit, STK, and Matlab using ModelCenter Sara Spangelo1 Jet Propulsion Laboratory (JPL), California Institute of Technology Hongman Kim2 Grant Soremekun3 Phoenix Integration, Inc. May 29/30, 2013 1 [email protected], 2 [email protected], [email protected] System Engineering Challenges Conventional approaches: • Focus on subset of subsystems Motivation – Over-simplified, low fidelity Overview – Neglect subsystem interactions Modeling • Requirements verification using average/best/worst-cases Simulating – Fail to capture realistic “dynamic” nature of missions Design Trades • Models and simulations are not integrated! Reflections – “Hacked” together for one-off cases Future Work – Not modular, extensible, reusable Why? Lack of integrated modeling/simulation tools to enable system-level engineering design/analysis. 2 1Type of miniature spacecraft (1U = 10cm3, <1 kg) Image Credit: www.cubesatkit.com System Engineering Challenges Particularly an issue for CubeSats1 because: • Physical components physically integrated Motivation • Extremely constrained: Overview – Limited ability to collect and store energy (e.g. batteries) Modeling • Operational constraints/ decisions coupled Simulating – When to collect data versus download data? Design Trades • Obits are unknown/ dynamic Reflections – Little/ no control over launch orbit Future Work – Experience variation in eclipse duration, may de-orbit • Operate in inefficient/ stochastic environments Integrated models and tools are critical to design and plan for these missions! 1 3 Type of miniature spacecraft (1U = 10cm , <1 kg) 3 Image Credit: www.cubesatkit.com Model-Based Systems Engineering (MBSE1) Why MBSE? 1) Enables system-level model capture Motivation • Formal, accurate, authoritative single source Overview • Contains elements, relationships, interactions Modeling • Multiple compatible views, e.g.
    [Show full text]
  • Modelling a C-Band Space Surveillance Radar Using Systems Tool Kit
    UNCLASSIFIED Modelling a C-Band Space Surveillance Radar using Systems Tool Kit Mark Graham and Stephen Bocquet Joint Operations Division Defence Science and Technology Organisation DSTO-TN-1164 ABSTRACT A model of the AN/FPQ-14 C-Band radar was developed using Analytical Graphics, Inc. (AGI) STK software to support studies investigating the operational performance of the system for surveillance of Space and the contribution it could make to the Space situational awareness mission. STK scenarios were developed to assess the detection performance of the radar model against a satellite target with a given orbital altitude, radar cross section (RCS) and minimum signal to noise ratio (SNR) required for detection. These results were compared to those obtained by evaluating the radar range equation. A comparison was also made on the effects of refraction using the effective radius method and International Telecommincations Union (ITU) model. RELEASE LIMITATION Approved for public release UNCLASSIFIED UNCLASSIFIED Published by Joint Operations Division DSTO Defence Science and Technology Organisation 506 Lorimer St Fishermans Bend, Victoria 3207 Australia Telephone: 1300 DEFENCE Fax: (03) 9626 7999 © Commonwealth of Australia 2013 AR-015-569 February 2013 APPROVED FOR PUBLIC RELEASE UNCLASSIFIED UNCLASSIFIED Modelling a C-Band Space Surveillance Radar using Systems Tool Kit Executive Summary The US Space Surveillance Network (SSN) is a collection of sensors dispersed around the world for surveillance of Space. These sensors are used to detect, track, identify and characterise objects in Space such as payloads, rocket bodies and debris to provide Space situational awareness information. The AN/FPQ-14 is a conventional (dish) radar used for surveillance of Space.
    [Show full text]
  • AGI Software and Solutions for Test and Evaluation (T&E)
    AGI Software and Solutions for Test and Evaluation (T&E) Agenda . Introductions – Company Overview – Current Industry Test & Evaluation Challenges . AGI Software Support of T&E Workflow – Typcal Test & Evaluation Processes – Software Simulation/Coordination Efforts . Pre-Mission Planning Design – Using Commercial Software for Planning/Analysis/Simulation – Test Event Rehearsal & Replanning . Testing Operations – Real-Time Visualization & Support – Data Analysis & Situational Awareness . Post Flight Analysis – Flight Reconstruction – Analyze Test Data – Refine Procedures & Testing Processes . Q&A Wrap Up AGI Asia Introductions . Matt Halferty – Director, Asia Pacific – US Army Officer - West Point . Jim Head – Partner Manager, Asia Pacific – Masters Degree Strategic Studies – RSIS Singapore . Nate McBee – Systems Engineer Manager, International – Masters Aerospace Engineering - Univ. of Tennessee . Dan Honaker – Aerospace Systems Engineer, Asia Pacific – Masters Aerospace Engineering - Univ. of Colorado . Melissa Honaker – Aerospace Systems Engineer, Asia Pacific – Bachelors Aerospace Engineering - Univ. of Colorado . Alex Ridgeway – Aerospace Systems Engineer, Asia Pacific – Bachelors Aerospace Engineering – Pennsylvania State Univ. AGI Global Overview . Analytical Graphics, Inc. (USA): A Global Aerospace Standard – 45,000+ global software installs – 700+ user organizations worldwide . Provider of COTS software since 1989 – Space mission design & engineering – Satellite operations – Space situational awareness . Validated astrodynamics,
    [Show full text]
  • Electromagnetic Interference Estimation Via Conditional Neural Processing
    Air Force Institute of Technology AFIT Scholar Theses and Dissertations Student Graduate Works 12-2020 Electromagnetic Interference Estimation via Conditional Neural Processing Edgar E. Gomez Follow this and additional works at: https://scholar.afit.edu/etd Part of the Electromagnetics and Photonics Commons Recommended Citation Gomez, Edgar E., "Electromagnetic Interference Estimation via Conditional Neural Processing" (2020). Theses and Dissertations. 4537. https://scholar.afit.edu/etd/4537 This Thesis is brought to you for free and open access by the Student Graduate Works at AFIT Scholar. It has been accepted for inclusion in Theses and Dissertations by an authorized administrator of AFIT Scholar. For more information, please contact [email protected]. Electromagnetic Interference Estimation via Conditional Neural Processing THESIS Edgar E. Gomez AFIT-ENG-MS-20-D-006 DEPARTMENT OF THE AIR FORCE AIR UNIVERSITY AIR FORCE INSTITUTE OF TECHNOLOGY Wright-Patterson Air Force Base, Ohio DISTRIBUTION STATEMENT A APPROVED FOR PUBLIC RELEASE; DISTRIBUTION UNLIMITED. The views expressed in this document are those of the author and do not reflect the official policy or position of the United States Air Force, the United States Department of Defense or the United States Government. This material is declared a work of the U.S. Government and is not subject to copyright protection in the United States. AFIT-ENG-MS-20-D-006 Electromagnetic Interference Estimation via Conditional Neural Processing THESIS Presented to the Faculty Department of Electrical and Computer Engineering Graduate School of Engineering and Management Air Force Institute of Technology Air University Air Education and Training Command in Partial Fulfillment of the Requirements for the Degree of Master of Science in Electrical Engineering Edgar E.
    [Show full text]
  • Design Considerations for a Software Space Elevator Simulator
    International Space Elevator Consortium ISEC Position Paper # 2017-1 Design Considerations for a Software Space Elevator Simulator Tether constants mass length climber mass density gravity Field constants axis angle rota4on rate strength solar pressure 4me plot Dennis H. Wright Steven Avery John Knapman Martin Lades Paul Roubekas Peter A. Swan Design Considerations for a Software Space Elevator Simulator International Space Elevator Consortium Autumn 2017 Authors: Dennis H. Wright Steven Avery John Knapman Martin Lades Paul Roubekas Peter A. Swan International Space Elevator Consortium ISEC Position Paper 2017-1 Design Considerations for a Software Space Elevator Simulator Copyright © 2018 by: Dennis H. Wright Steven Avery John Knapman Martin Lades Paul Roubekas Peter A. Swan All rights reserved, including the rights to reproduce this manuscript or portions thereof in any form. Published by Lulu.com [email protected] 978-1-387-65437-6 Printed in the United States of America ii International Space Elevator Consortium ISEC Position Paper 2017-1 Preface The vision of the International Space Elevator Consortium (ISEC) is to have “a world with inexpensive, safe, routine, and efficient access to space for the benefit of all mankind.” As a necessary step towards achieving this vision ISEC has undertaken a series of year-long studies, each of which focuses on a particular aspect of the design and construction of an operational Earth-based space elevator. The 2017 study deals with the requirements and preliminary design aspects of a software simulator of a space elevator system. The goals of the study are to identify the most important functions of such a simulator, derive from these the requirements of the software to be developed and outline its major design characteristics.
    [Show full text]
  • Visual Interactive Trajectory Design
    AAS 19-449 VISUAL INTERACTIVE TRAJECTORY DESIGN Ravishankar Mathur* A method of altering trajectories via visual “grab-and-drag” gestures with imme- diate graphical response, called Visual Interactive Trajectory Design (VITD), is presented. The various components of VITD are defined (e.g. draggable objects), and how they affect the trajectory is discussed. An implementation of VITD is demonstrated that uses the General Mission Analysis Tool (GMAT) to propagate trajectories, and visualizes them in realtime using the OpenFrames 3D visualiza- tion API. Examples of using VITD are shown, including finding a lunar free-re- turn trajectory by visually rotating the trajectory’s initial velocity vector. The ben- efits of VITD are explored, including for teaching, exploring the design space, and generating initial-guess trajectories for optimization. INTRODUCTION As a result of advances in astrodynamics applications over the past two decades, high-fidelity visualizations are no longer considered a novelty or optional component of mission design and analysis. Widely-used commercial and government-developed tools such as Systems Tool Kit (STK)1, Copernicus2, and the General Mission Analysis Tool (GMAT)3 all contain 3D visualiza- tions that provide critical information far above and beyond what text-based data or static plots can achieve. These visualizations have become an essential part of effective trajectory design and op- timization, so much so that they are used to affect design decisions and not merely for the sake of output pictures and presentations. For example, design for the NASA OSIRIS-REx mission’s Touch-and-Go (TAG) trajectory was performed in part with STK4, and 3D visualizations played an important role in validation of that trajectory.
    [Show full text]
  • Simulation and Control Toolkit for Small Satellite Projects (Programovy Balik Pro Simulaci a Navrh Rizeni Malych Satelitu) Author: B.Sc
    CZECH TECHNICAL UNIVERSITY IN PRAGUE FACULTY OF ELECTRICAL ENGINEERING DEPARTMENT OF CONTROL ENGINEERING Master's Thesis Simulation and control toolkit for small satellite projects (Programovy balik pro simulaci a navrh rizeni malych satelitu) Author: B.Sc. Adam Smia´ lek Supervisor: doc. Ing. Martin Hromˇc´ık,Ph.D. Study Program: Cybernetics and Robotics Specialization: Cybernetics and Robotics 14th of August 2020 MASTER‘S THESIS ASSIGNMENT I. Personal and study details Student's name: Śmiałek Adam Personal ID number: 492264 Faculty / Institute: Faculty of Electrical Engineering Department / Institute: Department of Control Engineering Study program: Cybernetics and Robotics Branch of study: Cybernetics and Robotics II. Master’s thesis details Master’s thesis title in English: Simulation and control toolkit for small satellite projects Master’s thesis title in Czech: Programovy balik pro simulaci a navrh rizeni malych satelitu Guidelines: The goal of the project is to propose, implement and demonstrate value of a software framework supporting teams building small satellites - typically CubeSat student projects - during the initial phases of conceptual design, mission planning, and selection and sizing of components. In relation to requirements coming from the expected navigation and flight control functionalities. 1. Make a review of existing related tools. Both from the large satellite business, and the small satellite community. Present a comparative analysis of strengths and weaknesses of existing solutions. 2. Based on the review, prepare a study and the software concept proposal showing specifically the need for this work and expected compatibility of the toolkit with relevant other packages. 3. Propose and implement essential data structures and procedures of the toolkit.
    [Show full text]
  • Blockchain Application Within a Multi-Sensor Satellite Architecture
    Blockchain application within a multi-sensor satellite architecture Rohit Mital SGT KBRwyle Jack de La Beaujardiere U. of Maryland, College Park Rohan Mital U. of Colorado, Colorado Springs Marge Cole NASA ESTO and SGT KBRwyle Dr. Charles Norton NASA Headquarters ABSTRACT With the thrust towards multi-sensor satellite architectures for earth and space exploration, such as constellations and swarms, new technologies are required to enable the transition to this future capability. One of the areas of interest is establishing secure, efficient and prioritized data and command communication pathways among ground and space-based sources for such systems. This paper presents early research results on the potential role, capabilities and value of blockchain usage within constellation and swarm satellite architectures. It demonstrates the use of blockchain’s smart contract and distributed ledger capabilities for secure and prioritized multi-sensor satellite collaborative data exchanges, as well as the logging and tracking of command and control events. Adapting and utilizing this emerging technology will aid in addressing technology gaps expected from future constellation flight architectures, such as managing collective computational operations (correlation), dynamic and autonomous observation planning, time-critical events, and provenance tied to ground and space-based autonomous operations and control recordkeeping. In this scenario blockchain is applied in encrypted command transmittal to multiple, yet specific, entities enabling acknowledgement transmittals, performance scalability, and automatic event-based triggering. INTRODUCTION The blockchain testbed project was started with the intent to research and experiment with blockchain technology and to assess whether this technology could be leveraged as an approach for some general use cases: secure and prioritized multi-sensor satellite collaborative data exchanges and the logging and tracking of command and control events.
    [Show full text]