Draft Environmental Assessment for Issuing an Experimental Permit to Spacex for Operation of the Grasshopper Vehicle at the Mcgregor Test Site, Texas September 2011

Total Page:16

File Type:pdf, Size:1020Kb

Draft Environmental Assessment for Issuing an Experimental Permit to Spacex for Operation of the Grasshopper Vehicle at the Mcgregor Test Site, Texas September 2011 Federal Aviation Administration Draft Environmental Assessment for Issuing an Experimental Permit to SpaceX for Operation of the Grasshopper Vehicle at the McGregor Test Site, Texas September 2011 HQ-111451 Draft EA for Issuing an Experimental Permit to SpaceX for Operation of the Grasshopper Vehicle at the McGregor Test Site, Texas TABLE OF CONTENTS Section Page ACRONYMS AND ABBREVIATIONS ...................................................................................... iv 1. INTRODUCTION ....................................................................................................................1 1.1 Background .....................................................................................................................1 1.2 Purpose and Need for Agency Action .............................................................................2 1.3 Request for Comments on the Draft EA .........................................................................2 2. DESCRIPTION OF THE PROPOSED ACTION AND NO ACTION ALTERNATIVE ......3 2.1 Proposed Action ..............................................................................................................3 2.1.1 Grasshopper RLV ..............................................................................................5 2.1.1.1 Description ......................................................................................... 5 2.1.1.2 Pre-flight and Post-flight Activities ................................................... 5 2.1.1.3 Flight Profile (Takeoff, Flight, and Landing) .................................... 6 2.1.2 Grasshopper Launch Pad and Infrastructure ......................................................6 2.2 No Action Alternative .....................................................................................................7 2.3 Alternatives Considered but Dismissed ..........................................................................7 2.4 Impacts and Resources Not Analyzed in Detail ..............................................................8 3. AFFECTED ENVIRONMENT................................................................................................9 3.1 Air Quality .....................................................................................................................10 3.2 Noise and Compatible Land Use ...................................................................................12 3.3 Land Use (Including U.S. Department of Transportation Section 4(f) Properties) ......16 3.4 Biological Resources (Fish, Wildlife, and Plants) ........................................................18 3.4.1 Vegetation ........................................................................................................18 3.4.2 Wildlife ............................................................................................................18 3.4.3 Special Status Species ......................................................................................19 3.5 Historical, Architectural, Archaeological, and Cultural Resources ..............................21 3.6 Hazardous Materials, Pollution Prevention, and Solid Waste .......................................22 3.7 Light Emissions and Visual Resources .........................................................................23 3.8 Natural Resources and Energy Supply ..........................................................................24 3.9 Water Resources (Surface Waters and Wetlands, Groundwater, Floodplains, and Water Quality) ...............................................................................................................24 3.9.1 Surface Waters and Wetlands, and Water Quality ...........................................25 3.9.2 Floodplains .......................................................................................................26 3.9.3 Groundwater ....................................................................................................26 3.10 Socioeconomics, Environmental Justice, and Children’s Environmental Health and Safety ......................................................................................................................27 3.10.1 Demographics and Housing .............................................................................27 3.10.2 Economy and Employment ..............................................................................28 3.10.3 Environmental Justice ......................................................................................28 3.10.4 Children’s Environmental Health and Safety ..................................................30 4. ENVIRONMENTAL CONSEQUENCES .............................................................................32 4.1 Proposed Action ............................................................................................................32 4.1.1 Air Quality .......................................................................................................32 September 2011 i Draft EA for Issuing an Experimental Permit to SpaceX for Operation of the Grasshopper Vehicle at the McGregor Test Site, Texas 4.1.1.1 Impacts from Construction .............................................................. 32 4.1.1.2 Impacts from Operations .................................................................. 32 4.1.1.3 Impacts from Launch Failures ......................................................... 35 4.1.2 Noise and Compatible Land Use .....................................................................35 4.1.2.1 Construction Noise........................................................................... 35 4.1.2.2 Engine Noise .................................................................................... 36 4.1.2.3 Human Exposure to Launch Noise .................................................. 36 4.1.2.4 Compatible Land Use ...................................................................... 37 4.1.3 Land Use (Including U.S. Department of Transportation Section 4(f) Properties) ........................................................................................................37 4.1.4 Biological Resources (Fish, Wildlife, and Plants) ...........................................38 4.1.4.1 Vegetation ........................................................................................ 38 4.1.4.2 Wildlife ............................................................................................ 38 4.1.4.3 Special Status Species ...................................................................... 39 4.1.5 Historical, Architectural, Archaeological, and Cultural Resources .................39 4.1.6 Hazardous Materials, Pollution Prevention, and Solid Waste .........................40 4.1.7 Light Emissions and Visual Resources ............................................................40 4.1.8 Natural Resources and Energy Supply ............................................................41 4.1.9 Water Resources (Surface Waters and Wetlands, Groundwater, Floodplains, and Water Quality) ......................................................................41 4.1.9.1 Surface Waters and Wetlands, and Water Quality ........................... 41 4.1.9.2 Floodplains ....................................................................................... 42 4.1.9.3 Groundwater .................................................................................... 42 4.1.10 Socioeconomics, Environmental Justice, and Children’s Environmental Health and Safety .............................................................................................42 4.1.10.1 Impacts to Demographics and Housing ........................................... 42 4.1.10.2 Impacts to Economy and Employment ............................................ 43 4.1.10.3 Impacts to Environmental Justice Populations ................................ 43 4.1.10.4 Impacts to Children’s Environmental Health and Safety ................ 43 4.1.11 Secondary (Induced) Impacts ..........................................................................43 4.2 No Action Alternative ...................................................................................................44 5. CUMULATIVE IMPACTS ...................................................................................................45 6. REFERENCES .......................................................................................................................47 7. LIST OF PREPARERS ..........................................................................................................51 7.1 Government Preparers ...................................................................................................51 7.2 Contractor Preparers ......................................................................................................51 8. DISTRIBUTION LIST ...........................................................................................................53 ii September 2011 Draft EA for Issuing an Experimental Permit to SpaceX for Operation of the Grasshopper Vehicle at the McGregor Test Site, Texas LIST OF EXHIBITS Exhibit Page 2-1 McGregor, Texas ................................................................................................................ 3 2-2 McGregor Test Site ............................................................................................................. 4 3-1 Operating Area ...................................................................................................................
Recommended publications
  • Open-Loop Flight Testing of COBALT GN&C Technologies for Precise Soft Landing
    Open-Loop Flight Testing of COBALT GN&C Technologies for Precise Soft Landing John M. Carson III1,3,∗, Farzin Amzajerdian2,y, Carl R. Seubert3,z, Carolina I. Restrepo1,x 1NASA Johnson Space Center (JSC), 2NASA Langley Research Center (LaRC), 3Jet Propulsion Laboratory (JPL), California Institute of Technology, A terrestrial, open-loop (OL) flight test campaign of the NASA COBALT (CoOper- ative Blending of Autonomous Landing Technologies) platform was conducted onboard the Masten Xodiac suborbital rocket testbed, with support through the NASA Advanced Exploration Systems (AES), Game Changing Development (GCD), and Flight Opportuni- ties (FO) Programs. The COBALT platform integrates NASA Guidance, Navigation and Control (GN&C) sensing technologies for autonomous, precise soft landing, including the Navigation Doppler Lidar (NDL) velocity and range sensor and the Lander Vision System (LVS) Terrain Relative Navigation (TRN) system. A specialized navigation filter running onboard COBALT fuzes the NDL and LVS data in real time to produce a precise navi- gation solution that is independent of the Global Positioning System (GPS) and suitable for future, autonomous planetary landing systems. The OL campaign tested COBALT as a passive payload, with COBALT data collection and filter execution, but with the Xo- diac vehicle Guidance and Control (G&C) loops closed on a Masten GPS-based navigation solution. The OL test was performed as a risk reduction activity in preparation for an upcoming 2017 closed-loop (CL) flight campaign in which Xodiac G&C will act on the COBALT navigation solution and the GPS-based navigation will serve only as a backup monitor. I. Introduction Introduction will discuss the NASA need for Precision Landing and Hazard Avoidance (PL&HA) tech- nologies for future, prioritized solar-system destinations (robotic and human missions), as well as provide an overview for the COBALT project and how it fits within the NASA PL&HA technology development roadmap.
    [Show full text]
  • China's Aircraft Carrier Ambitions
    CHINA’S AIRCRAFT CARRIER AMBITIONS An Update Nan Li and Christopher Weuve his article will address two major analytical questions. First, what are the T necessary and suffi cient conditions for China to acquire aircraft carriers? Second, what are the major implications if China does acquire aircraft carriers? Existing analyses on China’s aircraft carrier ambitions are quite insightful but also somewhat inadequate and must therefore be updated. Some, for instance, argue that with the advent of the Taiwan issue as China’s top threat priority by late 1996 and the retirement of Liu Huaqing as vice chair of China’s Central Military Commission (CMC) in 1997, aircraft carriers are no longer considered vital.1 In that view, China does not require aircraft carriers to capture sea and air superiority in a war over Taiwan, and China’s most powerful carrier proponent (Liu) can no longer infl uence relevant decision making. Other scholars suggest that China may well acquire small-deck aviation platforms, such as helicopter carriers, to fulfi ll secondary security missions. These missions include naval di- plomacy, humanitarian assistance, disaster relief, and antisubmarine warfare.2 The present authors conclude, however, that China’s aircraft carrier ambitions may be larger than the current literature has predicted. Moreover, the major implications of China’s acquiring aircraft carriers may need to be explored more carefully in order to inform appropriate reactions on the part of the United States and other Asia-Pacifi c naval powers. This article updates major changes in the four major conditions that are necessary and would be largely suffi cient for China to acquire aircraft carriers: leadership endorsement, fi nancial affordability, a relatively concise naval strat- egy that defi nes the missions of carrier operations, and availability of requisite 14 NAVAL WAR COLLEGE REVIEW technologies.
    [Show full text]
  • The SKYLON Spaceplane
    The SKYLON Spaceplane Borg K.⇤ and Matula E.⇤ University of Colorado, Boulder, CO, 80309, USA This report outlines the major technical aspects of the SKYLON spaceplane as a final project for the ASEN 5053 class. The SKYLON spaceplane is designed as a single stage to orbit vehicle capable of lifting 15 mT to LEO from a 5.5 km runway and returning to land at the same location. It is powered by a unique engine design that combines an air- breathing and rocket mode into a single engine. This is achieved through the use of a novel lightweight heat exchanger that has been demonstrated on a reduced scale. The program has received funding from the UK government and ESA to build a full scale prototype of the engine as it’s next step. The project is technically feasible but will need to overcome some manufacturing issues and high start-up costs. This report is not intended for publication or commercial use. Nomenclature SSTO Single Stage To Orbit REL Reaction Engines Ltd UK United Kingdom LEO Low Earth Orbit SABRE Synergetic Air-Breathing Rocket Engine SOMA SKYLON Orbital Maneuvering Assembly HOTOL Horizontal Take-O↵and Landing NASP National Aerospace Program GT OW Gross Take-O↵Weight MECO Main Engine Cut-O↵ LACE Liquid Air Cooled Engine RCS Reaction Control System MLI Multi-Layer Insulation mT Tonne I. Introduction The SKYLON spaceplane is a single stage to orbit concept vehicle being developed by Reaction Engines Ltd in the United Kingdom. It is designed to take o↵and land on a runway delivering 15 mT of payload into LEO, in the current D-1 configuration.
    [Show full text]
  • Off Airport Ops Guide
    Off Airport Ops Guide TECHNIQUES FOR OFF AIRPORT OPERATIONS weight and balance limitations for your aircraft. Always file a flight plan detailing the specific locations you intend Note: This document suggests techniques and proce- to explore. Make at least 3 recon passes at different levels dures to improve the safety of off-airport operations. before attempting a landing and don’t land unless you’re It assumes that pilots have received training on those sure you have enough room to take off. techniques and procedures and is not meant to replace instruction from a qualified and experienced flight instruc- High Level: Circle the area from different directions to de- tor. termine the best possible landing site in the vicinity. Check the wind direction and speed using pools of water, drift General Considerations: Off-airport operations can be of the plane, branches, grass, dust, etc. Observe the land- extremely rewarding; transporting people and gear to lo- ing approach and departure zone for obstructions such as cations that would be difficult or impossible to reach in trees or high terrain. any other way. Operating off-airport requires high perfor- mance from pilot and aircraft and acquiring the knowledge Intermediate: Level: Make a pass in both directions along and experience to conduct these operations safely takes either side of the runway to check for obstructions and time. Learning and practicing off-airport techniques under runway length. Check for rock size. Note the location of the supervision of an experienced flight instructor will not the touchdown area and roll-out area. Associate land- only make you safer, but also save you time and expense.
    [Show full text]
  • Planetary Basalt Construction Field Project of a Lunar Launch/Landing Pad – PISCES/NASA KSC Project Update R. P. Mueller1 and R
    47th Lunar and Planetary Science Conference (2016) 1009.pdf Planetary Basalt Construction Field Project of a Lunar Launch/Landing Pad – PISCES/NASA KSC Project Update R. P. Mueller1 and R. M. Kelso2, R. Romo2, C. Andersen2 1 National Aeronautics & Space Administration (NASA), Kennedy Space Center (KSC), Swamp Works Labora- tory, ) Mail Stop: UB-R, KSC, Florida, 32899, PH (321)867-2557; email: [email protected] 2 Pacific International Space Center for Exploration System (PISCES), 99 Aupuni St, Hilo, HI 96720, PH (808)935-8270; email: [email protected], [email protected], [email protected]. Introduction: odologies for constructing infrastructure and facilities Recently, NASA Headquarters invited PISCES to on the Moon and Mars using in situ materials such as become a strategic partner in a new project called “Ad- planetary basalt material. By using the indigenous ditive Construction with Mobile Emplacement” regolith materials on extra-terrestrial bodies, then the (ACME). The goal of this project is to investigate high mass and corresponding high cost of transporting technologies and methodologies for constructing facili- construction materials (e.g. concrete) can be avoided. ties and surface systems infrastructure on the Moon and At approximately $10,000 per kg launched to Low Mars using planetary basalt material. The first phase of Earth Orbit (LEO) this is a significant cost savings this project is to robotically-build a 20 meter (65-ft) which will make the future expansion of human civili- diameter vertical takeoff, vertical landing (VTVL) zation into space more achievable. Part of the first pad out of local basalt material on the Big Island of phase of the ACME project is to robotically-build a 20 Hawaii.
    [Show full text]
  • A Conceptual Design of a Short Takeoff and Landing Regional Jet Airliner
    A Conceptual Design of a Short Takeoff and Landing Regional Jet Airliner Andrew S. Hahn 1 NASA Langley Research Center, Hampton, VA, 23681 Most jet airliner conceptual designs adhere to conventional takeoff and landing performance. Given this predominance, takeoff and landing performance has not been critical, since it has not been an active constraint in the design. Given that the demand for air travel is projected to increase dramatically, there is interest in operational concepts, such as Metroplex operations that seek to unload the major hub airports by using underutilized surrounding regional airports, as well as using underutilized runways at the major hub airports. Both of these operations require shorter takeoff and landing performance than is currently available for airliners of approximately 100-passenger capacity. This study examines the issues of modeling performance in this now critical flight regime as well as the impact of progressively reducing takeoff and landing field length requirements on the aircraft’s characteristics. Nomenclature CTOL = conventional takeoff and landing FAA = Federal Aviation Administration FAR = Federal Aviation Regulation RJ = regional jet STOL = short takeoff and landing UCD = three-dimensional Weissinger lifting line aerodynamics program I. Introduction EMAND for air travel over the next fifty to D seventy-five years has been projected to be as high as three times that of today. Given that the major airport hubs are already congested, and that the ability to increase capacity at these airports by building more full- size runways is limited, unconventional solutions are being considered to accommodate the projected increased demand. Two possible solutions being considered are: Metroplex operations, and using existing underutilized runways at the major hub airports.
    [Show full text]
  • Reusable Rocket Upper Stage Development of a Multidisciplinary Design Optimisation Tool to Determine the Feasibility of Upper Stage Reusability L
    Reusable Rocket Upper Stage Development of a Multidisciplinary Design Optimisation Tool to Determine the Feasibility of Upper Stage Reusability L. Pepermans Technische Universiteit Delft Reusable Rocket Upper Stage Development of a Multidisciplinary Design Optimisation Tool to Determine the Feasibility of Upper Stage Reusability by L. Pepermans to obtain the degree of Master of Science at the Delft University of Technology, to be defended publicly on Wednesday October 30, 2019 at 14:30 AM. Student number: 4144538 Project duration: September 1, 2018 – October 30, 2019 Thesis committee: Ir. B.T.C Zandbergen , TU Delft, supervisor Prof. E.K.A Gill, TU Delft Dr.ir. D. Dirkx, TU Delft This thesis is confidential and cannot be made public until October 30, 2019. An electronic version of this thesis is available at http://repository.tudelft.nl/. Cover image: S-IVB upper stage of Skylab 3 mission in orbit [23] Preface Before you lies my thesis to graduate from Delft University of Technology on the feasibility and cost-effectiveness of reusable upper stages. During the accompanying literature study, it was determined that the technology readiness level is sufficiently high for upper stage reusability. However, it was unsure whether a cost-effective system could be build. I have been interested in the field of Entry, Descent, and Landing ever since I joined the Capsule Team of Delft Aerospace Rocket Engineering (DARE). During my time within the team, it split up in the Structures Team and Recovery Team. In September 2016, I became Chief Recovery for the Stratos III student-built sounding rocket. During this time, I realised that there was a lack of fundamental knowledge in aerodynamic decelerators within DARE.
    [Show full text]
  • Vertical Landing Aerodynamics of Reusable Rocket Vehicle
    Trans. JSASS Aerospace Tech. Japan Vol. 10, pp. 1-4, 2012 Research Note Vertical Landing Aerodynamics of Reusable Rocket Vehicle 1) 2) 3) 1) 1) By Satoshi NONAKA, Hiroyuki NISHIDA, Hiroyuki KATO, Hiroyuki OGAWA and Yoshifumi INATANI 1) The Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency, Sagamihara, Japan 2) Mechanical Systems Engineering, Tokyo University of Agriculture and Technology, Koganei, Japan 3) Chofu Aerospace Center, Japan Aerospace Exploration Agency, Chofu, Japan (Received November 26th, 2010) The aerodynamic characteristics of a vertical landing rocket are affected by its engine plume in the landing phase. The influences of interaction of the engine plume with the freestream around the vehicle on the aerodynamic characteristics are studied experimentally aiming to realize safe landing of the vertical landing rocket. The aerodynamic forces and surface pressure distributions are measured using a scaled model of a reusable rocket vehicle in low-speed wind tunnels. The flow field around the vehicle model is visualized using the particle image velocimetry (PIV) method. Results show that the aerodynamic characteristics, such as the drag force and pitching moment, are strongly affected by the change in the base pressure distributions and reattachment of a separation flow around the vehicle. Key Words: Counter Jet, Reusable Rocket, Landing Aerodynamics Nomenclature (VTVL) rocket vehicles are a type of reusable space transportation system. In the 1990s, the Delta Clipper 2 CD : drag coefficient, D (ρV∞ S 2) Experimental (DC-X) demonstrated both the key technical feasibility of a VTVL single stage to orbit (SSTO) vehicle 2 Cp : pressure coefficient, − ρ (Psurface P∞ ) ( V∞ S 2) and key operational concepts such as repeatability, safety, D : aerodynamic drag force [N] 1) reliability and inexpensive accessibility to space.
    [Show full text]
  • CALLISTO - Reusable VTVL Launcher First Stage Demonstrator
    View metadata, citation and similar papers at core.ac.uk brought to you by CORE provided by Institute of Transport Research:Publications SP2018_00406 CALLISTO - Reusable VTVL launcher first stage demonstrator E. Dumont (1), T. Ecker (2), C. Chavagnac (3) , L. Witte (4), J. Windelberg (5) J. Klevanski (6), S. Giagkozoglou (7) (1) DLR - Institute of Space Systems - Space Launcher Systems Analysis - Bremen (Germany), [email protected] (2)DLR - Institute of Aerodynamics and Flow Technology - Spacecraft - Göttingen (Germany) (3) CNES - Launcher directorate - Paris (France) (4) DLR - Institute of Space Systems – Landing and Exploration Systems - Bremen (Germany) (5)DLR - Institute of Flight Systems – Braunschweig (Germany) (6)DLR - Institute of Aerodynamics and Flow Technology - Supersonic and Hypersonic Technology - Cologne (Germany) (7)DLR - Institute of Structures and Design – Space System Integration - Stuttgart (Germany) KEYWORDS: CALLISTO, Reusability, RLV, VTVL, DRL Downrange Landing RTLS Demonstrator, LOx/LH2 FRR Flight Readiness Review ABSTRACT: GNSS Global Navigation Satellite System HNS Hybrid Navigation System DLR and CNES are jointly developing a demonstrator for a reusable vertical take-off vertical IMU Inertial Measurement Unit landing launcher first stage. It is called CALLISTO, MRO Maintenance, Repair and Operations which stands for “Cooperative Action Leading to PDR Preliminary Design Review Launcher Innovation in Stage Toss back Reliability, Availability, Maintainability Operations”. The CALLISTO project, benefiting from RAMS the long heritage and know-how available in Europe and Safety is pursuing two main goals. First it shall RTLS Return to Launch Site demonstrate the capabilities to perform the specific SRR System Requirement Review manoeuvres and operations needed for an VTVL Vertical Take-Off, Vertical Landing operational reusable first stage performing return to launch site.
    [Show full text]
  • COBALT: Development of a Platform to Flight Test Lander GN&C
    COBALT: Development of a Platform to Flight Test Lander GN&C Technologies on Suborbital Rockets John M. Carson III1,3,∗, Carl R. Seubert3,y, Farzin Amzajerdian2,z, Chuck Bergh3,x, Ara Kourchians3,, Carolina I. Restrepo1,O, Carlos Y. Villalpando3,{, Travis V. O'Neal4,F, Edward A. Robertson1,k, Diego F. Pierrottet5,∗∗, Glenn D. Hines2,yy, Reuben Garcia4,zz 1NASA Johnson Space Center (JSC), 2NASA Langley Research Center (LaRC), 3Jet Propulsion Laboratory (JPL), California Institute of Technology, 4Masten Space Systems (MSS), 5Coherent Applications, Inc. (CAI) The NASA COBALT Project (CoOperative Blending of Autonomous Landing Tech- nologies) is developing and integrating new precision-landing Guidance, Navigation and Control (GN&C) technologies, along with developing a terrestrial flight-test platform for Technology Readiness Level (TRL) maturation. The current technologies include a third- generation Navigation Doppler Lidar (NDL) sensor for ultra-precise velocity and line- of-site (LOS) range measurements, and the Lander Vision System (LVS) that provides passive-optical Terrain Relative Navigation (TRN) estimates of map-relative position. The COBALT platform is self contained and includes the NDL and LVS sensors, blending filter, a custom compute element, power unit, and communication system. The platform incorpo- rates a structural frame that has been designed to integrate with the payload frame onboard the new Masten Xodiac vertical take-off, vertical landing (VTVL) terrestrial rocket vehicle. Ground integration and testing is underway,
    [Show full text]
  • Safety Aspects of Tailwind Operationssafety Operations
    NationaalNa Lucht- en Ruimtevaartlaboratorium NLR-TP-2001-003 Safety aspects of tailwind operationsSafety operations G.W.H. van Es and A.K. Karwal Nationaal Lucht- en Ruimtevaartlaboratorium National Aerospace Laboratory NLR NLR-TP-2001-003 Safety aspects of tailwind operations G.W.H. van Es and A.K. Karwal This report is based on a presentation held on the Flight Safety Foundation Annual European Aviation Safety Seminar, Amsterdam, The Netherlands on 12-14 March, 2001. The contents of this report may be cited on condition that full credit is given to NLR and the authors. Division: Air Transport Issued: January 2001 Classification of title: Unclassified -3- NLR-TP-2001-003 Summary In the present study the safety aspects of aircraft takeoff and landing operations in tailwinds are explored. The study covers a description of legislative instruments that influence preferential runway selection in relation to the maximum tailwind component applied; tailwind certification issues; and relevant safety issues concerning tailwind operations in general. Also a systematic analysis of historical tailwind related overrun accidents and incidents is presented. Some of the important findings of this study are: • In many of the analysed accidents the actual tailwind exceeded the approved limit. • The tailwind component determined by the Flight Management System (FMS) appears to be relatively insensitive to common FMS errors. • Present-day wake vortex separation criteria for final approach may be insufficient in light tailwind conditions. • Operating on wet or contaminated runways in combination with a tailwind yields a high risk of an overrun. • Current certification requirements of operations in tailwinds greater than 10 Knots are limited to guidelines in the Flight Test Guide.
    [Show full text]
  • Guidance and Control for Launch and Vertical Descend of Reusable Launchers Using Model Predictive Control and Convex Optimisation
    Guidance and Control for Launch and Vertical Descend of Reusable Launchers using Model Predictive Control and Convex Optimisation Guillermo Zaragoza Prous Space Engineering, master's level (120 credits) 2020 Luleå University of Technology Department of Computer Science, Electrical and Space Engineering Abstract The increasing market of small and affordable space systems requires fast and reliable launch capabilities to cover the current and future demand. This project aims to study and implement guidance and control schemes for vertical ascent and descent phases of a reusable launcher. Specifically, the thesis focuses on developing and applying Model Predictive Control (MPC) and optimisation techniques to several kino-dynamic models of rockets. Moreover, the classical MPC method has been modified to include a decreas- ing factor for the horizon used, enhancing the performance of the guidance and control. Multiple scenarios of vertical launch, landing and full flight guidance on Earth and Mars, along with Monte Carlo analysis, were carried out to demonstrate the robustness of the algorithm against different initial conditions. The results were promising and invite to further research. Keywords Model Predictive Control; Rocket; Reusable Launch Vehicle; Vertical Takeoff; Vertical Landing; Guidance and Control; Convex Optimisation; Microcontroller; Processor-in- the-Loop; Space Engineering. v vi ABSTRACT Contents Abstract v Contents vii List of Figures xi List of Tables xiii List of Abbreviations xv Nomenclature xvii Acknowledgements xxi 1 Motivation 1 1.1 Background . .1 1.2 Fundamental Questions . .2 1.3 Outline . .3 2 Literature Review 5 2.1 Guidance and Control . .5 2.1.1 Guidance Subsystem . .6 2.1.1.1 Launch .
    [Show full text]