Low Density Supersonic Decelerators
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MARS SCIENCE LABORATORY ORBIT DETERMINATION Gerhard L. Kruizinga(1)
MARS SCIENCE LABORATORY ORBIT DETERMINATION Gerhard L. Kruizinga(1), Eric D. Gustafson(2), Paul F. Thompson(3), David C. Jefferson(4), Tomas J. Martin-Mur(5), Neil A. Mottinger(6), Frederic J. Pelletier(7), and Mark S. Ryne(8) (1-8)Jet Propulsion Laboratory, California Institute of Technology, 4800 Oak Grove Drive, Pasadena, California 91109, +1-818-354-7060, fGerhard.L.Kruizinga, edg, Paul.F.Thompson, David.C.Jefferson, tmur, Neil.A.Mottinger, Fred.Pelletier, [email protected] Abstract: This paper describes the orbit determination process, results and filter strategies used by the Mars Science Laboratory Navigation Team during cruise from Earth to Mars. The new atmospheric entry guidance system resulted in an orbit determination paradigm shift during final approach when compared to previous Mars lander missions. The evolving orbit determination filter strategies during cruise are presented. Furthermore, results of calibration activities of dynamical models are presented. The atmospheric entry interface trajectory knowledge was significantly better than the original requirements, which enabled the very precise landing in Gale Crater. Keywords: Mars Science Laboratory, Curiosity, Mars, Navigation, Orbit Determination 1. Introduction On August 6, 2012, the Mars Science Laboratory (MSL) and the Curiosity rover successful performed a precision landing in Gale Crater on Mars. A crucial part of the success was orbit determination (OD) during the cruise from Earth to Mars. The OD process involves determining the spacecraft state, predicting the future trajectory and characterizing the uncertainty associated with the predicted trajectory. This paper describes the orbit determination process, results, and unique challenges during the final approach phase. -
IMU/MCAV Integrated Navigation for the Powered Descent Phase Of
Overview of Chinese Current Efforts for Mars Probe Design Xiuqiang Jiang1,2, Ting Tao1,2 and Shuang Li1,2 1. College of Astronautics, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China 2. Space New Technology Laboratory, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China Email: [email protected], [email protected] Abstract Mars exploration activities have gathered scientific data and deepened the current understanding about the Martian evolution process and living environment. As a terrestrial planet, Mars is also an excellent proving ground of some innovative special-purpose aerospace technologies. In the U.S., Soviet Union (Russia), Europe, and India, missions sending spacecraft to explore Mars currently exist, and the first three have landed their spacecrafts on the surface of Mars. China has programmed five Mars landing missions in next 20 years, and some critical technologies for Mars landing mission have been studied beforehand. In this paper, we will report Chinese Mars exploration mission scenario and the latest progress in dynamics study and guidance navigation and control (GNC) system design for Chinese first Mars probe. Some elementary design rules and index will be described according to simulation experiments, analysis and survey. Several new coping strategies will be proposed to be competent for the challenges of the Mars entry descent and landing (EDL) dynamics process. Details of the work, the supporting data and preliminary conclusions of the investigation will be presented. Based on our current efforts, one candidate system configuration architecture of Chinese first Mars probe will be shown and elaborated in the end. United States launched the “Mars Pathfinder (MPF)” 1. -
Upgraded Inflatable Tire Foldable Commuter, Suitable for Adult & Kids
S10 8 Inch Foldable Electric Scooter Upgraded Inflatable Tire Foldable Commuter, Suitable for Adult & Kids For optimum performance and safety, please read these instructions carefully before operating the product. Please keep this manual for future reference. CONTENTS 1. General Information 3 2. Product Overview 4 2.1 General Information 4 2.2 What you need to know 4 3. Product Description 4 3.1 How to Unfold 4 3.2 How to Assemble 5 3.3 How to Fold 5 4. How to Ride 6 5. SCOOTER SAFETY PRECAUTIONS 8 6. Weight and Speed Limitations 10 6.1 Weight Restrictions 10 6.2 Speed Limits 10 7. Operating Range 10 8. Battery Information and Specications 11 9. Charging your Scooter 12 10. Inspection, Maintenance, and Storage 13 11. Scooter Specications 14 2 www.PyleUSA.com 1. General Information LCD Display Handle Folding Hook LED Light Long Pole Hook Hole Accelerate Throttle Back Fender Rear Brake Buckle Lock Electric Brake Folding Wrench Motor Deck Charging Port Kickstand Front Wheel www.PyleUSA.com 3 2. Product Overview 2.1 General information The original scooter is an intuitive, technologically advanced solution. Using the latest technology and production processes, each scooter undergoes strict testing for quality and durability. With its lightweight, portable design, ease of use, range, and low carbon footprint. 2.2 What you need to know Before you rst experience your scooter, please read the USER MANUAL thoroughly and learn the basics to ensure your safety and the safety of others. The power will be shut down if nobody operate in ve minutes, you need press power button before you ride. -
ACHILLES INFLATABLE BOATS a Division of Achilles USA, Inc
2018 INFLATABLE BOATS It begins with the best fabric. Designed and built with safety Because our boats last, Our quality CSM fabric has and performance in mind. so does our support. such a great reputation in the From built-in safety features like We provide our dealers and inflatable boat industry that the strongest four-layer seam customers with comprehensive other inflatable boat manufac- construction in the industry to and responsive post-sales turers buy their fabric from us. custom designs engineered to support in every aspect of It all starts with an exterior complement and enhance the Achilles ownership. Our The Achilles boating experience begins with best inflatable coating of our custom CSM performance of each of our customer and mobile-friendly boat fabric, designs and options and ends with unsurpassed over a heavy duty fabric which boats, boaters get more out of web site not only offers customer support for as long as you own your boat. makes our inflatables virtually an Achilles. Our boats are built comprehensive information In between you will enjoy years of on-the-water activities impervious to the elements, oil, to not only last, but to also about our current models, in the most durable inflatable boat you can find. gasoline and abrasions. And it deliver the practicality you but also on all Achilles boats ends with two interior coatings expect from an inflatable with- produced since 1978. of Chloroprene for unsurpassed out sacrificing the performance CSM exterior for air retention. you want from any boat. toughness www.achillesboats.com Heavy-duty Nylon or Polyester core fabric A SMOOTH, SIMPLE OAR SYSTEM NON-CORROSIVE CHECK VALVES Two layers of Chloroprene We invented the fold-down, locking oar system All Achilles valves are non-corrosive with no moving for unsurpassed that makes rowing a breeze while keeping oars parts that might break. -
How to Make an Inflatable Sphere Aka “Carbon Bubble”?
How to make an inflatable sphere aka “carbon bubble”? The inflatable carbon bubble is a great tool to transform a protest into a highly playful, fun and interactive event and at the same time raise awareness about the carbon bubble issue.*1 The making of the inflatable can be an inspiring group activity. It can be also used for symbolic or direct action: for example the popping of the inflatable carbon bubble can be very powerful to tell and visualise the future market crash of the fossil fuel industry. This manual is based on our 10 minute video tutorial: http://vimeo.com/user11411696/inflatablecarbonbubble Please email us on [email protected] if you have questions. And please send us pictures of your inflatable action! Yours, 350.org and Artúr van Balen / Tools for Action www.toolsforaction.net MATERIALS: -3 hours and 2 persons - strong black bin bags, as big as possible. – heavy duty double-sided tape with remov- able protective foil (important: please check if this tape glues well with your type of bin bags.) - Black gaffer tape & transparent tape - marker pen - scissors and/or utility knife - measurer - 5L plastic bottle - cardboard (same size as bin bag ) -fan or air mattress pump STEP 1: CONSTRUCT THE SAMPLE SHAPE -Cut out the cardboard in the above shape. The cardboard will be your sample shape. (You can find the shape at the end of this document.) -Add extra material at one side of the shape. This will be the seam. The width of the seam is dependent on the size of your double-sided tape. -
Design and Flight Testing of Inflatable Wings with Wing Warping
05WAC-61 Design and Flight Testing of Inflatable Wings with Wing Warping Jamey D. Jacob, Andrew Simpson, and Suzanne Smith University of Kentucky, Lexington, KY 40506 Copyright c 2005 Society of Automotive Engineers, Inc. ABSTRACT The paper presents work on testing of inflatable wings for unmanned aerial vehicles (UAVs). Inflatable wing his- tory and recent research is discussed. Design and con- struction of inflatable wings is then covered, along with ground and flight testing. Discussions include predictions and correlations of the forces required to warp (twist) the wings to a particular shape and the aerodynamic forces generated by that shape change. The focus is on charac- terizing the deformation of the wings and development of a model to accurately predict deformation. Relations be- Figure 1: Goodyear Model GA-468 Inflatoplane. tween wing stiffness and internal pressure and the impact of external loads are presented. Mechanical manipula- tion of the wing shape on a test vehicle is shown to be an effective means of roll control. Possible benefits to aero- craft was developed as a military rescue plane that could dynamic efficiency are also discussed. be dropped behind enemy lines to rescue downed pilots. Technology development, including delivery of dozens of INFLATABLE WINGS aircraft, continued until the early 1970s. PREVIOUS WORK While the concept of inflatable The Apteron unmanned aerial vehicle with inflatable structures for flight originated centuries ago, inflatable wings was developed in the 1970s by ILC Dover, Inc. wings were only conceived and developed within the last The Apteron (Figure 2) had a 1.55 m (5.1 ft) wingspan, few decades. -
Space Vehicle Conceptual Design Blue Team March 20, 2021
Hephaestus: Space Vehicle Conceptual Design Blue team March 20, 2021 Connor Cruickshank, Joel Lundahl, Birgir Steinn Hermannsson, Greta Tartaglia M.Sc. students, KTH Royal Institute of Technology, Stockholm, Sweden Abstract—A hypothetical contest has been issued to summit ms Structural mass Olympus Mons. This report details a conceptual design of a space P Power vehicle intended for that purpose. Functional requirements of the p Combustion chamber pressure vehicle were defined, and the primary subsystems identified. The 02 SpaceX Starship was chosen to serve as a design baseline and pe Exhaust gas exit pressure a comparison of suitable launch vehicles was made. Subsystems S Drag surface such as propulsion, reaction control, power generation, thermal T Thrust management and radiation shielding were considered, as well as ue Exhaust gas exit velocity interior design of the space vehicle and its protection measures W Weight for Mars entry and activities. The consequences of an engine-out scenario were studied. t Metric tonne The Starship launch system was deemed the most suitable launch vehicle candidate. Six Raptor engines were selected for the spacecraft main propulsion system, with 8 smaller thrusters I. INTRODUCTION for reaction control. A radiator mass of 890 kg was estimated In the year 2038 a challenge was issued for a team of for the thermal management system, and lithium metal hydride was determined an adequate radiation shielding material for the pioneers to be the first to reach the peak of Olympus Mons, the crew quarters. A radiation shelter was integrated into the pantry, highest mountain in the solar system. The reward for the first to and layouts of the crew quarters and cargo bay were prepared. -
Jim Winker Has Competencies in the Following Aspects of Ballooning: Management, Research and Development
James A. Winker was born in December of 1928 in Randall, Minnesota, fourth son of Lewis and Cecilia Winker. SOME OF JIM’S KEY BALLOONING EXPERIENCES: - His earliest ballooning experience was as a crew member for the launch and recovery of Don Piccard’s flight in a converted Japanese FUGO bombing balloon in February of 1947. - He participated in the preparation, inflation, free flight and recovery of the first modern hot air balloon flight by inventor Ed Yost in Bruning, Nebraska October 22,1960. - Received his first “Free Balloon Pilot” certificate in July of 1962. - His First solo flight (not under instruction) was in Led Zeppelin in May of 1970. -Became a FAA Balloon Pilot Examiner in 1973-1981 and again 1984-1987. - He piloted Raven’s hot air blimp “Starship Enterprise” at its world debut in Lucerne, Switzerland in May of 1975. - He flew as part of the opening ceremony at the Lake Placid Olympics in February of 1980. - Originated design for modern sport gas balloons, now known as “Quick Fill”. - Retired from Raven Industries at the end of 1990 completing 35 years of working with balloons, including the development of the hot air balloon. GENERAL BALLOONING EXPERIENCES: Jim Winker has competencies in the following aspects of ballooning: Management, Research and Development Planning, Balloon design (scientific and sport balloons), Heavy lift balloons, Air launched balloon techniques, Remotely piloted airships, Balloon and airship pilot, Deployable aerodynamic deceleration and recovery systems, Digital and photographic imagery, and as -
Development of Supersonic Retropropulsion for Future Mars Entry, Descent, and Landing Systems
JOURNAL OF SPACECRAFT AND ROCKETS Vol. 51, No. 3, May–June 2014 Development of Supersonic Retropropulsion for Future Mars Entry, Descent, and Landing Systems Karl T. Edquist∗ and Ashley M. Korzun† NASA Langley Research Center, Hampton, Virginia 23681 Artem A. Dyakonov‡ Blue Origin, LLC, Kent, Washington 98032 Joseph W. Studak§ NASA Johnson Space Center, Houston, Texas 77058 Devin M. Kipp¶ Jet Propulsion Laboratory, California Institute of Technology, Pasadena, California, 91109 and Ian C. Dupzyk** Lunexa, LLC, San Francisco, California 94105 DOI: 10.2514/1.A32715 Recent studies have concluded that Viking-era entry system deceleration technologies are extremely difficult to scale for progressively larger payloads (tens of metric tons) required for human Mars exploration. Supersonic retropropulsion is one of a few developing technologies that may enable future human-scale Mars entry systems. However, in order to be considered as a viable technology for future missions, supersonic retropropulsion will require significant maturation beyond its current state. This paper proposes major milestones for advancing the component technologies of supersonic retropropulsion such that it can be reliably used on Mars technology demonstration missions to land larger payloads than are currently possible using Viking-based systems. The development roadmap includes technology gates that are achieved through ground-based testing and high-fidelity analysis, culminating with subscale flight testing in Earth’s atmosphere that demonstrates stable and controlled flight. The component technologies requiring advancement include large engines (100s of kilonewtons of thrust) capable of throttling and gimbaling, entry vehicle aerodynamics and aerothermodynamics modeling, entry vehicle stability and control methods, reference vehicle systems engineering and analyses, and high-fidelity models for entry trajectory simulations. -
Co-Optimization of Mid Lift to Drag Vehicle Concepts for Mars Atmospheric Entry
10th AIAA/ASME Joint Thermophysics and Heat Transfer Conference AIAA 2010-5052 28 June - 1 July 2010, Chicago, Illinois Co-Optimization of Mid Lift to Drag Vehicle Concepts for Mars Atmospheric Entry Joseph A. Garcia1 , James L. Brown2 , David J. Kinney1 and Jeffrey V. Bowles1 NASA Ames Research Center, Moffett Field, CA 94035, USA and Loc C. Huynh3. Xun J. Jiang3, Eric Lau3, and Ian C. Dupzyk4 ELORET Corporation, Moffett Field, CA 94035, USA As NASA continues to make plans for future robotic precursor and eventual human missions to Mars, the need to characterize and develop designs for entry vehicles capable of delivering large masses to the surface of Mars will persist. In combination with this, NASA has recognized that the current heritage technology for Mars’ Entry Decent and Landing (EDL) does not have the capability to land the required payload masses. Both the Thermal Protection System (TPS) and the Descent/Landing systems require new design approaches. Because of these needs, NASA has performed an Entry, Descent and Landing Systems Analysis (EDL-SA) study for high mass exploration and science missions to identify key enabling technology areas for further investment. One key technology area identified includes rigid aeroshell shapes for aerodynamic performance and controllability. In this investigation, a system optimization study of alternative aeroshell shapes for Mars exploration class payloads of approximately 40 metric tons has been conducted. This system optimization is accomplished using a Multi-disciplinary Design Optimization (MDO) framework which accounts for the aeroshell shape, trajectory, thermal protection system, and vehicle subsystem closure along with a Multi Objective Genetic Algorithm (MOGA) for the initial shape exploration. -
Owner's Manual
TM OWNER’S MANUAL Read and understand this entire manual before riding! DO NOT RETURN TO STORE! This does not affect your statutory rights. NOTE: Manual illustrations are for demonstration purposes only. Illustrations may not refl ect exact appearance of actual product. Specifi cations subject to change without notice. Please have your 21 character product I.D. code ready before contacting Razor for warranty assistance and/or replacement parts. Product I.D. Code: _____________ - ____________ - ____________ EN_130402 CONTENTS Safety Warnings .............................................................................. 1-2 Repair and Maintenance......................................................................4 Before You Begin..................................................................................2 Check Before Riding .............................................................................5 Assembly Instructions ..........................................................................3 Safety Reminders/Warranty ................................................................7 SAFETY WARNINGS AN IMPORTANT MESSAGE TO PARENTS: This manual contains important • Adults must assist children in the initial adjustment procedures to assemble information. For your child’s safety, it is your responsibility to review this the scooter. information with your child and make sure that your child understands all • Obey all local traffic and scootering laws and regulations. warnings, cautions, instructions and safety topics. Razor USA -
The Exomars Programme
EE XX OO MM AA RR SS POCKOCMOC The ExoMars Programme O. Witasse, J. L. Vago, and D. Rodionov 1 June 2014 ESTEC, NOORDWIJK, THE NETHERLANDS 2000-2010 2011 2013 2016 2018 2020 + Mars Sample Odyssey Return TGO MRO (ESA-NASA) MAVEN Mars Express (ESA) MOM India Phobos-Grunt ExoMars MER Phoenix Mars Science Lab MSL2010 Insight MER The data/information contained herein has been reviewed and approved for release by JPL Export Administration on the basis that this document contains no export-controlled information. 4 Cooperation EE XX OO MM AA RR SS POCKOCMOC 5 ExoMars Programme Objectives 1. Technology Demonstration 2. Science 3. Relay orbiter ESA UNCLASSIFIED – For Official Use 6 ExoMars Programme Objectives Technology Demonstration Objectives Entry, Descent and Landing (EDL) on the Mars’ surface Mobility on Mars surface (several kilometres) Access to Mars sub-surface (2 metres) Scientific Objectives To search for signs of past and present life on Mars To characterise the water/geochemical environment as a function of depth in the shallow subsurface To study the surface environment and identify hazards to future human missions Atmosphere characterisation – Trace Gas detection Programmatic Objective Provide link communication to Mars landed surface assets ESA UNCLASSIFIED – For Official Use 7 Programme Overview Two missions launched in 2016 and 2018, respectively The 2016 flight segment consists of a Trace Gas Orbiter (TGO) and an EDL Demonstrator Module (EDM) The 2018 flight segment consists of a Carrier Module (CM) and a Descent Module (DM) with a Rover and a stationary Landing Platform 2016 Mission & 2018 Mission Trace Gas Orbiter (TGO) Carrier Module Descent Module (CM) (DM) ESA ESTRACK Roscosmos Ground Segment Antennas Landing EDL Demonstrator Module Platform Rover (EDM) ESA UNCLASSIFIED – For Official Use NASA DSN 8 Proton M/Breeze M Proton M/Breeze M ESA UNCLASSIFIED – For Official Use 9 2016 Mission Objectives EE XX OO MM AA RR SS TECHNOLOGY OBJECTIVE ‣Entry, Descent, and Landing (EDL) of a payload on the surface of Mars.