The Atmospheric Reentry Demonstrator
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Onboard Determination of Vehicle Glide Capability for Shuttle Abort Flight Managment (Safm)
Source of Acquisition NASA Johnson Space Center ONBOARD DETERMINATION OF VEHICLE GLIDE CAPABILITY FOR SHUTTLE ABORT FLIGHT MANAGMENT (SAFM) Mark Jackson, Timothy Straube, Thomas Fill, Scott Nemeth, When one or more main engines fail during ascent, the flight crew of the Space Shuttle must make several critical decisions and accurately perform a series of abort procedures. One of the most important decisions for many aborts is the selection ofa landing site. Several factors influence the ability to reach a landing site, including the spacecraft point of atmospheric entry, the energy state at atmospheric entry, the vehicle glide capability from that energy state, and whether one or more suitable landing sites are within the glide capability. Energy assessment is further complicated by the fact that phugoid oscillations in total energy influence glide capability. Once the glide capability is known, the crew must select the "best" site option based upon glide capability and landing site conditions and facilities. Since most of these factors cannot currently be assessed by the crew in flight, extensive planning is required prior to each mission to script a variety of procedures based upon spacecraft velocity at the point of engine failure (or failures). The results of this pre flight planning are expressed in tables and diagrams on mission-specific cockpit checklists. Crew checklist procedures involve leafing through several pages of instructions and navigating a decision tree for site selection and flight procedures - all during a time critical abort situation. With the advent of the Cockpit Avionics Upgrade (CAU), the Shuttle will have increased on-board computational power to help alleviate crew workload during aborts and provide valuable situational awareness during nominal operations. -
Spacex Launch Manifest - a List of Upcoming Missions 25 Spacex Facilities 27 Dragon Overview 29 Falcon 9 Overview 31 45Th Space Wing Fact Sheet
COTS 2 Mission Press Kit SpaceX/NASA Launch and Mission to Space Station CONTENTS 3 Mission Highlights 4 Mission Overview 6 Dragon Recovery Operations 7 Mission Objectives 9 Mission Timeline 11 Dragon Cargo Manifest 13 NASA Slides – Mission Profile, Rendezvous, Maneuvers, Re-Entry and Recovery 15 Overview of the International Space Station 17 Overview of NASA’s COTS Program 19 SpaceX Company Overview 21 SpaceX Leadership – Musk & Shotwell Bios 23 SpaceX Launch Manifest - A list of upcoming missions 25 SpaceX Facilities 27 Dragon Overview 29 Falcon 9 Overview 31 45th Space Wing Fact Sheet HIGH-RESOLUTION PHOTOS AND VIDEO SpaceX will post photos and video throughout the mission. High-Resolution photographs can be downloaded from: http://spacexlaunch.zenfolio.com Broadcast quality video can be downloaded from: https://vimeo.com/spacexlaunch/videos MORE RESOURCES ON THE WEB Mission updates will be posted to: For NASA coverage, visit: www.SpaceX.com http://www.nasa.gov/spacex www.twitter.com/elonmusk http://www.nasa.gov/nasatv www.twitter.com/spacex http://www.nasa.gov/station www.facebook.com/spacex www.youtube.com/spacex 1 WEBCAST INFORMATION The launch will be webcast live, with commentary from SpaceX corporate headquarters in Hawthorne, CA, at www.spacex.com. The webcast will begin approximately 40 minutes before launch. SpaceX hosts will provide information specific to the flight, an overview of the Falcon 9 rocket and Dragon spacecraft, and commentary on the launch and flight sequences. It will end when the Dragon spacecraft separates -
Module 1: Hypersonic Atmosphere Lecture1: Characteristics of Hypersonic Atmosphere
NPTEL –Aerospace Module 1: Hypersonic Atmosphere Lecture1: Characteristics of Hypersonic Atmosphere 1.1 Introduction Hypersonic flight has special traits, some of which are seen in every hypersonic flight. Presence of these particular features during a flight is highly dependant on type of trajectory, configuration etc. In short it is the mission requirement which decides the nature of hypersonic atmosphere encountered by the flight vehicle. Some missions are designed for high deceleration in outer atmosphere during reentry. Hence, those flight vehicles experience longer flight duration at high angle of attacks due to which blunt nosed configuration are generally preferred for such aircrafts. On the contrary, some missions are centered on low flight duration with major deceleration closer to earth surface hence these vehicles have sharp nose and low angle of attack flights. Reentry flight path of hypersonic vehicle is thus governed by the parameters called as ballistic parameter and lifting parameter. These parameters are obtained by applying momentum conservation equation in the direction of the flight path and normal to it. Velocity-altitude map of the flight is thus made from the knowledge of these governing flight parameters, weight and surface area. Ballistic parameter is considered for non lifting reentry flights like flight path of Apollo capsule, however lifting parameter is considered for lifting reentry trajectories like that of space shuttle. Therefore hypersonic flight vehicles are classified in four different types based on the design constraints imposed from mission specifications. 1. Reentry Vehicles (RV): These vehicles are typically launched using rocket propulsion system. Reentry of these vehicles is controlled by control surfaces. -
Notes on Earth Atmospheric Entry for Mars Sample Return Missions
NASA/TP–2006-213486 Notes on Earth Atmospheric Entry for Mars Sample Return Missions Thomas Rivell Ames Research Center, Moffett Field, California September 2006 The NASA STI Program Office . in Profile Since its founding, NASA has been dedicated to the • CONFERENCE PUBLICATION. Collected advancement of aeronautics and space science. The papers from scientific and technical confer- NASA Scientific and Technical Information (STI) ences, symposia, seminars, or other meetings Program Office plays a key part in helping NASA sponsored or cosponsored by NASA. maintain this important role. • SPECIAL PUBLICATION. Scientific, technical, The NASA STI Program Office is operated by or historical information from NASA programs, Langley Research Center, the Lead Center for projects, and missions, often concerned with NASA’s scientific and technical information. The subjects having substantial public interest. NASA STI Program Office provides access to the NASA STI Database, the largest collection of • TECHNICAL TRANSLATION. English- aeronautical and space science STI in the world. language translations of foreign scientific and The Program Office is also NASA’s institutional technical material pertinent to NASA’s mission. mechanism for disseminating the results of its research and development activities. These results Specialized services that complement the STI are published by NASA in the NASA STI Report Program Office’s diverse offerings include creating Series, which includes the following report types: custom thesauri, building customized databases, organizing and publishing research results . even • TECHNICAL PUBLICATION. Reports of providing videos. completed research or a major significant phase of research that present the results of NASA For more information about the NASA STI programs and include extensive data or theoreti- Program Office, see the following: cal analysis. -
Ceramic Matrix Composites with Nano Technology–An Overview
International Review of Applied Engineering Research. ISSN 2248-9967 Volume 4, Number 2 (2014), pp. 99-102 © Research India Publications http://www.ripublication.com/iraer.htm Ceramic Matrix Composites with Nano Technology–An Overview Saubhagya Sharma, Samresh Kumar Shashi and Vikram Tomar Department of Material Science & Nano Technology, University of Petroleum & Energy Studies, Dehradun, Uttrakhand. Abstract Ceramic matrix composites (CMCs) are promising materials for use in high temperature structural applications. This class of materials offers high strength to density ratios. Also, their higher temperature capability over conventional super alloys may allow for components that require little or no cooling. This benefit can lead to simpler component designs and weight savings. These materials can also contribute in increasing the operating efficiency due to higher operating temperatures being achieved. Using carbon/carbon composites with the help of Nanotechnology is more beneficial in structural engineering and can decrease the production cost. They can withstand high stresses and temperatures than the traditional alumina, silicon carbide which fracture easily under mechanical loads Fundamental work in processing, characterization and analysis is important before the structural properties of this new class of Nano composites can be optimized. The fields of the Nano composite materials have received a lot of attention to scientists and engineers in recent years. The fabrication of such composites using Nano technology can make a revolution in the field of material science engineering and can make the composites able to be used in long lasting applications. 1. Introduction As we know that Composite materials are the type of materials that are formed by combining two or more materials of different physical and chemical properties. -
A Perspective on the Design and Development of the Spacex Dragon Spacecraft Heatshield
A Perspective on the Design and Development of the SpaceX Dragon Spacecraft Heatshield by Daniel J. Rasky, PhD Senior Scientist, NASA Ames Research Center Director, Space Portal, NASA Research Park Moffett Field, CA 94035 (650) 604-1098 / [email protected] February 28, 2012 2 How Did SpaceX Do This? Recovered Dragon Spacecraft! After a “picture perfect” first flight, December 8, 2010 ! 3 Beginning Here? SpaceX Thermal Protection Systems Laboratory, Hawthorne, CA! “Empty Floor Space” December, 2007! 4 Some Necessary Background: Re-entry Physics • Entry Physics Elements – Ballistic Coefficient – Blunt vs sharp nose tip – Entry angle/heating profile – Precision landing reqr. – Ablation effects – Entry G’loads » Blunt vs Lifting shapes – Lifting Shapes » Volumetric Constraints » Structure » Roll Control » Landing Precision – Vehicle flight and turn-around requirements Re-entry requires specialized design and expertise for the Thermal Protection Systems (TPS), and is critical for a successful space vehicle 5 Reusable vs. Ablative Materials 6 Historical Perspective on TPS: The Beginnings • Discipline of TPS began during World War II (1940’s) – German scientists discovered V2 rocket was detonating early due to re-entry heating – Plywood heatshields improvised on the vehicle to EDL solve the heating problem • X-15 Era (1950’s, 60’s) – Vehicle Inconel and Titanium metallic structure protected from hypersonic heating AVCOAT » Spray-on silicone based ablator for acreage » Asbestos/silicone moldable TPS for leading edges – Spray-on silicone ablator -
FCC-20-54A1.Pdf
Federal Communications Commission FCC 20-54 Before the Federal Communications Commission Washington, D.C. 20554 In the Matter of ) ) Mitigation of Orbital Debris in the New Space Age ) IB Docket No. 18-313 ) REPORT AND ORDER AND FURTHER NOTICE OF PROPOSED RULEMAKING Adopted: April 23, 2020 Released: April 24, 2020 By the Commission: Chairman Pai and Commissioners O’Rielly, Carr, and Starks issuing separate statements; Commissioner Rosenworcel concurring and issuing a statement. Comment Date: (45 days after date of publication in the Federal Register). Reply Comment Date: (75 days after date of publication in the Federal Register). TABLE OF CONTENTS Heading Paragraph # I. INTRODUCTION .................................................................................................................................. 1 II. BACKGROUND .................................................................................................................................... 3 III. DISCUSSION ...................................................................................................................................... 14 A. Regulatory Approach to Mitigation of Orbital Debris ................................................................... 15 1. FCC Statutory Authority Regarding Orbital Debris ................................................................ 15 2. Relationship with Other U.S. Government Activities ............................................................. 20 3. Economic Considerations ....................................................................................................... -
Flight Opportunities and Small Spacecraft Technology Program Updates NAC Technology, Innovation and Engineering Committee Meeting | March 19, 2020
Flight Opportunities and Small Spacecraft Technology Program Updates NAC Technology, Innovation and Engineering Committee Meeting | March 19, 2020 Christopher Baker NASA Space Technology Mission Directorate Flight Opportunities and Small Spacecraft Technology Program Executive National Aeronautics and Space Administration 1 CHANGING THE PACE OF SPACE Through Small Spacecraft Technology and Flight Opportunities, Space Tech is pursuing the rapid identification, development, and testing of capabilities that exploit agile spacecraft platforms and responsive launch capabilities to increase the pace of space exploration, discovery, and the expansion of space commerce. National Aeronautics and Space Administration 2 THROUGH SUBORBITAL FLIGHT The Flight Opportunities program facilitates rapid demonstration of promising technologies for space exploration, discovery, and the expansion of space commerce through suborbital testing with industry flight providers LEARN MORE: WWW.NASA.GOV/TECHNOLOGY Photo Credit: Blue Origin National Aeronautics and Space Administration 3 FLIGHT OPPORTUNITIES BY THE NUMBERS Between 2011 and today… In 2019 alone… Supported 195 successful fights Supported 15 successful fights Enabled 676 tests of payloads Enabled 47 tests of payloads 254 technologies in the portfolio 86 technologies in the portfolio 13 active commercial providers 9 active commercial providers National Aeronautics and Space Administration Numbers current as of March 1, 2020 4 TECHNOLOGY TESTED IN SUBORBITAL Lunar Payloads ISS SPACE IS GOING TO EARTH ORBIT, THE MOON, MARS, AND BEYOND Mars 2020 Commercial Critical Space Lunar Payload Exploration Services Solutions National Aeronautics and Space Administration 5 SUBORBITAL INFUSION HIGHLIGHT Commercial Lunar Payload Services Four companies selected as Commercial Lunar Payload Services (CPLS) providers leveraged Flight Opportunities-supported suborbital flights to test technologies that are incorporated into their landers and/or are testing lunar landing technologies under Flight Opportunities for others. -
World Relieved by Safe Splashdown
COSP' TH2 LI33AH? OF 3 R BOCA BAIOI^ FL*\ 33432 Vol. 15, No. 95 BOCA RATON NEWS Sunday^April 19, 1970 30 Pages 10 Cents Wr? Telegrams pouring in World relieved by safe splashdown By United Press International immediately sent President Nixon boulevards as the spacecraft flashed Hundreds of persons gathered in front downtown Tehran, when the news nations applauded, cheered and raised It was a rare example of world unity "assurance of deep admiration . ." into view on television screens. of the U.S. Embassy to watch a series came. United Nations Secretary General glasses of champagne to toast the born of monumental relief and At the American Embassy in Lon- of placards telling of progress in the hi Moscow, the Soviet news agency United States. gratitude at the safe return Friday of Thant was among the first to send don, callers jammed the switchboard, spacecraft's return. Tass praised the "courage and cool U.S. Apollo 13 astronauts James Nixon his congratulations. congratulating the United States on the In Beirut, roars of approval erupted heads" of the Americans. Moscow Sirens of the Buenos Aires Lovell, Fred Haise and Jack Swigert. "The entire world is thankful and all safe return of the astronauts. from Arab cafes, jammed with people radio cut into its regular domestic newspapers La Prensa, Clarin and La Vatican aides said the Pope had men will long marvel at the un- "Most of the people were so who heard the landing on transistor newscast to report on Apollo 13's Nation blared at the moment the seldom looked so happy. -
Xii Multifunctional Composites 11 Thermal Protection Systems
xii Multifunctional Composites 11 Thermal protection systems, Maurizio Natali, Luigi Torre, and Jos´e Maria Kenny 337 11.1 The hyperthermal environment . 337 11.2 Non-ablative TPS materials . 339 11.2.1 NA-TPS on the Space Shuttle . 339 11.2.2 SSO reusable surface insulation . 341 11.2.3 Conclusion remarks on non-ablative TPS materials . 342 11.3 High temperature composites as polymeric ablatives . 342 11.4 Testing facilities . 348 11.4.1 The oxy-acetylene torch testbed - OATT . 349 11.4.2 The simulated solid rocket motor - SSRM . 349 11.4.3 Plasma jet torches . 351 11.4.4 Recession rate sensing techniques for TPSs . 352 11.5 PAs as thermal insulating materials . 356 11.5.1 Rigid HSMs . 356 11.5.2 Flexible HSMs for TPSs . 356 11.5.3 Elastomeric HSMs for SRMs . 357 11.6 Phenolic impregnated carbon ablators . 359 11.7 Differences between FRPAs and LCAs . 360 11.8 Nanostructured ablative materials . 360 11.8.1 Nanosilica as filler for traditional and nanostructured ablatives 363 Table of Contents xiii 11.8.2 Carbon nanofilaments based NRAMs . 366 11.9 Conclusions . 368 Bibliography . 369 Chapter 11 Thermal protection systems Maurizio Natali, Luigi Torre, and Jos´eMaria Kenny University of Perugia, Perugia, Italy Abstract Ablative materials play a vital role for the entire aerospace industry. Although some non-polymeric materials have been successfully used as ablatives, polymer ablatives (PA) represent the most versatile class of thermal protection system (TPS) materials. Compared with oxide, inorganic polymer, and metal based TPS materials, PAs have some intrinsic advantages, such as high heat shock resistance and low density. -
The Design and Development of an Electromechanical Drogue Parachute Line Release Mechanism for Level 3 High-Power Amateur Rockets
Portland State University PDXScholar University Honors Theses University Honors College 5-24-2019 The Design and Development of an Electromechanical Drogue Parachute Line Release Mechanism for Level 3 High-Power Amateur Rockets Marie House Portland State University Follow this and additional works at: https://pdxscholar.library.pdx.edu/honorstheses Let us know how access to this document benefits ou.y Recommended Citation House, Marie, "The Design and Development of an Electromechanical Drogue Parachute Line Release Mechanism for Level 3 High-Power Amateur Rockets" (2019). University Honors Theses. Paper 753. https://doi.org/10.15760/honors.770 This Thesis is brought to you for free and open access. It has been accepted for inclusion in University Honors Theses by an authorized administrator of PDXScholar. Please contact us if we can make this document more accessible: [email protected]. The design and development of an electromechanical drogue parachute line release mechanism for level 3 high-power amateur rockets by Marie House An undergraduate honors thesis submitted in partial fulfillment of the requirements for the degree of Bachelor of Science in University Honors and Mechanical Engineering Thesis Adviser Robert Paxton Portland State University 2019 Abstract This research has developed a viable drogue parachute release system sufficient for recovering level 3 amateur rockets. The system is based on the simple mechanics of combining two lever arms and a 2 to 1 pulley interaction to create a 200:1 force reduction between the weight applied to the system and the force required to release it. A linear actuator retracts a release cord, triggering the three rings that hold the system together to unfurl from one another and separate the drogue parachute from the payload. -
Status of the Space Shuttle Solid Rocket Booster
The Space Congress® Proceedings 1980 (17th) A New Era In Technology Apr 1st, 8:00 AM Status of The Space Shuttle Solid Rocket Booster William P. Horton Solid Rocket Booster Engineering Office, George C. Marshall Space Flight Center, Follow this and additional works at: https://commons.erau.edu/space-congress-proceedings Scholarly Commons Citation Horton, William P., "Status of The Space Shuttle Solid Rocket Booster" (1980). The Space Congress® Proceedings. 3. https://commons.erau.edu/space-congress-proceedings/proceedings-1980-17th/session-1/3 This Event is brought to you for free and open access by the Conferences at Scholarly Commons. It has been accepted for inclusion in The Space Congress® Proceedings by an authorized administrator of Scholarly Commons. For more information, please contact [email protected]. STATUS OF THE SPACE SHUTTLE SOLID ROCKET BOOSTER William P. Horton, Chief Engineer Solid Rocket Booster Engineering Office George C. Marshall Space Flight Center, AL 35812 ABSTRACT discuss retrieval and refurbishment plans for Booster reuse, and will address Booster status Two Solid Rocket Boosters provide the primary for multimission use. first stage thrust for the Space Shuttle. These Boosters, the largest and most powerful solid rocket vehicles to meet established man- BOOSTER CONFIGURATION rated design criteria, are unique in that they are also designed to be recovered, refurbished, It is appropriate to review the Booster config and reused. uration before describing the mission profile. The Booster is 150 feet long and is 148 inches The first SRB f s have been stacked on the in diameter (Figure 1), The inert weight Mobile Launch Platform at the Kennedy Space is 186,000 pounds and the propellant weight is Center and are ready to be mated with the approximately 1.1 million pounds for each External Tank and Orbiter in preparation for Booster.