Commercial Crew Program Status to the NRC ASEB
Total Page:16
File Type:pdf, Size:1020Kb
Load more
Recommended publications
-
Validation of Wind Tunnel Test and Cfd Techniques for Retro-Propulsion (Retpro): Overview on a Project Within the Future Launchers Preparatory Programme (Flpp)
VALIDATION OF WIND TUNNEL TEST AND CFD TECHNIQUES FOR RETRO-PROPULSION (RETPRO): OVERVIEW ON A PROJECT WITHIN THE FUTURE LAUNCHERS PREPARATORY PROGRAMME (FLPP) D. Kirchheck, A. Marwege, J. Klevanski, J. Riehmer, A. Gulhan¨ German Aerospace Center (DLR) Supersonic and Hypersonic Technologies Department Cologne, Germany S. Karl O. Gloth German Aerospace Center (DLR) enGits GmbH Spacecraft Department Todtnau, Germany Gottingen,¨ Germany ABSTRACT and landing (VTVL) spacecraft, assisted by retro-propulsion. Up to now, in Europe, knowledge and expertise in that field, The RETPRO project is a 2-years activity, led by the Ger- though constantly growing, is still limited. Systematic stud- man Aerospace Center (DLR) in the frame of ESA’s Future ies were conducted to compare concepts for possible future Launchers Preparatory Program (FLPP), to close the gap of European launchers [2, 3], and activities on detailed inves- knowledge on aerodynamics and aero-thermodynamics of tigations of system components of VTVL re-usable launch retro-propulsion assisted landings for future concepts in Eu- vehicles (RLV) recently started in the RETALT project [4, 5]. rope. The paper gives an overview on the goals, strategy, and Nevertheless, validated knowledge on the aerodynamic current status of the project, aiming for the validation of inno- and aerothermal characteristics of such vehicles is still lim- vative WTT and CFD tools for retro-propulsion applications. ited to a small amount of experimental and numerical inves- Index Terms— RETPRO, retro-propulsion, launcher tigations mostly on lower altitude VTVL trajectories, e. g. aero-thermodynamics, wind tunnel testing, CFD validation within the CALLISTO project [6, 7, 8]. Other studies were conducted to analyze the aerothermodynamics of a simplified generic Falcon 9 geometry during its re-entry and landing 1. -
Reusable Launch Vehicle Technology Program{
Acta Astronautica Vol. 41, No. 11, pp. 777±790, 1997 # 1998 Published by Elsevier Science Ltd. All rights reserved Printed in Great Britain PII: S0094-5765(97)00197-5 0094-5765/98 $19.00 + 0.00 REUSABLE LAUNCH VEHICLE TECHNOLOGY PROGRAM{ DELMA C. FREEMAN{ JR. and THEODORE A. TALAY} NASA Langley Research Center, Hampton, Virginia 23681-0001, USA R. EUGENE AUSTIN} NASA Marshall Space Flight Center, Marshall Space Flight Center, Alabama 35812-1000, USA (Received 25 April 1997) AbstractÐIndustry/NASA reusable launch vehicle (RLV) technology program eorts are underway to design, test, and develop technologies and concepts for viable commercial launch systems that also satisfy national needs at acceptable recurring costs. Signi®cant progress has been made in understanding the technical challenges of fully reusable launch systems and the accompanying management and oper- ational approaches for achieving a low-cost program. This paper reviews the current status of the RLV technology program including the DC-XA, X-33 and X-34 ¯ight systems and associated technology programs. It addresses the speci®c technologies being tested that address the technical and operability challenges of reusable launch systems including reusable cryogenic propellant tanks, composite structures, thermal protection systems, improved propul- sion, and subsystem operability enhancements. The recently concluded DC-XA test program demon- strated some of these technologies in ground and ¯ight tests. Contracts were awarded recently for both the X-33 and X-34 ¯ight demonstrator systems. The Orbital Sciences Corporation X-34 ¯ight test ve- hicle will demonstrate an air-launched reusable vehicle capable of ¯ight to speeds of Mach 8. -
A Review of Current Research in Subscale Flight Testing and Analysis of Its Main Practical Challenges
aerospace Article A Review of Current Research in Subscale Flight Testing and Analysis of Its Main Practical Challenges Alejandro Sobron * , David Lundström and Petter Krus Department of Management and Engineering, Division of Fluid and Mechatronic Systems, Linköping University, SE-58183 Linköping, Sweden; [email protected] (D.L.); [email protected] (P.K.) * Correspondence: [email protected]; Tel.: +46-1328-1893 Abstract: Testing of untethered subscale models, often referred to as subscale flight testing, has traditionally had a relatively minor, yet relevant use in aeronautical research and development. As recent advances in electronics, rapid prototyping and unmanned-vehicle technologies expand its capabilities and lower its cost, this experimental method is seeing growing interest across academia and the industry. However, subscale models cannot meet all similarity conditions required for simulating full-scale flight. This leads to a variety of approaches to scaling and to other alternative applications. Through a literature review and analysis of different scaling strategies, this study presents an overall picture of how subscale flight testing has been used in recent years and synthesises its main issues and practical limitations. Results show that, while the estimation of full-scale characteristics is still an interesting application within certain flight conditions, subscale models are progressively taking a broader role as low-cost technology-testing platforms with relaxed similarity constraints. Different approaches to tackle the identified practical challenges, implemented both by the authors and by other organisations, are discussed and evaluated through flight experiments. Citation: Sobron, A.; Lundström, D.; Keywords: subscale flight testing; similarity; scale model; remotely piloted aircraft; demonstration; Krus, P. -
+ Part 10: Test and Evaluation
10. Test and Evaluation 10.1 Approach Architecture Design, Development, Test, and Evaluation (DDT&E) schedule, costs, and risk are highly dependent on the integrated test and evaluation approach for each of the major elements. As a part of the Exploration Systems Architecture Study (ESAS), a top-level test and evaluation plan, including individual flight test objectives, was developed and is summarized in this section. The test and evaluation plan described here is derived from the Apollo Flight Test Program of the 1960s. A more detailed test and evaluation plan will be based on detailed verification requirements and objectives documented in specifications and verification plans. In order to support schedule, cost, and risk assessments for the reference ESAS architecture, an integrated test and evaluation plan was developed to identify the number and type of major test articles (flight and ground) and the timing and objectives of each major flight test, including facilities and equipment required to support those tests. This initial plan is based on the Apollo Program and the ESAS Ground Rules and Assumptions (GR&As)—including the human- rating requirements from NASA Procedural Requirements (NPR) 8705.2A, Human-Rating Requirements for Space Systems. 10. Test and Evaluation 645 10.2 Ground Rules and Assumptions ESAS GR&As establish the initial set of key constraints to testing. Although all ESAS GR&As are considered, the specific ones listed below are particularly significant, as they deal with schedule and testing/qualification assumptions. • The crew launch system shall facilitate crew survival using abort and escape. There will be three all-up tests of the Launch Abort System (LAS). -
Emotional Intelligence
O L O R A D AerospaceO S T E M M A G A Z i N E Orion Lockheed Martin Colorado E.I. Emotional Intelligence Apollopalooza 2019 July \\022v “An Experience for Everyone” Colorado Aerospace STEM Magazine believes that the key to success in seeing higher graduation rates, improved test- Orion Test ing results, student inspiration, creativity, Lockheed Martin excitement and career satisfaction rests in the hands of the teacher. The example and inspiration of individual educators carries tremendous weight on a daily basis, great- ly impacting the quality and effectiveness of the classroom environment. STEM Teaching Career Hill Our mission: Encourage curiosity, Betsy investigation, inspiration, creativity, and innovation; the foundations of every career passion and career in the Colorado workforce. STEM Careers of Tomorrow Laron Walker Wayne Carley Publisher Unlimited distribution is permitted to everyone receiving Colorado Aerospace Emotional Intelligence STEM Magazine. Please feel free to share Pat Kozyra with educators, students, parents and in- terested individuals or organizations. Colorado Aerospace STEM Magazine strives to encourage the educator to better STEM Tools Delights understand the importance of STEM skills, Estes, Boucvalt, their use in every school subject, the need Bryce Cathy and ease of integration into curriculum Steve Curtis, and Bruce Camber and the urgency for students to embrace STEM. To find out more, please send your E-mail request to: Apollopalooza [email protected] Lockheed Martin Orionwww.lockheedmartin.com This month, NASA will test the Orion’s The AA-2 test will last less than three launch abort system (LAS) for the final minutes, but the mock-up module will time, and the team charged with keep- reach up to 31,000 feet at more than 1,000 ing the crew safe from injury during the mph (Mach 1.3) before the LAS fires and most severe phases of space flight will be separates the module from the booster. -
Flight Engineer Knowledge Test Guide
AC 63-1 FLIGHT ENGINEER KNOWLEDGE TEST GUIDE U.S. Department of Transportation Federal Aviation Administration 1 FLIGHT ENGINEER KNOWLEDGE TEST GUIDE 1995 U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION Flight Standards Service 2 PREFACE The Flight Standards Service of the Federal Aviation Administration (FAA) has developed this guide to help applicants meet the knowledge requirements for the computer administered tests for flight engineer turbojet, turboprop, and reciprocating class certification. This guide contains information about the knowledge test eligibility requirements, test descriptions, testing and retesting procedures, and sample test questions with answers. As a convenience to the applicant, the eligibility requirements for the oral and flight tests are included. Appendix 1 provides a list of reference materials and subject matter knowledge codes, and computer testing designees. Changes to the subject matter knowledge code list will be published as a separate advisory circular. The sample questions and answers in this guide are predicated on Federal Aviation Regulations (FAR's) and references that were current at the time of publication. Questions and answers in the computer administered knowledge tests are updated when changes are made to these reference materials. The flight engineer test question bank and subject matter knowledge code list for all airmen certificates and ratings, with changes, may be obtained by computer access from FedWorld at (703) 321-3339. This bulletin board service is provided by the U.S. Department of Commerce, 24 hours a day, 7 days per week. For technical assistance regarding computer requirements for this service, contact the FedWorld help desk at (703) 487-4608 from 7:30 a.m. -
The Orion Launch Abort System
Constellation Program: Astronaut Safety in a Launch Emergency The Orion Launch Abort System When astronauts rocket to the moon notice and setting the stage for a safe aboard NASA’s Orion crew exploration landing. vehicle, they will lift off in a spacecraft that can escape safely should a malfunction in Making its first flights early in the next the launch vehicle occur. decade, the Orion/Ares I launch system is being developed by the Constellation The Orion launch abort system (LAS) will Program as it prepares to send human offer a safe, reliable method of pulling the explorers back to the moon, and then entire crew out of danger in the event of an onward to Mars and other destinations in emergency on the launch pad or during the the solar system. climb to Earth orbit. Mounted at the top of the Orion and Ares Launch Abort Sequence I launch vehicle stack, the abort system will be capable of automatically separating the If a launch pad or in-flight emergency spacecraft from the rocket at a moment’s occurs, the abort and attitude control Orion’s launch abort system is designed to pull the crew module to safety in an emergency. motors will ignite, pulling the Orion crew module safely free of the Ares I launch vehicle. Th e abort motor will generate 400,000 pounds of thrust in a Nose Cone fraction of a second, rapidly pulling the crew to safety while the attitude control motors maintain stability. Attitude Control Motor (Eight Nozzles) After the vehicle is safely away from the booster, the attitude control motor will reorient the capsule before the crew module is released from the abort system to Interstage begin its controlled descent. -
Nasa's Commercial Crew Development
NASA’S COMMERCIAL CREW DEVELOPMENT PROGRAM: ACCOMPLISHMENTS AND CHALLENGES HEARING BEFORE THE COMMITTEE ON SCIENCE, SPACE, AND TECHNOLOGY HOUSE OF REPRESENTATIVES ONE HUNDRED TWELFTH CONGRESS FIRST SESSION WEDNESDAY, OCTOBER 26, 2011 Serial No. 112–46 Printed for the use of the Committee on Science, Space, and Technology ( Available via the World Wide Web: http://science.house.gov U.S. GOVERNMENT PRINTING OFFICE 70–800PDF WASHINGTON : 2011 For sale by the Superintendent of Documents, U.S. Government Printing Office Internet: bookstore.gpo.gov Phone: toll free (866) 512–1800; DC area (202) 512–1800 Fax: (202) 512–2104 Mail: Stop IDCC, Washington, DC 20402–0001 COMMITTEE ON SCIENCE, SPACE, AND TECHNOLOGY HON. RALPH M. HALL, Texas, Chair F. JAMES SENSENBRENNER, JR., EDDIE BERNICE JOHNSON, Texas Wisconsin JERRY F. COSTELLO, Illinois LAMAR S. SMITH, Texas LYNN C. WOOLSEY, California DANA ROHRABACHER, California ZOE LOFGREN, California ROSCOE G. BARTLETT, Maryland BRAD MILLER, North Carolina FRANK D. LUCAS, Oklahoma DANIEL LIPINSKI, Illinois JUDY BIGGERT, Illinois GABRIELLE GIFFORDS, Arizona W. TODD AKIN, Missouri DONNA F. EDWARDS, Maryland RANDY NEUGEBAUER, Texas MARCIA L. FUDGE, Ohio MICHAEL T. MCCAUL, Texas BEN R. LUJA´ N, New Mexico PAUL C. BROUN, Georgia PAUL D. TONKO, New York SANDY ADAMS, Florida JERRY MCNERNEY, California BENJAMIN QUAYLE, Arizona JOHN P. SARBANES, Maryland CHARLES J. ‘‘CHUCK’’ FLEISCHMANN, TERRI A. SEWELL, Alabama Tennessee FREDERICA S. WILSON, Florida E. SCOTT RIGELL, Virginia HANSEN CLARKE, Michigan STEVEN M. PALAZZO, Mississippi VACANCY MO BROOKS, Alabama ANDY HARRIS, Maryland RANDY HULTGREN, Illinois CHIP CRAVAACK, Minnesota LARRY BUCSHON, Indiana DAN BENISHEK, Michigan VACANCY (II) C O N T E N T S Wednesday, October 26, 2011 Page Witness List ............................................................................................................ -
Applied Aeroscience and CFD Branch Overview
https://ntrs.nasa.gov/search.jsp?R=20140009378 2019-08-31T20:33:41+00:00Z Applied Aeroscience and CFD Branch Overview Gerald J. LeBeau Dr. Benjamin S. Kirk Applied Aeroscience and CFD Branch Engineering Directorate Houston, Texas USA 1 Lyndon B. Johnson Space Center Principal Mission: Human Spaceflight International Space Station MPCV Orion Commercial Crew Mission Control Astronauts 2 The Future of Human Space Exploration NASA’s Building Blocks to Mars Expanding capabilities by visiting an asteroid in a Lunar distant retrograde orbit U.S. companies provide affordable access to low Earth orbit Exploring Mars and other deep space Learning the destinations fundamentals aboard the International Traveling beyond low Earth Space Station orbit with the Space Launch System rocket and Orion crew capsule Missions: 6 to 12 months Missions: 1 month up to 12 months Missions: 2 to 3 years Return: hours Return: days Return: months 3 Earth Reliant Proving Ground Earth Independent Aeroscience Technical Competencies (1) Aerodynamic Characterization (2) Aerothermodynamic Heating (3) Rarefied Gas Dynamics (4) Decelerator (Parachute) Systems Ground Testing Modeling and Simulation Flight Testing 5 Principal JSC Initiatives & Aeroscience Support 1. Operate the International Space Station • Aerodynamic & aerothermodynamic response for rarefied flows • Plume modeling for visiting vehicles • ISS end-of-life disposal 2. Develop the Multipurpose Crew Vehicle Orion • Develop aerodynamic & aeroheating databases • Support development of the parachute recovery system -
The Apollo Spacecraft Chronology, Takes up the Story Where the First Left Off, in November 1962
A CHRONOLOGY NASA SP-4009 THE APOLLO SPACECRAFT A CHRONOLOGY VOLUME II November 8, 1962--September 80, 1964 by Mary Louise Morse and Jean Kernahan Bays THE NASA HISTORICAL SERIES Scientific and Technical ln[ormation Office 1973 /LS.P,. / NATIONAL AERONAUTICS AND SPACE ADMINISTRATION Washington, D.C. For sale by the Superintendent of Documents U.S. Government Printing Office, Washington, D.C. 20402 Price $3.20 Stock Number 3300-0455 (Paper Cover) Library o] Congress Catalog Card Number 69-60008 FOREWORD This, tile second volume of the Apollo Spacecraft Chronology, takes up the story where the first left off, in November 1962. The first volume dealt with the birth of the Apollo Program and traced its early development. The second concerns its teenage period, up to September 30, 1964. By late 1962 the broad conceptual design of the Apollo spacecraft and the Apollo lunar landing mission was complete. The Administrator formally advised the President of the United States on December 10 that NASA had selected lunar orbit rendezw)us over direct ascent and earth orbit rendezvous as the mode for landing on the moon. All major spacecraft contractors had been selected; detailed system design and early developmental testing were under way. On October 20, 1962, soon after Wally Schirra's six-orbit mission in .Sigma 7, the first formal overall status review of the Apollo spacecraft and flight mission effort was given to Administrator James E. _Vebb. The writer of this foreword, who was then the Assistant Director for Apollo Spacecraft Development, recalls George Low, then Director of Manned Spacecraft and Flight Missions trader D. -
UAS FLIGHT TEST for SAFETY and for EFFICIENCY Seamus M
UAS FLIGHT TEST FOR SAFETY AND FOR EFFICIENCY Seamus M. McGovern, U.S. DOT National Transportation Systems Center, Cambridge, Massachusetts Abstract (e.g., SAE International technical standards and recommended practices) but also takes advantage of Manned aircraft that operate in the National competitive racing in order to evaluate new Airspace System (NAS) typically undergo technologies and materials (as it turns out, this may certification flight test to ensure they meet a have applicability to UASs as well with the advent of prescribed level of safety—dependent on their several organizations and sanctioning bodies category—before they are able to enter service [for including the European Rotor Sports Association and example, Federal Aviation Administration (FAA) the Drone Racing League). Other aviation-related advisory circular (AC) 25-7C is the flight-test guide tests and test formats not discussed here include the for certification of transport-category airplanes]. typically Department of Defense-focused With the integration of unmanned aircraft systems developmental test and evaluation; operational test (UAS) into the NAS, in the future some type of and evaluation; and research, development, test, and certification flight test may ultimately be required, evaluation structures. however, even lacking such a requirement UAS manufacturers can find value in flight testing UASs In terms of flight test, the military services have using familiar experimental and certification flight- their own criteria for evaluating their various aircraft. test procedures, the results of which can enhance the These requirements are often bound by contractual safety of the design, the safety of the operation, agreements between the service and the vendor, and/or the efficiency of the operation. -
A Flight Dynamics Perspective of the Orion Pad Abort One Flight Test
A Flight Dynamics Perspective of the Orion Pad Abort One Flight Test Jinu Idicula,∗ Peggy S. Williams-Hayes,∗ and Ryan Stillwater,∗ NASA Dryden Flight Research Center, Edwards, CA, 93523 Lt. Max Yates∗ Unites States Air Force, Edwards, CA, 93523 The Orion Crew Exploration Vehicle is America’s next generation of human rated space- craft. The Orion Launch Abort System will take the astronauts away from the exploration vehicle in the event of an aborted launch. The pad abort mode of the Launch Abort System will be flight-tested in 2009 from the White Sands Missile Range in New Mexico. This pa- per examines some of the efforts currently underway at the NASA Dryden Flight Research Center by the Controls & Dynamics group in preparation for the flight test. The concept of operation for the pad abort flight is presented along with an overview of the guidance, control and navigation systems. Preparations for the flight test, such as hardware testing and development of the real-time displays, are examined. The results from the validation and verification efforts for the aerodynamic and atmospheric models are shown along with Monte Carlo analysis results. Nomenclature α Angle of Attack (deg) β angle of sideslip, deg) AA-1 Ascent Abort 1 AA-2 Ascent Abort 2 AA-3 Ascent Abort 3 ACM Attitude Control Motor AGL above ground level AIL article-in-the-loop AM Abort Motor ANTARES Advanced NASA Technology Architecture for Exploration Studies API Application Programming Interface c.g. center of gravity CAP CEV Aerosciences Project CEV Crew Exploration Vehicle CM Crew Module DFI Developmental Flight Instrumentation DOF degrees of freedom FADS Flush Air Data System FTA Flight Test Article GN&C guidance, navigation, and control GPS Global Positioning System GRAM Global Reference Atmospheric Model IADS Interactive Analysis and Display Software INS Inertial Navigation System ∗Aerospace Engineer, Controls & Dynamics Branch, M/S 4840D, AIAA Member.