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NASA Johnson Space Center Houston, Texas 77058 October 1999 Volume 4, Issue 4
A publication of The Orbital Debris Program Office NASA Johnson Space Center Houston, Texas 77058 October 1999 Volume 4, Issue 4. NEWS Marshall Researchers Developing Patch Kit to Mitigate ISS Impact Damage Stephen B. Hall, FD23A procedure and developmental status. external patching for several reasons: time KERMIt Lead Engineer constraints, accessibility, work envelope, Marshall Space Flight Center External Repair Rationale collateral damage and EVA suit compatibility. KERMIt, a Kit for External Repair of The decision was made to develop a kit for A primary risk factor in repairing Module Impacts, is now punctured modules is the being developed at the time constraint involved. Marshall Space Flight Even given the relatively Center in Huntsville, Ala. large volume of air within Its purpose: to seal the Space Station upon punctures in the assembly completion, International Space Station analyses have shown that a caused by collisions with 1-inch-diameter hole can meteoroids or space cause pressure to drop to debris. The kit will enable unacceptable levels in just crewmembers to seal one hour. In that timeframe, punctures from outside the crew must conclude a damaged modules that module has been punctured, have lost atmospheric determine its location, pressure. Delivery of the remove obstructions kit for operational use is restricting access, obtain a scheduled for next year. repair kit and seal the leak. This article -- which This action would be a expands on material challenge even if the crew appearing in the July 1999 was not injured and no issue of “Orbital Debris significant subsystem Quarterly” -- discusses the damage had occurred. rationale for an externally applied patch, Astronaut installing toggle bolt in simulated puncture sample plate on Laboratory requirements influencing Module in Neutral Buoyancy Laboratory. -
Launch and Deployment Analysis for a Small, MEO, Technology Demonstration Satellite
46th AIAA Aerospace Sciences Meeting and Exhibit AIAA 2008-1131 7 – 10 January 20006, Reno, Nevada Launch and Deployment Analysis for a Small, MEO, Technology Demonstration Satellite Stephen A. Whitmore* and Tyson K. Smith† Utah State University, Logan, UT, 84322-4130 A trade study investigating the economics, mass budget, and concept of operations for delivery of a small technology-demonstration satellite to a medium-altitude earth orbit is presented. The mission requires payload deployment at a 19,000 km orbit altitude and an inclination of 55o. Because the payload is a technology demonstrator and not part of an operational mission, launch and deployment costs are a paramount consideration. The payload includes classified technologies; consequently a USA licensed launch system is mandated. A preliminary trade analysis is performed where all available options for FAA-licensed US launch systems are considered. The preliminary trade study selects the Orbital Sciences Minotaur V launch vehicle, derived from the decommissioned Peacekeeper missile system, as the most favorable option for payload delivery. To meet mission objectives the Minotaur V configuration is modified, replacing the baseline 5th stage ATK-37FM motor with the significantly smaller ATK Star 27. The proposed design change enables payload delivery to the required orbit without using a 6th stage kick motor. End-to-end mass budgets are calculated, and a concept of operations is presented. Monte-Carlo simulations are used to characterize the expected accuracy of the final orbit. -
Rocket Propulsion Fundamentals 2
https://ntrs.nasa.gov/search.jsp?R=20140002716 2019-08-29T14:36:45+00:00Z Liquid Propulsion Systems – Evolution & Advancements Launch Vehicle Propulsion & Systems LPTC Liquid Propulsion Technical Committee Rick Ballard Liquid Engine Systems Lead SLS Liquid Engines Office NASA / MSFC All rights reserved. No part of this publication may be reproduced, distributed, or transmitted, unless for course participation and to a paid course student, in any form or by any means, or stored in a database or retrieval system, without the prior written permission of AIAA and/or course instructor. Contact the American Institute of Aeronautics and Astronautics, Professional Development Program, Suite 500, 1801 Alexander Bell Drive, Reston, VA 20191-4344 Modules 1. Rocket Propulsion Fundamentals 2. LRE Applications 3. Liquid Propellants 4. Engine Power Cycles 5. Engine Components Module 1: Rocket Propulsion TOPICS Fundamentals • Thrust • Specific Impulse • Mixture Ratio • Isp vs. MR • Density vs. Isp • Propellant Mass vs. Volume Warning: Contents deal with math, • Area Ratio physics and thermodynamics. Be afraid…be very afraid… Terms A Area a Acceleration F Force (thrust) g Gravity constant (32.2 ft/sec2) I Impulse m Mass P Pressure Subscripts t Time a Ambient T Temperature c Chamber e Exit V Velocity o Initial state r Reaction ∆ Delta / Difference s Stagnation sp Specific ε Area Ratio t Throat or Total γ Ratio of specific heats Thrust (1/3) Rocket thrust can be explained using Newton’s 2nd and 3rd laws of motion. 2nd Law: a force applied to a body is equal to the mass of the body and its acceleration in the direction of the force. -
Commercial Space Transportation Developments and Concepts: Vehicles, Technologies and Spaceports
Commercial Space Transportation 2006 Commercial Space Transportation Developments and Concepts: Vehicles, Technologies and Spaceports January 2006 HQ003606.INDD 2006 U.S. Commercial Space Transportation Developments and Concepts About FAA/AST About the Office of Commercial Space Transportation The Federal Aviation Administration’s Office of Commercial Space Transportation (FAA/AST) licenses and regulates U.S. commercial space launch and reentry activity, as well as the operation of non-federal launch and reentry sites, as authorized by Executive Order 12465 and Title 49 United States Code, Subtitle IX, Chapter 701 (formerly the Commercial Space Launch Act). FAA/AST’s mission is to ensure public health and safety and the safety of property while protecting the national security and foreign policy interests of the United States during commercial launch and reentry operations. In addition, FAA/AST is directed to encour- age, facilitate, and promote commercial space launches and reentries. Additional information concerning commercial space transportation can be found on FAA/AST’s web site at http://ast.faa.gov. Federal Aviation Administration Office of Commercial Space Transportation i About FAA/AST 2006 U.S. Commercial Space Transportation Developments and Concepts NOTICE Use of trade names or names of manufacturers in this document does not constitute an official endorsement of such products or manufacturers, either expressed or implied, by the Federal Aviation Administration. ii Federal Aviation Administration Office of Commercial Space Transportation 2006 U.S. Commercial Space Transportation Developments and Concepts Contents Table of Contents Introduction . .1 Significant 2005 Events . .4 Space Competitions . .6 Expendable Launch Vehicles . .9 Current Expendable Launch Vehicle Systems . .9 Atlas 5 - Lockheed Martin Corporation . -
Development of a Reliable Performance Gas Generator of 75 Tonf-Class Liquid Rocket Engine for the Korea Space Launch Vehicle II
DOI: 10.13009/EUCASS2019-521 8TH EUROPEAN CONFERENCE FOR AERONAUTICS AND SPACE SCIENCES (EUCASS) Development of a Reliable Performance Gas Generator of 75 tonf-class Liquid Rocket Engine for the Korea Space Launch Vehicle II Byoungjik Lim*, Munki Kim*, Donghyuk Kang*, Hyeon-Jun Kim*, Jong-Gyu Kim*, and Hwan-Seok Choi* *Korea Aerospace Research Institute 169-84, Gwahak-ro, Yuseong-Gu Daejeon, 34133, South Korea [email protected] Abstract In this paper, development history and result of a reliable performance gas generator of 75 tonf-class liquid rocket engine is described. Based on the experience acquired from the 30 tonf-class gas generator development, the almost identical concept was adopted to 75 tonf-class gas generator such as a coaxial swirl injector and a regeneratively cooled combustion chamber. During the entire development process using the full-scale and subscale technological demonstration model and development model up to now, combustion tests of over 430 times and cumulative time of over 17 700 seconds have been carried out for a 75 tonf-class gas generate. Now the 75 tonf-class fuel-rich gas generator shows very reliable and reproducible characteristics throughout the entire lifetime including the flight test which was done with the test launch vehicle in November 2018. Thus, it can be said that the development of a 75 tonf-class fuel rich gas generator which will be used in Korea first independent space launch vehicle, KSLV-II was finished successfully. 1. Introduction As a leading institute for technology which is related with space launch vehicle and a national space development agency in the Republic of KOREA, the Korea Aerospace Research Institute (KARI) has been continuously researching and developing technology related to space launch vehicles since establishment in 1989. -
Learning from Other People's Mistakes
Learning from Other People’s Mistakes Most satellite mishaps stem from engineering mistakes. To prevent the same errors from being repeated, Aerospace has compiled lessons that the space community should heed. Paul Cheng and Patrick Smith he computer onboard the Clementine spacecraft froze immediately after a thruster was commanded to fire. A “watchdog” algorithm designed to stop “It’s always the simple stuff the thrusters from excessive firing could not execute, and CTlementine’s fuel ran out. !e mission was lost. Based on that kills you…. With all the this incident, engineers working on the Near Earth Asteroid Rendezvous (NEAR) program learned a key lesson: the testing systems, everything watchdog function should be hard-wired in case of a com- puter shutdown. As it happened, NEAR suffered a similar computer crash during which its thrusters fired thousands looked good.” of times, but each firing was instantly cut off by the still- —James Cantrell, main engineer operative watchdog timer. NEAR survived. As this example illustrates, insights from past anoma- for the joint U.S.-Russian Skipper lies are of considerable value to design engineers and other mission, which failed because program stakeholders. Information from failures (and near its solar panels were connected failures) can influence important design decisions and pre- vent the same mistakes from being made over and over. backward (Associated Press, 1996) Contrary to popular belief, satellites seldom fail because of poor workmanship or defective parts. Instead, most failures are caused by simple engineering errors, such as an over- looked requirement, a unit mix-up, or even a typo in a docu- ment. -
Atlas Launch System Mission Planner's Guide, Atlas V Addendum
ATLAS Atlas Launch System Mission Planner’s Guide, Atlas V Addendum FOREWORD This Atlas V Addendum supplements the current version of the Atlas Launch System Mission Plan- ner’s Guide (AMPG) and presents the initial vehicle capabilities for the newly available Atlas V launch system. Atlas V’s multiple vehicle configurations and performance levels can provide the optimum match for a range of customer requirements at the lowest cost. The performance data are presented in sufficient detail for preliminary assessment of the Atlas V vehicle family for your missions. This guide, in combination with the AMPG, includes essential technical and programmatic data for preliminary mission planning and spacecraft design. Interface data are in sufficient detail to assess a first-order compatibility. This guide contains current information on Lockheed Martin’s plans for Atlas V launch services. It is subject to change as Atlas V development progresses, and will be revised peri- odically. Potential users of Atlas V launch service are encouraged to contact the offices listed below to obtain the latest technical and program status information for the Atlas V development. For technical and business development inquiries, contact: COMMERCIAL BUSINESS U.S. GOVERNMENT INQUIRIES BUSINESS INQUIRIES Telephone: (691) 645-6400 Telephone: (303) 977-5250 Fax: (619) 645-6500 Fax: (303) 971-2472 Postal Address: Postal Address: International Launch Services, Inc. Commercial Launch Services, Inc. P.O. Box 124670 P.O. Box 179 San Diego, CA 92112-4670 Denver, CO 80201 Street Address: Street Address: International Launch Services, Inc. Commercial Launch Services, Inc. 101 West Broadway P.O. Box 179 Suite 2000 MS DC1400 San Diego, CA 92101 12999 Deer Creek Canyon Road Littleton, CO 80127-5146 A current version of this document can be found, in electronic form, on the Internet at: http://www.ilslaunch.com ii ATLAS LAUNCH SYSTEM MISSION PLANNER’S GUIDE ATLAS V ADDENDUM (AVMPG) REVISIONS Revision Date Rev No. -
NYC Aerospace Rocket Program
NYC Aerospace Rocket Program NYC Aerospace’s 100,000ft rocket program is committed to designing and manufacturing a sounding rocket to reach 100,000ft, above 99% of the atmosphere. The purpose of this mission is to research the applications of ammonium perchlorate composite propellant (APCP) to large rockets. Many future aerospace engineers have learned a great deal about rocketry from participating in this project, which is one of NYC Aerospace’s many projects involving students citywide. Rocket details Our goal is to send a single-stage rocket to 100,000ft using ammonium perchlorate composite propellant (APCP). In order to reach this altitude, the rocket will likely need to maintain structural integrity at velocities on the order of Mach 2 and above. Therefore, the rocket body will need to be made of a light metal such as aluminum or titanium. A metal body necessitates the capacity of the rocket motor to be in the O range of near 30,000Ns of impulse. Assuming a perfectly efficient motor, this requires around 30lb of propellant. We can calculate fuel fraction by first establishing our delta v budget. Δv = √2gz = √2(9.8m/s2)(30480m) =772m/s= mach 2.25 Using the delta v necessary, we can calculate the minimum fuel fraction using Tsiolkovsky’s ideal rocket equation. Assuming the specific impulse of our motor is 228s: m final Δv =− v eln m initial m final = exp(− 772/2280) = 0.71 m initial Thus, we only need 29% of our rocket to be fuel. This brings the max mass of our rocket to 103lb. -
Interstellar Probe on Space Launch System (Sls)
INTERSTELLAR PROBE ON SPACE LAUNCH SYSTEM (SLS) David Alan Smith SLS Spacecraft/Payload Integration & Evolution (SPIE) NASA-MSFC December 13, 2019 0497 SLS EVOLVABILITY FOUNDATION FOR A GENERATION OF DEEP SPACE EXPLORATION 322 ft. Up to 313ft. 365 ft. 325 ft. 365 ft. 355 ft. Universal Universal Launch Abort System Stage Adapter 5m Class Stage Adapter Orion 8.4m Fairing 8.4m Fairing Fairing Long (Up to 90’) (up to 63’) Short (Up to 63’) Interim Cryogenic Exploration Exploration Exploration Propulsion Stage Upper Stage Upper Stage Upper Stage Launch Vehicle Interstage Interstage Interstage Stage Adapter Core Stage Core Stage Core Stage Solid Solid Evolved Rocket Rocket Boosters Boosters Boosters RS-25 RS-25 Engines Engines SLS Block 1 SLS Block 1 Cargo SLS Block 1B Crew SLS Block 1B Cargo SLS Block 2 Crew SLS Block 2 Cargo > 26 t (57k lbs) > 26 t (57k lbs) 38–41 t (84k-90k lbs) 41-44 t (90k–97k lbs) > 45 t (99k lbs) > 45 t (99k lbs) Payload to TLI/Moon Launch in the late 2020s and early 2030s 0497 IS THIS ROCKET REAL? 0497 SLS BLOCK 1 CONFIGURATION Launch Abort System (LAS) Utah, Alabama, Florida Orion Stage Adapter, California, Alabama Orion Multi-Purpose Crew Vehicle RL10 Engine Lockheed Martin, 5 Segment Solid Rocket Aerojet Rocketdyne, Louisiana, KSC Florida Booster (2) Interim Cryogenic Northrop Grumman, Propulsion Stage (ICPS) Utah, KSC Boeing/United Launch Alliance, California, Alabama Launch Vehicle Stage Adapter Teledyne Brown Engineering, California, Alabama Core Stage & Avionics Boeing Louisiana, Alabama RS-25 Engine (4) -
Atlas V Cutaway Poster
ATLAS V Since 2002, Atlas V rockets have delivered vital national security, science and exploration, and commercial missions for customers across the globe including the U.S. Air Force, the National Reconnaissance Oice and NASA. 225 ft The spacecraft is encapsulated in either a 5-m (17.8-ft) or a 4-m (13.8-ft) diameter payload fairing (PLF). The 4-m-diameter PLF is a bisector (two-piece shell) fairing consisting of aluminum skin/stringer construction with vertical split-line longerons. The Atlas V 400 series oers three payload fairing options: the large (LPF, shown at left), the extended (EPF) and the extra extended (XPF). The 5-m PLF is a sandwich composite structure made with a vented aluminum-honeycomb core and graphite-epoxy face sheets. The bisector (two-piece shell) PLF encapsulates both the Centaur upper stage and the spacecraft, which separates using a debris-free pyrotechnic actuating 200 ft system. Payload clearance and vehicle structural stability are enhanced by the all-aluminum forward load reactor (FLR), which centers the PLF around the Centaur upper stage and shares payload shear loading. The Atlas V 500 series oers 1 three payload fairing options: the short (shown at left), medium 18 and long. 1 1 The Centaur upper stage is 3.1 m (10 ft) in diameter and 12.7 m (41.6 ft) long. Its propellant tanks are constructed of pressure-stabilized, corrosion-resistant stainless steel. Centaur is a liquid hydrogen/liquid oxygen-fueled vehicle. It uses a single RL10 engine producing 99.2 kN (22,300 lbf) of thrust. -
Aeronautical, Spacecraft, and Launch Vehicle Examples
The Value of Identifying and Recovering Lost GN&C Lessons Learned: Aeronautical, Spacecraft, and Launch Vehicle Examples Cornelius J. Qennehy 1 NASA Engineering and Safety Center (NESC) Steve Labbe2 NASA Johnson Space Center, Houston, TX, 77058 · Kenneth L. Lebsock3 Orbital Sciences Corporation, Technical Services Division, Greenbelt, MD 20770 Within the broad aerospace community the importance of identifying, documenting and widely sharing lessons learned during system development, flight test, operational or research programs/projects is broadly acknowledged. Documenting and sharing lessons learned helps managers and engineers to minimize project risk and improve performance of their systems. Often significant lessons learned on a project fail to get captured even though they are well known 'tribal knowledge" amongst the project team members. The physical act of actually writing down and documenting these lessons learned for the next generation of NASA GN&C engineers fails to happen on some projects for various reasons. In this paper we will first review the importance of capturing lessons learned and then wlll discuss reasons why some lessons are not documented. A simple proven approach called 'Pause and Learn' will be highlighted as a proven low-impact method of organizational learning that could foster the timely capture of critical lessons learned. Lastly some examples of "lost"GN&C lessons learned from the aeronautics, spacecraft and launch vehicle domains are briefly highlighted. In the context of this paper "lost" refers to lessons that have not achieved broad visibility within the NASA-wide GN&C CoP because they are either undocumented, masked or poorly documented in the NASA Lessons Learned Information System (LLIS). -
Accesso Autonomo Ai Servizi Spaziali
Centro Militare di Studi Strategici Rapporto di Ricerca 2012 – STEPI AE-SA-02 ACCESSO AUTONOMO AI SERVIZI SPAZIALI Analisi del caso italiano a partire dall’esperienza Broglio, con i lanci dal poligono di Malindi ad arrivare al sistema VEGA. Le possibili scelte strategiche del Paese in ragione delle attuali e future esigenze nazionali e tenendo conto della realtà europea e del mercato internazionale. di T. Col. GArn (E) FUSCO Ing. Alessandro data di chiusura della ricerca: Febbraio 2012 Ai mie due figli Andrea e Francesca (che ci tiene tanto…) ed a Elisabetta per la sua pazienza, nell‟impazienza di tutti giorni space_20120723-1026.docx i Author: T. Col. GArn (E) FUSCO Ing. Alessandro Edit: T..Col. (A.M.) Monaci ing. Volfango INDICE ACCESSO AUTONOMO AI SERVIZI SPAZIALI. Analisi del caso italiano a partire dall’esperienza Broglio, con i lanci dal poligono di Malindi ad arrivare al sistema VEGA. Le possibili scelte strategiche del Paese in ragione delle attuali e future esigenze nazionali e tenendo conto della realtà europea e del mercato internazionale. SOMMARIO pag. 1 PARTE A. Sezione GENERALE / ANALITICA / PROPOSITIVA Capitolo 1 - Esperienze italiane in campo spaziale pag. 4 1.1. L'Anno Geofisico Internazionale (1957-1958): la corsa al lancio del primo satellite pag. 8 1.2. Italia e l’inizio della Cooperazione Internazionale (1959-1972) pag. 12 1.3. L’Italia e l’accesso autonomo allo spazio: Il Progetto San Marco (1962-1988) pag. 26 Capitolo 2 - Nascita di VEGA: un progetto europeo con una forte impronta italiana pag. 45 2.1. Il San Marco Scout pag.