Space Almanac 2005
Total Page:16
File Type:pdf, Size:1020Kb
Load more
Recommended publications
-
Instruction 10-1204 1 June 2006
BY ORDER OF THE COMMANDER AIR FORCE SPACE COMMAND AIR FORCE SPACE COMMAND INSTRUCTION 10-1204 1 JUNE 2006 Operations SATELLITE OPERATIONS COMPLIANCE WITH THIS PUBLICATION IS MANDATORY NOTICE: This publication is available digitally on the AFDPO WWW site at: http://www.e-publishing.af.mil. OPR: A3FS (Lt Col Kirk Jester) Certified by: A3F (Col David Jones) Pages: 22 Distribution: F This instruction implements Air Force Policy Directive (AFPD) 10-12, Space, Air Force Instruction (AFI) 10-1201, Space Operations and United States Space Command Policy Directive (UPD) 10-39, Sat- ellite Disposal Procedures (UPD 10-39 is being updated to a Strategic Command Directive (SD)), by establishing guidance and procedures for satellite operations and disposal. It applies to Headquarters Air Force Space Command (HQ AFSPC) and all subordinate units utilizing dedicated satellite control assets or common use and/or unique resources of the Air Force Satellite Control Network (AFSCN), except for Royal Air Force (RAF) Telemetry and Command Squadron (TCS), Oakhanger. This instruction applies to Air National Guard (ANG) and Air Force Reserve Command (AFRC) units with satellite control respon- sibilities. Submit changes to HQ AFSPC/A3F, Global Space Operations Division, 150 Vandenberg St., Ste 1105, Peterson AFB CO 80914-4250. If there is a conflict between this instruction and unit, contractor or other major command publications, this instruction applies. Maintain and dispose of records created as a result of prescribed processes in accordance with Air Force Records Disposition Schedule (RDS) which may be found on-line at https://afrims.amc.af.mil. The previous Air Force Space Command Instruction (AFSPCI) 10-1204, dated 1 September 1998, was rescinded in 2001. -
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. -
L AUNCH SYSTEMS Databk7 Collected.Book Page 18 Monday, September 14, 2009 2:53 PM Databk7 Collected.Book Page 19 Monday, September 14, 2009 2:53 PM
databk7_collected.book Page 17 Monday, September 14, 2009 2:53 PM CHAPTER TWO L AUNCH SYSTEMS databk7_collected.book Page 18 Monday, September 14, 2009 2:53 PM databk7_collected.book Page 19 Monday, September 14, 2009 2:53 PM CHAPTER TWO L AUNCH SYSTEMS Introduction Launch systems provide access to space, necessary for the majority of NASA’s activities. During the decade from 1989–1998, NASA used two types of launch systems, one consisting of several families of expendable launch vehicles (ELV) and the second consisting of the world’s only partially reusable launch system—the Space Shuttle. A significant challenge NASA faced during the decade was the development of technologies needed to design and implement a new reusable launch system that would prove less expensive than the Shuttle. Although some attempts seemed promising, none succeeded. This chapter addresses most subjects relating to access to space and space transportation. It discusses and describes ELVs, the Space Shuttle in its launch vehicle function, and NASA’s attempts to develop new launch systems. Tables relating to each launch vehicle’s characteristics are included. The other functions of the Space Shuttle—as a scientific laboratory, staging area for repair missions, and a prime element of the Space Station program—are discussed in the next chapter, Human Spaceflight. This chapter also provides a brief review of launch systems in the past decade, an overview of policy relating to launch systems, a summary of the management of NASA’s launch systems programs, and tables of funding data. The Last Decade Reviewed (1979–1988) From 1979 through 1988, NASA used families of ELVs that had seen service during the previous decade. -
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) -
Los Motores Aeroespaciales, A-Z
Sponsored by L’Aeroteca - BARCELONA ISBN 978-84-608-7523-9 < aeroteca.com > Depósito Legal B 9066-2016 Título: Los Motores Aeroespaciales A-Z. © Parte/Vers: 1/12 Página: 1 Autor: Ricardo Miguel Vidal Edición 2018-V12 = Rev. 01 Los Motores Aeroespaciales, A-Z (The Aerospace En- gines, A-Z) Versión 12 2018 por Ricardo Miguel Vidal * * * -MOTOR: Máquina que transforma en movimiento la energía que recibe. (sea química, eléctrica, vapor...) Sponsored by L’Aeroteca - BARCELONA ISBN 978-84-608-7523-9 Este facsímil es < aeroteca.com > Depósito Legal B 9066-2016 ORIGINAL si la Título: Los Motores Aeroespaciales A-Z. © página anterior tiene Parte/Vers: 1/12 Página: 2 el sello con tinta Autor: Ricardo Miguel Vidal VERDE Edición: 2018-V12 = Rev. 01 Presentación de la edición 2018-V12 (Incluye todas las anteriores versiones y sus Apéndices) La edición 2003 era una publicación en partes que se archiva en Binders por el propio lector (2,3,4 anillas, etc), anchos o estrechos y del color que desease durante el acopio parcial de la edición. Se entregaba por grupos de hojas impresas a una cara (edición 2003), a incluir en los Binders (archivadores). Cada hoja era sustituíble en el futuro si aparecía una nueva misma hoja ampliada o corregida. Este sistema de anillas admitia nuevas páginas con información adicional. Una hoja con adhesivos para portada y lomo identifi caba cada volumen provisional. Las tapas defi nitivas fueron metálicas, y se entregaraban con el 4 º volumen. O con la publicación completa desde el año 2005 en adelante. -Las Publicaciones -parcial y completa- están protegidas legalmente y mediante un sello de tinta especial color VERDE se identifi can los originales. -
Conestoga Launch Vehicles
The Space Congress® Proceedings 1988 (25th) Heritage - Dedication - Vision Apr 1st, 8:00 AM Conestoga Launch Vehicles Mark H. Daniels Special Projects Manager, SSI James E. Davidson Project Manager, SSI Follow this and additional works at: https://commons.erau.edu/space-congress-proceedings Scholarly Commons Citation Daniels, Mark H. and Davidson, James E., "Conestoga Launch Vehicles" (1988). The Space Congress® Proceedings. 7. https://commons.erau.edu/space-congress-proceedings/proceedings-1988-25th/session-11/7 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]. CONESTOGA LAUNCH VEHICLES by Mark H. Daniels Special Projects Manager, SSI and James E. Davidson Project Manager, SSI launch into space. As such, it represents an Abstract important precedent for all other space launch companies. Several major applications for commercial and government markets have developed recently which In order to conduct the launch, the company will make use of small satellites. A launch solicited and received approvals from 18 different vehicle designed specifically for small satellites Federal agencies. Among these were the Air Force, brings many attendant benefits. Space Services the State Department, the Navy, and the Commerce Incorporated has developed the Conestoga family of Department. Commerce required SSI to obtain an launch vehicles to meet the needs of five major export license, due to the extra-territoriality of markets: low orbiting communication satellites, the vehicle's splashdown point. positioning satellites, earth sensing satellites, space manufacturing prototypes, and scientific Since that time, the company has organized a team experiments. -
The Annual Compendium of Commercial Space Transportation: 2017
Federal Aviation Administration The Annual Compendium of Commercial Space Transportation: 2017 January 2017 Annual Compendium of Commercial Space Transportation: 2017 i Contents About the FAA 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 51 United States Code, Subtitle V, Chapter 509 (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 encourage, facilitate, and promote commercial space launches and reentries. Additional information concerning commercial space transportation can be found on FAA AST’s website: http://www.faa.gov/go/ast Cover art: Phil Smith, The Tauri Group (2017) Publication produced for FAA AST by The Tauri Group under contract. 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 Annual Compendium of Commercial Space Transportation: 2017 GENERAL CONTENTS Executive Summary 1 Introduction 5 Launch Vehicles 9 Launch and Reentry Sites 21 Payloads 35 2016 Launch Events 39 2017 Annual Commercial Space Transportation Forecast 45 Space Transportation Law and Policy 83 Appendices 89 Orbital Launch Vehicle Fact Sheets 100 iii Contents DETAILED CONTENTS EXECUTIVE SUMMARY . -
Methodology for Identifying Key Parameters Affecting Reusability for Liquid Rocket Engines
Methodology for Identifying Key Parameters Affecting Reusability for Liquid Rocket Engines Presented by: Bruce Askins Rhonda Childress-Thompson Marshall Space Flight Center & Dr. Dale Thomas The University of Alabama in Huntsville Outline • Objective • Reusability Defined • Benefits of Reusability • Previous Research • Approach • Challenges • Available Data • Approach • Results • Next Steps • Summary Objective • To use statistical techniques to identify which parameters are tightly correlated with increasing the reusability of liquid rocket engine hardware. Reusability/Reusable Defined Ideally • “The ability to use a system for multiple missions without the need for replacement of systems or subsystems. Ideally, only replenishment of consumable commodities (propellant and gas products, for instance)occurs between missions.” (Jefferies, et al., 2015) For purposes of this research • Any space flight hardware that is not only designed to perform multiple flights, but actually accomplishes multiple flights. Benefits of Reusability • Forces inspections of returning hardware • Offers insight into how a part actually performs • Allows the development of databases for future development • Validates ground tests and analyses • Allows the expensive hardware to be used multiple times Previous Research – Identification of Features Conducive for Reuse Implementation 1. Reusability Requirement Implemented at the Conceptual Stage 2. Continuous Test Program 3. Minimize Post-Flight Inspections & Servicing to Enhance Turnaround Time 4. Easy Access 5. Longer Service Life 6. Minimize Impact of Recovery 7. Evolutionary vs. Revolutionary Changes MSFC Legacy of Propulsion Excellence (Evolutionary Changes) Saturn V J-2S 1970 1980 1990 2000 2010 2015 Challenges • Engine data difficult to locate • Limited data for reusable engines (i.e. Space Shuttle, Space Shuttle Main Engine (SSME) and Solid Rocket Booster (SRB) • Benefits of reusability have not been validated • Industry standards do not exist Engine Data Available Engine Time from No. -
High Delta V Nanosatellite Missions Using a Diverging Cusped Field Thruster
High Delta V Nanosatellite Missions using a Diverging Cusped Field Thruster IEPC-2009-047 Presented at the 31st International Electric Propulsion Conference, University of Michigan, Ann Arbor, Michigan, USA September 20{24, 2009 Ryan M. Daspit,∗ Christopher J. Han,y Paulo Lozano,z and David Millerx Massachusetts Institute of Technology, Cambridge, Massachusetts, 02139, USA The MIT satellite team is currently constructing the Cathode/Anode Satellite Technol- ogy for Orbital Repositioning (CASTOR) satellite as part of the 6th University Nanosatel- lite Program (UNP-6) Flight Competition. The objective of the CASTOR satellite is to verify the on-orbit performance of the Diverging Cusped Field Thruster (DCFT) developed at MIT. The DCFT is an electrostatic thruster based on a cusped magnetic field configu- ration to confine ionizing electrons through a combination of processes, including magnetic mirroring. The DCFT is currently undergoing integration and performance testing for use on the CASTOR satellite. A power processing unit (PPU) has been developed to optimally operate the DCFT during the satellite mission. Preliminary testing with the PPU has been successful and has allowed for the next stage in development of the PPU. Nomenclature T = thrust mo = total wet mass t = time a = vehicle acceleration Pa = anode power ηt = anode thrust efficiency c = exhaust velocity Isp = specific impulse g = acceleration due to gravity ∆V = velocity change ∗Graduate Student, Department of Aeronautics and Astronautics, [email protected]. yGraduate Student, Department of Aeronautics and Astronautics, [email protected]. zProfessor, Department of Aeronautics and Astronautics, [email protected]. xProfessor, Department of Aeronautics and Astronautics, [email protected]. 1 The 31st International Electric Propulsion Conference, University of Michigan, USA September 20{24, 2009 I. -
SPACE POLICY PRIMER Key Concepts, Issues, and Actors SECOND EDITION
JOHN PAUL BYRNE John Paul Byrne is an undergraduate at the United States Air Force Academy. He was recently an intern at The Aerospace Corporation, where he supported the work of the Center for Space Policy and Strategy. He is working as the president of the Air Force Academy’s International Applied Space Policy and Strategy cadet club, where they focus on developing space-minded officers for the Air and Space Forces. John will earn his bachelor’s degree in political science with a focus in international relations, and a minor in German in 2021. ROBIN DICKEY Robin Dickey is a space policy and strategy analyst at The Aerospace Corporation’s Center for Space Policy and Strategy, focusing on national security space. Her prior experience includes risk analysis, legislative affairs, and international development. She earned her bachelor’s and master’s degrees in international studies at Johns Hopkins University. MICHAEL P. GLEASON Dr. Michael P. Gleason is a national security senior project engineer in The Aerospace Corporation’s Center for Space Policy and Strategy and is a well-regarded author on space policy subjects, including international cooperation, space traffic management, national security, and deterrence. He has presented his research on critical space policy issues at conferences in Canada, Europe, Japan, and across the United States. A graduate of the U.S. Air Force Academy, Gleason served 29 years active in the Air Force space career field, including stints in spacecraft operations, on the Air Force Academy faculty, at the Pentagon, and at the Department of State. He holds a Ph.D. -
A Methodology for Preliminary Sizing of a Thermal and Energy Management System for a Hypersonic Vehicle
A methodology for preliminary sizing of a Thermal and Energy Management System for a hypersonic vehicle. Roberta Fusaro1, Davide Ferretto 1, Valeria Vercella1, Nicole Viola1, Victor Fernandez Villace2 and Johan Steelant2 Abstract This paper addresses a methodology to parametrically size thermal control subsystems for high-speed transportation systems. This methodology should be sufficiently general to be exploited for the derivation of Estimation Relationships (ERs) for geometrically sizing characteristics as well as mass, volume and power budgets both for active (turbopumps, turbines and compressors) and passive components (heat exchangers, tanks and pipes). Following this approach, ad-hoc semi-empirical models relating the geometrical sizing, mass, volume and power features of each component to operating conditions have been derived. As a specific case, a semi-empirical parametric model for turbopumps sizing is derived. In addition, the Thermal and Energy Management Subsystem (TEMS) for the LAPCAT MR2 vehicle is used as an example of a highly integrated multifunctional subsystem. The TEMS is based on the exploitation of liquid hydrogen boil-off in the cryogenic tanks generated by the heat load penetrating the aeroshell, all along the point-to-point hypersonic mission. Eventually, specific comments about the results will be provided together with suggestions for future improvements. Keywords: Thermal and Energy Management System, sizing models, turbopumps, LAPCAT MR2 1. Introduction The high operating temperature characterizing the hypersonic flight regime is a long-term issue. Vehicles able to reach hypersonic speed are currently considered for both aeronautical (e.g. high speed antipodal transportation systems) and space transportation purposes (e.g. reusable launcher stages and re-entry systems).