IGNITION! an Informal History of Liquid Rocket Propellants by John D
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Transport of Dangerous Goods
ST/SG/AC.10/1/Rev.16 (Vol.I) Recommendations on the TRANSPORT OF DANGEROUS GOODS Model Regulations Volume I Sixteenth revised edition UNITED NATIONS New York and Geneva, 2009 NOTE The designations employed and the presentation of the material in this publication do not imply the expression of any opinion whatsoever on the part of the Secretariat of the United Nations concerning the legal status of any country, territory, city or area, or of its authorities, or concerning the delimitation of its frontiers or boundaries. ST/SG/AC.10/1/Rev.16 (Vol.I) Copyright © United Nations, 2009 All rights reserved. No part of this publication may, for sales purposes, be reproduced, stored in a retrieval system or transmitted in any form or by any means, electronic, electrostatic, magnetic tape, mechanical, photocopying or otherwise, without prior permission in writing from the United Nations. UNITED NATIONS Sales No. E.09.VIII.2 ISBN 978-92-1-139136-7 (complete set of two volumes) ISSN 1014-5753 Volumes I and II not to be sold separately FOREWORD The Recommendations on the Transport of Dangerous Goods are addressed to governments and to the international organizations concerned with safety in the transport of dangerous goods. The first version, prepared by the United Nations Economic and Social Council's Committee of Experts on the Transport of Dangerous Goods, was published in 1956 (ST/ECA/43-E/CN.2/170). In response to developments in technology and the changing needs of users, they have been regularly amended and updated at succeeding sessions of the Committee of Experts pursuant to Resolution 645 G (XXIII) of 26 April 1957 of the Economic and Social Council and subsequent resolutions. -
Propulsion Options for the Global Precipitation Measurement Core Satellite
PROPULSION OPTIONS FOR THE GLOBAL PRECIPITATION MEASUREMENT CORE SATELLITE Eric H. Cardiff*, Gary T. Davist, and David C. FoltaS NASA Goddard Space Flight Center Greenbelt, MD 2077 1 Abstract This study was conducted to evaluate several propulsion system options for the Global Precipitation Measurement (GPM) core satellite. Orbital simulations showed clear benefits for the scientific data to be obtained at a constant orbital altitude rather than with a decayheboost approach. An orbital analysis estimated the drag force on the satellite will be 1 to 12 mN during the five-year mission. Four electric propulsion systems were identified that are able to compensate for these drag forces and maintain a circular orbit. The four systems were the UK-lO/TS and the NASA 8 cm ion engines, and the ESA RMT and RITlO EVO radio-frequency ion engines. The mass, cost, and power requirements were examined for these four systems. The systems were also evaluated for the transfer time from the initial orbit of 400 x 650 km altitude orbit to a circular 400 km orbit. The transfer times were excessive, and as a consequence a “dual” system concept (with a hydrazine monopropellant system for the orbit transfer and electric propulsion for drag compensation) was examined. Clear mass benefits were obtained with the “dual” system, but cost remains an issue because of the larger power system required for the electric propulsion system. An electrodynamic tether was also evaluated in this trade study. Introduction The propulsion system is required to perform two The Global Precipitation Measurement (GPM) primary functions. The first is to transfer the mission will be launched in late 2008 to measure satellite from the launch insertion orbit to the final the amount and type of precipitation around the circular orbit. -
Monopropellant System
~™ mil ii ii nun mi iiiii iiiii (19) J European Patent Office Office europeen des brevets (11) EP 0 950 648 A1 (12) EUROPEAN PATENT APPLICATION (43) Date of publication:ation: (51) Int. CI.6: C06D 5/08 20.10.1999 Bulletin 1999/42 (21) Application number: 98201190.0 (22) Date of filing: 15.04.1998 (84) Designated Contracting States: (72) Inventors: AT BE CH CY DE DK ES Fl FR GB GR IE IT LI LU • van den Berg, Ronald Peter MC NL PT SE 2291 KJ Wateringen (NL) Designated Extension States: • Mul, Johannes Maria AL LT LV MK RO SI 2013 AE Haarlem (NL) • Elands, Petrus Johannes Maria (71) Applicant: 2804 LK Gouda (NL) NEDERLANDSE ORGANISATIE VOOR TOEGEPAST-NATUURWETENSCHAPPELIJK (74) Representative: ONDERZOEK Smulders, Theodorus A.H.J., Ir. et al TNO Vereenigde Octrooibureaux 2628 VK Delft (NL) Nieuwe Parklaan 97 2587 BN 's-Gravenhage (NL) (54) Monopropellant system (57) The invention is directed to a monopropellant composition for propulsion and/or gas generation, com- prising a solution of hydrazinium nitroformate (HNF) and/or ammonium dinitramide (ADN) in water and/or an alkanol. < CO CO o LO o Q_ LU Printed by Xerox (UK) Business Services 2.16.7/3.6 EP 0 950 648 A1 Description [0001] The present invention is in the area of monopropellant composition systems, for instance for spacecraft pro- pulsion, in emergency systems for jet fighters or in emergency gasgeneration systems for submarines. 5 [0002] Spacecraft propulsion is defined as that needed for the orientation (attitude control) and positioning (orbit con- trol including de-orbiting) of spacecraft after delivery into the required orbit by the launch vehicle. -
1 the Merits of Cold Gas Micropropulsion in State-Of
IAC-02-S.2.07 THE MERITS OF COLD GAS MICROPROPULSION IN STATE-OF-THE-ART SPACE MISSIONS Hugo Nguyen, Johan Köhler and Lars Stenmark The Ångström Space Technology Centre, Uppsala University, Box 534, SE-751 21 Uppsala, Sweden. [email protected] Fax: +46 18 471 3572 Abstract: Cold gas micropropulsion is a sound 1. INTRODUCTION choice for space missions that require extreme For Attitude and Orbit Control System (AOCS) stabilisation, pointing precision or contamination- requirements on extreme stabilisation, pointing free operation. The use of forces in the micronewton precision, contamination-free operation is the range for spacecraft operations has been identified as most important for many missions. Examples a mission-critical item in several demanding space include DARWIN, LISA, SIM, NGST, and those systems currently under development. which have optical or other equipments pointing Cold gas micropropulsion systems share merits with exactly to a certain object or in a certain direction. traditional cold gas systems in being simple in Other obviously desirable properties include design, clean, safe, and robust. They do not generate design simplicity, cleanliness, safety, robustness, net charge to the spacecraft, and typically operate on low-power operation, no net charge generation to low-power. The minute size is suitable not only for the craft, together with low mass, and a wide inclusion on high-performance nanosatellites but dynamic range. Cold gas micropropulsion has also for high-demanding future space missions of those merits and in the present paper, larger sizes. technological solutions will be treated By using differently sized nozzles in parallel emphatically, at the same time the mentioned systems the dynamic range of a cold gas merits will be brought out clearly. -
Ni33nh3+3Nhi
Pure & Appi. Chem., Vol. 49, pp.67—73. Pergamon Press, 1977. Printed in Great Britain. NON-AQJEOUS SOLVENTS FOR PREPARATION AND REACTIONS OF NITROGEN HALOGEN COMPOUNDS Jochen Jander Department of Chemistry, University of Heidelberg, D 69 Heidelberg, Germany Abstract -Theimportance of non—aqueous solvents for the chemistry of haloamines is shown in more recent reaction examples. The solvents must be low-melting because of the general temperature sensitivity of the haloamines. They may take part in the reaction (formation of CH NI •CH NH (CH )2NI, NI-,.5 NH-, and NH0I.NH-)ormay e ner (ormation of I .quinuiilidin, 2 NI •1 trithylenediamine, [I(qunuclidine),] salts pure NBr, and compounds of the type R1R2NC103 with R1 and R2 =orgnicgroup or hydrogen). INTRODUCTION Non-aqueous solvents play an important role in preparation and reactions of nitrogen halogen compounds. Due to the fact, that all haloamines are derivatives of ammonia or amines, liquid ammonia or liquid organic amines are used as solvents very often. Liquid ammonia and the lower organic amines reveal, in addition, the advantage of low melting points (liquid ammonia -78, liquid monomethylamine -93.5, liquid dimethylamine -92, liquid tn-. methylamine -12k°C); these meet the general temperature sensitivity of the nitrogen halogen compounds, especially of the pure .lorganic ones. Ammonia and amines are very seldom inert solvents; they mostly take part in the reaction planned for synthesis or conversion of the haloamine. In case a reaction of the solvent is to be avoided, one has to look for a low melting inert solvent, for example methylene chloride (m.p. -
A "Green Cold-Gas" Propulsion System for Cubesats
A "Green Cold-Gas" Propulsion System for Cubesats John Lee1, Adam Huang2 1 Department of Mechanical Engineering, University of Arkansas, [email protected] 2 Department of Mechanical Engineering, University of Arkansas, [email protected] Background – Cubesat Maneuvering Propellant Characterization Thrust Generated • Current Cubesat maneuvering techniques are mainly passive, with little to no • Vaporizing a propellant via nanochannels to vacuum was • Experiments were conducted in a vacuum HD Lifecam ability to change orbits. studied as a means of propulsion for small satellites. chamber that maintained a milliTorr • Specific impulse (Isp) - measure of propellant efficiency • Basic attitude control primarily using Earth’s magnetic field or gravity. Black Out Bell Jar Curtain pressure to simulate space conditions 훾+1 훾푅푇 ∗ ∗ • Very low torque, long time-constant stability (hours), and low accuracy. 푐 훾 2 2 훾−1 푐 = 훾+1 • Various trials were conducted to 퐼푠푝 = where 2 2훾−1 푔 훾 − 1 훾 + 1 훾 • Near-term flights with momentum wheels. Need momentum dumping. 0 훾 + 1 determine properties of vapor phase Light Source • Available technologies aqueous propylene glycol by varying: Test Apparatus • Using Aqueous PG Isp and nanochannel array dimensions • Magnets, Magnetorquers, Momentum wheels (needs dump), Conventional 250μm • Temperature – controlled with a bang- Mass Scale the theoretical thrust was calculated thrusters (solid, fluid thrusters), Gravity gradient, Drag, Electric Thrusters bang thermostat • Thrust is tuned by adjusted the nanochannel dimensions -
Design, Analysis, and Simulation of Rocket Propulsion System By
Design, Analysis, and Simulation of Rocket Propulsion System By Sarah L. Kulhanek Submitted to the graduate degree program in Aerospace Engineering and the Graduate Faculty of the University of Kansas in partial fulfillment of the requirements for the degree of Masters of Science. ________________________________ Chairperson, Dr. Ray Taghavi ________________________________ Committee member, Dr. Saeed Farokhi ________________________________ Committee member, Dr. Shahriar Keshmiri Date Defended: 6/6/2012 The Thesis Committee for Sarah L. Kulhanek certifies that this is the approved version of the following thesis: Design, Analysis, and Simulation of Rocket Propulsion System __________________________________ Chairperson, Dr. Ray Taghavi, Date approved: 6/6/2012 ii Abstract This document details the functionality of a software program used to streamline a rocket propulsion system design, analysis and simulation effort. The program aids in unifying the nozzle, chamber and injector portions of a rocket propulsion system design effort quickly and efficiently using a streamlined graphical user interface (GUI). The program also allows for the selection of common nozzle profiles including 80% rao, conical, a user selected percentage bell, and a minimum length nozzle (MLN) using method of characteristics (MOC). Chamber dimensions, propellant selections, and injector selection between doublet or triplet allow for further refinement of the desired rocket system design. The program takes the available selections and specifications made by the user and outputs key design parameters calculated from the input variables. A 2-D graphical representation of the nozzle and/or chamber is plotted and coordinates of the plotted line are displayed. Additional design calculations are determined and displayed within the program such as specific impulse, exhaust velocity, propellant weight flow, fundamental instability frequencies, etc. -
Cave-73-02-Fullr.Pdf
EDITORIAL Production Changes for Future Publication of the Journal of Cave and Karst Studies SCOTT ENGEL Production Editor The Journal of Cave and Karst Studies has experienced December 2011 issue, printed copies of the Journal will be budget shortfalls for the last several years for a multitude automatically distributed to paid subscribers, institutions, of reasons that include, but are not limited to, increased and only those NSS members with active Life and cost of paper, increased costs of shipping through the Sustaining level memberships. The remainder of the NSS United State Postal Service, increased submissions, and membership will be able to view the Journal electronically stagnant funding from the National Speleological Society online but will not automatically receive a printed copy. Full (NSS). The cost to produce the Journal has increased 5 to content of each issue of the Journal will be available for 20 percent per year for the last five years, yet the budget for viewing and downloading in PDF format at no cost from the the Journal has remained unchanged. To offset rising costs, Journal website www.caves.org/pub/journal. the Journal has implemented numerous changes over recent Anyone wishing to receive a printed copy of the Journal years to streamline the production and printing process. will be able to subscribe for an additional cost separate However, the increasing production costs, combined with from normal NSS dues. The cost and subscription process the increasing rate of good-quality submissions, has were still being determined at the time of this printing. resulted in the number of accepted manuscripts by the Once determined, the subscription information will be Journal growing faster than the acquisition of funding to posted on the Journal website. -
Trade Studies Towards an Australian Indigenous Space Launch System
TRADE STUDIES TOWARDS AN AUSTRALIAN INDIGENOUS SPACE LAUNCH SYSTEM A thesis submitted for the degree of Master of Engineering by Gordon P. Briggs B.Sc. (Hons), M.Sc. (Astron) School of Engineering and Information Technology, University College, University of New South Wales, Australian Defence Force Academy January 2010 Abstract During the project Apollo moon landings of the mid 1970s the United States of America was the pre-eminent space faring nation followed closely by only the USSR. Since that time many other nations have realised the potential of spaceflight not only for immediate financial gain in areas such as communications and earth observation but also in the strategic areas of scientific discovery, industrial development and national prestige. Australia on the other hand has resolutely refused to participate by instituting its own space program. Successive Australian governments have preferred to obtain any required space hardware or services by purchasing off-the-shelf from foreign suppliers. This policy or attitude is a matter of frustration to those sections of the Australian technical community who believe that the nation should be participating in space technology. In particular the provision of an indigenous launch vehicle that would guarantee the nation independent access to the space frontier. It would therefore appear that any launch vehicle development in Australia will be left to non- government organisations to at least define the requirements for such a vehicle and to initiate development of long-lead items for such a project. It is therefore the aim of this thesis to attempt to define some of the requirements for a nascent Australian indigenous launch vehicle system. -
Chemical Chemical Hazard and Compatibility Information
Chemical Chemical Hazard and Compatibility Information Acetic Acid HAZARDS & STORAGE: Corrosive and combustible liquid. Serious health hazard. Reacts with oxidizing and alkali materials. Keep above freezing point (62 degrees F) to avoid rupture of carboys and glass containers.. INCOMPATIBILITIES: 2-amino-ethanol, Acetaldehyde, Acetic anhydride, Acids, Alcohol, Amines, 2-Amino-ethanol, Ammonia, Ammonium nitrate, 5-Azidotetrazole, Bases, Bromine pentafluoride, Caustics (strong), Chlorosulfonic acid, Chromic Acid, Chromium trioxide, Chlorine trifluoride, Ethylene imine, Ethylene glycol, Ethylene diamine, Hydrogen cyanide, Hydrogen peroxide, Hydrogen sulfide, Hydroxyl compounds, Ketones, Nitric Acid, Oleum, Oxidizers (strong), P(OCN)3, Perchloric acid, Permanganates, Peroxides, Phenols, Phosphorus isocyanate, Phosphorus trichloride, Potassium hydroxide, Potassium permanganate, Potassium-tert-butoxide, Sodium hydroxide, Sodium peroxide, Sulfuric acid, n-Xylene. Acetone HAZARDS & STORAGE: Store in a cool, dry, well ventilated place. INCOMPATIBILITIES: Acids, Bromine trifluoride, Bromine, Bromoform, Carbon, Chloroform, Chromium oxide, Chromium trioxide, Chromyl chloride, Dioxygen difluoride, Fluorine oxide, Hydrogen peroxide, 2-Methyl-1,2-butadiene, NaOBr, Nitric acid, Nitrosyl chloride, Nitrosyl perchlorate, Nitryl perchlorate, NOCl, Oxidizing materials, Permonosulfuric acid, Peroxomonosulfuric acid, Potassium-tert-butoxide, Sulfur dichloride, Sulfuric acid, thio-Diglycol, Thiotrithiazyl perchlorate, Trichloromelamine, 2,4,6-Trichloro-1,3,5-triazine -
United States Rocket Research and Development During World War II
United States Rocket Research and Development During World War II Unidentified U.S. Navy LSM(R) (Landing Ship Medium (Rocket)) launching barrage rockets during a drill late in the Second World War. Image courtesy of the U.S. National Archives and Records Administration. and jet-assisted takeoff (JATO) units for piston-pow- Over the course of the Second World War, rockets ered attack fighters and bombers. Wartime American evolved from scientific and technical curiosities into rocket research evolved along a number of similar and practical weapons with specific battlefield applications. overlapping research trajectories. Both the U.S. Navy The Allied and Axis powers both pursued rocket re- and Army (which included the Army Air Forces) devel- search and development programs during the war. Brit- oped rockets for ground bombardment purposes. The ish and American rocket scientists and engineers (and services also fielded aerial rockets for use by attack their Japanese adversaries) mainly focused their efforts aircraft. The Navy worked on rocket-powered bombs on tactical applications using solid-propellant rockets, for antisubmarine warfare, while the Army developed while the Germans pursued a variety of strategic and the handheld bazooka antitank rocket system. Lastly, tactical development programs primarily centered on both the Army and Navy conducted research into JATO liquid-propellant rockets. German Army researchers units for use with bombers and seaplanes. Throughout led by Wernher von Braun spent much of the war de- the war, however, limited coordination between the veloping the A-4 (more popularly known as the V-2), armed services and federal wartime planning bodies a sophisticated long-range, liquid-fueled rocket that hampered American rocket development efforts and led was employed to bombard London and Rotterdam late to duplicated research and competition amongst pro- in the war. -
Progress on Colloid Micro-Thruster Research and Flight Testing
PROGRESS ON COLLOID MICRO-THRUSTER RESEARCH AND FLIGHT TESTING F REDDY M ATHIAS P RANAJAYA PROF. MARK CAPPELLI, ADVISOR Space Systems Development Laboratory Department of Aeronautics and Astronautics, Stanford University Plasma Dynamic Laboratory Department of Mechanical Engineering, Stanford University ABSTRACT - Electric propulsion devices are know for their high specific impulses, which 1. INTRODUCTION makes them very appealing to space mission requiring ultimate utilization of the limited Space mission designers have long been resources on board the spacecraft. relying on electric propulsion because of its characteristic of high specific impulse, Advances in microelectronics have allowed allowing higher total delta-V, which makes it increased functionality while reducing the suitable for long space missions or for sizes of the spacecraft. However this has not spacecraft with limited fuel storage capacity. been entirely true for propulsion units. Colloid Despite of this advantage, the high power Micro-Thruster held the promise for micro- consumption and massive power supply and nanosatellite propulsion application requirements have made electric propulsion because of their size, low cost, integrated option unattractive for 100kg-class package, high efficiency, and custom microsatellites and 10-kg class nanosatellites. configurability to fit a specific application. Colloid Micro-Thruster technology is expected This paper outlines the renewed research to satisfy the need for high-performance efforts on Colloid Thruster, in an attempt to propulsion units for small spacecraft. Recent understand the underlying principles and to study by Mueller, 1997 [1] concluded that “… uncover its true potential. A one-nozzle and a of all micro-electric primary propulsion 100-nozzle prototype have been built and options reviewed, Colloid Thrusters are quite tested.