Monopropellant Selection Criteria--Hydrazine and Other Options
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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. -
From Biomimetic Chemistry to Bio‐Inspired Materials
www.advmat.de www.MaterialsViews.com REVIEW Progressive Macromolecular Self-Assembly: From Biomimetic Chemistry to Bio-Inspired Materials Yu Zhao , Fuji Sakai , Lu Su , Yijiang Liu , Kongchang Wei , Guosong Chen ,* and Ming Jiang * Dedicated to the 20th Anniversary of the Department of Macromolecular Science of Fudan University was highlighted, with the purpose of Macromolecular self-assembly (MSA) has been an active and fruitful research expanding the scope of chemistry.[ 1b ] At fi eld since the 1980s, especially in this new century, which is promoted by its early stage, biomimetic chemistry was the remarkable developments in controlled radical polymerization in polymer regarded as a branch of organic chemistry and the work concentrated on the level chemistry, etc. and driven by the demands in bio-related investigations and of molecules, formation and cleavage of applications. In this review, we try to summarize the trends and recent pro- covalent bonds following the way learning gress in MSA in relation to biomimetic chemistry and bio-inspired materials. from the living body. Artifi cial enzymes Our paper covers representative achievements in the fabrication of artifi cial aiming at fast and high selectivity have building blocks for life, cell-inspired biomimetic materials, and macro- been the key research subject in biomi- metic chemistry with emphasis on the molecular assemblies mimicking the functions of natural materials and their idea of molecular recognition, which is applications. It is true that the current status of the deliberately designed and also the center of supramolecular chem- obtained nano-objects based on MSA including a variety of micelles, multi- istry. Later, the principle and methodology compartment vesicles, and some hybrid and complex nano-objects is at their of biomimetic chemistry have gradually very fi rst stage to mimic nature, but signifi cant and encouraging progress expanded and penetrated to other sub-dis- has been made in achieving a certain similarity in morphologies or properties ciplines with great successes. -
Thermal Analysis of a Monopropellant Micropropulsion System for a Cubesat
THERMAL ANALYSIS OF A MONOPROPELLANT MICROPROPULSION SYSTEM FOR A CUBESAT A Thesis presented to the Faculty of California Polytechnic State University, San Luis Obispo In Partial Fulfillment of the Requirements for the Degree Master of Science Degree in Aerospace Engineering by Erin C. Stearns August 2013 © 2013 Erin C. Stearns ALL RIGHTS RESERVED ii COMMITTEE MEMBERSHIP TITLE: Thermal Analysis of a Monopropellant Micropropulsion System for a CubeSat AUTHOR: Erin C. Stearns DATE SUBMITTED: August 2013 COMMITTEE CHAIR: Dr. Kira Abercromby, Assistant Professor Cal Poly Aerospace Engineering Department COMMITTEE MEMBER: Dr. Jordi Puig-Suari, Professor Cal Poly Aerospace Engineering Department COMMITTEE MEMBER: Dr. Kim Shollenberger, Professor Cal Poly Mechanical Engineering Department COMMITTEE MEMBER: Chris Biddy, Vice President of Engineering Stellar Exploration, Inc. iii ABSTRACT Thermal Analysis of a Monopropellant Micropropulsion System for a CubeSat Erin C. Stearns Propulsive capabilities on a CubeSat are the next step in advancement in the Aerospace Industry. This is no longer a quest that is being sought by just university programs, but a challenge that is being taken on by all of the industry due to the low-cost missions that can be accomplished. At this time, all of the proposed micro-thruster systems still require some form of development or testing before being flight- ready. Stellar Exploration, Inc. is developing a monopropellant micropropulsion system designed specifically for CubeSat application. The addition of a thruster to a CubeSat would expand the possibilities of what CubeSat missions are capable of achieving. The development of these miniature systems comes with many challenges. One of the largest challenges that a hot thruster faces is the ability to complete burns for the specified mission without transferring excessive heat into the propulsion tank. -
Modular Impulsive Green Monopropellant Propulsion System (MIMPS-G): for Cubesats in LEO and to the Moon
aerospace Article Modular Impulsive Green Monopropellant Propulsion System (MIMPS-G): For CubeSats in LEO and to the Moon Ahmed E. S. Nosseir 1,2,* , Angelo Cervone 1,* and Angelo Pasini 2,* 1 Department of Space Engineering, Faculty of Aerospace Engineering, Delft University of Technology (TU Delft), 2629 Delft, The Netherlands 2 Sede di Ingegneria Aerospaziale, Dipt. di Ingegneria Civile e Industriale, Università di Pisa (UniPi), 56122 Pisa, Italy * Correspondence: [email protected] or [email protected] (A.E.S.N.); [email protected] (A.C.); [email protected] (A.P.) Abstract: Green propellants are currently considered as enabling technology that is revolutioniz- ing the development of high-performance space propulsion, especially for small-sized spacecraft. Modern space missions, either in LEO or interplanetary, require relatively high-thrust and impulsive capabilities to provide better control on the spacecraft, and to overcome the growing challenges, particularly related to overcrowded LEOs, and to modern space application orbital maneuver require- ments. Green monopropellants are gaining momentum in the design and development of small and modular liquid propulsion systems, especially for CubeSats, due to their favorable thermophysical properties and relatively high performance when compared to gaseous propellants, and perhaps simpler management when compared to bipropellants. Accordingly, a novel high-thrust modular impulsive green monopropellant propulsion system with a micro electric pump feed cycle is pro- posed. MIMPS-G500mN is designed to be capable of delivering 0.5 N thrust and offers theoretical total impulse I from 850 to 1350 N s per 1U and >3000 N s per 2U depending on the burnt mono- Citation: Nosseir, A.E.S.; Cervone, tot A.; Pasini, A. -
Low Cost Catalysts for Hydrazine Monopropellant Thrusters
See discussions, stats, and author profiles for this publication at: https://www.researchgate.net/publication/268483024 Low Cost Catalysts for Hydrazine Monopropellant Thrusters Conference Paper · August 2009 DOI: 10.2514/6.2009-5232 CITATIONS READS 2 53 5 authors, including: Jose Nivaldo Hinckel National Institute for Space Research, Brazil 27 PUBLICATIONS 50 CITATIONS SEE PROFILE All content following this page was uploaded by Jose Nivaldo Hinckel on 27 June 2018. The user has requested enhancement of the downloaded file. Low Cost Catalysts for Hydrazine Monopropellant Thrusters Jos´eNivaldo Hinckel∗ INPE/DMC, S˜aoJos´edos Campos, SP, 12201-970, Brazil Jos´eA. R. Jorge†Tur´ıbioG. Soares Neto†Marisa A. Zacharias†Jalusa A. L. Palandi‡ INPE/LCP, Cachoeira Paulista, SP, 12630-000, Brazil Hydrazine monopropellant engines are widely used in space missions; mainly in reaction control systems. The most widely used catalyst is the aluminum oxide supported iridium. It is also very expensive. The cost of the catalyst weights heavily, especially in the high thrust, short life thrusters used for roll control of launch vehicles. In this paper we present the results of testing of low cost catalysts in a 35 newton thruster. The catalysts tested were aluminum oxide supported ruthenium and a homogeneous catalyst, tungsten carbide. The test sequence included pre-heated and cold starts, pulsed and continuous firing modes, a range of feed pressure and life cycle that exceed the requirements of roll control systems. The start and energetic performance of the thruster matched very closely the performance of the iridium catalyst. Nomenclature ∗ C [m/s] Characteristic Velocity Pc [MPa] Chamber Pressure Cf Thrust Coefficient tig [ms] Ignition time F [N] Thrust tresp [ms] Response time ◦ Isp [m/s] Specific Impulse Tin [ C] Initial Temperature Pi [MPa] Injection Pressure I. -
A Monopropellant Milli-Newton Thruster System for Attitude Control of Nanosatellites
SSC02-VII-4 A Monopropellant Milli-Newton Thruster System for Attitude Control of Nanosatellites Donald Platt Micro Aerospace Solutions, Inc. 2280 Pineapple Avenue Melbourne, FL 32935 Phone: (321)253-0638 Email: [email protected] Abstract. Work is progressing on monopropellant thrusters for use as an attitude control system for nanosatellites (satellites whose mass is under 10 kilograms). The thrust range for these microthrusters is on the order of milli- newtons. Systems using both hydrazine and hydrogen peroxide are being developed which will offer higher performance than currently available thrusters for nanosatellites. Complete thruster systems using both propellant combinations have been built and are undergoing evaluation. Hot firings are currently being conducted. The microthruster system will be tested on an upcoming nanosatellite to be launched at the end of this year. These thrusters will offer an inexpensive, high performance option for attitude control for nanosatellites or fine pointing control for small satellites. Introduction an excellent choice for university and other school- based nanosatellite programs to have thruster attitude Microthrusters for nanosatellites are needed to provide control on-board. Hydrogen peroxide is non-toxic, can attitude control and pointing capability. Currently the be diluted with water and does not pose the health state-of-the-art in thruster systems for nanosatellites is problems of hydrazine. With careful system cleaning cold gas systems. These systems provide relatively low and choice of materials, hydrogen peroxide’s capability performance and are prone to leakage and their high to self-decompose can be controlled for a nanosatellite operating pressures require massive tank structures. mission duration of about one year. -
High-Performing Hydrogen Peroxide Hybrid Rocket with 3-D Printed and Extruded ABS Fuel
Aeronautics and Aerospace Open Access Journal Research Article Open Access High-performing hydrogen peroxide hybrid rocket with 3-D printed and extruded ABS fuel Abstract Volume 2 Issue 6 - 2018 Development of a high-performing hybrid rocket system that employs 90% hydrogen Stephen A Whitmore,1 Isaac W Armstrong,2 peroxide and 3-D printable thermoplastic materials is reported. Traditionally, high- 2 2 grade peroxide has been employed as a monopropellant using noble-metal catalysts Mark C Heiner, Christopher J Martinez 1Professor, Mechanical and Aerospace Engineering Department, to initiate thermal decomposition. Catbeds beds are expensive, heavy, and contribute Utah State University, USA no propulsive mass to the system. Catbeds exhibit limited operational lifetimes, and 2Graduate Research Assistant, Mechanical and Aerospace are often rendered inactive due to the high temperatures of thermal decomposition. Engineering Department, Utah State University, USA The presented alternative thermally-decomposes the injected peroxide stream using an electrostatic ignition system, where as a moderate electric field is introduced to the Correspondence: Stephen A Whitmore, Professor, Mechanical additively layered ABS fuel grain. Electrostatic arcs are induced within the 3-D printed and Aerospace Engineering Department, Utah State University, surface features, and produce sufficient pyrolyzed fuel vapor to induce spontaneous Logan Utah, 84322-4130, USA, Tel 435-797-2951 combustion when a flow of gaseous oxygen is introduced. Heat released is sufficient Email to thermally decompose the injected peroxide stream. The liberated heat and oxygen from decomposition drive full combustion along the length of the fuel grain. Gaseous Received: October 05, 2018 | Published: November 20, 2018 oxygen pre-leads as small as 250ms reliably initiate combustion. -
Development and Testing of a Green Monopropellant Ignition System I
Extended Abstract for: 49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit San Jose Convention Center , San Jose, CA, 15-17 July 2013 Development and Testing of a Green Monopropellant Ignition System Stephen A. Whitmore, Associate Professor Daniel P. Merkley, Graduate Research Assistant Shannon D. Eilers, Graduate Research Assistant Michael I. Judson, Graduate Research Assistant Mechanical and Aerospace Engineering (MAE) Department Utah State University, UMC 4130, 4130 Old Main Hill Logan Utah, 84322-4130 And Terry L. Taylor, Asst. Manager / Technology Transfer Lead NASA Marshall Spaceflight Center November 7, 2012 I. Introduction This paper will detail the development and testing of a “green” monopropellant booster ignition system. The proposed booster ignition technology eliminates the need for a pre-heated catalyst bed, a high wattage power source, toxic pyrophoric ignition fluids, or a bi-propellant spark ignitor. The design offers the simplicity of a monopropellant feed system features non-hazardous gaseous oxygen (GOX) as the working fluid. The approach is fundamentally different from all other “green propellant” solutions in the aerospace in the industry. Although the proposed system is more correctly a “hybrid” rocket technology, since only a single propellant feed path is required, it retains all the simple features of a monopropellant system. The technology is based on the principle of seeding an oxidizing flow with a small amount of hydrocarbon.1 The ignition is initiated electrostatically with a low-wattage inductive spark. Combustion gas byproducts from the hydrocarbon-seeding ignition process can exceed 2400 C and the high exhaust temperature ensures reliable main propellant ignition. The system design is described in detail in the Hydrocarbon-Seeded Ignition System Design subsection. -
An Optimized Hybrid Rocket Motor for the SARA Platform Reentry System
doi: 10.5028/jatm.2012.04032312 An Optimized Hybrid Rocket Motor for the SARA Platform Reentry System Pedro Luiz Kaled Da Cás, Cristiano Queiroz Vilanova, Manuel Nascimento Dias Barcelos Jr.*, Carlos Alberto Gurgel Veras Universidade de Brasília - Brasília/DF Brazil Abstract: This paper has described a system design process, based on a multidisciplinary optimization technique, of a conceptual optimized hybrid propellant rocket motor. The proposed engine could be a technological option for the reentry maneuvering system of the Brazilian recoverable satellite (SARA), which was designed by the Brazilian Institute of Aeronautics and Space. The resulting optimized propulsion system must be viewed as a proof of concept allowing comparison to more conventional technologies, i.e., liquid and solid motors. Design effort was conducted for hybrid SURSHOODQWVHQJLQHVEDVHGRQDOLTXHI\LQJIXHO VROLGSDUDI¿Q DQGWZRGLIIHUHQWR[LGL]HUV+2O2 KLJKWHVWSHUR[LGH and self-pressurizing N227KHPXOWLGLVFLSOLQDU\FRQ¿JXUDWLRQRSWLPL]DWLRQWHFKQLTXHZDVVXSSRUWHGRQJHRPHWULFDO operating parameters of the motor, rather than on performance, in order to facilitate subsequent design and fabrication. Results from the code presented a hybrid motor, which was considered a competitive alternative for the deboost engine when compared to the traditional chemical systems, solid and liquid bipropellant, and monopropellant. The estimated mass of the reentry system, for the cases addressed in this study, varied from 22 to 29 kg, which is lower than either liquid bipropellant or solid engines formerly proposed. Keywords:+\EULGURFNHWSURSXOVLRQ0XOWLSK\VLFVDQDO\VLV'HVLJQRSWLPL]DWLRQ INTRODUCTION The SARA satellite was conceived as a microgravity 300 km from the launch site. The system should be accelerated recoverable and reusable research platform by both Brazilian by a Brazilian VS-40 sounding rocket (Fig. -
IGNITION! an Informal History of Liquid Rocket Propellants by John D
IGNITION! U.S. Navy photo This is what a test firing should look like. Note the mach diamonds in the ex haust stream. U.S. Navy photo And this is what it may look like if something goes wrong. The same test cell, or its remains, is shown. IGNITION! An Informal History of Liquid Rocket Propellants by John D. Clark Those who cannot remember the past are condemned to repeat it. George Santayana RUTGERS UNIVERSITY PRESS IS New Brunswick, New Jersey Copyright © 1972 by Rutgers University, the State University of New Jersey Library of Congress Catalog Card Number: 72-185390 ISBN: 0-8135-0725-1 Manufactured in the United Suites of America by Quinn & Boden Company, Inc., Rithway, New Jersey This book is dedicated to my wife Inga, who heckled me into writing it with such wifely re marks as, "You talk a hell of a fine history. Now set yourself down in front of the typewriter — and write the damned thing!" In Re John D. Clark by Isaac Asimov I first met John in 1942 when I came to Philadelphia to live. Oh, I had known of him before. Back in 1937, he had published a pair of science fiction shorts, "Minus Planet" and "Space Blister," which had hit me right between the eyes. The first one, in particular, was the earliest science fiction story I know of which dealt with "anti-matter" in realistic fashion. Apparently, John was satisfied with that pair and didn't write any more s.f., kindly leaving room for lesser lights like myself. -
Delta Qualification Test of Aerojet Hydrazine
45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit AIAA 2009-5481 2 - 5 August 2009, Denver, Colorado Delta-Qualification Test of Aerojet 6 and 9 lbf MR-106 Monopropellant Hydrazine Thrusters for Use on the Atlas Centaur Upper Stage During the Lunar Reconnaissance Orbiter (LRO) and Lunar Crater Observation and Sensing Satellite (LCROSS) Missions Jeffrey P. Honse1 Aerojet-General Corporation, Redmond, WA, 98052 Carl T. Bangasser2 United Launch Alliance, Littleton, CO, 80127 Michael J. Wilson3 Aerojet-General Corporation, Redmond, WA, 98052 This paper discusses a Delta-Qualification test of Aerojet’s 6 and 9 lbf monopropellant hydrazine MR-106 thrusters for use on the Atlas Centaur upper stage while operating in an atypical mode and for an extended period of time. This qualification testing was performed in support of the Lunar Reconnaissance Orbiter (LRO) and Lunar Crater Observation and Sensing Satellite (LCROSS) missions. The primary objective of the LCROSS mission is to determine the presence or absence of water ice in a permanently shadowed crater near a lunar polar region. The accomplishment of this objective requires that the Atlas V rocket’s Centaur upper stage perform a LCROSS orbit insertion as well as a fly-by of the moon before the Centaur upper stage crashes into a lunar crater to create a debris plume. The LCROSS satellite will pass through the debris to collect and relay plume constituent data back to Earth. Prior to the LCROSS separation from the Centaur upper stage, the Centaur pneumatic pressurization system will transition from regulated to blow-down mode, which requires that the thrusters operate at a lower propellant feed pressure than had previously been qualified. -
A Survey of Automatic Control Methods for Liquid-Propellant Rocket Engines
A survey of automatic control methods for liquid-propellant rocket engines Sergio Pérez-Roca, Julien Marzat, Hélène Piet-Lahanier, Nicolas Langlois, Francois Farago, Marco Galeotta, Serge Le Gonidec To cite this version: Sergio Pérez-Roca, Julien Marzat, Hélène Piet-Lahanier, Nicolas Langlois, Francois Farago, et al.. A survey of automatic control methods for liquid-propellant rocket engines. Progress in Aerospace Sciences, Elsevier, 2019, pp.1-22. 10.1016/j.paerosci.2019.03.002. hal-02097829 HAL Id: hal-02097829 https://hal.archives-ouvertes.fr/hal-02097829 Submitted on 12 Apr 2019 HAL is a multi-disciplinary open access L’archive ouverte pluridisciplinaire HAL, est archive for the deposit and dissemination of sci- destinée au dépôt et à la diffusion de documents entific research documents, whether they are pub- scientifiques de niveau recherche, publiés ou non, lished or not. The documents may come from émanant des établissements d’enseignement et de teaching and research institutions in France or recherche français ou étrangers, des laboratoires abroad, or from public or private research centers. publics ou privés. A survey of automatic control methods for liquid-propellant rocket engines Sergio Perez-Roca´ a,c,∗, Julien Marzata,Hel´ ene` Piet-Lahaniera, Nicolas Langloisb, Franc¸ois Faragoc, Marco Galeottac, Serge Le Gonidecd aDTIS, ONERA, Universit´eParis-Saclay, Chemin de la Huniere, 91123 Palaiseau, France bNormandie Universit´e,UNIROUEN, ESIGELEC, IRSEEM, Rouen, France cCNES - Direction des Lanceurs, 52 Rue Jacques Hillairet, 75612 Paris, France dArianeGroup SAS, Forˆetde Vernon, 27208 Vernon, France Abstract The main purpose of this survey paper is to review the field of convergence between the liquid-propellant rocket- propulsion and automatic-control disciplines.