Monopropellant Selection Criteria--Hydrazine and Other Options

Total Page:16

File Type:pdf, Size:1020Kb

Monopropellant Selection Criteria--Hydrazine and Other Options A99931 331 th AIANASME/SAElASEE Join Propulsion Conferenc J 111 For permission to copy or republish, contact American institute of Aeronautics and Astronautics 1801 Alexander Bell Drive, Suite 500 Reston, Virginia 20191-4344 Olwen Morgan ([email protected]) Dennis Meinhardt ([email protected]) PRIMEX Aerospace Company Redmond, Washington Abstract: Monopropellant propulsion systems offer many advantages for mid-size spacecraft, ha&ding simplicity of operation, high reliability, and Ilow cost. Much effort recently has 0een centered on developing lower toxicity propellants and electric propulsion altesnatives, and many of these options show significant promise. This paper will show that hydrazine monopropellant propulsion systems continue to be an excellent choice for many spacecraft applications, and that on-going work to simplify designs and fueling carts bas reduced costs and increased simplicity. We will also explore trade studies where some of these other propulsive options are shown to be more appropriate. Introduction REA Rocket Engine Assembly REM Rocket Engine Module Since their first flight application in 1966 on Martin TLV ThresholdLimit Value Marietta’s Titan I launch vehicle’s Transtage, UDMH Unsymmetrical Dimethyl Hydrazine monopropellant hydrazine rocket engines with Introduction/Historv spontaneou? catalyst have often been the propulsion of choice. Hydrazine as a propellant offers The advantages of hydrazine as a monopropellant was substantially improved specific impulse over cold recognized early on. In 1949, the Jet Propulsion gas, and hydrazine systems require half as many Laboratory funded both engine and catalyst development, tanks, propellant lines, and valves as a comparable and has been credited with the start of the industry’. bi-propellant system. Versatile and dependable, a Catalytic hydrazine thrusters and systems have evolved monopropellant thruster will operate in steady state, sinca their first space flight in 1966, becoming less on-pulse, and off-pulse modes. mission specific and more commercially oriented. Over Nomenclature time, PRIMEX Aerospace Company (formerly Rocket Research Company and Olin Aerospace Company) has ACGIH American Conferenceof GovernmentalIndustrial designed, built, and tested monopropellant hydrazine Hygienists thrusters for many purposes including some key ACS Attitude Control System interplanetary missions. In the year 2000 we expect to CSD Chemical SystemsDivision, United Technologies ship our lO,OOO* thruster. We are particularly proud of DFA Design for Asstmbly our contributions to the following interplanetary missions: DFM Design for Manufacturing EHT ElectrothermalHydrazine Thruster Viking 1 and Viking 2’. Landed on Mars in 1975. F Thrust, N Actively guided descent using three 2700N GE0 Geosynchr&ous or GeostationaryOrbit throttleable engines for a soft landing, as well as GPS Global Positioning System HAN Hydroxyl Ammonium Nitrate attitude control and delta-V for the cruise stage. HPB Hydrazine PropellantBlend Voyager 1 and Voyager 2. Launched in 1977, these IDLH Immediately Dangerousto Life or Health satellites are still operational today as they approach ISP Specific Impulse, set LEO Low Earth Orbit the heliopause. The 20N and 445N engines have LTHG Low TemperatureHAN Glycine long since been jettisoned, but the 1N REAs are still MIT Minimum Impulse Thruster functioning nominally. MMH Monomethyl Hydrazine NIOSH National Institute for Occupational Safety & Magellan. Launched in 1989 with residual Viking Health 20N REAs, Voyager 1N REAs, and new MR-104A NVR Non-Volatile Residue 445N REAs mounted on four similar but non- OAM Orbit Adjust Module identical Rocket Engine Modules, this satellite OSHA OccupationalSafety and Health Administration mapped the surface of Venus for four years. Fuel and PAC PRIMEX AerospaceCompany valve temperatures were substantially hotter than PEL PermissibleExposure Limit expected; operation at 140 “C was validated in Pf Feed or Inlet Pressure,Bar support of this mission3. PPT PulsedPlasma Thruster Copyright01999 by theAmerican Instituteof Aeronauticsand Astronautics. All rights reserved. American Institute of Aeronautics and Astronautics 99-2595 0 Mars Pathfinder. Mars landing July, 1997. MR- the middle, catalytic monopropellants offer low cost, 11 IC 4.4N REAs provided attitude control flexibility, and a wide thrust range. Figure 1 shows during the cruise stage and to position the theoretical performance for a range of monopropellant satellite to deploy the rover Soujourner. choices. Table 1 shows some physical properties. @ Mars Climate Orbiter and Mars Polar Lander. Hvdrazine Mars mapping and landing expected in the fall of Hydrazine propulsion systems offer the greatest heritage 1999. Cruise stage REMs for both satellites and of the candidates with a wide array of choices in qualified 7-lContent 1600 I I , I / Low Temp / HAN/Glycine __ Blend I I I I --- . 190 200 210 220 230 240 250 260 270 280 290 Vacuum Specific Impulse, Isp (set) dual 300N REMs on the lander for the first thrusters, as well as tanks, latch and pyro valves, service actively guided descent since Viking landed on valves, and all the other items needed to assemble a Mars. propulsion system. Their reliability is high, its performance is moderate, and its cost relatively low. Its While hydrazine has a strong heritage, other long-term storage stability is excellent. propellants and blends offer potential for improved performance and reduced toxicity. Some of these Compatible dual mode thrusters exist for missions choices include low temperature HAN-based requiring large delta-V, and electrothermal hydrazine propellants with performance approaching that of thrusters and arcjets offer high performance compatible hydrazine, high temperature HAN-based propellants choices for such applications as geostationary satellite with performance approaching that of a bi-propellant station-keeping. One of the issues associated with system, hydrogen peroxide, and hydrazine blends. hydrazine is its toxicity. While novel fueling approaches can mitigate some of the toxicity concerns, other Pronellant Choices propellants show promise of reduced toxicity and For extremely small satellites (10 kg class), attendant reduced fueling costs. propulsion is usually not an option. For slightly Low Combustion Temperature Hvdroxvl Ammonium larger satellites (100 kg class) with low propulsive Nitrate (HAN) Blends requirements, cold gas has typically been used. For launch vehicles, only solid motors and/or liquid bi- Laboratory thruster testing with “low combustion propellant stages are adequate to escape earth’s temperature” blends of HAN/Glycine (refer to Figure 1) gravity. Electric propulsion systems offer high has demonstrated proof of concept for this new family of specific impulse, but carry both the cost and weight environmentally friendly monopropellants. These HAN of the electronics and power conditioning hardware blends have a higher density and lower melting point than with them. But for a broad band of applications in hydrazine, and because there is no toxic vapor pressure, Copyright01999 by theAmerican 3 Instituteof Aeronauticsand Astronautics. All rights reserved. American Institute of Aeronautics and Astronautics 99-2595 ground support operations are simplified. Additionally,-with these HAN-based blends, there are no identified carcinogenic issues. Table l-Physical Properties of Some Typical Monopropellant Fuels Characteristic Hydrogen Peroxide, 90% Melting -11.5 Point, “C Boiling Point, 113.5 Not 141.7 T Measured Specific 1.0 1.42 1.4 Gravity Figure 2-HAN Thruster Firing at Sea Level Explosion 232 Not 149 Temp, “C4 available Hiah Performing Hvdroxvl Ammonium Nitrate (HAN) Long-Term Excellent if Slowly Slowly Blends Storage kept decom- decom- High temperature HAN-based monopropellants also show Stability blanketed poses to poses to promise. Theoretically, performance will approach that with inert form form of conventional bi-propellant systems, but without the gas acidic bi- water and need for dual tanks, dual valves, dual propellant lines and products oxygen other duplicate system hardware. The biggest challenge Toxicity- 0.01 Vapor 1.0 offered by the high temperature blends is their ACGIH TLV, pressure decomposition temperatures, with gas temperatures ppm ranging near 2200 “C. Material choices and ignition Toxicity- G-+%2- 1.0 methods for monopropellants at these temperatures are OSHA PEL, 1 pressure limited. Recent ignition testing with a blend of HAN, ppm methanol, and water shows promise for monopropellants Toxicity- “” 75 with specific impulses of 270 or greater. NIOSH IDLH, ppm Hvdroaen Peroxide Other Strong Hydrogen peroxide has been proposed for use in small Precautions oxidizer, satellites instead of nitrogen propulsion7. Laboratory corrosive testing, using bench-distilled hydrogen peroxide resulted Figure 2 shows a flight concept HAN thruster firing in an impressive display of thrust with few attendant risks with the “low temperature” HAN/glycine (LTHG) to the by-standers. But lack of long term stability of propellantI blend. This thruster was made from the hydrogen peroxide renders it impractical for most satellite same materials of construction used in a hydrazine applications. However, hydrogen peroxide would appear thruster. Demonstration tests, like that shown in to have significant applications for monopropellant Figure 3, have shown clean, reliable, stable attitude control thrusters when coupled with a bi- decomposition/combustion of the propellant in a propellant system
Recommended publications
  • 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.
    [Show full text]
  • 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.
    [Show full text]
  • 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.
    [Show full text]
  • 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.
    [Show full text]
  • 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.
    [Show full text]
  • 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.
    [Show full text]
  • 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.
    [Show full text]
  • 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.
    [Show full text]
  • 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.
    [Show full text]
  • 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.
    [Show full text]
  • 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.
    [Show full text]
  • 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.
    [Show full text]