Monopropellant Hydrazine 700 Lbf Throttling Terminal Descent Engine
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Oxygen Exosphere of Mars: Evidence from Pickup Ions Measured By
Oxygen Exosphere of Mars: Evidence from Pickup Ions Measured by MAVEN By Ali Rahmati Submitted to the graduate degree program in the Department of Physics and Astronomy, and the Graduate Faculty of the University of Kansas in partial fulfillment of the requirements for the degree of Doctor of Philosophy. ________________________________ Professor Thomas E. Cravens, Chair ________________________________ Professor Philip S. Baringer ________________________________ Professor David Braaten ________________________________ Professor Mikhail V. Medvedev ________________________________ Professor Stephen J. Sanders Date Defended: 22 January 2016 The Dissertation Committee for Ali Rahmati certifies that this is the approved version of the following dissertation: Oxygen Exosphere of Mars: Evidence from Pickup Ions Measured by MAVEN ________________________________ Professor Thomas E. Cravens, Chair Date approved: 22 January 2016 ii Abstract Mars possesses a hot oxygen exosphere that extends out to several Martian radii. The main source for populating this extended exosphere is the dissociative recombination of molecular oxygen ions with electrons in the Mars ionosphere. The dissociative recombination reaction creates two hot oxygen atoms that can gain energies above the escape energy at Mars and escape from the planet. Oxygen loss through this photochemical reaction is thought to be one of the main mechanisms of atmosphere escape at Mars, leading to the disappearance of water on the surface. In this work the hot oxygen exosphere of Mars is modeled using a two-stream/Liouville approach as well as a Monte-Carlo simulation. The modeled exosphere is used in a pickup ion simulation to predict the flux of energetic oxygen pickup ions at Mars. The pickup ions are created via ionization of neutral exospheric oxygen atoms through photo-ionization, charge exchange with solar wind protons, and electron impact ionization. -
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. -
Mars Science Laboratory Entry Capsule Aerothermodynamics and Thermal Protection System
Mars Science Laboratory Entry Capsule Aerothermodynamics and Thermal Protection System Karl T. Edquist ([email protected], 757-864-4566) Brian R. Hollis ([email protected], 757-864-5247) NASA Langley Research Center, Hampton, VA 23681 Artem A. Dyakonov ([email protected], 757-864-4121) National Institute of Aerospace, Hampton, VA 23666 Bernard Laub ([email protected], 650-604-5017) Michael J. Wright ([email protected], 650-604-4210) NASA Ames Research Center, Moffett Field, CA 94035 Tomasso P. Rivellini ([email protected], 818-354-5919) Eric M. Slimko ([email protected], 818-354-5940) Jet Propulsion Laboratory, Pasadena, CA 91109 William H. Willcockson ([email protected], 303-977-5094) Lockheed Martin Space Systems Company, Littleton, CO 80125 Abstract—The Mars Science Laboratory (MSL) spacecraft TABLE OF CONTENTS is being designed to carry a large rover (> 800 kg) to the 1. INTRODUCTION ..................................................... 1 surface of Mars using a blunt-body entry capsule as the 2. COMPUTATIONAL RESULTS ................................. 2 primary decelerator. The spacecraft is being designed for 3. EXPERIMENTAL RESULTS .................................... 5 launch in 2009 and arrival at Mars in 2010. The 4. TPS TESTING AND MODEL DEVELOPMENT.......... 7 combination of large mass and diameter with non-zero 5. SUMMARY ........................................................... 11 angle-of-attack for MSL will result in unprecedented REFERENCES........................................................... 11 convective heating environments caused by turbulence prior BIOGRAPHY ............................................................ 12 to peak heating. Navier-Stokes computations predict a large turbulent heating augmentation for which there are no supporting flight data1 and little ground data for validation. -
Complete List of Contents
Complete List of Contents Volume 1 Cape Canaveral and the Kennedy Space Center ......213 Publisher’s Note ......................................................... vii Chandra X-Ray Observatory ....................................223 Introduction ................................................................. ix Clementine Mission to the Moon .............................229 Preface to the Third Edition ..................................... xiii Commercial Crewed vehicles ..................................235 Contributors ............................................................. xvii Compton Gamma Ray Observatory .........................240 List of Abbreviations ................................................. xxi Cooperation in Space: U.S. and Russian .................247 Complete List of Contents .................................... xxxiii Dawn Mission ..........................................................254 Deep Impact .............................................................259 Air Traffic Control Satellites ........................................1 Deep Space Network ................................................264 Amateur Radio Satellites .............................................6 Delta Launch Vehicles .............................................271 Ames Research Center ...............................................12 Dynamics Explorers .................................................279 Ansari X Prize ............................................................19 Early-Warning Satellites ..........................................284 -
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. -
Mars Exploration Entry, Descent and Landing Challenges1,2
Mars Exploration Entry, Descent and Landing Challenges1,2 Robert D. Braun Robert M. Manning Georgia Institute of Technology Jet Propulsion Laboratory Atlanta, GA 30332-0150 California Institute of Technology (404) 385-6171 Pasadena, CA 91109 [email protected] (818) 393-7815 [email protected] Abstract—The United States has successfully landed five interesting locations within close proximity (10’s of m) of robotic systems on the surface of Mars. These systems all pre-positioned robotic assets. These plans require a had landed mass below 0.6 metric tons (t), had landed simultaneous two order of magnitude increase in landed footprints on the order of hundreds of km and landed at sites mass capability, four order of magnitude increase in landed below -1 km MOLA elevation due the need to perform accuracy, and an entry, descent and landing operations entry, descent and landing operations in an environment sequence that may need to be completed in a lower density with sufficient atmospheric density. Current plans for (higher surface elevation) environment. This is a tall order human exploration of Mars call for the landing of 40-80 t that will require the space qualification of new EDL surface elements at scientifically interesting locations within approaches and technologies. close proximity (10’s of m) of pre-positioned robotic assets. This paper summarizes past successful entry, descent and Today, robotic exploration systems engineers are struggling landing systems and approaches being developed by the with the challenges of increasing landed mass capability to 1 robotic Mars exploration program to increased landed t while improving landed accuracy to 10’s of km and performance (mass, accuracy and surface elevation). -
Nuclear Power to Advance Space Exploration Gary L
Poster Paper P. 7.7 First Flights: Nuclear Power to Advance Space Exploration Gary L. Bennett E. W. Johnson Metaspace Enterprises EWJ Enterprises Emmett, Idaho Centerville, Ohio International Air & Space Symposium and Exposition Dayton Convention Center 14-17 July 2003 Dayton, Ohio USA r ... penni.. l .. 10 p~bli . h ..... ..,."b ll .~, ... ~ t .d til. <Op)'rigbt 0 ........ aomod oa tho fin' po_" ...... A1M.IIdd ..., yri ,hl, ... rit< .. AIM hrmi.. lou Dop a_I, 18(11 AI . ..od ... B<l1 Ori .... S.11e SIlO , R.stu. VA. 20191""-i44 FIRST FLIGHTS: NUCLEAR POWER TO ADVANCE SPACE EXPLORATION Gary L. Bennett E. W. Johnson Metaspace Enterprises EWJ Enterprises 5000 Butte Road 1017 Glen Arbor Court Emmett, Idaho 83617-9500 Centerville, Ohio 45459-5421 Tel/Fax: 1+208.365.1210 Telephone: 1+937.435.2971 E-mail: [email protected] E-mail: [email protected] Abstract One of the 20th century's breakthroughs that enabled and/or enhanced challenging space flights was the development of nuclear power sources for space applications. Nuclear power sources have allowed spacecraft to fly into regions where sunlight is dim or virtually nonexistent. Nuclear power sources have enabled spacecraft to perform extended missions that would have been impossible with more conventional power sources (e.g., photovoltaics and batteries). It is fitting in the year of the 100th anniversary of the first powered flight to consider the advancements made in space nuclear power as a natural extension of those first flights at Kitty Hawk to extending human presence into the Solar System and beyond. Programs were initiated in the mid 1950s to develop both radioisotope and nuclear reactor power sources for space applications. -
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. -
Scientific Exploration of Mars
Chapter 5 Scientific Exploration of Mars UNDERSTANDING MARS successfully inserted Mariner 9 into an orbit about Mars8 on November 13, 1971. It was the The planets have fascinated humankind ever first spacecraft to orbit another planet (box 5-A). since observers first recognized that they had For the first 2 months of the spacecraft’s stay in characteristic motions different from the stars. Mars’ orbit, the most severe Martian dust storms Astronomers in the ancient Mediterranean called ever recorded obscured Mars surface features. them the wanderers because they appear to wan- After the storms subsided and the atmosphere der among the background of the stars. Because cleared up, Mariner 9 was able to map the entire of its reddish color as seen by the naked eye, Mars Martian surface with a surface resolution of 1 9 drew attention. It has been the subject of scientif- kilometer. ic and fictiona13 interest for centuries.4 In recent Images from Mariner 9 revealed surface fea- years, planetary scientists have developed in- tures far beyond what investigators had expected creased interest in Mars, because Mars is the from the earlier flybys. The earlier spacecraft had most Earthlike of the planets. “The study of Mars by chance photographed the heavily cratered is [therefore] an essential basis for our under- southern hemisphere of the planet, which looks standing of the evolution of the Earth and the more like the Moon than like Earth. These first inner solar system.”5 closeup images of Mars gave scientists the false Planetary exploration has been one of the Na- impression that Mars was a geologically “dead” tional Aeronautics and Space Administration’s planet, in which asteroid impacts provided the (NASA) primary goals ever since the U.S. -
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.