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Monday, November 30, 2020 | History

3 edition of Iridium-coated rhenium thrusters by CVD found in the catalog.

Iridium-coated rhenium thrusters by CVD

Iridium-coated rhenium thrusters by CVD

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  • 30 Currently reading

Published by National Aeronautics and Space Administration, For sale by the National Technical Information Service in [Washington, DC], [Springfield, Va .
Written in English

    Subjects:
  • Rocket engines -- Thrust,
  • Rhenium,
  • Iridium

  • Edition Notes

    Other titlesIridium coated rhenium thrusters by CVD.
    StatementJohn T. Harding, John M. Kazaroff, and Marshall A. Appel.
    SeriesNASA technical memorandum -- 101309.
    ContributionsKazaroff, John M., Appel, Marshall A., United States. National Aeronautics and Space Administration.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL15284740M

      Read "Laminar iridium coating produced by pulse current electrodeposition from chloride molten salt, Applied Surface Science" on DeepDyve, the largest online rental service for scholarly research with thousands of academic publications available at your fingertips. A superalloy, or high-performance alloy, is an alloy that exhibits several key characteristics: excellent mechanical strength, resistance to thermal creep deformation, good surface stability, and resistance to corrosion or crystal structure is typically face-centered cubic es of such alloys are Hastelloy, Inconel, Waspaloy, Rene alloys, Incoloy, . Journal Articles. Polk, J. E., Capece, A. M., Mikellides, I. G., Katz, I., “Barium Depletion in Hollow Cathode Emitters,” Journal of Applied Physics, Vol.


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Iridium-coated rhenium thrusters by CVD Download PDF EPUB FB2

What rhenium lacks is oxidation resistance, but this can be provided by a coating of iridium, also by CVD. This paper describes the process used by Ultramet to fabricate N (5-lbf) and, more recently, N (lbf) Ir/Re thrusters; characterizes the CVD-deposited materials; and summarizes the materials effects of firing these : J.

Kazaroff, M. Appel and J. Harding. Get this from a library. Iridium-coated rhenium thrusters by CVD. [John T Harding; John M Kazaroff; Marshall A Appel; United States.

National Aeronautics and Space Administration.]. IRIDIUM-COATED RHENIUM THRUSTERS BY CVD e- rn 0 d I w John T. Harding U1 tramet Pacoima, California John M.

Kazaroff Lewis Research Center C1 eve 1 and, Ohio 35 National Aeronautics and Space Admini stration and Marshall A.

Appel Jet Propulsion Laboratory Pasadena, California SUMMARYFile Size: 3MB. Rhenium possesses a unique combination of properties that make it an excellent choice for many applications demanding high-temperature strength, wear resistance and erosion resistance.

While the major use of rhenium is still in bimetallic catalysts, renewed interest in improved propulsion and space-power systems has led to increased development Iridium-coated rhenium thrusters by CVD book rhenium Cited by: The iridium coated rhenium (Ir/Re) combustion chamber, allowing hours of operation up to degrees C, offers the thermal margin for high performance and.

The Aerojet Propulsion Division has developed thruster chambers using chemical vapor-deposited (CVD) Re coated with CVD Ir on the inside surface which is exposed to hot combustion gases. Iridium serves as an oxidation barrier protecting the Re which maintains structural integrity at high by: Rhenium (Re), a refractory metal that has gained significant recognition as a high performance engineer- Iridium-coated Re nozzles are used in aerospace applications for small Iridium-coated rhenium thrusters by CVD book rockets and resistojet thrusters [3].

A combustion cham- Among other coating processes, Reed et al. claimed that chemical vapor deposition (CVD) is the. The chemical vapour deposition (CVD) processing of Ir has progressed significantly in recent years, particularly for very high-temperature applications. Ir was first applied by CVD to rhenium rocket thruster chambers for high-temperature oxidation protection inand a N chamber was flight-qualified in (68).

For the purpose of predicting and improving the performance limit of the Ir-coated Re thruster, the diffusion kinetics of Ir/Re, prepared by electrodeposition in molten salt and chemical vapor deposition (CVD) respectively, was studied in the temperature range of to °C using the semi-infinite diffusion model for the diffusion of Re Cited by: 7.

Iridium coated Rhenium (Ir/Re) chamber selected Assessed: Chemical Vapor Deposition (CVD), electroforming (El-FormTM), Low Pressure Plasma Spray (LPPS) and Vacuum Plasma Spray (VPS) CVD is the incumbent process used to fabricate the R-4D HiPATTM thrust chambers. Acta Astronautica Vol. 28, pp.0(/92 $+ Printed in Great Britain Pergamon Press Ltd High Temperature Thruster Technology for Spacecraft Propulsion Steven J.

Schneider NASA Lewis Research Center Cleveland, OH Abstract A technology program has been underway since to develop high temperature oxidation-resistant thrusters for Cited by: Electroforming of iridium, rhenium, molybdenum, niobium and other less common metals is a cost-effective method for the production of rocket combustion chambers as well as other thruster.

Researchers discover electroplated rhenium's unexpected superconductive characteristics by University of Colorado at Boulder The process of. This report describes the AJ, a high performance Iridium-coated Rhenium (Ir-Re) lbf (N) welded rocket chamber with area ratio nozzle.

This engine was designed, built, and hot fired for over 6 hours on this program. It demonstrated an I(s) of sec, which is 10 sec higher than conventional lbf silicide coated Cb chambers now in use.

coating for rhenium because of its adequate melting temperature ( C), good oxidation resistance (3 orders of magnitude better than Re), close coefficient of thermal expansion to rhenium, ductility, and fabricability into an adherent coating on rhenium by a CVD process.7 The CVD procedure for depositing iridium is shown schematically in File Size: 6MB.

rhenium (Re) rocket thrusters against extreme environ-ments. At present, one successful application of Ir coat-ing is its use in a liquid rocket motor. Ultramet’s °ag-ship product Ir/Re combustion chamber can operate at temperatures up to –C [7].

Many methods can be used to prepare Ir coating, such as metal organic chem-Cited by: 8. Owing to its unique physical and chemical properties, Ir has been evaluated for applications in a wide range of fields, including as a barrier layer on structural carbon materials (56, 57), Ir crucibles, Re-Ir rocket thrusters, heavy metal ion sensors, precision glass moulding components (61, 62), patterned thin film microelectrodes, spark.

Diffusion mechanisms in chemical vapor-deposited iridium coated on chemical vapor-deposited rhenium. By N. Yang, J.

E Radiation-cooled rocket thruster chambers have been developed which use CVD Re coated with CVD Ir on the interior surface that is exposed to hot combustion gases. The diffusion kinetics of CVD materials at. A uniform and even film of Iridium (Ir) layer was prepared by potentiostatic electrodeposition in LiCl-KCl molten salt using IrCl3 as main salt.

The morphology and constitutions of Ir film prepared under different conditions were examined using Scanning Electron Microscope (SEM) and Energy Dispersive Spectrometer (EDS) respectively. It was found that the electrodeposition conducted Author: Jian Gang Qian, Peng Rui Li, Hai Ting Li, Tian Zhao.

CVD hydrogen reduction of volatile rhenium oxides Meng BAI, Zhi-hong LIU, Le-jun ZHOU, Zhi-yong LIU, Chuan-fu ZHANG School of Metallurgical Science and Engineering, Central South University, ChangshaChina Received 11 November ; accepted 3 May Abstract: A novel CVD process for the preparation of ultrafine rhenium powders was Cited by: Nickel-based super alloy, niobium alloy, refractory metal and carbon fiber reinforced composite are the most common structural materials used in aviation and spaceflight fields.

Reduced oxidation and corrosion resistance at high temperature are limiting factors to the application of theses materials. Adapted protective coatings such as pure precious metal coatings, precious Cited by: 1. This is the second part of a two-part report that describes the AJ, a high performance iridium-coated rhenium (Ir-Re) lbf (N) welded rocket chamber with area ratio nozzle.

This engine was designed, built, and hot fired for over 6 hours on this program. ELCTE MAR 2 5 7 February Authors: Ultramet J.

Harding Montague Street FABRICATION OF IRIDIUM COATED RHENIUM THRUSTERS FOR AEROJET 19 CONCLUSIONS AND RECOMMENDATIONS 22 REFERENCES 24 chemical vapor deposition (CVD) of Ir, Pt, Rh. Carbon fiber reinforced silicon carbide(C/SiC)composite has low density,high oxidation and erosion resistance,as well as high mechanical performance at high ore,it is the most perfect material to fabricate thrust chamber which is used in liquid propellant rocket engine.

The development and application of rocket engine thrusters made of the ceramic matrix. John T. Harding has written: 'Iridium-coated rhenium thrusters by CVD' -- subject(s): Thrust, Iridium, Rhenium, Rocket engines Asked in Video Games How do you get free thrusters.

progress in the research of iridium-coated rhenium thruster nozzle prepared by chemical vapor deposition(CVD) is reviewed in this 。. manufacturing and testing a new 20kW class Hall effect thruster, the HT20k, together with the associated high current hollow cathode, the HC This paper provides the description of the development approach and the status of the project.

INTRODUCTION Advantages offered by the high specific impulse ofFile Size: KB. Rhenium CVD from the carbonyl has been performed below C, but the residual carbon content degraded mechanical properties (Fig.

As long as the high-temperature and ductility properties of rhenium are not important for the application, the carbonyl CVD technique is acceptable. Though the rhenium carbonyl CVD is low-temperature, it is. The iridium deposition process developed here was applied in the fabrication of several rhenium thrusters.

Some of these have been test fired by Aerojet Techsystems using MMH/NTO propellant. One chamber has completed over 8 hours of operation including over starts and 4 hours burn time between and C at a mixture ratio of Near-net shape powder metallurgy rhenium thruster.

Todd Leonhardt, Mark Hamister, Jan Carlen, Iridium coated rhenium rocket chambers produced by electroforming. Toenshoff, R. Lanam, Historical paper session of AIAA Joint Propulsion Conference - The first operational liquid rocket for aircraft developed and produced in quantity.

What rhenium lacks is oxidation resistance, but this can be provided by a coating of iridium, also by CVD. This paper describes the process used by Ultramet to fabricate N (5-lbf) more» and, more recently, N (lbf) Ir/Re thrusters; characterizes the CVD-deposited materials; and summarizes the materials effects of firing these thrusters.

Testing of electroformed deposited iridium/powder metallurgy rhenium rockets (SuDoc NAS ) [Reed, Brian D.] on *FREE* shipping on qualifying offers. Testing of electroformed deposited iridium/powder metallurgy rhenium rockets (SuDoc NAS )Author: Brian D.

Reed. In some cases, such as for X-ray anodes manufacturing, Tungsten is mixed with Rhenium to improve alloy’s ductility, high temperature resistance, corrosion resistance and tensile strength. Tungsten-Rhenium Deposition By CVD. To deposit a tungsten-rhenium alloy, two precursors are used: Tungsten Hexafluoride (WF 6) and Rhenium Hexafluoride (ReF.

A study of CVD growth kinetics and morphological evolution of rhenium from ReCl5 Surface and Coatings Technology, Vol. Growth kinetics and microstructure of MOCVD iridium coating from iridium(III) acetylacetonate with hydrogenCited by: The technology characteristics and development trend of liquid apogee engines for satellites at home and abroad are summarized in this performance specification and the application of the typical engines abroad and the N engines of three generations made in China are s,the performance of the injectors in liquid apogee engines for satellites Author: Liu Chang-guo.

A technology program intended to develop high-temperature oxidation-resistant thrusters for spacecraft applications is considered. The program will provide the. For example, rhenium-coated balls used in thrusters currently are manufactured by CVD and cost about $8, to $10, each because each one.

Books. Publishing Support. Login. Zhang X, Wang X, Jia Z and Hu X Research progress of material of small thruster for attitude and orbit control J. Aerosp. Mater. Technol. 35 11–5. Google Scholar Tuffias R H and Kaplan R B The properties and applications of rhenium produced by CVD JOM 43 20–3.

Crossref Google Scholar. The region of Auvergne-Rhône-Alpes supports Acerde publié le 04 April Acerde receives financial support from the region to develop its production tool. Unfortunately, this book can't be printed from the OpenBook.

If you need to print pages from this book, we recommend downloading it as a PDF. Visit to get more information about this book, to buy it in print, or to download it as a free PDF.

alloys and iridium/rhenium are used. Material selection and fabrication method is selected pending the application and thruster size. The thruster propellant Flow Control Valves (FCV) are COTS components with extensive flight heritage and are manufactured by Moog Inc.

1 N THRUSTER The 1 N HPGP thruster has been designed for attitudeCited by: 4.There are two generic types of Hall thrusters described in the literature. Hall thrusters, Hall-effect thrusters (HETs), stationary plasma thrusters (SPTs), and magnetic-layer thrusters are all names for essentially the same device that is characterized by the use of a dielectric insulating wall in the plasma channel, as illustrated in Fig.

File Size: 1MB.Chapter 2 Thruster Principles Electric thrusters propel the spacecraft using the same basic principle as chemical rockets—accelerating mass and ejecting it from the vehicle. The ejected mass from electric thrusters, however, is primarily in the form of energetic charged particles.

This changes the performance of the propulsionFile Size: KB.