Download or read book Propellant Material Compatibility Study written by and published by . This book was released on 1971 with total page 61 pages. Available in PDF, EPUB and Kindle. Book excerpt: The objective of this program was to define the threshold sensitivity limit of hydrazine fuels in common metallic materials of construction as a function of temperature and pressure. Four propellants were included in the program: hydrazine, monomethylhydrazine, MHF-5, and MHF-7. Eleven metallic materials of construction were included in the program: stainless steel 304L, 316, 321, 347, and 17-7PH; aluminum 1100-0, 6061-T6, and 2014-T6; Inconel-X 750; Haynes-25; and Hastelloy-X. Three standard tests were used to determine the threshold sensitivity limit of the propellants in the various materials: thermal stability test, detonation propagation test, and U-tube adiabatic compression test.

Download or read book Compatibility of Rocket Propellants with Materials of Construction written by Walter K. Boyd and published by . This book was released on 1960 with total page 70 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Compatibility of Materials with Rocket Propellants and Oxidizers written by Walter K. Boyd and published by . This book was released on 1965 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: The memorandum summarizes the available information on the compatibility of liquid rocket propellants with prominent materials of construction. Fuels and oxidizers of current interest are discussed. The corrosion data which are presented will apply to storing, handling, and control equipment outside of missiles and to missile components excluding combustion chamber. The compatibility of materials with reaction products in combustion chambers, nozzles, etc., is not considered. Included in the summary are data for many nonmetallic materials. The memorandum is subdivided into sections according to the propellant. Each material of construction is rated for a given medium as belonging to one of four classes, based primarily upon corrosion resistance. Consideration also is given to such factors as catalytic decomposition and sensitivity to impact.

Download or read book Propellant material Compatibility Program and Results written by and published by . This book was released on 1976 with total page 80 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Propellant material Compatibility Program and Results written by Clifford M. Moran and published by . This book was released on 1982 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Material Compatibility with Space Storable Propellants Design Guidebook written by and published by . This book was released on 1972 with total page 152 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Monomethylhydrazine Propellant Material Compatibility Investigation and Results written by and published by . This book was released on 1977 with total page 86 pages. Available in PDF, EPUB and Kindle. Book excerpt: The compatibility effect of monomethylhydrazine propellant on aluminum and corrosion-resistant steel materials in the welded form was investigated. Storage tests were conducted using specification grade MMH and a special grade (doped with water and carbon dioxide) for a period 123 days at a temperature of 71.1 deg C (160 deg F). Based upon the experimental test results, it was concluded that (1) aluminum alloy types 5052, 5086, 6061, and CRES types 316, 316L, 321, and 430 are compatible with both grades of MMH, and (2) that these materials and similar generic types would be suitable materials for use as shipping and storage containers for MMH propellant.

Download or read book A Rare Robert Morris Caricature written by Robert William Glenroie Vail and published by . This book was released on 1936 with total page 3 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Evolution of Rocket Engine Propellant written by G. A. Beane and published by . This book was released on 1963 with total page 11 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book The Compatiblity of Advanced Packageable Rocket Propellants with Materials of Construction written by and published by . This book was released on 1963 with total page 31 pages. Available in PDF, EPUB and Kindle. Book excerpt: The object of this investigation was to determine materials of construction compatible with the rocket propellants and Hydrazoid P for extended periods of time. As Army requirements demand storability at any temperature between -65 F and + 160 F, compatibility studies should emphasize the behavior of the materials investigated at the latter temperature. The two studies reported emphasize the behavior of the propellants and the construction materials at the high temperature end of the storage range. Al alloys, Ta, Ti, polyethylene, and Teflon were unaffected by Hydrazoid P. Inconel, Ni and the stainless steels were appreciably corroded and the propellant was contaminated by corrosion products. The Kel-F swelled and blistered. None of the materials tested were appreciably corroded by Cl F3. Al and Ti are recommended for tank materials for Hydrazoid P, and polyethylene and Teflon for O-ring material. Both Al and stainless steel can be recommended as tank materials for Cl F3. Teflon is the only non-metallic O-ring material recommended.

Download or read book Electrochemical Test Method for Evaluating Long Term Propellant Material Compatibility written by and published by . This book was released on 1978 with total page 195 pages. Available in PDF, EPUB and Kindle. Book excerpt: An electrochemical technique for evaluating the long-term compatibility of liquid propellants in various containment materials is described. The method requires that the liquid and containment material be electrical conductors, that the exchange current be measurable, and that the propellant decomposition mechanism be known. The time base is then altered by electrolysis of the system at some multiple of the natural decomposition rate. As a result, a simulated time scale is achieved in which the propellant decomposition rate can be predicted up to fifteen years while the actual time required for the tests is on the order of one to two months, depending on the particular metal tested.

Download or read book Stability and Compatibility Studies on Advanced Rocket Propellant Components written by Ivan C. Smith and published by . This book was released on 1970 with total page 166 pages. Available in PDF, EPUB and Kindle. Book excerpt: A number of candidate advanced propellant ingredients were studied with the objective of obtaining definitive information regarding their usefulness in new propellant systems. The research was laboratory based, involved small quantities (generally less than 100 mg.) of the ingredient, and dealt generally with the stability of individual ingredients and with stability- compatibility of two or more components of proposed propellants. The ingredients studied include: Perchlorates--HAP, HP-2, DOAP and AP (for comparison); N-F materials--P-BEP, TVOPA and P-722; Fuel--AlH3; and numerous state-of-the-art binder prepolymers and curatives.

Download or read book Propellants Manufacture Hazards and Testing written by Carl Boyars and published by . This book was released on 1969 with total page 416 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book NASA Technical Note written by and published by . This book was released on 1973 with total page 738 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Hydroxylammonium Nitrate Compatibility Tests with Various Materials A Liquid Propellant Study written by Eckart W. Schmidt and published by . This book was released on 1990 with total page 120 pages. Available in PDF, EPUB and Kindle. Book excerpt: The compatibility of hydroxylammonium nitrate ('HAN'), a key ingredient of liquid gun propellants, with 48 different materials of construction was tested in short-term immersion tests in constant temperature baths with observation and measurement of gas evolution. Test temperatures were 298 k and 338 K (25C and 65C). Test duration was 30 days. Materials tested included metals, plastics, ceramics, coatings, and lubricants. At the end of the test, the gas spaces above the solutions were analyzed for gas composition. Evolution of nitrous oxide and nitrogen was evidence of incipient decomposition in the propellant. The off-loaded HAN solutions were analyzed for leached metals. Based on the rate of gas evolution, weight loss of the specimens, discoloration of the liquid, and amount of metals leached, several materials were identified as being incompatible with 60% HAN solution. Keywords: Liquid gun propellants, Compatibility, Hydroxylammonium nitrate, Liquid propellants.

Download or read book Engine System Assessment Study Using Martian Propellants written by Dennis Pelaccio and published by . This book was released on 1992 with total page 554 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Technical and Economic Analyses to Assess the Feasibility of Using Propellant No 2 Fuel Oil Slurries as Supplemental Fuels written by and published by . This book was released on 1991 with total page 157 pages. Available in PDF, EPUB and Kindle. Book excerpt: There is currently a large inventory of obsolete conventional munitions and waste propellants. Current alternatives to storage are open burning/open detonation (OB/OD) and incineration to reduce the inventory of these materials. Since environmental impact of OB/OD is under intense scrutiny, the US Army Toxic and Hazardous Materials Agency is conducting a program to determine the feasibility of using propellants as supplemental fuels for the Army's industrial combustors. The first propellant studied was a nitrocellulose containing 13.15% nitrogen by weight. Laboratory tests were conducted to evaluate the physical and chemical characteristics, as well as the chemical compatibility, of nitrocellulose-solvent-No. 2 fuel oil solutions. Unfortunately, the tests using nitrocellulose indicated that solvation and mixing with No. 2 fuel oil is questionable from a cost standpoint due to the low solubility of this material; an economic analysis did indicate potential cost effectiveness using propellant-No. 2 fuel oil slurries as supplemental fuels. A second project assessed the technical, economic, and safety aspects of using propellant-No. 2 fuel oil slurries as supplemental fuels. Materials studies were nitrocellulose, nitroguanidine, and AA2 double-base propellant. Similar laboratory tests were again conducted. This report discusses results from these tests as well as from an economic analysis of the process.