The hard start phenomena in hypergolic engines. Volume 2: Combustion characteristics of propellants and propellant combinations

The combustion characteristics of hypergolic propellants are described. A research project was conducted to determine if the reaction control system engine propellants on Apollo spacecraft undergo explosive reaction when subjected to conditions present in the engine at the time of ignition. Combustion characteristics pertinent to the hard-start phenomenon are considered. The thermal stability of frozen mixtures of hydrazine-based fuels with nitrogen tetroxide was analyzed. Results of the tests are presented in the form of tables and graphs

The hard start phenomena in hypergolic engines. Volume 1: Bibliography

A bibliography of reports pertaining to the hard start phenomenon in attitude control rocket engines on Apollo spacecraft is presented. Some of the subjects discussed are; (1) combustion of hydrazine, (2) one dimensional theory of liquid fuel rocket combustion, (3) preignition phenomena in small pulsed rocket engines, (4) experimental and theoretical investigation of the fluid dynamics of rocket combustion, and (5) nonequilibrium combustion and nozzle flow in propellant performance

When Disaster Strikes: A Proposed Model for Child Life Programming in Disaster Relief Settings

In the aftermath of a major natural disaster, few are equipped to respond effectively to the unique emotional and psychological needs to children. Child life specialists are specifically trained to help children effectively cope with traumatic situations, though very few child life specialists have engaged in disaster-related work. There exists the need for a medium through which child life specialists can become involved and offer their crucial and unique services. This project offers a rationale for why this medium is necessary and proposes a model for the integration of child life into the pre-existing Red Cross disaster relief model

The hard start phenomena in hypergolic engines. Volume 3: Physical and combustion characteristics of engine residuals

An investigation was conducted to determine the cause of starting problems in the hypergolic rocket engines of the Apollo reaction control (RCS) engines. The scope of the investigation was as follows: (1) to establish that chemical reactions occurred during the preignition and post combustion periods, (2) to identify the chemical species of the products of preignition and post combustion reaction, and (3) to determine the explosive nature of the identified species. The methods used in identifying the chemical products are described species. The infrared spectra, X-ray spectra, and other signatures of the compounds are presented. The physical and explosion characteristics of various hypergolic agents are reported

The hard start phenomena in hypergolic engines. Volume 5: RCS engine deformation and destruct tests

Tests were conducted to determine the causes of Apollo Reaction Control (RCS) engine failures. Stainless steel engines constructed for use in the destructive tests are described. The tests conducted during the three phase investigation are discussed. It was determined that the explosive reaction that destroys the RCS engines occurs at the time of engine ignition and is apparently due to either the detonation of the heterogeneous constituents of the rocket engine, consisting primarily of unreacted propellant droplets and vapors, and/or the detonation of explosive materials accumulated on the engine walls from previous pulses. Photographs of the effects of explosions on the simulated RCS engines are provided

Summary of literature survey of hypergolic ignition spike phenomena, phase I Final report, Apr. 8 - Dec. 31, 1965

Summary of industry survey and literature search of ignition spike phenomena in low thrust, hypergolic, liquid bipropellant rocket engine

Exploratory study of hypergolic ignition spike phenomena, phase 2, part 2, July 1 to September 30, 1966

Chemical analysis, physical properties, and combustion characteristics of hydrazine nitrat

The hard start phenomena in hypergolic engines. Volume 4: The chemistry of hydrazine fuels and nitrogen tetroxide propellant systems

The various chemical reactions that occur and that could possibly occur in the RCS engines utilizing hydrazine-type fuel/nitrogen tetroxide propellant systems, prior to ignition (preignition), during combustion, and after combustion (postcombustion), and endeavors to relate the hard-start phenomenon to some of these reactions are discussed. The discussion is based on studies utilizing a variety of experimental techniques and apparatus as well as current theories of chemical reactions and reaction kinetics. The chemical reactions were studied in low pressure gas flow reactors, low temperature homogeneous- and heterogeneous-phase reactors, simulated two-dimensional (2-D) engines, and scaled and full size engines

Adsorption kinetics for the removal of copper(II) from aqueous solution by adsorbent PSTM-3T

The batch removal of copper (II) from aqueous solution under different experimental conditions using silicon-organic sorbent poly[N,N’-bis(3-silseskquioxanilpropyl)thiocarbamide] (PSTM-3T) was investigated in this study. This sorbent was produced from the hydrolytic poly-condensation reaction. The removal was favoured at pH = 5 for PSTM-3T. The effects of concentration and temperature have been reported. PSTM-3T was found to efficiently remove Cu(II) from solution. The batch sorption kinetics have been tested for a first-order reaction. The rate constants of adsorption have been calculated. The thermodynamic parameters (ΔG0, Kc) obtained to indicate the endothermic nature of Cu(II) adsorption on PSTM-3T.DOI: http://dx.doi.org/10.5564/mjc.v12i0.162 Mongolian Journal of Chemistry Vol.12 2011: 1-