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This paper describes a research project that was undertaken to develop an enhanced completion method. The criteria for the method was to have a procedure which was capable of perforating, fracturing, and propping in a very short period of time, i.e., on the order of a few seconds at most. A downhole energy generating device was developed which creates gas at high pressure for the Initial fracture. The control of this device is crucial to a successful completion. A means to store potential energy in the vicinity of the zone to be fractured was found in the form of a column of compressed sand-laddened foam. This foam provides from 90 to 95% of the total energy dissipated into the zone to be fractured. A computer code was developed to predict the pressure history of the material within the well bore during the procedure. A second computer code was developed which calculates the fracture volume and weight of sand injected into the fracture. Finally, a test was performed to check the operational procedures, reliability of the ignition sequence, and gas generation capability of the gas generating device.

The contamination that results from the exhaust plume of small thrusters used for attitude control maneuvers can pose severe problems for long-lift satellite systems. In order to assess this type of contamination problem, analytical and experimental techniques must be developed. Mass deposition rate measurements of a representative 0.44-N thrust hydrazine thruster were made in the Jet Propulsion Laboratory (JPL) Molsink space simulation chamber using five appropriately placed variable-temperature quartz crystal microbalances. The mass deposition rates within the thruster plume were measured while operating the thruster over a wide range of operating parameters, including duty cycles, catalyst bed start temperatures, propellant water variation, as well as thruster aging effects. The contamination measurements were made over a temperature range of 144 to 256 K for all duty cycles. In addition, the nominal duty cycle of 100 mse** on and 10 sec off was run at a temperature of 106 K. These data will make possible better prediction of deposition rates of contaminants from thrusters used in satellite systems.