Abstract: A windowless microbolometer for use in terrestrial applications and non-terrestrial applications is provided. The windowless microbolometer array may interact with a flow of gas such that a pixel-based image of the gas is generated when the flow of gas impinges upon the windowless microbolometer array. The windowless microbolometer array may also interact with a molecular beam to provide information related to density, shape, and propagation of the molecular beam.

Abstract: A windowless microbolometer for use in terrestrial applications and non-terrestrial applications is provided. The windowless microbolometer array may interact with a flow of gas such that a pixel-based image of the gas is generated when the flow of gas impinges upon the windowless microbolometer array. The windowless microbolometer array may also interact with a molecular beam to provide information related to density, shape, and propagation of the molecular beam.

Abstract: An apparatus for igniting a larger rocket motor is provided. The apparatus may be a smaller rocket motor that can be ignited hypergolically, when a pressurized oxidizer contacts hypergolic fuel grains of the smaller rocket motor. The hypergolic ignition causes the larger rocket motor to be ignited. The hypergolic ignition of the smaller rocket motor may be stopped after the larger rocket motor is ignited, and the remaining hypergolic fuel grains and the pressurized oxidizer can be reserved for reigniting the larger rocket motor at a later time.

Abstract: An apparatus for igniting a larger rocket motor is provided. The apparatus may be a smaller rocket motor that can be ignited hypergolically, when a pressurized oxidizer contacts hypergolic fuel grains of the smaller rocket motor. The hypergolic ignition causes the larger rocket motor to be ignited. The hypergolic ignition of the smaller rocket motor may be stopped after the larger rocket motor is ignited, and the remaining hypergolic fuel grains and the pressurized oxidizer can be reserved for reigniting the larger rocket motor at a later time.

Abstract: A fuel injector system for combustion engines and motors, such as pulsed bipropellant thrusters, includes noncircular fuel and oxidizer injectors at the ends of respective dribble channels for controlling the mixture ratio of the propellants passing into a combustion chambers for maintaining a desire or ideal mixture ratio as determined by the cross-sectional area of the injectors well suited for pulse combustion fuel injector systems.

Abstract: A fuel injector system for combustion engines and motors, such as pulsed bipropellant thrusters, includes noncircular fuel and oxidizer injectors at the ends of respective dribble channels for controlling the mixture ratio of the propellants passing into a combustion chambers for maintaining a desire or ideal mixture ratio as determined by the cross-sectional area of the injectors well suited for pulse combustion fuel injector systems.