Northrop Grumman Systems Corporation

Cal Poly Corporation

California Polytechnic State University Foundation

James Alan Gerhardt

Thomas W Carpenter

Patrick J E Lemieux

Yuan Li

Russell V Westhphal

Anne M Sullivan

Kris I Lawrence

Htet Htet Oo

Brittany Reanne Kinkade

Christopher A Harris

Russell V Westphal

Daniel R Cuppoletti

William R Murray

A pressure sensor assembly for simultaneously providing a time-resolved total pressure measurement and steady state flow angles of an airflow. The assembly includes an outer shroud having a front face, a rear face and a central bore having a wall. A dynamic absolute pressure sensor is positioned within the bore and provides a time-resolved total airflow pressure measurement. First and second spaced apart static pressure ports extend from the front face of the shroud to the rear face of the shroud and adjacent to the bore. The pressure ports provide a pressure that can be measured by pressure probes, where a combination of the time-resolved total pressure measurement and pressure measurements from the probes provides a steady state flow angle of the airflow.

Directional dynamic absolute pressure sensor shroud and arrangement

An apparatus for assisting with measurement of a fluid pressure includes a cover layer having a leading cover edge and upper and lower cover surfaces. A cover aperture fluidly connects the upper and lower cover surfaces. A spacer layer has oppositely facing upper and lower spacer surfaces. A cavity has an upper cavity surface, defined by the lower cover surface, which includes the leading cover edge and the cover aperture. A measuring tube is located adjacent to the upper cover surface. The measuring tube includes a tube lumen. When the lower spacer surface is connected to the substrate, the substrate defines a lower cavity surface and extant fluid is present within the cavity. Variable fluid flowing toward the cavity exerts pressure on the extant fluid to generate an extant fluid pressure level which is physically transmitted through the apparatus and made available for measurement as an extant fluid pressure level.

Apparatus and method for assisting with fluid pressure measurement

A system and method of cooling a rocket motor component includes injecting a high pressure liquid coolant through an injector nozzle into a cooling chamber. The cooling chamber having a pressure lower than the high pressure liquid coolant. The liquid coolant flashes into a saturated liquid-vapor coolant mixture in the cooling chamber. The saturated liquid-vapor coolant mixture is at equilibrium at the lower pressure of the cooling chamber. Heat from the rocket motor component to be cooled is absorbed by the coolant. A portion of the liquid portion of the saturated liquid-vapor coolant mixture is converted into gas phase, the converted portion being less than 100% of the coolant. A portion of the coolant is released from the cooling chamber and the coolant in the cooling chamber is dynamically maintained at less than 100% gas phase of the coolant as the thrust and heat generated by the rocket motor varies.

System, method and apparatus for cooling rocket motor components using a saturated liquid vapor coolant mixture

A nozzle flow thrust vector measurement system employs a thrust vector table, and a gas supply. The thrust vector table employs a thrust measurement table; a reference table; and at least three load cell assemblies coupled to the thrust measurement table and the reference table. The gas supply system employs a gas supply conduit substantially fixed relative to the reference table; a gas supply manifold substantially fixed relative to the thrust vector table; and a zero force connecting system coupled between the gas supply conduit and the gas supply manifold, wherein the zero force connecting system applies substantially zero net force to the gas supply manifold allowing substantially all force applied to the thrust vector table to act on said load cell assemblies.

Nozzle flow thrust vector measurement

Growing community of inventors

Atascadero, CA, United States of America

James Alan Gerhardt