United States of America As Represented by the Administrator of Nasa

The United States of America As Represented by the Administrator of the

Other

The United States of America As Represented by the United States

The United States of America As Represented by the Administrator

W Neill Myers

Jeffrey Lee Lindner

Charles S Cornelius

Michael D Shadoan

Robert E Berry

John S Townsend

Frederick Scott Gant

David L Sparks

John C Forbes

Eric S Taylor

Huu P Trinh

Timothy W Lawrence

Michael A Martin

Richard H Counts

Jeffrey D Lackey

Warren Peters

Anthony R Kelley

Henry J Dennis, Jr

D Andy Hissam

Ewell M Scott

Hong Q Yang

Kevin J Baker

George D Xenofos

Darron C Rice

Wayne L Barnes

R Scott Michaels

A frequency-tunable vibration damper includes a first container having rigid wall regions and compliant wall regions. A second container is coupled to the first container such that a wall region of the second container includes one of the compliant wall regions. A fluid fills the first container and a gas fills the second container. A flow restrictor is included in the second container and is spaced-apart from the one of the compliant wall regions included with the second container.

Fluid-filled frequency-tunable vibration damper

A unidirectional damping system includes a shaft and unidirectional damping modules. Each module is fixedly coupled to the shaft. Each module includes a fluid-filled variable-volume chamber and spring(s). The chamber has at least one port through which fluid flows based on changes in volume of the chamber wherein, when the shaft is adapted to have a unidirectional force applied thereto, the chamber decreases in volume. The spring(s) is coupled to the chamber for increasing volume of the chamber when the unidirectional force is not applied to the shaft. A fluid-filled spacer chamber is coupled between adjacent modules and is uncoupled from the shaft. The spacer chamber includes at least one venting port through which fluid flows based on pressure in the spacer chamber.

Unidirectional damping system

A damping system includes a spool about which a tension line is wound. The line's first end is coupled to a first structure subject to forces causing unwanted movement thereof. A damper is coupled to a second structure not subject to the unwanted movement of the first structure. The damper is coupled to the spool for engagement with the spool to slow a rotational speed thereof when the spool rotates in a first direction. The damper is disengaged from the spool when the spool rotates in a second direction in opposition to the first direction. A device, coupled to the line's second end and to the second structure, applies a tension force to the line's second end. The tension force is exceeded when the first structure moves to place the line in tension, and is not exceeded when the first structure moves to place the line in compression.

Structure movement damping system using tension element

A bi-directional damping system generates damping forces in two opposing directions. A shaft has a plurality of bi-directional damping modules fixedly coupled thereto. Each module includes a fluid-filled variable-volume first chamber including at least one port through which fluid can flow based on changes in volume of the first chamber, and a fluid-filled variable-volume second chamber including at least one port through which fluid can flow based on changes in volume of the second chamber. The first chamber and second chamber are fluidically isolated from one another. A fluid-filled spacer chamber is coupled to adjacent ones of the modules. The spacer chamber includes at least one venting port through which fluid can flow based on pressure in the spacer chamber.

Bi-directional damping system

A method for determining the optimum inlet geometry of a liquid rocket engine swirl injector includes obtaining a throttleable level phase value, volume flow rate, chamber pressure, liquid propellant density, inlet injector pressure, desired target spray angle and desired target optimum delta pressure value between an inlet and a chamber for a plurality of engine stages. The method calculates the tangential inlet area for each throttleable stage. The method also uses correlation between the tangential inlet areas and delta pressure values to calculate the spring displacement and variable inlet geometry of a liquid rocket engine swirl injector.

Method for determining optimum injector inlet geometry

A variable-aperture reciprocating reed valve includes a valve body defining a through hole region having a contoured-profile portion. A semi-rigid plate is affixed on one side thereof to the valve body to define a cantilever extending across the through hole region. At least one free edge of the cantilever opposes the contoured-profile portion of the through hole region in a non-contact relationship.

Variable-aperture reciprocating reed valve

An injector for use with the rocket thruster has a plurality of fuel ports separated from a plurality of oxidizer ports. The oxidizer and fuel ports are paired together directing their respective fluids along a path with radial and tangential components so that the two fluids impinge at a predetermined spaced apart distance from the chamber wall of the combustion chamber at an impingement track. By providing the fuel at a steeper angle relative to the chamber walls than the oxidizer, the fuel can be utilized to provide a fuel rich zone near the chamber walls to assist in cooling the chamber walls during operation.

Liquid propellant tracing impingement injector

An ignitor for use with the MC-1 rocket engine has a cartridge bounded by two end caps with rupture disc assemblies connected thereto. A piston assembly within the cartridge moves from one end of the cartridge during the ignition process. The inlet of the ignitor communicates with a supply taken from the discharge of the fuel pump. When the pump is initially started, the pressure differential bursts the first rupture disc to begin the movement of the piston assembly toward the discharge end. The pressurization of the cartridge causes the second rupture disc to rupture and hypergolic fluid contained within the cartridge is discharged out the ignitor outlet.

Hypergolic ignitor

An ignitor for use with the MC-1 rocket engine has a cartridge bounded by two end caps with rupture disc assemblies connected thereto. A piston assembly within the cartridge moves from one end of the cartridge during the ignition process. The inlet of the ignitor communicates with a supply taken from the discharge of the fuel pump. When the pump is initially started, the pressure differential bursts the first rupture disc to begin the movement of the piston assembly toward the discharge end. The pressurization of the cartridge causes the second rupture to rupture and hypergolic fluid contained within the cartridge is discharged out the outlet. Once the piston assembly reaches the discharge end of the cartridge, purge grooves allow for fuel and remaining hypergolic fluid, to be discharged out the ignitor outlet into the combustion chamber to purge the ignitor of any remaining hypergolic fluid.

Hypergolic ignitor assembly

A thrust chamber assembly for liquid fueled rocket engines and the method of making it wherein a two-piece mandrel wrapped with a silica tape saturated with a phenolic resin, the tape extending along the mandrel and covering the combustion chamber portion of the mandrel to the throat portion. The phenolic in the tape is cured and the end of the wrap is machined. The remainder of the mandrel is wrapped with a third silica tape. The resin in the third tape is cured and the assembly is machined. The entire assembly is then wrapped with a tow of graphite fibers wetted with an epoxy resin and, after the epoxy resin is cured, the graphite is machined to final dimensions.

Rocket engine thrust chamber assembly

Fabrication process for combustion chamber/nozzle assembly

A thrust chamber assembly for liquid fueled rocket engines and the method of making it wherein a two-piece mandrel having the configuration of an assembly having a combustion chamber portion connected to a nozzle portion through a throat portion is wrapped with a silica tape saturated with a phenolic resin, the tape extending along the mandrel and covering the combustion chamber portion of the mandrel to the throat portion. The width of the tape is positioned at an angle of 30 to 50&deg; to the axis of the mandrel such that one edge of the tape contacts the mandrel while the other edge is spaced from the mandrel. The phenolic in the tape is cured and the end of the wrap is machined to provide a frustoconical surface extending at an angle of 15 to 30&deg; with respect to the axis of the mandrel for starting a second wrap on the mandrel to cover the throat portion. The remainder of the mandrel is wrapped with a third silica tape having its width positioned at a angle of 5 to 20&deg; from the axis of the mandrel. The resin in the third tape is cured and the assembly is machined to provide a smooth outer surface. The entire assembly is then wrapped with a tow of graphite fibers wetted with an epoxy resin and, after the epoxy resin is cured, the graphite is machined to final dimensions.

A gas generator and ignitor assembly for powering a turbine of a turbopump assembly for a rocket engine comprises an injector and a combustion chamber, the injector having a body member including a fuel inlet and an oxidizer inlet spaced one from the other and communicating with respective radially spaced apart annular members in the body member. Three annuli communicate with the fuel inlet and two annuli communicate with the oxidizer inlet, the annuli which communicates with the oxidizer being positioned between pairs of the other annuli. The body member is enclosed by a plate having an array of bores arranged in two series with three radially spaced apart groups of circular rows in each series. The outer series has 28 groups of triplet bores while the inner series has 14 groups of triplet bores. The annuli which communicate with oxidizer feed bores of each series that are between the other bores of a triplet, the latter bores communicating with annuli that communicate with fuel. The inner and outer bores of the triplets of each series are inclined relatively to each other and to the third bore of the triplet so that fuel and oxidizer atomizes as it is sprayed into the inlet of the combustion chamber where the propellants are mixed, and burned. The burning of the propellants is effected by ignition of a plug of solid propellant fuel mounted to communicate with the interior of the combustion chamber.

Low-cost gas generator and ignitor

An integral, lightweight combustion chamber/nozzle assembly for a rocket engine has a refractory metal shell defining a chamber of generally frusto-conical contour. The shell communicates at its larger end with a rocket body, and terminates at its smaller end in a tube of generally cylindrical contour, which is open at its terminus and which serves as a nozzle for the rocket engine. The entire inner surface of the refractory metal shell has a thermal and oxidation barrier layer applied thereto. An ablative silica phenolic insert is bonded to the exposed surface of the thermal and oxidation barrier layer. The ablative phenolic insert provides a chosen inner contour for the combustion chamber and has a taper toward the open terminus of the nozzle. A process for fabricating the integral, lightweight combustion chamber/nozzle assembly is simple and efficient, and results in economy in respect of both resources and time.

Combustion chamber/nozzle assembly and fabrication process therefor

A clutch that connects a first rotating member to a second rotating member in a manner that allows directional rotation between the two members in an engaged mode and free rotation between the members in a disengaged mode. The novelty of this invention lies in the combination of directional rotation (i.e., rotation in one direction) capability with free rotation (i.e., rotation in both directions) capability in a single device.

Growing community of inventors

Huntsville, AL, United States of America

W Neill Myers