US Government As Represented by the Secretary of the Army

United States of America As Represented by the Administrator of Nasa

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

Other

Charles S Cornelius

W Neill Myers

Michael D Shadoan

David A Gibson

David L Sparks

Warren Peters

Timothy W Lawrence

Richard H Counts

Jeffrey D Lackey

Stephen C Cayson

Charles M Vessels

Bob R Hurst

A delivery and release device for release and detonation of sequential explosive charges is disclosed to penetrate hardened structures. An aerodynamic shell is sized for delivery to a target by hand or mechanical means, including a first explosive charge is in a forward portion and a release device enclosing a second explosive charge is disposed in a shell rear portion. The release device includes a segmented cone positioned behind the first explosive charge, and a segmented cylindrical unit extending rearwards to enclose the second explosive charge within the shell during flight. Upon impact with the target, the first explosive charge detonates and directs high pressure gases against the target and deflection of gases rearwards against the segmented cone. The segmented cone and cylindrical unit are forced to separate and pivot outwards thereby releasing the second explosive charge for delayed delivery and detonation against the target leading to breach and destruction.

Missile-borne explosive activated grenade release device

A soft shell camper top for use on pickup truck cargo compartments is disclosed. The invention consists of a space frame and a flexible outer covering. The frame is removably attachable to the pickup truck bed and includes provisions for the attachment of a roof rack. The outer covering includes front and rear curtains and side curtains. The curtains may be securely fixed to attachments on the frame to protect cargo from the elements or may be rolled up to facilitate easy access to the truck bed.

Soft shell camper top including a roof rack for use on a pickup truck

A Non-Protrusive Expandable Clamping Device fastens together two bodies when conventional fastening devices cannot be used because of the unique space constraints and/or the shape of the joining surfaces of the bodies. The expandable clamping device, which has two tenons on opposite sides of its housing, can be slid into the bodies that have corresponding mortises on their joining surfaces to accommodate the tenons. The clamping device connects the bodies in one linear plane using motion in an orthogonal plane. When the clamping process is completed, facilitated by the rotational motion of a threaded bolt within the cavity inside the housing, what results is a joint that is strong in all directions as well as flush and airtight between the surfaces when an appropriate gasket or O-ring is utilized. Such a joint ensures proper alignment of the bodies while providing fixity in six degrees of freedom.

Non-protrusive expandable clamping device

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.

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

An injector for liquid fueled rocket engines wherein a generally flat core having a frustoconical dome attached to one side of the core to serve as a manifold for a first liquid, with the core having a generally circular configuration having an axis. The other side of the core has a plurality of concentric annular first slots and a plurality of annular concentric second slots alternating with the first slots, the second slots having a greater depth than said first slots. A bore extends through the core for inletting a second liquid into said core, the bore intersecting the second slots to feed the second liquid into the second slots. The core also has a plurality of first passageways leading from the manifold to the first annular slots for feeding the first liquid into said first slots. A faceplate brazed to said other side of the core is provided with apertures extending from the first and second slots through said face plate, these apertures being positioned to direct fuel and liquid oxygen into contact with each other in the combustion chamber. The first liquid may be liquid oxygen and the second liquid may be kerosene or liquid hydrogen.

Injector for liquid fueled rocket engine

The booster motors, each attached to and surrounding a centerbody, are mully connected to each other via one or more hollow manifold legs through which propulsive gases flow freely. At a predetermined time, the manifold cutter receives a signal activating the cutter to sever the manifold leg. Upon severance, the cut manifold leg still attached to the booster acts as a nozzle by venting residual propulsive gases and thereby propelling the booster away from the centerbody.

Manifold separation device

Upon the occurrence of a preset event, compressed gas is released from a mber and travels to fill a bellows. The bellows inflates and provides the power to eject a force transfer strut from the cavity of one body. The strut being fixedly attached at one end to a second body, this ejection accomplishes the separation of the two bodies from each other.

Growing community of inventors

Huntsville, AL, United States of America

Charles S Cornelius