General Dynamics Corp., Pomona Division

General Dynamics Corporation

Hughes Missile Systems Company

General Dynamics Corporation, Air Defense Systems Division

Other

Edward T Piesik

A decubitus ulcer healing airflow device includes a motorized airflow intake fan disposed within a housing body devised to be attached to a bed rail A tubular airflow outlet is attached to a rear side of the housing body. An air filter slideably engages an access slot and is disposed between a protective grill and an airflow intake fan. At least one strap has a central elastomeric central section engageable onto the bed rail and a pair of u-shaped outer ends. Each strap engages a respective one of a pair of strap support holders disposed on each or one of a top and bottom side of the housing body. A slotted compartment, within the airflow outlet, contains a fragrance or a vaporized medicine to assist in healing the ulcers.

Decubitus ulcer healing airflow device

Apparatus for reducing the pressure and thermal impingement effects of a supersonic exhaust gas plume emanating from a rocket motor nozzle. A pair of wedge-shaped pieces comprise a disrupter positioned on opposite sides of the central longitudinal axis of the rocket exhaust plume in order to disrupt and disperse the plume concentration. The positioning of these pieces is such that at least a portion of the exhaust gas plume may pass between them. The disrupter defines a flow area normal to the central axis of the exhaust flow which is less than the cross sectional area of the exhaust plume at the position of the disrupter pieces. The reduced flow area causes the exhaust flow to undergo a normal shock wave adjacent the position of the disrupter device before the exhaust gases pass between the disrupter body pieces at subsonic velocity. The presence and configuration of the disrupter device disrupts and disperses the plume concentration, and the reduced flow velocity significantly reduces downstream pressure and thermal effects of the exhaust gas plume.

Rocket exhaust disrupter shapes

An exhaust gas management system for missile launch arrangements which incorporates multiple launch cells exhausting into a common plenum. The system provides a flow passage configuration with a transition section that permits rocket exhaust flow gas to expand to fill the channel area downstream of the nozzle exit. Automatic aft closure members are included which serve to close off the flow passages to inactive cells while providing an open passage for exhaust gases from an active cell undergoing a missile firing. This arrangement prevents back flow or recirculation of exhaust gases into the volume in the cell which is upstream of the rocket nozzle exit.

Multi-missile canister gas management system

A convoluted fan structure is provided along the bottom surface of each diagonal segment of a petal-formed aft cover for a missile canister. As the cover petals open under influence of rocket exhaust impingement on the cover, the fan structures cover the diagonal areas toward the corners of the opening. This prevents recirculation of rocket exhaust gases from the plenum into the canister through the formerly open corner areas and augment the closure force to restore the petals to the closed position after completion of missile launch.

Apparatus for limiting recirculation of rocket exhaust gases during

A structural arrangement is provided in conjunction with the upper closure of a missile cell which, upon launch of the missile, generates a rarefaction wave which assists in closing the bottom closure of the missile cell. As a result, reverse flow of exhaust gases back up into the missile chamber from an associated plenum chamber is prevented or minimized.

Self-activated rocket launcher cell closure

An exhaust gas management system for missile launch arrangements having multiple launch cells exhausting into a common plenum includes automatic aft closure members which serve to close off the flow passages to inactive cells while providing an open passage for exhaust gases from an active cell undergoing a missile firing. This arrangement prevents back flow or recirculation of exhaust gases into the volume in the cell which is upstream of the rocket nozzle exit.

Self-actuating rocket chamber closures for multi-missile launch cells

A missile canister hatch cover is provided which deflects the rocket exhaust from an adjacent uptake channel away from a missile as it leaves the canister. After diverting the uptake exhaust flow away from the missile, the hatch cover is returned to its closed position by the missile rocket exhaust as the missile nozzle clears the canister opening. Overall wear and tear on the launching system from the rocket exhaust is reduced and the uptake flow plume is stopped from expanding above the launcher. During missile launch the hatch cover is unlatched and spring loading opens it more than 90.degree. to a locked position where it interferes with the exhaust flowing from the uptake. The interference deflects the uptake flow away from the missile during flyout to avoid the heating, side thrusts, and contamination associated with the uptake exhaust flow field. After the missile clears the canister and the rocket exhaust begins to impinge on the hatch cover, the hatch cover is unlocked from its open position by actuation of a drag flap that is deployed to help close the hatch cover. An ablative material is applied to exposed surfaces of the hatch cover to prevent heat damage while it is deflecting the uptake exhaust flow.

Rocket exhaust deflector

A rocket exhaust recirculation obturator or cover member is designed to extend across the base of a missile in a launch tube between the exit nozzle of the missile rocket exhaust and the walls of the launch tube. The cover member has a central opening which seals against the rocket motor nozzle exit, and an outer periphery which seals against the launch tube walls. During launch, pressure of exhaust gases recirculating back up the launch tube will urge the obturator against the base of the missile, and both the missile and obturator will accelerate together up the launch tube. A release assembly is provided at the upper end of the launch tube which engages corresponding release devices at the outer periphery of the obturator. The engagement releases the pressure bond between the obturator, the missile base, and the launch tube. This allows the rocket exhaust to impinge upon the upper surface of the obturator in opposition to the obturator's momemtum. The exhaust impingement forces the obturator back down the launch tube, eliminating debris outside the launch tube.

Rocket exhaust recirculation obturator for missile launch tube

A missile support structure comprises at least two sabots or packing bodies which surround a missile in a launch tube and extend along at least part of its length. The sabots substantially fill the gap between the outer surface of the missile and the walls of the launch tube to restrict lateral movement. A capture assembly is provided to capture the sabots at the launch tube exit as the missile leaves the tube, and a return mechanism is provided on each sabot for intercepting the missile exhaust flow to urge the sabots back down into the launch tube.

Missile support structure for a launch tube

An apparatus for reducing the pressure and thermal impingement effects of a supersonic exhaust gas plume emanating from a rocket motor nozzle. A disrupter body positioned within the exhaust plume along the central longitudinal axis thereof disrupts and disperses the plume concentration. The body has a central passage through which a portion of the exhaust may pass. The body and passage are sized and shaped to provide a flow area normal to the exhaust flow less than the cross-sectional area of the exhaust plume at the position of the body. The reduced flow area causes the exhaust flow to undergo a normal shock wave upstream of the body before passing through and around the body at a subsonic velocity. The presence and configuration of the body disrupts and disperses the plume concentration, and the reduced flow velocity significantly reduces the downstream pressure and thermal effects of the exhaust gas plume.

Rocket exhaust disrupter

A dissipator device comprises a container having an inlet for connection to a rocket exhaust and a plurality of exhaust orifices of smaller dimensions than the inlet for exhaust flow out of the container in a plurality of different directions. A deflector member is positioned in the container in alignment with the inlet in the path of incoming exhaust gases for deflecting the flow. A disrupter member is positioned between the inlet and deflector member, and has a through bore defining an orifice of area less than the exhaust flow area at the plane of the disrupter member, so that exhaust gases flow both through and around the disrupter member, substantially reducing the downstream pressure and impingement heat transfer.

Exhaust dissipator/disrupter device

Pivotable deflector panels are installed in the transition sections between a plurality of rocket storage and launch chambers and a lower plenum or manifold chamber which is provided to dispose of the exhaust gases from missile firings. The deflector panels are in addition to the sets of doors which are provided to close off the missile storage chambers upon the firing of a missile in another chamber in order to prevent recirculation of exhaust gases into the closed off chambers. The deflector panels act with the doors to control exhaust gas flow, thereby improving the effectiveness of the gas plug which is formed by exhaust gases within a transition section.

Gas management deflector

An exhaust dissipator device for a rocket exhaust has an inlet for connection to the exhaust and a plurality of smaller exhaust orifices spaced around its surface to dissipate the flow into a plurality of smaller jets. A deflector surface in the direction of exhaust flow into the container acts to further dissipate the flow and deflect it out of its original path. This may comprise an internal surface of the container, or a separate deflector plate spaced from the container surface.

Exhaust dissipator device

A transition region for a missile launch chamber providing a smooth transition from a generally square cross-section chamber in which a missile is stored and launched to a round exit opening of the chamber which connects with an exhaust manifold or plenum. The transition section is provided with a pair of pivoted doors for closing off the bottom of the missile chamber to prevent the flow of recirculation gases from the plenum into the chamber when a missile in another chamber coupled to the same plenum system is being fired. The portion of the missile exhaust chamber between the square cross-section and the circular exit opening serves to direct the exhaust gases of a missile being fired into a smooth round exhaust plume which functions as a 'gas plug', preventing the recirculation of the exhaust gases back into the chamber of the missile being fired.

Gas management transition device

Apparatus for preventing a missile's rocket exhaust gases from contacting and adversely affecting, such as by overheating, the launch rails from which a missile may be launched. Such apparatus includes an angled member having first and second leg portions, the end of the first leg portion being pivotably secured to the rail. A member having an angled surface is mounted to the second leg portion. Prior to the launching of said missile, the apparatus is in a first operative position such that it is out of contact with said launch rail. When the exhaust gases are emitted from said missile, a portion of the exhaust is incident upon the angled surface which causes the apparatus to rotatably pivot into contact with the launch rail, whereby portions of two surfaces of the launch rail are protected from the exhaust. In alternative arrangements, springs or counterweights are provided to hold the protective apparatus open to facilitate loading of a missile on the launch rails while permitting the apparatus to close around the rails when the missile is being launched. Other arrangements provide for translation as well as rotation of a pair of angled members in a clam shell configuration for protection of particularly shaped launch rails.

Growing community of inventors

Pomona, CA, United States of America

Edward T Piesik