Charles J Camarda, 722308 Beach Haven Dr APT 303, Virginia Beach, VA 23451

7357606, Apr 15, 2008

Feb 3, 2006

11/357461

Donald R. Pettit - Houston TX, US
Ronald K. Penner - Hampton VA, US
Larry D. Franklin - Hampton VA, US
Charles J. Camarda - League City TX, US

United States of America as represented by the Administrator of the National Aeronautics and Space Administration - Washington DC

B23G 5/20
B23B 51/08

408222, 408 1 R, 408225, 470199

Methods and tool for simultaneously forming a bore in a work piece and forming a series of threads in said bore. In an embodiment, the tool has a predetermined axial length, a proximal end, and a distal end, said tool comprising: a shank located at said proximal end; a pilot drill portion located at said distal end; and a mill portion intermediately disposed between said shank and said pilot drill portion. The mill portion is comprised of at least two drill-tap sections of predetermined axial lengths and at least one transition section of predetermined axial length, wherein each of said at least one transition section is sandwiched between a distinct set of two of said at least two drill-tap sections. The at least two drill-tap sections are formed of one or more drill-tap cutting teeth spirally increasing along said at least two drill-tap sections, wherein said tool is self-advanced in said work piece along said formed threads, and wherein said tool simultaneously forms said bore and said series of threads along a substantially similar longitudinal axis.

8002219, Aug 23, 2011

Nov 16, 2007

11/941119

Charles J. Camarda - League City TX, US
Stephen J. Scotti - Grafton VA, US
Pieter G. Buning - Yorktown VA, US
Steven X. S. Bauer - Yorktown VA, US
Walter C. Engelund - Seaford VA, US
David M. Schuster - Williamsburg VA, US

The United States of America as represented by the Administrator of the National Aeronautics and Space Administration - Washington DC

B64G 1/40

2441713

An annular fairing having aerodynamic, thermal, structural and acoustic attributes couples a launch abort motor to a space vehicle having a payload of concern mounted on top of a rocket propulsion system. A first end of the annular fairing is fixedly attached to the launch abort motor while a second end of the annular fairing is attached in a releasable fashion to an aft region of the payload. The annular fairing increases in diameter between its first and second ends.

5527588, Jun 18, 1996

May 3, 1995

8/433009

Charles J. Camarda - Virginia Beach VA
George P. Peterson - College Station TX
Donald R. Rummler - Hampton VA

The United States of America as represented by the Administrator of the
National Aeronautics and Space Administration - Washington DC
Texas A&M University - College State TX

B32B 320

428188

Flat or curved micro heat pipe panels are fabricated by arranging essentially parallel filaments in the shape of the desired panel. The configuration of the filaments corresponds to the desired configuration of the tubes that will constitute the heat pipes. A thermally conductive material is then deposited on and around the filaments to fill in the desired shape of the panel. The filaments are then removed, leaving tubular passageways of the desired configuration and surface texture in the material. The tubes are then filled with a working fluid and sealed. Composite micro heat pipe laminates are formed by layering individual micro heat pipe panels and bonding them to each other to form a single structure. The layering sequence of the micro heat pipe panels can be tailored to transport heat preferentially in specific directions as desired for a particular application.

5720339, Feb 24, 1998

Mar 27, 1995

8/410959

David E. Glass - Hampton VA
Charles J. Camarda - Virginia Beach VA
Michael A. Merrigan - Santa Cruz NM

F28D 1500

16510426

A thermal protection system containing several innovative features has been developed with heat pipes embedded in a composite material. The techniques used in the fabrication of the heat pipes permit a smaller radius and a higher use temperature heat pipe than could be manufactured under pervious techniques. The techniques used to embed the heat pipes in a refractory composite material yield a light weight leading edge that is able to tolerate the thermal stresses generated by the difference in thermal expansion between the heat pipes and the composite material. The heat pipes for the leading edge have a "J-shape", and are placed so that the long leg of the heat pipe alternates between the upper and lower surfaces. A coating is placed on the heat pipes that protects the heat pipe from oxidation and reaction with the components of the composite material. A compliant layer is placed between the heat pipes and the composite material to reduce the effects of the thermal stresses that arise due to the mismatch of thermal expansion between the heat pipe and the composite material.

5107920, Apr 28, 1992

Mar 30, 1990

7/501909

Stephen J. Scotti - Grafton VA
Max L. Blosser - Newport News VA
Charles J. Camarda - Virginia Beach VA

The United States of America as represented by the Administrator of the
National Aeronautics and Space Administration - Washington DC

F28D 1700
F28F 1302

1651091

Various heat exchange apparatuses are described in which an oscillating flow of primary coolant is used to dissipate an incident heat flux. The oscillating flow may be imparted by a reciprocating piston, a double action twin reciprocating piston, fluidic oscillators or electromagnetic pumps. The oscillating fluid flows through at least one conduit in either an open loop or a closed loop. A second flow of coolant may be used to flow over the outer walls of at least one conduit to remove heat transferred from the primary coolant to the walls of the conduit.

4485670, Dec 4, 1984

Feb 13, 1981

6/234222

Charles J. Camarda - Newport News VA
Lana M. Couch - Mathews VA

The United States of America as represented by the Administrator of the
National Aeronautics and Space Administration - Washington DC

G01L 1904

73179

The basic heat pipe principle is employed to provide a self-contained passively cooled probe that may be placed into a high temperature environment. The probe consists of an evaporator region 13 of a heat pipe 10 and a sensing instrument 17. Heat is absorbed as the working fluid 22 evaporates in the probe. The vapor is transported to the vapor space 14 of the condenser region 15. Heat is dissipated from the condenser region and fins 20 causing condensation of the working fluid, which returns to the probe by gravity and the capillary action of the wick 18. Working fluid, wick and condenser configurations and structure materials can be selected to maintain the probe within an acceptable temperature range.

4838346, Jun 13, 1989

Aug 29, 1988

7/237036

Charles J. Camarda - Virginia Beach VA
Philip O. Ransone - Hayes VA

The United States of America as represented by the Administrator of the
National Aeronautics and Space Administration - Washington DC

F28D 1502
F28F 1902

16510414

A reusable, durable heat pipe which is capable of operating at temperatures up to about 3000. degree. F. in an oxidizing environment and at temperatures above 3000. degree. F. in an inert or vacuum environment is produced by embedding a refractory metal pipe within a carbon-carbon composite structure. A reusable, durable heat pipe panel is made from an array of refractory-metal pipes spaced from each other, each refractory-metal pipe being embedded within a carbon-carbon composite structure. The reusable, durable, heat-pipe panel is employed to fabricate a hypersonic vehicle leading edge and nose cap.

5598632, Feb 4, 1997

Oct 6, 1994

8/320622

Charles J. Camarda - Virginia Beach VA
George P. Peterson - College Station TX
Donald R. Rummler - Hampton VA

The United States of America as represented by the Administrator of the
National Aeronautics and Space Administration - Washington DC
Texas A&M - College Station TX

B23P 1526

29890032

Flat or curved micro heat pipe panels are fabricated by arranging essentially parallel filaments in the shape of the desired panel. The configuration of the filaments corresponds to the desired configuration of the tubes that will constitute the heat pipes. A thermally conductive material is then deposited on and around the filaments to fill in the desired shape of the panel. The filaments are then removed, leaving tubular passageways of the desired configuration and surface texture in the material. The tubes are then filled with a working fluid and sealed. Composite micro heat pipe laminates are formed by layering individual micro heat pipe panels and bonding them to each other to form a single structure. The layering sequence of the micro heat pipe panels can be tailored to transport heat preferentially in specific directions as desired for a particular application.