Patents Represented by Attorney Norman T. Musial
  • Patent number: 4335503
    Abstract: A method is provided for making a high voltage multijunction solar cell which comprises a plurality of discrete voltage generating regions, or unit cells, which are formed in a single semiconductor wafer (10) and are connected together so that the voltages of the individual cells are additive. The unit cells comprise doped regions of opposite conductivity types (30, 32) separated by a gap. The method includes forming V-shaped grooves (16) in the wafer and thereafter orienting the wafer so that ions of one conductivity type can be implanted in one face (e.g., 16a) of the groove while the other face (e.g., 16b) is shielded. A metallization layer (22) is applied and selectively etched away to provide connections between the unit cells.
    Type: Grant
    Filed: December 24, 1980
    Date of Patent: June 22, 1982
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: John C. Evans, Jr., An-Ti Chai, Chandra P. Goradia
  • Patent number: 4335190
    Abstract: This invention is directed to an improved thermal barrier system by improving the adherence between a ceramic thermal barrier coating and a metal bond coating. First a primer film is deposited on the bond coat by ion sputtering a ceramic film thereon. A ceramic thermal barrier coating is then plasma-sprayed onto this primer film. This improves the integrity and strength of the interface between the plasma-sprayed ceramic layer and metallic bond coat which insures stronger adherence between the metal and the ceramic.
    Type: Grant
    Filed: January 28, 1981
    Date of Patent: June 15, 1982
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: Robert C. Bill, James S. Sovey
  • Patent number: 4331746
    Abstract: A flexible, porous battery separator comprising a coating applied to a porous, flexible substrate. The coating comprises:(a) a thermoplastic rubber-based resin which is insoluble and unreactive in the alkaline electrolyte,(b) a polar organic plasticizer which is reactive with the alkaline electrolyte to produce a reaction product which contains a hydroxyl group and/or a carboxylic acid group, and(c) a mixture of polar particulate filler materials which are unreactive with the electrolyte, the mixture comprising at least one first filler material having a surface area of greater than 25 meters.sup.2 /gram, at least one second filler material having a surface area of 10 to 25 meters.sup.2 /gram, wherein the volume of the mixture of filler materials is less than 45% of the total volume of the fillers and the binder, the filler surface area per gram of binder is about 20 to 60 meters.sup.2 /gram, and the amount of plasticizer is sufficient to coat each filler particle.A method of forming the battery separator.
    Type: Grant
    Filed: February 27, 1981
    Date of Patent: May 25, 1982
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventor: Dean W. Sheibley
  • Patent number: 4329385
    Abstract: This invention is concerned with fabricating textured surfaces on polymers without altering their surface chemistries.A surface of a fluorocarbon polymer 10 is exposed to a beam 12 of ions from a source 14 to texture it. The polymer 18 which is to be surface-roughened is then cast over the textured surface 20 of the fluorocarbon polymer. After curing, the cast polymer is peeled off the textured fluorocarbon polymer, and the peeled off surface 22 has a negative replica of the textured surface 20.The microscopic surface texture provides large surface areas for adhesive bonding. In cardiovascular prosthesis applications the surfaces are relied on for the development of a thin adherent well nourished thrombus.
    Type: Grant
    Filed: December 19, 1980
    Date of Patent: May 11, 1982
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: Bruce A. Banks, Albert J. Weigand, James S. Sovey
  • Patent number: 4329114
    Abstract: An axial compressor is provided with a cooling air manifold surrounding a portion of the shroud, and means for bleeding air from the compressor to the manifold for selectively flowing it in a modulating manner axially along the outer side of the stator/shroud to cool and shrink it during steady-state operating conditions so as to obtain minimum shroud/rotor clearance conditions. Provision is also made to selectively divert the flow of cooling air from the manifold during transient periods of operation so as to alter the thermal growth or shrink rate of the stator/shroud and result in adequate clearance with the compressor rotor.
    Type: Grant
    Filed: July 25, 1979
    Date of Patent: May 11, 1982
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: Richard P. Johnston, Malcolm H. Knapp, Charles E. Coulson
  • Patent number: 4315194
    Abstract: A coupled cavity traveling wave tube (10, 10') is provided having a velocity taper, i.e., gradual velocity reduction, which affords beam-wave resynchronization and thereby enhances efficiency. The required wave velocity reduction is achieved by reducing the resonant frequencies of the individual resonant cavities as a function of the distance from the electron gun (16, 16'), through changes in internal cavity dimensions. The required changes in cavity dimensions can be accomplished for example, by gradually increasing the cavity radius (R.sub.2, R.sub.3, R.sub.4) or decreasing the gap length (l.sub.1, l.sub.2), from cavity to cavity. With this approach the velocity reduction is carried out without an increase in circuit resistive losses and the upper and lower cut off frequencies are reduced in approximately the same manner.
    Type: Grant
    Filed: February 20, 1980
    Date of Patent: February 9, 1982
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventor: Denis J. Connolly
  • Patent number: 4310574
    Abstract: A low cost coating protects metallic base system substrates from high temperatures, high gas velocity oxidation, thermal fatigue and hot corrosion. The coating is particularly useful for protecting vanes and blades in aircraft and land based gas turbine engines.A lacquer slurry comprising cellulose nitrate containing high purity silicon powder is sprayed onto the superalloy substrates. The silicon layer is then aluminized to complete the coating.The Si-Al coating is less costly to produce than advanced aluminides and protects the substrate from oxidation and thermal fatigue for a much longer period of time than the conventional aluminide coatings. While more expensive Pt-Al coatings and physical vapor deposited MCrAlY coatings may last longer or provide equal protection on certain substrates, the Si-Al coating exceeded the performance of both types of coatings on certain superalloys in high gas velocity oxidation and thermal fatigue.
    Type: Grant
    Filed: June 20, 1980
    Date of Patent: January 12, 1982
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: Daniel L. Deadmore, Stanley G. Young
  • Patent number: 4309372
    Abstract: A method of making a membrane comprised of a hydrochloric acid-insoluble sheet of a mixture of a rubber and a powdered ion transport material is disclosed. The sheet can be present as a coating upon a flexible and porous substrate. These membranes can be used in oxidation-reduction electrical accumulator cells wherein the reduction of one member of a couple is accompained by the oxidation of the other member of the couple on the other side of the cell and this must be accompained by a change in chloride ion concentration in both sides. The method comprises preparing a mixture of fine rubber particles, a solvent for the rubber and a powdered ion transport material. The mixture is formed into a sheet and dried to produce a microporous sheet. The ion transport material includes particles ranging from about 0.01 to 10 microns in size and comprises from 20 to 50 volume percent of the microporous sheet.
    Type: Grant
    Filed: November 3, 1977
    Date of Patent: January 5, 1982
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventor: Dean W. Sheibley
  • Patent number: 4278220
    Abstract: A bypass duct outer cowl includes a fixed cascade disposed between axially spaced fixed cowl portions and a translatable cowl sleeve and blocker doors movably disposed on the respective radially outer and inner sides of the cascade. Actuation and linkage structure located entirely within the outer cowl provides for selectively moving the cowl sleeve rearwardly and rotating the blocker doors to a position across the bypass duct to cause the fan airflow to pass through the cascade in a thrust-reversing manner.
    Type: Grant
    Filed: March 30, 1979
    Date of Patent: July 14, 1981
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: Everett A. Johnston, Edward W. Ryan
  • Patent number: 4277721
    Abstract: The object of the invention is to provide a depressed collector which captures the spent electrons of a microwave transmitting tube at high efficiency in both high and low power modes of operation.The collector comprises entrance and end electrodes (14 and 18, respectively), electrode (18) having a spike extending toward entrance electrode (14). Intermediate electrodes (15, 16 and 17) and the entrance electrode (14) each have a central aperture and, together, these electrodes capture most high power mode spent electrons. The apertures of the electrodes (14-17) increase in size in a downstream direction.To capture low power mode spent electrons a low power mode electrode (19) is positioned between the last intermediate electrode (17) and the end electrode (18). This electrode (19) has a central aperture preferably smaller but no larger than that of electrode (17).
    Type: Grant
    Filed: September 7, 1979
    Date of Patent: July 7, 1981
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventor: Henry G. Kosmahl
  • Patent number: 4262067
    Abstract: A method of producing a cross-linked polyvinyl alcohol structure, such as a battery separator membrane or electrode envelope. An aqueous solution of a film-forming polyvinyl alcohol is admixed with an aldehyde cross-linking agent at basic pH to inhibit cross-linking. The cross-linking agent, preferably a dialdehyde such as glutaraldehyde, is used in an amount of from about 1/2 to about 20% of the theoretical amount required to cross-link all of the hydroxyl groups of the polymer. The aqueous admixture is formed into a desired physical shape, such as by casting a sheet of the solution. The sheet is then dried to form a self-supporting film. Cross-linking is then effected by immersing the film in aqueous acid solution. The resultant product has excellent properties for use as a battery separator, including a low electrical resistivity, the value of which is principally determined by the amount of cross-linking which is easily and closely controlled by the amount of cross-linking agent added to the polymer.
    Type: Grant
    Filed: January 18, 1980
    Date of Patent: April 14, 1981
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: Warren H. Philipp, Li-Chen Hsu, Dean W. Sheibley
  • Patent number: 4262064
    Abstract: The present invention is drawn to a toroidal cell which includes a wound core disposed within a pair of toroidal channel shaped electrodes spaced apart by nylon insulator. The shape of the case electrodes of this toroidal cell allows a first planar doughnut shaped surface and the inner cylindrical case wall to be used as a first electrode and a second planar doughnut shaped surface and the outer cylindrical case wall to be used as a second electrode. Connectors may be used to stack two or more toroidal cells together by connecting substantially the entire surface area of the first electrode of a first cell to substantially the entire surface area of the second electrode of a second cell. The central cavity of each toroidal cell may be used as a conduit for pumping a fluid through the toroidal cell to thereby cool the cell.
    Type: Grant
    Filed: March 28, 1980
    Date of Patent: April 14, 1981
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventor: William J. Nagle
  • Patent number: 4249238
    Abstract: An improved gas turbine engine control system maintains a selected level of engine performance despite the failure or abnormal operation of one or more engine parameter sensors. The control system employs a continuously updated engine model which simulates engine performance and generates signals representing real time estimates of the engine parameter sensor signals. The estimate signals are transmitted to a control computational unit which utilizes them in lieu of the actual engine parameter sensor signals to control the operation of the engine. The estimate signals are also compared with the corresponding actual engine parameter sensor signals and the resulting difference signals are utilized to update the engine model. If a particular difference signal exceeds specific tolerance limits, the difference signal is inhibited from updating the model and a sensor failure indication is provided to the engine operator.
    Type: Grant
    Filed: May 24, 1978
    Date of Patent: February 3, 1981
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: Henry A. Spang, III, Robert P. Wanger
  • Patent number: 4245469
    Abstract: A heat exchanger of increased effectiveness is disclosed. A porous metal matrix is disposed in a metal chamber or between walls through which a heat-transfer fluid is directed. The porous metal matrix has internal bonds and is bonded to the chamber in order to remove all thermal contact resistance within the composite structure. Utilization of the invention in a rocket chamber is disclosed as a specific use. Also disclosed is a method of constructing the heat exchanger.
    Type: Grant
    Filed: April 23, 1979
    Date of Patent: January 20, 1981
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: Anthony Fortini, John M. Kazaroff
  • Patent number: 4244857
    Abstract: A curing agent for a polyepoxide has the formula: ##STR1## wherein R.sub.1 is a divalent aryl radical such as phenylene and wherein R.sub.2 is a tetravalent aryl radical such as a tetravalent benzene radical. An epoxide is cured by admixture with the curing agent. The cured epoxy product retains the usual properties of cured epoxides and, in addition, has a high char residue after burning, on the order of 45% by weight. The high char residue is of value in preventing release to the atmosphere of carbon fibers from carbon fiber-epoxy resin composites in the event of burning of the composite.
    Type: Grant
    Filed: August 30, 1979
    Date of Patent: January 13, 1981
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: Tito T. Serafini, Peter Delvigs, Raymond D. Vannucci
  • Patent number: 4242864
    Abstract: An integrated control system for a gas turbine engine of the turbofan type receives signals from a plurality of engine sensors and from the engine operator and generates control signals therefrom. A first control signal regulates the fan exhaust nozzle area in order to control inlet throat Mach number to maintain a low level of engine noise. Additional control signals regulate fuel flow to control engine thrust and fan pitch to control fan speed. A plurality of schedules are utilized to maintain a predetermined relationship between the controlled parameters and a number of fixed and calculated limits can override the control signals to prevent unsatisfactory engine performance.
    Type: Grant
    Filed: May 25, 1978
    Date of Patent: January 6, 1981
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: Jack E. Cornett, Andrew A. Saunders, Jr., Ira E. Marvin, Richard S. Beitler
  • Patent number: 4220171
    Abstract: An inlet for a gas turbine engine is disposed about a curved centerline for the purpose of accepting intake air that is flowing at an angle to engine centerline and progressively turning that intake airflow along a curved path into alignment with the engine. This curved inlet is intended for use in under-the-wing locations and similar regions where airflow direction is altered by aerodynamic characteristics of the airplane. By curving the inlet, aerodynamic loss and acoustic generation and emission are decreased.
    Type: Grant
    Filed: May 14, 1979
    Date of Patent: September 2, 1980
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: William C. Ruehr, James L. Younghans, Edwin B. Smith
  • Patent number: 4218280
    Abstract: A self-supporting sheet structure comprising a water soluble, non-cross-linked polymer such as polyvinyl alcohol which is capable of being cross-linked by reaction with hydrogen atom radicals and hydroxyl molecule radicals is contacted with an aqueous solution having a pH of less than 8 and containing a dissolved salt in an amount sufficient to prevent substantial dissolution of the non-cross-linked polymer in the aqueous solution. The aqueous solution is then irradiated with ionizing radiation to form hydrogen atom radicals and hydroxyl molecule radicals and the irradiation is continued for a time sufficient to effect cross-linking of the water soluble polymer to produce a water-insoluble polymer sheet structure. The method has particular application in the production of battery separators and electrode envelopes for alkaline batteries.
    Type: Grant
    Filed: December 20, 1978
    Date of Patent: August 19, 1980
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: Warren H. Philipp, Charles E. May, Li-Chen Hsu, Dean W. Sheibley
  • Patent number: 4218633
    Abstract: A source of hydrogen ions is disclosed and includes a chamber having at one end a cathode which provides electrons and through which hydrogen gas flows into the chamber. Screen and accelerator grids are provided at the other end of the chamber. A baffle plate is disposed between the cathode and the grids and a cylindrical baffle is disposed coaxially with the cathode at the one end of the chamber. The cylindrical baffle is of greater diameter than the baffle plate to provide discharge impedance and also to protect the cathode from ion flux. An anode electrode draws the electrons away from the cathode.The hollow cathode includes a tubular insert of tungsten impregnated with a low work function material to provide ample electrons. A heater is provided around the hollow cathode to initiate electron emission from the low work function material.
    Type: Grant
    Filed: October 23, 1978
    Date of Patent: August 19, 1980
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: Michael J. Mirtich, Jr., James S. Sovey, Robert F. Roman
  • Patent number: 4184327
    Abstract: Upon a landing approach, the normal compressor stator schedule of a fan speed controlled turbofan engine is temporarily varied to substantially close the stators to thereby increase the fuel flow and compressor speed in order to maintain fan speed and thrust. This running of the compressor at an off-design speed substantially reduces the time required to subsequently advance the engine speed to the takeoff thrust level by advancing the throttle and opening the compressor stators.
    Type: Grant
    Filed: December 9, 1977
    Date of Patent: January 22, 1980
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: Jack E. Cornett, Ralph C. Corley, Thomas O. Fraley, Andrew A. Saunders, Jr.