Patents Represented by Attorney John R. Manning
  • Patent number: 5265994
    Abstract: In the space shuttle, a cargo bay storage rack was required which was to be manufactured from a metal-plastic composite and bolted to a cargo structure. Following completion, utilization of the rack was disallowed due to tolerances, that is, the size differences between the outside bolt diameter and the inside hole diameter. In addition to the space shuttle problem there are other close tolerance requirements for bolts. Such environments often benefit from close tolerance bolting. Frequently such fabrication is not cost effective. Consequently there is a need for means of achieving close tolerances between bolts and bolt holes. Such means are provided herein. After compressing the elements together a strong rigid plastic, ceramic, or ceramic plastic fluid is forced into a channel extending through the bolt.
    Type: Grant
    Filed: January 27, 1993
    Date of Patent: November 30, 1993
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: David L. Johnston, Phillip G. Bryant
  • Patent number: 5265415
    Abstract: Thrust chambers for liquid propellant rocket engines include three principal components. One of these components is an injector which contains a plurality of injection elements to meter the flow of propellants at a predetermined rate, and fuel to oxidizer mixture ratio, to introduce the mixture into the combustion chamber, and to cause them to be atomized within the combustion chamber so that even combustion takes place. Evolving from these injectors are tube injectors. These tube injectors have injection elements for injecting the oxidizer into the combustion chamber. The oxidizer and fuel must be metered at predetermined rates and mixture ratios in order to mix them within the combustion chamber so that combustion takes place smoothly and completely. Hence tube injectors are subject to improvement.
    Type: Grant
    Filed: January 27, 1993
    Date of Patent: November 30, 1993
    Assignee: The United States of America as represented by the administrator of the National Aeronautics and Space Administration
    Inventor: George B. Cox, Jr.
  • Patent number: 5264907
    Abstract: Space savings are effected in the optical output system of a laser velocimeter. The output system comprises pairs of optical fibers having output ends from which a beam of laser light emerges, a transfer lens for each light beam, and at least one final (LV) lens for receiving the light passing through the transfer lenses and for focussing that light at a common crossing point or area. In order to closely couple the transfer lenses to the final lens, each transfer lens is positioned relative to the final lens receiving light therefrom such that the output waist of the corresponding beam received by the final lens from the transfer lens is a virtual waist located before the transfer lens.
    Type: Grant
    Filed: April 17, 1991
    Date of Patent: November 23, 1993
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: Dana H. Lynch, William D. Gunter, Kenneth W. McAlister
  • Patent number: 5261482
    Abstract: A cooling apparatus includes a container filled with a quantity of coolant fluid initially cooled to a solid phase, a cooling loop disposed between a heat load and the container. A pump for circulating a quantity of the same type of coolant fluid in a liquid phase through the cooling loop, a pair of couplings for communicating the liquid phase coolant fluid into the container in a direct interface with the solid phase coolant fluid.
    Type: Grant
    Filed: May 21, 1991
    Date of Patent: November 16, 1993
    Assignee: The United States of America as represented by the Administrator of National Aeronautics and Space Administration
    Inventors: Curtis Lomax, Bruce Webbon
  • Patent number: 5261735
    Abstract: A deployable table stowable in and deployable from a storage compartment based upon a non-self rigidizing 4-hinge arch support structure that collapses or folds upon itself to stow and that expands to deploy. The work surfaces bypass each other above and below each other to allow the deployment mechanism to operate. This assembly includes first and second primary pivot hinges disposed respectively at the opposite ends of the storage compartment, first and second lateral frame members having proximal ends connected respectively to the first and second pivot hinges, a medial frame member offset from and pivotally connected to distal ends of the first and second members through third and fourth medial pivot hinges, left-side, right-side and middle trays connected respectively to the first, second and third frame members and being foldable into and out of the storage compartment by articulation of the first, second, third and fourth joints.
    Type: Grant
    Filed: February 3, 1992
    Date of Patent: November 16, 1993
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: Marc M. Cohen, Peter Lissol
  • Patent number: 5256241
    Abstract: A method for controlling the crystallization of protein by solvent evaporation including placing a drop of protein solution between and in contact with a pair of parallel plates and driving one of the plates toward and away from the other plate in a controlled manner to adjust the spacing between the plates. The drop of solution forms a liquid cylinder having a height dependent upon the plate spacing thereby effecting the surface area available for solvent evaporation. When the spacing is close, evaporation is slow. Evaporation is increased by increasing the spacing between the plates until the breaking point of the liquid cylinder. One plate is mounted upon a fixed post while the other plate is carried by a receptacle movable relative to the post and driven by a belt driven screw drive. The temperature and humidity of the drop of protein solution are controlled by sealing the drop within the receptacle and mounting a heater and dessicant within the receptacle.
    Type: Grant
    Filed: August 28, 1992
    Date of Patent: October 26, 1993
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventor: David A. Noever
  • Patent number: 5254173
    Abstract: In vacuum plasma spraying a turntable must be provided which not only makes it possible to rotate and tilt a heavy workpiece, but to operate at vacuum plasma temperatures to do so. In the vacuum plasma coating of large parts such as combustion chambers of rocket engines the workpiece must not only be rotated, but it must be tilted. Hence the turntable must be capable not only of supporting heavy parts, but of angulating such heavy workpieces. And this must be done without drive means failure due to extremely high temperatures under which the turntable mechanism is operated. Herein a turntable mechanism is provided which is capable of operating under such conditions. For cooling the turntable drive mechanism internal cooling means are included.
    Type: Grant
    Filed: January 31, 1992
    Date of Patent: October 19, 1993
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventor: William N. Myers
  • Patent number: 5249357
    Abstract: A process for making a combustion chamber for a rocket engine wherein a copper alloy in particle form is injected into a stream of heated carrier gas in plasma form which is then projected onto the inner surface of a hollow metal jacket having the configuration of a rocket engine combustion chamber. The particles are in the plasma stream for a sufficient length of time to heat the particles to a temperature such that the particles will flatten and adhere to previously deposited particles but will not spatter or vaporize. After a layer is formed, cooling channels are cut in the layer, than the channels are filled with a temporary filler and another layer of particles is deposited.
    Type: Grant
    Filed: January 27, 1993
    Date of Patent: October 5, 1993
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: Richard R. Holmes, Timothy N. McKechnie, Christopher A. Power, Ronald L. Daniel, Jr., Robert M. Saxelby
  • Patent number: 5245885
    Abstract: A robotic joint wherein an elongated support member attached at one end to a base has the other end thereof pivotally attached to one end of a lever, the other end of the lever extending away from the support member. A tension strip extends along the support member and over the other end of the lever, the ends of the tension strip being attached to the base on opposite sides of the support member. A pair of bladders positioned between the tension strip and the support member on opposite sides thereof can be inflated to apply a tensile force to the strip and cause the lever to pivot, carring with it a finger which is attached to the lever.
    Type: Grant
    Filed: July 13, 1992
    Date of Patent: September 21, 1993
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventor: Glen A. Robertson
  • Patent number: 5241866
    Abstract: A method and apparatus for directly measuring the time-averaged streamwise momentum in a turbulent stream use a probe which has total head response which varies as the cosine-squared of the angle of incidence. The probe has a nose with a slight indentation on its front face for providing the desired response. The method of making the probe incorporates unique design features. Another probe may be positioned in a side-by-side relationship to the first probe to provide a direct measurement of the total pressure. The difference between the two pressures yields the sum of the squares of the cross-stream components of the turbulence level.
    Type: Grant
    Filed: February 21, 1991
    Date of Patent: September 7, 1993
    Assignee: The United States of America respresented by the Administrator of National Aeronautics and Space Administration
    Inventor: Vernon J. Rossow
  • Patent number: 5239864
    Abstract: A dynamic tester (10) for testing vibration damping seals and bearings is constructed having a hollow shaft (12) extending through the seal or bearing, with the shaft internally supported at each end by fluid bearings (19, 21) on hollow bosses (18, 20) connected to an interior of an enclosure (11) , with no rolling members connected to the shaft. A high pressure working fluid is forced through the hollow bosses (18, 20) to operate the bearings. Additionally, the shaft (12) is provided with a reaction turbine (32) that angularly vents a portion of the high pressure working fluid in order to rotate the shaft at high speed, up top 40,000 rpm. The seal or bearing (44) is mounted in a bushing (70), in turn supported by rods (80, 82, 86 of FIG. 3, or rods 72, 74 of FIG. 2) coupled by flex hinges (90, 90a of FIG. 3, 76, 76a of FIG. 2) to a shaking device (92 of FIG. 3, or 78 of FIG. 2) that vibrates the seal or bearing as the shaft is rotated.
    Type: Grant
    Filed: April 1, 1991
    Date of Patent: August 31, 1993
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventor: George L. von Pragenau
  • Patent number: 5233865
    Abstract: A method and apparatus for measuring time-averaged static or ambient pressure and turbulence intensity in a turbulent stream involve placing a plurality of probes in the stream. Each probe responds in a different manner to characteristics of the fluid stream, preferably as a result of having varying cross sections. The responses from the probes are used to eliminate unwanted components in the measured quantities for accurate determination of selected characteristics.
    Type: Grant
    Filed: April 24, 1991
    Date of Patent: August 10, 1993
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventor: Vernon J. Rossow
  • Patent number: 5226308
    Abstract: A system for testing bearings wherein a pair of spaced bearings provide support for a shaft on which is mounted a bearing to be tested, with a bearing holder spaced from and in alignment with the pair of bearings. The bearing holder is provided with an annular collar positioned in an opening in the bearing holder for holding the bearing to be tested. A screw threaded through the bearing holder into engagement with the collar can be turned to move the collar radially out of alignment with the pair of bearings to apply a radial load to the bearing.
    Type: Grant
    Filed: December 26, 1991
    Date of Patent: July 13, 1993
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventor: John C. Gibson
  • Patent number: 5226447
    Abstract: A detection system is provided for sensing a malfunction of a valve having an outlet connected to an end of a first pipe through which pressurized fluid may be flowed in a downstream direction away from the valve. The system includes a bypass pipe connected at its opposite ends to the first pipe and operative to bypass a portion of the fluid flow therethrough around a predetermined section thereof. A housing is interiorly divided by a flexible diaphragm into first and second opposite chambers which are respectively communicated with the first pipe section and the bypass pipe, the diaphragm being spring-biased toward the second chamber. The diaphragm housing cooperates with check valves and orifices connected in the two pipes to create and maintain a negative pressure in the first pipe section in response to closure of the valve during pressurized flow through the first pipe. A pressure switch senses the negative pressure and transmits a signal indicative thereof to a computer.
    Type: Grant
    Filed: October 7, 1992
    Date of Patent: July 13, 1993
    Assignee: The United States of America as represented by the Administration of the National Aeronautics and Space Administration
    Inventor: Richard K. Burley
  • Patent number: 5223461
    Abstract: The present invention concerns novel high strength ceramic fibers derived from boron, silicon, and carbon organic precursor polymers. The ceramic fibers are thermally stable at and above 1200.degree. C. in air. The method for preparation of the boron-silicon-carbon fibers from a low oxygen content organosilicon boron precursor polymers of the general formula Si(R.sub.2)BR.sup.1 by melt-spinning, crosslinking and pyrolysis. Specifically, the crosslinked (or cured) precursor organic polymer fibers do not melt or deform during pyrolysis to form the silicon-boron-carbon ceramic fiber. These novel silicon-boron-carbon ceramic fibers are useful in high temperature applications because they retain tensile and other properties up to 1200.degree. C., from 1200.degree. to 1300.degree. C., and in some cases higher than 1300.degree. C.
    Type: Grant
    Filed: May 11, 1992
    Date of Patent: June 29, 1993
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: Salvatore R. Riccitiello, Ming-ta S. Hsu, Timothy S. Chen
  • Patent number: 5212718
    Abstract: A gamma ray collimator including a housing having first and second sections. The first section encloses a first section of depleted uranium which is disposed for receiving and supporting a radiation emitting component such as cobalt 60. The second section encloses a depleted uranium member which is provided with a conical cut-out focusing portion disposed in communication with the radiation emitting element for focusing the emitted radiation to the target.
    Type: Grant
    Filed: August 6, 1991
    Date of Patent: May 18, 1993
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventor: Edgar J. Casanova
  • Patent number: 5211489
    Abstract: An outer race carrier (52) is constructed for receiving an outer race (26) of an antifriction bearing assembly (10). The carrier (52) in turn is slidably fitted in an opening (57) of a support wall to accommodate slight axial movements of a shaft (14). A plurality of longitudinal splines (54) on the carrier are disposed to be fitted into matching slots (56) in the opening (57). A deadband gap (60) is provided between sides of the splines and slots, with a radial gap (62) at ends of the splines and slots and a gap (59) between the splines and slots sized larger than the deadband gap. With this construction, operational distortions (slope) of the support wall are accommodated by the larger radial gaps (62, 59) while the deadband gaps (60) maintain a relatively high springrate of the housing. Additionally, side loads applied to the shaft are distributed between sides of the splines and slots, distributing such loads over a larger surface area than a race carrier (28) of the prior art.
    Type: Grant
    Filed: October 7, 1992
    Date of Patent: May 18, 1993
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventor: Jerry H. Moore
  • Patent number: 5199305
    Abstract: A method and apparatus are provided for determining the strain developed in a coated surface. A beam with a coating on a surface thereof is mounted as a cantilever and a force is applied to the free end of the beam to cause deflection of the beam until the coating on the beam fails. The strain in the beam, and hence in the coating at the point of failure, is determined based on the dimensions of the beam, the point along the beam where failure of the coating occurs and the amount of deflection of the beam, and this determination is made independently of the temperature of the beam and the material from which the beam is made. The determination is made based on the equation E=1.5.sub.x /1.sup.3, where E is strain, h is the beam thickness, d is the beam deflection, x is the distance from the free end of the beam to the point where failure of the coating occurred, and l is the length of the beam.
    Type: Grant
    Filed: October 21, 1991
    Date of Patent: April 6, 1993
    Assignee: The United States of America as represented by the Administrator of National Aeronautics and Space Administration
    Inventors: Sheldon M. Smith, Clement C. Hiel
  • Patent number: 5173944
    Abstract: An apparatus for producing pseudo-stereophonic sound from a monaural signal including a monaural source having a first speaker disposed in an anechoic room and having a sound output generated by the monaural signal. Second, third, fourth and fifth speaker disposed in the anechoic room (substantially) symmetrically about a listener having two ears. The monaural signal from the source is processed to output processed signals to each of the second, third, fourth and fifth speakers, each speaker producing a sound output corresponding to the received processed signal. A pair of microphones are disposed in the ears of the listener for receiving the sound outputs of the first, second, third, fourth and fifth speakers and producing two differentiated audio channels.
    Type: Grant
    Filed: January 29, 1992
    Date of Patent: December 22, 1992
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventor: Durand R. Begault
  • Patent number: 5173087
    Abstract: Gravitational phenomena, including convection, sedimentation, and interactions of materials with their containers all affect the crystal growth process. If they are not taken into consideration they can have adverse effects on the quantity and quality of crystals produced. As a practical matter, convection and sedimentation can be completely eliminated only under conditions of low gravity attained during orbital flight. There is, then, an advantage to effecting crystallization in space. But in the absence of of convection in a microgravity environment cooling proceeds by thermal diffusion from the walls to the center of the solution chamber. This renders control of nucleation difficult. Accordingly there is a need for a new and improved nucleation process in space. Herein crystals are nucleated by creating a small localized region of high relative supersaturation in a host solution at a lower degree of supersaturation.
    Type: Grant
    Filed: June 19, 1991
    Date of Patent: December 22, 1992
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: Roger L. Kroes, Donald A. Reiss, Sandor L. Lehoczky