Patents Examined by Charles E. Frankfort
  • Patent number: 4606649
    Abstract: A modification to thermogravimetric analyzers with data acquisition devised to allow concurrent TG (thermogravimetry) and DTA (differential thermal analysis) measurements employs three samples mounted close to each other in a TG furnace. Two of the samples are active ones, i.e. of the material to be analyzed, and the third is a reference sample of an inert material. The first active sample is suspended from the beam of a thermobalance. The change in weight of this sample is recorded and plotted versus the temperature of the second active sample. The sample thermocouple and another identical thermocouple are placed in contact with crucibles containing the second active sample and the reference material, respectively. The differential temperature between the sample and the reference material is taken from the two identical thermocouples. The differential signal is amplified and plotted against the temperature of the second active sample.
    Type: Grant
    Filed: January 14, 1985
    Date of Patent: August 19, 1986
    Assignee: Her Majesty the Queen in right of Canada, as represented by the Minister of Energy, Mines and Resources
    Inventor: Shaheer A. Mikhail
  • Patent number: 4598660
    Abstract: A device for scaring birds thereby aiding in the prevention of crop destruction due to the birds feeding thereon comprises in combination an actuator, such as an air gun which ejects at increased velocity a gaseous stream in a predetermined path, a frame including a target disposed in an impinging relationship to the gaseous stream path so as to be moved between rest and operative positions responsive to the gaseous stream, and visual scaring member operatively connected to the target for scaring birds, the visual member being reciprocally operable between inactive and active positions in response to the target being moved between the rest and operable position, respectively. According to another embodiment of the present invention, automatic controls are provided for disabling the device during night hours and/or during periods of increased wind velocities which could potentially damage the device.
    Type: Grant
    Filed: March 29, 1984
    Date of Patent: July 8, 1986
    Inventor: Peter Konzak
  • Patent number: 4575257
    Abstract: A thermal shock chamber comprising a test area, a high-temperature air conditioning unit having a gas outlet and a gas inlet adjacent to the test area, an outside air supplying unit having an air outlet and an air inlet adjacent to the test area, a low-temperature air conditioning unit having a gas outlet and a gas inlet adjacent to the test area, a first damper assembly for opening the outlet and the inlet of one of the high-temperature air conditioning unit and the outside air supplying unit and closing the outlet and the inlet of the other unit at the same time, and a second damper assembly for opening the outlet and the inlet of one of the low-temperature air conditioning unit and the outside air supplying unit and closing the outlet and the inlet of the other unit at the same time.
    Type: Grant
    Filed: March 1, 1984
    Date of Patent: March 11, 1986
    Assignee: Tabai Espec Corp.
    Inventors: Toichi Ogura, Ikuo Kanamori, Keiichi Murano
  • Patent number: 4531407
    Abstract: A fuel gauge includes a stationary capacitor located within a fuel tank in such a manner as to be partially immersed in the fuel so that the capacitance of the capacitor varies with the level of fuel. A measuring device determines the capacitance of the capacitor to measure the level of the fuel or the amount of fuel remaining within the tank.
    Type: Grant
    Filed: December 19, 1983
    Date of Patent: July 30, 1985
    Assignee: Nissan Motor Company, Limited
    Inventor: Hiroshi Kobayashi
  • Patent number: 4530160
    Abstract: A multicoordinate sensing head is disclosed which includes a sensing pin and a tappet. Both the sensing pin and the tappet define respective 90.degree. conical recesses which serve to capture a ball therebetween. This arrangement converts both axial and radial movement of the pin into axial movement of the tappet at a constant 1:1 ratio. A position measuring system is used to measure the axial position of the tappet. This position measuring system therefore can be used to measure both axial and radial deflection of the sensing pin. The sensing pin is mounted in the sensing head by means of an axial guide and a two-dimensional guide such that the axis of the sensing pin is maintained parallel to the axis of the tappet. This arrangement allows simultaneous radial and axial deflections of the sensing pin.
    Type: Grant
    Filed: September 12, 1983
    Date of Patent: July 23, 1985
    Assignee: Johannes Heidenhain GmbH
    Inventor: Kurt Feichtinger
  • Patent number: 4523450
    Abstract: This invention contemplates a rapid method of calibrating probe-pin combinations, such as star probes or rotary-swing probes, which method is applicable when the probe system forms part of or is coupled to the control system of a measuring machine wherein a self-centering probe of workpieces is possible. The calibration procedure employs a calibration standard having a plurality of probe-centering elements distributed over its surface and facing in different directions, the positional geometry of these elements being stored in the computer of the measuring machine. Each of the individual probe balls is successively introduced into a centering element which is accessible. Thereupon, the position of each ball-center point is determined in the computer, from the stored positional data and the pre-established diameter of corresponding probe balls.
    Type: Grant
    Filed: September 20, 1982
    Date of Patent: June 18, 1985
    Assignee: Carl-Zeiss-Stiftung, Heidenheim/Brenz
    Inventor: Klaus Herzog
  • Patent number: 4518137
    Abstract: Liquid hydrogen stored aboard a space vehicle, and constituting a fuel for use in the vehicle's main rocket motor, is introduced, in a gaseous state, into an inflatable aerodynamic braking member, for moving it from a collapsed stored position outwardly into an inflated operational position. Such member provides a large area braking surface which extends generally laterally outwardly from the space vehicle. During reentry the space vehicle is oriented to reenter nozzle end first. Fuel is consumed within the rocket motor to produce gases which are discharged out through the rocket nozzle to provide a cooling layer of gases forwardly of the large area braking surface. A space vehicle equipped with such an aerodynamic braking system is operated to reenter into the atmosphere. The drag produced by the braking member slows the space vehicle down and then the space vehicle is set into a low earth orbit.
    Type: Grant
    Filed: November 1, 1979
    Date of Patent: May 21, 1985
    Assignee: The Boeing Company
    Inventor: Dana G. Andrews
  • Patent number: 4488280
    Abstract: The player is provided with a pair of spaced apart spine latching members which hook up with an inner record retaining spine as a disc record caddy is inserted into the player so that when the outer sleeve is withdrawn, the record/spine assembly is retained inside the player. A selected one of the spine latching members is equipped with a moveably mounted overtravel member which precludes the selected latching member from capturing the spine until the other latching member is also in position to latch up the spine. A connecting member rigidly intercoupling the latching members precludes the other latching member from capturing the spine until both latching members are ready to latch up the spine to ensure simultaneous latching of the spine.
    Type: Grant
    Filed: September 27, 1983
    Date of Patent: December 11, 1984
    Assignee: RCA Corporation
    Inventor: Robert W. Jebens
  • Patent number: 4486871
    Abstract: A continuous repeating type simplified sound reproducing device including on its casing, a fixed locking lever having a locking face parallel to the plane of rotation of a record disc and a rotating locking lever on the record disc which rotates together with the record disc and is able to enter under the locking face of the fixed locking lever only when the record disc is placed at its retracted position. At least one of the locking faces of the two locking members are arranged to have a face length corresponding to the angle of rotation sufficient to maintain the record disc at its retracted position until the record disc has completely returned to the starting point of sound reproduction. By virtue of this construction, satisfactory returning motion of this continuous repeating type sound reproduction device can be assured by a comparatively simplified construction.
    Type: Grant
    Filed: January 6, 1984
    Date of Patent: December 4, 1984
    Assignee: Ozen Corporation
    Inventor: Eishi Koike
  • Patent number: 4482115
    Abstract: The invention is an improved flight control system for aircraft. The improved flight control system mixes or blends several flight control movements into a unified operation. The flight control mixing system of this invention combines the functions of standard ailerons (a roll and lateral control device) with standard flaps (a lift control device) on aircraft into a single control device, referred to herein as flaperons. The improved system can also be used on tailess or flying wing type aircraft to combine the functions of standard ailerons with the elevator functions (a nose up or down pitch control device) into a single control device, referred herein as elevons. The improved system is also applicative to V-tail type aircraft for controlling the elevators in a similar single control operation, herein referred to as ruddervators.
    Type: Grant
    Filed: May 4, 1981
    Date of Patent: November 13, 1984
    Inventor: John Lassiter, Jr.
  • Patent number: 4476717
    Abstract: Apparatus is disclosed for controlling a pair of transverse scanning gauges disposed along the length of a moving sheet of material whereby continuous same-spot measurements of the material may be made irrespective of any variations in the speed of the material even as it traverses the distance between the scanning gauges.
    Type: Grant
    Filed: May 22, 1981
    Date of Patent: October 16, 1984
    Inventor: Richard F. Murphy
  • Patent number: 4474344
    Abstract: A compression-sealed door assembly for use in controlling air flow pressure levels within a supersonic jet nacelle inlet, wherein substantially U-shaped strips of resiliently compressible material is compressed between a door and the nacelle inlet to seal air flow passageways through the inlet when the door assembly is pivoted to its fully closed position.
    Type: Grant
    Filed: March 25, 1981
    Date of Patent: October 2, 1984
    Assignee: The Boeing Company
    Inventor: Charles O. Bennett
  • Patent number: 4470568
    Abstract: A method for changing the spin rate of a spinning spacecraft having a dynamic balancing mechanism which utilizes the communications channel between the spacecraft and the receiving terminal, the master index pulse generator on the spacecraft, and the spacecraft axial thrusters. To change the spin rate, a dynamic imbalance of a known wobble angle and phase is introduced by the dynamic balancing mechanism. An axial thruster is then fired for a predetermined time interval thereby coupling a portion of the axial thrust force into the rotational energy of the spinning body.
    Type: Grant
    Filed: September 8, 1980
    Date of Patent: September 11, 1984
    Assignee: Hughes Aircraft Company
    Inventor: Murray J. Nuefeld
  • Patent number: 4467986
    Abstract: A reserve parachute for deployment under low descent speeds includes a rubber ring packed with the canopy and rigging lines and attached to the canopy in the region of the canopy apex and being disposed concentric with respect to a vent hem of the canopy. Upon deployment the ring expands to increase profile drag to ensure the canopy mouth faces substantially downwardly during deployment. The peripheral hem of the canopy at the canopy mouth is stiffened with a tape loop treated with polyurethane so that the peripheral hem springs apart upon deployment. An inhibitor tie is attached to a loop of the folded rigging lines within the pack to permit only a part of the rigging to be released initially; the inhibitor tie breaks at a predetermined tension in the lines to permit the remainder of the rigging lines to be released and to permit fully canopy deployment.
    Type: Grant
    Filed: September 2, 1981
    Date of Patent: August 28, 1984
    Inventors: Stanley A. Birch, Sidney B. Jackson, Eric J. F. Edmonds, Robert V. Gigg, Norman L. Haggert
  • Patent number: 4452410
    Abstract: An aircraft containing aerodynamic and gyroscopic stability that has a high angle of take-off and landing capabilities, with high speed horizontal powered flight, but is also able to sustain power-off flight with auto-rotation of its multiple extending airfoils. The fuselage has the shape of an inverted saucer with aerodynamic configuration and has an open circular track at its periphery; and riding in this track is a rotary frame and extended airfoil assembly that isin-line with the fuselage. Each extending airfoil contains solid weighted bodies at their tips and this rotary frame and extended airfoil assembly is rotated on the track by an internal power unit. The extending airfoils taper toward their tips and these tips have a knife sharp edge for penetrating the air resistance.
    Type: Grant
    Filed: December 18, 1981
    Date of Patent: June 5, 1984
    Inventor: Robert A. Everett
  • Patent number: 4449682
    Abstract: A nacelle mounted directly to and below a wing so as to extend forwardly therefrom. The wing has a critical zone, which includes an area in the airstream flow about the wing where either of the following conditions occur:1. The local pressure coefficient in the airstream has an absolute magnitude greater than 0.05,2. The airstream flow about the airfoil is supersonic.The nacelle has a critical surface region which is a side surface portion of the nacelle adjacent to a forwardly swept portion of the wing. The critical contour area of the nacelle surface is that portion of the critical surface region that is within the critical zone. The critical contour area of the nacelle is shaped to be in alignment with a plurality of airfoil streamlines that are immediately adjacent the critical contour area. Other surface portions of the nacelle are out of alignment with adjacent streamlines and correspond more closely to the engine structure contour.
    Type: Grant
    Filed: December 22, 1980
    Date of Patent: May 22, 1984
    Assignee: The Boeing Company
    Inventors: Louis B. Gratzer, Walter B. Gillette
  • Patent number: 4449680
    Abstract: A nacelle mounted by a pylon above and forwardly of a wing. The wing has a critical zone, which includes an area in the airstream flow about the wing where either of the following conditions occur:1. The local pressure coefficient in the airstream has an absolute magnitude greater than 0.05,2. The airstream flow about the airfoil is supersonic.The nacelle and pylon have a critical surface region which is a lower side surface portion of the nacelle and the contiguous pylon surface adjacent to a forwardly swept portion of the wing. The critical contour area of the nacelle surface is that portion of the critical surface region that is within the critical zone. The critical contour area of the nacelle and pylon are shaped to be in alignment with a plurality of airfoil stream lines that are immediately adjacent the critical contour area. Other surface portions of the nacelle are out of alignment with adjacent stream lines and correspond more closely to the engine structure contour.
    Type: Grant
    Filed: December 22, 1980
    Date of Patent: May 22, 1984
    Assignee: The Boeing Company
    Inventors: Louis B. Gratzer, Walter B. Gillette
  • Patent number: 4449684
    Abstract: This invention relates to an improved satellite servicing system. The improvements include improvements in payload distribution in the cargo bay of the Shuttle Orbiter and improvements in the location of the targets required for positioning end effectors with respect to the component which they are to engage. In the improved satellite servicing system, the remote manipulator system which is normally used for the purpose of capturing and deploying satellites is also used for servicing the satellites when captured and secured for servicing. An improved payload distribution system is provided in the cargo bay which permits optimum utilization of the cargo bay by primary payload units by providing for the location of secondary payload units at any convenient position of opportunity along the length of the cargo bay.
    Type: Grant
    Filed: June 2, 1981
    Date of Patent: May 22, 1984
    Assignee: Spar Aerospace Limited
    Inventor: Charles M. Hinds
  • Patent number: 4449683
    Abstract: A nacelle mounted by a pylon below and forwardly of a wing. The wing has a critical zone, which includes an area in the airstream flow about the wing where either of the following conditions occur:1. The local pressure coefficient in the airstream has an absolute magnitude greater than 0.05,2. The airstream flow about the airfoil is supersonic.The nacelle and pylon have a critical surface region which is an upper side surface portion of the nacelle and the contiguous pylon surface adjacent to a forwardly swept portion of the wing. The critical contour area of the nacelle surface is that portion of the critical surface region that is within the critical zone. The critical contour area of the nacelle and pylon are shaped to be in alignment with a plurality of airfoil streamlines that are immediately adjacent the critical contour area. Other surface portions of the nacelle are out of alignment with adjacent streamlines and correspond more closely to the engine structure contour.
    Type: Grant
    Filed: December 22, 1980
    Date of Patent: May 22, 1984
    Assignee: The Boeing Company
    Inventors: Louis B. Gratzer, Walter B. Gillette
  • Patent number: 4449681
    Abstract: A nacelle mounted directly to and above a wing so as to extend forwardly therefrom. The wing has a critical zone, which includes an area in the airstream flow about the wing where either of the following conditions occur:1. The local pressure coefficient in the airstream has an absolute magnitude greater than 0.05,2. The airstream flow about the airfoil is supersonic.The nacelle has a critical surface region which is a side surface portion of the nacelle adjacent to a forwardly swept portion of the wing. The critical contour area of the nacelle surface is that portion of the critical surface area that is within the critical zone. The critical contour region of the nacelle is shaped to be in alignment with a plurality of airfoil streamlines that are immediately adjacent the critical contour area. Other surface portions of the nacelle are out of alignment with adjacent streamlines and correspond more closely to the engine structure contour.
    Type: Grant
    Filed: December 22, 1980
    Date of Patent: May 22, 1984
    Assignee: The Boeing Company
    Inventors: Louis B. Gratzer, Walter B. Gillette