Patents Represented by Attorney John J. Sullivan
  • Patent number: 4380070
    Abstract: A hand held apparatus for automatically identifying a hybrid or monolithic integrated circuit or any standard circuit module having a known pin configuration (10) and an unknown identity. A plurality of test instructions (FIG. 6 ) for devices of known identity are stored in a test procedure memory (22) and sequentially provided (125) to the unit under test until the unit either passes a test thus revealing its identity (137) or fails all tests in the memory (145). The socket (10) is connected to a pair of peripheral chips (25a, 25b) having pin definable input/output ports (46, 65, 66) which are used selectively to treat any pin as input, output, or supply.
    Type: Grant
    Filed: February 17, 1981
    Date of Patent: April 12, 1983
    Assignee: Lockheed Corporation
    Inventor: William G. Steiner
  • Patent number: 4375614
    Abstract: A power supply (17) having a regulator featuring a series pass transistor (150) connected as a common collector amplifier is shown. The power supply is turned on and off by switching devices (11, 151, 160, 159) which control base current only to a transistor switch (155, 170) operating analog circuitry (157) which controls the pass transistor. Microcomputer control (181) of the power supply and self latching embodiments are also shown. The power supply shown herein can successfully regulate output voltages which differ from the raw DC input by no more than the saturation voltages of series pass transistor.
    Type: Grant
    Filed: April 6, 1981
    Date of Patent: March 1, 1983
    Assignee: Lockheed Corporation
    Inventor: William G. Steiner
  • Patent number: 4336595
    Abstract: This is an electronic device which determines the fatigue life of a structure and its crack growth characteristics when subjected to repeated loading by using the signal from an electrical resistance type strain gage secured to the structure to provide the input to a processor which monitors cyclic excursions, calculates the fatigue and fracture structural damage from those excursions, stores the cumulative damage, and displays that damage on command.
    Type: Grant
    Filed: June 26, 1981
    Date of Patent: June 22, 1982
    Assignee: Lockheed Corporation
    Inventors: Thomas E. Adams, Walter D. Murray, Raymond F. Woolf
  • Patent number: 4327152
    Abstract: A protective coating to retard crack growth in aluminum and aluminum alloys has particular utility when applied to the surfaces of structural parts of aircraft providing a crack growth inhibitor to a crack surface when and as it develops in such parts. This inhibitor is a compound having a vapor pressure high enough to volatilize the inhibitor and emit molecules which will react with the surface of the metal to form a protective film. It is blended within a selected primer and is thereby available for interaction with the surface and tip of any crack which may initiate beneath the primer. A topcoat of low-permeability polyurethane covers the inhibitor-reinforced primer to prevent escape of the inhibitor from the primer.
    Type: Grant
    Filed: September 29, 1980
    Date of Patent: April 27, 1982
    Assignee: Lockheed Corporation
    Inventors: Robert N. Miller, Richard L. Smith
  • Patent number: 4317121
    Abstract: A flush-mounted HF (2 to 30 megahertz) transmitting and receiving antenna is developed which is especially suitable for installation on a Jeep (CJ7) type vehicle. This antenna is formed by bonding a copper strip to the inside surface of the non-metallic top of the vehicle. The strip is grounded to the vehicle body just aft of the driver's door and runs overhead to the aft right lower corner of the non-metallic vehicle top which becomes the feed point for the antenna. The strip is connected in two places to an isolated aluminum skin bonded to the top of the vehicle. The antenna is suitable for use as a transmitting antenna provided an impedance matching device (coupler) is inserted between the antenna and the transmitter/receiver.
    Type: Grant
    Filed: February 15, 1980
    Date of Patent: February 23, 1982
    Assignee: Lockheed Corporation
    Inventors: William P. Allen, Jr., Benjamin S. Zieg
  • Patent number: 4310390
    Abstract: A process is described for sealing anodic coatings on aluminum and the alloys of aluminum while simultaneously impregnating the anodic coating with organic resin during the sealing operation, thereby providing a protective coating to the anodized aluminum which, among other things has superior corrosion resistant characteristics.A specified water-borne resin coating material possessing excellent stability at temperatures in excess of 200.degree. F. is used to convert the unsealed anodic coating to the monohydrate/trihydrate form of aluminum oxide during the sealing step of an otherwise conventional aluminum anodizing process. Subsequently, the sealed anodic film is cured at temperatures up to 500.degree. F. This process provides a total protection system having characteristics superior to separately sealed and organically primed aluminum obtained through conventional processing.
    Type: Grant
    Filed: June 27, 1980
    Date of Patent: January 12, 1982
    Assignee: Lockheed Corporation
    Inventors: Robert E. Bradley, William R. Keithler
  • Patent number: 4291850
    Abstract: This shock absorber strut incorporates an annular piston between the lower and upper bearings of the shock absorber piston; together with a separator piston in the bore of the shock absorber piston. The volume below the separator piston is filled with hydraulic fluid and is connected to an external hydraulic power source. An external hydraulic power source is also connected between the annular piston and the shock absorber lower bearing. Application of external hydraulic pressure to the underside of the annular piston, while simultaneously draining off fluid below the separator piston, causes the shock absorber to contract. The volume vacated by the fluid below the separator piston provides a reservoir for displaced shock absorber fluid which pushes the separator piston down the bore of the shock absorber piston. The contracted strut is then locked hydraulically. The procedure is reversed for shock absorber extension.
    Type: Grant
    Filed: March 19, 1979
    Date of Patent: September 29, 1981
    Assignee: Lockheed Corporation
    Inventor: Wilbert Sharples
  • Patent number: 4291404
    Abstract: A battery operated microcomputer controlled programmable circuit testing device. Standard I/O/memory devices (25a, 25b) are connected to a microcomputer (20) in such a manner as to treat the I/O ports (46, 47) of the I/O memory devices as programmable interfaces and to allow pin receptors in a socket (10) to be individually programmed as inputs or outputs. Double detent switches (12, 13) connected to testable inputs T0, T1, 45) the microcomputer are used to scroll a roll table containing names of devices which may be tested in either a forward or a reverse direction at two different speeds. Compression of the roll table storage is provided by storing only data which differs from the previous element. A power supply (17) having a regulator featuring a series pass transistor (150) connected as a common collector amplifier is shown.
    Type: Grant
    Filed: November 20, 1979
    Date of Patent: September 22, 1981
    Assignee: Lockheed Corporation
    Inventor: William G. Steiner
  • Patent number: 4256012
    Abstract: A launching mechanism for missiles from aircraft is defined which eliminates the need for changing the missiles from a transport position to a launch position and which employs the force of gravity as the motive force for launching. Missiles are suspended from carriage assemblies which incorporate an ejector mechanism, power sources, power actuators and trigger/safety devices. Each carriage/missile unit is installed in a transport module which can be configured to contain an array of missiles. One or more transport modules are installed in the aircraft cargo compartment aligned with each other and an acceleration module, all such modules being secured to the compartment floor and to each other. The acceleration module is the aftmost unit of the launcher system, serving as a transition unit for each missile from the transport modules to the release position and as an acceleration unit for each missile just before it leaves the aircraft.
    Type: Grant
    Filed: November 20, 1978
    Date of Patent: March 17, 1981
    Assignee: Lockheed Corporation
    Inventors: William L. Cowart, Cropper W. Holland, Jr., Don R. Scarbrough, Sr.
  • Patent number: 4247063
    Abstract: Retractable wing-tip mounted vanes are actuated from the normal cockpit controls of an airplane to provide both roll control and direct lift control. When not required, these devices retract into wing fairings. Simple to manufacture and operate, these controls permit reduced manufacturing costs through much simpler wing construction. The vanes consist of suitably constructed plates that slide over one another and which form an end plate to the wing when fully deployed. Asymmetric deployment produces an out-of-balance moment in roll; symmetric deployment induces direct lift by increasing wing lift on both wing panels.
    Type: Grant
    Filed: August 7, 1978
    Date of Patent: January 27, 1981
    Assignee: Lockheed Corporation
    Inventor: Michael W. Jenkins
  • Patent number: 4245192
    Abstract: A circuit for high speed testing of the periodicity of an alternating signal (60) independently of signal amplitude. A bistable multivibrator (128) changes state in response to each positive slope zero-crossing of the signal and alternately activates each of a pair of integrators (116, 118, 180 and 117, 114, 181) on alternate cycles of the signal. A pair of high speed gated comparators (112, 115) compares the integrator voltages at the end of each pair of cycles. A reference voltage (130) which increases with the number of cycles is provided to maintain a narrow comparator window as the integrator voltages increase.
    Type: Grant
    Filed: October 19, 1978
    Date of Patent: January 13, 1981
    Assignee: Lockheed Corporation
    Inventor: Maurice C. Whiffen
  • Patent number: 4238960
    Abstract: An accelerometer mechanically attached to a machine senses the machine rotor's unbalance and outputs an electrical signal which is indicative of the magnitude and position of the rotor unbalance. A tachometer generator's rotor is mechanically coupled to the machine rotor and outputs an electrical signal delineating the speed and rotational position (with respect to time) of the rotor. By physically indexing one of the tachometer generator rotor poles (north or south) to an index/mark on the engine rotor, the position of the mark at any instant in time is determined. The physical location of the unbalance is obtained by determining the phase relationship of the unbalance signal to that of the tachometer generator signal. This is accomplished by obtaining simultaneous "snapshots" of the two signals employing multiplexing techniques to alternately sample each signal. The signal is then recorded and later reduced by ground equipment.
    Type: Grant
    Filed: November 27, 1978
    Date of Patent: December 16, 1980
    Assignee: Lockheed Corporation
    Inventors: George C. Curtis, Joe A. McInturff, Herbert J. Rubel, William F. Wall
  • Patent number: 4190219
    Abstract: The vortex system behind an aircraft is responsible for more than half of the aircraft drag in cruise flight and sometimes more in other flight conditions. The purpose of the vortex diffuser is to intercept the wing tip vortex just aft of the wing trailing edge, diffuse the trailing vorticity and thereby achieve a reduction in drag. To do this, an airfoil-shaped device is mounted on a trailing boom situated at or near to the wing tip. The airfoil is mounted above the boom at an angle inboard of the vertical. Its height is a percentage of wing semispan as is also the mean airfoil chord.The aft-mounting feature permits greater drag reduction at high subsonic Mach number and the inboard vane cant provides significant structural relief. In addition to drag reduction by diffusing the wing tip vortex, some reduction in trailing vortex hazard is also obtained.
    Type: Grant
    Filed: May 17, 1977
    Date of Patent: February 26, 1980
    Assignee: Lockheed Corporation
    Inventor: James E. Hackett
  • Patent number: 4180224
    Abstract: A series of dispersal nozzles is placed along the wing of an airplane near the hinge line of its edge flap which extends virtually from wing-root to wing-tip and is made up of numerous individual spanwise flap segments. Adjacent flap segments deflect in opposite directions so that a discontinuity exists in the trailing edge and, locally, high turbulence results. By placing the nozzles in this region, and ejecting the dispersants at these points, rapid and controlled distribution of these dispersants is made. This trailing edge flap arrangement is also used as a flight path control device both during and at the end of dispersal passes by the airplane.
    Type: Grant
    Filed: April 6, 1978
    Date of Patent: December 25, 1979
    Assignee: Lockheed Corporation
    Inventor: Dallas M. Ryle, Jr.
  • Patent number: 4175754
    Abstract: An effective seal is provided which fulfills the requirement for a trouble free joint, particularly "V" band joints which are dependent on accurately controlled tube end flanges. Rolled sheet metal flanges are particularly subject to excessive leakages due to deformation during handling and installation. The normal tendency to stop leakage on any joint is by additional torque of the coupling. With the rolled sheet metal flanges, this causes additional deflection of the flange and aggravates the leakage problem rather than reducing it. Furthermore on aircraft environment systems leaks are extremely difficult to pinpoint and time consuming to repair.
    Type: Grant
    Filed: May 8, 1978
    Date of Patent: November 27, 1979
    Assignee: Lockheed Corporation
    Inventor: William E. Wilhelm
  • Patent number: 4167258
    Abstract: A rotary segment aft cargo door for aircraft is geometrically defined by an arcuate slice through the aft fuselage or other nacelle. The door is rotated to an open position, for example and preferably by a cable drive system. The door is suspended by tracks mounted on its inner surface and roller carriages attached to the aft fuselage or nacelle structure. The track and carriage configuration prevents binding as it is a three-point suspension with predetermined clearances in the closed position. Hydraulically actuated interconnected hooks along with lock pins at the pressure door hold the door in the locked position. One-half of the pressure bulkhead is fixed to the aircraft and the other half is carried by the aft cargo door providing automatic pressure door opening with aft cargo door opening. Inflatable pressure seals are used to seal the door in the closed position.
    Type: Grant
    Filed: March 24, 1978
    Date of Patent: September 11, 1979
    Assignee: Lockheed Corporation
    Inventor: Arthur J. Robertson
  • Patent number: 4161301
    Abstract: This apparatus proposes to sequentially deploy stores, such as mines or missiles, from a moving vehicle, such as an airplane or ship, at a predetermined rate and velocity. It includes modular palletized stowage of these stores, limited in size and shape only by vehicle weight and/or space considerations, devices to lock the pallets together and to the vehicle, a cradle to support and facilitate propulsion of the stores prior to launch, a drive mechanism to propel the stores through the pallets, and devices to properly release each store from the vehicle and from its cradle.
    Type: Grant
    Filed: February 27, 1978
    Date of Patent: July 17, 1979
    Assignee: Lockheed Corporation
    Inventors: Richard G. Beardsley, Norman S. Currey
  • Patent number: 4132376
    Abstract: A ball joint connection for the torque scissors of aircraft landing gear provides realignment of the scissors during stroking of the piston to avoid the usual distortion and wearing of parts in the conventional straight pin hinge. Quick disconnect of the scissors for aircraft towing is accomplished through the simple expediency of rotating the ball portion of the scissors design, upon which two diametrically opposed flats have been machined. The scissors can thereby be easily and quickly disconnected prior to towing and then reconnected for the torque transfer operation. As an added feature a ball rotating and locking device is provided as an integral part of the scissors assembly.
    Type: Grant
    Filed: September 12, 1977
    Date of Patent: January 2, 1979
    Assignee: Lockheed Corporation
    Inventor: Wilbert Sharples
  • Patent number: 4113061
    Abstract: This automatic lubricator is an adaption of sound hydraulic principle, that is the application of lubricant over a sustained time period by pressure in the lubricant. The novel feature is that the design permits readily available pressure from a service gun to be directly responsible for the pressure application, which is then trapped in the device, and made to feed out slowly to the surfaces requiring lubrication. Also, included in the preferred form of the device is a gage to indicate visually the quantity of lubricant within the device.
    Type: Grant
    Filed: January 17, 1977
    Date of Patent: September 12, 1978
    Assignee: Lockheed Corporation
    Inventor: Bertram Anthony Peaster
  • Patent number: 4112355
    Abstract: The tapered fastener system is one of the more reliable fastener systems for assuring the longevity of connected members, especially like those found in aircraft, which are subjected to stresses on the order of 20,000 psi and up. However, in order to achieve such joint longevity, a high quality installation of the tapered fastener has been determined to be necessary. The three areas which are the most critical to such an installation are: hole finish, fastener-to-hole bearing contact, and interference fit of fastener in hole.The apparatus herein proposed evaluates these three factors to determine if the necessary quality level has been attained in the fabrication of the fastener and in hole preparation prior to actual installation. To this end this apparatus includes a probe and receptacle, simulating the fastener and hole respectively in conjunction with a computer and display box to electronically and instantaneously determine hole condition and comparative fastener-to-hole bearing and interference.
    Type: Grant
    Filed: October 22, 1976
    Date of Patent: September 5, 1978
    Assignee: Lockheed Corporation
    Inventors: Harry S. Gibson, Jr., Charlie Gene Trevillion