Patents Assigned to Grumman Aerospace Corporation
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Patent number: 5315272Abstract: A light emitting tunnel diode oscillator comprising a body of single crystalline material having a first portion n-doped and a second portion p-doped in such a way that the resulting p-n junction has the low voltage conductance characteristics of a tunnel diode as well as characteristics of light emission.The light emitting tunnel diode oscillator comprises a plurality of alternately layered n-doped portions and p-doped portions.a light emitting tunnel diode oscillator wherein said first n-doped portion and said second p-doped portion are formed to have a thickness corresponding to an integral number of desired wave lengths.Type: GrantFiled: April 26, 1993Date of Patent: May 24, 1994Assignee: Grumman Aerospace CorporationInventor: William E. VonWicklen
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Patent number: 5315147Abstract: An integrated circuit wafer is formed as a monolithic focal plane array having signal processing circuitry formed upon a first surface thereof and infrared detector elements formed upon a second surface thereof. A process for forming the same is also disclosed. The wafer has an array of waffle-like hollows formed upon one surface. The floor of each hollow has a dense array of small diameter vias formed thereon. The vias extend through the wafer to the second surface thereof. Conductive conduits are formed through the hollows and vias to connect infrared detectors on the second side of the wafer to their associated signal processing circuitry formed upon the first side of the wafer.Type: GrantFiled: September 25, 1989Date of Patent: May 24, 1994Assignee: Grumman Aerospace CorporationInventor: Allen L. Solomon
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Patent number: 5315620Abstract: An arrangement for detecting quadrature phase errors introduced by a synchronous demodulator between the two quadrature channels, in-phase (I) and quadrature-phase (Q), of a synchronous demodulator, and for correcting for such detected quadrature phase errors without the need for high data sampling rates. During an initial test period, a periodic symmetrical test signal of known frequency is introduced into the synchronous demodulator. During the test period, the output of the synchronous demodulator is integrated over an integer multiple of periods to detect the quadrature phase error introduced by the synchronous demodulator, and an error signal is generated representative of the detected quadrature phase error. During a following period of operation of the synchronous demodulator, the in-phase (I) and quadrature-phase (Q) signals produced by the synchronous demodulator are applied to a quadrature phase error correction network, along with the generated quadrature phase error signal.Type: GrantFiled: May 1, 1992Date of Patent: May 24, 1994Assignee: Grumman Aerospace CorporationInventors: Natalie Halawani, Theodore Koutsoudis, John M. Kowalski
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Patent number: 5313852Abstract: A differential linear actuator is disclosed which minimizes the torque that must be reacted by an input, rotary drive sleeve member. The differential linear actuator includes an actuator housing within which the drive sleeve is rotatably mounted. An intermediate actuating member is concentrically mounted between the actuator housing and the drive sleeve and is connected to the drive sleeve through a spline connection such that rotation of the drive sleeve results in rotation of the intermediate actuator member. In addition, due to the spline connection and a rotary to linear connection assembly between the intermediate actuator member and the actuator housing, rotation of the intermediate actuator member results in axial displacement of the member relative to the actuator housing.Type: GrantFiled: November 6, 1992Date of Patent: May 24, 1994Assignee: Grumman Aerospace CorporationInventor: Aldo Arena
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Patent number: 5312070Abstract: A segmented variable sweep wing for an aircraft has a plurality of wing segments. A structural device movably affixes the wing segments to the fuselage of the aircraft adjacent each other at their root areas. The structural device moves the segments conjointly to a power position where the segments are perpendicular to the fuselage and spaced from each other. The structural device also moves the segments conjointly to a cruise position wherein the segments are swept back at an angle with the fuselage and in abutment with each other thereby forming a unitary continuous surface airfoil.Type: GrantFiled: April 2, 1992Date of Patent: May 17, 1994Assignee: Grumman Aerospace CorporationInventor: Aldo Arena
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Patent number: 5313214Abstract: Scaled multiple function non-linear FM waveforms are generated for use in digitally implemented low frequency radar. The non-linear FM waveforms are generated by combining a plurality of functions, each having varying characteristics, to form a single waveform which has the desirable characteristics of weighted linear FM waveforms without the undesirable attributes due to weighting. Accordingly, the use of the non-linear FM waveform results in an increase in detection range of eight percent over existing linear FM waveforms with no degradation in range resolution.Type: GrantFiled: April 8, 1993Date of Patent: May 17, 1994Assignee: Grumman Aerospace CorporationInventors: Robert F. Graziano, Russell Singer
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Patent number: 5309724Abstract: In a normal mode, a primary heat exchanger for heated bleed airflow is situated upstream of an aircraft air conditioner compressor. A secondary heat exchanger is located downstream of the compressor. In response to hot and humid environmental conditions, three-way switching valves reposition the primary heat exchanger downstream of the compressor. The result will be the reduction of heat exchange exit temperature, which translates into lower turbine inlet and outlet temperatures at satisfactory airflow rates.Type: GrantFiled: September 16, 1992Date of Patent: May 10, 1994Assignee: Grumman Aerospace CorporationInventors: Melvin Schreiber, Richard Yurman
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Patent number: 5311191Abstract: A calibration reference target fixture is mounted on a pylon having a motorized spline extending longitudinally therethrough. The body of the fixture is teardrop shaped so as to present a low reflection cross section to a transmitting antenna. The reference target itself is a hinge-mounted plate which is driven by cam means connected to the motorized spline for selectively moving the plate between a deployed exposed position and a stored position, within the recess of the fixture body.Type: GrantFiled: November 2, 1992Date of Patent: May 10, 1994Assignee: Grumman Aerospace CorporationInventor: Gerald P. Scannapieco
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Patent number: 5308715Abstract: An aircraft system battery pack is housed in a housing having a removable cover with a window formed therein. A pair of batteries is positioned in the housing. A lamp is mounted in the window of the cover. A pushbutton switch is mounted in the cover and manually depressible from outside the cover. Electrical conductors electrically connect the batteries in series and provide a DC output voltage and electrical conductors electrically connect the batteries in circuit with the lamp and the switch in a manner whereby manual depression of the switch closes the circuit with the batteries and the lamp. The lamp then indicates the power output condition of the batteries.Type: GrantFiled: August 19, 1993Date of Patent: May 3, 1994Assignee: Grumman Aerospace CorporationInventor: Armand J. Aronne
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Patent number: 5307194Abstract: A covert communication system uses ultraviolet light rather than radio waves as a medium for communication. Suitable wavelengths are chosen by examining atmospheric penetration, attenuation by clouds, presence of interfering sources, and ease of generation and detection. The transmitted ultraviolet light may contain both voice information and other data, impressed upon the light by frequency or pulse modulation using a Pockels cell light modulator. A corresponding receiver can be arranged as a transponder to determine range by phase angle differences between transmitted and reflected waveforms. By using an appropriate lens, the receiver can also determine the angle of incidence of a detected ultraviolet signal, and therefore the bearing of the transmitter.Type: GrantFiled: March 24, 1992Date of Patent: April 26, 1994Assignee: Grumman Aerospace CorporationInventors: James J. Hatton, Saulius Janusas
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Patent number: 5303768Abstract: An improved capillary pumped loop evaporator includes circumferential grooves formed in the outer heat exchanger portion of the evaporator. The grooves open to the interface existing between the heat exchanger and a centrally positioned tubular wick. Axially extending vapor channels are formed in the wick and also open onto the interface. The circumferential grooves continuously communicate with the interface and provide a vapor escape to the vapor channels which direct vapor passage from the evaporator. By shortening the vapor path from the interface, a thinner vapor barrier is possible at the interface which results in more efficient heat transfer.Type: GrantFiled: February 17, 1993Date of Patent: April 19, 1994Assignee: Grumman Aerospace CorporationInventors: Joseph P. Alario, Fred Edelstein, Robert L. Kosson, Maria Liandris
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Patent number: 5303881Abstract: Threaded shafts engage threaded fittings at the top and bottom of a pilot's ejection seat. A motorized gear train selectively rotates the threaded shafts so as to adjust the fore-aft position of a seat while maintaining it behind a pre-designed emergency ejection path from a cockpit.Type: GrantFiled: August 21, 1992Date of Patent: April 19, 1994Assignee: Grumman Aerospace CorporationInventor: Armand J. Aronne
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Patent number: 5301903Abstract: An assembly for restraining the upper limbs of an occupant of a seat, particularly an aircraft ejector seat, includes a storage unit which is adapted to be fixedly secured to an upper back portion of the seat. The storage houses a pair of movable cover members and first and second bladder units. The cover members and bladder units are connected by means of straps to a quick release mechanism which mates with a corresponding fitting carried by the occupant and then to a fixed structure adjacent the seat. When it is desired to deploy the restraint assembly, a tension is applied to the straps which causes the cover members to extend around opposite sides and laterally inward of the occupant's body, about respective arms of the occupant, and the bladder units to extend about the occupant's neck. The bladder units are then inflated so as to permit undesirable movement of the occupant's head.Type: GrantFiled: April 6, 1993Date of Patent: April 12, 1994Assignee: Grumman Aerospace CorporationInventor: Armand J. Aronne
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Patent number: 5299762Abstract: A leading edge construction for reducing drag on an airfoil, the construction includes a relatively thin solid plate extending forwardly from the air foil, the plate having an exposed top surface and an exposed bottom surface, and a relatively sharply radiused forward edge forming the leading edge of the air foil. The construction further includes slots adjacent to the top and bottom surfaces of the plates for injecting coolant over the top and bottom surfaces of the plate, toward the leading edge, to provide active cooling of the plate for removing stagnant heat lead.Type: GrantFiled: October 15, 1991Date of Patent: April 5, 1994Assignee: Grumman Aerospace CorporationInventors: Robert L. Kosson, Herbert J. Schneider
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Patent number: 5296712Abstract: A source of neutrons is pulsed. A resultant flow of pulsed neutrons is detected and initiates a time delay. During the time delay, more quickly moving sources of radiation, such as fast and epithermal neutrons as well as gamma rays pass by an imaging device which is not turned on. Accordingly, these sources of noise are not detected. At the end of the time delay, the detecting imaging device is turned on; and during a resulting window interval, the pulsed thermal neutrons are detected and imaged after passage through an intermediately positioned object.Type: GrantFiled: November 12, 1992Date of Patent: March 22, 1994Assignee: Grumman Aerospace CorporationInventor: Frank R. Swanson
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Patent number: 5274904Abstract: Electromagnetic coils of laminated, foil construction are suitable for use in guideways of magnetically-levitated-vehicle systems. The coils are each constructed by applying a double-sided adhesive tape of insulating material to both surfaces of a continuous ribbon of conductive foil to form a tri-layer laminate or matrix. Then, the tri-layer matrix is shaped into a coil of a desired configuration. The coil loops or turns are formed by folding the tri-layer matrix along diagonal fold lines in selected bend regions so as to transpose the top and bottom surfaces of the laminate on either side of the folds, and bring the surface interior of the folds into contact. The insulating material in the laminate is omitted from the interior bend regions, so that, after folds have been made, the interior surfaces in those regions are exposed foil which electrically contact one-another.Type: GrantFiled: August 7, 1991Date of Patent: January 4, 1994Assignee: Grumman Aerospace CorporationInventor: Michael Proise
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Patent number: 5275325Abstract: In a system for superplastic forming and diffusion bonding of metal layers, an inlet fitting is employed which includes a threaded barrel and a headed threaded male connector. The latter is threadingly received within the threaded barrel and creates a positive sealing relationship between the inlet fitting and a sandwich sheet undergoing processing. The inlet fitting has an axial bore formed therethrough to allow evacuation and pressurization of a manifold groove formed between the two sandwich sheets undergoing processing.Type: GrantFiled: December 10, 1992Date of Patent: January 4, 1994Assignee: Grumman Aerospace CorporationInventor: Salvatore J. Stracquadaini
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Patent number: 5275515Abstract: An index-locator pin passes through an aligned hole formed through a drill plate and juxtaposed pack-up and is displaced by a power fastener tool. A gauge pin is transversely positioned within the index-locator pin and pushes the pack-up against a drill plate in response to displacement of the index-locator pin. By maintaining the drill plate in clamping relationship against a multi-layer pack-up, a hole pattern in the drill plate may be replicated in the pack-up with high precision.Type: GrantFiled: June 22, 1992Date of Patent: January 4, 1994Assignee: Grumman Aerospace CorporationInventor: J. Arthur Leifsen
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Patent number: 5265456Abstract: Fatigue lifetime enhancement of the holes formed in structural members occurs by introducing a cold working tool or interference fit fasteners fabricated from shape memory alloy materials. The tool may be employed to expand the wall of a hole while the tool material is raised above the critical transitional temperature. Then, upon lowering the tool material below the critical transitional material, it contracts permitting it to be withdrawn. Bushings and interference fit fasteners may be installed in holes formed in structural members when a shape alloy material bushing or fastener is heated above the critical transitional temperature so that an interference fit results and the hole is cold worked. If the alloy material is not cooled below the critical transitional temperature, the interference fit may be permanently maintained, thereby further enhancing the fatigue life of the members.Type: GrantFiled: June 29, 1992Date of Patent: November 30, 1993Assignee: Grumman Aerospace CorporationInventors: James R. Kennedy, David J. Larson, Jr.
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Patent number: 5264905Abstract: Primary and secondary mirrors constitute a collimator which permit measurements to be made within a reasonably sized equipment enclosure. An incoming laser beam, from a unit undergoing test, has its light dispersed by an integrating sphere from which radiometric measurements may be made. Further, the output from the sphere passes through an avalanche photo diode for detecting laser beam pulse envelopes. These envelopes may be measured for such parameters as pulse width, and interval. A focal plane array camera is provided to measure boresight deviation from the unit undergoing test.Type: GrantFiled: April 27, 1992Date of Patent: November 23, 1993Assignee: Grumman Aerospace CorporationInventors: Paul J. Cavanagh, Jon M. Hoimes, Louis A. Luceri