Patents Assigned to The Cessna Aircraft Company
  • Patent number: 5469830
    Abstract: The system is an on-board and in-line system for blending two fuels of known characteristics to achieve instantaneous in-line change in the octane rating of fuel flowing to the engine. The blending system provides a means of precise in-line blending of two reference fuels in an on-board aircraft or land vehicle installation. Based on appropriate calibration blending curves, the system will provide instantaneous indications of both lean and rich performance ratings of the fuel. Instantaneous lean and rich performance ratings of the blended fuel streams may be recorded concurrently with engine parameters and ambient test data, and with combustion knock severity numbers derived from the previously mentioned detonation indication system.
    Type: Grant
    Filed: February 24, 1995
    Date of Patent: November 28, 1995
    Assignee: The Cessna Aircraft Company
    Inventor: Cesar Gonzalez
  • Patent number: 5433586
    Abstract: An aircraft variable pitch propeller blade utilized in subsonic flight at relatively slow turning applications with relatively high power coefficients. The blade in plan form is tapered at both ends with the maximum chord approximate the mid station of the blade, the leading edge of the blade being swept behind the longitudinal axis of the blade near its tip and the trailing edge is convex and essentially straight from its maximum chord outward to the tip.
    Type: Grant
    Filed: May 3, 1993
    Date of Patent: July 18, 1995
    Assignee: Cessna Aircraft Company
    Inventor: Gregory M. Cole
  • Patent number: 5209643
    Abstract: An aircraft propeller blade utilized in subsonic flight at relatively slow turning applications with relatively high power coefficients. The blade in plan form is tapered at both ends with the maximum chord approximate the 44% percent station of the blade, the leading edge of the blade being swept behind the longitudinal axis of the blade near its tip and the trailing edge is convex and essentially straight from its maximum chord outward to the tip.
    Type: Grant
    Filed: March 27, 1991
    Date of Patent: May 11, 1993
    Assignee: The Cessna Aircraft Company
    Inventor: Gregory M. Cole
  • Patent number: 5137074
    Abstract: The invention is a method of forming a spherical bearing shell comprising an overlay casting process which utilizes a ceramic insert having a semi-spherical close-tolerance outer surface with a casting sprue opening therethrough and lubrication ribs on said outer surface. The ceramic insert is placed within structural bearing housing, defining an overlay cavity therebetween which is then cast with a molten bearing alloy into the sprue opening of the insert to a level above the height of the overlay cavity. The sprue opening is then back-drilled so that the ceramic insert and plug of bearing alloy can be separated from the bearing housing and overlay surface leaving a semi-spherical bearing surface with lubrication grooves cast therein.
    Type: Grant
    Filed: October 9, 1990
    Date of Patent: August 11, 1992
    Assignee: The Cessna Aircraft Company
    Inventor: Cesar Gonzalez
  • Patent number: 5094195
    Abstract: A barrel type internal combustion engine having a plurality of axially-positioned cylinders, with reciprocating pistons, arranged in a circular pattern with a drive shaft supported in a cylinder block in a cantilevered manner by a sleeve bearing and a wobble spider rotatably supported on an offset portion of the drive shaft by a second sleeve bearing. A first roller bearing positioned between the offset portion of the drive shaft and the wobble spider, and another roller bearing at the opposite end of the drive shaft acting in opposition to the first roller between the shaft and the engine block supporting thrust loads.
    Type: Grant
    Filed: April 20, 1990
    Date of Patent: March 10, 1992
    Assignee: The Cessna Aircraft Company
    Inventor: Cesar Gonzalez
  • Patent number: 5090378
    Abstract: A fuel-injection system for a stratified charge hybrid internal combustion engine including a main combustion chamber and prechamber, fuel injectors in both the main chamber and the prechamber which open at higher and lower pressure levels respectively to sequentially inject fuel into the prechamber and main chamber. The system also includes a timed-spark ignition means in the prechamber and an engine-driven and timed fuel injection pump having a variable output capacity which varies with the power level requirements, the injection pump being supplied by a low pressure charge pump.
    Type: Grant
    Filed: February 22, 1991
    Date of Patent: February 25, 1992
    Assignee: The Cessna Aircraft Company
    Inventor: Cesar Gonzalez
  • Patent number: 4765293
    Abstract: A low compression reciprocating internal combustion piston engine with a prechamber in the head connected to a main combustion chamber in the piston, the prechamber having an igniter, a pilot fuel injector and connecting lineal passage; the main chamber including a fuel injector for mixing the prechamber gases with the gases being compressed in the cylinder. The engine is a hybrid having transitional combustion modes from spark-ignited stratified charge mode at low power, to a spark-assisted compression ignition at higher power loads, and a strictly compression ignition mode at maximum power loads.
    Type: Grant
    Filed: May 7, 1986
    Date of Patent: August 23, 1988
    Assignee: The Cessna Aircraft Company
    Inventor: Cesar Gonzalez
  • Patent number: 4736672
    Abstract: A lockout valve in a hydraulic system which meters the flow thereacross in accordance with the actuation pressure applied.
    Type: Grant
    Filed: April 7, 1986
    Date of Patent: April 12, 1988
    Assignee: Cessna Aircraft Company
    Inventor: Robert M. Diel
  • Patent number: 4723476
    Abstract: A regenerative valve which includes a valve body having a bore therein intersected by first and second control passages connected respectively to a four-way directional control valve; the bore is also intersected by first and second cylinder control cavities connecting with the head end and rod end respectively of a double-acting cylinder; a check valve poppet is seated in said bore blocking flow to the head chamber of the cylinder. A shuttle spool is also positioned in said bore and is movable between a first working position allowing the cylinder to retract its piston and a regeneration position opening flow across the first and second cylinder control cavities while blocking flow to the second control passage. The shuttle spool engages the poppet member in its regeneration position causing the poppet to open a flow path from the first control passage to the first cylinder control cavity and thereby allow regeneration flow.
    Type: Grant
    Filed: February 22, 1982
    Date of Patent: February 9, 1988
    Assignee: The Cessna Aircraft Company
    Inventor: Dennis J. Stucky
  • Patent number: 4723478
    Abstract: A self-leveling series type hydraulic system including boom and bucket valves which separately control boom and bucket cylinders and a flow divider valve positioned in the exhaust flow path from the rod end of the boom cylinder. The flow divider valve splits the flow sending a portion of it to the cap end of the bucket cylinder so as to maintain the bucket in a level condition during raising of the boom with the remaining flow returning to the control valve downstream of the boom valve along with the return flow from the rod end of the bucket cylinder which is also returned to the control valve downstream of the boom valve whereby the bucket valve can be separately actuated concurrent with the boom valve and supplied with oil so as to override the self-leveling function if desired.
    Type: Grant
    Filed: February 4, 1983
    Date of Patent: February 9, 1988
    Assignee: The Cessna Aircraft Company
    Inventors: Robert M. Diel, Robert W. Calvert
  • Patent number: 4709618
    Abstract: A self-leveling series type hydraulic system including boom and bucket valves which separately control boom and bucket cylinders and a flow divider valve positioned in the exhaust flow path of the rod end of the boom cylinder. The flow divider valve splits the flow sending a portion of it to the cap end of the bucket cylinder so as to maintain the bucket in a level condition during raising of the boom with the remaining flow connected to one of the boom valve motor ports. An improved boom lower circuit which bypasses the flow divider valve as the boom is lowered to achieve a faster boom lower rate and the inclusion of an unloading valve in the bucket circuit which includes the dual function of preventing cavitation and relieving high pressure.
    Type: Grant
    Filed: October 2, 1985
    Date of Patent: December 1, 1987
    Assignee: The Cessna Aircraft Company
    Inventor: Dwight E. Zongker
  • Patent number: 4666125
    Abstract: A normally closed high pressure solenoid valve structure including a plunger pin spring-urged against a composite valve seat having a steel reinforcing ring positioned against the seat and backed up by a fixed spacer. The seat has a projecting neck with orifice. The steel reinforcing ring surrounds and contains any radial movement of the seat which is of elastic material softer than the plunger pin which provides a very low leakage level across the valve from either direction. A lost-motion connection between the plunger pin and the solenoid armature provides that the spring load on the plunger pin is retained even with cold flow of the seating material during cycling.
    Type: Grant
    Filed: February 14, 1986
    Date of Patent: May 19, 1987
    Assignee: The Cessna Aircraft Company
    Inventors: Maynard W. Marts, Michael F. Mendoza
  • Patent number: 4655250
    Abstract: An unloading valve utilized in an open center hydraulic system in conjunction with a conventional open center control valve having an open center passage and a dead end power passage; the unloading valve is supplied by a system pressure from a pump and divides the pump flow into two paths in a set proportion regardless of the amount of flow or pressure levels in either flow path, one flow path is directed to reservoir with the other flow path directed to the open center passage in the directional control valve while the dead end power passage of the control valve is separately provided with system pump pressure in a parallel path whereby only a portion of the pump discharge passes across the open center passage when the directional control valve is neutrally positioned.
    Type: Grant
    Filed: February 3, 1986
    Date of Patent: April 7, 1987
    Assignee: The Cessna Aircraft Company
    Inventor: Alan C. Jackson
  • Patent number: 4648798
    Abstract: A variable pitch propeller, particularly suited for use with turbine engines, includes a range of beta control in low pitch and reverse pitch positions, in which the pilot can obtain a ground angle range with substantially lower angles in relation to the flight idle position. This is accomplished by the provision of lost motion connections in the form of sliding sleeves mounted on the beta feedback rods which come into operation at a particularly defined low pitch angle, under control of the pilot, and permits the blades to move to a still lower pitch angle for ground operations, by providing for relative movement between the blade yoke and the beta feedback rods.
    Type: Grant
    Filed: May 1, 1985
    Date of Patent: March 10, 1987
    Assignee: The Cessna Aircraft Company
    Inventor: Walter B. Voisard
  • Patent number: 4642028
    Abstract: A variable pitch propeller is provided with a blade cuff, with a radially inner portion of the cuff formed in closely surrounding relation to the cylindrical shank of the blade, and with a nose portion of the cuff extending radially outwardly and smoothly flaring to the full cordwise dimension of the cuff, through the conventional blade opening in a spinner. The arrangement eliminates regions for ice entrapment or build-up, and permits a heater boot to be applied to the leading edge down to or even into the blade opening.
    Type: Grant
    Filed: April 2, 1984
    Date of Patent: February 10, 1987
    Assignee: The Cessna Aircraft Company
    Inventors: William C. Buckman, Michael R. Tapp
  • Patent number: 4624445
    Abstract: The invention is a lockout valve used in a hydraulic circuit to prevent leakage in a static condition; the lockout valve does not require outside force to hold the lockout open once flow across the lockout is established due to the positioning of an orifice ring around the poppet upstream of the poppet seat with the closing area acting on the poppet in conjunction with a spring which senses the pressure downstream of the orifice ring so that when there is sufficient flow across the orifice ring, the force created by the opening area on the poppet, which is located upstream of the orifice ring, will exceed the combined force of the spring and the closing area so that the lockout valve will remain open without an outside force so long as sufficient flow is maintained across the poppet.
    Type: Grant
    Filed: September 3, 1985
    Date of Patent: November 25, 1986
    Assignee: The Cessna Aircraft Company
    Inventor: Richard C. Putnam
  • Patent number: 4594976
    Abstract: A low compression reciprocating internal combustion piston engine with a prechamber in the head connected to a main combustion chamber in the piston, the prechamber having an igniter and a pilot fuel injector; the main chamber including a fuel injector and a ramp for mixing the prechamber gases with the gases being compressed in the cylinder. The engine is a hybrid having transitional combustion modes from spark-ignited stratified charge mode at low power, to a spark-assisted compression ignition at higher power loads, and a strictly compression ignition mode at maximum power loads.
    Type: Grant
    Filed: March 18, 1985
    Date of Patent: June 17, 1986
    Assignee: The Cessna Aircraft Company
    Inventor: Cesar Gonzalez
  • Patent number: 4561342
    Abstract: A self-leveling series type hydraulic system with a float position including boom and bucket valves which separately control boom and bucket cylinders and a flow divider valve positioned in the exhaust flow path from the rod end of the boom cylinder. The flow divider valve in one position splits the flow sending a portion of it to the cap end of the bucket cylinder so as to maintain the bucket in a level condition during raising of the boom with the remaining flow returning to the control valve downstream of the boom valve whereby the bucket valve can be separately actuated concurrent with the boom valve and supplied with oil so as to override the self-leveling function if desired. The flow divider valve having a second position which bypasses all of the flow from the boom cylinder to reservoir when the boom control valve is in a float position.
    Type: Grant
    Filed: July 25, 1983
    Date of Patent: December 31, 1985
    Assignee: The Cessna Aircraft Company
    Inventor: Robert W. Calvert
  • Patent number: 4545287
    Abstract: A metering lockout check valve which lowers gravity loads without chatter. The poppet has a conical concave face which surrounds an annular seat and is shaped so that as the poppet opens, the effective closing force increases requiring higher pressures in the opposite motor port to open the poppet. Conversely an overrun condition is prevented since when the pressure drops in the pump pressure side of the circuit, the poppet will reduce its opening and provide a metering function.
    Type: Grant
    Filed: October 22, 1982
    Date of Patent: October 8, 1985
    Assignee: The Cessna Aircraft Company
    Inventor: Alan D. Jackson
  • Patent number: D302220
    Type: Grant
    Filed: December 29, 1986
    Date of Patent: July 18, 1989
    Assignee: The Cessna Aircraft Company
    Inventors: Mark S. Blair, Melvin S. Nichols, James A. Bertram, Jeffrey B. Saltz