Patents by Inventor William C. Fischer
William C. Fischer has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 4966526Abstract: A circulation control rotor system for aircraft in which compressed air is directly supplied at generally constant pressure to plenums in the rotor blades and discharged through area controlled slots, the area controlling means involving camming surfaces and being actuated by cyclic, collective, aircraft vibration and flight stability inputs.Type: GrantFiled: July 13, 1989Date of Patent: October 30, 1990Assignee: United Technologies CorporationInventors: Armand F. Amelio, William C. Fischer, Jr.
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Patent number: 4965879Abstract: A complete, computer based, vehicle management system (VMS) for X-Wing aircraft using digital "fly-by-wire" technology controlling many subsystems and providing functions beyond the classical aircraft flight control system. The vehicle management system receives input signals from a multiplicity of sensors and provides commands to a large number of actuators controlling many subsystems. The VMS includes--segregating flight critical and mission critical factors and providing a greater level of back-up or redundancy for the former; centralizing the computation of functions utilized by several subsystems (e.g. air data, rotor speed, etc.); integrating the control of the flight control functions, the compressor control, the rotor conversion control, vibration alleviation by higher harmonic control, engine power anticipation and self-test, all in the same flight control computer (FCC) hardware units.Type: GrantFiled: October 13, 1988Date of Patent: October 23, 1990Assignee: United Technologies CorporationInventor: William C. Fischer, Jr.
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Patent number: 4953098Abstract: In an X-Wing aircraft a dynamic higher harmonic control (HHC) system addresses the vibration which typifies a very rigid rotor and is implemented in two ways--a scheduled HHC and an active HHC. A scheduled HHC is located within the quadruple redundant portion of the flight control computers (FCC). This includes look-up maps for the second through fifth harmonic coefficients of the control equation as a function of airspeed and lift for rotary wing (RW) operation, and as a function of rotor speed for conversion (CV) operation. These are added to the collective and cyclic terms of the control equation and implemented through the pneumatic control valve (PCV) actuators. This flight critical portion of the HHC maintains vibration loads within structural limits. An active HHC, implemented in a dual redundant configuration, is added primarily to enhance vibration control during maneuver conditions and during conversions.Type: GrantFiled: October 13, 1988Date of Patent: August 28, 1990Assignee: United Technologies CorporationInventors: William C. Fischer, Jr., Kenneth C. Arifian
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Patent number: 4890284Abstract: A backup software program is installed in an isolated portion in the memory of at least one of redundant computers. The backup program performs basically the same functions as the prime program but is dissimilarly programmed to prevent a common software error. Switchover to the backup program occurs either automatically in response to monitors, or manually by the operator (i.e. pilot) when he detects an anomaly.Type: GrantFiled: February 22, 1988Date of Patent: December 26, 1989Assignee: United Technologies CorporationInventors: Richard D. Murphy, William C. Fischer
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Patent number: 4750174Abstract: A backup software program is installed in an isolated portion in the memory of at least one of redundant computers. The backup program performs basically the same functions as the prime program but is dissimilarly programmed to prevent a common software error. Switchover to the backup program occurs either automatically in response to monitors, or manually by the operator (i.e. pilot) when he detects an anomaly.Type: GrantFiled: March 22, 1985Date of Patent: June 7, 1988Assignee: United Technologies CorporationInventors: Richard D. Murphy, William C. Fischer
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Patent number: 4691315Abstract: A backup software program is installed in an isolated portion in the memory of at least one of redundant computers. The backup program performs basically the same functions as the prime program but is dissimilarly programmed to prevent a common software error. Switchover to the backup program occurs either autoamtically in response to monitors, or manually by the operator (i.e. pilot) when he detects an anomaly.Type: GrantFiled: March 22, 1985Date of Patent: September 1, 1987Assignee: United Technologies CorporationInventors: Richard D. Murphy, William C. Fischer
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Patent number: 4626998Abstract: A heading trim reference system provides beep commands indicative of a desired heading/attitude change to the roll channel of an AFCS as roll commands at slow speed in a conventional manner, and to the yaw channel as yaw commands at cruise speed. At cruise speed, the yaw synchronizing integrator responds to the beep commands and provides an error signal to existing turn coordination logic to turn the aircraft.Type: GrantFiled: May 2, 1983Date of Patent: December 2, 1986Assignee: United Technologies CorporationInventors: Don L. Adams, Stuart C. Wright, William C. Fischer, David J. Verzella
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Patent number: 4599698Abstract: The directions of travel of an inner and an outer loop actuator are monitored for movement in opposite directions within selected ranges and the outer loop actuator is disabled under selected conditions. These conditions may include movement of both the inner and outer loop actuators in opposite directions, any one of which has been detected moving at a rate greater than a selected rate or to a position outside a selected range. The invention is particularly suited for an aircraft trim actuator shutdown monitor system.Type: GrantFiled: May 2, 1983Date of Patent: July 8, 1986Assignee: United Technologies CorporationInventors: William C. Fischer, Don L. Adams, Stuart C. Wright, David J. Verzella
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Patent number: 4594714Abstract: In a dual actuator system, runaways are identified by comparing the position and rate of one actuator to another. When there is a threshold position discrepancy and a sustained rate discrepancy, a fault is indicated. The faster actuator is identified as the runaway.Type: GrantFiled: May 2, 1983Date of Patent: June 10, 1986Assignee: United Technologies CorporationInventors: William C. Fischer, David J. Verzella, Stuart C. Wright
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Patent number: 4592055Abstract: The sense (direction) of outer-loop commands is compared with the sense (direction) of inner-loop signals in an aircraft AFCS. A disparity in sense indicates an outer-loop failure. To reduce nuisance failures the comparison is made only when inner-loop signal thresholds are exceeded and, in the context of outer-loop commands which are pulses, only at the onset of an outer-loop command and for a limited time thereafter.Type: GrantFiled: May 2, 1983Date of Patent: May 27, 1986Assignee: United Technologies CorporationInventors: William C. Fischer, Stuart C. Wright, David J. Verzella
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Patent number: 4534702Abstract: Quad-redundant signal processors in a flight control computer control valves to modulate airflow in a circulation control rotor system. The valves are arranged in a series and each valve is responsive to two signal processors. Loss of a valve occurs when both signal processors for that valve fail. A first valve, and every fourth valve in the series thereafter is responsive to a first signal processor and a third signal processor. The next valve in the series, and every fourth valve in the series thereafter is responsive to a second signal processor and a fourth signal processor. The third valve in the series, and every fourth valve in the series thereafter is responsive to the first signal processor and the fourth signal processor. The next valve in the series, and every fourth valve in the series thereafter is responsive to the second signal processor and the third signal processor.Type: GrantFiled: December 27, 1983Date of Patent: August 13, 1985Assignee: United Technologies CorporationInventors: Raymond G. Johnson, Jr., Bill L. Trustee, William C. Fischer
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Patent number: 4528628Abstract: An improved PBA shutdown monitor circuit senses collective pitch control position rate of change magnitude and inhibits PBA shutdown in response to the continuous presence of sensed magnitude within a range of selected collective pitch rate magnitudes bounded by a slow rate limit signal value and a fast rate limit signal value.Type: GrantFiled: December 6, 1982Date of Patent: July 9, 1985Assignee: United Technologies CorporationInventors: William C. Fischer, Don L. Adams, Stuart C. Wright, David J. Verzella, Arthur L. Sivigny
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Patent number: 4484283Abstract: In an aircraft automatic flight control system, automatic shutdown (42) of the roll axis thereof (FIG. 1) as a consequence of faults detected therein also provides automatic shutdown of the yaw axis thereof (180) in the same fashion as detection of faults in the yaw axis (171, 167) provides shutdown of the yaw axis. Coupling of the roll axis shutdown into the yaw axis shutdown allows determining which of three axes cause lighting of a single trim shutdown indicator by resetting the yaw shutdown register (145) and simultaneously resetting both the pitch and roll shutdown registers by means of a single cyclic pitch control switch. Automatic yaw trim outer loop and yaw inner loop stability systems are disclosed (FIG. 2).Type: GrantFiled: March 30, 1981Date of Patent: November 20, 1984Assignee: United Technologies CorporationInventors: David J. Verzella, William C. Fischer, Don L. Adams, Stuart C. Wright, Byron Graham, Jr.
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Patent number: 4477876Abstract: In an aircraft automatic flight control system having a reference parameter synchronizing system (70) operable in response to a trim release switch (44), an initial trim release period (139), on the order of a large fraction of a second (137) causes (217, 218) a relatively slow effect trim reference integrator (208, 211) time constant, for smooth transitions of any error signal, followed by a relatively fast (216) effective reference integrator time constant for close, rapid tracking of the reference signal with the actual aircraft parameter.Type: GrantFiled: March 30, 1981Date of Patent: October 16, 1984Assignee: United Technologies CorporationInventors: Stuart C. Wright, Don L. Adams, William C. Fischer, David J. Verzella
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Patent number: 4417308Abstract: In an automatic flight control system, failure of dual inner loop actuators (12, 13) to track position (22, 23) within a permissible tolerance (182) of each other will cause automatic shut down (185, 190) of an outer loop actuator (37) which is responsive (61) to the same proportional signals (54, 55) as are the inner loop actuators. The invention is disclosed in a system in which automatic flight control positioning of the control surfaces of the aircraft is through a fast, limited authority inner loop, the authority of which is centered by repositioning of the outer loop.Type: GrantFiled: March 30, 1981Date of Patent: November 22, 1983Assignee: United Technologies CorporationInventors: Stuart C. Wright, Don L. Adams, William C. Fischer, David J. Verzella
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Patent number: 4392203Abstract: An aircraft automatic flight control system having a roll channel (FIG. 1), a yaw outer loop trim system (bottom of FIG. 2) and a yaw stability inner loop (top of FIG. 2) provides proportional (129) and integral (114) lateral acceleration inputs to the yaw trim system (106, 93) during coordinated turns, and provides proportional (130) and lagged (131) roll rate inputs to the trim system to provide initial coordination to the turns.Type: GrantFiled: March 30, 1981Date of Patent: July 5, 1983Assignee: United Technologies CorporationInventors: William C. Fischer, Don L. Adams, David J. Verzella, Stuart C. Wright
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Patent number: 4387431Abstract: In an aircraft automatic flight control system (FIG. 4) the application of force to a control member (35R, FIG. 5) forces (222, 216, 217, 212, 213) the flight path controlling, full authority outer loop to be disengaged. Once disengaged by force, the outer loop remains disengaged (224) until force is removed (225) and a signal indicates (226) a need to reestablish the outer loop. Reestablishment may be indicated by beeping (228) or by the controlled attitude (54R, 55R) being restored to within a predetermined level (230).Type: GrantFiled: March 30, 1981Date of Patent: June 7, 1983Assignee: United Technologies CorporationInventors: Stuart C. Wright, Don L. Adams, William C. Fischer, David J. Verzella
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Patent number: 4387432Abstract: In an aircraft automatic flight control system, proportional commands (54, 55) provided to fast, limited authority inner loop actuators (12, 13) are integrated (41), and when the integrator output indicates that the inner loop actuators 12, 13 have been driven a certain percentage of their authority, a comparator (130, 132) activates a pulse generator (137, 138) to provide timed excitation of an actuator (150), thereby to position the aircraft control system outer loop by a commensurate increment. Driving the actuator for a longer time than the desired pulse width is detected (165-169) and causes automatic shutdown (190) of the actuator. Resetting the integrator at the start of each pulse (162, 104), and pulse-controlled gating of the pulse circuits (172, 135, 136) allow sensing of authority transitions which occur within a pulse, and permit a subsequent pulse in response thereto.Type: GrantFiled: March 30, 1981Date of Patent: June 7, 1983Assignee: United Technologies CorporationInventors: William C. Fischer, Don L. Adams, David J. Verzella, Stuart C. Wright
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Patent number: 4387430Abstract: In an aircraft automatic flight control system, a flight path controlling, full authority outer loop actuator (37) operated in response to the integral (41) of commands thereto, is shutdown (111, 113-115) in response to the sensing (31, 32) of force on the related pilot control member (27). After removal of force (118), the outer loop is continued to be shut down for a time interval (119) to allow the aircraft to resettle toward the trim point before building up error in the integrator, unless high input demand (122) is indicated.Type: GrantFiled: March 30, 1981Date of Patent: June 7, 1983Assignee: United Technologies CorporationInventors: David J. Verzella, William C. Fischer, Don L. Adams, Stuart C. Wright
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Patent number: 4385355Abstract: An aircraft automatic flight control system includes a pair of fast, limited authority inner loop actuators (12, 13) responsive to signals (52-55) indicative of aircraft attitude (68, 69) or other flight parameters such as airspeed (84), the inner loop being recentered by an outer loop actuator (37) responsive to attitude or other aircraft parameter-indicating signals (54, 55). Commands (40) applied to the outer loop are applied in a lagged fashion (58, 59) in opposite direction so as to drive the inner loop actuators (12, 13) back toward the center of their authority. The rate of response of the outer loop (FIG. 2, FIG. 5) is adaptive in dependence upon airspeed (93, 96, 212, 213) and in response to magnitude of inner loop input (101, FIG. 2). An integral gain (41), pulsed (39), open loop drive of the outer loop actuator (37) and outer loop automatic shutdown (38) are disclosed.Type: GrantFiled: March 30, 1981Date of Patent: May 24, 1983Assignee: United Technologies CorporationInventors: David J. Verzella, William C. Fischer, Don L. Adams, Stuart C. Wright