| Patent application number | Description | Published |
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| 20090133443 | Glassware forming machine blowhead arm assembly - A glassware forming machine blowhead arm assembly includes a one-piece blowhead arm body having at least one longitudinal air passage and a plurality of lateral air passages connected to the longitudinal passage. A blowhead chuck is removably received in a first end of each lateral passage and a cap is threaded into the second end of each lateral passage spaced from the associated blowhead chuck. A spring is captured in compression between each cap and an associated blowhead chuck biasing the blowhead chuck in a direction out of the lateral passage and away from the cap. In an exemplary embodiment of the disclosure adapted for use in conjunction with so-called isolated finish cooling blowheads, there are first and second longitudinal air passages extending through the blowhead arm body separately from each other, and separate air inputs in the body respectively coupled to the first and second longitudinal passages. Each lateral air passage is separately connected to the longitudinal air passages, and the blowhead chucks have separate air passages for feeding blow air and finish cooling air to a blowhead mounted in the chuck. | 05-28-2009 |
| 20100284767 | Threadless Nut - A glassware forming machine baffle arm assembly that includes a quick-connect/disconnect arrangement mounting a baffle manifold on a baffle arm. The arrangement includes a baffle arm having an aperture, and a baffle manifold having a segment extending through said aperture and permitting rotation of said baffle manifold with respect to said baffle arm. The arrangement also includes a threadless nut, and a bayonet connection between said threadless nut and said baffle manifold segment. | 11-11-2010 |
| 20110027048 | Threadless Nut - A glassware forming machine baffle arm assembly that includes a quick-connect/disconnect arrangement mounting a baffle manifold on a baffle arm. The arrangement includes a baffle arm having an aperture, and a baffle manifold having a segment extending through said aperture and permitting rotation of said baffle manifold with respect to said baffle arm. The arrangement also includes a threadless nut, and a bayonet connection between said threadless nut and said baffle manifold segment. | 02-03-2011 |
| Patent application number | Description | Published |
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| 20110180656 | Method and Apparatus for Aircraft Sensor and Actuator Failure Protection Using Reconfigurable Flight Control Laws - A method and apparatus for reconfiguring flight control of an aircraft during a failure while the aircraft is flying. The method and apparatus provide a control law that is software-implemented and configured to automatically send flight control data to a mixing/mapping matrix and a reconfiguration management tool configured to communicate with the mixing/mapping matrix in order to safely transfer authority from a failed actuator to a back-up actuator. A sensor management tool is provided for input to the reconfiguration management tool in order to smooth any transient conditions that may occur during reconfiguration. The method and apparatus provide for a way of smoothing any possible transient situation that might otherwise occur by employment of a fader, the fader being used to gradually convert positioning of failed actuators and positioning of reconfigured actuators. | 07-28-2011 |
| 20110282523 | Control System for Automatic Flight in Windshear Conditions - A flight control system is configured for controlling the flight of an aircraft through windshear conditions. The system has means for measuring values of selected flight performance states of the aircraft and a control system for operating flight control devices on the aircraft. A windshear detection system located on the aircraft uses at least some of the measured values of the selected flight performance states to calculate a gust average during flight for comparison to pre-determined values in a table for determining whether windshear conditions exist. The control system then operates at least some of the flight control devices in response to an output of the windshear detection system. | 11-17-2011 |
| 20120253558 | Flight Control Laws for Constant Vector Flat Turns - An aircraft and method to control flat yawing turns of the aircraft while maintaining a constant vector across a ground surface. The aircraft includes a control system in data communication with control actuators, a lateral control architecture, a longitudinal control architecture, and an initialization command logic. The lateral control architecture controls the aircraft in the lateral direction, while the longitudinal control architecture controls the aircraft in the longitudinal direction. The initialization command logic automatically activates the lateral control architecture and the longitudinal control architecture to maintain a constant vector across the ground whenever a directional control input is made at low speed. | 10-04-2012 |
| 20130060406 | Flight Control Laws for Vertical Flight Path - A flight control system and method for controlling the vertical flight path of an aircraft, the flight control system includes a stable decoupled model having a decoupled lateral equation of motion and a decoupled longitudinal equation of motion and a feedback command loop operably associated with the stable decoupled model. The feedback command loop includes a vertical flight path angle control law; an altitude control law; and a vertical speed control law. | 03-07-2013 |
| 20130090788 | FLIGHT CONTROL LAWS FOR FULL ENVELOPE BANKED TURNS - A flight control system and method for controlling full envelope banked turns of an aircraft, the flight control system including one or more of a control law architectures having one or more control laws adapted for controlling the flight of an aircraft for full envelope banked turns. | 04-11-2013 |
| 20130138270 | FLIGHT CONTROL LAWS FOR AUTOMATIC HOVER HOLD - A system and method to control hovering flight of a rotary aircraft. The system including a lateral speed hold loop, a longitudinal loop, a vertical control loop, and a directional loop. The method includes defining a first flight envelope having a first groundspeed threshold; defining a second flight envelope having a second groundspeed threshold, the second flight envelope being defined within the first envelope; engaging a hover hold with a control law hover hold architecture as the aircraft enters the first flight envelope; and engaging a position hold with a control law position hold architecture as the aircraft enters the second flight envelope. | 05-30-2013 |
| 20130261853 | VEHICLE MANAGEMENT SYSTEM USING FINITE STATE MACHINES - A system includes a plurality of actuators and a management system operably associated with the plurality electronic and mechanical devices. The management architecture includes interfaces configured to the entire electronics and mechanics to provide a parameter to a computer. The computer includes a control and management architecture using modular finite state flow designs configured to analyze the parameter. The computer with a plurality of finite state machines can conduct a plurality of control laws operably associated with one or more actuators for finite functions of mobility. The method includes matching the parameter with the finite state machine and controlling the actuator via control law operably associated with finite state machine. The method can therefore be achieved either manually, semi-autonomously and autonomously with seamless and switchless control using a central control computer with integration of electronic and mechanic sensors and devices. | 10-03-2013 |
| 20130274963 | EXTENSION OF THREE LOOP CONTROL LAWS FOR SYSTEM UNCERTAINTIES, CALCULATION TIME DELAY AND COMMAND QUICKNESS - A system includes a plurality of actuators and a control system operably associated with the plurality of actuators. The control system having a control logic architecture having a dynamic command input shaping model associated with an input command, a robust inner loop associated with the dynamic command input shaping model, and a time delay cancellation model. The method includes selecting a control law based upon a flight performance of an aircraft, decoupling the control law into a first individual component and a second individual component of the aircraft flight motion, analyzing each individual component separately, regrouping the component of flight motion, analyzing the control law with a time delay cancellation model and providing the necessary dynamic flight quickness with a different command input condition. | 10-17-2013 |
| 20130325221 | Takeoff/Landing Touchdown Protection Management System - An air/ground contact logic management system for use with fly-by-wire control systems in an aircraft. The system includes a first sensor configured to provide an output signal to determine when the aircraft is in a transition region. A logic management system is in communication with the first sensor and is configured to receive and process the output signal and classify a mode of the aircraft. A controller receives signal data from the logic management system and communicates with a control axis actuator to regulate a level of control authority provided to a pilot. The control authority is individually regulated within each integrator as a result of the individual landing gear states. | 12-05-2013 |
| 20140005862 | Method and Apparatus for Aircraft Sensor and Actuator Failure Protection Using Reconfigurable Flight Control Laws | 01-02-2014 |
| 20140025237 | FLIGHT CONTROL LAWS FOR CONSTANT VECTOR FLAT TURNS - An aircraft and method to control flat yawing turns of the aircraft while maintaining a constant vector heading across a ground surface. The aircraft includes a control system in data communication with a model, a lateral control architecture, a longitudinal control architecture, and an initialization command logic. The model decouples the directional movement of the aircraft into a lateral equation of motion and a longitudinal equation of motion. The lateral control architecture utilizes the lateral equation of motion to control the aircraft in the lateral direction, while the longitudinal control architecture utilizes the longitudinal equation of motion to control the aircraft in the longitudinal direction. The initialization command logic selectively activates the lateral control architecture and the longitudinal control architecture. | 01-23-2014 |
| 20140316615 | METHOD AND APPARATUS FOR AIRCRAFT SENSOR AND ACTUATOR FAILURE PROTECTION USING RECONFIGURABLE FLIGHT CONTROL LAWS - A method and apparatus for reconfiguring flight control of an aircraft during a failure while the aircraft is flying. The method and apparatus provide a control law that is software-implemented and configured to automatically send flight control data to a mixing/mapping matrix. The method and apparatus also provide a reconfiguration management tool configured to communicate with the mixing/mapping matrix in order to safely transfer authority from a failed actuator to a back-up actuator. The method and apparatus also provide a sensor management tool for providing input to the reconfiguration management tool in order to smooth any transient conditions that may occur during reconfiguration. The method and apparatus provide for a way of smoothing any possible transient situation that might otherwise occur by employment of a fader, the fader being used to gradually convert positioning of failed actuators and positioning of reconfigured actuators. An exemplary aircraft for using the method and apparatus of a reconfigurable flight control system is a quad tilt rotor. The quad tilt rotor provides a variety of redundant and back-actuators, as such, having a robust and highly qualified reconfigurable flight control system is very desirable. | 10-23-2014 |
