Patents by Inventor T. Todd Griffith
T. Todd Griffith 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: 9656641Abstract: An electric brake system architecture for an aircraft with two or more electrical braking subsystems including brake system controls configured to communicate pilot pedal commands to electric brake actuator controllers that apply or release brakes in wheel groups. The system allows independent brake activation of wheel groups through a plurality of brake system controls and electric brake actuator controllers. The electric braking system further includes remote data consolidators to collect and transmit wheel data to brake system controls through a digital data communication bus. The system reduces aircraft weight, prevents inadvertent braking, and prevents error propagation between subsystems.Type: GrantFiled: August 4, 2006Date of Patent: May 23, 2017Assignee: THE BOEING COMPANYInventors: T. Todd Griffith, David T. Yamamoto, Erik L. Godo, Tu-Luc H. Nguyen
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Patent number: 9108602Abstract: A system and procedures for setting a parking brake for an aircraft having an electric brake system are disclosed. Electric activation of a parking brake as described herein mimics the sequence of events that is performed to engage the parking brake of legacy hydraulic brake systems. The electric activation process obtains brake pedal deflection data and parking brake lever status data, and determines whether to set the parking brake mechanism based upon the received data. Once the electric brake actuators are set, the electric brake system engages a friction brake to hold the brake actuators in place without having to physically lock or latch the brake pedals in a depressed position.Type: GrantFiled: December 5, 2006Date of Patent: August 18, 2015Assignee: The Boeing CompanyInventors: T. Todd Griffith, Neil T. Rapues, Tanong Nalamliang, Mark R. McConoughey
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Patent number: 8974012Abstract: An electric autobrake interlock system for an aircraft includes an autobrake power interlock mechanism that prevents inadvertent (uncommanded) application of brakes. The autobrake power interlock removes operating power from the brake actuators whenever the autobrake actuation data does not indicate a legitimate autobrake application condition. The interlock processing occurs in parallel with the autobrake command processing such that even if an inadvertent autobrake command is generated, the brake actuators will be enable to act upon the inadvertent autobrake command. In this regard, the brake actuators are unable to apply brakes automatically unless the following two actions happen concurrently: the operating power is provided to enable the electric brake actuators and autobrake actuation control is commanded in response to the legitimate autobrake application condition.Type: GrantFiled: December 12, 2012Date of Patent: March 10, 2015Assignee: The Boeing CompanyInventors: T. Todd Griffith, David T. Yamamoto, Andreea D. Uta
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Patent number: 8641154Abstract: A system and procedures for adjusting brake mechanisms for an aircraft having an electric brake system are disclosed. The brake actuator mechanisms are controlled to achieve different parking brake actuation states as a function of the current engine run status (e.g., engine off, engine idle, or engine above idle). Procedures for adjusting an aircraft parking brake as disclosed herein include setting the brake actuator mechanisms to achieve a relatively low clamping force when the aircraft engines are off or idling, and setting the brake mechanisms to achieve a relatively high clamping force when the aircraft engines are running above idle, and to maintain commanded brake force without active or battery power by engaging a mechanical clutch or latch to the brake actuator.Type: GrantFiled: October 9, 2006Date of Patent: February 4, 2014Assignee: The Boeing CompanyInventors: T. Todd Griffith, Pete Goranson, Dan Adkinson
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Patent number: 8393689Abstract: An electric autobrake interlock system for an aircraft includes an autobrake power interlock mechanism that prevents inadvertent (uncommanded) application of brakes. The autobrake power interlock removes operating power from the brake actuators whenever the autobrake actuation data does not indicate a legitimate autobrake application condition. The interlock processing occurs in parallel with the autobrake command processing such that even if an inadvertent autobrake command is generated, the brake actuators will be unable to act upon the inadvertent autobrake command. In this regard, the brake actuators are unable to apply brakes automatically unless the following two actions happen concurrently: the operating power is provided to enable the electric brake actuators and autobrake actuation control is commanded in response to the legitimate autobrake application condition.Type: GrantFiled: December 22, 2006Date of Patent: March 12, 2013Assignee: The Boeing CompanyInventors: T. Todd Griffith, David T. Yamamoto, Andreea D. Uta
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Patent number: 8244428Abstract: An automatic fore/aft detection procedure as described herein may be implemented in connection with an aircraft brake control system that utilizes wheel-mounted accelerometers that detect landing gear acceleration for purposes of antiskid control. The fore/aft detection procedure automatically determines that the aircraft is moving in a forward direction based upon the current wheel speed and rotational direction of the wheels. Once detected, forward direction is assigned to the rotational direction of each wheel (clockwise or counterclockwise) and a fore/aft orientation can be assigned to the accelerometer for each wheel.Type: GrantFiled: May 10, 2006Date of Patent: August 14, 2012Assignee: The Boeing CompanyInventor: T. Todd Griffith
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Patent number: 7784882Abstract: An electric brake system for an aircraft as described herein electrically actuates brake mechanisms in a seamless manner when a power interrupt condition is experienced. While operating in an autobraking mode and in response to a power interrupt condition, the electric brake system preserves the last brake actuation command generated by the autobrake function. After normal operating power is reestablished, the last brake actuation command is retrieved and processed by the electric brake system. While operating in a pedal braking mode and in response to a power interrupt condition, the electric brake system discards the last brake actuation command generated from brake pedal interaction. After normal operating power is reestablished, the brake pedal data is refreshed to generate a new brake actuation command. These procedures reduce lurching and unexpected brake actuation levels following a power interrupt in the electric brake system.Type: GrantFiled: September 26, 2006Date of Patent: August 31, 2010Assignee: The Boeing CompanyInventor: T. Todd Griffith
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Patent number: 7766431Abstract: A system and methods for an electric autobrake function suitable for use with an aircraft is disclosed. The system includes a single master autobrake channel configured to generate a master autobrake command and a plurality of slave autobrake channels configured to receive the autobrake master command. The methods receive autobrake command actuation data, compute a common autobrake master command based upon the autobrake command actuation data, and synchronize brake application by utilizing the common autobrake master command to actuate all brake actuators.Type: GrantFiled: April 27, 2007Date of Patent: August 3, 2010Assignee: The Boeing CompanyInventors: T. Todd Griffith, Andreea D. Uta, John Gowan
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Patent number: 7717527Abstract: An electric brake system for an aircraft employs a brake control process to alleviate high dynamic structural loading of the aircraft landing gear caused by braking maneuvers. The system obtains and processes real-time data—which may include the current aircraft speed, the current brake pedal deflection position, and the current brake pedal deflection rate—to determine how best to control the onset of the brakes. The braking control scheme delays the onset of the desired braking condition to reduce high dynamic loading and lurching of the aircraft.Type: GrantFiled: September 15, 2006Date of Patent: May 18, 2010Assignee: The Boeing CompanyInventor: T. Todd Griffith
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Publication number: 20100109429Abstract: An electric brake system for an aircraft employs a brake control process to alleviate high dynamic structural loading of the aircraft landing gear caused by braking maneuvers. The system obtains and processes real-time data—which may include the current aircraft speed, the current brake pedal deflection position, and the current brake pedal deflection rate—to determine how best to control the onset of the brakes. The braking control scheme delays the onset of the desired braking condition to reduce high dynamic loading and lurching of the aircraft.Type: ApplicationFiled: September 15, 2006Publication date: May 6, 2010Inventor: T. Todd Griffith
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Patent number: 7618100Abstract: An electric brake system for an aircraft includes a power interlock mechanism that prevents inadvertent (uncommanded) application of brakes. The interlock removes operating power from the brake mechanisms whenever the brake system sensor data does not indicate a legitimate brake application condition. The interlock processing occurs in parallel with the brake command processing such that even if an inadvertent brake command is generated, the brake mechanisms will be unable to act upon the inadvertent brake command.Type: GrantFiled: December 13, 2006Date of Patent: November 17, 2009Assignee: The Boeing CompanyInventors: T. Todd Griffith, Erik Godo
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Publication number: 20080150353Abstract: An electric autobrake interlock system for an aircraft includes an autobrake power interlock mechanism that prevents inadvertent (uncommanded) application of brakes. The autobrake power interlock removes operating power from the brake actuators whenever the autobrake actuation data does not indicate a legitimate autobrake application condition. The interlock processing occurs in parallel with the autobrake command processing such that even if an inadvertent autobrake command is generated, the brake actuators will be unable to act upon the inadvertent autobrake command. In this regard, the brake actuators are unable to apply brakes automatically unless the following two actions happen concurrently: the operating power is provided to enable the electric brake actuators and autobrake actuation control is commanded in response to the legitimate autobrake application condition.Type: ApplicationFiled: December 22, 2006Publication date: June 26, 2008Inventors: T. Todd Griffith, David T. Yamamoto, Andreea D. Uta
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Publication number: 20080149436Abstract: A system and methods for an electric autobrake function suitable for use with an aircraft is disclosed. The system includes a single master autobrake channel configured to generate a master autobrake command and a plurality of slave autobrake channels configured to receive the autobrake master command. The methods receive autobrake command actuation data, compute a common autobrake master command based upon the autobrake command actuation data, and synchronize brake application by utilizing the common autobrake master command to actuate all brake actuators.Type: ApplicationFiled: April 27, 2007Publication date: June 26, 2008Inventors: T. Todd Griffith, Andreea D. Uta, John Gowan
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Publication number: 20080142318Abstract: An electric brake system for an aircraft includes a power interlock mechanism that prevents inadvertent (uncommanded) application of brakes. The interlock removes operating power from the brake mechanisms whenever the brake system sensor data does not indicate a legitimate brake application condition. The interlock processing occurs in parallel with the brake command processing such that even if an inadvertent brake command is generated, the brake mechanisms will be unable to act upon the inadvertent brake command.Type: ApplicationFiled: December 13, 2006Publication date: June 19, 2008Inventors: T. Todd Griffith, Erik Godo
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Publication number: 20080133073Abstract: A system and procedures for setting a parking brake for an aircraft having an electric brake system are disclosed. Electric activation of a parking brake as described herein mimics the sequence of events that is performed to engage the parking brake of legacy hydraulic brake systems. The electric activation process obtains brake pedal deflection data and parking brake lever status data, and determines whether to set the parking brake mechanism based upon the received data. Once the electric brake actuators are set, the electric brake system engages a friction brake to hold the brake actuators in place without having to physically lock or latch the brake pedals in a depressed position.Type: ApplicationFiled: December 5, 2006Publication date: June 5, 2008Inventors: T. Todd Griffith, Neil T. Rapues, Tanong Nalamliang, Mark R. McConoughey
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Publication number: 20080084109Abstract: A system and procedures for adjusting brake mechanisms for an aircraft having an electric brake system are disclosed. The brake actuator mechanisms are controlled to achieve different parking brake actuation states as a function of the current engine run status (e.g., engine off, engine idle, or engine above idle). Procedures for adjusting an aircraft parking brake as disclosed herein include setting the brake actuator mechanisms to achieve a relatively low clamping force when the aircraft engines are off or idling, and setting the brake mechanisms to achieve a relatively high clamping force when the aircraft engines are running above idle, and to maintain commanded brake force without active or battery power by engaging a mechanical clutch or latch to the brake actuator.Type: ApplicationFiled: October 9, 2006Publication date: April 10, 2008Inventors: T. Todd Griffith, Pete Goranson, Dan Adkinson
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Publication number: 20080073970Abstract: An electric brake system for an aircraft as described herein electrically actuates brake mechanisms in a seamless manner when a power interrupt condition is experienced. While operating in an autobraking mode and in response to a power interrupt condition, the electric brake system preserves the last brake actuation command generated by the autobrake function. After normal operating power is reestablished, the last brake actuation command is retrieved and processed by the electric brake system. While operating in a pedal braking mode and in response to a power interrupt condition, the electric brake system discards the last brake actuation command generated from brake pedal interaction. After normal operating power is reestablished, the brake pedal data is refreshed to generate a new brake actuation command. These procedures reduce lurching and unexpected brake actuation levels following a power interrupt in the electric brake system.Type: ApplicationFiled: September 26, 2006Publication date: March 27, 2008Inventor: T. Todd Griffith
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Publication number: 20080030069Abstract: An electric brake system architecture for an aircraft with two or more electrical braking subsystems including brake system controls configured to communicate pilot pedal commands to electric brake actuator controllers that apply or release brakes in wheel groups. The system allows independent brake activation of wheel groups through a plurality of brake system controls and electric brake actuator controllers. The electric braking system further includes remote data consolidators to collect and transmit wheel data to brake system controls through a digital data communication bus. The system reduces aircraft weight, prevents inadvertent braking, and prevents error propagation between subsystems.Type: ApplicationFiled: August 4, 2006Publication date: February 7, 2008Inventors: T. Todd Griffith, David T. Yamamoto, Erik L. Godo, Tu-Luc H. Nguyen
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Publication number: 20070265739Abstract: An automatic fore/aft detection procedure as described herein may be implemented in connection with an aircraft brake control system that utilizes wheel-mounted accelerometers that detect landing gear acceleration for purposes of antiskid control. The fore/aft detection procedure automatically determines that the aircraft is moving in a forward direction based upon the current wheel speed and rotational direction of the wheels. Once detected, forward direction is assigned to the rotational direction of each wheel (clockwise or counterclockwise) and a fore/aft orientation can be assigned to the accelerometer for each wheel.Type: ApplicationFiled: May 10, 2006Publication date: November 15, 2007Inventor: T. Todd Griffith