| Patent application number | Description | Published |
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| 20090099080 | MITOCHONDRIA-TARGETED ANTI-TUMOR AGENTS - Described are mitochondria-targeted anti-tumor agents, and methods of making and using the same for the treatment of disorders associated with unwanted cell proliferation. | 04-16-2009 |
| 20110136743 | Survivin, a protein that inhibits cellular apoptosis, and its modulation - The present invention provides the amino acid of a protein that inhibits cellular apoptosis, herein termed the Survivin protein and nucleic acid molecules that encode Survivin. Based on this disclosure, the present invention provides isolated Survivin protein, isolated Survivin encoding nucleic acid molecules, methods of isolating other members of the Survivin family of proteins, methods for identifying agents that block Survivin mediated inhibition of cellular apoptosis, methods of using agents that block Survivin mediated inhibition or Survivin expression to modulate biological and pathological processes, and methods of assaying Survivin activity. | 06-09-2011 |
| 20110268722 | COMBINATION THERAPIES WITH MITOCHONDRIAL-TARGETED ANTI-TUMOR AGENTS - Described are mitochondria-targeted anti-tumor agents, death receptor agonists, autophagy inhibitors, and NF-κB signaling pathway inhibitors, and methods of making and using the same for the treatment of disorders associated with unwanted cell proliferation. | 11-03-2011 |
| Patent application number | Description | Published |
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| 20080200924 | METHODS FOR MINIMALLY INVASIVE, NON-PERMANENT OCCLUSION OF A UTERINE ARTERY - A method of treating a uterine disorder comprising non-permanently occluding a uterine artery with a resorbable embolic mass for a therapeutically effective time period. The occluding step includes selectively positioning the resorbable embolic mass within the uterine artery, and monitoring positioning of the resorbable embolic mass at a desired location within the uterine artery. The monitoring step may include using ultrasound or magnetic resonance imaging (MRI) for positioning the resorbable embolic mass at the desired location within the uterine artery. The resorbable embolic mass may be swellable and may be formed of a polymeric material selected from the group consisting of polylactic acid, polyglycolic acid, polyethylene glycol, or copolymers thereof. | 08-21-2008 |
| 20090287088 | LUMINAL CLIP APPLICATOR WITH SENSOR AND METHODS FOR OCCLUDING BODY LUMENS - A method for occluding a body lumen includes providing a clamping device having a pair of opposed pressure applying jaws, providing a sensor on one of the pressure applying jaws for sensing blood flow through a body lumen, and releasably securing a luminal clip between the pressure applying jaws. The method includes using the sensor for detecting blood flow through the body lumen for locating the body lumen, positioning the luminal clip adjacent the located body lumen, and closing the pressure applying jaws for clamping the luminal clip over the body lumen for at least partially occluding blood flow through the body lumen. | 11-19-2009 |
| 20100300549 | MODULATED WATERING SYSTEM - A modulated watering system includes a timer for powering at least one solenoid valve and a controller for modulating power provided to the solenoid valve and an adjuster, in communication with the controller, for changing the modulation. | 12-02-2010 |
| 20100301133 | MODULATED WATERING DEVICE - A device for controlling an irrigation system includes an interrupter for interconnection in a serial manner between a solenoid return common line and a preexisting irrigation timer, a controller for operating the interrupter in a periodic fashion is provided as well as an adjuster, in communication with the controller, for changing the periodicity of the interrupter operation. | 12-02-2010 |
| Patent application number | Description | Published |
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| 20090055129 | AIRCRAFT VEHICULAR PROPULSION SYSTEM MONITORING DEVICE AND METHOD - Methods and systems for monitoring rotating shaft shafts and couplings in an aircraft propulsion system is described. The measurement system/method provides for accurate and precise monitoring of a rotating shaft flexible coupling in a fixed wing aircraft vehicle propulsion system. The measuring system/method provides for a high reliability short take off vertical landing fixed wing aircraft in which the vertical propulsion dynamically rotating drive shaft system and couplings are monitored in real time. The vehicular shaft coupling misalignment measuring system utilizes multiple positional sensors to provide highly reliable and precise determination of the dynamic characteristics of the rotating sensor target components of the propulsion system drive shaft. The relative position of the sensors is rigidly fixed externally from the rotating targets with a structural frame. The collar misalignment measuring system of the invention provide a misalignment measurement of the propulsion system drive shaft flexible coupling which relates to a critical performance of rotating shaft coupling in the operation of an aircraft vehicle. The method/system provides for monitoring a rotating drive shaft system and dynamically measuring a rotating drive shaft coupling in a fixed wing aircraft propulsion system. | 02-26-2009 |
| 20090254230 | Distributed active vibration control systems and rotary wing aircraft with suppressed vibrations - An aircraft with at least one rotating machine creating troublesome vibrations, the aircraft comprised of an aerostructure, the aircraft including:
| 10-08-2009 |
| 20090306829 | AIRCRAFT WITH TRANSIENT-DISCRIMINATING PROPELLER BALANCING SYSTEM - A system for balancing an aircraft propeller system receives a vibration signal from the aircraft propeller system and determines whether the vibration signal indicates a transient vibration condition. If it is determined that the vibration signal does not indicate a transient condition, the system enables a balance correction controller. The controller generates a balance correction signal based on the vibration signal, and balances the aircraft propeller system in response to the balance correction signal if the balance correction controller is enabled. | 12-10-2009 |
| 20100034655 | HELICOPTER HUB MOUNTED VIBRATION CONTROL AND CIRCULAR FORCE GENERATION SYSTEMS FOR CANCELING VIBRATIONS - A rotary wing aircraft including a vehicle vibration control system. The vehicle vibration control system includes a rotating hub mounted vibration control system, the rotating hub mounted vibration control system mounted to the rotating rotary wing hub with the rotating hub mounted vibration control system rotating with the rotating rotary wing hub. The vehicle vibration control system includes a rotary wing aircraft member sensor for outputting rotary wing aircraft member data correlating to the relative rotation of the rotating rotary wing hub member rotating relative to the nonrotating body, at least a first nonrotating body vibration sensor, the at least first nonrotating body vibration sensor outputting at least first nonrotating body vibration sensor data correlating to vibrations, at least a first nonrotating body circular force generator, the at least a first nonrotating body circular force generator fixedly coupled with the nonrotating body, a distributed force generation data communications network link, the distributed force generation data communications system network link linking together at least the first nonrotating body circular force generator and the rotating hub mounted vibration control system wherein the rotating hub mounted vibration control system and the first nonrotating body circular force generator communicate force generation vibration control data through the distributed force generation data communications network, the at least first nonrotating body circular force generator controlled to produce a rotating force with a controllable rotating force magnitude and a controllable rotating force phase, the controllable rotating force magnitude controlled from a minimal force magnitude up to a maximum force magnitude, and with the controllable rotating force phase controlled in reference to the rotary wing aircraft member sensor data correlating to the relative rotation of the rotating rotary wing hubrotating relative to the nonrotating body wherein the vibration sensed by the at least first nonrotating body vibration sensor is reduced. | 02-11-2010 |
| 20100221096 | COMPUTER SYSTEM AND PROGRAM PRODUCT FOR CONTROLLING VIBRATIONS - The computer programmable system and program product include first program instructions for actively driving a first imbalance mass concentration rotor and a second imbalance mass concentration rotor at a vibration canceling rotation frequency while controlling the rotational position of the first imbalance mass concentration and the second imbalance mass concentration to produce a rotating net force vector to inhibit periodic vibrations. The program product includes second program instructions to opposingly orient the first imbalance mass concentration relative to the second imbalance mass concentration during a starting stopping rotation speed less than the vibration canceling rotation frequency. The system includes a fault mode control protocol for controlling a rotation of the rotors during a sensed failure of the rotating assembly vibration control system. | 09-02-2010 |
| 20110204882 | AIRCRAFT VEHICULAR PROPULSION SYSTEM MONITORING DEVICE AND METHOD - Methods/systems for monitoring an aircraft propulsion system is described. The measurement system/method provides for accurate and precise monitoring of rotating members in an aircraft vehicle propulsion system. The measuring system/method provides for a high reliability aircraft in which the propulsion dynamically rotating drive shaft system and couplings are monitored in real time. The vehicular measuring system utilizes multiple positional sensors to provide highly reliable and precise determination of the dynamic characteristics of the rotating sensor target components of the aircraft system. The relative position of the sensors is rigidly fixed externally from the rotating targets with a structural frame. The measuring system provides a misalignment measurement of the propulsion system drive shaft flexible coupling which relates to a critical performance of rotating shaft coupling in the operation of an aircraft vehicle. The method/system provides for monitoring a rotating drive shaft system and dynamically measuring a rotating drive shaft coupling in an aircraft. | 08-25-2011 |
