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Hamilton, AZ
Brian Hamilton, Glendale, AZ US
| Patent application number | Description | Published |
|---|---|---|
| 20100152953 | METHODS AND SYSTEMS FOR EFFICIENTLY ORIENTING AN AGILE VEHICLE USING A GYROSCOPE ARRAY - Methods and systems are provided for orienting an agile vehicle using a control moment gyroscope array. A method comprises obtaining initial vehicle parameters for the vehicle and obtaining target vehicle parameters for the vehicle. The method further comprises determining command parameters based on a difference between the target vehicle parameters and the initial vehicle parameters, and simulating operation of the control moment gyroscope array using the command parameters and a torque value being at least equal to a maximum achievable torque for the control moment gyroscope array. When the simulated vehicle parameters are substantially equal to the target vehicle parameters, the method further comprises determining a torque profile for the control moment gyroscope array based on the simulated operation and operating the control moment gyroscope array using the torque profile. | 06-17-2010 |
| 20110101167 | METHODS AND SYSTEMS FOR IMPOSING A MOMENTUM BOUNDARY WHILE REORIENTING AN AGILE VEHICLE WITH CONTROL MOMENT GYROSCOPES - Methods and systems are provided for reorienting an agile vehicle, such as a satellite or spacecraft, using a control moment gyroscope (CMG) array. The CMG array comprises a plurality of CMGs onboard the agile vehicle. A method comprises obtaining an input torque command for reorienting the vehicle using the CMG array and, when the angular momentum of the CMG array violates or is approaching a momentum boundary criterion, decreasing the input torque command in the kinetic momentum direction, resulting in a modified torque command, and operating the CMG array using the modified torque command. | 05-05-2011 |
Brian J. Hamilton, Glendale, AZ US
| Patent application number | Description | Published |
|---|---|---|
| 20080228332 | ACTIVE CONTROL OF SOFT HYBRID ISOLATION SYSTEMS - Apparatus, Systems, and Methods are provided for controlling motion of a spacecraft. One apparatus includes a non-contacting actuator and a passive mechanical system coupled in parallel with one another. A system includes a payload, a bus, and a hybrid actuator including a non-contacting actuator and a passive mechanical system coupled in parallel, and coupled between the bus and the payload. The system also includes an inertial actuator configured to maneuver the bus to maintain a relative position and/or attitude of the bus with respect to the payload. One method includes receiving a signal instructing a first controller to change the position and/or attitude of a payload and utilizing a hybrid system to change the position and/or attitude of the payload. The method also includes receiving the signal at a second controller and utilizing a system to change a position and/or attitude of the bus independent of the payload. | 09-18-2008 |
| 20090121399 | VIBRATION REDUCTION SYSTEM EMPLOYING ACTIVE BEARING MOUNTS - A vibration reduction system is provided for use in conjunction with a rotational device including a stationary body, a rotating body, and a first bearing assembly disposed between the stationary body and the rotating body. The vibration reduction system includes a first plurality of bearing mount actuators residing between the stationary body and the first bearing assembly. The first plurality of bearing mount actuators is configured to adjust the radial position of the first bearing assembly. The vibration reduction system further includes a vibration sensor, which is coupled to the stationary body, and a controller, which is coupled to the vibration sensor and to the first plurality of bearing mount actuators. The controller is configured to reduce vibrations sensed by the vibration sensor by selectively adjusting the radial position of the first bearing assembly utilizing the first plurality of bearing mount actuators. | 05-14-2009 |
Brian K. Hamilton, Mesa, AZ US
| Patent application number | Description | Published |
|---|---|---|
| 20100025538 | COMPOSITE MATERIAL FOR GEOMETRIC MORPHING WING - An airfoil member and an airfoil member altering system are provided for significantly modifying the shape and size of the airfoil member while simultaneously providing an airfoil member with increased adaptability to various flight conditions throughout a flight envelope. The airfoil member comprises at least one motor or actuator, a system controller, a plurality of vehicle performance sensors, at least one temperature controller and airfoil member comprising at least one geometric morphing device that is adjustable in both size and shape and one or more rigid members. | 02-04-2010 |
| 20110001018 | COMPOSITE MATERIAL FOR GEOMETRIC MORPHING WING - An airfoil member and an airfoil member altering system are provided for significantly modifying the shape and size of the airfoil member while simultaneously providing an airfoil member with increased adaptability to various flight conditions throughout a flight envelope. The airfoil member comprises at least one motor or actuator, a system controller, a plurality of vehicle performance sensors, at least one temperature controller and airfoil member comprising at least one geometric morphing device that is adjustable in both size and shape and one or more rigid members. | 01-06-2011 |
George A. Hamilton, Peoria, AZ US
| Patent application number | Description | Published |
|---|---|---|
| 20090278762 | Antenna Modular Sub-array Super Component - In accordance with various aspects of the present invention, a method and system for an antenna modular sub-array super component is presented. The modular sub-array super component allows for multiple antenna product designs to utilize a common low cost aperture element assembly block, quantities of which may be scaled up or down to suit the physical, performance, and power requirements of a specific antenna system. More specifically, a method and system for connecting various components of an antenna modular sub-array using a bar with leads connector is discussed. The bar with leads may connect antenna subcomponents or subassemblies. | 11-12-2009 |
Russell J. Hamilton, Tucson, AZ US
| Patent application number | Description | Published |
|---|---|---|
| 20100004499 | Methods And Devices For Minimally-Invasive Extraocular Delivery of Radiation To The Posterior Portion Of The Eye - Methods and devices for minimally-invasive delivery of radiation to the posterior portion of the eye including a cannula comprising a distal portion connected to a proximal portion and a means for advancing a radionuclide brachytherapy source (RBS) toward the tip of the distal portion; a method of introducing radiation to the human eye comprising inserting a cannula between the Tenon's capsule and the sclera of the human eye and emitting the radiation from the cannula on an outer surface of said sclera. | 01-07-2010 |
| 20100004581 | METHODS AND DEVICES FOR MINIMALLY-INVASIVE EXTRAOCULAR DELIVERY OF RADIATION TO THE POSTERIOR PORTION OF THE EYE - Methods and devices for minimally-invasive delivery of radiation to the posterior portion of the eye including a cannula comprising a distal portion connected to a proximal portion and a means for advancing a radionuclide brachytherapy source (RBS) toward the tip of the distal portion; a method of introducing radiation to the human eye comprising inserting a cannula between the Tenon's capsule and the sclera of the human eye and emitting the radiation from the cannula on an outer surface of said sclera. | 01-07-2010 |
Vernon D. Hamilton, Tucson, AZ US
| Patent application number | Description | Published |
|---|---|---|
| 20080296541 | CHEMICALLY BONDED CERAMIC RADIATION SHIELDING MATERIAL AND METHOD OF PREPARATION - A composition of matter and method of forming a radiation shielding member at ambient temperatures in which the composition of matter includes a ‘cold-fired’ chemically bonded oxide-phosphate ceramic cement matrix; with one or more suitably prepared and distributed radiation shielding materials dispersed in the ‘cold-fired’ chemically bonded oxide-phosphate ceramic cement matrix. | 12-04-2008 |