Resumes
Resumes
Daryl Hosick Phones & Addresses
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126 Oak Knoll Dr, Santa Cruz, CA 95060 (831) 438-1139 (831) 438-7926 (831) 438-7168
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Scotts Valley, CA
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Cadiz, CA
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126 Oak Knoll Dr, Santa Cruz, CA 95060 (831) 915-1486
Emails
Publications
Us Patents
Drive Circuit For Electric Propulsion Thruster
View pageUS Patent:
61824410, Feb 6, 2001
Filed:
Feb 4, 2000
Appl. No.:
9/497920
Inventors:
Daryl K. Hosick - Santa Cruz CA
Assignee:
Space Systems/Loral, Inc. - Palo Alto CA
International Classification:
F03H 100
US Classification:
60202
Abstract:
In drive circuitry for powering an arc jet or ion engine aboard a spacecraft carrying solar panels, a start-up circuit interconnects an array of series-parallel connected solar panels to establish and maintain an arc and plasma in the engine. In the start-up circuit, an electric switch is placed in parallel with an electrode assembly of the engine. One terminal of the engine connects directly with the solar panel array, and another terminal of the engine connects via an inductor to the solar panel array. A capacitor connects across terminals of the solar panel array. A series connection of solar panels increases the voltage from that which is available from a single panel. Conduction of current from the solar panel via the inductor is initiated by the switch to store magnetic energy within the conductor. Thereupon, upon an opening of the switch, the inductor produces a relatively high voltage which strikes an arc in the engine. The voltage outputted by the solar panel array is sufficient to maintain operation of the engine subsequent to the generation of the arc.
Multiple Usage Thruster Mounting Configuration
View pageUS Patent:
60329041, Mar 7, 2000
Filed:
Feb 23, 1998
Appl. No.:
9/027668
Inventors:
Daryl K. Hosick - Santa Cruz CA
Walter S. Gelon - Redwood City CA
Richard M. Mills - San Jose CA
Walter S. Gelon - Redwood City CA
Richard M. Mills - San Jose CA
Assignee:
Space Systems/Loral, Inc. - Palo Alto CA
International Classification:
B64G 126
US Classification:
244169
Abstract:
A three-axis stabilized spacecraft having roll, pitch, and yaw axes and when on station in orbit about the earth having a north face and a south face is equipped with a first and second thruster which may be electric thrusters. A first support device mounts the first thruster adjacent the north face and the first thruster is positioned a spaced distance away from the north face in a first direction parallel to the pitch axis and spaced from the pitch axis in a second direction normal to the pitch axis. A second support device mounts the second thruster adjacent the south face, the second thruster being positioned a spaced distance away from the south face in a third direction opposite the first direction and spaced from the pitch axis in the second direction. A gimbal mechanism pivotally mounts the first and second thrusters on the first and second support devices, respectively, for selectively positioning the attitude of the first and second thrusters. The spacecraft includes a system for performing one or more operations including the following: thrusting along the yaw axis to assist in reaching a geosynchronous orbit; reducing the stored angular momentum of the momentum wheels; and north-south station keeping of the spacecraft.
Drive Circuit For Electric Propulsion Thruster
View pageUS Patent:
60294388, Feb 29, 2000
Filed:
Oct 15, 1997
Appl. No.:
8/950692
Inventors:
Daryl K. Hosick - Santa Cruz CA
Assignee:
Space Systems/Loral, Inc. - Palo Alto CA
International Classification:
F03H 100
US Classification:
60202
Abstract:
In drive circuitry for powering an arc jet or ion engine aboard a spacecraft carrying solar panels, a start-up circuit interconnects an array of series-parallel connected solar panels to establish and maintain an arc and plasma in the engine. In the start-up circuit, an electric switch is placed in parallel with an electrode assembly of the engine. One terminal of the engine connects directly with the solar panel array, and another terminal of the engine connects via an inductor to the solar panel array. A capacitor connects across terminals of the solar panel array. A series connection of solar panels increases the voltage from that which is available from a single panel. Conduction of current from the solar panel via the inductor is initiated by the switch to store magnetic energy within the conductor. Thereupon, upon an opening of the switch, the inductor produces a relatively high voltage which strikes an arc in the engine. The voltage outputted by the solar panel array is sufficient to maintain operation of the engine subsequent to the generation of the arc.
High Power Spacecraft With Full Utilization Of All Spacecraft Surfaces
View pageUS Patent:
60738871, Jun 13, 2000
Filed:
Jul 16, 1997
Appl. No.:
8/895363
Inventors:
Daryl K. Hosick - Santa Cruz CA
Assignee:
Space Systems/Loral, Inc. - Palo Alto CA
International Classification:
B64G 100
US Classification:
244158R
Abstract:
A spacecraft for deployment in geosynchronous orbit about the Earth, comprising six face panels which enclose a compartment containing electronic powering components mounted on the interior surfaces thereof. The panels include opposed north-facing and south-facing panels which do not undergo sun-exposure, remain cool and provide safe interior surfaces for the electronic powering components mounted thereon, and four side panels which are successively rotated into diurnal sun-exposure attitude during which their temperature normally rises so excessively as to damage electronic powering components mounted on the interior surfaces thereof. The invention comprises providing the east-facing and west-facing panels with at least one continuous circulation system containing a heat exchange fluid which absorbs heat from the one of said panels undergoing sun exposure and circulates it to the other of said panels to moderate the temperature of the east-facing and west-facing panels. This prevents heat-damage to electronic powering components mounted on the interior surfaces of the east and west panels, whereby the total interior surface area of the panels available for the safe mounting of the components is substantially increased.