Star Technology and Research, Inc.

Other

Tether Applications, Inc.

USA As Represented by Secretary of the Navy

Eugene Levin

Joseph A Carroll

Paul Oppenheimer

Jerome Pearson

Adam Thurn

Jordan R Schlater

Shannon Coffey

Ivan Galysh

Curt Hogan

A tethered spacecraft has a first endmass and a second endmass with a telescoping stacer spring and a tether arranged between the endmasses. The spring is coiled around a center rod and initially contained within a housing, the spring being biased to push the first endmass away from the second endmass. The spring housing is affixed to the first endmass, a first end of the spring being affixed to the spring housing, and tether are affixed to spring at one end and to the second endmass at the other end. A pretensioned loop holds the endmasses abuttingly together, and a burnwire release mechanism cuts the loop to deploy the spring. Upon deployment, the spring extends to its full length to form a cylindrical boom, and the endmasses continue to move outward along the spring centerline until stopped by the tether.

Separation system and burn wire release mechanism for tethered spacecraft

A processing and delivery system is in space around a celestial body having a magnetic field. The system includes at least one facility having supplies and configured for in-space recycling and manufacturing to produce processed objects utilizing space debris objects and the supplies. The system includes at least one space vehicle configured to deliver the space debris objects from their orbits to the at least one facility using electrodynamic propulsion. The system includes at least one space vehicle configured to deliver new supplies to the at least one facility from other orbits using electrodynamic propulsion. The system includes at least one space vehicle configured to deliver the processed objects from the at least one facility to their destination orbits using electrodynamic propulsion.

In-space processing and delivery system

An electrodynamic method includes providing an electrodynamic structure with a periphery, providing power, collecting electrons, and emitting electrons. The emitting electrons and the collecting electrons utilizes at least 20% of the periphery of the electrodynamic structure. The method includes conducting current to provide at least one of electrodynamic propulsion and power generation.

Electrodynamic method

An electrodynamic structure having a periphery. The electrodynamic structure includes a power system, a plurality of collectors, a plurality of emitters, and conductive paths. The plurality of collectors are disposed on the periphery of the electrodynamic structure and configured to collect electrons. The plurality of emitters are disposed on the periphery of the electrodynamic structure and configured to emit electrons. At least 20% of the periphery of the electrodynamic structure is utilized for electron collection and electron emission. The conductive paths are configured to conduct current between the power system, the collectors, and the emitters to provide at least one of power generation and electrodynamic propulsion.

Electrodynamic structure

The present invention improves the orbital maneuvering and power generation capabilities of a system of a satellite(s) connected with a conducting tether(s) by spinning the system about its mass center at an angular rate which is relatively high compared to the average orbital rate. An improvement in tether performance is achieved because at many times during rotation the tether is positioned at much better angles with the magnetic field and significantly higher currents are driven through the tether without destabilizing the system. The current can flow either in the direction of the EMF induced in the tether, or in the reverse direction, depending on the tether orientation with respect to the magnetic field and the mission goals. The reverse current is driven by the onboard power sources. Spinning electrodynamic tether systems can also be lighter and simpler in design and more flexible in operation.

Method and apparatus for propulsion and power generation using spinning electrodynamic tethers

A tether system for space applications includes at least one electron collector, at least one electron emitter, a power system, and at least one electrodynamic tether electrically coupled to the power system. The electrodynamic tether conducts electrical current between at least one electron collector and at least one electron emitter. Electric current and voltage are measured. Selected tether dynamics and electrodynamics based on the measured electric current and voltage are ascertained. The electric current and/or current distribution is adjusted to thereby control at least one tether system state based on the ascertained selected tether dynamics and electrodynamics.

Method for observing and stabilizing electrodynamic tethers

Apparatus for observing and stabilizing electrodynamic tethers

A disposable foil grill is disclosed which consists of a corrugated and perforated sheet of heavy duty aluminum foil. The corrugations allow smoke to access virtually the entire bottom surface of the food being cooked so that the desired barbecue flavor is obtained. Fat from meat being cooked drips into troughs formed by the corrugation and exits through holes in the troughs onto the coals for generation of the smoke and flame which give food a desireable barbecue flavor. Another advantage of the disclosed disposable grill cover is that the distances between adjacent troughs may be changed by a slight pull on the ends of the foils to perfectly align the troughs with the spacings between the wire grating of the grill. In this way, holes formed in the bottom of the troughs for fat drippings do not allow the drippings to come in contact with the wire grating.

Growing community of inventors

Minnetonka, MN, United States of America

Eugene Levin