Tether Applications, Inc.

Other

USA As Represented by Secretary of the Navy

United States of America As Represented by the Administrator of Nasa

J.s.t. Corporation

Star Technology and Research, Inc.

Baseload Energy, Inc.

Joseph A Carroll

Eugene Levin

Ming-ta S Hsu

Daniel J Rasky

Paul Oppenheimer

Jerome Pearson

Huy K Tran

Adam Thurn

Jordan R Schlater

Shannon Coffey

Ivan Galysh

Christine E Szalai

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 power generation system including an airborne electricity generator, a tether assembly configured to carry electricity from the generator to land, the tether assembly having a first end portion coupled to the generator, and a winch assembly configured to reel the tether assembly onto a drum, wherein the winch assembly is configured to apply a reel tension to the tether assembly reeled onto the drum that is lower than a tension in the first end portion of the tether assembly.

Tether handling for airborne electricity generators

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

A power generation system () including an airborne electricity generator (), a tether assembly () configured to carry electricity from the generator to land, the tether assembly having a first end portion () coupled to the generator, and a winch assembly () configured to reel the tether assembly onto a drum (), wherein the winch assembly is configured to apply a reel tension to the tether assembly reeled onto the drum that is lower than a tension in the first end portion of the tether assembly.

A low density organic polymer impregnated preformed fibrous ceramic article includes a plurality of layers. A front layer includes ceramic fibers or carbon fibers or combinations of ceramic fibers and carbon fibers, and is impregnated with an effective amount of at least one organic polymer. A middle layer includes polymer impregnated ceramic fibers. A back layer includes ceramic fibers or carbon fibers or combinations of ceramic fibers and carbon fibers, and is impregnated with an effective amount of at least one low temperature pyrolyzing organic polymer capable of decomposing without depositing residues.

Secondary polymer layered impregnated tile

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.

Growing community of inventors

Chula Vista, CA, United States of America

Joseph A Carroll