Thermal interfaces or joints including stepped gaskets and/or shims therein and their methods of making and using are described herein.

Thermal interfaces or joints including stepped gaskets and/or shims therein and their methods of making and using are described herein.

A dielectric element for a resonator and a corresponding resonator are described. The dielectric element has a first chamber and a second chamber, which are fluidically connected to one another by a connecting channel. A liquid crystal is contained in the first chamber, a gas is contained in the second chamber. Changes in the volume of the liquid crystal can be compensated by a change in the volume of the gas, because the liquid crystal can move in the connecting channel. Consequently, such a resonator can be exposed to greatly fluctuating temperature ranges without requiring any further compensation for temperature-induced changes in the volume of the liquid crystal. The dielectric element can also be hermetically closed to complete the production process.

A dielectric element for a resonator and a corresponding resonator are described. The dielectric element has a first chamber and a second chamber, which are fluidically connected to one another by a connecting channel. A liquid crystal is contained in the first chamber, a gas is contained in the second chamber. Changes in the volume of the liquid crystal can be compensated by a change in the volume of the gas, because the liquid crystal can move in the connecting channel. Consequently, such a resonator can be exposed to greatly fluctuating temperature ranges without requiring any further compensation for temperature-induced changes in the volume of the liquid crystal. The dielectric element can also be hermetically closed to complete the production process.

A three-dimensional multi-shell insulation configured to conform to the shape of a spacecraft component to be insulated. The insulation may have a plurality of nested shell layers that are displaceable relative to each other for providing natural separation between the shell layers when the insulation is used in low-pressure and/or low-gravity space-related applications. To establish the spacing between shell layers, an edge clamp may be operatively coupled to an edge portion on at least one side of each shell layer. The shell layers may have sufficient flexibility and/or may be sufficiently displaceable relative to each other to allow the insulation to be installed or removed from the spacecraft component. One or more restraints may be provided in the space between the shell layers for restricting the relative lateral and/or transverse movement between shell layers for preventing contact. Additive manufacturing may be employed to fabricate the insulation and integrate features.

A three-dimensional multi-shell insulation configured to conform to the shape of a spacecraft component to be insulated. The insulation may have a plurality of nested shell layers that are displaceable relative to each other for providing natural separation between the shell layers when the insulation is used in low-pressure and/or low-gravity space-related applications. To establish the spacing between shell layers, an edge clamp may be operatively coupled to an edge portion on at least one side of each shell layer. The shell layers may have sufficient flexibility and/or may be sufficiently displaceable relative to each other to allow the insulation to be installed or removed from the spacecraft component. One or more restraints may be provided in the space between the shell layers for restricting the relative lateral and/or transverse movement between shell layers for preventing contact. Additive manufacturing may be employed to fabricate the insulation and integrate features.

Space vehicles with paraglider re-entry, and associated systems and methods are disclosed. A representative system includes a re-useable space vehicle, a collapsible, deployable and re-stowable re-entry heat shield carried by the space vehicle, and a collapsible, deployable and re-stowable flexible paraglider wing also carried by the space vehicle. The space vehicle can accordingly carry out repeated space-based missions, and can be refurbished and replenished on Earth and/or at an orbiting dock between missions.

Space vehicles with paraglider re-entry, and associated systems and methods are disclosed. A representative system includes a re-useable space vehicle, a collapsible, deployable and re-stowable re-entry heat shield carried by the space vehicle, and a collapsible, deployable and re-stowable flexible paraglider wing also carried by the space vehicle. The space vehicle can accordingly carry out repeated space-based missions, and can be refurbished and replenished on Earth and/or at an orbiting dock between missions.

A condensation-controlling insulation system includes an interior insulation layer for application to a cold surface. The system may further include an exterior absorption layer adapted to retain condensation during a first environmental condition and to release the condensation as a vapor during a second environmental condition.

A condensation-controlling insulation system includes an interior insulation layer for application to a cold surface. The system may further include an exterior absorption layer adapted to retain condensation during a first environmental condition and to release the condensation as a vapor during a second environmental condition.