Negative-stiffness-producing mechanisms can be incorporated with structural devices that are used on spacecraft that provide thermal coupling between a vibrating source and a vibration-sensitive object. Negative-stiffness-producing mechanisms can be associated with a flexible conductive link (FCL) or “thermal strap” or “cold strap” to reduce the positive stiffness of the FCL. The negative-stiffness-producing mechanisms can be loaded so as to create negative stiffness that will reduce or negate the natural positive stiffness inherent with the FCL. The FCL will still be able to provide maximum thermal conductance while achieving low or near-zero stiffness to maximize structural decoupling.

A cryocooler includes a second-stage cooling stage, a second cylinder which includes the second-stage cooling stage on a terminal of the second-stage cylinder, a second-stage displacer which includes a magnetic regenerator material and is accommodated in the second-stage cylinder so as to be able to reciprocate in the second-stage cylinder, and a tubular magnetic shield which is installed on the second-stage cooling stage and extends along the second-stage cylinder outside the second-stage cylinder. The magnetic shield is formed of a normal conductor and a product of an electrical conductivity in a temperature range of 10 K (Kelvin) or less and a thickness of the tubular magnetic shield is 60 MS (Mega-Siemens) to 1980 MS.

A refrigerated cargo container includes a cargo container and a refrigeration unit. A plurality of refrigerant tubes are in fluid communication with the refrigeration unit and extend along a roof of the cargo container. The plurality of refrigeration tubes are configured to convey refrigerant there through and cool an interior of the cargo container via natural convection and thermal radiation. A method of cooling a cargo in a cargo container includes flowing a refrigerant through a plurality of refrigerant tubes disposed at a roof of the cargo container. Thermal energy is transferred from container air in the container to the refrigerant thereby cooling the container air. The container air is circulated via natural convection toward the cargo thereby cooling the cargo via thermal energy transfer to the container air. The container air is recirculated toward the plurality of refrigerant tubes.

A preconditioned air unit for supplying preconditioned air to an aircraft parked on the ground, the preconditioned air unit comprising a housing accommodating a flow duct with an air inlet for ambient air and an air outlet for connection to the parked aircraft, a blower connected with the flow duct for generation of an air flow from the air inlet toward the air outlet, at least one refrigeration system, each of which includes at least one compressor, at least one condenser, at least one expansion valve, and at least one evaporator connected in a flow circuit containing a refrigerant, and wherein the at least one evaporator interacts with the air flow in the flow duct, and at least one variable frequency driver for power supply of at least one of the at least one compressor of the at least one refrigeration system.

A magnetic resonance apparatus has a magnet unit that includes at least one superconducting basic magnetic field coil, a magnet housing unit surrounding the at least one superconducting basic magnetic field coil, a cooling system that has at least one cooling loop and a heat absorption unit to cool the at least one superconducting basic magnetic coil, and an additional unit. The cooling system has a switching unit with at least one first cooling mode, and the switching unit couples the at least one cooling loop of the cooling system with the additional unit for a heat exchange in the first cooling mode.

In this invention, vibrations generated by a freezer from a cooling mechanism for cooling an ion source emitter tip are prevented from being transmitted to the emitter tip as much as possible, while the cooling capability of the cooling mechanism is improved widely. The ion beam device (10) is equipped with: an ion source housing (22) provided with an emitter tip (45) and defining an ion source chamber (27) supplied with an ionization gas or gas molecules; a gas pot (51) provided in the ion source chamber (27) so as to be thermally connected to the emitter tip (45) and accommodated so as to have no direct physical contact with a cooling stage (57) of a freezer (52); and a spacer (59) provided on the peripheral surface of the cooling stage (57) housed by the gas pot (51) and maintaining a given interval or greater between the peripheral surface of the cooling stage (57) and the internal peripheral surface of the gas pot (52).

Variable temperature analytical instrument heat exchanger components are provided that can include a conduit in thermal communication with at least one thermally discrete mass, the discrete mass being configured as a cold source to be coupled to a member to facilitate the transfer of thermal energy. Variable temperature analytical instrument components are also provided that can include: a first mass to be maintained at a first temperature; a first conduit in fluid communication with the first mass; and a second mass thermally connected to the first conduit, the second mass having a different temperature than the first mass. Methods for varying the temperature within variable temperature analytical instruments are also provided. The methods can include thermally coupling at least a portion of an exhaust fluid conduit with a first mass and using the first mass as a cold source.

Variable temperature analytical instrument heat exchanger components are provided that can include a conduit in thermal communication with at least one thermally discrete mass, the discrete mass being configured as a cold source to be coupled to a member to facilitate the transfer of thermal energy. Variable temperature analytical instrument components are also provided that can include: a first mass to be maintained at a first temperature; a first conduit in fluid communication with the first mass; and a second mass thermally connected to the first conduit, the second mass having a different temperature than the first mass. Methods for varying the temperature within variable temperature analytical instruments are also provided. The methods can include thermally coupling at least a portion of an exhaust fluid conduit with a first mass and using the first mass as a cold source.

A vacuum adiabatic body includes: a first plate member defining at least one portion of a wall for a first space; a second plate member defining at least one portion of a wall for a second space having a different temperature from the first space; a sealing part sealing the first plate member and the second plate member to provide a third space that has a temperature between the temperature of the first space and the temperature of the second space and is in a vacuum state; a supporting unit maintaining the third space; a heat resistance unit for decreasing a heat transfer amount between the first plate member and the second plate member; an exhaust port through which a gas in the third space is exhausted; a side frame provided at an edge portion of the third space, the side frame having at least one portion defining a wall for the third space; and a peripheral frame fixed to the side frame to have a part mounted thereto. Accordingly, each part of the vacuum adiabatic body can be mounted without any interference, and an adiabatic effect can be improved.

A cooling unit has a cold plate extending in a horizontal direction, and a tank and a pump disposed above the cold plate in a first direction perpendicular to the horizontal direction. The tank has a tank chamber which stores a refrigerant. The pump has a pump chamber in which a rotating body that transfers the refrigerant is accommodated, and an upper end of the tank chamber in the first direction is positioned at an upper side than an upper end of the pump chamber in the first direction.