A support structure for a spacecraft is disclosed having a first side wall, a second side wall which is parallel to and opposite the first side wall, a third side wall attached to at least the first side wall, and a fourth side wall which is parallel to and opposite the third side wall; at least one interior panel attached between and perpendicular to the first side wall and to the second side wall, at least one first thermal coupling device bearing against the second side wall and attached to the interior panel, electronic devices arranged on and in direct thermal contact with at least a portion of the first thermal coupling device.

A high efficiency satellite transmitter comprises an RF amplifier chip in thermal contact with a radiant cooling element via a heat conducting element. The RF amplifier chip comprises an active layer disposed on a high thermal conductivity substrate having a thermal conductivity greater than about 1000 W/mK, maximizing heat conduction out of the RF amplifier chip and ultimately into outer space when the chip is operating within a satellite under normal transmission conditions. In one embodiment, the active layer comprises materials selected from the group consisting of GaN, InGaN, AlGaN, and InGaAlN alloys. In one embodiment, the high thermal conductivity substrate comprises synthetic diamond.

A high efficiency satellite transmitter comprises an RF amplifier chip in thermal contact with a radiant cooling element via a heat conducting element. The RF amplifier chip comprises an active layer disposed on a high thermal conductivity substrate having a thermal conductivity greater than about 1000 W/mK, maximizing heat conduction out of the RF amplifier chip and ultimately into outer space when the chip is operating within a satellite under normal transmission conditions. In one embodiment, the active layer comprises materials selected from the group consisting of GaN, InGaN, AlGaN, and InGaAlN alloys. In one embodiment, the high thermal conductivity substrate comprises synthetic diamond.

An example of a satellite includes a first radiator panel, a second radiator panel, a space defined between the first radiator panel and the second radiator panel, and one or more first heat-generating components located in the space. Each of the first heat-generating components is attached to at least one of the first or second radiator panels. The satellite further includes a third radiator panel extending from the space and one or more second heat-generating components located in the space, each of the second heat-generating components is attached to the third radiator panel.

A heat storage device including a metal layer containing a protrusion-and-recess-shaped object, in which the protrusion-and-recess-shaped object has an average height of 100 nm or more and 1,000 nm or less.

A heat storage device including a metal layer containing a protrusion-and-recess-shaped object, in which the protrusion-and-recess-shaped object has an average height of 100 nm or more and 1,000 nm or less.

A passenger cabin air distribution system includes a ventilation system and an ejector-diffuser. The ventilation system is operable to provide a conditioned air. The ejector-diffuser is positioned to receive a flow of the conditioned air from the ventilation system. The ejector-diffuser includes an induction unit and a diffuser section. The induction unit includes a secondary inlet in communication with a cabin air from a passenger cabin and is configured to mix the flow of the conditioned air with an induced flow of the cabin air into a mixed air. The diffuser section includes a discharge to eject the mixed air to the passenger cabin. The diffuser section is shaped to provide for efficient mixing with low backpressure in order to maintain the low motive pressure in the nozzle.

The present invention relates to a solar panel to which a high-damping stacked reinforcement part is applied and, more specifically, to a solar panel to which a high-damping stacked reinforcement part is applied, comprising: a power generation unit for generating electrical energy; a coupling part to which the power generation unit is coupled, and which has a circuit formed therein; and a reinforcement part for reinforcing the rigidity of the coupling part and damping vibration to be transmitted, and thus the present invention can prevent the power generation unit from being damaged by vibration, or the solar panel from inducing wobbling of a satellite by failing to damp the vibration.

A thermal management system adapted to vent a two-phase working fluid into an environment having a higher pressure than a vapor pressure of a working fluid corresponding to a set point of the system including a secondary vessel containing a secondary species. The system includes a primary vessel containing the working fluid and the secondary species, and at least one valve to selectively control venting of a mixture of the working fluid and the secondary species from the primary vessel to the environment. The system includes at least one valve connected between the primary vessel and the secondary vessel to selectively control charging of the secondary species into the primary vessel.

A thermal management system adapted to vent a two-phase working fluid into an environment having a higher pressure than a vapor pressure of a working fluid corresponding to a set point of the system including a secondary vessel containing a secondary species. The system includes a primary vessel containing the working fluid and the secondary species, and at least one valve to selectively control venting of a mixture of the working fluid and the secondary species from the primary vessel to the environment. The system includes at least one valve connected between the primary vessel and the secondary vessel to selectively control charging of the secondary species into the primary vessel.