A photovoltaic generator deployable for a satellite stabilized on three axes. The photovoltaic generator includes an assembly of planar panels articulated with respect to each other, and an attachment arm to the structure of the body of the satellite. In a first or launch position of the photovoltaic generator, the planar panels are folded one over the other. In a second or deployed position of the photovoltaic generator, the planar panels are fully deployed with at least a part of the planar panels being photovoltaic panels. At least one planar panel consists of a thermal radiator, with the radiative face thereof being orientated to be opposite the face of the photovoltaic panels carrying the photovoltaic sensors when the photovoltaic generator is in the deployed position. This radiative face is termed the shade face, and the face opposite the panel shaped radiator is termed the sun face.

A radiator comprising at least one heat conductive layer having an in-plane heat conductivity of at least 500 W/mK and at least one heat emission layer in contact with the heat conductive layer, wherein the emission layer has an exposed surface with an emissivity of at least 0.7. Preferably, the heat conductive layer comprises a carbon-based material. The radiator is to be used in combination with a space vehicle structure, and due to its flexible character may be conformed to the particular shapes of such structure.

Disclosed is a spacecraft including:a housing defining an inner space and an outer space, the housing having a first surface and a second surface opposite the first surface; a first radiator and a second radiator supported by the first surface and the second surface, respectively, the first radiator and the second radiator each having a main inner surface, a main outer surface opposite the main inner surface and side surfaces. The spacecraft further includes a first auxiliary radiator and a first auxiliary heat-transfer device thermally connecting the first auxiliary radiator to the main inner surface of the second radiator, the first auxiliary radiator being arranged in a first portion of the outer space, the first portion being defined by the main outer surface of the first radiator and by the first planes containing the side surfaces of the first radiator.

Disclosed is a heat exchange device for effecting a heat exchange between a heat transfer fluid of a first network of capillary heat pipes and a heat transfer fluid of a second network of capillary heat pipes. The heat exchange device includes a solid block provided with a first channel and a second channel which are independent of one another, the first channel having at least one opening intended to be connected to a capillary heat pipe of the first network, the second channel having at least one opening intended to be connected to a capillary heat pipe of the second network, the first channel having a portion which lies near a portion of the second channel such that the heat transfer fluid of the first network is able to exchange heat with the heat transfer fluid of the second network via the heat exchanging portions.

An apparatus includes a thermally conductive interface assembly including a first component associated with a first interface surface and a second component associated with a second interface surface. The apparatus also includes a shape memory alloy component coupled to the thermally conductive interface assembly and configured to move one or more components of the thermally conductive interface assembly between a first state and a second state based on a temperature of the shape memory alloy component. In the first state, the first interface surface is in physical contact with the second interface surface, and in the second state, a gap is defined between the first interface surface and the second interface surface.

A radiator, comprising at least one heat conductive layer with pyrolytic graphite material and an in-plane heat conductivity of at least 500 W/m.Math.K. The radiator further comprises at least one heat emission layer that is in contact with the heat conductive layer, wherein the emission layer has an exposed surface with an emissivity of at least 0.7. The radiator is to be used in combination with a space vehicle structure, and due to its flexible character may be conformed to the particular shapes of such structure.

A spacecraft includes a spacecraft main body, including payload equipment disposed on an inner panel surface of at least one radiator panel, the at least one radiator panel having an exterior-facing outer panel surface. The spacecraft includes at least one electric thruster disposed proximate to an aft facing panel of the spacecraft main body. The at least one electric thruster is thermally coupled with the at least one radiator panel by way of a thermally conductive path.

The invention relates to a spacecraft (1) comprising: a housing (2) defining an inner space and an outer space, the housing having a first surface and a second surface opposite the first surface, a first radiator (16) and a second radiator (18) supported by the first surface and the second surface, respectively, the first radiator (16) and the second radiator (18) each having a main inner surface, a main outer surface opposite the main inner surface and side surfaces (19).

The spacecraft (1) further comprises a first auxiliary radiator (32) and a first auxiliary heat-transfer device (34) thermally connecting said first auxiliary radiator (32) to the main inner surface of the second radiator (36), the first auxiliary radiator (18) being arranged in a first portion of the outer space (13), said first portion being defined by the main outer surface of the first radiator and by the first planes (48, 50, 52, 54) containing the side surfaces (19) of the first radiator.

Systems, methods, and apparatus for dual condenser loop heat pipes for satellites with sun-normal radiators are disclosed. In one or more embodiments, a disclosed method for a satellite thermal management system comprises heating, in an evaporator, a liquid to convert the liquid to a vapor. The method further comprises passively circulating within tubing, from the evaporator, the vapor to a first radiator not illuminated by a sun and to a second radiator illuminated by the sun. Also, the method comprises converting the vapor to the liquid when the vapor is within the first radiator not illuminated by the sun. Further, the method comprises passively circulating within the tubing, from the first radiator not illuminated by the sun, the liquid to the evaporator.

Composite heat pipes, methods of assembling composite heat pipes, sandwich panels having one or more composite heat pipes, methods of assembling sandwich panels, radiator panels, methods of assembling radiator panels, spacecraft, and methods of assembling spacecraft are disclosed. Composite heat pipes include an elongate conductive casing and one or more fiber reinforced composite layers operatively coupled to one or more lateral sides of the elongate conductive casing. Sandwich panels include two spaced-apart face-sheets, a core positioned between the two spaced-apart face-sheets, and one or more composite heat pipes. Spacecraft include a body and two radiator panels operatively coupled to the body opposite each other.